NASA SP-7037(39) AERONAUTICAL ENGINEERING A SPECIAL BIBLIOGRAPHY WITH INDEXES Supplement 39 JANUARY 1974 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION https://ntrs.nasa.gov/search.jsp?R=19740013517 2020-03-23T09:33:16+00:00Z ACCESSION N U M B E R RANGES Accession numbers cited in this Supplement fa l l w i th in the fol lowing ranges: IAA (A-10000 Series) A73-43 191—A73-45560 STAR (N-10000 Series) N73-31925—N73-33931 This bibliography was prepared by the NASA Scientific and Technical In fo rmat ion Facility operated for the Nat ional Aeronautics and Space Adminis t ra t ion by Informat ics Tisco, Inc. The Administrator of the National Aeronautics and Space Administration has determined that the publication of this periodical is necessary in the transaction of the public business required by law of this Agency. Use of funds for pr in t ing this periodical has been approved by the Director of the Office of Management and Budget through July I, 1974. NASA SP-7037 (39) AERONAUTICAL ENGINEERING A Special Bibliography Supplement 39 A selection of annotated references to unclas- sified reports and journal articles that were introduced into the NASA scientific and tech- nical information system and announced in December 1973 in • Scientific and Technical Aerospace Reports (STAR) • International Aerospace Abstracts (IAA). Scientific and Technical Information Of/ice JANUARY 1974 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION Washington. D.C. This Supplement is available from the National Technical Information Service (NTIS), Springfield, Virginia 22151,for $3.00. For copies mailed to addresses outside the United States, add $2.50 per copy for handling and postage. INTRODUCTION Under the terms of an interagency agreement with the Federal Aviation Administra- tion this publication has been prepared by the National Aeronautics and Space Administra- tion for the joint use of both agencies and the scientific and technical community concerned with the field of aeronautical engineering. The first issue of this bibliography was published in September 1970 and the first supplement in January 1971. Since that time, monthly sup- plements have been issued. This supplement to Aeronautical Engineering—A Special Bibliography (NASA SP-7037) lists 417 reports, journal articles, and other documents originally announced in December 1973 in Scientific and Technical Aerospace Report* I STAR I or in International Aerospace Abstracts 11A A}. The coverage includes documents on the engineering and theoretical aspects of design, construction, evaluation, testing, operation, and performance of aircraft (including aircraft engines) and associated components, equipment, and systems. It also includes research and development in aerodynamics, aeronautics, and ground support equipment for aero- nautical vehicles. Each entry in the bibliography consists of a standard bibliographic citation accompanied in most cases by an abstract. The listing of the entries is arranged in two major sections, IA A Entries and STAR Entries in that order. The citations, and abstracts when available, are reproduced exactly as they appeared originally'.in IAA or STAR, including the original accession numbers from the respective announcement journals. This procedure, which saves time and money, accounts for the slight variation in citation appearances. Three indexes—subject, personal author, and contract number—are included. An annual cumulative index will be published. A V A I L A B I L I T Y OF CITED PUBLICATIONS IAA ENTRIES (A73-10000 Series) All publications abstracted in this Section are available from the Technical Information Service. American Institute of Aeronautics and Astronautics. Inc.. IAIAA). as follows: Paper copies are available at $5 00 per document up to a maximum of 20 pages. The charge for each additional page is 25 cents Microfiche'"are available at the rate of $100 per microfiche for documents identified by the j symbol following the accession number A number of publications, because of their special characteristics, are available only for reference in the AIAA Technical Information Service Library Minimum airmail postage to foreign countries is $1 00 Please refer to the accession number, e.g.. A73-10468. when requesting publications. STAR ENTRIES (N73-10000 Series) A source from which a publication abstracted in this Section is available to the public is ordinarily given on the last line of the citation, e.g.. Avail: NTIS. The following are the most commonly indicated sources (full addresses of these organizations are listed at the end of this introduction): Avail: NTIS. Sold by the National Technical Information Service at the price shown in the citation. If no price is shown in a current STAR citation, it may be ascertained by referring to Government Reports Announcements or to NTIS. Beginning with documents announced in Issue 21. 1973. "stocked" reports, such as printed NASA reports are priced on a step schedule ranging irregularly from $2.75 for a 1-to-25 page report to $10.75 for 576 to 600 pages, plus $2.00 for each additional 100-page increment. Demand print reports (those for which a facsimile reproduction will be made to fill orders) are priced at $3.00 for the first 20 pages plus 25 cents for each five pages or portions thereof. These prices are not applied retroactively; i.e., reports previously announced at a certain price continue to be sold at that price. If "Avail: NTIS" without a price appeared in the citation of a NASA report (asterisked) it is sold at $3.00 whether printed copy or facsimile is supplied. Because of price changes and possible surcharges, it is recommended that for any document announced in STAR before July 1970. NTIS be queried as to the price. Document prices are subject to change without notice. See "Avail: SOD" below for documents available from both the Superintendent of Documents and NTIS. Microfiche. Microfiche is available from NTIS at a standard price of $1.4 5 (regardless of age) for those documents identified by the # sign following the accession number (e.g., N73-10281$) and having an NTIS availability shown in the citation. Standing orders for microfiche of (1) the full collection of NTIS-available documents announced in STAR with the # symbol. (2) NASA reports only (ident- ified by an asterisk (*)), (3) NASA-accessioned non-NASA reports only (for those who wish to maintain an integrated microfiche file of aerospace documents by the "N" accession number), or (4) any of these classes within one or more STAR categories, also may be placed with NTIS at greatly reduced prices per title (e.g., 45 cents) over individual requests. Inquiries concerning NTIS Selective Categories (DA microfiche is a tcansparent sheet of film. 105 x 148 mm in size, containing as many as 60 to 98 pages of information reduced to micro images (not to exceed 24:1 reduction). in Microfiche should be addressed to the Subscription Unit. National Technical Information Service. Deposit Accounts and Customers Outside U.S. NTIS encourages its customers to open deposit accounts to facilitate the purchase of its documents now that prices vary so greatly. NTIS customers outside the United States are reminded that they should add the following handling and postage charges to the standard or announced prices: hard (paper) copy. $2.50 each document, microfiche. $1.50 each document. For subscribers outside the United States who receive microfiche through the Selective Categories in Microfiche program. NTIS will add 15''cents for each title shipped. Avail. SOD (or GPO) Sold by the Superintendent of Documents. U.S. Government Printing Office, in hard copy. The price is given following the availability line. (An order received by NTIS for one of these documents will be filled at the SOO price if hard copy is requested. NTIS will also fill microfiche requests, at the standard $1.45 price, for those documents identified by a jsymbol.) Avail: NASA Public Document Rooms. Documents so indicated may be examined at or purchased from the National Aeronautics and Space Administration. Public Documents Room (Room 126). 600 Independence Ave. S.W.. Washington. D.C. 20546. or public document rooms located at each of the NASA research centers, the Mississippi Test Facility, and the NASA Pasadena Office at the Jet Propulsion Laboratory. Avail: NASA Scientific and Technical Information Office. Documents with this availability are usually news releases or informational brochures available without charge in paper copy. Avail: AEC Depository Libraries. Organizations in U.S. cities and abroad that maintain collections of U.S. Atomic Energy Commission reports, usually in microfiche form, are listed in Nuclear Science Abstracts. Services available from the USAEC and its depositories are described in a booklet. Science Information Available from the Atomic Energy Commission (TID-4550). which may be obtained without charge from the USAEC Technical Information Center. Avail: Univ. Microfilms Documents so indicated are dissertations selected from Dissertation Abstracts, and are sold by University Microfilms as xerographic copy (HO at $10.00 each and microfilm at $4.00 each, regardless of the length of the manuscript. Handling and shipping charges are additional. All requests should cite the author and the Order Number as they appear in the citation. Avail: HMSO Publications of Her Majesty's Stationery Office are sold in the U.S. by Pendragon House. Inc.. (PHI). Redwood City. California. The U.S. price (including a service charge) is given, or a conversion table may be obtained from PHI. Avail: BLL (formerly NLL): British Library Lending Division, Boston Spa, Wetherby, York- shire, England. Photocopies available from this organization at the price shown (If none is given, inquiry should be addressed to BLL). Avail: ZLDI Sold by the Zentralstelle fur Luftfahrtdokumentation und -Information. Munich. Federal Republic of Germany, at the price shown in deutschmarks (DM). Avail: Issuing Activity, or Corporate Author, or no indication of availability: Inquiries as to the availability of these documents should be addressed to the organization shown in the citation as the corporate author of the document. Avail: U.S. Patent Office. Sold by Commissioner of Patents. U.S. Patent Office, at the standard price of $.50 each, postage free. Other availabilities: If the publication is available from a source other than the above, the publisher and his address will be displayed entirely on the availability line or in combination with the corporate author line. GENERAL AVAILABILITY All publications abstracted in this bibliography are available to the public through the sources as indicated in the STAR Entries and IAA Entries sections. It is suggested that the bibliog- raphy user contact his own library or other local libraries prior to ordering any publication inasmuch as many of the documents have been widely distributed by the issuing agencies, especially NASA. A listing of public collections of NASA documents is included on the inside back cover. SUBSCRIPTION AVAILABILITY This publication is available on subscription from the National Technical Information Service (NTIS). The annual subscription rate for the monthly supplements, excluding the annual cumulative index, is $18.00. All questions relating to subscriptions should be referred to the NTIS ADDRESSES OF ORGANIZATIONS American Institute of Aeronautics and Astronautics Technical Information Service 750ThirdAve. New York. N.Y. 10017 British Library Lending Division. Boston Spa. Wetherby. Yorkshire. England Commissioner of Patents U.S. Patent Office Washington. D.C. 20231 Engineering Sciences Data Unit Ltd. 251-259 Regent Street London W1R 7AD. England ESRO/ELDO Space Documentation Service European Space Research Organization 114. av. Charles de Gaulle 92-Neuilly-sur-Seine. France Her Majesty's Stationery Office P 0. Box 569. S.E. 1 London. England NASA Scientific and Technical Information Facility P.O. Box 33 College Park. Maryland 20740 National Technical Information Service Springfield. Virginia 22151 Pendragon House. Inc. 899 Broadway Avenue Redwood City. California 94063 Superintendent of Documents U.S. Government Printing Office Washington. D.C. 20402 University Microfilms. Inc. A Xerox Company 300 North Zeeb Road Ann Arbor. Michigan 48106 University Microfilms, Inc. Tylers Green London. England U.S. Atomic Energy Commission Technical Information Center P 0 Box 62 Oak Ridge. Tennessee 37830 Zentralstelle fur Luftfahrtdoku- mentation und-lnformation 8 Munchen86 Postfach 880 Federal Republic of Germany National Aeronautics and Space Administration Scientific and Technical Information Office (KSI) Washington. D.C. 20546 TABLE OF CONTENTS IAA Entries.. STAR Entries Page .621 .637 Subject Index ..................................... Personal Author Index ............................ Contract Number Index ................................... Q.. B_.j TYPICAL CITATION AND ABSTRACT FROM STAR NASA SPONSORED ACCESSION NUMB! TITLE AUTHORS OR GRANT NUMBER H THE SIMULATION OF A JUMBO JET TRANSPORT 1 — •» AIRCRAFT. VOLUME 2: MODELING DATA J i-v C. Rodney Hanke and Donald R. Nordwall Sep. J970 506 p _J 2 Vol. ^ , ^ (Contract NAS2-5S24) I ^(NASA-CR-1 14494; D6-30643-Vol-2) Avail: NTIS^HC $27 50 1 The manned simulation of a large transport aircraft i» J described. Aircraft and systems data necessary to implement the mathematical model described in Volume 1 and a discussion of how these data are used in model are presented. The results of the real-time computations in the NASA Ames Research Center Flight Simulator for Advanced Aircraft are shown and comoared to flight test data and to the results obtained in a training simulator known to be satisfactory. Author AVAILABLE ON SOURCE DATE SOURCE CODE TYPICAL CITATION AND ABSTRACT FROM IAA NASA SPONSORED DOCUMENT ACCESSION- NUMBER AUTHORS -»-A73-10302 * // Optimum configurations for banglets sonic booms. W. D^Hayes and F. B. Weiskope. Jr. (Princeton University. Princeton, NJ.I. Quarterly of Applied Mathematics, vol. 30. Oct. 1972. p. 311-328. 13 refs. Grant No. NGL 31-001-119. A number of optimization problems are posed and solved for supersonic aircraft flight subject to the condition that a shock wave appears only incipiently in the sonic boom signal at a given point. The principal result is one giving the maximum effective gross weight of an aircraft of given effective length under given flight conditions. The calculus of variations with inequality constraints is used, with the novel Matures of a non-local isoperimetric relation and of only an upper bound on a control variable. (Author) AVAILABLE ON ' MICROFICHE •TITLE AUTHORS' AFFILIATION PUBLICATION DATE VIII AERONAUTICAL ENGINEERING A Spec/a/ Bibliography (Suppl. 39) JANUARY 1974 IAA ENTRIES A73-43205 H A note on the flow in a trailing vortex. K. K. Tarn. Journal of Engineering Mathematics, vol. 7, Jan. 1973, p. 1 -6. 7 refs. National Research Council of Canada Grant No. A-5228. It is shown that if the equations governing the fluid motion in a trailing vortex are linearized, as was done by Batchelor, more than one solution can be constructed. Within the framework of the linear theory, there is no criterion to determine which solution is to be used. To clarify the situation, the Navier-Stokes equations are formulated in parabolic coordinates, and asymptotic solutions are sought which are valid far downstream. By insisting that the interaction of the swirl with the uniform stream be a first-order effect, the first two terms in the asymptotic expansions for the Stokes stream function and the angular momentun are obtained. The result thus obtained differs from that given by Batchelor in that the axial velocity defect decays algebraically. (Author) A73-43210 # On the application of a new version of lifting surface theory to nonslender and kinked wings. T. E. Labrujere (Nationaal Luchtvaartlaboratorium, Amsterdam, Netherlands) and P. J. Zandbergen (Technische Hogeschool Twente, Enschede, Nether- lands). Journal of Engineering Mathematics, vol. 7, Jan. 1973, p. 85-96. Results of a determination of the characteristics of thin wings in subsonic flow by a new elaborate method. Attention is paid to the rate of convergence of the numerical solutions, especially with respect to the number of collocation points. Two rectangular wings have been treated in order to examine the influence of the aspect ratio. The influence of the rounding of a kink is demonstrated by means of a series of constant-chord wings with hyperbolic edges. (Author) A73-43263 ft Glide modes in problem] with a conflict situation (Skol'ziashchie rezhimy v zadachakh \ konfliktnoi si- tuztsiei). E. V. Kuzin. In: Studies of spacecraft flight dynamics. Moscow, Izdatel'stvo Nauka, 1973, p. 33-43. 5 refs. In Russian. The necessary conditions for the existence of an optimal control on a set of glide modes are formulated. The optimality conditions obtained are extended to cover problems with a conflict situation. V.P. A73-43277 Sensitivity, adaptivity and optimality; Pro- ceedings of the Third Symposium, Ischia, Italy, June 18-23, 1973. Sponsored by the International Federation of Automatic Control, Consiglio Nazionale delle Ricerche, and Associazione Nazionale Italiana per I'Automazione. Edited by G. Guardabassi, A. Locatelli, and _S. Rinaldi IMilano, Politecnico, Milan, Italy). Dusseldorf, International Federation of Automatic Control; Pittsburgh, Instru- ment Society of America, 1973.462 p. $25. Topics discussed include model reference adaptive techniques, sensitivity and covariance matrices for performance estimation, the effect of feedback control on trajectory sensitivity, the use of the state-space and transfer-function concepts in the design of linear multivariable systems, the synthesis of feedback systems which minimize the effect of sensor white noise at the plant input, the synthesis of parameter- and state-insensitive feedback systems, automatic aircraft landing control, the sensitivity of optimal control systems, the design of adaptive models for real-time identification, the design of discrete model reference adaptive systems, the design of multivariable adaptive models, the synthesis of a two-level controller for linear plants, and the effect of structural perturbations on large-scale dynamic systems. A.8.K. A73-43284 Optimal landing flare control of aircraft) with sensitivity consideration. H. Ohta and I. Sugiura (Nagoya University, Nagoya, Japan). In: Sensitivity, adaptivity and optimality; Proceed- ings of the Third Symposium, Ischia, Italy, June 18-23, 1973. Dusseldorf, International Federation of Auto- matic Control; Pittsburgh, Instrument Society of America, 1973, p. 251-259. 8 refs. Theoretical synthesis of an automatic closed-loop optimal landing flare control system characterized by reduced sensitivity. The reduced sensitivity system shows excellent responsiveness to flight velocity and mass parameter variations. Further theoretical and experimental studies are necessary for putting the obtained results into practice. M.V.E. A73-43288 Design of multivariable adaptive model follow- ing control systems. I. D. Landau and B. Courtiol (Societe Generate de Constructions Electriques et Mecaniques Alsthom, Grenoble, France). In: Sensitivity, adaptivity and optimality; Proceedings of the Third Symposium, Ischia, Italy, June 18-23, 1973. Dusseldorf, International Federation of Automatic Control; Pittsburgh, Instrument Society of America, 1973, p. 315-322. 5 refs. Research supported by the Delegation Generate a la Recherche Scientif ique et Technique. The results for the problems of perfect model following and hyperstability of model reference adaptive systems are integrated in order to develop a general design method for multivariable adaptive model following control systems. Two types of adaptation are involved: adaptation of the parameters of the control loop and signal synthesis adaptation for model following control systems with a fixed structure. The design and the implementation of the adaptation mechanism based on the use of a hyperstable adaptation algorithm are discussed. The feasibility and the advantages of the procedure are illustrated by applying it to a nontrivial aircraft control problem. (Author) A73-43296 The effect of variable environment tempera- ture on heat transfer in extended surfaces. 0. Pnueli (Technion - Israel Institute of Technology, Haifa, Israel). I Israel Conference on 621 A73-43327 Mechanical Engineering, 7th, Haifa, Israel, June 27, 28, 1973.1 Israel Journal of Technology, vol. 11, no. 4,1973, p. 233-235. Extended surfaces appear as structural members in aircraft. These fin-like parts are subjected to temperatures which can be well above those considered safe. Heat transfer analysis must yield the temperatures which are actually reached by these members. Because modern aircraft design cannot allow for large safety factors, the thermal analysis must be rather accurate, therefore, a general solution for heat transfer in fins with variable environment tempera- tures is presented. It is generalized to include variable .convection coefficients. Two examples are also presented. (Author) A73-43327 Emissions from and within an Allison J-33 combustor. II - The effect of inlet air temperature. J. H. Tuttle, R. A. Altenkirch, and A. M. Mellor (Purdue University, West Lafayette, Ind.). Combustion Science and Technology, vol. 7, no. 3, 1973, p. 125-134. 10 refs. Environmental Protection Agency Grant No. R-801284. A model of the flow pattern within an Allison J-33 combustor using unheated inlet air was previously postulated (Mellor et al., 1972), based on internal measurements. Additional data consistent with the postulated flow model were obtained from the same combustor using heated inlet air at near design conditions. Profiles of gas temperature, carbon monoxide, unburned hydrocarbons, and nitric oxide concentrations are reported as a function of axial and radial position inside the combustor. Combustor exit-plane pollutant concentrations are also reported; specifically, the effects of com- bustor pressure, overall equivalence ratio, air flow rate, and inlet air temperati"-.. were investigated. (Author) A73-43385 Response of glass-fiber-reinforced epoxy speci- mens to high rates of tensile loading. A. E. Armenakas (Brooklyn, Polytechnic institute, Brooklyn, N.Y.) and C. A. Sciammarella (Illinois Institute of Technology, Chicago, III.). Experimental Me- chanics, vol. 13, Oct. 1973, p. 433-440. 11 refs. Contract No. F33615-71-C-1533. petroleum fuel) flowing at 0.5 m/sec. The test temperature was 20 C and the usable length 100 mm. It is shown that the fatigue strength in pure bending of aircraft aluminum 2-mm sheet samples exposed to the magnetized medium was greater than in the absence of a,, magnetic field. .. V-P... , A73-43493 // Closing the air transport gap on intermodal containers. J. L. Weingarten (USAF, Aeronautical Systems Div., Wright-Patterson AFB, Ohio). Intersociety Conference on Trans- portation. 2nd, Denver, Colo., Sept. 23-27, 1973, ASME Paper 73-ICT-30. 8 p. 7 refs. Members, $1.00; nonmembers, $3.00. The intermodal container today is still limited to movement by land and sea. The United States Air Force is currently working to close this gap and provide true intermodality. A three-prong approach is underway to determine capabilities and limitations of air movement of containers. This includes a major revision of air transportability concepts, testing of current land-sea containers to determine air movement procedures, and design and development of tri-mode containers. Much of the results of these efforts will help mold air cargo movement of the future. (Author) A73-43494 # Economics of airport system planning. J. A. Neiss (Aerospace Corp., Los Angeles, Calif.). Intersociety Conference on Transportation, 2nd, Denver, Colo., Sept 23-27, 1973, ASME Paper 73-ICT-33. 8 p. Members, $1.00; nonmembers, $3.00. . An airport system plan generally defines the developmental needs and requirements that are necessary to meet five-, ten-, and twenty-year aeronautical activity forecasts. Unfortunately, these system plans do not adequately address or meet the current1 economic needs of many of the nation's airports with respect to economics of operation, ownership, and finance. An analysis is made of the economics of airport operation, ownership, and finance, and the economic criteria that should be integrated into airport system planning to produce a viable plan are indicated. (Author) A73-43396 A study of a fluidic open loop damping flight stability augmentation syitem. F. Holoubek (Royal Aircraft Estab- lishment, Farnborough, Hants., England). In: Cranfield Fluidics Conference, 5th, Uppsala, Sweden, June 13-16, 1972, Proceedings. Volume 1. Cranfield, Beds., England, British Hydromechanics Research Association, 1973, p. C3-49 to C3-68. 7 refs. The ideas underlying the open loop damping method of stability augmentation for flight attitude control systems, its parametric design, and laboratory performance testing are described. The use of conventional response rate feedback, requiring some form of a rate gyroscope, is obviated, in a feed-forward manner, by operating on the demand signal by means of shaping network in such a way as to achieve a system response identical or similar to that realised by the application of rate feedback. The obvious advantage of such an arrangement is the absence of the need of any differentiation,'which is here replaced by relatively easier time integration (lead-lag RC networks). The paper outlines the derivation of a suitable shaping function and the calculation of the necessary gains and'time constants. (Author) A73-43466 # Improvement of the corrosion-fatigue ftrangth of aluminum alloys by exposure of the medium to a magnetic field (Povythenia korrozionno-ustalostnoi prochnosti aliuminievogo tplava pri obrabotke sredy magnitnym polem). A. V. Karlashov and I.I. Priakhin (Kievskii Institut Inzhenerov Grazhdanskoi Aviatsii, Kiev, Ukrainian SSR). Fiziko-Khimicheskaia Mekhanika Materialov, vol. 9, no. 4, 1973, p. 23-26. 7 refs. In Russian. A 7000-Oe unipolar constant magnetic field was applied to corrosive media (3% aqueous solution of NaCI, fresh water, and a A73-43495 # Reducing the threat of mid-air collisions. T. M. Johnston (FAA, Technical Programs Div., Washington, D.C.). Inter- society Conference on Transportation, 2nd, Denver, Colo., Sept. 23-27, 1973, ASME Paper 73-ICT-49. 7 p. Members, $1.00; nonmembers, $3.00. ' A much discussed but poorly understood problem, associated with air travel, is the threat of midair collision by the ever-increasing number of planes utilizing the air space over the United States. This problem is put in the proper perspective, and current efforts by Government and industry to advance the state-of-the-art in collision avoidance systems and to develop a timely solution to the midair collision problem are discussed. . (Author) A73-43496 # Dual lane runway issues. J. C. Koegler (MIT, Lexington, Mass.). Intersociety Conference on Transportation, 2nd. Denver, Colo., Sept 23-27, 1973, ASME Paper 73-ICT-61. 13 p. 5 refs. Members, $1.00; nonmembers, $3.00. The issues involved in the design and operation of dual-lane runways are discussed. Dual-lane runway questions were investigated via fast-time and real-time simulations at Lincoln Laboratory over the period from October 1971 to December 1972. Included is an overview of the critical issues and findings identified with dual-lane runway configuration and operation. .. . - (Author) A73-43497 # The role ground transportation can play in the airport site selection process. N. F. McGinnis (TRW, Inc., Washington, D.C.). Intersociety Conference on Transportation, 2nd, Denver, Colo., Sept. 23-27, 1973, ASME Paper 73-ICT-70. 17 p. Members, $1.00; nonmembers, $3.00. Significant aspects of the mass transit system analysis activity associated with the recent South Florida Airport Site Selection 622 A73-43733 Program are discussed. The configuration, performance, cost, and service characteristics of the quasi-conceptual ground access trans- portation systems continually represented one of the main decision factors as the review authorities deliberated on each candidate airport site. Discussion of the transportation system impact on these deliberations is essentially the prime objective of this presentation. (Author) A73-43498 * ft Some considerations for air transportation analysis to non-urban areas. S. D. Norman (NASA, Ames Research Center, Systems Studies Div., Moffett Field, Calif.), tntersociety Conference on Transportation, 2nd, Denver, Colo., Sept 23-27, 1973. ASME Paper 73-ICT-72. 6 p. 6 refs. Members, $1.00; nonmembers, $3.00. Review of some of the problems associated with air transporta- tion to and from nonurban areas. While a significant proportion of public transportation needs of nonurban areas are met by aircraft, there are indications that improvement in air transportation service are called for and would be rewarded by increased patronage. However, subsidized local service carriers are attracted by large aircraft operation, and there is a tendency to discontinue service to low density areas. Prospects and potential means for reversing this. trend are discussed. M.V.E. A73-43499 * # Potential of hydrogen fuel for future air transportation systems. W. J. Small, D. E. Fetterman, and T. F. Bonner, Jr. (NASA, Langley Research Center, Hampton, Va.). Intersociety Conference on Transportation, 2nd, Denver, Colo., Sept 23-27, 1973, ASME Paper 73-ICT-104. 11 p. 26 refs. Members, $1.00; nonmembers, $3.00. Recent studies have shown that hydrogen fuel can yield spectacular improvements in aircraft performance in addition to its more widely discussed environmental advantages. The characteristics of subsonic, supersonic, and hypersonic transport aircraft using hydrogen fuel are discussed, and their performance and environ- mental impact are compared to that of similar aircraft using conventional fuel. The possibilities of developing hydrogen-fueled supersonic and hypersonic vehicles with sonic boom levels acceptable for overland flight are also explored. (Author) A73-43S20 # The future for STOL. R. E. Hage and M. D. Marks (Douglas Aircraft Co., Long Beach, Calif.). RAeS, AIAA, and CAS/, Anglo-American Aeronautical Conference, 13th, London, England, June 4-8, 1973, Paper. 6 p. Technology developments which are important for the future of short 'takeoff and landing aircraft in the high-density air transport system are examined. The developments relate to the relief of major airport congestion and community acceptance of satellite short-haul airports. A system evaluation is discussed together with the tech- nology base. Attention is given to the high lift system, handling qualities, the functions of the stability augmentation system, aspects of airfoil design, problems of acoustics, and questions of operating economics. G.R. i A73-43720 #' A generalization of thin foil theory (Ob odnom obobshchenii teorii tonkogo prof ilia). I. L. Goloborod'ko and I. V. Ostoslavskii. Aviatsionnaia Tekhnika, vol. 16, no. 2, 1973, p. 19-23. In Russian. Description of a method of determining the aerodynamic characteristics of a slightly bent thin foil in the case of an arbitrarily located flow separation point. The problem is solved on the basis of thin foil theory. Analytical expressions are obtained for determining the lift coefficient and the longitudinal moment of the foil, and a study is made of the effect of the location of the flow separation point on the values of these two parameters. A.B.K. .1 A73-43722 # The effect of walls on the lifting force of a solid-foil wing (Vliianie stenok na pod'emnuiu tilu kryla telesnogo profilia). V. N. Kravets. Aviatsionnaia Tekhnika, vol. 16, no. 2, 1973, p. 29-33. 7 refs. In Russian. Consideration of the motion of a wing in a bounded ideal incompressible two-dimensional fluid flow. It is shown that if the perturbations introduced into the flow by the wing are small, a fairly general theory concerning this motion can be developed with the aid of the acceleration potential method. The solution of the singular integral equations to which this method leads can be simplified by using the asymptotic method of functional parameters. Curves showing the variation of the influence function for specific foil configurations are presented. A.B.K. A73-43723 ft Determination of the deflections and stresses in a small-aspect-ratio wing by the displacement method (K opredeleniiu progibov i napriazhenii v kryle malogo udlineniia metodom peremeshchenii). P. D. Levashov. Aviatsionnaia Tekhnika, vol. 16, no. 2, 1973, p. 34-39. In Russian. Description of a method of obtaining a system of resolvent equations for determining the deflections of the middle plane of a thin-walled small-aspect-ratio wing. The proposed method is similar in form to the Ritz method but differs from it in that the values of the node deflections are taken directly as the unknowns. The boundary kinematic conditions in the root cross section are satisfied by solving a conditional-extremum energy-minimization problem. The system of resolvent equations for the deflections is simple to derive, and the calculation of the coefficients of the unknowns can be easily programmed. A.B.K. A73-43724 ff Calculation of the deformations of a propeller blade in flight (Raschet deformatsii lopasti vozdushnogo vinta v polete). A. lu. Liss. Aviatsionnaia Tekhnika, vol. 16, no. 2, 1973, p. 40-45.9 refs. In Russian. Development of a method of calculating the in-flight deforma- tions of a propeller blade with allowance for bending in two planes and torsion. The proposed method is based on an expansion of the deformations in powers of the blade eigenmodes, followed by a determination of the deformation coefficients with the aid of the Galerkin method. In addition, a method of allowing for a nonlinear damper mounted on a vertical hinge is also proposed, as well as a method of allowing for the variability of the blade setting angle with • respect to azimuth. A.B.K. A73-43725 # Study and calculation of the vibrations of a rotating rotor with allowance for clearances in the bearings (Issle- dovanie i raschet kolebanii vrashchaiushchegosia rotora s uchetom zazorov v oporakh). lu. M. Klimov. Aviatsionnaia Tekhnika, vol. 16, no. 2, 1973, p. 46-52. 6 refs. In Russian. Consideration of the problem of calculating the nonlinear vibrations of elastically deformable rotors of gas turbine engine compressors and turbopump units with allowance for radial clear- ances in the bearings. The equations describing the forced vibrations of such a rotor are derived, and an approximate analytical method of solving them is proposed. The results of theoretical and experimental studies of the effect of clearances and rotor imbalance on the excitation of parametric vibrations are presented. Recommendations are made regarding the elimination of dangerous resonances so as to improve the reliability of the machines. A.B.K. A73-43728 # Designing a slender-wing-type cantilever plate under conditions of unsteady creep (Raschet konsol'noi plastiny tipa tonkogo kryla v usloviiakh neustanovivsheisia polzuchesti). V. G. Shataev. Aviatsionnaia Tekhnika, vol. 16, no. 2, 1973, p. 66-71. 7 refs. In Russian. A73-43733 tt Thermodynamics of an air-cooled gas-turbine stage (K termodinamike stupeni gazovoi turbiny s vozduthnym okhlazhdeniem). E. N. Bogomolov. Aviatsionnaia Tekhnika, vol. 16, no. 2. 1973. p. 97-106. In Russian. 623 A73-43735 Formulas are derived for calculating the efficiency and other principal parameters of a gas-turbine stage with air-cooled nozzle ring and rotor. The formulas are valid in the case where the cooling air is fed into the air-gas flow area. Quantitative estimates of the enthalpy drop in the rotor and other thermodynamic effects are obtained from example computations. V.P. A73-A373S ft'' Vibrations of turbojet-engine components con- taining structural dampers of the type of sandwich rods (K zadache o kolebaniiakh detalei TRD, soderzhashchikh konstruktsionnye dempfery tipa sloenykh sterzhnei). A. A. Samarin. Aviatsionnaia Tekhnika,vo\. 16, no. 2, 1973, p. 111-115. In Russian. The problem of determining the dissipation of the vibrational energy in a two-layer rod of arbitrarily varying cross section is examined. The layers are pressed together by a force that varies along the rod's length. The interface is governed by Coulomb's dry friction law. Inertia forces are taken into account. An expression for calculating the mutual slipping of the layers is derived for the case of phased vibrations of the layers. V.P. A73-43736 § Classification of methods for solving the direct problem of axlsymmetrie flow calculation in turboenginei (0 Massifikatsii metodov resheniia priamoi zadachi ratchets osesim- metrichnogo potoka v turbomashinakh). A. M. Topunov and R. D. losifov. Aviatsionnaia Tekhnika, vol. 16, no. 2, 1973, p. 116-121. 33 refs. In Russian. A73-43740 # Effect of the circumferential nonuniformity of a temperature field in front of a turbine on the vibrational stresses in the turbine blades (0 vliianii okruzhnoi neravnomernosti tamperatur- nogo polia pered turbinoi na vibronapriazhennosf rabochikh lopatok). N. A. Gachegov and V. D. Ronzin. Aviatsionnaia Tekhnika, vol. 16, no. 2,1973, p. 131-135. In Russian. A73-43741 # The problem of extrapolating test data on the efficiency of turbine-blade cooling to actual conditions (K voprosu pereneseniia rezul'tatov opytov po effektivnosti okhlazhdeniia tur- binnykh lopatok na naturnye usloviia). V. I. Lokai and A. S. Limanskii. Aviatsionnaia Tekhnika, vol. 16, no. 2,1973, p, 135-143. 10 refs. In Russian. Lokai's (1970) formulas for extrapolating cooling efficiency to actual high-altitude conditions are verified experimentally, using a gasdynamlc test stand and longitudinally cooled turbine blades. The need for careful study of the heat transfer in the cooling channels of rotating blades is demonstrated. V.P. A73-43742 ft Synchronized operation of a positive- displacement gear pump and a vane pump within the lubricant oil delivery system of a jet engine (0 sovmestnoi rabote ob'emnogo I lopatochnogo nesosov v kachalushchem agregate maslosistemy VRD). V. A. Rakhal'skll. Aviatsionnaia Tekhnika, vol. 16, no. 2, 1973, p. 144-147. In Russian. The efficiency of two versions of a jet-engine high-speed oil delivery system Is analyzed and compared. One system consists of a vaned booster pump which supplies the oil to a conventional positive-displacement gear pump, and whose rpm'i may be higher than those of the gear pump. The other system uses a common shaft to drive a gear and centrifugal impellers mounted in front of the gear. It is shown that the first system is the more efficient one. It provides synchronous operation over the entire range of rpm's. Maximum- power altitude is limited only by the cavitation parameters of the vane pump. V.P. A73-43743 ft Utilization of semiartificial thermocouples in gas-turbine engine tests (K voprosu primeneniia poluiskusstvennykh termopar pri ispytaniiakh gazoturbinnykh dvigatelei). D. F. Sim- birskii, L. S. Grigor'ev, A. la. Anikin, and L. O. Miroshnichenko. Aviatsionnaia Tekhnika, vol. 16, no. 2, 1973, p. 148-150. In Russian: Thermocouples, one of whose wires was prepared from the same metal as the component studied, were used to determine the temperature fields in combustion-chamber casings, disks, and blades of gas turbine engines. It is found that the use of such 'semiartificial' thermocouples diminishes the distortion of the temperature fields. The thermoelectric properties of a number of heat-resistant alloys are studied at temperatures of up to 1200 C. V.P. A73-43809 Fatigue crack growth retardation after single- cycle peak overload in Ti-6AI-4V titanium alloy. R. E. Jones (Dayton, University, Dayton, Ohio). Engineering Fracture Me- chanics, vol. 5. Sept. 1973, p. 585-604. 13 refs. . A73-43811 Environmental effects on fracture resistant and biaxial fatigue design of aircraft structures. U. G. Goransson and D. D. Froerer (Boeing Co., Seattle, Wash.). (Symposium on Fracture and Fatigue, George Washington University, Washington, D.C., May 3-5, 1972.) Engineering Fracture Mechanics, vol. 5, Sept. 1973, p. 627-645. 10 refs. Discussion of the two interrelated fields of crack initiation and crack propagation, presenting analytical techniques for calculating fatigue damage in biaxially stressed structures along with determina- tions of safe inspection intervals for contained crack growth. The equivalent stress concept is used to derive a set of uniaxial stresses that produce the same amount of fatigue damage as the biaxial stress exposure. The distortion energy, concept serves as the basis for combining alternating principal stresses by translating the uniaxial SN curves for zero mean stress into a family of concentric ellipses. Empirical procedures are given for treating problems with varying principal stress directions and areas with directionally dependent fatigue performance. The Goodman diagram relates alternating stresses and mean stresses at any constant cyclic life. If two uniaxial Goodman diagrams are constructed on each reference axis, a three-dimensional body can be visualized'which intercepts the zero alternating stress plane in a shape identical to that described by the applicable static load criterion. (Author) A73-43813 * Fracture analysis of surface- and through- cracked sheets and plates. J. C. Newman, Jr. (NASA, Langley Research Center, Hampton, Va.). (Symposium on Fracture and Fatigue, George Washington University, Washington, D.C., May 3-5, 1972.1 Engineering Fracture Mechanics, vol. 5, Sept. 1973, p. 667-689. 33 refs. The Neuber stress-concentration relation for notches in an elastic-plastic material subjected to shear loading was generalized for a crack in a finite plate subjected to tensile loading. An equation was derived which related the linear elastic stress-intensity factor, the applied stress, and two material parameters. The equation was then used as a two-parameter fracture criterion for surface- and through- cracked specimens. Fracture data from the literature on surface- and through-cracked sheet and plate specimens of steel, titanium alloy, titanium weldment, and aluminum alloy tested at room and cryogenic temperature were analyzed according to the proposed equation. For surface cracks, wide ranges of crack-depth to crack- length ratio and crack-depth to specimen-thickness ratio were considered. For through cracks, wide ranges of crack length and specimen width were also considered. (Author) A73-43869 Meridional distribution of tropospheric ozone from measurements aboard commercial airliners. H. K. Tiefenau, P. G. Pruchniewicz, and P. Fabian (Max-Planck-lnstitut fur Aeronomie, Lindau iiber Northeim, West Germany). (Symposium on At- mospheric Ozone, Arosa, Switzerland, Aug. 21-25, 1972.) Pure end Applied Geophysics, vol. 106-108, no. 5-7, 1973, p. 1036-1040. Research supported by the Deutsche Forschungsgemeinschaft. 624 A7 3-44056 A73-43911 Present status and development trends in the processing of titanium (Stand und Entwicklungstendenzen der Titanverarbeitung). H. Kellerer and G. Cans (Messerschmitt-Bolkow- Blohm GmbH, Munich, West Germany). (Universitat Erlangen- Nurnberg, Hauskolloquium, 3rd, Eriangen, West Germany, Oct 12, 1972.) Zeitschrift fur Metallkunde, vol. 64, Sept 1973, p. 606-612. 11 refs. In German. Metal-physical parameters strongly influence the technology of fabrication of titanium alloys: hexagonal structure, high strength at low Young's modulus, Bauschinger effect, high affinity to oxygen, stable oxides, susceptibility to hydrogen embrittlement, stress corrosion cracking by halogens, and low thermal conductivity. Techniques of fabrication are described which serve to overcome these problems in aeronautic and space applications: hot forming - e.g., by creep and relaxation deformation, shaping by chemical means and spark cutting, electron beam and diffusion welding under vacuum, stress relaxation annealing, special quenching media, and coating and hardening of surfaces. Moreover, unsolved problems • e.g., problems regarding techniques and heat treatments - are discussed. (Author) A73-44000 Aluminum brazed titanium honeycomb sand- wich structure • A new system. S. D. Elrod, D. T. Lovell, and R. A. Davis (Boeing Co., Seattle, Wash.). (American Welding Society and Welding Research Council, International Brazing Conference, 4th, Chicago, III., Apr. 4, 5, 1973.) Welding Journal, Research Supple- ment, vol. 52, Oct. 1973, p. 425-s to 432-s. The results of a development and production scale-up program for an Al-brazed Ti honeycomb sandwich structure are summarized, covering tests results for corrosion resistance, creep, metallurgical stability, mechanical strength, and fracture toughness. Creep-rupture tests were conducted at 450, 600 and 800 F. The corrosion tests included aircraft service of about three years, laboratory salt spray tests, and electric-potential measurements. The flatwise tension creep-rupture strength was adequate for structural applications of 800 F. The corrosion resistance was essentially equivalent to that of 3033 aluminum sheet. The production process is evaluated positively for 800 F operation, wedge and acoustic panel designs, and panel configurations for 30,000 Ib/in. Cost analysis shows that the structure is economically feasible for high performance vehicles. V.Z. A73-44026 The effect of composition changes on the fracture toughness of an AI-Zn-Mg-Cu-Mn forging alloy. C. J. Peel end P. J. E. Foreyth (Royal Aircraft Establishment, Materials Dept., Farnborough, Hants., England). Metal Science Journal, vol. 7, July 1973, p. 121-127. 15 refs. A73-440B2 Society of Flight Test Engineers, National Symposium, 3rd, Arlington, Tex., September 11-14, 1972, Pro- ceeding*. California, Md., Society of Flight Test Engineers, 1973. 420 p. Aspects of FAA certification flight testing are discussed together with details of Army flight test program management, the manage- ment of Air Force test and evaluation activities, the flight test programs of the Naval Air Systems Command, the management of commercial flight test programs, and the control of flight test programs at Bell Helicopter Company. The role of a military flight test engineer in test management and the capabilities of government test facilities are considered. G.R. A73-44053 # Management and control of flight test pro- grams of the Western Region FAA. C. E. Richards (FAA, Aircraft Engineering Div., Los Angeles, Calif.). In: Society of Flight Test Engineers, National Symposium, 3rd, Arlington, Tex.,- September 11-14, 1972, Proceedings. California, Md., So- ciety of Flight Test Engineers, 1973. 30 p. The mission performed by the Aircraft Engineering Division of the Federal Aviation Administration (FAA) is considered. As a service organization, the Aircraft Engineering Division influences the management and planning of a manufacturer's test program but does not directly manage it. Basically, the Aircraft Engineering Division certificates the aircraft which use the airports and airways. The specialties involved in certifying a modern complex aircraft are examined. The certification requires a close coordination of the Manufacturing Inspection Branch, the Airframe Branch, the Systems and Equipment Branch, the Propulsion Branch, and the Flight Test Branch. Questions regarding the general philosophy behind the. certification program are discussed and sample pages from a typical flight test program are provided. G.R. A73-44054 # Management and control of flight test pro- grams at U.S. Army Aviation Systems Command. C. C. Crawford, Jr. (U.S. Army, Washington, D.C.). In: Society of Flight Test Engineers, National Symposium, 3rd, Arlington, Tex., September 11-14, 1972, Proceedings. California, Md., Society of Flight Test Engineers, 1973. 28 p. Organizational questions are considered, giving attention to the Contractor's Development and Airworthiness Qualification Program, fhe tests are done entirely by industry and witnessed to varying extents by Army technical specialists. Specifications are provided to industry regarding the tests required to convince the Army that the aircraft is in fact airworthy. Tests carried out by industry are supplemented with tests conducted by the Army within the framework of an Army Preliminary Evaluation (APE). The APE's are generally short two week evaluations. A typical program would involve one APE early for performance assessment. Other investiga- tions include a flying qualities evaluation and an evaluation of key subsystems on the aircraft. These tests are followed by endurance tests, flight characteristics tests, climatic laboratory tests, and a service test. G.R. A73-44055 # Management of Air Force test and evaluation activities. J. P. Streit (USAF, Systems Command, Andrews AFB, Washington, D.C.). In: Society of Flight Test Engineers, National Symposium, 3rd, Arlington, Tex., September 11-14, 1972, Pro- ceedings. California, Md., Society of Flight Test Engineers, 1973. 51 p. The Air Force manages a wide variety of testing activities beginning with such tasks as the examination of the smallest pieces or components undergoing environmental or qualification testing and extending to the assessment of the relative effectiveness of different tactical applications of entire new weapon systems. In addition, there are other testing programs related to basic research and technology advancement. The current Air Force test and evaluation (T and E) management concepts are discussed, giving attention to the evolution of these concepts in the period since about 1967. The total Air Force test and evaluation work effort is now divided into three broad classes, including R and D T and E, acquisition T and E, and engineering services T end E. G.R. A73-44056 # Management and control of flight test pro- grams of the Naval Air Systems Command. F. H. Baughman (U.S. Naval Air Systems Command, Washington, D.C.). In: Society of Flight Test Engineers, National Symposium, 3rd, Arlington, Tex., September 11-14, 1972, Proceedings. California, Md., Society of Flight Test Engineers, 1973. 17 p. The planning and setting up of a flight test program for a major Navy weapons systems development are discussed, giving attention to Navy project manager reporting relationships. The S-3A Viking contractor flight test program considered consists of three inter- locking phases, including a detailed laboratory test integration and evaluation program. The second phase, the flying test bed, is an intermediate step between the laboratory and aircraft tests. The third phase is the normal aircraft flight test program itself. Questions of avionics development and testing are explored together with aspects of the S-3A initial operational test and evaluation. G.R. 625 A73-44057 A73-44057 # Management and control of commercial flight test programs. H. W. Zimmerman (Boeing Co., Flight Operations Dept, Seattle, Wash.). In: Society of Flightiest Engineers, National Symposium. 3rd, Arlington, Tex., September 11-14, 1972, Pro- ceedings. California, Md., Society of Flight Test Engineers, 1973. 33 p. The historical evolution of commercial flight test programs is discussed, giving attention to advances occurring in response to the changes which took place since 1963 in the commercial transport market. Various aspects regarding the development of the Boeing 747 are considered, taking into account special design problems and aerodynamic testing conducted with the aid of an onboard electronic calculator. Questions of specific program responsibilities are in- vestigated. Details of aircraft control are discussed together with the responsibilities of the product division, the technology staff of the group engineering, and the flight operations department. The manufacturing preflight is considered along with the results of the Boeing 747 flight test program. G.R. A73-44061 # Air Force Prototype Program management R. E. Whelan (USAF, Prototype Program Office, Wright-Patterson AFB, Ohio). In: Society of Flight Test Engineers, National Symposium, 3rd, Arlington, Tex., September 11-14, 1972, Proceedings. California, Md., Society of Flight Test Engineers. 1973. 34 p. The Charter of the AF Advanced Prototype Program Office basically delineates a low cost advanced development effort for the development of advanced prototype aircraft and subsystems for technical evaluation against anticipated operational needs. The factors which characterize adaptive management as applied to advanced prototype programs are discussed. The prototype program concept is considered together with questions of prototype program office organization, the responsibilities of Air Force and other government agencies, aspects of program control, engineering, procurement/financial management, and logistics. The lightweight fighter prototype project is examined as one of the major programs to result from the prototype study. G. R. A73-44058 ft Management and control of military and com- mercial flight test programs at Bell Helicopter Company. R. H. Wheelock (Bell Helicopter Co., Fort Worth, Tex.). In: Society of • Flight Test Engineers, National Symposium, 3rd, Arlington, Tex., September 11-14, 1972, Proceedings. California, Md., Society of Flight Test Engineers, 1973. 13 p. Problem areas which have to be investigated are related to torsional stability, power management, fuel control characteristics, preflight ground endurance, components fatigue life, static and dynamic stability of the machine, cooling, and throttle response. Aspects of management procedures are considered, taking into account general technical measurements, instruction influence, data management, and cost-time schedule performance. Questions of instrumentation are discussed together with approaches for the efficient evaluation of test data. The responsibilities of various experts involved in the analysis of the test are examined. Attention is given to cost-schedule performance control methods designed to avoid major cost overruns in the development of the aircraft. G.R. A73-44062 ft The role of a military flight test engineer in test management J. K. Potts (USAF, Aeronautical Systems Div., Wright-Patterson AFB, Ohio). In: Society of Flight Test Engineers, National Symposium, 3rd, Arlington, Tex., September 11-14, 1972, Proceedings. California, Md., Society of Flight Test Engineers, 1973. 16 p. Test and evaluation is the single largest task_of the Air Force Systems Command. The Air Force flight test engineer has the background to play an important role in flight test management beyond the actual testing operations. The flight test engineer at the Air Force Flight Test Center is not a specialist. He reads film, prepares test plans, develops data reduction routines, flies in the test aircraft and plots and analyzes the test data. If he demonstrates the necessary competence he will become a project engineer responsible for an entire flight test program. After one or two major projects the project engineer will become a flight test manager at the test center level. The genesis of an engineering development program is discussed, giving particular attention to the role of the flight test manager. G.R. A73-44059 ft Management and control of military flight test programs at McDonnell Douglas St Louis, Missouri. R. L. Tuttle (McDonnell Douglas Corp., St. Louis, Mo.). In: Society of Flight Test Engineers, National Symposium, 3rd, Arlington, Tex., 'September 11-14, 1972, Proceedings. • California, Md., Society of Flight Test Engineers, 1973. 26 p. A contractor must thoroughly understand the objective of the weapon system and must design and test it for the most probable critical service environments. Testing requires sound management techniques. Basic considerations peculiar to test program manage- ment are discussed. In the development phase, fatigue testing will investigate the life of the system. The various phases of flight testing are described. Questions of test effectiveness are examined along with test program plans and requirements of test support. G.R. A73-44060 ff SFTE Symposium 12 October 1972. F. G. Edwards (Grumman Aerospace Corp., Bethpage, N.Y.). In: Society of Flight Test Engineers, National Symposium, 3rd, Arlington, Tex., September 11-14, 1972, Proceedings. California, Md., Society of Flight Test Engineers, 1973. 52 p. A number of basic questions regarding the objectives of flight tests are examined, giving attention to the responsibility to the customer, obligations to the corporation, and organizational rela- tions. A flight test system was developed through the integration of five elements, including detailed planning, advanced test techniques, supporting facilities, integrated flight operations, and control. The heart of the flight test system is an Automated Telemetry Station (ATS). ATS test operations are discussed together with ATS real time benefits, integrated flight operations, budget considerations, and plans for improvements. G.R. A73-44063 # NAFEC test facilities. R. M. Spangler (FAA, National Aviation Facilities Experimental Center, Atlantic City, N.J.). In: Society of Flight Test Engineers, National Symposium, 3rd, Arlington, Tex., September 11-14, 1972, Proceedings. California, Md., Society of Flight Test Engineers, 1973. 27 p. Technical data are presented regarding the functions and capabilities of the test-bed, service, and commissioned facilities at the National Aviation Facilities Experimental Center (NAFEC), Atlantic City, New Jersey. The background of NAFEC is discussed together with the range instrumentation environment, the navigational aids environment, the communications environment, the ATC systems laboratory environment, the service facilities environment, the aircraft safety environment, the aircraft environment, the airport environment, and the computation environment. Other subjects considered include the magnetic tape data acquisition systems, the flight simulation facility, and the vortex measurement facility. G.R. A73-44064 # The capabilities of army test facilities. S. G. Cockerham (U.S. Army, Washington, D.C.). In: Society of Flight Test Engineers, National Symposium, 3rd, Arlington, Tex., September 11-14, 1972, Proceedings. California, Md., Society of Flight Test Engineers, 1973. 55 p. The Army test capabilities which are dedicated to aircraft testing are discussed, giving attention to the people, the locations, and the equipment which provide these capabilities. Questions of organizational relations are considered. The Aviation Systems Com- mand is responsible for aircraft procurement, engineering, engi- neering flight tests, and logistics support. The Test and Evaluation Command tests and evaluates all Army Materiel Command material 626 A73-44377 with tht exception of aircraft. Important installations include the Electronic Proving Ground, the Yuma Proving Ground, the Tropic Test Center, and the Central Ground Station. G.R. A73-44066 ft Remarks before the Third National Sym- posium Society of Flight Test Engineers 13 September 1972. R. M. Isaman (U.S. Naval Air Test Center, Patuxent River, Md.). In: Society of Flight Test Engineers, National Symposium, 3rd, Ar- lington, Tex., September 11-14, 1972, Proceedings. California, Md., Society of Flight Test Engineers, 1973. 12 p. The Navy's capabilities for the test and evaluation of aircraft are examined, giving attention to organizational relationships. The Naval Civil Engineering Laboratory, the Naval Electronics Laboratory Center, the Naval Ordnance Laboratory, and the Naval Undersea Center are oriented along technology lines. The Naval Air Develop- ment Center and the Naval Ship Research and Development Center are concerned with associated technologies such as the materials, structures, fluid dynamics, and control problems of aircraft and ships. The Naval Weapons Laboratory and the Naval Weapons Center are focused on surface warfare, air warfare, and air-launched weapons. G.R. A73-44155 ft On the process of precipitation in Mg-Ce alloy. G. Omori, S. Matsuo (National Research Institute for Metals, Tokyo, Japan), and H. Asada (Ninon University, Chiba, Japan). Japan Institute of Metals, Journal, vol. 37, July 1973, p. 677-682. 17 refs. In Japanese, with abstract in English. The precipitation process in Mg-1.3 wt % Ce alloy was studied by means of electrical resistivity measurement and electron micro- scopy. On isochronal annealing of the alloy, the electrical resistivity decreased gradually up to about 200 C, followed by an abrupt decrease between 200 and 325 C. This abrupt decrease was attributed to the precipitation of an intermediate phase. On further heating, the electrical resistivity increased steadily, but the increase halted temporarily at 450 to 500 C. At this stage, the precipitation of the equilibrium phase was observed. On isothermal annealing in the temperature range from 100 to 150 C. the electrical resistivity decreased in two stages. Following Johnson-Mehl equation, the values of 2/3 and 1.0 were obtained as the time exponents, n. for the first and second stage, respectively. Using the isothermal curves of resistivity change, estimations of apparent activation energies for the above two stages were also made. (Author) A73-44219 Measuring technological change - Aircraft turbine engines. A. J. Alexander and J. R. Nelson (Rand Corp., Santa Monica, Calif.). Technologies/ Forecasting and Social Change, vol. 5, no. 2,1973, p. 189-203. 5 refs. A technique for measuring technological change is discussed, giving attention to the definition of a breakthrough and the meaning of the phrase that a device is ahead of its time. The analysis conducted is confined to the development process. It proceeds on the assumption that the device under development can be adequately characterized by a limited number of parameters. The increase in the value of the parameter set is called technological advance. Basic research and invention are excluded. American aircraft turbine engines are selected as the initial subject for testing the new technique. A statistical analysis of a data sample on turbine engines is performed. The analysis of technological change is extended to take . into account additional factors. Thus, a technological production function is defined. The function relates the technology and production costs to the resources or costs of development. G.R. A73-44223*# The many uses of the dirigible. J. R. Hunt (Embry-Riddle Aeronautical University, Daytona Beach, Fla.), B. B. Levitt (Operations Research, Inc., Silver Spring, Md.), F. Morse (Boston University, Boston, Mass.), K. R. Stehling (NASA, Washington, D.C.), and J. G. Vaeth (NOAA, National Environmental Satellite Service, Washington, D.C.). Astronautics and Aeronautics, vol. 11, Oct. 1973, p. 58-65. 6 refs. Prospects for a revival of large airships are based on a number of unique services which can be provided by the dirigibles. It is shown that airships are not unduly weather-sensitive. Modern technological advances will give the airship of the future operational features which will be greatly superior to those of the Zeppelins of the past. Projections set the payload of a 22-million-cu ft conventionally propelled airship of conservative design at 615.000 Ib for a range of 2950 mi. The corresponding figure for the C-5A aircraft is only 265,000 Ib. Dirigibles could, therefore, become merchant ships of the air, carrying low-density and large-dimension cargoes that jet freighters find economically unattractive or practically impossible to handle. The absence of landing-facility requirements would make the airship a logical candidate for introducing trade into otherwise inaccessible regions of the world. G.R. A73-44292 # Errors produced by the influence of unsteady heating in strain measurement by wire-type resistance strain gages (Pogreshnost* v izmerenii deformatsii provolochnymi tenzo- rezistorami, obuslovlennaia vliianiem nestatsionamogo nagreva). A. N. Ser'eznov and G. A. Tsareva. Problem/ Prochnosti, vol. 5, Aug. 1973, p. 85-87. 7 refs. In Russian. A73-44294 H Determination of the temperature fields of turbine disks and blades, using irradiated diamond indicators (Opredelenie polei temperatur diskov i lopatok turbin indikatorami iz obluchennogo almaza). E. F. Barbashin, K. S. Pul'kis, and V. A. Nikolaenko. Problemy Prochnosti, vol. 5, Aug. 1973, p. 117-119. In Russian. The method proposed is based on the property of a crystalline diamond to increase the volume of the crystal lattice under bombardment by high-energy particles, and to gradually decrease the volume to the initial size under the effect of heating. The method provides an effective means of monitoring turbine temperatures in the temperature range from 130 to 1200 C. V.P. A73-44329 Determinate systems on modal control theory. T. P. Grigor'eva and L. I. Kozhinskaia. tAvtomatika i Telemekhanika, Apr. 1973, p. 5-8.) Automation and Remote Control, vol. 34, no. 4, Sept. 1, 1973, pt. 1,p. 513-516. Translation. Consideration of the problem of synthesizing a linear control system with a desired spectrum on the basis of incomplete information regarding this system. Necessary and sufficient condi- tions are obtained under which a closed-loop linear control system possesses a desired spectrum and the information vector of the system has a minimum dimension. . A.B.K. A73-44377 # Dynamic buckling of an axially compressed cylindrical shell with discrete rings and stringers. C. A. Fisher and C. W. Bert (Oklahoma, University, Norman, Okl?.). (Canadian Congress of Applied Mechanics, 4th, Montreal, Canada, May 28-June 1, 1973.) ASME, Transactions, Series £ • Journal of Applied Mechanics, vol. 40, Sept. 1973, p. 736-740. 19 refs. As an exploratory effort toward improving the crashworthiness of light aircraft cabins, a theoretical analysis was made to predict the dynamic buckling load and buckling time of a stiffened, thin-walled circular cylindrical shell. To provide for the large stiffener spacing in light aircraft, the stiffeners were considered as discrete elements by means of a Dirac delta procedure. The nonlinear governing equations vwf-e derived using Hamilton's principle and the final equations were obtained by means of Galerkin's method. Solution was carried out by using a Gauss-Jordan technique on the algebraic equations and a Runge-Kutta technique on the nonlinear differential equations. Numerical results are presented for an idealized model of a typical light aircraft cabin. . (Author) 627 A73-44575 A73-44575 The translantic charter policy of the United States. L. S. Keyes. Journal of Air Law and Commerce, vol. 39, Spring 1973, p. 215-248. 81 refs. In 1972, the governments of both the U.S. and the UK abandoned longstanding restrictive attitudes toward the air trans- portation of passengers by charter carriers and by charters operated by scheduled carriers. The early policy of extreme caution on the part of the U.S. toward independent international charter air carriage is considered together with the change in policy and its impact on IATA fares. Questions of the expansion of charter traffic and the renewal of certificates are examined. Recent moves towards liberali- zation are discussed, giving attention to the disapproval of resolution 045, the adoption of nonaffinity charter regulations, and efforts to regularize charter landing rights. G.R. A73-44690 The aerodynamics of aircraft and other things /Fifteenth Lanchester Memorial Lecture/. P. R. Owen (Imperial College of Science and Technology, London, England). Aeronautical Journal, vol. 77, Aug. 1973, p. 383-405. 65 refs. A review of some basic problems of aircraft aerodynamics, including the author's contributions to the field. Among the topics covered are the slender body theory, the responses of airships and buildings to atmospheric turbulence, boundary layers vs atmospheric turbulence, wind tunnel contractions, grids and boiler tubes as turbulence agents, aircraft radiator blocks, and various types of vortex-induced oscillations. Rough surfaces and sand storms, wind tunnel simulation, laminar flows, turbulent-to-laminar flow transition in the human lung, and a hypersonic flow past a blunt body are also considered. V.Z. shown that, a one-dimensional calculation of the flow parameters from the measured wall pressure leads to contradictory results in regimes far from thermal cutoff. A calculation of the parameters of a supersonic flame jet from the measured wall pressure in the case of the two-stream Crocco model also leads to contradictory results. Results which are physically more justifiable are obtained for a separation model which assumes the presence of separation zones in the flow. The separation model also makes it possible to give a quantitative description of the flow in an isothermal pseudoshock. A.B.K. A73-44827 # Supersonic jet noise generated by large scale disturbances. C. K. W. Tarn (Florida State University, Tallahassee, Fla.). American Institute of Aeronautics and Astronautics, Aero- Acoustics Conference, Seattle, Wash., Oct 15-17, 1973, Paper 73-992. 14 p. 22 refs. Members, $1.50; nonmembers, $2.00. NSF Grant No. GK-35790. A number of experimental evidence and theoretical arguments are now available to suggest that the dominant part of supersonic jet noise is produced by orderly large scale disturbances in the jet flow. This paper presents a mathematical theory which predicates the total noise power and its directional distribution of a nearly ideally expanded supersonic jet generated by this process. Supersonic jet flows are highly unstable. The amplified large scale disturbances of the flow not only enhance the unsteady entrainment of ambient gas into the jet, but also cause the jet to vibrate laterally. Both of these phenomena result in the emission of acoustic waves to the ambient environment. Numerical calculations on a Mach 2.2 cold supersonic jet based on the present theory compare favorably with experimental measurements. (Author) A73-44692 On problems of flight over an extended angle-of-attack range. H. H. B. M. Thomas (Royal Aircraft Establish- ment, Farnborough, Hants., England). Aeronautical Journal, vol. 77, Aug. 1973, p. 412-423. 53 refs. An attempt is made at providing a basis for the preparation of brief background leaflets as supplements to airworthiness require- ment statements, with particular attention to adequate high lift performance and safe post-stall flight control of'the aircraft. The topics include design features affecting aircraft performance under limiting angle-of-attack conditions, lateral forces and moments, interactions between wind and various aircraft components, control effectiveness, and buffeting. The needed wind tunnel tests and flight dynamics analysis at and beyond critical conditions are considered. V.Z. A73-44695 F-14. M. Wilson. Flight International, vol. 104, Sept 27, 1973, p. 508-517. The F-14 Tomcat is intended to replace the Phantom. The aircraft is to be used for escort missions, fleet defense, interdiction, and close support. The top speed called for is a little over Mach 2.2, permitting the use of conventional aluminum-based alloys. By the refuelling technique F-14s can be kept airborne for periods from 4 to 8 hrs, limited only by crew fatigue. Structurally the Tomcat is significant in being the first Western aircraft designed to use composite materials for load-bearing applications. G.R. A73-44702 ft Piecewise-one-dimensional models of super- sonic combustion and pseudoshock in a channel (O kusochno- odnomernykh modeliakh sverkhzvukovogo goreniia i psevdoskachka v kanale). E. S. Shchetinkov. Fizika Goreniia i Vzryva, vol. 9, July-Aug. 1973, p. 473-483. 15 refs. In Russian. Analysis of the phenomenon of thermal cutoff which limits a one-dimensional heat input to a supersonic flow in a cylindrical channel. It is found that thermal cutoff of a supersonic flow occurs according to different mechanisms in long and short pipes. In long pipes with a developed boundary layer combustion occurs in the presence of a pseudoshock, while in short pipes no pseudoshock is formed. In the case of supersonic combustion in a long pipe it is A73-44829 ff Acoustic fatigue resistance of aircraft struc- tures at elevated temperatures. C. W. Schneider (Lockheed-Georgia Co., Marietta, Ga.) and F. F. Rudder (Acoustics and Vibration Associates, Inc., Smyrna, Ga.). American Institute of Aeronautics and Astronautics, Aero-Acoustics Conference, Seattle, Wash., Oct 15-17. 1973, Paper 73-994. 9 p. 11 refs. Members, $1.50; non- members, $2.00. Contract No. F33615-72-C-1141. An analytical and experimental program was conducted to develop acoustic fatigue design criteria for aircraft structures subjected to intense noise in a high temperature environment. Equations for the dynamic response of a buckled panel were formulated for simply supported and clamped boundary conditions using large deflection plate theory. Random amplitude acoustic fatigue testing of representative aircraft structure was accomplished at temperatures up to 600 F to provide data for correlation with the analytical results. Empirical design criteria are presented in the form of design equations and nomographs for predicting the thermal and dynamic response of aircraft structures subjected to combined environments. (Author) A73-44834 * # Subsonic and supersonic jets and supersonic suppressor characteristics. H. T. Nagamatsu and R. E. Sheer, Jr. (GE Research and Development Center, Schenectady, N.Y.). American Institute of Aeronautics and Astronautics, Aero-Acoustics Con- ference. Seattle, Wash., Oct 15-17, 1973, Paper 73-999. 25 p. 36 refs. Members, $1.50; nonmembers, $2.00. NASA-FAA-supported research. The flow and acoustic characteristics over a Mach number range of 0.6 to 1.5 were determined for convergent and parallel flow nozzles with room temperature air. Mean velocity and fluctuating impact and static pressure distributions were investigated. Near-and far-field acoustic measurements were obtained, and overall sound power levels were compared with subsonic theory of Lighthill and supersonic theory of Nagamatsu and Horvay. Flow and acoustic characteristics of single and multiple shroud supersonic suppressors were studied. With 191 tubes and shrouds the overall sound power level for a Mach 1.4 jet was reduced 15.3 and 20.5 db respectively. (Author) 628 A73-44851 A73-44836 • # Jet noise suppression by swirling the jet flow. I. R. Schwartz (NASA, Ames Research Center, Moffett Field, Calif.). •American Institute of Aeronautics and Astronautics, Aero-Acoustics Conference, Seattle, Wash., Oct. 15-17, 1973, Paper 73-1003. 8 p. 6 refs. Members, $1.50; nonmembers, $2.00. The effect of swirling flow on jet noise suppression was experimentally investigated in a relatively small, low-thrust, fan-jet engine. Measurements of acoustic properties of the near and far fields, jet-flow characteristics, and engine thrust were made with and without stationary swirl vanes installed in the primary exhaust nozzle. Preliminary test results indicate that substantial reductions in jet overall sound pressure levels and overall acoustic power were obtained with minimal thrust losses. Based on preliminary analysis, present results, and previous experiments with swirling hot jets, it is predicted that even greater jet noise reductions can be obtained in higher thrust engines, particularly with afterburning, by swirling jet exhaust. (Author) A73-44838 * # A theoretical and experimental study of sound attenuation in an annular duct. H. E. Plumblee (Lockheed-Georgia Co., Marietta, Ga.). American Institute of Aeronautics and Astro- nautics, Aero-Acoustics Conference, Seattle, Wash., Oct. 15-17, 1973, Paper 73-1005. 12 p. 8 refs. Members, $1.50; nonmembers. $2.00. Contract No. NAS1-10472. The flow duct used in the experiments for this study was described in an earlier paper by Plumblee and Dean (1972). Angular and radial standing modes were excited in isolation, and the modal attenuation and phase speed were measured in an annular duct with locally reacting liners. Contour maps of constant attenuation and phase speed were computed in the wall impedance plane for no-flow and several flow conditions, and experimental data were compared with some of these calculations. The effect of flow on modal attenuation and phase speed was measured and is theoretically verified. The major result of this study is the verification of theoretical predictions which ultimately can lead to a duct liner design optimization without resort to expensive and lengthy test programs. (Author) A73-44840 * # A difference theory for noise propagation in an acoustically lined duct with mean flow. K. J. Baumeister and E. J. Rice (NASA, Lewis Research Center, Cleveland, Ohio). American Institute of Aeronautics and Astronautics, Aero-Acoustics Con- ference, Seattle, Wash.. Oct 15-17, 1973. Paper 73-1007. 10 p. 12 refs. Members, $1.50; nonmembers, $2.00. A finite difference formulation is presented for sound propaga- tion in a two-dimensional straight soft-walled duct with uniform flow. The difference analysis is developed in terms of complex notation. The governing acoustic difference equations and the appropriate displacement boundary conditions associated with uni- form flow are presented. Example calculations are presented for the sound attenuation in straight hard and soft-walled ducts. At present the finite Mach number case is solved only for the one-dimensional hard walled duct. (Author) A73-44844 # Theoretical studies of sound emission from aircraft ducts. H. D. Hogge and E. W. Ritzi (Douglas Aircraft Co., Long Beach, Calif.). American Institute of Aeronautics and Astro- nautics, Aero-Acoustics Conference, Seattle, Wash., Oct. 15-17, 1973, Paper 73-1012. 12 p. 11 refs. Members, $1.50; nonmembers, $2.00. Research sponsored by the Douglas Aircraft Independent Research and Development Program. A finite-element solution to the problem of sound propagation in a duct of finite length and with axial variation in cross section and mean flow Mach number is obtained by matching cylindrical and conical duct elements. The effect of reflection from the open end is provided by a simple model of the radiation impedance of the opening. Examples are included to show the effects of (1) reflections from the open end, (2) source impedance, (3) mean flow, (4) cone angle, (5) cross section variation, and (6) finite wall impedance on the propagation of rotating pressure waves in ducts. (Author) A73-44848 H The influence of aerooyna.iiii. tiow noise in turbofan engines. R. A. Mangiarotty (Boeing Commercial Airplane Co., Seattle, Wash.). American Institute of Aeronautics and Astro- nautics, Aero-Acoustics Conference. Seattle, Wash., Oct. 15-17, 1973, Paper 73-1016. 5 p. 7 refs. Members, $1.50; nonmembers, $2.00. The component noise sources of advanced technology turbofan engines are reviewed showing that previously unimportant noise sources are unmasked by the lowering of jet noise and the use of acoustic linings for reducing turbomachinery noise. The two main sources unmasked are the engine core noise and aerodynamic noise generated by airflow in the engine nacelle ducts. A review of aerodynamic noise mechanisms show that turbulent flow confined in a duct generates more energy than in free space, particularly at the lower frequencies. Because airflow is continuously generated along a duct whereas turbomachinery noise is attenuated by acoustic linings, aerodynamic noise could limit the attenuation of turbomachinery noise by linings. (Author) A73-44849 * H Noise comparisons from full-scale fan tests at NASA Lewis Research Center. M. F. Heidmann and C. E. Feiler (NASA, Lewis Research Center, Cleveland, OhM. American Institute of Aeronautics and Astronautics, Aero-Acoustics Conference, Seattle. Wash., Oct. 15-17, 1973. Paper 73-1017. 12 p. 11 refs. Members, $1.50; nonmembers, $2.00. The overall aero and acoustic design features of eight 6-foot- diameter, single-stage fans tested in an outdoor acoustic facility are described. A correlation of the acoustic results for subsonic tip-speed fans showed the total sound power to be proportional to the mechanical power imparted to the fan and the specific work performed on the air to within plus or minus 2 dB. The correlation was relatively insensitive to fan design variables over a broad range of operating conditions. Maximum perceived noise levels were generally proportional to the sound power levels with both noise levels exhibiting a relatively unique increase with fan pressure ratio when normalized by the delivered thrust. The spectra of broadband noise attributed to the fan exhibited a bimodal characteristic for most of the fans. A predominant mode centered near the blade-passage tone and another at 8 to 16 times the tone frequency. • (Author) A73-44850 # Broadband noise generation by aerofoils and axial flow fans. B. D. Mugridge (Southampton, University, Southampton, England). American Institute of Aeronautics and Astronautics, Aero-Acoustics Conference, Seattle, Wash., Oct. 15-17, 1973, Paper 73-1018. 10 p. 32 refs. Members, $1.50; nonmembers, $2.00. Research supported by the Ministry of Defence. The generation of broadband noise by aerofoils and fan blades has been investigated and working formulae developed, for cases where the mean flow velocity is subsonic. The derivation of the aero-acoustic transfer function for unsteady flow interactions is the major feature of the paper. New two-dimensional wind tunnel data yield a flow-force relationship for acoustically compact aerofoils for reduced flow frequencies for both random and discrete interactions. Integrated force spectra compare favorably with standard unsteady lift theory although the surface pressure phase relationships do not conform to a Kutta edge criterion. The acoustic calculations utilise established line force models. (Author) A73-44851 # Sound generation by wake cutting, H. Fujita and L. S. G. Kovasznay (Johns Hopkins University, Baltimore, Md.). American Institute of Aeronautics and Astronautics, Aero-Acoustics Conference, Seattle, Wash., Oct. 15-17, 1973, Paper 73-1019. 6 p. 7 refs. Members, $1.50; nonmembers, $2.00. Research supported by the United Aircraft Corp. The sound generated by the interaction of an airfoil and a passing wake was studied experimentally. A square jet was 'cut' periodically by circular rods moving across the flow to produce a row of oblique wakes. A circular arc symmetrical airfoil was placed in the 629 A73-44852 flow, and by means of periodic sampling and averaging the strictly periodic components of the instantaneous surface pressure fluctua- tion at different chordwise locations on the airfoil as well as of the radiated sound field were determined. First, the airfoil leading edge was aligned with the wake to obtain a nearly two-dimensional interaction. Later, the airfoil was turned at an angle with respect to the wake so that the wake interaction swept spanwise along the leading edge (three-dimensional flow). All pressure fluctuations as well as the sound radiation were found to be decreasing with increasing skew angle between the airfoil and the wake. (Author) A73-44852 # The effects of modulated blade spacing on static rotor acoustics and performance. P. A. Shahady, C. A. Lyon (USAF, Aero Propulsion Laboratory, Wright-Patterson AFB, Ohio). J. J. Schauer (Dayton, University, Dayton, Ohio), M. H. Chopin, and M. S. Ewing (USAF, Aeronautical Systems Div., Wright-Patterson AFB, Ohio). American Institute of Aeronautics and Astronautics, Aero-Acoustics Conference, Seattle, Wash., Oct. 15-17, 1973, Paper 73-1020. 7 p. Members, $1.50; nonmembers, $2.00. A method'to assess the aural detection possibilities of aircraft was developed in connection with programs designed to provide the technology to quiet military aircraft for reconnaissance/surveillance and special tactical operations. The aural detection of aircraft depends to a large extent on the background noise environment in which the receiver is located. Curves for a comparison of the aircraft acoustic noise signature and detection level criteria are shown in a graph. The effects of blade spacing on acoustic performance are theoretically analyzed. Theoretical findings are compared with the results of experimental studies. G.R. A73-44853 * H Multiple pure tone noise generation and con- trol. M. J. Benzakein, S. B. Kazin, and C. T. Saved (General Electric Co., Evendale, Ohio). American Institute of Aeronautics and Astronautics, Aero-Acoustics Conference, Seattle, Wash., Oct. 15-17, 1973, Paper 73-1021. 9 p. 8 refs. Members, $1.50; nonmembers, $2.00. Contract No. NAS3-12430. The generation of multiple pure tones in supersonic .* discussed. The theoretical results of Kurasaka are reviewed and compared with experimental data obtained on a 36-in. diameter, 1550 ft/sec, 1.6 pressure ratio fan. Detailed measurements on bow shock locations taken with pressure transducers indicate that blade to blade discrepancies are the source of MPT generation. The paper presents some experimental results on an attempt to reduce the shock strength, and subsequently the MPT's, through blade modifica- tions. Other attempts at reducing the MPT's through wall treatment, high inlet flow Mach number, acoustically treated splitters - are discussed. Experimental data is presented on the validity of these noise reduction methods. (Author) A73-44854 # Inlet geometry and axial Mach number effects on fan noise propagation. D. C. Mathews and R. T. Nagel (United Aircraft Corp., Pratt and Whitney Aircraft Div., East Hartford, Conn.). American Institute of Aeronautics and Astronautics, Aero- Acoustics Conference, Seattle, Wash., Oct. 15-17, 1973, Paper 73-1022. 11 p. 8 refs. Members, $1.50; nonmembers, $2.00. Extensions of existing noise propagation theories to three- dimensional inlets are developed and applied to the propagation behavior of both acoustic spinning modes and nonlinear shock waves in typical aircraft inlets operating under a range of conditions. Aspects of the propagation of linear spinning modes in contoured inlets are discussed together with questions of three-dimensional nonlinear shock wave theory. Results of experimental investigations are also considered, giving attention to a powered nacelle model engine, the effect of inlet contour changes at speeds near cutoff, and the study of a full scale high bypass ratio engine. G.R. A73-44855 # A review of combustion generated noise. W. C. Strahle (Georgia Institute of Technology, Atlanta, Ga.). American Institute of Aeronautics and Astronautics, Aero-Acoustics Con- ference. Seattle. Wash.. Oct 15-17, 1973, Paper 73-1023. 9 p. 38 refs. Members, $1.50; nonmembers, $2.00. NSF Grant No. GK-32544; Grant No. AF-AFOSR-72-2365. The available information on noise generation by turbulent combustion processes is reviewed with the goal in mind to be able to predict its importance in core engine noise in turbopropulsion systems. Noise data from research burners, furnaces and engines are reviewed as are the available theories of combustion noise. Emphasis is placed upon the total sound power output and the spectral content as well as upon the effects of enclosures on the radiated noise. Conclusions are drawn concerning the research required to ade- quately assess the importance of combustion noise in turbo- propulsion systems. (Author) A73-44857 # Core engine noise. E. Grande (Foster-Miller Associates, Inc., Waltham, Mass.). American Institute of Aeronautics and Astronautics. Aero-Acoustics Conference, Seattle, Wash., Oct. 15-17, 1973, Paper 73-1026. 6 p. 13 refs. Members, $1.50; nonmembers, $2.00. This paper considers sources of core noise in a turbofan engine. A brief assessment is made of noise due to obstructions in the flow passage, turbulence level and swirl in the mean flow, turbine noise due to interaction with upstream turbulence, and combustor noise. It is tentatively concluded that combustor noise is the primary source of core noise. A core noise prediction procedure is formulated, considering the noise generation in the combustion chamber and the noise transmission through the turbine and the primary exhaust nozzle. The resulting prediction scheme expresses the far field core noise level as a function of the turbine pressure ratio, the nozzle pressure ratio, the combustor inlet and outlet temperatures and the nozzle temperature, and the combustor configuration and size. Comparison of the measured and predicted core noise levels for two turbofan engines yields satisfactory agreement. (Author) A73-44858 # Core engine noise. R. P. Gerend, H. A. Kumasaka, and J. P. Roundhill (Boeing Commercial Airplane Co., Seattle, Wash.). American Institute of Aeronautics and Astronautics, Aero-Acoustics Conference, Seattle, Wash., Oct. 15-17, 1973, Paper 73-1027. 10 p. 5 refs. Members, $1.50; nonmembers, $2.00. The low frequency noise component of full-scale engines has generally exhibited a significant deviation from that observed for jet noise alone. Tests have indicated that at least a portion of this noise component is generated inside the engine, upstream of the exhaust nozzle. This 'excess' noise, called 'core noise,' has been studied. The studies include a model test, in which an artificial upstream noise source of known level was introduced. A full-scale engine test, involving a JT9D turbofan with an extended, lined tail pipe was also conducted. Other studies were concerned with the development of a preliminary prediction procedure, based on full-scale engine data. G.R. A73-448S9 # Mechanisms of externally blown flap noise. M. R. Fink (United Aircraft Research Laboratories, East Hartford, Conn.). American Institute of Aeronautics and Astronautics, Aero- Acoustics Conference, Seattle, Wash., Oct. 15-17, 1973, Paper 73-1029. 11 p. 20 refs. Members, $1.50; nonmembers, $2.00. In the analysis of noise mechanisms, effects of reflection and shielding are considered together with the leading-edge noise, scrubbing noise, trailing-edge noise, and sideline and forward-flight effects. Under-the-wing spectra are discussed along with questions of under-the-wing directivity, over-the-wing spectra, and over-the-wing directivity. Noise beneath over-the-wing configuration models is typified by a sixth-power velocity law and a very small decrease of intensity as the exit direction is approached. G.R. A73-44860 * # Acoustic investigation of the engine-over-the- wing concept using a D-shaped nozzle. M. Reshotko and R. Friedman (NASA, Lewis Research Center, Cleveland, Oh'\o). American Institute 630 A73-44887 of Aeronautics and Astronautics, Aero-Acoustics Conference, Seat- tle;.Wash., Oct 15-17, 1973. Paper 73-1030. 10p. 11 refs. Members. $1.50; nonmembers, $2.00. Small-model experiments were conducted of the engine-over- the-wing concept using a D-shaped nozzle in order to determine the static-lift and acoustic characteristics at two wing-flap positions. Configurations were tested with the flow attached and unattached to the upper surface of the flaps. Attachment was obtained with a nozzle flow deflector. In both cases, high frequency noise shielding by the wing was obtained. Configurations using the D-shaped nozzle are compared with corresponding ones using a circular nozzle. With flow attached to the flaps, the static lift and acoustic results are almost the same for both nozzles. Without the nozzle flow deflector (unattached flap flow), the D-nozzle is considerably noisier than a circular nozzle in the low and middle frequencies. (Author) A73-44861 H Progress in source noise suppression of sub- sonic tip speed fans. F. B. Metzger (United Aircraft Corp., Hamilton Standard Div., Windsor Locks, Conn.). American Institute of Aeronautics and Astronautics, Aero-Acoustics Conference, Seattle, Wash.. Oct 15-17, 1973, Paper 73-1032. 13 p. 19 refs. Members, $1.50; nonmembers, $2.00. Work has been proceeding to develop subsonic tip speed fan engines operating at low pressure ratio. The fans considered are inherently quieter than existing turbofans. However, on account of the great number of blades in these fans, there is still a significant amount of noise energy at the higher frequencies that contribute most to annoyance. Effects of new fan designs on the noise characteristics are discussed, giving attention to the incorporation of a few blades only, low tip speed, and low pressure ratios. G.R. A73-44862 if Spectral trends in rotor noise generation. S. E. Wright (Southampton University, Southampton, England). American Institute of Aeronautics and Astronautics, Aero-Acoustics Con- ference, Seattle, Wash., Oct. 15-17, 1973, Paper 73-1033. 12 p. 15 refs. Members. $1.50; nonmembers, $2.00. Research supported by the Science Research Council. Rotor noise from a range of rotor types is examined, giving attention to propellers, helicopter rotors, and fans. The study assumes that the major radiation properties lie within the rotor, and are not affected to a first order by the presence of a duct. The effect of forward motion on the radiation process is assumed to be small for moderate forward speeds. Aspects of spectral adjustment are discussed together with questions regarding the minimum rotor noise, rotor excess noise, and rotor spectra. G.R. A73-44863 * # A study to determine the feasibility of a low sonic boom supersonic transport E. J. Kane (Boeing Commercial Airplane Co., Seattle, Wash.). American Institute of Aeronautics and Astronautics, Aero-Acoustics Conference. Seattle, Wash., Oct. 15-17, 1973, Paper 73-1035. 11 p. 11 refs. Members, $1.50; nonmembers, $2.00. Contract No. NAS1-11877. The objective of this study was to determine if a supersonic transport designed to produce a sonic boom signature with low overpressure represented a feasible concept. Two design goals were chosen: an overpressure of 1.0 psf or less for cruise at Mach 2.7 and an overpressure of 0.5 psf for cruise at Mach 1.5. Projected 1985 technology was assumed for the analysis. The principal effort was to develop cruise configurations capable of meeting the sonic boom goals. The Mach 2.7 goal was achieved with a blended arrow wing configuration and the Mach 1.5 design was a low arrow wing configuration with a horizontal tail. The development of these airplanes is summarized and the concept of a low sonic boom SST is evaluated. (Author) A73-44866 // A new device for measuring local acoustic power output of subsonic jets. J. T. Yen (Grumman Aerospace Corp., Bethpage, N.Y.) and T. E. Siddon (British Columbia, University, Vancouver, Canada). American Institute of Aeionautics and Astronautics, Aero-Acoustics Conference, Seattle, Wash., Oct. 15-17. 1973, Paper 73-1042. 8 p. 6 refs. Members, $1.50; non- members, $2.00. The use of microphone arrays or collector-microphone systems for the measurement of the total noise power output of a small volume element is discussed. The performance of a circular-arc array with 10 dynamic microphones is considered, taking into account measurements conducted in cases in which speakers operating at 500 and 1000 Hz were used as sources. With the aid of computer computations it is found that an optimal configuration is composed of a 14 feet diameter, semicircular array of 60 microphones. G.R. A73-44867 * # Comparison of results obtained with various sensors used to measure fluctuating quantities in jets. S. P. Parthasarathy, P. F. Massier, and R. F. Cuffel (California Institute of Technology, Jet Propulsion Laboratory, Pasadena, Calif.). American Institute of Aeronautics and Astronautics, Aero-Acoustics Con- ference, Seattle. Wash., Oct. 15-17. 1973, Paper 73-1043. 8 p. 5 refs. Members, $1.50; nonmembers, $2.00. Contract No. NAS7-100. An experimental investigation has been conducted to compare the results obtained with six different instruments that sense fluctuating quantities in free jets. These sensors are typical of those that have recently been used by various investigators who are engaged in experimental studies of jet noise. Intensity distributions and two-point correlations with space separation and time delay were obtained. The static pressure, density, and velocity fluctuations are well correlated over the entire cross section of the jet and the cross-correlations persist for several jet diameters along the flow direction. The eddies appear to be flattened in the flow direction by a ratio of 0.4. (Author) A73-44868 //' Introduction of the viscous force sensing fluctuating probe technique, with measurement in the mixing zone of a circular jet. D. Y. Cheng (Santa Clara, University, Santa Clara, Calif.). American Institute of Aeronautics and Astronautics, Aero- Acoustics Conference, Seattle, Wash., Oct. 15-17, 1973, Paper 73-1044. 6 p. Members, $1.50; nonmembers, $2.00. A73-44871 * # Comparison of aircraft noise measured in flight test and in the NASA Ames 40- by 80-foot wind tunnel. A. Atencio, Jr. (NASA, Ames Research Center, Moffett Field, Calif.) and P. T. Soderman (U.S. Army, Air Mobility Research and Development Laboratory, Moffett Field, Calif.). American Institute of Aeronautics and Astronautics, Aero-Acoustics Conference, Seat- tle, Wash., Oct 15-17. 1973. Paper 73-1047. 9 p. 8 refs. Members. $1.50; nonmembers, $2.00. A method to determine free-field aircraft noise spectra from wind-tunnel measurements has been developed. The crux of the method is the correction for reverberations. Calibrated loud speakers are used to simulate model sound sources in the wind tunnel. Corrections based on the difference between the direct and rever- berant field levels are applied to wind-tunnel data for a wide range of aircraft noise sources. To establish the validity of the correction method, two research aircraft - one propeller-driven (YOV-10A) and one turbojet-powered (XV-5B) - were flown in free field and then tested in the wind tunnel. Corrected noise spectra from the two environments agree closely. (Author) A73-44887 Low-pressure prepregs as structural material for light-construction designs (Niederdruck-Prepregs als Konstruk- tionswerkstoff fur die Leichtbauweise). H. Schonland, A. Knop, and U. Neumann (Eltro GmbH und Co., Flensburg; Bakelite Gesellschaft mbH, Duisburg-Meiderich, West Germany). In: Arbeitsgemeinschaft Verstarkte Kunststoffe, Open Meeting, 10th, Freudenstadt, West Germany, October 3-6, 1972, Reports. Munich. 631 A73-44899 Carl Manser Verlag; Hamburg, Verlag Brunke Carrels, 1972, p. 23-1 to 23-8. 7 refs. In German. A number of novel low-pressure preimpregnated materials are discussed, giving attention to questions of material specifications. Problems of the selection of suitable binders and reinforcement materials are discussed together with details of the manufacture of prepregs and the advantages of the preimpregnation process in comparison to a procedure involving wet lamination. Methods concerning the processing of prepregs are considered along with the tools to be used, questions of the manufacture of structural components, and specific cases illustrating the use of the new manufacturing process. These cases include components for conven- tional aircraft, the 'Airbus,' and the Sikorsky helicopter. G.R. A73-44899 ff Emission of sound from a rectangular plate vibrating under the action of pressure pulsations in a turbulent boundary layer (Izluchenie zvuka priamougol'noi plastinoi, kole- bliushchebia pod deistviem pul'satsii davleniia v turbulentnom pogranichnom sloe). R. A. Mkhitarov (Akademiia Nauk SSSR, Akusticheskii Institut, Moscow, USSR). Akusticheskii Zhurnal, vol. 19, July-Aug. 1973, p. 580-587. In Russian. A73-44916 # Distribution of losses in an annular cascade of an axial-flow compressor (Rozklad strat w kolowej palisadzie sprazarki osiowej). J. Krai (Instytut Lotnictwa, Warsaw, Poland). Roiprawy Inzynierskie, vol. 21, no. 2, 1973, p. 249-277. 28 refs. In .Polish. Published experimental data are analyzed in a study of factors affecting the distribution of total pressure losses in viscous flow of gas through annular cascades of axial-flow compressors. Three- dimensional aspects of the flow are examined along with their effects on boundary layer development and the formation of associated secondary flows resulting in vortices. Existing methods of calculating the magnitudes and radial distributions of pressure losses in axial-flow fans and compressors are reviewed. T.M. A73-44994 ff Program plan to develop airworthiness standards for STOL aircraft. R. A. Chubboy (FAA. Systems and Development Service, Washington, D.C.). Canadian Aeronautics and Space Journal, vol. 19, June 1973, p. 289-295. This paper outlines a joint French/UK/US simulator program to develop criteria for supporting airworthiness standards for powered- lift transport category aircraft. STOL considerations, test methodolo- gy and some preliminary results obtained on the Baseline Breguet 941 are discussed. The following impressions are significant. Multiple configuration changes following balked landing and/or one engine inoperative go-around may not pose a problem for STOL aircraft. Thrust response in the landing approach seems to influence man/ machine performance more than thrust margin, especially on go-around. Lateral/directional characteristics of the powered-lift aircraft are critical, especially during flare and immediately following touchdown In crosswlnd and/or turbulence. (Author) A73-44995 # Some results from tests In the NAE high Reynolds number two-dimensional test facility on shockless and other airfoils. L. H. Ohman, J. J. Kacprzynski, and D. Brown (National Aeronautical Establishment, Ottawa, Canada). Canadian Aeronautics and Space Journal, vol. 19, June 1973, p. 297-312. 26 refs. Results from investigations in the NAE high Reynolds number two-dimensional test facility on two classical NACA airfoils and two contemporary supercritical airfoils are presented. The results are compared with other published experimental data. Comparisons are also made with results from theoretical calculations performed at NAE for subcritical as well as supercritical flow, incorporating boundary-layer displacement effects for some subcritical Experimental and theoretical results compare favorably.' Com- parisons with other experimental data demonstrate good cor- respondence in some cases as well as gross discrepancies in other cases. For the latter, the discrepancies are attributed to Reynolds number effects or differences in experimental techniques. (Author) A73-45076 tf Burn-up of the high temperature products of incomplete combustion in a supersonic flow by a second injection of oxidizer (Dozhiganie vysokotemperaturnykh produktov nepolnogo sgoraniia v sverkhzvukovom potoke pri vtorichnom vpryske okirii- telia). Z. G. Shaikhutdinov, A. M. Rusak, V. M. Klevanskii, I. S. Saburov, and L. F. Shaikhinurova. Inzhenerno-Fizicheskii Zhurnal, vol. 25, Aug. 1973, p. 197-203. In Russian. A73-45088 ft Processing experimental aviation data. R. L. Lackman (National Center for Atmospheric Research, Boulder, Colo.). Atmospheric Technology, Sept. 1973, p. 44-48. 5 refs. The Research Aviation Facility (RAF) provides the atmospheric science community with an aircraft data gathering and data processing service. Several options of an existing computer program are available for processing aircraft data tapes. Aspects of standard data processing are discussed together with problems of special processing, data merging, data enhancement, and future software developments. It is pointed out that the acquisition of the Electra aircraft with its highly sophisticated instrumentation system has itself vastly expanded the RAF's data processing commitments. A new general processing program was developed in connection with new software developments. Aspects of future resource requirements are also considered. G.R. A73-45144 Toward reliable composites - An examination of design methodology. J. R. Eisenmann, B. E. Kaminski, D. L. Reed, and D. J. Wilkins (General Dynamics Corp., Convair Aerospace Div., Fort Worth, Tex.). Journal of Composite Materials, vol. 7, July 1973, p. 298-308. 9 refs. The current deterministic design approach is reviewed, and an alternate reliability-based design procedure is described which is more appropriate to the distinct behavioral characteristics of composite materials. The proposed procedure treats: load generation, material characterization, reliability apportionment, scaling, and complexity. (Author) A73-45153 j X-22A - The total in-flight simulator. J. L. Beilman (Calspan Corp., Buffalo, N.Y.). Aircraft Engineering, vol. 45, Sept. 1973, p. 8-12. Recognition of the urgent need for a systematic approach to obtain reliable flying qualities data in advance of design has led to the concept of the variable stability aircraft. By 1970, the original concept of the variable stability aircraft had reached maturity in the Total In-Flight Simulator (TIPS). The TIPS has been used for simulation of the USAF B-1 Bomber, the Concorde SST, and the space shuttle vehicle. The basic characteristics of the new aircraft, called the X-22A, are discussed together with Its variable stability system. G.R. A73-46154 # Alternating currant starter generators. D. 0. Burnt. Aircraft Engineering, vol. 45, Sept. 1973, p. 16-18, 21. An alternator directly coupled to a spool of a jet propulsion engine produces a variable frequency of ac supply. This variable frequency can be converted to a constant (400 Hz) frequency by a switching device known as a cycloconverter. The use of the variable frequency generator as a variable frequency motor with the objective to start up the main engine electrically is considered. Cycloconverter starter-generators are compared with the more conventional methods, such as turbine starters. G.R. 632 A73-45199 A73-45155 tf The use of single crystal blades. D. A. Petrov and A. T. Tumanov (Organisation fur Internationale Lizenzen. Moscow, USSR). Aircraft Engineering, vol. 45, Sept. 1973, p. 20, 21. Advantages of gas-turbine engines using single-crystal blades are connected with the absence of grain boundaries in the blade metal. In conventional castings grain boundaries are weak lines-along which premature damage can occur. At very high temperatures single- crystal blades can operate for about four times as long as conventionally cast blades. The technique developed in the USSR for obtaining single-crystal blades is free from the limitations imposed on the choice of crystallographic orientation in an approach used in the U.S. G.R. A73-45156 § Advantages of a fixed ground supply system. Aircraft Engineering, vol. 45, Sept. 1973, p. 30-32, 34. In March 1972, a new aircraft ground supply system was introduced at London Heathrow, UK, which in its operation to date has clearly indicated the advantages of a fixed installation in this service. The installation supplies ground power to the aircraft using Pier Four, Terminal One. The ground supply system is discussed, giving attention to motor-alternators, plant control cubicles, selector . switchboxes, the distribution cubicle, the busbar switchbox, the connector box, and fault protection devices. G.R. tests in order to select the version providing the mgiiesi increase in critical rotational speed subject to tradeoffs involving ease of conversion during scheduled maintenance operations. Modifications evaluated entailed changes in shaft curvature and in the length, diameter, and number of individual shaft segments. The selected final version features an enlarged cross section of one shaft segment and provides a 600 rpm (21%) gain in the critical rotational speed. T.M. A73-45196 ff Principal failures of turbines during turbine engine operation (Zasadnicze niesprawnosci turbin w czasie eksploa- tacji silnikow turbinowych). M. Mokrzyszczak and M. Stukonis (Instytut Techniczny Wojsk Lotniczych, Warsaw, Poland). Technika Lotnicza i Astronautyczna, vol. 28, Sept. 1973, p. 8-15. 5 refs. In Polish. Description of the main causes of in-service damage experienced by turbine blades in gas turbine engines. Engine operating conditions resulting in blade failure are defined, and the characteristic aspects and mechanisms of sustained damage are described for fatigue failure of blades at the airfoil section, fatigue fracture in fir-tree root attachments, damage produced by overheating in engines with axial-flow compressors, and. damage resulting from overheating in unsteady engine operation. T.M. A73-45162 Burning rate ttudiei of fuel air mixture! at high pressurei. J. D. Knapton, I. C. Stobie (U.S. Army, Ballistics Research Laboratories, Aberdeen Proving Ground, Md.l, and H. Krier (Illinois, University, Urbana, III.). Combustion and Flame, vol. 21, Oct. 1973, p. 211-220. 10 refs. High pressure burning studies of fuel air mixtures (mainly JP4 and air) were carried out in a closed chamber to determine what parameters control the maximum combustion rate and maximum pressure. The fuel was injected through shower-type nozzles into air at initial pressures of 2000-4000 psi. Densities of loading ranged 0.18-0.36 gm/cu cm, and the equivalence ratio ranged 0.6-2.7 fuel to air. A method for evaluating the burning velocity is presented. It was found that a wide variation in the burning velocity could be obtained with maximum burning velocities occurring at minimum fuel air mixing times. The pressure-time history during the closed vessel explosion agrees remarkably well with a time cubed dependence. Such pressure-time data are used to interpret the pressure rise predicted by a simple isothermal model. (Author) A73-45172 # Hypersonic flow about a spatial body with an attached (hock wave (Qlperzvukove obtikannla prottorovogo tila z prlednanoiu udarnolu khvilelu). L. I. Dzvonik (Klivs'ki! Derzhavnii Universltet, Kiev, Ukrainian SSR). Akademlla Nauk Ukralns'koi flSfl, DopovM. Sortie A • FMko-Tekhnlchnl I Matamatlchnl A/at/*/, vol. 35, Aug. 1973, p. 717-721. In Ukrainian. Concepts of the hypersonic theory of small perturbations are applied to solve a Riemann-Polncare1 boundary value problem formulated In an analysis of the characteristics of a flow about a slender rhomblform wing with an attached shock wave when the Mach number tends to Infinity. Functions describing the shock wave curvature are octalned. V.Z. A7346196 # Increasing the critical rotational spaad of the tail rotor drive shaft in SM-1 and SM-2 helicopters (Zwiekszenle llczby obrotow krytycznych walu napedu imlgla ogonowego iml- glowcow SM-1 I SM-2). A. Jarczyk (Instytut Techniczny Wojsk Lotniczych, Warsaw, Poland). Technika Lotnicza i Astronautyczna, vol. 28, Sept. 1973, p. 6, 7, 41. In Polish. Several structurally modified versions of the tubular segmented drive shaft used in the tail-rotor drive train of SM-1 and SM-2 helicopters were examined analytically and by full-scale vibration A73-4S197 H Reliability calculations for flight vehicles (Obliczanie niezawodnosci obiektow latajacych). J. Jazwinski, J. Migdalski, and W. Wieremiejczyk (Instytut Techniczny Wojsk Lot- niczych, Warsaw, Poland). Technika Lotnicza i Astronautyczna, vol. 28, Sept. 1973, p. 16-18. In Polish. Description of a method for estimating the reliability of repairable and nonrepairable flight vehicles (rockets, airplanes, helicopters, and parachutes). In the context of this article, reliability is understood as the measure of risk in using the particular vehicle at a given time under given physical conditions. The proposed graphical technique permits rapid estimates of (1) the probability that the vehicle will satisfy defined requirements through a given interval of time, (2) the cumulative risk function, and (3) the failure rate function. T.M. A73-4B198 # Modern structural materials in aviation (Wspolczesne materialy konstrukcyjne w lotnictwie). E. Gruszc- zynski (Instytut Techniczny Wojsk Lotniczych, Warsaw, Poland). Technika Lotnicza i Astronautyczna, vol. 28, Sept. 1973, p. 23-28. 15 refs. In Polish. The properties and applications of various structural materials in modern aircraft are discussed together with research and develop- ment efforts aimed at new materials and improved technological processes. Relative merits, drawbacks, and typical uses are described for aluminum alloys, steels, titanium alloys, magnesium alloys, beryllium alloys, and laminate composites incorporating single- crystal fibers, polycrystalline fibers, glass fibers, and fibers of complex structure. T.M. A73-4B199 ff Preparation of airport surfaces for htavy and supersonic aircraft (Przygotowanle nawlarzchni lotnlsk dla same- lotow ciezkich i naddzwiekowych). R. Grzywacz (Instytut Tech- niczny Wojsk Lotniczych, Warsaw, Poland). Technika Lotnicza I Aitronautycine, vol. 28, Sept. 1973, p. 29-31. In Polish. The need for special modifications of existing airport surfaces to accommodate heavy-load and supersonic aircraft is demonstrated by tabulating typical characteristics (static and dynamic load aspects, landing-gear configurations, and physical dimensions) of specific new cargo and SST airplanes. Attention is given to international regula- tions detailing length and width requirements as well as structural configurations of runway and taxi surfaces. T.M. 633 A73-45245 A73-45245 # Propeller blade vibrations (Drgania lopat smigla). J. Maryniak, W. Mierzejewski, and j. Krutul (Warszawa, Politechnika, Warsaw, Poland). Mechanika Teoretyczna i Stosowana, vol. 11. no. 3, 1973; p. 229-243. 11 refs. In Polish. Calculated modes and frequencies of natural vibrations for helicopter tail-rotor blades are'compared with experimental results. Measured values of mass distribution, moments of inertia, and stiffness are used as the input data for calculations. The rotor blade is represented by eleven segments and is treated as a discrete system. Six mathematical models of the blade are analyzed with allowance for rotational inertia of individual blade segments. Eigenmodes and frequencies of flexural, torsional, and torsional-flexural vibrations calculated for the six models are compared with resonance measure- ments. T.M. A73-45345 'Air piracy' and the latest work of ICAO on this subject (La 'piraterie aenenne' et les derniers travaux de I'OACI a ce sujet). G. Guillaume. Revue Franfaise de Droit Aerien, vol. 27, July-Sept. 1973, p. 257-260. In French. A73-45346 The development of civil air navigation in the People's Republic of China - Agreements with other states as well as the tasks and the position of the China Civil Aviation Corporation /CAAC/ (Le developpement de la navigation aenenne civile en Ripublique populaire de Chine - Les accords avec d'autres Etats ainsi que les tacfies et la position de la compagnie aenenne CAAC). J. L. Kneifel. Revue Franfaise de Droit Aerien, vol. 27, July-Sept. 1973, p. 261 -283. 16 refs. In French. A73-45264 * A comparison of the overall and broadband noise characteristics of full-scale and model helicopter rotors. J. W. Leverton and J. S. Pollard (Westland Helicopters, Ltd., Yeovil, Somerset, England). Journal of Sound and Vibration, vol. 30, Sept. 22, 1973, p. 135-152. 14 refs. Research supported by the Ministry qf Defence and NASA. The broadband noise generated by full-scale and model rotors is compared in terms of spectral content and the dependence on tip speed and rotor thrust/pitch angle. Low frequency broadband noise and high frequency broadband noise are studied separately and blade 'scaling' effects are outlined. The degree of agreement between measurements and theoretical and semi-empirical prediction methods is reviewed together with the directionality patterns. The parameters relating to the overall noise are also discussed. It is shown that in general good agreement is obtained between the full-scale and model rotors when considering spectral content and the dependency of the noise levels on tip speed and thrust. The scaling factors usually considered applicable to the low frequency broadband noise do not, however, appear to apply to either the model or full scale rotors. (Author) A73-45269 Compressibility and sonic boom (Com- presibilidad y estampido sonico). M. C. Alvarez (IBERIA, Lfneas Aereas de Espana, Madrid, Spain). Revista de Aeronautics y Astronautica, vol. 33, Aug. 1973, p. 601-615. 10 refs. In Spanish. The compressibility characteristics of a fluid can be quantitative- ly represented with the aid of the Bulk modulus. Differences in sound propagation for incompressible and compressible fluids are considered, giving attention to formulas for the sonic velocity and the effects of various parameters on this velocity. Conditions for the five flight velocity ranges as determined by the Mach numbers are discussed, taking into account the formation of the Mach cone, details of air particle behavior, shock waves, and heating effects. An analysis is conducted of the various factors affecting the sonic boom. The application of general principles is demonstrated by an investiga- tion of three specific hypothetical cases involving aircraft of different types. Sonic boom effects on water, land, and buildings are examined. • " G.R. A73-45309 Stability of a potential vortex with a non- rotating and rigid-body rotating top-hat jet core. M. Lessen, N. V. Deshpande, and B. Hadji-Ohanes (Rochester, University, Rochester, N.Y.), Journal of Fluid Mechanics, vol. 60, Sept. 18, 1973, pt. 3, p. 459-466. 8 refs. NSF-supported research. The stability of a potential vortex in the presence of a rotating and a nonrotating axial jet core is examined theoretically. The eigenvalue problem has been solved numerically, and the influence of the ratio of the strength of the vortex to the axial velocity of the jet is determined. Numerical values of the growth rates are obtained, and it is shown that the potential vortex becomes unstable in the presence of a rotating axial jet. • T.M. A73-45358 # Effect of a slipstream on the acoustic radiation of ultrasonic annular jets (Vpliv suputnogo potoku na akustichne viprominiuvannia nadzvukovimi kil'tsevimi strumeniami). V. O. Liutii and 0. I. Shvets' (Kiivs'kii Derzhavnii Universitet, Kiev, Ukrainian SSR). Akademiia Nauk Ukrains'koi RSR, Dopovidi, Seriia A - Fiziko-Tekhnichni i Matematichni Nauki, vol. 35, July 1973, p. 639-642. In Ukrainian. A setup with changeable nozzles is used in the measurement of slipstream effects on the acoustic radiation of annular jets at M 2.0, 3.1 and 3.6. The depressing effect of a slipstream on the acoustic wave expansion in ultrasonic annular jets is discussed. Decay of acoustic radiation with the increasing slipstream is noted. V.Z. A73-45373 Noise - Maplin and the new technology. P. G. Masefield. Flight International, vol. 104, Aug. 16, 1973, p. 301-309. The history and controversy surrounding the proposed third London airport at Maplin are reviewed. Maplin is seen as a planned development to reduce noise and to add runway capacity. The questions of whether the assumptions are correct about Maplin's potential benefit in relief of noise, whether there is a real requirement for more runway capacity, and Maplin's alleged environ- mental advantages are evaluated. In general, it is considered that the choice of Maplin would not be satisfactory. F.R.L. A73-45374 Hush-kits or new fans. M. J. T. Smith (Rolls-' Royce, Ltd., Engine Div., Derby, England). Flight International, vol. 104, Aug. 16, 1973, p. 318, 319. There are two alternative approaches to noise reduction. That offering the lowest initial cost is the concept of a single 'add-on' suppressor kit. The second approach involves a partial or complete re-engining of the aircraft. Refanning is an attempt to produce the noise signature of the new high-bypass engines without the expense of a complete engine redesign. It has been found possible to provide engine cycles at about half the bypass ratio of the RB.211 with a varying take-off thrust in the region of 14,000 to 16,000 Ib according to the fan and turbine design. F.R.L. A73-45377 j The combustion process in a pulsejet engine (Proces spalania w silniku pulsacyjnym). S. Wojcicki (Warszawa, Politechnika, Warsaw, Poland). Archiwum ProcesowSpalania, vol. 3, no. 1,1972, p. 51-57. In Polish. The combustion process in a pulsejet engine is described on the basis of experimental data obtained by direct and schlieren photog- raphy and by measurement of pressure distributions in the com- bustion chamber. It is shown that self-ignition in the combustion chamber is a consequence of the turbulent mixing of the inlet air and 634 A73-45547 fuel doses with combustion products remaining from the preceding cycle. Ignition by compression waves is not a necessary condition for continuous operation of the engine, and combustion gases containing burning particles from the previous cycle can provide ignition. Continuous operation is conditioned by the requirement for feed- back between pressure changes and the combustion rate. T.M. 1973, p. 258-271. 43 refs. In German. The changes in aviation laws, resulting from the continuous growth and new developments in air traffic are reviewed. Particular attention is given to liability situations where accidents are caused by flight controller errors or by malfunction of AFC equipment. It is shown that the liability regulations in the field of air traffic control have become obsolete and require a thorough revision. V.P. A73-45381 ft Some comments to mathematical interpreta- tion of performance characteristics of jet engine combustion chambers. O. Schurek (Vyzkumny a Zkusebni Letecky Ustav, Prague, Czechoslovakia). Archiwum Procesow Spalania, vol. 3, no. 2, 1972, p. 133-151. A survey is presented of the problems in analyzing combustion chambers of jet engines. The solution of the work is divided into partial blocks: analysis of throttling and altitude characteristics, the selection of the form and the type of chamber, and choice of the air-inlet law. The analysis proceeds by designing an atomization device, and then analyzing chamber pressure losses, the combustion efficiency, the ignition and extinguishing characteristics and the temperature profile. For the solution of individual analytical blocks, results of experimental works, some statistical techniques, and a digital computer have been employed. (Author) A73-45391 The POHWARO takeoff assist system (Start- hilfegerat POHWARO). P. Kiing. Plug Revue/Flugwelt International. Oct. 1973, p. 23-26. In German. The POHWARO (Pulsated Over-Heated WAter ROcket) system, developed in Switzerland, is described. By providing additional thrust, primarily, for military combat aircraft, the system provides higher loading levels, and permits takeoff from shorter runways and under critical temperature and weather conditions. An attractive feature of the system is its low cost of operation. V.P. A73-45475 RAT has hydraulic pitch change servo. P. W. Morris (Dowry Rotol, Ltd., Cheltenham, Glos., England). Hydraulics and Pneumatics, vol. 26, Oct. 1973, p. 87-90. An emergency power source for retaining control of an aircraft in the event of complete main engine failure must become available immediately when needed. The emergency power source must also have an extremely high standard of integrity. The ram air turbine (RAT) meets both requirements. The constant speed features of the turbine are discussed together with aspects of turbine installation, the hydraulic pitch control system, and the governor valve. Questions of RAT operation are considered along with details of hydraulic pump control, in-service testing, and checkout. G.R. A73-45529 # Universal equations for the laminar boundary layer on a body -of revolution in oblique flow (Universal'nye uravneniia laminarnogo pogranichnogo sloia na tele vrashcheniia v kosom gazovom potoke). L. I. Bogovaia. Akademiia Nauk SSSR, Uvestiia, Mekhanika Zhidkosti i Gaza, July-Aug. 1973, p. 32-41. 6 refs. In Russian. The laminar motion of a gas at an angle of incidence in the boundary layer on a body of revolution is examined. A solution is obtained by Loitsianskii's (1965) parametric method, in which the influence of the external flow and of the configuration of the body is taken into account by introducing three series of parameters. The corresponding system of universal equations is integrated numerically over a wide range of parameters and their combinations. V.P. A73-45399 A review of the American RPV scene. I. Stambler. Interavia, vol. 28, Oct. 1973, p. 1070-1073. The remotely piloted vehicle (RPV) can, in the opinion of (ts adherents, offer many of the capabilities of manned aircraft for a fraction of the cost. Applications being considered include several reconnaissance roles, electronic warfare systems, target acquisition, weapon delivery, air-to-air combat, and various combinations, of these. Vehicles in hardware form include both expendable and nonexpendable systems. A number of current RPV projects under- taken by various manufacturers are reviewed. It is emphasized that electronics are vital to the success of the overall RPV concept. F.R.L. A73-45540 # Approximate calculation of the cavitation flow past low-aspect-ratio wings (Priblizhennyi raschet kavitatsion- nogo obtekaniia kryl'ev malogo udlineniia). I.I. Efremov and R. A. Soroka. Akademiia Nauk SSSR, Izvestiia. Mekhanika Zhidkosti i Gaza, July-Aug. 1973, p. 166-170. In Russian. The system of singular integral equations of a cavitating low-aspect-ratio wing is reduced to one dimensional equations with the aid of the Lawrence (1951) approximation. The equations are solved numerically by the method of discrete singularities. Plots of cavitation number vs the cavity length for various aspect ratios and plots of the lift coefficient vs the aspect ratio for various cavitation numbers are presented. V.P. A73-45443 Liability and insurance in international air traffic (Haftung und Versicherung im internationalen Luftverkehr). I. H. P, Diederiks-Verschoor, .W. P. Heere, and A. Moll. Zeitschrift fur Luftrecht und Weltraumrechtsfragen, vol. 22, Oct. 1, 1973, p. 250-257. 15 refs. In German. (Translation). Research supported by the Rijksuniversiteit te Utrecht. International air-traffic liability agreements (which also have been declared applicable to national air-traffic by most of the signatory states) are examined in some detail. The problem of passenger accident insurance and aircraft (not cargo) insurance in international air-traffic is discussed. V.P. A73-45444 Flight safety, air traffic control, and liability (Flugskherheit, Luftverkehrskonstrolle und Haftung). E. Ruhwedel. Zeitschrift fur Luftrecht und Weltraumrechtsfragen, vol. ?2, Oct. 1, A73-4S542 # Determination of the impulses and moments imparted by shock waves to bodies of revolution (Ob opredelenii impul'iov sil i momentov, soobshchaemykh telam vrashcheniia udarnymi volnami). V. A. Kazakov. Akademiia Nauk SSSP, Izvestiia, Mekhanika Zhidkosti i Gaza, Ju!y-Aug. 1973, p. 186-190. In Russian. The three-dimensional problem of the unsteady supersonic flow past a body of revolution along which glides a weak incident shock wave is discussed for the case of constant flow parameters behind the shock front and for the case where the pressure gradient vanishes according to a linear law. The total impulses and moments imparted to the body during the transient process are computed. V.P. A73-45547 Nonunrform supersonic flow part wedges. S. Nadir (Northrop Corp., Aircraft Div., Hawthorne, Calif.). Zeitschrift fur angewandte Mathematik und Physik, vol. 24, May 25, 1973, p. 355-364. Consideration of the problem of the flowfield over pointed 635 A73-45547 wedges in an isoenergetic flow of thermally and calorically perfect gases in which the nonuniform incident flow is such that it results in attached shock waves. It is shown that the one-strip approximation of the method of integral equations is capable of predicting physically realistic surface pressure distributions. A comparison is made between theoretical predictions and experimental data in examples involving the determination of ramp surface pressures in two-dimensional inlets. A.B.K. 636 N73-31934 STAR ENTRIES N73-31927*# Aeronautical Research Inst. of Sweden. Stock- holm. RESEARCH ON THE SONIC BOOM PROBLEM. PART 1: SECOND-ORDER SOLUTIONS FOR THE FLOW FIELD AROUND SLENDER BODIES IN SUPERSONIC FLOW FOR SONIC BOOM ANALYSIS Final Report M. Landahl and P. Loefgren Washington NASA Oct. 1973 66 p refs (Grant NGR-52-120-001) (NASA-CR-2339; FFA-AU-621-P1-1) Avail: NTIS HC $3.50 CSCL 200 A second-order theory for supersonic flow past slender bodies' is presented. Through the introduction of characteristic coordinates as independent variables and the expansion procedure proposed by Lin and Oswatitsch. a uniformly valid solution is obtained for the whole flow field in the axisymmetric case and for far field in the general three-dimensional case. For distances far from the body the theory is an extension of Whitham's first-order solution and for the domain close to the body it is a modification of Van Dyke's second-order solution in the axisymmetric case. From the theory useful formulas relating flow deflections to the Whitham F-function are derived, which permits one to determine the sonic boom strength from wind tunnel measurements fairly close to the body. Author N73-31928*# National Aeronautics and Space Administration. Ames Research Center. Moffett Field. Calif. EXPERIMENTAL INVESTIGATION OF A LARGE-SCALE, TWO-DIMENSIONAL, M IXED -COMP RESSION INLET SYSTEM: INTERNAL PERFORMANCE AND DRAG AT TRANSONIC CONDITIONS, FREE STREAM MACH EQUALS 0.6 TO 1.28 Norman D. Wong and Warren E. Anderson Washington Oct. 1973 47 p refs (NASA-TN-D-7445: A-4775) Avail: NTIS HC $3.00 CSCL 20D A large scale, variable-geometry inlet system with a design Mach number of 3.0 was tested at Mach numbers from 0.6 to 1.28. Variable features for off-design operation are an adjustable- height ramp system and a translating cowl. Experimental results are presented for transonic rarnp and cowl positions showing the effect of throat boundary layer bleed and vortex generators on engine-face performance. Detailed pressure and force-balance data are used to evaluate transonic drag characteristics. Author N73-31929*# National Aeronautics and Space Administration. Ames Research Center. Moffett Field. Calif. INVESTIGATION. AT INLET LOCATIONS. OF FUSELAGE FLOW FIELDS AT TRANSONIC AND SUPERSONIC SPEEDS Lyndell S. King Washington Aug. 1973 124 p refs (NASA-TN-D-7364; A-4582) Avail: NTIS HC $4.25 CSCL 01C Wind tunnel tests were conducted to determine the flow distribution about fuselage configurations at transonic and supersonic speeds and at angles of attack up to 20 degrees. The models tested were approximately one-twelfth scale and consisted of a main fuselage forebody member and several attachable components. The components were mounted in several combinations to represent different possible configurations for tactical aircraft. Row distribution surveys were conducted at two inlet locations ahead of and under the wing to assess the effects of forebody geometry for the conditions indicated. The data indicate the influence of the canopy, nose droop, and fuselage shape on flow angularities in the forward survey plane. Author N73-31930*# Pratt and Whitney Aircraft. West Palm Beach. Fla. Research and Development Center. STUDY OF INDUCED LOAD AND STRESS. VOLUME 3 Final Report L. L. Coons. J. M. Reddecliff. A. E. Wemmell. and W. E. Young Nov. 1972 134 p refs (Contract NAS3-11216) (NASA-CR-72712 ; PWA-FR-3704-Vol-3) Avail: NTIS HC $8.75 CSCL 20D An analytical and experimental investigation into the effects of blade tip clearance on inducer performance and of leading edge sweepback on both blade pressure loading and performance was performed. Tip clearance flow was represented with a vortex flow model and measured data from previous inducer tests at three clearances were correlated with model predictions. A leading edge model was added to an existing inducer internal flow analysis, tests with two sweepbacks were conducted, and blade pressure and performance predictions were correlated with measured data. Author N73-31931*# National Aeronautics and Space Administration. Lewis Research Center, Cleveland. Ohio. WIND TUNNEL TESTS OF A 20 INCH DIAMETER 1.15 PRESSURE RATIO FAN ENGINE MODEL H. L. Wesoky and F. W. Steffen 1973 32 p refs Presented at the 9th Propulsion Joint Specialist Conf.. Las Vegas, Nev, 5-7 Nov. 1973; cosponsored by AIAA and SAE (NASA-TM-X-71445: E-7705) Avail: NTIS HC $3.75 CSCL 20D Aerodynamic and acoustic measurements at a typical STOL aircraft takeoff and landing velocity demonstrated that a 1.35 inlet lip area contraction ratio was superior to a 1.26 ratio at high nacelle incidence angles. Reverse thrust, obtained with a variable pitch rotor, was lower at the landing velocity, and the noise level higher, than at the static condition. High speed tests showed that, for the design cruise Mach number of 0.75. internal losses and external drag were 27 percent of the ideal fan net thrust, and propulsive efficiency was estimated to be 59 percent for an 85 percent efficient fan stage. Author N73-31932*# National Aeronautics and Space Administration. Lewis Research Center, Cleveland, Ohio. TWO-DIMENSIONAL ANALYTICAL AND EXPERIMENTAL PERFORMANCE COMPARISON FOR A COMPRESSOR STATOR SECTION WITH D-FACTOR OF 0.47 Nelson L. Sanger Washington Oct. 1973 41 p refs (NASA-TN-D-7425: E-7280) Avail: NTIS HC $3.00 CSCL 20D Analytically computed flow parameters were compared to measured values for the midspan double-circular-arc section of a stator in subsonic flow. Analytical procedures included calculations for inviscid flow, blade surface boundary layers, and loss coefficients. Comparisons were made at three incidence angles. Methods for prescribing the exit fluid angle in inviscid flow calculations were investigated. Measured loss coefficients were compared to calculated values. Two methods for predicting performance involving iterative use of ideal flow and boundary layer calculations were investigated. Author N73-31934# Aerospace Research Labs., Wright-Patterson AFB. Ohio. IN-PLANE AND OUT OF PLANE STABILITY DERIVATIVES OF SLENDER CONES AT MACH 14 637 N73-31935 Otto Walchner and Frank M. Sawyer Jul. 1973 27 p refs (AF Pro). 7064) (AD-765164; ARL-73-0090) Avail: NTIS CSCL 16/3 A 10-deg circular cone with various spherical and conical (45 degrees) nose bluntnesses of 1.7%. 10% and 25% was investigated in ARL's Mach-14 wind tunnel. Test results confirm that the static and dynamic stability coefficients are not equal in pitch and in yaw for nonzero angles of attack if the pitching moment becomes a nonlinear function of angle of attack due to nose blunting. The inequality of the in plane and out of plane stability derivatives was found at small angles of attack which are only fractions of the cone half angle. Author (GRA) N73-31935 Purdue Univ.. Lafayette. Ind. OPTIMAL MULTIPLE AIRCRAFT CONTROL FOR TERMINAL AREA APPROACH Ph.D. Thesis David Kelso Schmidt 1972 176 p Avail: Univ. Microfilms Order No. 73-15862 The specification of the curved approach paths and landing sequence for a group of aircraft desiring to land in a terminal area such that the terminal-area system performance is maximized was investigated. The multiple-aircraft problem includes the aspect of competition or cooperation between the vehicles by formulating the problem as a set of disconnected optimal trajectories. The flight paths are governed by kinematic equations of motion while in-flight and terminal-time separation inequality constraints between trajectories are imposed. The performance criterion for the system is the sum of the flight durations plus the inte- grated weighted accelerations of the aircraft. The solution approach employs penalty functions for the treatment of the inequality contraints and is based on the steepest descent algorithm. Dissert. Abstr. N73-31936 Rhode Island Univ.. Kingston. AN ANALYSIS OF THE RELATIONSHIP BETWEEN THE PARACHUTE SYSTEM PARAMETERS AND THEIR EFFECT ON THE SYSTEM IN FLIGHT Ph.D. Thesis Gregory C. DeSantis 1973 219 p Avail: Univ. Microfilms Order No. 73-16332 The cause and effect relationships which exist among the parameters associated with a parachute-payload system during the deployment and trajectory are analyzed. A computer simulation model with the capability of providing a wide range of flexibility in predicting the characteristics of full-scale and model systems in flight was developed. Prior to the study, most research was concentrated on the analysis of individual areas of parachute technology such as parachute inflation, snatch force, parachute filling time and steady state trajectories. The simulation integrates the specific characteristics of the parachute-payload system, airdrop aircraft and drop zone into a conglomerate analysis which can be exercised M many times as needed to evaluate the various parameters. Dissert. Abstr. N73-31937*! Boeing Vertol Co., Philadelphia, Pa. NOISE REDUCTION OF A TILT-ROTOR AIRCRAFT INCLUD- ING EFFECTS ON WEIGHT AND PERFORMANCE J. Gibs. W. Stepniewski. R. Spencer, and G. Kohler Jun. 1973 223 p refs Sponsored in part by Army Air Mobility R and D Lab., Ames Directorate (Contract NAS2-6784) (NASA-CR-114648; 0222-10062-1) Avail: NTIS HC $13.25 CSCL 20A Various methods for far-field noise reduction of a tilt-rotor acoustic signature and the performance and weight tradeoffs which result from modification of the noise sources are considered in this report. In order to provide a realistic approach for the investigation, the Boeing tilt-rotor flight research aircraft (Model 222), was selected as the baseline. This aircraft has undergone considerable engineering development. Its rotor has been manufactured and tested in the Ames full-scale wind tunnel. The study reflects the current state-of-the-art of aircraft design for far-field acoustic signature reduction and is not based solely on an engineering feasibility aircraft. This report supplements a previous study investigating reduction of noise signature through the management of the terminal flight trajectory. Author N73-31938# Defence and Civil Inst. of Environmental Medicine. Downsview (Ontario). EJECTION CLEARANCES IN CANADIAN FORCES AIR- CRAFT P. W. Cressman May 1973 12 p refs (DCIEM-936) Avail: NTIS HC S3.00 The knee clearance ejection envelopes are reported for all Canadian Forces aircraft presently in service. The effects of clothing, posture and restraint harness on ejection clearances are discussed in some detail. The maximum safe thigh length for each aircraft and the percentage of Canadian Forces pilots affected is presented for each aircraft. Author N73-31939*# National Aeronautics and Space. Administration. Flight Research Center, Edwards. Calif. ANALYTICAL STUDY OF TAKEOFF AND LANDING PERFORMANCE FOR A JET STOL TRANSPORT CONFIGU- RATION WITH FULL-SPAN. EXTERNALLY BLOWN. TRIPLE- SLOTTED FLAPS Harold P. Washington and John T. Gibbons Washington Oct. 1973 49 p refs (NASA-TN-D-7441: H-709) Avail: NTIS HC $3.00 CSCL QIC Takeoff and landing performance characteristics and field length requirements were determined analytically for a jet STOL transport configuration with full-span, externally blown, triple- slotted flaps. The configuration had a high wing, high T-tail. and four pod-mounted high-bypass-ratio turbofan engines located under and forward of the wing. One takeoff and three approach and landing flap settings were evaluated The effects of wing loading, thrust-to-weight ratio, weight, ambient temperature.: altitude on takeoff and landing field length requirements are discussed. '' Author N73-31940*# National Aeronautics and Space Administration. Ames Research Center, Moffett Field. Calif. LOW-SPEED WIND-TUNNEL INVESTIGATION OF THE LONGITUDINAL CHARACTERISTICS OF A LARGE-SCALE V A R I A B L E WING-SWEEP FIGHTER MODEL IN THE HIGH-LIFT CONFIGURATION William T. Eckert and Ralph L. Maki Aug. 1973 85 p Prepared in cooperation with Army Air Mobility R and D Lab., Moffett Field, Calif. (NASA-TM-X-62244) Avail: NTIS HC $6.75 CSCL 01C The low-speed characteristics of a large-scale model of.the U S. Navy/Grumman F-14A aircraft were studied in testa conducted in the Ames Research Center 40- by 60-Foot Wind Tunnel. The primary purpose of the program was the determination of lift and stability levels and landing approach attitude of the aircraft in its high-lift configuration. Tests were conducted at wing angles of attack between minus 2 deg and 30 deg with zero yaw. Data were taken at Reynolds numbers ranging from 3.48 million to 9.64 million based on a wing mean aerodynamic chord of 7.36 ft. The model configuration was changed as required to show the effects of glove slat, wing slat leading-edge radius, cold flow ducting, flap deflection, direct lift control (spoilers), horizontal tail, speed brake, landing gear and missiles. Author N73-31941*# Lockheed-California Co., Burbank. STUDY OF QUIET TURBOFAN STOL AIRCRAFT FOR SHORT HAUL TRANSPORTATION T. P. Higgins, E. G. Stout, and H. S. Sweet Washington NASA Jul. 1973 76 p refs Prepared in cooperation with Lockheed- Georgia Co.. Marietta (Contract NAS2-6995I 638 N73-31950 (NASA-CR-135481) Avail: NTIS HC $6.00 CSCL01C A study of quiet turbofan short takeoff aircraft for short haul air transportation was conducted. The objectives of the study were to: (1) define representative aircraft configurations, characteristics, and costs associated with their development. (2) identify critical technology and technology related problems to bfr resolved in successful introduction of representative short haul aircraft. (3) determine relationships between quiet short takeoff aircraft and the economic and social viability of short haul, and (4) identify high payoff technology areas. Author N73-31942# National Transportation Safety Board. Washington. D.C. AIRCRAFT ACCIDENT REPORTS: BRIEF FORMAT. US CIVIL AVIATION. ISSUE NO. 5 OF 1972 ACCIDENTS 9 Jul. 1973 344 p (NTSB-BA-73-7) Avail: NTIS HC $19.25 Aircraft accidents occurring in U.S. Civil Aviation during calendar year 1972 are reported. The reports concern 542 General Aviation and 13 U.S. Carrier accidents. The format presents the facts, conditions, circumstances, and probable cause for each accident. Author N73-31943# National Transportation Safety Board. Washington. D.C. AIRCRAFT ACCIDENT REPORT: JU 6 OSLOVE NSKI AEROTRANSPORT UAT) BOEING 707-321. YU-AGA. JOHN F. KENNEDY INTERNATIONAL AIRPORT. JAMAICA. NEW YORK. 13 AUGUST 1972 4 Apr. 1973 30 p (NTSB-AAR-73-7) Avail: NTIS HC $3.50 An aircraft accident involving a Boeing 707 aircraft which ran off the runway following an aborted takeoff at John F. Kennedy Airport. New York, on 13 August 1972 is reported. The pilot elected to abort the takeoff when the right cockpit window came open during the takeoff run. The speed and weight of the aircraft made it impossible to stop within the distance remaining and the aircraft impacted a blast fence at the end of the runway Author N73-31944# Tennessee Univ. Space Inst.. Tullahoma. FUNDAMENTAL RESEARCH ON ADVANCED TECHNIQUES FOR SONIC SUPPRESSION Final Report B. H. Goethert. Y. S. Pan. S. N. Chaudhuri. R. Kohl. H. Gruschka, and Philip Kessel Nov. 1972 209 p refs (Contract DOT-FA70WA-2260) (FAA-RD-73-4) Avail: NTIS HC $12.50 CSCL 20A A multiphase theoretical investigation on predicting and alleviating sonic boom intensity is described. A new theory to predict sonic boom intensity on the ground from wind tunnel tests using normal size models (as opposed to the very small models presently used) was developed. A relatively easy method to determine aircraft contours with desirable finite pressure rise times is presented, as is a method to determine phantom body shapes with desirable pressure rise times which can be simulated by heat addition to the flow upstream of the aircraft. It is shown that a slotted nozzle engine exhaust has the unique capability to shift lift from the solid surface of the wing to the region behind the wing, with a resulting reduction in sonic boom intensity. Author N73-31945*# Boeing Commercial Airplane Co.. Seattle. Wash. AIRCRAFT NOISE SOURCE AND CONTOUR ESTIMATION D. G. Dunn and N. A. Peart Jul. 1973 233 p refs (Contract NAS2-6969) (NASA-CR-114649: D6-60233) Avail: NTIS HC $13.75 CSCL 20A Calculation, procedures are presented for predicting the noise-time histories and noise contours (footprints) of five basic types of aircraft: turbojet, turofan. turboprop. V/STOL. and helicopter. The procedures have been computerized to facilitate prediction of the noise characteristics during takeoffs. flyovers, and/or landing operations. Author N73-31946*# Boeing Commercial Airplane Co.. Seattle. Wash. AIRCRAFT NOISE SOURCE AND COMPUTER PRO- GRAMS - USER'S GUIDE K. C. Crowley. M. A. Jaeger, and D. F. Meldrum Jul. 1973 112 p refs (Contract NAS2-6969) (NASA-CR-114650: 06-60234) Avail: NTIS HC $7.75 CSCL 20A The application of computer programs for predicting the noise-time histories and noise contours for five types of aircraft is reported. The aircraft considered are: (1) turbojet. (2) turbofan. (3) turboprop. (4) V/STOL. and (5) helicopter. Three, principle considerations incorporated in the design of the noise prediction program are core effectiveness, limited input, and variable output reporting. Author N73-31947*# Boeing Vertol Co , Philadelphia. Pa. V/STOL TILT ROTOR AIRCRAFT STUDY MATHEMATICAL MODEL FOR A REAL TIME SIMULATION OF A TILT ROTOR AIRCRAFT (BOEING VERTOL MODEL 222). VOLUME 8 H. Rosenstein. M. A. McVeigh, and P. A. Mollenkof Apr. 1973 570 p refs (Contract NAS2-6598) (NASA-CR-114601: D222-10061-1-Vol-8) Avail: NTIS HC $30.50 CSCL 01 C A mathematical model for a real time simulation of a tilt rotor aircraft was developed. The mathematical model is used for evaluating aircraft performance and handling qualities. The model is based on an eleven degree of freedom total force representation. The rotor is treated as a point source of forces and moments with appropriate response time lags and actuator dynamics. The aerodynamics of the wing. tail, rotors, landing gear, and fuselage are included. • Author N73-31949*# National Aeronautics and Space Administration. Langley Research Center. Langley Station. Va. A FIXED-BASE SIMULATION STUDY OF TWO STOL AIRCRAFT FLYING CURVED. DESCENDING INSTRUMENT APPROACH PATHS Margaret S. Benner, Richard H. Sawyer, and Milton D. Mclaughlin Washington Oct. 1973 35 p (NASA-TN-D-7298: L-8868) Avail: NTIS HC $3.00 CSCL 01C A real-time, fixed-base simulation study has been conducted to determine the curved, descending approach paths (within passenger-comfort limits) that would be acceptable to pilots, the flight-director-system logic requirements for curved-flight-path guidance, and the paths which can be flown within proposed microwave landing system (MLS) coverage angles. Two STOL aircraft configurations were used in the study. Generally, no differences in the results between the two STOL configurations were found. The investigation showed that paths with a 1828.8 meter turn radius and a 1828.8 meter final-approach distance were acceptable without winds and with winds up.to at least 15 knots for airspeeds from 75 to 100 knots. The altitude at roll-out from the final turn determined which final-approach distances were acceptable. Pilots preferred to have an initial straight leg of about 1 n. mi. after MLS guidance acquisition before turn intercept. The.size of the azimuth coverage angle necessary to meet passenger and pilot criteria depends on the size of the turn angle: plus or minus 60 deg was adequate to cover all paths except ones, with a 180 deg turn. Author N73-31950*# National Aeronautics and Space Administration. Flight Research Center. Edwards, Calif. FLIGHT INVESTIGATION OF A STRUCTURAL MODE 639 N73-31951 CONTROL SYSTEM FOR THE XB-70 AIRCRAFT Wilton P. Lock. Eldon E. Kordes. James M. McKay, and John H. Wykes (N. Am. Rockwell Corp.. Los Angeles) Washington Oct. 1973 83 p refs (NASA-TN-D-7420: H-732) Avail: NTIS HC $3.75 CSCL 01C A flight investigation of a structural mode control system termed identical location of accelerometer and force (I LAP) was conducted on the XB-70-1 airplane. During the first flight tests, the I LAP system encountered localized structural vibration problems requiring a revision of the compensating network. After modification, successful structural mode control that did not adversely affect the rigid body dynamics was demonstrated. The I LAP system was generally more effective in supersonic than subsonic flight, because the conditions for which the system was designed were more nearly satisfied at supersonic speeds. The results of a turbulence encounter at a Mach number of 1.20 and an altitude of 9754 meters indicated that the I LAP system was effective in reducing the vehicle's response at this flight condition. An analytical study showed that the addition of a small canard to the modal suppression system would greatly improve the automatic control of the higher frequency symmetric mode? Author N73-31951*# National Aeronautics and Space Administration. Plight Research Center, Edwards. Calif. SIMULATOR EVALUATION OF THE LOW-SPEED FLYING QUALITIES OF AN EXPERIMENTAL STOL CONFIGURATION WITH AN EXTERNALLY BLOWN FLAP WING OR AN AUGMENTOR WING Bruce G. Powers and David A. Kier Washington Oct. 1973 74 p refs (NASA-TN-D-7454; H-780) Avail: NTIS HC $3.50 CSCL 01C The low-speed flying qualities of an experimental STOL configuration were evaluated by using a fixed-base six-degree-of- freedom simulation. The configuration had either an externally blown flap (EBP) wing or an augmentor wing (AW). The AW configuration was investigated with two tails, one sized for the AW configuration and a larger one sized for the EBP configuration. The emphasis of the study was on the 70-knot approach task. The stability and control characteristics were compared with existing criteria. Several control systems were investigated for the normal four-engine condition and for the engine-out transient condition. Minimum control and stall speeds were determined for both the three- and four-engine operation. Author N73-31953*# Rockwell International Corp.. Downey. Calif. A METHODOLOGY FOR HYPERSONIC TRANSPORT TECHNOLOGY PLANNING E. M. Repic, G. A. Olson, and R. J. Milliken Washington NASA Sep. 1973 284 p refs (Contract NAS1-6024)(NASA-CR-2286; SD-73-SA-0019) Avail: NTIS HCS6.50 CSCL 01A A systematic procedure by which the relative economic value of technology factors affecting design, configuration, and operation of a hypersonic cruise transport can be evaluated is discussed. Use of the methodology results in identification of first-order economic gains potentially achievable by projected advances in each of the definable, hypersonic technologies. Starting with a baseline vehicle, the formulas, procedures and forms which are integral parts of this methodology are developed. A demonstration of the methodology is presented for one specific hypersonic vehicle system Author N73-31954# Advisory Group for Aerospace Research and Development. Paris (France). ESCAPE MEASURES FOR COMBAT HELICOPTER CREWS Aug. 1973 39 p refs (AGARD-AR-62) Avail: NTIS HC S4.00 A study was conducted to determine the requirements and characteristics of escape systems for use with 'helicopters. It was stated that escape systems are feasible, but that the rotary wing creates the greatest obstacle to emergency seat ejection. It was recommended that helicopter escape concepts be considered under the following categories: (1) an escape system for retrofit into helicopters already in production or in service, (2) an escape system for a near-term solution, and (3) an escape system for a far-term solution. The conclusion of the study was that a retrofittable escape system is practical only if it requires an absolute minimum of development time and does require major changes to the helicopter. The only likely canidates to satisfy the requirement are manual bailout or sideward ejection. Author N73-31956*# National Aeronautics and Space Administration. Flight Research Center. Edwards. Calif. FLIGHT CALIBRATION TESTS OF A NOSE-BOOM- MOUNTED FIXED HEMISPHERICAL FLOW-DIRECTION SENSOR Katharine H. Armistead and Lannie D. Webb Washington Oct. 1973 29 p refs (NASA-TN-D-7461: H-779) Avail: NTIS HC $3.00 CSCL 01C Flight calibrations of a fixed hemispherical flow angle-of-attack and angle-of-sideslip sensor were made from Mach numbers of 0.5 to 1.8. Maneuvers were performed by an F-104 airplane at selected altitudes to compare the measurement of flow angle of attack from the fixed hemispherical sensor with that from a standard angle-of-attack vane. The hemispherical flow-direction sensor measured differential pressure at two angle-of-attack ports and two angle-of-sideslip ports in diametrically opposed positions. Stagnation pressure was measured at a center port. The results of these tests showed that the calibration curves for the hemispherical flow-direction sensor were linear for angles of attack up to 13 deg. The overall uncertainty in determining angle of attack from these curves was plus or minus 0.35 deg or less. A Mach number position error calibration curve was also obtained for the hemispherical flow-direction sensor. The hemispherical flow-direction sensor exhibited a much larger position error than a standard uncompensated pilot-static probe. Author N73-31957*# United Aircraft Corp., Stratford, Conn. Sikorsky Aircraft Div. APPLICATION OF COMPOSITES TO HELICOPTER AIR- FRAME AND LANDING GEAR STRUCTURES Technical Report, Jul. 1972 - Feb. 1973 M. J. Rich, G. P. Ridgley. and D. W. Lowry Sep. 1973 138 p refs Sponsored in part by Army (Contract NAS1-11688) (NASA-CR-112333) Avail: NTIS HC $9.00 CSCL01C A design study has indicated that advanced composite helicopter airframe structures can provide significant system cost advantages. The most successful concept was found to be all-molded composite modular panels which provide integral skin/stringer and frame subassemblies. Based on present information it is estimated that a prototype composite airframe would cost approximately four percent more than a protoype metal frame. The difference \9 due primarily to the higher engineering design time, as the increased materials cost is largely offset by reduction of fabrication labor costs. Author N73-31958*# National Aeronautics and Space Administration. Plight Research Center. Edwards, Calif. SUMMARY OF STABILITY AND CONTROL CHARACTERIS- TICS OF THE XB-70 AIRPLANE Chester H. Wolowicz and Roxanah B. Yancey Washington Oct. 1973 56 p refs (NASA-TM-X-2933: H-781) Avail: NTIS HC $3.50 CSCL 01C The stability and control characteristics of the XB-70 airplane were evaluated for Mach numbers up to 3.0 and altitudes up to 21.300 meters (70.000 feet). The airplane's inhorent longitu- 640 N73-31965 dinal characteristics proved to be generally satisfactory. In the lateral-directional modes, the airplane was characterized by light wheel forces, low static directional stability beyond approximately 2 deg of sideslip, adverse yaw response to aileron inputs throughout the entire Mach number range, and negative effective dihedral with wingtips full down. At subsonic Mach numbers, with the flight augmentation control system off. the light wheel forces and adverse yaw response to aileron inputs caused the pilots to minimize use of the ailerons. At supersonic Mach numbers, with the augmentation system off. the adverse yaw due to aileron and the negative effective dihedral were conducive to pilot- induced oscillations. Author N73-31969*# National Aeronautics and Space Administration. Lewis Research Center. Cleveland, Ohio. COMPARISON OF GROUND AND FLIGHT TEST RESULTS USING A MODIFIED F106B AIRCRAFT Fred A. Wilcox 1973 20 p refs Presented at 9th Propulsion Joint Specialist Conf.. Las Vegas. Nev., 5-7 Nov. 1973: sponsored by AIAA and SAE (NASA-TM-X-71439; E-7695) Avail: NTIS HC $3.00 CSCL 01C Two aft underwing nacelles housing afterburning J85 engines were added to an F106 to study exhaust nozzles in flight at Mach numbers up to 1.3. Installation effects were determined for several nozzles by comparing flight data to data from an isolated wind tunnel model. Reynolds number effects were studied at subsonic flight speeds for nozzles intended for use with afterburning turbofan engines. A wide range of Reynolds number was obtained by,flying the F106 over a range of altitude and by using 5 and 22% wind tunnel models of the F106. A contoured nozzle had a boattail drag as low as that of a longer circular •re nozjle over the Reynolds number range studied. Author N73-31960# Royal Netherlands Aircraft Factories Fokker, Amsterdam. RATIONAL CALCULATION OF DESIGN GUST LOADS IN RELATION TO PRESENT AND PROPOSED AIRWORTHI- NESS REQUIREMENTS J. Yff [1973] 12 p refs Presented at AGARD Symp. on Flight in Turbulence, Bedfordshire. United Kingdom (Fok-K66) Avail: NTIS HC $3.00 Accurately calculated gust loads for three short haul aircraft have been used to: (1) Compare PSD and discrete gust methods: (2) compare PSD mission analysis and design envelope results; (3) compare PSD results for vertical and lateral gusts: and (4) study in detail the specific problems of T-tails. Author N73-31961| Technische Univ., Berlin (West Germany). Inst. fuer Luft- und Raumfahrt. DESIGN STUDY OF AN ELECTRONIC LANDING DISPLAY FOR STOL AIRCRAFT [GEDANKEN ZUR AUSLEGUNG EINES ELEKTRONISCHEN LANDEDISPLAYS FUER STOL- FLUGZEUGE] Wolfgang Holatein 1973 37 p refs In GERMAN Presented at the OGLR-DGON Symp. on Neue Anflug- und Landeverfahren. Ouesseldorf, 2-4 May 1973 (DGLR-Paper-73-038) Avail: NTIS HC $4.00 The design of landing display devices for- STOL aircraft, was investigated on the basis of information presentation and information content. A proposal is made for a contact analogous landing display.'which includes the perspective representation of the mean flight path, information about the actual flight status, predisplay of flight path coordinates, and boundary values for the flight parameters. An approach procedure using the im- proved display is described. ESRO N73-31962| Technische Universitaet. Brunswick (West Germany). Inst. fuer VenVehr. Eisenbahnwesen und Verkerhs- sicherhait-Sonderforschungsbereich Flugfuehrung. FLIGHT CONTROL PROBLEMS REGARDING STEEP APPROACH [FLUGFUEHRUNGSPROBLEME DES STEIL- ANFLUGES] R. Brockhaus 1973 35 p refs In GERMAN Presented at the DGLR-DGON Symp. of Neue Anflug- und Landeverfahren. Duesseldorf, 2-4 May 1973 (DGLR-Paper-73-027) Avail: NTIS HC $3.75 Some problems concerning steep approach landings and in particular flight control, are discussed. The flight control problem was one of the main reasons the extreme requirements of vertical landing was relaxed, and why. with respect to flight equipment and flight methods, little difference is to be found between steep landing and conventional jet landing. Although all equipment necessary for steep landing is available. STOL traffic will be limited to approach angles of 6 deg. for economic reasons. ESRO N73-31963# Technische Universitaet. Brunswick (West Germany). Lehrstuhl fuer Flugmechanik. LONGITUDINAL MOTION OF AN AIR LINER DURING STEEP APPROACH [ZUR LAENGSBEWEGUNG EINES VERKEHRSFLUGZEUGS BEI STEILEN ANFLUEGEN] G. Bruening, J. Lademann. and D. Schafranek 1973 24 p ref In GERMAN Presented at the DGLR-DGON Symp. on Neue Anflug- und Landeverfahren, Duesseldorf, 2-4 May 1973 (DGLR-Paper-73-023) Avail: NTIS HC 53.25 Calculations were carried out on a Boeing 707 aircraft in order to assess the effects on longitudinal stability of steep approach landings. The investigations point out that the present passenger aircraft can perform steeper than usual landings. The sinking velocity will increase as the path velocity remains unchanged. In order to avoid too much throttling of the engines, the air brakes should be lowered. The dynamic longitudinal stability is only slightly disturbed. The angle of attack oscillation will be slightly undampened. the phugoid dampened. A glide path of 3 deg is recommended. ESRO N73-31964# Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt, Brunswick (West Germany). Inst. fuer Ftugfuehrung. MONITOR DISPLAY FOR AUTOMATICALLY CONTROLLED STEEP APPROACH [EIN MONITORDISPLAY FUER AUTOMATISCH GEREGELTE STEILANFLUEGE] Hans-Dieter Schenk and Josef Thomas 1973 8 p refs In GERMAN Presented at the DGLR-DGON Symp. on Neue Anflug- und Landeverfahren, Duesseldorf. 2-4 May 1973 (DGLR-Paper-73-031) Avail: NTIS HC $3.00 A display for monitoring automatic steep approach was designed. This display shows a sideways view of the curved approach profile with a mobile aircraft symbol and a rotating flight path vector. The equipment was investigated in a flight simulator, and improved. A flight test, as well as further investigations concerning the operational usefulness of the equipment, are in preparation. ESRO N73-31965# Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt. Brunswick (West Germany). Inst. fuer Flugmechanik. FLIGHT MECHANICAL PROBLEMS IN LANDING AP- PROACH WITH DIRECT LIFT CONTROL, EXEMPLIFIED BY HFB 320 HANSA [FLUGMECHANISCHE PROBLEME BEIM LANDEANFLUG MIT DIREKTER AUFTRIEBSSTEUERUNG AM BEISPIEL DER HFB 320 HANSA] D. Hanke and H.-H. Lange 1973 32 p refs In GERMAN Presented at the DGLR-DGON Symp. on Neue Anflug- und Landeverfahren, Duesseldorf. 2-5 May 1973 (DGLR-Paper-73-024) Avail: NTIS HC $3.75 A possibility for reducing flight control problems in steep approach landing by direct lift control is discussed. The possibilities and limitations of direct lift controls are presented for the HFB 320 Hansa aircraft, by means of simulation and flight results. The first experiences with steep, noise-reducing. 2 segment ap- proaches, using the HFB 320. are reported. ESRO 641 N73-31966 N73-31966# Messerschmitt-Boelkow-Blohm G.m.b.H.. Hamburg (West Germany). EFFECTS. AND THEIR SIGNIFICANCE OF NEW APPROACH METHODS ON COCKPIT DESIGN [AU SWIRKU NGEN NEUER ANFLUGVERFAHREN AUF DIE COCKPITAUSLE- GUNG UND MOEGLICHKEITEN IHRER BERUECKSICHTI- GUNG] Haeuser 4 May 1973 23 p In GERMAN Presented at the DGLR-DGON Symp. on Neue Anflug- und Landeverfahren, Duesseldorf. 2-4 May 1973 (MBB-UH-07-73-0; DGLR-Paper-73-033) Avail: NTIS HC $3.25 The layout of cockpits is discussed in view of new landing approach methods. Parameters for cockpit layouts, based on the flight control functions to be executed, are developed, and modifications are introduced as a result of new approach methods. ESRO N73-31967# Messerschmitt-Boelkow-Blohm G.m.b.H.. Otto- brunn (West Germany). Unternehmensbeceich Flugzeuge. CONTROL TECHNIQUE IN STEEP APPROACH OF ROTARY WING AIRCRAFT [REGELUNGSTECHNIK BEI STEILAN- FLUEGEN VON DREHFLUEGLERN] Wolfgang Kubbat May 1973 26 p In GERMAN Presented at the DGLR-DGON Symp. on Neue Anflug- und Landeverfahren. Duesseldorf. 2-4 May 1973 (MBB-UFE-1021-0; DGLR-Paper-73-029) Avail: NTIS HC $3.50 Feedback control for flexible landing approach profiles of rotary wing aircraft was investigated. The feedback control circuit, in which the state vector contains 8 variables, is described. Solutions to the linearized state equation are illustrated by examples with results of simulation, during which straight-line, curved, and spatially curved approaches were investigated. ESRO N73-31968# Messerschmitt-Boelkow-Blohm G.m.b.H.. Otto- brunn (West Germany). NOISE REDUCING METHODS FOR STOL AIRCRAFT APPROACH AND TAKE-OFF [LAERMREDUZIERENDE AN- UND ABFLUGVERFAHREN FUER STOL-FLUGZEUGE] K. Weise and H. Anders 3 May 1973 43 p refs In GERMAN Presented at the DGLR-DGON Symp. on Neue Anflug- und Landeverfahren. Duesseldorf. 2-4 May 1973 (MBB-UH-06-73-O: DGLR-Paper-73-039) Avail: NTIS HC $4.25 The noise propagation of three projected STOL aircraft was investigated during takeoff and approach flight. It was shown that takeoff noise can be reduced a few dB by thrust reduction (three segment takeoff profile) near airports. As with CTOL aircraft, the landing paths should be as steep as possible, and landing flaps and gear should be lowered at low altitude. By using all possibilities during landing, obtainable noise reduction can be considerable. Keeping to the exact flight path was also found to be noise reducing. ESRO are shown for a flight path angle of 15 deg over the ILS approach. Some necessary prerequisites for a steep landing approach by instruments are briefly considered. ESRO N73-31970# Bodenseewerk Geraetetechnik G.m.b.H.. Ueberlin- gen (West Germany). PROBLEMS INVOLVED IN DEVELOPING AN INTEGRATED FLIGHT CONTROL SYSTEM WITH EMPHASIS ON CURVED FLIGHT PATH PROFILES [REALISIERUNGSPROBLEME EINES INTEGRIERTEN FLUGREGELUNGSSYSTEMS UNTER BESONDERER BERUECKSICHTIGUNG GEKRUEMMTER FLUGBAHNPROFILE] H. Boehret 1973 32 p refs In GERMAN Presented at the D G L R - D G O N Symp. on Neue Anflug- und Landeverfahren. Duesseldorf. 2-4 May 1973 (DGLR-Paper-73-030) Avail: NTIS HC $3.75 An integrated flight control system. FRG 70, which is especially adapted to curved flight path profiles, is presented. The feedback control parameters are coupled to elevators and thrust, which limitation facilitates the realization of this principle. The system is characterized by a precise matching to the aerodynamic flow conditions and high passenger comfort. The exact path guidance is supported by a path angle dependent thrust control, allowing for larger thrust rest. The properties of the integrated system were analyzed during over 500 automatic approaches and landings. They can be improved by direct lift controls and by using a monitor display. ESRO N73-31971# Dornier-Werke G.m.b.H., Friedrichshafen (West Germany). COMPARISON OF METHODS FOR FLIGHT TESTS AND THEIR EVALUATION FOR THE DETERMINATION OF CHARACTERISTICS AND PERFORMANCE OF MODERN JET A I R C R A F T [VERGLEICH VON VERFAHREN ZUR DURCHFUEHRUNG UND AUSWERTUNG VON FLUGVER- SUCHEN ZUR BESTIMMUNG VON EIGENSCHAFTEN UND LEISTUNGEN MODERNER STRAHLFLUGZEUGE] U. VonMeier, H. Ruf, H. Friedrich. W. Kohl, H. J. Munser, and H. Wuennenberg Bonn Bundeswehramt 1973 169 p refs In GERMAN; ENGLISH summary Sponsored by Bundesmin. Fuer Verteidigung (BMVg-FBWT-73-12) Avail: NTIS HC $10.50: Bundeswehramt 25 DM Five techniques for analyzing the stability derivatives of a G91T aircraft were compared. They included manual evaluation of special flight maneuvers, time vector method, forced oscillation method, analog matching, and regression analysis. Parameters taken into account were elapsed time, equipment for flight tests, data reduction, and result quality. It was shown that several measuring and evaluation techniques should be used in parallel. The advantages and disadvantages of the different techniques are discussed. ESRO N73-31969# Messerschmitt-Boelkow-Blohm G.m.b.H., Otto- brunn (West Germany). STEEP APPROACH LIMITS FOR ROTARY WING AIRCRAFT [UEBER DIE GRENZEN VON STEILA NFLU EG EN MIT DREHFLUEGLERN] M. Rade 1973 8 p refs In GERMAN Presented at the DGLR-DGON Symp. on Neue Anflug- und Landeverfahren. Duesseldorf. 2-4 May 1973 (MBB-UD-101-73-0: DGLR-Paper-73-026) Avail: NTIS HC $3.00 The flight characteristics and boundary conditions which affect a steep approach are described for rotary wing aircraft. The limits for steep instrument approach are presented, and experiences in flight operation are depicted. Essential advantages N73-31972# Calspan Corp.. Buffalo. N.Y. DEVELOPMENT AND EVALUATION OF AN AUTOMATIC DEPARTURE PREVENTION SYSTEM AND STALL INHIBI- TOR FOR FIGHTER AIRCRAFT Final'Report Robert T. N. Chen. Fred D. Newell, and Arno E. Schelhorn Wright-Patterson AFB. Ohio AFFDL Apr. 1973 126 p refs (Contract F33615-72-C-1162: AF Proj. 8225: AF Proj 8219) (AD-764767; CALSPAN-AK-5112-F-1; AFFDL-TR-73-29) Avail- NTIS CSCL 01/3 The report documents the conceptual design, breadboard development and pilot-in-the-loop evaluation of an automatic departure prevention system and a stall inhibitor for fighter aircraft. Using the A-7D as the study aircraft, a departure boundary characterized by alpha and beta was determined from the available data. This departure boundary was then used to help design an 642 N73-31980 automatic departure preventer and a stall inhibitor. An automatic departure prevention device as described in the report works smoothly and will benefit the A-7 aircraft. With just the departure preventer, the pilots could maneuver freely, with great confidence and use the full capability of the airplane, well beyond the present departure boundary. (Modified author abstract) GRA N73-31973# Air Force Inst. of Tech.. Wright-Patterson AFB. Ohio. School of Engineering. PREDICTING HEADING TASK FLYING QUALITIES WITH PAPER PILOT M.S. Thesis Calvin Ronald Taylor Jun. 1973 136 p refs (AD-764695: GE/MA/73-1) Avail: NTIS CSCL 01/3 A mathematical model for predicting the pilot rating of a fighter aircraft in a precision heading task is described. The model includes the lateral-directional aircraft equations of motion, a stochastic gust model, a pilot model with four free pilot parameters, and a pilot rating expression that is a function of rms heading angle, rms yaw rate, and rms roll rate. The pilot gains and lead time constants are selected to minimize the pilot rating expression. The resulting minimum is used to compute a heading paper pilot rating. The heading paper pilot rating was computed for 32 flight conditions at different gust intensities for the F-5 and A-7 aircraft. Heading paper pilot ratings agree well with the actual ratings for the F-5, but are low for the A-7. In addition, there is good correlation between computed and actual rms heading angle, rms yaw rate, and rms slideslip. Author (GRA) IM73-31974# Air Force Inst. of Tech.. Wright-Patterson AFB, Ohio. School of Engineering. AN IMPROVED METHOD OF PREDICTING AIRCRAFT LONGITUDINAL HANDLING QUALITIES BASED ON THE MINIMUM PILOT RATING CONCEPT M.S. Thesis John D. Arnold Jun. 1973 152 p refs (AD-764696; GGC/MA/73-1) Avail: NTIS CSCL 01/3 A fixed-base simulation of some, of the flight tests in the USAF/CAL variable stability T-33 aircraft was performed. The task was maintaining pitch attitude in the presence of vertical turbulence. The root-mean-square state data and parameters in a linear pilot model were determined from the simulation. These items were correlated with the Cooper-Harper Pilot Ratings. This led to the development of a pilot-rating expression based on rms state errors and pilot workload. This rating expression was used in a digital computer program to accurately predict pilot ratings and rms state errors using only the aircraft stability derivatives, airspeed, and altitude as inputs. Author (GRA) N73-3197B| Air Force Inst. of Tech., Wright-Patterson AFB, Ohio. School of Engineering. DESIGN AND INVESTIGATION OF A WIND-SHEAR-PROOF CONTROL SYSTEM FOR AUTOMATIC LANDING M.S. Thttll Loull Q. Trlvett Jun. 1973 91 p reft (AD-764697; GQC/MA/73-4) Avail: NTIS CSCL 01/2 An analog computer simulation of the longitudinal portion of an All-Weather Landing System Is prasentad. Tha linearized longitudinal equations of motion of a DC-8 aircraft during landing approach are converted to state-variable form to facilitate the analog simulation. An Advanced Automatic Flight Control System is added and the approach phase of an automatic landing is simulated. A severe turbulence atmospheric environ- ment consisting of wind gusts and wind shears is an integral part of the simulation. A systematic method is presented for developing a Kelman Filter based wind-shear-proofing system to reduce deviations from glide slope caused by wind'shears. (Modified author abstract) GRA N73-31978# Air Force Inst. of Tech., Wright-Patterson AFB. Ohio. School of Engineering. PREDICTING PITCH TASK FLYING QUALITIES USING PAPER PILOT M.S. Thesis Robert B. Johnson Jun. 1973 155 p refs (AD-764698: GGC/MA/73-2) Avail: NTIS CSCL 01/3 A mathematical model for predicting the pilot rating of an aircraft in a pitch tracking task is described. The model includes the longitudinal-directional aircraft equations of motion, a stochastic gust model, a pilot model with two free parameters, and a pilot rating expression that is a function of rms pitch angle, rms pitch rate, and the pilot lead time constant. The pilot parameters are then adjusted to provide at least a 20% stability margin, and the adjusted pilot parameters are used to compute a Flypaper Pilot rating of the aircraft/gust configuration. The Flypaper Pilot rating was computed for 32 aircraft/gust configurations. A range of actual ratings from 2 to 8 was encountered and the Flypaper Pilot ratings agree quite well with the actual ratings. Author (GRA) N73-31977# Uniroyal Tire Co.. Detroit. Mich. CONTINUOUS WOUND TOROIDAL AIRCRAFT TIRE Final Report. 17 Mar. 1970 - 9 Feb. 1973 Edwin Sj English and Jerome J. Wojciechowski Mar. 1973 35 p (Contract F33615-70-C-1775: AF Proj. 1369) (AO-764888; AFFDL-TR-73-35) Avail. NTIS CSCL 01/3 The primary objective of the program was to establish basic design requirements for a toroidal continuous wound aircraft tire concept. Using these basic design requirements, tires were fabricated. and shipped to the Flight Dynamics Laboratory at WPAFB for their evaluation so as to aid in determining the performance characteristics of the toroidal tire concept on military aircraft applications. Author (GRA) N73-31979# Naval Aerospace Medical Research Lab.. Pensacola Fla. HUMAN FACTORS APPROACH TO AIRCRAFT ACCIDENT ANALYSIS Richard H. Shannon and Wayne L Waag 18 Jun. 1973 46 p refs (AD-764868: NAMRL-1184) Avail: NTIS CSCL 01/2 Naval Accident reports involving the P-3 and F-4 aircraft were examined over seven and five-year periods, respectively. The critical incident technique was used to catalogue, describe, and analyze operational flight crew errors in both aircraft. An in-depth study was performed in order to identify those problems which were common as well as specific to both aircraft. The P-3 and F-4 aircraft were selected because of their completely different fleet missions and handling characteristics. From the F-4 accident reports, 437 human errors were isolated while the P-3 reports contained 345 errors. Twenty-eight major error categories emerged from the analysis of these errors. The accident reports were further analyzed for the errors which both aircraft had In common. Twenty common error groups were found to occur In the P-3 and the F-4, representing 22.9% and 18.8% of the total errors, respectively. The flight segment of Takeoff/ Landing, and the error type of Procedures, shared the moat commonality across the two aircraft. The results of this investigation suggest that although common errors can be isolated across highly dissimilar aircraft with highly different flight missions, they comprise a relatively small percentage of total errors. By far, the majority of errors concerned characteristics unique to the particular aircraft in question. Implications in the remedial areas of creyv coordination, training, discipline and design are discussed. Author (GRA) N73-31980# CADCOM, Inc.. Annapolis, Md. SIMULATION OF THE COMPATIBILITY OF AN AIR CAPABLE SHIP AND A VTOL AIRCRAFT Final Report, 16 Jun. 1972 • Mar. 1973 George H. Daffer and David F. Rogers Mar. 1973 208 p refs 643 N73-31981 (Contract N00014-72-C-0531; NR Proj. 215-208) (AD-764865: CADCOM-73-6) Avail: NTIS CSCL 01/3 An interactive computer simulation. LARC-I. has been designed to solve the non-linear equations of motion of a generalized VTOL aircraft taking off from or landing on the deck of a ship moving in an irregular or random seaway. This version of LARC-I is limited to longitudinal motions, but is designed for eventual expansion to all degrees of freedom. The LARC-I programs makes use of ship motion amplitudes and frequencies derived separately in a ship motions program, wherein the forcing functions of the seaway are based on a stochastic representation of the waves for any given sea state. The pitching and heaving motions of the ship are transmitted to the aircraft by a realistic simulation of the landing gear. (Modified author abstract) GRA N73-31981# Defense Documentation Center. Alexandria, Va. HELICOPTER ENGINES AND ROTORS Report. Bibliography, Jan. 1968 - Mar. 1973 Jul. 1973 454 p refs (AD-764900: DDC-TAS-73-48) Avail: NTIS CSCL 01/3 The bibliography comprises annotated citations of 300 unclassified reports dealing with helicopter engines and rotors. The following references are on some of the topics dealing with the subject: helicopter engines, rotor materials, rotor hover, rigid rotors, hot cycle rotors, rotor blades, heavy-lift rotors, rotor noise, and flight control systems. Corporate Author-Monitoring Agency, Subject, Title. Personal Author,' Contract, and Report Number Indexes are included. Author (GRA) N73-31984# Naval Ship Research and Development Center, Bethesda, Md. Aviation and Surface Effects Dept. HIGHER HARMONIC CIRCULATION CONTROL ROTOR MODEL - MODEL INSTRUMENTATION AND DATA ACQUISITION Michael B. Stone Apr. 1973 44 p refs (AD-765320: TN-AL-288) Avail: NTIS CSCL 01/3 A higher harmonic circulation control rotor was tested in the 8 ft x 10 ft subsonic wind tunnel at various advance ratios, blade tip Mach numbers, blowing air pressures, shaft angles and collective angles. The model was instrumented with strain gages, pressure transducers, thermocouples, magnetic pick-ups and a pitch-roll trim resolver. This information was recorded on an analog to digital acquisition system and on P.M. tape recorders for later digitization. The purpose of the report is to provide descriptive documentation of the model instrumentation and data acquisition portion of the test, and there is no attempt made to elaborate on helicopter or higher harmonic theory. Author (GRA) N73-31985# San Diego Aircraft Engineering. Inc.. Calif. CONCEPTUAL DESIGN OF A AIR CUSHION LANDING SYSTEM FOR AN UNMANNED AIRCRAFT Final Report. 27 Mar. - 11 Aug. 1972 Henry B. McCudden. Paul D. Sorensen. George R. Lutz. William H. Stewart, and Donald R, Walborn 3 Jan. 1973 126 p refs (Contract F33615-72-C-1769: AF Proj. 1369) (AD-764774: SAE-72-031: AFFDL-TR-72-155) Avail: NTIS CSCL 01/3 The problems associated with existing recovery systems include difficulty in mid-air retrieval of RPV's in excess of 1500 Ibs: high operations and support costs of parachutes, recovery helicopters, other aircraft and their crews: long recycle time: paving quality requirements for wheeled or skid type landing gear: and frequent damage of RPV's recovered by parachute/ attenuation bag or parachute/mid-air recovery systems. Ac- cordingly, this preliminary design study report describes an air cushion landing system (ACLS) applied to the 3.000 Ib Jindivik Mk 3A unmanned aircraft. The ACLS is stowed for cruise flight in a clean aerodynamic fairing on the underfuselage. resulting in a minimum performance degradation. For recovery, hinged clam-shell type doors are unlatched, and open, permitting inflation/deployment of an inelastic type elongated toroid-shaped trunk. The trunk is inflated and blown with bleed air tapped off an existing port on the Jindivik's Viper Mk 201 engine. After landing, the aircraft is placed on a fixture and the trunk is manually restowed in the fairing. (Modified author abstract) GRA N73-31986# Lockheed-California Co.. Burbank. EXPERIMENTAL PROGRAM FOR THE DEVELOPMENT OF IMPROVED HELICOPTER STRUCTURAL CRASHWORTHI- NESS ANALYTICAL AND DESIGN TECHNIQUES. VOLUME 2: TEST DATA AND DESCRIPTION OF AN UNSYMMETRI- CAL CRASH ANALYSIS COMPUTER PROGRAM. INCLUD- ING A USER'S GUIDE AND SAMPLE CASE Gilbert Wittlin and Max A. Gannon May 1973 251 p refs (Contract DAAJ02-71-C-0066: DA Proj. 1F1-62203-A-529) (AD-764986: USAAMRDL-TR-72-72B) Avail: NTIS CSCL 01/2 Volume 2 contains supporting data for the details presented in Volume I. The report contains abstracts for the 32 technical reports reviewed during the program. Included in the literature survey section is a matrix categorization of the reports by subject and applicable areas of interest. A brief description is presented on STAGS, the LMSC computer program used to perform the analysis of the P2V-4 fuselage bumper. A comprehensive description of program KRASH is presented, including the theory, initial conditions, the User's Guide, and a sample problem. Twenty-six channels of recorded test data and film data are presented in another section. Additional analytical data are presented in the last section. Author (GRA) N73-32058 Magnavox Research Labs., Torrance, Calif. SPREAD SPECTRUM APPLICATIONS AND STATE OF THE ART EQUIPMENTS Charles R. Cahn In AGARD Spread Spectrum Commun. Jul. 1973 111 p refs The applications of spread spectrum communications to avionics systems are described. The following topics are discussed: (1) multiple access capabilities. (2) interference rejection. (3) identification characteristics, and (4) distance measuring and position location capabilities. The characteristics and uses of current spread spectrum equipment are reported. Recent technology discoveries, such as acoustic surface wave and charge coupled devices are explained. Author N73-32131# Air Force Cambridge Research .Labs.. L G. Hanscom Field. Mass. A LIGHTWEIGHT. LOW-PROFILE ANTENNA FOR AIR- BORNE STATION-KEEPING APPLICATION Physical Sciences Research Papers William G. Mavroides. Raymond A. Schofield. and Robert J Mailloux 12 Jan. 1973 27 p (AF Proj. 4600) (AD-764685: AFCRL-TR-73-0047: AFCRL-PSRP-527) Avail NTIS CSCL 09/5 The report describes a low-profile, all dielectric lightweight antenna array to replace the directional antenna for the AN/APN 169 Aircraft Station-Keeping Antenna. The array consists of eight (LEXAN) polycarbonate channel guide elements partially plated with copper enabling the antenna system to be reduced from the present 8 inches in height to less than 2 inches. Design data and radiation patterns are given for the individual elements as well as for the eight-element array. Author (GRA) N73-32135/JI Air Force Materials Lab.. Wright-Patterson AFB. Ohio. THERMAL AGJNG OF SILVER-PLATED COPPER AIRCRAFT 644 N73-32162 ELECTRICAL WIRE Technical Report. Aug. 1971 - Jan. 1973 Lawrence R. Bidwell May 1973 58 p refs (AF Proj. 7351) (AD-764731: AFML-TR-73-113) Avail: NTIS CSCL 09/1 FEP/Polyimide insulated silver-plated copper aircraft electrical wire was thermally aged at temperatures of 150-230C for periods of up to 1000 hrs. The wires were examined for evidence that the insulation contributed to strand blocking during high temperature exposure. No evidence for a reaction between the insulation and the metal conductors was found. The phenomenon can be attributed entirely to the interstrand diffusion of silver. Two types of conductor degradation, unrelated to strand blocking, were identified. The nature, possible cause and probable effect of each is discussed and.a change in the current temperature rating procedure is recommended. Author (GRA) N73-j2141# Joint Army-Navy Aircraft Instrumentation Research Project. Washington. D.C. COCKPIT SWITCHING STUDY: LOGIC AND DESIGN PROCEDURE DEVELOPMENT FOR MULTIFUNCTION MODE SWITCHING CONTROLS Final Report D. K. Graham May 1973 76 p refs (Contract N00014-72-C-0191; NR Proj. 213-088) (AD-764617: D180-15335-1: JANAIR-730501) Avail: NTIS CSCL 09/1 The purpose of the cockpit switching study was to develop a procedure for design and application of multifunction switching concepts to cockpit controls, and thereby reduce both the number of cockpit switches required and the switching workload of the , pilot or aircrew. Such a procedure was developed and is printed under separate cover in a self-guiding handbook format. The procedure is a logical, step-by-step method of consolidating many switching functions on relatively few multifunction switches. The procedure handbook includes appendices containing a review of multifunction switching hardware, and human-engineering design considerations. (Modified author abstract) GRA on Air Breathing Engines. Marseille, 19-23 Jun. 1972 Avail: NTIS HC $3.00 The S4-MA hypersonic wind tunnel is equipped with a Mach 6 nozzle, working at maximum stagnation conditions of 40 bars and 1650 K. The diameter of the free jet test section is 0.68 m. The possibilities offered by the high pressure and temperature air supply system were used for studying the operation of a ramjet supersonic combustion chamber, fed with hydrogen, in the flight conditions. The Mach 6 nozzle was replaced by a duct of appropriate shape, directly connected to the annual intake. Apart from this type of test in closed duct, the wind tunnel permits, with its Mach 6 nozzle, the study of the aerodynamic behavior of large size air intakes, under the actual flight conditions of pressure and temperature. The model may be set in pitch and/or yaw. up to plus or minus 15 deg. The study of a complete airbreathing engine, with its intake and diffusor and with actual flight conditions (Mach 6, 25 km altitude) at intake is possible. The downstream conditions are obtained by using an adequate exhaust system for the combustion gases, either towards spherical vacuum tanks (4000 or 5000 cu m at 0.02 bar) or to atmosphere through a compressed air ejector. Author N73-32159# Minister fuer Wirtschaft. Mittelstand und Verkehr des Landes Nordrhein. Westfalen (West Germany). TASKS OF REGIONAL AIRPORTS AND RESULTING GROUND FACILITIES REQUIREMENTS [AUFGABEN DER REGIONALFLUGPLAETZE; DARAUS RESULTIERENDE ANFORDERUNGEN UND DIE BODENANLAGEN] G. Ruff 1973 14 p In GERMAN Presented at the DGLR-DGON Symp. on Neue Anflug- und Landeverfahren. Duesseldorf, 2-4 May 1973 (DGLR-Paper-73-035) Avail: NTIS HC $3.00 The role of regional airports is described, and the requirements for ground facilities are surveyed from a sociological and economic point of view. ESRO N73-32153 Purdue Univ.. Lafayette, Ind. THE APPLICATION OF ENERGY CONCEPTS TO PAVE- MENTS Ph.D. Thesis William Henry Highter 1972 178 p Avail: Univ. Microfilms Order No. 73-15817 Pavement engineers have not been able to predict the performance of pavement systems prior to their actual construction and operational utilization. A solution to this problem was obtained by verifying the following hypothesis: There is a functional relationship between the cumulative energy as measured by cumulative peak deflections imparted to a given pavement system and the condition of that system. The hypothesis was tested by applying it to load-deflection and performance trend data gathered in the AASHO Road Test. Regression analysis was performed to find a relationship that predicted the level of the Present Serviceability Index (PSI) as a function of the pavement profile and a measure of the cumulative energy imparted to the pavement. Because of the paucity of airfield condition and deflection data, indirect means had to be used to test the working hypothesis for airfield pavement. Traffic records and construc- tion histories for two Air Force Bases were analyzed. The analysis indicated there is a threshold cumulative total peak deflection at which cracking develops in airfield pavements. Dissert. Abstr. N73-32161# Calspan Corp.. Buffalo. N.Y. SELF-CORRECTING WIND TUNNELS W. R. Sears Jul. 1973 48 p refs (Contract N00014-72-C-0102: NR Proj. 061-199) (AD-764957: CALSPAN-RK-5070-A-2) Avail: NTIS CSCL 14/2 The familiar technique of accounting for wind-tunnel boundary effects by correcting measured data fails in some of the most important flight regimes, such as the transonic and V/STOL. In such domains, typically strongly nonlinear, it seems necessary that the wind tunnel provide the same flow conditions in the vicinity of the model as in flight, since corrections are virtually impossible. Present-day slotted and perforated tunnels, for example, are intended to do this, but are often inadequate. However, unconfined flow is characterized by certain functional relationships among the flow variables at points on a surface within the tunnel: it is always possible to ascertain whether unconfined-flow conditions are actually present, by measuring such quantities and verifying that these relationships are indeed satisfied. These relationships are independent of the configuration being tested. It is proposed here that wind tunnels be provided with sensors to measure such selected quantities on a convenient surface and means to vary wall geometry so as to approach such conditions in an iterative process. (Modified author abstract) GRA N73-32158# Office National d'Etudes et de Recherches Aerospatiales. Paris (France). THE S 4 MODANE HYPERSONIC WIND-TUNNEL: ITS USE FOR AIR BREATHING ENGINE TESTS Jean Laverre and Christian Soulier [1973] 10 p refs In FRENCH; ENGLISH_summary Presented at .1st .Intern. Symp. N73-32162# Illinois Univ.. Savoy. Aviation Researcn Lab. A DIGITAL COMPUTER-GENERATED CONTACT ANALOG LANDING DISPLAY Terry L. Hummel May 1973 92 p refs (Contract F44620-70-C-0105) (AD-764764: ARL-73-9/AFOSR-73-5: A F O S R - 7 3 - 1 2 5 8 T R ) 645 N73-32166 Avail: NTIS CSCL 17/7 A flexible display device was constructed to present a visual landing and navigation display to a pilot. The device makes use of a small digital computer, a flight simulator, and display equipment. A contact analog visual representation of external world objects plus control information is displayed to the pilot. The system is capable of simulating a nighttime approach to an airport and various types of enroute visual information. Author (GRA) N73-32166 Iowa State Univ. of Science and Technology. Ames. NUMERICAL CALCULATION OF FLOW FIELDS A B O U T RECTANGULAR WINGS OF FINITE THICKNESS IN SUPERSONIC FLOW Ph.D. Thesis Jerald Milo Vogel 1973 178 p Avail: Univ. Microfilms Order No. 73-16985 The inviscid flow fields about a three dimensional rectangular wing of finite thickness at angle of attack with a subsonic tip in a supersonic flow are determined by applying a second order finite difference technique to the gas dynamic equations of motion in their conservative form. The analysis includes a comparison of the second order technique with a current third order method. Dissert. Abstr. N73-32193# Kyushu Univ.. Fukuoka (Japan). SMALL DISTURBANCE THEORY OF ROTATING SUBSONIC AND TRANSONIC CASCADES M. Namba 23 Jun. 1972 45 p refs Presented at 1st Intern. Symp. on Air Breathing Engines, Marseille, 19-23 Jun. 1972: sponsored by Army and AF European Res. Offices. London, by Roy. Soc. of London, and by Cambridge Univ. Avail: NTIS HC $4.25 A linearized inviscid, isentropic, three-dimensional flow theory for a rotating thin blade row in a cylindrical duct with subsonic axial flow velocity and subsonic or supersonic relative tip velocity was developed on the basis of pressure dipole representations. A new method of approximation to Fourier Bessel double series was employed to evaluate the singularities. The theory was successfully applied to the inverse problem. Some numerical examples are provided. The validity of the blade element concept is discussed. The essential flow features for transonic compressors are demonstrated. Author N73-32194# Aeronautical Research Labs., Melbourne (Aus- tralia). VISCOUS INTERACTION IN INTEGRATED SUPERSONIC INTAKES Murdoch Culley 23 Jun. 1972 33 p refs Presented at 1st Intern. Symp. on Air Breathing Engines, Marseille 19-23 Jun 1973 Avail: NTIS HC $3.75 An experimental investigation has been conducted into the nature of the flow interference which occurs between a supersonic intake and an airframe in an integrated design of aircraft. It has been shown that an intake pressure field is of ample strength to cause three dimensional separation of a boundary-layer within its influence. The most energy deficient portion of the separated boundary layer is diverted by the separation, to be spilled into the airstream as vortices. A shock wave is generated by the three dimensional separation, and through this the boundary layer is able to influence the intake flow. There is good evidence that the separation shock is not steady. Author Jacques Paulon 19/2 B p refs In FRENCH: ENGLISH summary Presented at 1st Intern. Symp. on Air Breathing Engines, Marseille. 19-23 Jun. 1973 Avail. NTIS HC $3.00 Performance and operation stability of a transonic or supersonic compressor are conditioned by the intensity of the shock waves and their position in the blade channels. An experimental facility which, in a small height annular channel, .simulates a rotating cascade at supersonic speed, provides optimum conditions to study the shock wave pattern and stability. This facility, using Freon 114 as working gas, includes a window for visualization through which one records instantaneous schlieren shock wave configurations. Outer wall pressure taps give mean pressure repartitions in blade channels and check indications taken from schlieren pictures. Thus, it is possible to show that in function of back pressure, several flow patterns are obtained which extend from entirely supersonic operation in blade channels to rotating stall operation. Author N73-32208# Bell Aerospace Co, New Orleans, La. WATER-AUGMENTED VEHICLE (WAVE) STUDY - PHASE 1 Final Report. 5 Jun. - 31 Dec. 1972 Charles D. Hope-Gill. .George Rudinger, Stephen W. Zelazny, and John H. Morgenthaler 1 Mar. 1973 134 p refs (Contract N00014-72-C-0306: NR Proj. 259-097) (AD-765332) Avail: NTIS CSCL 13/10 The report deals with the analytical investigation of the thrust augmentation, lift forces and mixing properties of a two-phase flow propulsion/lift system which has application to Air Cushion Vehicles (ACV) and Surface Effect Ships (SES). The results of Water-Augmented Vehicles (WAVE) computer program investiga- tions show that significant thrust augmentation can be obtained by the injection of spray inherently produced through the interaction of ACV's and SES's with water surfaces. In addition propulsive efficiencies of 60% can be obtained with relatively quiet operation. The flow model I analysis conducted was based on a modified, one-dimensional duct flow and considered the transverse injection of spray and cushion air into the propulsion duct. Flow pressure losses, leakage of propulsion air from the propulsion duct, droplet breakup and the penetration of spray droplets into the propulsion duct where taken into account. (Modified author abstract) GRA N73-32209# Air Force Systems Command, Wright-Patterson AFB. Ohio. Foreign Technology Div. THE EFFECT OF REAL PROPERTIES OF AIR ON PARAME- TERS OF FLOW NEAR AN ELLIPTIC CONE. AERODYNAMIC CHARACTERISTICS OF ELLIPTIC CONES AT LARGE ANGLES OF ATTACK A. P. Bazzhin. 0. N. Trusova, and I. F. Chelysheva 27 Jul. 1973 16 p refs Transl. into ENGLISH from Uch. Zap. Tsagi, Tsent. Aerogidrodinam. Inst. (USSR), v. 1, no. 2, 1970 p 46-52 (AD-764945; FTD-HT-23-708-73) Avail: NTIS CSCL 20/4 The calculation results of a flow around a family of elliptic cones by a flow of ideal gas at large angles of attack were presented in previous reports. Subsequently, several variants of flow were calculated taking into account the real properties of air, which are in a state of thermodynamic equilibrium. These calculation results permit one to evaluate the effect of real gas properties, which proves to be insignificant for the variants of flow. The first part of this report is devoted to this problem. Calculated aerodynamic characteristics of elliptic cones over the angle of attack range from 30 degrees to 50 degrees in the case of an ideal gas are presented in the second pan: of this report. GRA N73-32196# Office National d'Etudes et de Recherches Aerospatiales, Paris (France). STUDY OF SHOCK WAVES PATTERNS IN AN AXIAL SUPERSONIC COMPRESSOR N73-32296# California Univ.. Livermore. Lawrence Livermore Lab. 646 N73-32381 DOT-CIAP PROGRAM Annual Report M. C. MacCracken 13 Feb. 1973 220 p refs (Contract W-7405-eng-48) (UCRL-51336; AR-1) Avail: NTIS HC $7.60 Research projects to determine the effects of large numbers of aircraft operating in the stratosphere on global and local climatic conditions are discussed. The projects are concerned with developing models to show: (1) global kinetics and transport. (2) zonal atmospheric conditions. (3) stratospheric conditions. (4) radiation transport, and (5) meteorological conditions. Mathematical models are developed to analyze the dispersion of the aircraft exhaust plume under various conditions. The chemical reactions of the exhaust plume with atmospheric constituents are discussed. Author (NSA) N73-32298# Istituto di Fisica Dell Atmosfera. Rome (Italy). THERMAL SURVEYS ON GARDA LAKE USING INFRARED EQUIPMENT M. Giorgi. M. Colacino. and F. M. Vivona Jan. 1973 54 p refs In ITALIAN: ENGLISH summary (IFA-STR-23) Avail: NTIS HC $4.75 Annual variations of the Garda Lake surface temperature were studied by bolometric measurements using helicopter-borne devices. Superficial isotherms were derived for two sets of flights performed in different months. Thermal anomalies of morning- evening inversions were analyzed. Earth based thermograms obtained by using the thermovision instrument are presented and compared to bolometer measurements. ESRO N73-32374*# Virginia Univ.. Charlottesville. NONLINEAR TRANSIENT ANALYSIS OF MULTI-MASS FLEXIBLE ROTORS - THEORY AND APPLICATIONS R. Gordon Kirk and Edgar J. Gunter Washington NASA Sep. 1973 265 p refs (Grant NGL-47-005-050) (NASA-CR-2300: ME-4040-112-72U) Avail: NTIS HC $6.35 CSCL 131 The equations of motion necessary to compute the transient response of multi-mass felxible rotors are formulated to include unbalance, rotor acceleration, and flexible damped nonlinear bearing stations. A method of calculating the unbalance re- sponse of flexible rotors from a modified Myklestad-Prohl technique is discussed in connection with the method of solution for the transient response. Several special cases of simplified rotor-bearing systems are presented and analyzed for steady-state response, stability, and transient behavior. These simplified rotor models produce extensive design information necessary to insure stable performance to elastic mounted rotor-bearing systems under varying levels and forms of excitation. The nonlinear journal bearing force expressions derived from the short bearing approximation are utilized in the study of the stability and transient response of the floating bush squeeze damper support system. Both rigid and flexible rotor models are studied, and results indicate that the stability of flexible rotors supported by journal bearings can be greatly improved by the use of squeeze damper supports. Results from linearized stability studies of flexible rotors indicate that a tuned support system can greatly improve the performance of the units from the standpoint of unbalanced response and impact loading. Extensive stability and desijn charts may be readily produced for given rotor specifications by the computer codes presented in this analysis. Author N73-32354# Air Force Cambridge Research Labs.. L G. Hanscom Field. Mass. FLIGHT TESTING OF A CR YOG ENICA LLY COOLED HYGROMETER James F. Church and Russell M. Peirce 4 May 1973 30 p refs (AF Proj. 6670) (AD-764718: AFCRL-TR-73-0292: AFCRL-IP-188) Avail: NTIS CSCL 04/2 The cryogenically cooled, optical dew/frost point hygrometer was developed to provide a fast response aircraft instrument for the measurement of very low frost-point temperatures encountered at the higher altitudes. A detailed description of the device is presented, along with a discussion of the laboratory and flight tests performed to date. Problems encountered during the tests are outlined, and recommended changes to the instrument are made for the benefit of those contemplating its use in the future. Author (GRA) N73 32357# Naval Academy. Annapolis. Md. Michelson Physical Lab. AVRG: A POP 8/1 DATA ACQUISITION AND AVERAGING PROGRAM FOR SYNCHRONOUS HOT WIRE MEASURE ME NTS Samuel A. Elder 31 May 1973 28 p refs (AD-764851: E-7302) Avail: NTIS CSCL 14/2 The program, in function-modified FOCAL, is specifically designed to enable measurements to be performed on oscillating vertical velocity profiles in the mouth of a flow-excited cavity resonator. Simultaneous hot wire and pressure microphone data samples are recorded at an exact multiple (20X) of the oscillation frequency so as to obtain a synchronous record of the cyclic variation of longitudinal stream velocity at many points in the mouth region. Data is automatically averaged over 100-cycle intervals to remove turbulent background variation. From the stored data, either two or three dimensional velocity profile information can be reconstructed, using sound pressure at the base of the cavity as a phase reference. Options are provided for Fourier analysis, real time (oscilloscope) display, and TTY printout. Author (GRA) N73-32375*# National Aeronautics and Space Administration. Lewis Research Center. Cleveland. Ohio. BALL MOTION AND SLIDING FRICTION IN AN ARCHED OUTER RACE BALL BEARING Bernard J. Hamrock [1973] 41 p refs Proposed for submittal to ASME for presentation at the ASME-ASLE Joint Lubrication Conf.. Montreal, 8-10 Oct. 1974 (NASA-TM-X-71442: E-7607) Avail: NTIS HC $4.25 CSCL 131 The motion of the ball and sliding friction in an arched outer race ball bearing under thrust loads is determined. Fatigue life evaluations were made. The analysis is applied to a 150 millimeter bore ball bearing. The results indicated that for high speed-light load applications the arched bearing has significant improvement in fatigue life over that of a conven- tional bearing. An arching of 0.254 mm (0.01 in.) was found to be an optimal. For an arched bearing it was also found that a considerable amount of spinning occurs at the outer race contacts. Author N73-32381# George Washington Univ.. Washington. U.\.. PERFORMANCE EVALUATION OF FOA INTERNAL ENERGY SEPARATORS Final Report. 3 Jan. - 30 Nov. 1972 R. Whitney and S. Smith Dec. 1972 65 p refs Prepared by Columbia Res. Corp.) (Contract N00019-72-C-0122) (AD-764585: R-116A) Avail: NTIS CSCL 13/1 The report details the work performed by a contractor to evaluate the actual performance of model energy separators, including a variable geometry device fabricated specifically for this purpose. Tests were conducted on a single rotor energy separator with fixed geometry and a double rotor energy separator with interchangeable collectors and center sections. The latter device is referred to as the variable geometry model. Test results are presented in graphic form and evaluated to reveal preferred Foa energy separators geometry. Fabrication and test procedures are also outlined. GRA 647 N73-32382 N73-32382# Army Engineer Waterways Experiment Station. Vicksburg, Miss. NONDESTRUCTIVE TESTING OF PAVEMENTS: FINAL TEST RESULTS AND EVALUATION PROCEDURE Technical Report. Jan. 1971 • Apr. 1972 J. W. Hall. Jr. Kirtland AFB. N. Mex. AFWL Jun. 1973 B4 p refs (Contract F29601-71-X-0004; AF Proj. 683M) (AD-764787; AFWL-TR-72-151) Avail: NTIS CSCL 13/2 The report presents results for an investigation to develop techniques of nondestructive evaluation of the load-carrying capacity of airfield pavements. Tests were performed with vibratory equipment on pavements where conventional pavement parame- ters were also measured. Two evaluation approaches, deflection- extrapolation and stiffness methods, are discussed. The nondestructive stiffness method was found to relate to conven- tional pavement evaluation criteria. Results of the study showed the reliability of the nondestructive pavement evaluation, and a proposed nondestructive evaluation procedure was developed. The equipment used is described in detail, and recommendations are given for improvements to the equipment. Author (GRA) was chosen for lubricating the anvils in forging 7075 Al. and in conjunction with a glass coating applied to the workplace, also for Ti. (Modified author abstract) GRA N73-32390# Grumman Aerospace Corp., Bethpage. N.Y. MECHANICAL RELIABILITY PREDICTION PILOT STUDY Final Report L. Kutin and A. Durner Jun. 1973 157 p refs (Contract N00600-73-C-0562) (AD-765367: R/M-73-R-2) Avail: NTIS CSCL 14/4 Grumman Aerospace Corporation performed a pilot study for the Naval Weapons Engineering Support Activity to determine the feasibility of developing mechanical equipment reliability prediction techniques. The results of this study substantiate the feasibility of establishing a standard for mechanical equipment reliability prediction. Continued studies are recommended on additional and varied aircraft mechanical equipment, to expand the scope and data for the eventual development of a mechanical equipment reliability handbook. Author (GRA) N73-32383# Boeing Commercial Airplane Co.. Seattle, Wash. APPLICATION OF RELIABILITY ANALYSIS TO AIRCRAFT STRUCTURES SUBJECT TO FATIGUE CRACK GROWTH AND PERIODIC STRUCTURAL INSPECTION Final Report, 16 Jul. 1972 - 31 Mar. 1973 I. C. Whittaker and S. C. Saunders Wright-Patterson AFB. Ohio AFML Jun. 1973 47 p refs (Contract F33615-71-C-1134; AF Proj. 7351) (AD-764775: AFML-TR-73-92) Avail: NTIS CSCL 01/3 A method of simulating crack growth has been investigated. The proposed model, which is based on linear elastic fracture mechanics theory, allows for the variability in crack growth behavior found in the experimental data of various materials. Given a reference stress intensity factor range and central tendency values for the crack growth rate and the exponent of the stress intensity factor excursions of a material in a specified configuration, Monte Carlo simulation is used to select various combinations of parameters. These are then used to generate fatigue cracks, on the assumption that crack growth rate is a power function of the stress intensity factor range. The residual strength of the cracked structure is considered to be a decreasing function of the Induced crack length. The probability of crack detection also depends on the generated crack and is assumed to improve with increasing crack length. However, this improved detection probability is modified by the probability that the crack location ia not the one being inspected. (Modified author abstract) GRA N73-32384# Illinois Univ.. Chicago. Dept. of Materials Engineering. PRINCIPLES OF INCREMENTAL FORGING: PHASES Find Report. Nov. 1971 - May 1973 T. F. Restivo. A. H. Lonn, and J. A. Schey Jul. 1973 70 p refs (Contract N00019-72-C-0084) (AD-764618; Rept-73-4) Avail: NTIS CSCL 13/8 The principles of deformation and of equipment design estab- lished in the first two phases formed the basis of development in this third phase of the program. A subpress was designed and built, in which wedge-actuated side rams assured complete synchronization of the vertical (indenting) and horizontal (rib- forming) anvils. .Interconnection of the controls of the hydraulic press with those of an electrically actuated manipulator allowed rapid and precise sequencing of deformation increments. The practicability of the process was demonstrated by hot forging 7075 Al and commercial purity titanium into parts with H-sections of 1/4 in. thick ribs and webs, incorporating stiffening cross-ribs. Lubrication became critical in hot forging: on the basis of solid film durability tests, a commercial resin-bonded graphite film N73-32470# CIBA-GEIGY (UK) Ltd, Cambridge (England). Bonded Structures Div. THE APPLICATION OF ADHESIVE BONDED STRUCTURES AND COMPOSITE MATERIALS ON ADVANCED TURBOFAN ENGINES E. M. Pendlebury 23 Jun. 1972 33 p Presented at 1st Intern. Symp. on Air Breathing Engines, Marseille. 19-23 Jun. 1972 Avail: NTIS HC $3.75 The aero engine industry has a special Interest in high temperature adhesives which will withstand environmental exposure more rigorous than most other applications. It is also essential that such systems, be they of glass, carbon, prepreg form, or standard adhesives, are capable of easy production handling and have realistic shelf life properties. There is continuing development in this area and manufacturers of structural adhesives and honeycomb collaborate to a considerable extent with aero engine manufacturers on these subjects. It should be possible in the not too distant future to replace, on a cost basis, existing brazing and welding techniques by bonding, but not until sufficient confidence ia gained, which can only be achieved by extensive long term development testing and in-service experience. Author N73-32611 Purdue Univ., Lafayette. Ind. INTERMITTENT POSITIVE CONTROL. OF AIR TRAFFIC IN A HORIZONTAL PLANE Ph.D. Thesli Alvin Leroy Me Fa Da nd 1972 280 p Avail: Univ. Microfilms Order No. 73-15836 The task of selecting a horizontal resolution maneuver is approached from the point of view of optimal control theory, choosing as e. performance index to be minimized, the maneu- ver duration. One aircraft in the conflict maintains a constant velocity path. The problem reducea to that of selecting for the other aircraft the optimum flight path consisting of three circular arcs and two straight legs, which allows the two aircraft to pass with a separation no less than a specific value. The complete theoretical solution to the optimal control problem is stated. Because this exact solution is much too complex for use in practice, a suboptimal solution is proposed, and a means for evaluating the loss of optimality devised. The conflict resolution model and solution could also find application in an automated positive control environment, in a nationwide flow control system, and. with some adaptation, in terminal area metering and spacing schemes. Dissert. Abstr. N73-32612# Mitre Corp.. McLean. Va. EVALUATION OF ATCRBS PERFORMANCE IN AN IN 648 N73-32519 TERFERENCE ENVIRONMENT Final Report Stanley R. Jones Washington FAA Aug. 1972 218 p refs (Contract DOT-FA70WA-2448) (MTR-6239: FAA-EM-73-4) Avail: NTIS HC $13.00 Uplink and downlink ATCRBS interference measurements in terminal areas were coordinated with assessments of the sources of these mutual interference conditions. The average values of these observations as well as many burst characteristics corroborated the results of an analytical model coupling the environmental features to their effects on the surveillance system. Simulation efforts based on statistical representation of the input conditions enabled an association of these interference levels with deterioration in performance of the ARTS III and TPX-42 processors. Results of these modeling efforts indicate that the performance of both processors is degraded for transponder reply probabilities below 0.85. Forecasts based on these results indicate that ARTS HI performance degradation due to asynchronous interference may limit the terminal area traffic count to about 600 aircraft when approximately 40 interrogators are within view. Author N73-32513# Collins Radio Co., Cedar Rapids. Iowa. EVALUATION OF EXISTING VOR, LOCALIZER AND QLIOESLOPE RECEIVING EQUIPMENT. VOLUME 2. BOOK 2 Final Report W. 0. Ashby Feb. 1973 300 p refs (Contract DOT-FA72WA-2772) (FAA-RD-730-Vol-2-Bk-2: Rept-523-0764695-00111M-V2-Bk2) Avail: NTIS HCS17.00 Tests of VHF Omnirange navigation system, localizer, and glideslope receiving equipment were conducted to determine performance under various conditions of radio frequency interference. The basic test results for each of the sixty one receivers tested are presented. The purpose of the test .was to provide data on which to base geographic facility separations to avoid mutual electromagnetic interference. Author Robert A. Clark and James F. Zakers Oct. 1972 46 p (FAA-NA-73-54: FAA-RD-73-119) Avail: NTIS HC $4.50 A programmable ARTS II B. non-tracking, beacon alphanu- meric system was installed in a TRACAB configuration in a live air traffic control tower environment. Operational suitability and techniques to be used in the automation program for low-density terminal/towers were evaluated. The system was evaluated over a -six-week period through collection of subjective data obtained from controller questionnaries. It was concluded that while suitable for application in a TRACAB environment and compatible with the controller, extensive modification to both display subsystem and software were required to improve its usefulness. Author N73-32517| Flight Inspection National Field Office Oklahoma City. Okla EVALUATION OF CLOSE-IN/SHORT TURN ON PATTERNS(ILS) Final Report Harold R. Richards. Jr. and Frank Parr Washington Aug. 1973 (AFS Proj. 600-72-3) (FAA-AFS-500-1) Avail: NTIS HC $4.25 It was suggested that increased IFR traffic could be accepted at an airport if it were possible for traffic, controllers to feed some of the smaller aircraft into gaps in the flow of normal traffic. Flight tests were flown in a Cessna 310 to intercept an ILS localizer at distances of 1.0. 1.5, 2.0. 2.5 and 3.0 NM from the runway -threshold to evaluate flyability factors. Nominal airspeed used in maneuvering and on the approach was 110 MPH (100 knots), giving a margin of 9 knots for turbulence over the maximum Category A airspeed of 91 knots. Intercept angles were 45 and 90 degrees to the localizer centerline. Glide slope interception altitude was 500 feet above ground level. All flight tracks were recorded by an APTAR radar system. It was found that ILS intercepts inside the outer marker caused full scale localizer needle deflection during the intercept maneuver, and that pilot opinion did not support implementation of the procedure as a standard operation. Author N73-32616*# National Aeronautics and Space Administration. Ames Research Center, Moffett Field, Calif. FLIGHT RESULTS FROM A STUDY OF AIDED INERTIAL NAVIGATION APPLIED TO LANDING OPERATIONS Leonard A. McGee, Gerald L. Smith, Daniel M. Hegarty, Thomas M. Carson, Robert B. Merrick, S. F. Schmidt (Anal. Mech. Aasoc., Inc., Mt. View, Calif.), and B. Conrad (Anal. Mech. Assoc., Inc., Mt. View. Calif.) Washington Oct. 1973 42 p refs (NASA-TN-D-7302; A-4584) Avail:. NTIS HC $3.00 CSCL 17G An evaluation is presented of the approach and landing performance of a Kalmen filter aided inertial navigation system using flight data obtained from a series of approaches and landings of the CV-340 aircraft at an instrumented test area. A description of the flight test is given, in which data recorded included: (1) accelerometer signals from the platform of an INS: (2) three ranges from the Ames-Cubic Precision Ranging System; and (3) radar and barometric altimeter signals. The method of system evaluation employed was postflight processing of the recorded data using a Kalman filter which was designed for use on the XDS920 computer onboard the CV-340 aircraft. Results shown include comparisons between the trajectories as estimated by the Kalman filer aided system and as determined from cinetheodo- lite data. Data start initialization of the Kalman filter, operation at a practical data rate, postflight modeling of sensor errors and operation under the adverse condition of bad data are illus- trated. • Author N73-32516# National Aviation Facilities Experimental Center. Atlantic City, N.J. FIELD EVALUATION OF ARTS 2 B (TRACAB) Interim Reoort. Feb. - Apr. 1973 N73-32B18# National Aviation Facilities Experimental Center, Atlantic City, N.J. SYSTEM INTEGRATION AND SYSTEM SHAKEDOWN TESTS. NASENROUTE STAGE A MODEL A3d1 Final Report, Sep. 1972 • Apr. 1973 Joseph Levy and Victor Crawford Oct. 1973 77 p (FAA-NA-73-55; FAA-RD-73-135) Avail: NTIS HC $5.75 A series of tests of the national Air Space (NAS) Enroute Stage A Model A3dl System were conducted in a total system environment. Simulated and live radar inputs to evaluate the total system capability to accomplish the air traffic control task and to provide guidance for conduct of System Integration and System Shakedown tests at field facilities were conducted. The tests and the results obtained are described. Author N73-32519|jl Technische Universitaet. Brunswick (West Germeny). Inst. fuer Verkehr. Eisenbahnwesen und Verkehrs- sicherung-Sonderforschungsbereich Flugfuehrung. DIGITAL SYNCHRONIZATION FOR TIME SYNCHRONOUS COLLISION AVOIDANCE SYSTEMS IN AVIATION [Dl- GITALE SYNCHRONISATION FUER ZEITSYNCHRONE KOLLISIONSSCHUTZSYSTEME DER LUFTFAHRT] Peter Form 1973 18 p refs In GERMAN Presented at trie DGLR-DGON Symp. on Neue Anflug- und Landeverfahren. Duesseldorf. 2-4 May 1973 (DGLR-Paper-73-012) Avail: NTIS HC $3.00 Some problems in the digital synchronization of airborne collision avoidance systems are discussed. The economies of such existing time synchronous systems were investigated, and replacement of the relatively expensive onboard precision reference 649 N73-32520 source by a synchronization of corresponding accuracy is proposed. This completion of time-synchronous systems is explained by describing the present state of the art. ESRO N73-32520# Technische Universitaet. Brunswick (West .Germany). Inst. fuer Verkehr. Eisenbahnwesen und Verkehrs- sicherung-Sonderforschungsbereich Flugfuehrung. PRESENT STATUS OF ALL-WEATHER LANDING: PROB- LEMS AND LIMITS [SCHLECHTWETTERLANDUNG HEUTE-IHRE PROBLEME UND GRENZEN] Dirk Brunner 1973 13 p In GERMAN Presented at the DGLR-DGON Symp. on Neue Anflug- und Landeverfahren. Duesseldorf, 2-4 May 1973 (DGLR-Paper-73-015) Avail: NTIS HC $3.00 The problems in aircraft landing under low visibility weather conditions are discussed. Most of these problems are based on the fact that ILS is not a landing system, but an approach aid. Its incompleteness has to be compensated with auxiliary equipment, such as radio altitude measurement, optical landing aids. ect. The decision of the pilot of land or not to land under certain weather conditions should be supported more than by . present displayed information. The aritificial improvement of optical visibility is an interesting consequence. ESRO N73-32521# Technische Universitaet. Brunswick (West Germany). Abteilung fuer Fernmelde- und Hochfrequenztechnik in der Verkehrssicherung POSSIBILITIES FOR IMPROVING THE CONVENTIONAL INSTRUMENT LANDING SYSTEM (ILS) [VERBES- SERUNGSMOEGLICHKEITEN DES KONVENTIONELLEN INSTRUMENTENLANDESYSTEMS (ILS)] H. Frilke 1973 18 p In GERMAN Presented at the DGLR-DGON Symp. on Neue Anflug- und Landeverfahren. Duesseldorf. 2-4 May 1973 (DGLR-Paper-73-017) Avail: NTIS HC $3.00 Two possibilities for improving instrument landing systems were investigated. These deal with interferences during aircraft landing and gliding as a result of multipath propagation and variations of earth surface signal reflectivity. To minimize multipath propagation effects, which can be felt 12 km before touching ground, interference should be detected, and consequently suppressed. Methods to realize these steps are briefly described. Two methods to suppress the variable surface reflection, especially on the glide path are discussed: the formation of quotients in antenna reception signals, and the use of circular polarization. ESRO N73-32522# Bundesanstalt fuer Flugsicherung. Frankfurt am Main (West Germany). FLIGHT OPERATIONS AND GUIDE BEAM SYSTEMS [FLUGBETRIEB UND LEITSTRAHLSYSTEM] T.Bohr 1973 13 p In GERMAN Presented at the DGLR-DGON Symp. on Neue Anflug- und Landeverfahren. Duesseldorf. 2-4 May 1973 (DGLR-Paper-73-011) Avail: NTIS HC $3.00 The history and perspectives of the instrument landing system are presented. The present operational requirements for these systems, as endorsed by the ICAO. are formulated and discussed. ESRO N73-32523# Standard Electrik Lorenz A.G.. Stuttgart (West Germany). DETAILS OF DLS AND SETAC LANDING AIDS [EINIGE BESONDERHEITEN DER LANDENHILFEN DLS UND SETAC] K. D. Eckert and G. Peuker Apr. 1973 34 p In GERMAN Presented at the DGLR-DGON Symp. on Neue Anflug- und Landeverfahren. Duesseldorf. 2-4 May 1973 (DGLR-73-019) Avail: NTIS HC $3.75 Two new instrument landing systems are described. These systems replace ILS. in view of its inherent problems, such as multipath propagation, increasing traffic, equipment volume, and application both in military and civil aviation. The SETAC system, short for sector-Tacan. is based on the military medium range navigation system Tacan and consists of two ground stations and a onboard ancillary device of Tacan equipment. The DLS system is based on DME in the L-band. from which the DME-supported landing system originated. The system allows distance measurements as follows: onboard request, ground transponder, and reply after exactly 50 microsec. The requests are received with special antenna arrays, allowing determination of azimuthaj incidence angle, and elevation incidence angle. ESRO N73-32524# Standard Electrik Lorenz A.G.. Stuttgart (West Germany). Erzeugnisgebiet Navigation. IMPROVEMENT OF STANDARD ILS WHILE RETAINING COMPATIBILITY [VERBESSERUNG DES STANDARD-ILS UNTER BEIBEHALTUNG DER KOMPATIBILITAET] G. Hoefgen 1973 7 p In GERMAN Presented at the DGLR-DGON Symp. on Neue Anflug- und Landeverfahren. Duesseldorf. 2-4 May 1973 (DGLR-Paper-73-018) Avail: NTIS HC $3.00 Two methods of improving the standard instrument landing system, while retaining compatibility, are presented. The compatible instrument landing system (CILS) consists of the following components: (1) standard ILS for clearance, and (2) microwave ILS 5 GHz, based on conventional pnciple (SO/ 150 Hz) only for approach sector. To be compatible with the existing two carrier systems with 9 kHz difference carrier frequency, the microwave oscillator frequency is also radiated. The precision instrument landing system (PILS). necessitates more onboard equipment and includes linear antenna arrays, consisting of elements sequentially radiating signals. An advantage over standard ILS is that the glide angle can be selected at random onboard. ESRO N73-32525# Messerschmitt-Boelkow-Blohm G.m.b.H.. Otto- brunn (West Germany). MIXED CTOL/QTOL TRAFFIC [GEMISCHTER CTOL/QTOL- VERKEHR] F. Schoenberger 15 Apr. 1973 30 p In GERMAN Presented at the DGLR-DGON Symp. on Neue Anflug- und Landeverfahren, Duesseldorf. 2-4 May 1973 (MBB-UH-05-73-0: DGLR-Paper-73-014) Avail: NTIS HC $3.50 The results of the transition period when conventional air .traffic (CTOL) will be replaced by quiet takeoff and landing (QTOL) traffic, are reviewed. The introduction of QTOL aircraft from about the year 1978 will entail the simultaneous operation of present CTOL and QTOL aircraft types. The effects of this transition period, to be felt by introduction of microwave instrument landing systems and area navigation, are surveyed. ESRO N73-32526# Bodenseewerk Geraetetechnik G.m.b.H., Ueberlin- gen (West Germany). FLIGHT PATH CONTROL EQUIPMENT FOR PRODUCING CURVED FLIGHT PATH PROFILES IN MICROWAVE LANDING SYSTEMS [FLUGBAHNFUEHRUNGSGER AET ZUM ERZEUGEN GEKRUEMMTER FLUGBAHNPROFILE AN MIKROWELLEN-LANDESYSTEMEN] G. Schaenzer 1973 36 p refs In GERMAN Presented at the DGLR-DGON Symp. on Neue Anflug- und Landeverfahren. Duesseldorf. 2-4 May 1973 650 N73-32610 (DGLR-Paper-73-Olb) Avail: NTIS HC $4.00 The properties of a flight control display device for producing curved approach profiles, and the flight control along these profiles, are discussed in the case of a microwave instrument landing system. The prolems of maneuverability, accuracy, and the stability of aircraft motions are treated, and the requirements of the guide beam system and flight control system are formulated. Flight tests have shown that the methods discussed contribute to reduction of pilot workload. ESRO Test reports on 3610 samples of JP-4 fuel purchased in 1972 were analyzed to determine the average properties and distribution of values for eight geographical districts. As required by the JP-4 specification. MIL-T-5624H. 21 of the inspection tests were selected for analysis. Although since 1964. the API Gravity has gradually increased, no other significant trends were noted. Author (GRA) N73-3254O*# Pennsylvania State Univ.. University Park. THE DESIGN AND DEVELOPMENT OF AN AUTOMATIC CONTROL SYSTEM FOR THE IN-DUCT CANCELLATION OF SPINNING MODES OF SOUND M.S. Thesis Walter W. Harrington Jun. 1973 249 p refs (Grant NGL-39-009-121) (NASA-CR-132317) Avail: NTIS HCS14.50 CSCL 20A The reduction is discussed of the discrete tones generated by jet engines which is essential for jet aircraft to meet present and proposed noise standards. The discrete tones generated by. the blades and vanes propagate in the inlet and exhaust duct in the form of spiraling acoustic waves, or spinning modes. The reduction of these spinning modes by the cancellation effect of the combination of two acoustic fields was investigated. The spinning mode synthesizer provided the means for effective study of this noise reduction scheme. Two sets of electrical-acoustical transducers located in an equally-spaced circular array simulta- neously generate a specified spinning mode and the cancelling mode. Analysis of the wave equation for the synthesizer established the optimum cancelling array acoustic parameters for maximum sound pressure level reduction. The parameter dependence of the frequency ranges of propagation of single, specified circumferential modes generated by a single array, and of effective cancellation of the modes generated by two arrays, was determined. Substantial sound pressure level reduction was obtained for modes within these limits. Author N73-32543# Deutsche Forschungsanstalt fuer Luft- und Raumfahrt, Brunswick (West Germany). Inst. fuer Luftsaugende Antriebe. SOME EXPERIMENTS ON THE NOISE EMISSION OF COAXIAL JETS Helmut W. Dahlen 23 Jun. 1972 18 p refs Presented at 1st Intern. Symp. on Air Breathing Engines, Marseille, 19-23 Jun. 1972 Avail: NTIS HC $3.00 The noise emission of coaxial jets or the reduction of jet noise by surrounding a circular primary jet with an annular flow is discussed. Acoustic experiments have been performed with a model hot primary jet which had a Mach number very close to one surrounded by a secondary cold annular flow of variable velocity and area ratios of the coplanar convergent nozzles. The experiments show that the reduction of high frequency noise emission depends on secondary flow velocity. In most cases this reduction seems to be not compensated by an increase in low frequency noise power. The small reduction in the total emitted noise power is uprated by weighting for perceived noise. so that the effects are not more negligible in view of the noise control of jet engines with fair by-pass ratios for SST and military aircraft. Author N73-32608*# General Electric Co.. Evendale. Ohio. ACOUSTIC TESTING OF A SUPERSONIC TIP SPEED FAN WITH ACOUSTIC TREATMENT AND ROTOR CASTING SLOTS. QUIET ENGINE PROGRAM SCALE MODEL FAN C S. B. Kazin Oct. 1973 98 p refs (Contract NAS3-12430) (NASA-CR-134501: R73AEG148) Avail: NTIS HC$7.00 CSCL 21E Acoustic tests were conducted on a high tip speed (1550 ft/sec, 472.44 m/sec) single stage fan with varying amounts of wall acoustic treatment and with circumferential slots over the rotor blade tips. The slots were also tested with acoustic treatment placed behind the slots. The wall treatment results show that the inlet treatment is more effective at high fan speeds and aft duct treatment is more effective at low fan speeds. Maximum PNL's on a 200-foot (60.96 m) sideline show the untreated slots to have increased the rear radiated noise at approach. However, when the treatment was added to the slots inlet radiated noise was decreased, resulting in little change relative to the solid casing on an EPNL basis. Author N73-32609*# National Aeronautics and Space Administration. Lewis Research Center, Cleveland, Ohio. NOISE COMPARISON OF TWO 1.2-PRESSURE-RATIO FANS WITH 15 AND 42 ROTOR BLADES Richard P. Woodward, Frederick W. Glassr, and Joseph A. Wazyniak Washington Oct. 1973 76 p refs (NASA-TM-X-2891: E-7477) Avail: NTIS HC $3.75 CSCL 21E Two 1.829-m-(6-ft-) diameter fans suitable for a quiet engine for future short-takeoff-and-landing (STOL) aircraft were compared. Both fans were designed for a 1.2 pressure ratio with similar weight flows, thrusts, and tip speeds. The first fan, designated QF-9, had 15 rotor blades and 11 stator blades. The rotor was highly loaded and the tip solidity was less than 1. The QF-9 rotor blades had an adjustable pitch feature which can be used for thrust reversal. The second fan, designated QF-6, operated at a moderate loading with a rotor tip solidity greater than 1. Fan QF-6 had 42 rotor blades and 50 stator blades. The low number of rotor blades for QF-9 reduced the frequency of the blade-passage tone below the range of maximum annoyance. In addition to this difference, the QF-9 fan had a somewhat smaller rotor-stator separation than the QF-6 fan. In terms of sound pressure level and sound power level, QF-9 was the noisier fan, with the power level results for QF-9 being about 1 db above those for QF-6 at equivalent operating points as determined by similar stage pressure ratios. At the same equivalent operating points, the maximum perceived noise along a 152.5-m (500-ft) sideline for QF-9 was about 2.5 PNdb below that for QF-6. which indicated that QF-9 was less objectionable to human hearing. Author N73-32605# Air Force Aero Propulsion Lab., Wright-Patterson AFB, Ohio. PHYSICAL AND CHEMICAL PROPERTIES OF JP-4 JET FUEL FOR 1972 James R. McCoy Jun. 1973 119 p (AF Proj. 3048) (AD-764690: AFAPL-TR-73-15) Avail: NTIS CSCL 21/4 N73-32610*# AiResearch Mfg. Co.. Phoenix, Ariz. ADVANCED TWO-STAGE COMPRESSOR P R O G R A M DESIGN OF INLET STAGE C. A. Bryce. C. J. Paine, A. R. S. McCutcheon. R. K. Tu, and G. L. Perrone Aug. 1973 301 p refs (Contract NAS3-15324) 651 N73-32613 (NASA-CR-120943: AT-6133-R) Avail: NTIS HCS17.25 CSCL 21E The aerodynamic design of an inlet stage for a two-stage, 10/1 pressure ratio, 2 Ib/sec flow rate compressor is discussed. Initially a performance comparison was conducted for an axial, mixed flow and centrifugal second stage. A modified mixed flow configuration with tandem rotors and tandem stators was selected-for the inlet stage. The term conical flow compressor was coined to describe a particular type of mixed flow compressor configuration which utilizes axial flow type blading and an increase in radius to increase the work input potential. Design details of the conical flow compressor are described. Author Results are presented of NASA studies to determine optimum engine cycles for noise levels of 10. 15, and 20 EPNdb below current FAA regulations. The study aircraft were 200-passenger trijets flying over ranges of 5,556 and 10,200 km at cruise speeds of Mach 0.90 to 0.98. The economic impact of reducing noise, the identification of needed advanced technology and the effect of these advances are presented. The studies showed that the noise constraints imposed compromises on the optimum cycle with resulting economic penalties. The application of advanced engine technologies, however, could effectively offset these economic penalties. Author N73-32613*# National Aeronautics and Space Administration. Lewis Research Center, Cleveland. Ohio. ODOR INTENSITY AND CHARACTERIZATION STUDIES OF EXHAUST FROM A TURBOJET ENGINE COMBUSTOR Helmut F. Butze and David A. Kendall 1973 12 p refs Presented at 9th Propulsion Conf, Las Vegas. Nev.. 5-7 Nov. 1973: sponsored by AIAA and Soc. of Automotive Engr. (NASA-TM-X-71429: E-7680) Avail: NTIS HC $3.00 CSCL 21E Sensory odor tests of the exhaust from a turbojet combustor operating at simulated idle conditions were made by a human panel sniffing diluted exhaust gas. Simultaneously, samples of undiluted exhaust gas were collected on adsorbent substrates, subsequently removed by solvent flushing, and analyzed chemically by liquid chromatographic methods. The concentrations of the principal malodorous species, the aromatic (unburned fuel-related) and the oxygenated (partially burned fuel) fractions, as determined chromatographically. correlated well with the intensity of the odor as determined by sniffing. Odor intensity increased as combustion efficiency decreased. Combustor modifications which increased combustion efficiency decreased odor intensity. Author N73-32614*# National Aeronautics and Space Administration. Lewis Research Center. Cleveland, Ohio. THE EFFECTS OF INLET TEMPERATURE AND PRESSURE DISTORTION ON TURBOJET PERFORMANCE Willis M. Braithwaite. Edwin J. Graber. Jr., and Charles M. Mehalic 1973 16 p refs Presented at 9th Propulsion Joint Specialists Conf., Las Vegas, Nev.. 5-7 Nov. 1973: sponsored by AIAA and Soc. of Automotive Engr. (NASA-TM-X-71431: E-7302) Avail: NTIS HC $3.00 CSCL 21E The effects on stability of steady-state, 180 degree extent circumferential distortions of inlet total temperature and pressure were experimentally determined for a turbojet engine. Results for both individual and combined temperature and pressure distortions are presented showing the losses incurred in stall pressure ratio and are compared with results predicted using a simplified parallel compressor model. The loss due to combined distortions was dependent upon the relative orientation between the low pressure and high temperature regions. Reasonable agreement was achieved between the predicted and observed loss in stall pressure ratio when based on a constant corrected speed relationship. Author N73-32620*# National Aeronautics and Space Administration. Lewis Research Center, Cleveland. Ohio. THE EFFECT OF NOISE CONSTRAINTS ON ENGINE CYCLE OPTIMIZATION FOR LONG-HAUL TRANSPORTS Robert J. Antl 1973 11 p refs Presented at the 9th Propulsion Joint Specialist Conf.. Las Vegas. Nev.. 5-7 Nov. 1973: sponsored by AIAA and SAE (NASA-TM-X-71447; E-7712) Avail: NTIS HC $3.00 CSCL 21A N73-32622*# National Aeronautics and Space Administration. Lewis Research Center. Cleveland. Ohio. THRUST AND PUMPING CHARACTERISTICS OF CYLIN- DRICAL EJECTORS USING AFTERBURNING TURBOJET GAS GENERATOR Nick E. Samanich and Sidney C. Huntley 1969 44 p refs (NASA-TM-X-52565) Avail: NTIS HC $4.25 CSCL 21E Static tests of cylindrical ejectors having ejector to primary diameter ratios from 1.1 to 1.6 and ejector length to primary nozzle diameter ratios from 0.9 to 2.1 are reported. Power setting of the J85-13 turbojet engine was varied from part power to maximum afterburning. Corrected secondary weight flow ratio was varied from 0.02 to 0.08 over a range of exhaust nozzle pressure ratios from 2.0 to 9.0. Secondary flow temperature rise and pressure drop characterist ics through the nacelle secondary flow passage were also obtained. Author N73-32624*# Santa Clara Univ.. Calif. R E V E R S E D COWL FLAP INLET THRUST AUGMENTOR Patent Application Dah Yu Cheng, inventor (to NASA) Filed 17 Sep. 1973 18 p (Grant NGR-05-017-033) (NASA-Case-ARC-10754-1: US-Patent-Appl-SN-398886) Avail: NTIS HC $3.00 CSCL 21E An adjustable airfoil is described for varying the geometry of a jet inlet and an ejector inlet in a jet engine for providing thrust augmentation and noise reduction. The airfoil comprises essentially a plurality of segments which are extended radially outwardly and retracted relative to the longitudinal axis of the engine as a function of a change in the pressure differential between the upstream and downstream surfaces of the airfoil. A servo mechanism responsive to the change in the pressure differential is coupled to the airfoil to extend and retract the airfoil segments to maintain the pressure at a maximum on the downstream side of the airfoil relative to the pressure on the upstream side of the airfoil. At low speeds, such as at take-offs and landings, the airfoil is fully extended while at high speeds it is fully retracted. NASA N73-32626# Office National d'Etudes et de Recherches Aerospatiales, Paris (France). P E R F O R M A N C E OPTIMIZATION FOR SUPERSONIC RAMJET THEORETICAL AND EXPERIMENTAL STUDIES Francis Hirsinger 1972 12 p refs In FRENCH: ENGLISH summary Presented at 1st Intern. Symp. on Air Breathing Engines. Marseille, 19-23 Jun. 1972 Avail: NTIS HC $3.00 Simple theoretical studies show off a combustion process called transition combustion, which is of interest for airbreathing propulsion by means of fixed geometry ramjets, and permits emphasis on some principles for the performance, optimization. During this combustion, which is initiated at subsonic speed, the stream is accelerated, through a thermal throat, up to a supersonic speed. Experimental tests were run which confirm the existence of this phenomenon and have helped to elaborate ^mathematical pattern fitted Jo _a_p.rqper description of the flow. 652 N73-32636 This pattern may be used successfully for the prediction of the optimal performances. Computed results show that the so defined configuration leads to competitive performances in a wide domain of flight velocity. Author N73-32628# Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt. Porz (West Germany). Inst. fuer Luftstrahl- antriebe. A NON-CONTACT METHOD FOR SUPERVISION AND MEASUREMENT OF THE EFFECTIVE GAP BETWEEN ROTOR BLADES AND CASING OF TURBOMACHINE DURING OPERATION [UEBER EIN BERUEHRUNGSLOSES VERFAHREN ZUR UEBERWACHUNG UND MESSUNG DER EFFEKTIVEN SPALTE 74 ISCHEN DEN LAUFRADSCHAU- FELN UND DEM GEHAEUSE VON TURBOMASCHINEN WAEHREND DES BETRIEBSJ Hans Hungenberg and Heinrich Weyer 27 Jun. 1972 33 p refs In GERMAN; ENGLISH summary (DLR-FB-72-40) Avail: NTIS HC $3.75; DFVLR. Porz. West Ger. 11.30 DM A contactless. capacitive method for measuring the gaps' between the rotor blades and the casing of a running turbomachine is discribed. The main parameters affecting this method are explained. From this, the most practical calibration of the probe was derived and the limits of the measuring accuracy are shown. Directions for the construction of the probe are given, and some results from measurements of the tip clearance in an axial flow compressor are presented. Author (ESRO) N73-32631# Air Force Systems Command. Wright-Patterson AFB, Ohio. Foreign Technology Div. APPLICATION OF THE THEORY OF SIMILITUDE TO THE DESIGN OF CONTROL SYSTEMS FOR GAS TURBINE ENGINES Yu. V. Lvubomudrov 25 May 1973 267 p refs Transl. into ENGLISH from Mono. "Primenenie Teorii Podobiya pri Gazoturbin- nykh Dvigatelei" Moscow. 1971 p 1-20 (AD-764683: FTD-HC-23-1340-72) Avail: NTIS CSCL 21/5 The report discusses the questions related to optimum design using the theory of similitude of automatic control systems for aircraft gas turbine engines (GTE) considered as objects with characteristics varying during flight. The equation of motion of the controlled object, expressed in terms of reduced variables, is unique for all conditions of its operation and may be represented as a graph of the dynamic characteristic of a GTE that can be used as a basis to determine the required control laws. The selection of the optimal formula for the control system is done by using power complexes of GTE parameters. A foundation is provided for the principles of designing a single control system that combines higher reliability of control in the entire range of flight conditions with reliability of control. GRA N73-32632# ARO. Inc., Arnold Air Force Station. Tenn. MEASUREMENT OF EXHAUST EMISSIONS FROM A 185-GE-5B ENGINE AT SIMULATED HIGH-ALTITUDE SUPERSONIC FREE-STREAM FLIGHT CONDITIONS Technical Report. 15 Dec. 1972 - 10 Jan. 1973 R. C. German. M. D. High, and C. E. Robinson AEDC Jul. 1973 140 p refs (Contract DOT-AS-20024; ARO Proj. PA038; ARO Proj. PB038) (AD-764717. ARO-PWT-TR-73-49; AEDC-TR-73-103; FAA-RD-73-92) Avail: NTIS CSCL 21/5 Exhaust emissions were measured in the plume of a J85-GE-5 turbojet engine as part of an investigation to determine the impact on the climate of a fleet of supersonic aircraft flying in the stratosphere. Measurements were made for both military and partial afterburning power at Mach numbers and simulated altitudes of Mach 1.6/55.000 ft and Mach 2.0/65.000 ft. A continuous sampling technique was used to measure carbon dioxide, carbon monoxide, total unburned hydrocarbons, oxides of nitrogen, and participates. The experimental results were compared with the calculated emission profiles and were in good agreement. The results represent the only available full-scale turbojet engine emission data to date which have been obtained at simulated high altitude with a supersonic, external stream. (Modified author abstract) GRA N73-32633# Dayton Univ. Research Inst.. Ohio. A COMPUTER PROGRAM FOR AXIAL COMPRESSOR DESIGN. VOLUME 1: THEORY DESCRIPTIONS. AND USERS INSTRUCTIONS Final Technical Report, 16 Jun. 1972 - 15 Jun. 1973 Richard M. Hearsey Jul. 1973 96 p refs 2 Vol. (Contract F33615-72-C-2026; AF Proj. 3066; AF Proj. 7065) (AD-764733: AFAPL-TR-73-66-Vol-1) CSCL 21/5 A computer program for the design of axial compressors is presented. It comprises of three principal sections, two alternative means of determining blade geometry, and an aerodynamic computation for the flow through the compressor. One method of determining blade geometry revolves around the use of various analytic meanlines for the blade sections, and leads to the aerodynamic analysis of the flow through specified blading. The other method consists of creating arbitrary blade sections to follow the flow directions previously determined in an aerodynamic design calculation. The aerodynamic design section incorporates a loss calculation routine that may be used to estimate the design point performance of the compressor. The report describes the computer program, and gives all information necessary to use it. (Modified author abstract) GRA N73-32634# Dayton Univ. Research Inst.. Ohio. A COMPUTER PROGRAM FOR AXIAL C O M P R E S S O R DESIGN. VOLUME 2: PROGRAM LISTING AND PROGRAM USE EXAMPLE Final Technical Report. 16 Jun. 1972 - 15 Jun 1973 Richard M. Hearsey Aug. 1973 160 p 2 Vol. (Contract F33615-72-C-2026; AF Proj. 3066; AF Proj. 7065) (AD-764734; AFAPL-TR-73-66-Vol-2) Avail: NTIS CSCL 21/5 A computer program for the design of axial compressors is presented. It comprises of three principal sections; two alternative means of determining blade geometry, and an aerodynamic computation for the flow through the compressor. The report shows the FORTRAN program listing and an example of the use of the program. (Modified author abstract) GRA N73-32636# Aerospace Research Labs.. Wright-Patterson AFB. Ohio. THE DESIGN OF AXIAL COMPRESSOR AIRFOILS USING ARBITRARY CAMBER LINES Final Report George R. Frost and Arthur J. Wennerstrom Jul. 1973 106 p refs (AF Proj. 7065) (AD-765165; ARL-73-0107) Avail. NTIS CSCL 21/5 The report describes a technique which has been developed for use in the design of axial compressor airfoils with camber lines of arbitrary shape. The slope of the camber line at several points on a streamsurface is determined from the air angles at these points as well as the incidence and deviation angle distributions for the blade. A camber line is produced by fitting a smooth curve segment through each pair of points from the leading to the trailing edge. A thickness distribution is applied to this camber line to produce the blade element. A computer program, which uses this technique to produce blade elements, stacks them, and then determines coordinates for plane surfaces through the resultant blade is also described. Author (GRA) 653 N73-32638 N73-32638# General Motors Corp., Indianapolis. Ind. Diesel Allison Div. INVESTIGATION OF AIRCRAFT GAS TURBINE COM BUS- TOR HAVING LOW MASS EMISSIONS Final Report D. L Troth. A. J. Verdouw. and F. J. Verkamp Fort Eustis. Va. Army Air Mobility Res. and Develop. Lab. Apr. 1973 730 p refs (Contract DAAJ02-72-C-0005: DA Proj. 1G1-62207-AA-71) (AD-764987; ERD-7725: USAAMRDL-TR-73-6) Avail: NTIS CSCL 13/2 The objective of this one-year program was to develop and demonstrate emission abatement technology sufficient to obtain a 50% overall reduction in gas turbine engine mass emissions (CO. CxHy. NOx and smoke) with no increase in any individual pollutant when tested over a typical Army light observation helicopter (LOH) duty cycle. The selected baseline was the Army T63-A-5A gas turbine engine combustor. Seventeen potential low-emission combustors. each incorporating one or more of the selected concepts, were tested to determine their emission performance. Experimental results indicated that several designs had the potential for meeting the program objectives. Two combustors selected for final experimental evaluation were the Prechamber and Modified Conventional. The low-emission feature in the Prechamber combustor was premix/prevaporization. The Modified Conventional combustor incorporated four low- emission features: airblast fuel atomization. delayed dilution, convection cooling, and variable geometry. Both of these combustors met the emission reduction objectives. Experimental results indicated that both of these liners can be developed to meet all other conventional T63 combustor requirements, i.e., light-off, temperature profile, durability, etc. The estimated development time for the Prechamber is longer than for the Modified Conventional. However, the Prechamber combustor has better emission reduction potential when both combustors are designed as either fixed or variable geometry combustors. (Modified author abstract) GRA N73-32735*# Dudley Observatory, Albany, N.Y. FEASIBILITY STUDY FOR THE USE OF A YF-12 AIRCRAFT AS A SCIENTIFIC INSTRUMENT PLATFORM FOR OBSERV- ING THE 1970 SOLAR ECLIPSE Final Technical Report Robert D. Mercer 18 Sep. 1973 284 p refs (Grant NGR-33-011-009) (NASA-CR-135482) Avail. NTIS HC $16.25 CSCL 03A The scientific and engineering findings are presented of the feasibility study for the use of a YF-12 aircraft as a scientific instrument platform for observing the 1970 solar eclipse. Included in the report is the computer program documentation of the solar eclipse determination; summary data on SR-71A type aircraft capabilities and limitations as an observing platform for solar eclipses: and the recordings of an informal conference on observations of solar eclipses using SR-71 A type aircraft. K.M.M. and the subscript u denotes the value at zero humidity), the emission index increased exponentially with increasing normalized inlet air temperature to the 1.14 power. Additional tests made to determine the effect of pressure and reference Mach number on NOx showed that the NOx emission index varies directly with pressure to the 0.5 power and inversely with reference Mach number. • Author N73-32842*# Stanford Univ.. Calif. Dept. of Aeronautics and Astronautics. STUDIES IN SHORT HAUL AIR TRANSPORTATION IN THE CALIFORNIA CORRIDOR: EFFECTS OF DESIGN-RUNWAY LENGTH; COMMUNITY A C C E P T A N C E ; IMPACT OF RETURN ON INVESTMENT AND FUEL COST INCREASES. VOLUME 1 Richard S. Shevell and David W. Jones. Jr. Jul. 1973 207 p refs 2 Vol. (Contract NAS2-7199) (NASA-CR-114634; SUDAAR-460-Vol-1) Avail: NTIS HC $12.50 CSCL01E The impact of design runway length on the economics and traffic demand of a 1985 short haul air transportation system in the California Corridor was investigated.' The community acceptance of new commercial airports for short haul service was studied. The following subjects were analyzed: (1) travel demand. (2) vehicle technology. (3) infrastructure. (4) systems analysis, and (5) effects on the community. The operation of the short haul system is compared with conventional airline operations. Author N73-32843*# Stanford Univ.. Calif. Dept. of Aeronautics and Astronautics. STUDIES IN SHORT HAUL AIR TRANSPORTATION IN THE CALIFORNIA CORRIDOR: EFFECTS OF DESIGN RUNWAY LENGTH; COMMUNITY ACCEPTANCE; IMPACT OF RETURN ON INVESTMENT AND FUEL COST INCREASES. VOLUME 2: APPENDICES Richard S. Shevell and David W. Jones. Jr. Jul. 1973 194 p refs 2 Vol. (Contract NAS2-7199) (NASA-CR-114634(1); SUDAAR-460-Vol-2-App) Avail: NTIS HC $11.75 CSCL01E The development of a forecast model for short haul air transportation systems in the California Corridor is. discussed. The factors which determine the level of air traffic demand are identified. A forecast equation for use in airport utilization analysis is developed. A mathematical model is submitted to show the relationship between population, employment, and income for indicating future air transportation utilization. Diagrams and tables of data are included to support the conclusions reached regarding air transportation economic factors. Author N73-32822*tf National Aeronautics and Space Administration. Lewis Research Center, Cleveland, Ohio. EFFECT OF INLET-AIR HUMIDITY, T E M P E R A T U R E , PRESSURE, AND REFERENCE MACH NUMBER ON THE FORMATION OF OXIDES OF NITROGEN IN A GAS TURBINE COMBUSTOR Nicholas R. Marchionna, Larry A. Diehl, and Arthur M. Trout Washington Oct. 1973 34 p refs (NASA-TN-D-7396; E-7465) Avail: NTIS HC $3.00 CSCL 21B Tests were conducted to determine the effect of inlet air humidity on the formation of oxides of nitrogen (NOx) from a gas turbine combustor. Combustor inlet air temperature ranged from 506 K (450 F) to 838 K (1050 F). The tests were primarily run at a constant pressure of 6 atmospheres and reference Mach number of 0.065. The NOx emission index was found to decrease with increasing inlet air humidity at a constant exponential rate: NOx = NOxOe-19H (where H is the humidity N73-32848*# Massachusetts Inst. of Tech.. Cambridge. Flight Transportation Lab. PROCEEDINGS OF THE NASA/MIT W O R K S H O P ON AIRLINE SYSTEMS ANALYSIS. VOLUME 1 Joseph F. Vittek. ed. Jul. 1972 744 p refs Workshop held at Waterville Valley. New Hampshire, 10-21 Jul. 1972 2 Vol. (Contract NASw-2412) (NASA-CR-135634; FTL-R72-7-Vol-1) Avail: NTIS HC $39.25 CSCL 05C Economic principles, financial aspects, forecast and demand, and marketing in the development of an air transport industry are considered. N73-32849* Massachusetts Inst. of Tech., Cambridge. DEVELOPMENT OF THE AIR TRANSPORT INDUSTRY Nawal Taneja In its Proc. of the NASA/MIT Workshop on 654 N73-32857 Airline Systems Analysis. Vol. 1 Jul! 1972 p 1-44 refs CSCL 05C The major developments are outlined in the U.S. scheduled air transport industry both domestic and international, together with a brief history of the European air transport system. The role and formulation of the U.S. Civil Aeronautics Board. International Civil Aviation Organization, and International Air Transport Association are also covered. Author N73-32850* Massachusetts Inst. of Tech.. Cambridge. Flight Transportation Lab. THE ROLE OF THE FEDERAL GOVERNMENT IN THE DEVELOPMENT OF THE US AIR TRANSPORTATION SYSTEM Joseph F, Vittek In its Proc. of the NASA/MIT Workshop on Airline Systems Analysis. Vol. 1 Jul. 1972 27 p CSCL 05A Reviewed are the roles of the various Federal agencies in the regulation, control, and development of the Air System, with major emphasis on the Department of Transportation (Office of the Secretary. Federal Aviation Administration, and National Transportation Safety Board) and the Civil Aeronautics Board. Author N73-32851* Massachusetts Inst. of Tech.. Cambridge. Flight Transportation Lab. AN ANALYSIS OF AIRLINE COSTS. LECTURE NOTES FOR MIT COURSES. THE 16.73 AIRLINE MANAGEMENT AND MARKETING Robert W. Simpson In its Proc. of the NASA/MIT Workshop on Airline Systems Analysis. Vol. 1 Jul. 1972 43 p refs CSCL 05A The cost analyst must understand the operations of the airline and how the activities of the airline are measured, as well as how the costs are incurred and recorded. The data source is usually a cost accounting process. This provides data on the cumulated expenses in various categories over a time period like a quarter, or year, and must be correlated by the analyst with cumulated measures of airline activity which seem to be causing this expense. Author N73-32852* Massachusetts Inst. of Tech.. Cambridge. THE "ATA-67 FORMULA FOR DIRECT OPERATING COST Henry B. Faulkner In its Proc. of the NASA/MIT Workshop on Airline Systems Analysis. Vol. 1 Jul. 1972 18 p refs CSCL 05C The ATA formulas for direct operating cost were developed for the purpose of comparing different aircraft, existing or not. on the same route or the same aircraft on different routes. Such characteristics of the airline as crew pay. maintenance procedures, and depreciation schedules are kept constant. In air transportation systems analysis the 1967 ATA formula is usually used with appropriate exceptions or modifications, such as: different maintenance labor rate, total maintenance multiplied by a factor, maintenance burden deleted, different depreciation schedule, or different spares percentages. Author N73-32853* Massachusetts Inst. of Tech.. Cambridge. Flight Transportation Lab. TECHNOLOGY FOR DESIGN OF TRANSPORT AIRCRAFT. LECTURE NOTES FOR MIT COURSES: SEMINAR 1.61 FRESHMAN SEMINAR IN AIR TRANSPORTATION AND GRADUATE COURSE 1.201. TRANSPORTATION SYSTEMS ANALYSIS Robert W. Simpson In its Proc. of the NASA/MIT Workshop on Airline Systems Analysis. Vol. 1 Jul. 1972 50 p CSCL 01C The design parameters which determine cruise performance for a conventional subsonic jet transport are discussed. It is assumed that the aircraft burns climb fuel to reach cruising altitude and that aeronautical technology determines the ability to carry a given payload at cruising altitude. It is shown that different sizes of transport aircraft are needed to provide the cost optimal vehicle for different given payload-range objectives. G.G. N73-32864* Harvard Univ.. Cambridge. Mass. Dept. of Economics. BASIC ECONOMIC PRINCIPLES T. Nicholaus Tideman In MIT Proc. of the NASA/MIT Workshop on Airline Systems Analysis. Vol. 1 Jul. 1972 7 p refs CSCL 05C An economic approach to design efficient transportation systems involves maximizing an objective function that reflects both goals and costs. A demand curve can be derived by finding the quantities of a good that solve the maximization problem as one varies the price of that commodity, holding income and the prices of all other goods constant. A supply curve is derived by applying the idea of profit maximization of firms. The production function determines the relationship between input and output. G.G. N73-328SS* Massachusetts Inst. of Tech.. Cambridge. BASIC TRANSPORTATION ECONOMICS James T. Kneafsey In its Proc. of the NASA/MIT Workshop on Airline Systems Analysis. Vol. 1 Jul. 1972 18 p refs CSCL 05C Transportation economics is an integral part of all transporta- tion activities. Refined, detailed, and careful economic analyses consider conduct-performance methodology and the specifications of production, cost and demand functions. Author N73-32856* Texas A&M Univ.. College Station. DETERMINATION OF FARES: PRICING THEORY AND ECONOMIC EFFICIENCY James C. Miller. Ill In MIT Proc. of the NASA/MIT Workshop on Airline Systems Analysis. Vol. 1 Jul. 1972 30 p refs CSCL 05C The concept of economic efficiency is described, its applica- tion to the pricing of air transport services, and its relevance as a policy objective are outlined. The first two sections discuss economic efficiency in general terms, whereas the third applies this norm to several airline pricing problems. The final section emphasizes the importance of industry behavior as a parameter in policy analysis. Author N73-32857* United Air Lines. Inc.. Chicago. III. DIFFERENTIAL PRICING POLICY J. B. Gebhardt In MIT Proc. of the NASA/MIT Workshop on Airline Systems Analysis. Vol. 1 Jul. 1972 15 p' CSCL 05C Differential pricing is a valid means of improving- profits, keeping the total cost of air transportation down, and making it possible for more people to use air transportation. Author 655 N73-32858 N73-32858* United Air Lines.-Inc.. Chicago. III. THE ECONOMIC EFFECT OF COMPETITION IN THE AIR TRANSPORTATION INDUSTRY Herbert B. Hubbard In MIT Proc. of the NASA/MIT Workshop on Airline Systems Analysis, Vol. 1 Jul. 1972 25 p CSCL 05C The air transportation industry has been described as a highly-competitive, regulated oligopoly or as a price-regulated cartel with blocked entry, resulting in excessive service and low load factors. The current structure of the industry has been strongly influenced by the hypotheses that increased levels of competition are desirable per se. and that more competing carriers can be economically supported in larger markets, in longer haul markets, with lower unit costs, and with higher fare levels. An elementary application of competition/game theory casts doubt on the validity of these hypotheses, but rather emphasizes the critical importance of the short-term non-variable costs in determining economic levels of competition. Author N73-32859* Massachusetts Inst. of Tech.. Cambridge. Flight Transportation Lab. BASIC FINANCE Joseph F. Vittek In its Proc. of the NASA/MIT Workshop on Airline Systems Analysis. Vol. 1 Jul. 1972 66 p CSCL 05C A discussion of the basic measures of corporate financial strength, and the sources of the information is reported. Considered are: balance sheet, income statement, funds and cash flow, and financial ratios. Author N73-32860* Air Transport Association of America, Washington, D.C. CAPITAL REQUIREMENTS FOR THE AIR TRANSPORT INDUSTRY George W. James In MIT Proc. of the NASA/MIT Workshop on Airline Systems Analysis. Vol. 1 Jul. 1972 13 p CSCL 05C In recent years the U.S. scheduled airline industry has been involved in the largest re-equipment program that involves the addition of hundreds of new aircraft to the airline fleet. The costs associated with the purchase of this new equipment, along with the other costs involving such matters as the environment and security, are presenting the carriers with significant financial challenges. Author N73-32861* American Airlines. Inc.. New York. FINANCING THE AIR TRANSPORTATION INDUSTRY D. J. Lloyd-Jones In MIT Proc. of the NASA/MIT Workshop on Airline Systems Analysis, Vol. 1 Jul. 1972 50 p CSCL 05C The basic characteristics of the air transportation industry are outlined and it is shown how they affect financing requirements and patterns of production. The choice of financial timing is imperative in order to get the best interest rates available and to insure a fair return to investors. The fact that the industry cannot store its products has a fairly major effect on the amount of equipment to purchase, the amount of capital investment required, and the amount of return required to offset industry depriciation. G.G. N73-32862* Export-Import Bank. Washington. D.C. THE ROUE OF THE EXPORT-IMPORT BANK IN DEVE! OP- ING THE EXPORT POTENTIAL OF AIRCRAFT SALES Chosei Kuge In MIT Proc. of the NASA/MIT-Workshop-on Airline Systems Analysis. Vol. 1 1972 11 p CSCL 05C A description of the current patterns, terms, and conditions of Eximbank commercial jet aircraft export financing is given. Some discussion of the factors affecting export financing will be noted. -. . . , Author N73-32863* Massachusetts Inst. of Tech.. Cambridge. Flight Transportation Lab. THE MARKET DEMAND FOR AIR TRANSPORTATION ,, Nawal Taneja In its Proc. of the NASA/MIT Workshop on Airline Systems Analysis. Vol. 1 Jul. 1972 65 p refs CSCL 05C Although the presentation will touch upon the areas of market for air transportation, the theoretical -foundations of the demand function, the demand models, and model selection and evaluation, the emphasis of the presentation will be on a qualitative description of the factors affecting the demand for air transporta- tion. The presentation will rely heavily on the results of market surveys carried out by the Port of New York Authority, the University of Michigan, and Census of Transportation. Author N73-32864* Massachusetts Inst. of Tech.. Cambridge. Flight Transportation Lab. TECHNIQUES FOR FORECASTING AIR PASSENGER TRAFFIC Nawal Taneja In its Proc. of the NASA/MIT Workshop on Airline Systems Analysis, Vol. 1 Jul. 1972 .16 p refs CSCL 05A The basic techniques of forecasting the air passenger traffic are outlined. These techniques can be broadly classified into four categories: judgmental, time-series analysis, market analysis and analytical. The differences between these methods exist, in part, due to the degree of formalization of the forecasting procedure. Emphasis is placed on describing the analytical method. Author N73-32865* International Civil Aviation Organization. Montreal (Quebec). AVIATION FORECASTING IN ICAO '-,, James McMahon In MIT Proc. of the NASA/MIT Workshop on Airline Systems Analysis, Vol. 1 Jul. 1972 20 p CSCL 05A Opinions or plans of qualified experts in the field are used for forecasting future requirements for air navigational facilities and services of international civil aviation. ICAO periodically collects information from Stators and operates on anticipated future operations, consolidates this information, and forecasts the future level of activity at different airports. Author N73-32866* American Airlines. Inc.. New York. A M E R I C A N AIRLINES PROPELLER STOL TRANSPORT ECONOMIC RISK ANALYSIS Bob Ransone In MIT Proc. of the NASA/MIT Workshop on Airline Systems Analysis. Vol. 1 Jul. 1972 27 p ' CSCL 05C A Monte Carlo risk analysis on the economics of STOL transports in air passenger traffic established the probability of 656 N73-32876 making the expected internal rate of financial return, or better. in a hypothetical regular Washington/New York intercity operation. G.G. N73-32869* Harvard Univ.. Cambridge. Mass DETERMINANTS OF MARKET STRUCTURE AND THE AIRLINE INDUSTRY William Raduchel In MIT Proc. of the NASA/MIT Workshop on Airline Systems Analysis. Vol. 1 Jul. 1972 20 p CSCL 05A The general economic determinants of market structure are outlined with special reference to the airline industry. Included are the following facets: absolute size of firms; distributions of firms by size; concentration, entry barriers, product and service differentiation; diversification; degrees of competition; vertical integration; market boundaries; and economies of scale. Also examined are the static and dynamic properties of market structure in terms of mergers, government policies, and economic growth conditions. Author N73-32870* Massachusetts Inst. of Tech., Cambridge. OBJECTIVES OF THE AIRLINE FIRM: THEORY James T. Kneafsey In its Proc. of the NASA/MIT Workshop on Airline Systems Analysis. Vol. 1 Jul. 1972 14 p CSCL 05A Theoretical models are formulated for airline firm operations that revolve around alternative formulations of managerial goals which these firms are persuing in practice. Consideration is given to the different objective functions which the companies are following in lieu of profit maximization. G.G. N73-32871* North Carolina Univ.. Chapel Hill. PROBLEMS OF EXCESS CAPACITY George Douglas In MIT Proc. of the NASA/MIT Workshop on Airline Systems Analysis. Vol. 1 Jul. 1972 15 p CSCL 05A The problems of excess capacity in the airline industry are discussed with focus on the following topics: load factors: fair rate of return on investment; service-quality rivalry among airlines: pricing (fare) policies: aircraft production: and the impacts of excess capacity on operating costs. Also included is a discus- sion of the interrelationships among these topics. Author N73-32873* Pan American World Airways. Inc.. New York. CONSUMER MARKETING AND THE AIRLINE INDUSTRY William R. Roy In MIT Proc. of the NASA/MIT Workshop on Airline Systems Analysis. Vol. 1 Jul. 1972 21 p CSCL 05A The fundamentals of consumer marketing as applied to the airline industry are considered. An attempt is made to boil down the mystique and jargon which frequently surround the subject of marketing. Topics covered include: (1) The marketing concept: 12) consumer expectations from airlines; 13) planning of marketing strategy: and (4) the roles of advertising, sales, and middlemen. Author N73-32874* Pan American World Airways. Inc.. New York. FUTURE DIRECTION IN AIRLINE MARKETING Dan A. Colussy In MIT Proc. of the NASA/MIT Workshop on Airline Systems Analysis. Vol. 1 Jul. 1972 20 p CSCL 05A The rapid growth and broadening of the air travel market, coupled with a more sophisticated consumer, will dramatically change airline marketing over the next decade. Discussed is the direction this change is likely to take and its implications for companies within the industry. New conceptualization approaches are required if the full potential of this expanding market is to be fully realized. Marketing strategies are developed that will enable various elements of the travel industry to compete not only against each other but also with other products that are competing for the consumer's discretionary income. Author N73-32875*# Massachusetts Inst. of Tech.. Cambridge Flight Transportation Lab. MIT-NASA WORKSHOP AIRLINE SYSTEMS ANALYSIS. VOLUME 2 Jul. 1972 602 p refs (Contract NASw-2412) (NASA-CR-135635; FTL-R72-7-Vo l -2 ) Avail: NTIS HC $32.25 CSCL 05A The proceedings of a conference on the Air Transport Industry are presented. The subjects discussed are: (1) analysis of .airline costs. (2) transportation economics. (3) airline financing. (4) market demand for air transportation. (5) planning, management, and economics of airport operation. (6) air cargo operations. (7) commuter aircraft operations. (SI regulation of air traffic rates. (9) airline merger policies, and (10) international air transportation operations. N73-32872* Douglas Aircraft Co.. Inc., Long Beach. Calif. THE ROLE OF THE MANUFACTURER IN AIR TRANSPOR- TATION PLANNING James MacKenzie In MIT Proc. of the NASA/MIT Workshop on Airline Systems Analysis. Vol. 1 Jul. 1972 40 p CSCL 05A The role of the aircraft manufacturer in the airline industry is considered. The process is illustrated by using a fictitious airline as an example-thai is, a case study approach with Mid-Coast Airways serving as the example. Both in slide form and with supporting papers, a brief history of the airline, a description of its route structure and a forecast based on econometric analysis are presented. Once the forecast rationale is explained, information outlines the requirements for additional aircraft and the application of new aircraft across the system using alternative fleet plan options. The fleet plan is translated into financial summaries which indicate the relative merit of alternative aircraft types or operating plans. Author N73-32876* Massachusetts Inst. of Tech.. Cambridge. CONCENTRATION OF AIRLINE OPERATIONS AT INDIVID- UAL AIRPORTS W. Gelerman and R. DeNeufville In its MIT-NASA Workshop on Airline Systems Analysis. Vol. 2 Jul. 1972 29 p refs CSCL 01E It is shown that it is a natural property of air transportation networks for competitive airlines to concentrate their operations at individual airports serving a given market. This implies that a strategy of developing satellite airports is doomed to failure unless the competitives behavior of the airlines is restricted. The results are demonstrated by tracing out the implications of observed patterns of traveller behavior as regards choice of carrier on the optimal game strategy for any particular airline. Analytic results for a two airline, two airport situation are extrapolated to the more general case, and specific supportive evidence from current operations are cited. Author 657 N73-32877 N73-32877* Massachusetts Inst. of Tech.. Cambridge. PLANNING, MANAGEMENT, AND ECONOMICS OF AIRPORT OPERATION John Wiley In its MIT-NASA Workshop qn Airline Systems Analysis. Vol 2 Jul. 1972 18 p CSCL 05A An overview of the role of the airport in the transportation complex and in the community is presented. The establishment of the airport including its requirements in regional planning and the operation of the airport as a social and economic force are discussed. Author John W. Kersey In MIT MiT-NASA Workshop on Airline Systems Analysis. Vol. 2 Jul. 1972 Up CSCL 05A The economic factors involved in air cargo operations and air cargo marketing development are discussed. Specific steps which are followed by various airports to reduce operating costs are described. The economics of cargo handling within an airline are analyzed with respect to: (1) paperwork costs. (2) terminal costs. (3) line haul costs, and (4) claims costs. Author N73-32878* Port of New York Authority. N.Y. AIRPORT ECONOMICS: MANAGEMENT CONTROL FINANCIAL REPORTING SYSTEMS Allen Buchbinder In MIT MIT-NASA Workshop on Airline Systems Analysis. Vol. 2 Jul. 1972 16 p • CSCL 058 The development of management control financial reporting systems for airport operation is discussed. The operation of the system to provide the reports required for determining the specific revenue producing facilities of airports is described. The organiza- tion of the cost reporting centers to show the types of information provided by the system is analyzed. Author N73-32882* Eastern Air Lines. Inc., Miami. Fla. AIR CARGO MARKETING DEVELOPMENT John W. Kersey In MIT MIT-NASA Workshop on Airline Systems Analysis, Vol. 2 Jul. 1972 12 p CSCL 05A The factors involved in developing a market for air cargo services are discussed. A comparison is made between the passenger traffic problems and those of cargo traffic. Emphasis is placed on distribution analyses which isolates total distribution cost, including logistical costs such as transportation, inventory, materials handling, packaging, and processing. Specific examples of methods for reducing air cargo costs are presented. Author N 73-32879* Port of New York Authority. N.Y. Aviation Economics Div. AIR TRAFFIC FORECASTING AT THE PORT AUTHORITY OF NEW YORK AND NEW JERSEY Johannes G. Augustine In MIT MIT-NASA Workshop on Airline Systems Analysis, Vol. 2 Jul. 1972 23 p refs CSCL 05A Procedures for conducting air traffic forecasts with specific application to the Port Authority of New York and New Jersey are discussed. The procedure relates air travel growth to detailed socio-economic and demographic characteristics of the U.S. population rather than to aggregate economic data such as Gross National Product, personal income, and industrial production. Charts are presented to show the relationship between various selected characteristics and the use of air transportation facilities. Author N73-32880* Massachusetts Port Authority. Boston. ROUTE AWARD CONSIDERATIONS Wilson D Rogers. Jr. In MIT MIT-NASA Workshop on Airline Systems Analysis. Vol. 2 Jul. 1972 22 p CSCL 05A The organization, responsibilities, and functions of the Civil Aeronautics Board are discussed. Several examples of decisions made by the Civil Aeronautics Board on the award of specific air routes to competing air lines are presented. The manner in which route proceedings are initiated and examined is explained. Recommendations are made concerning actions which can be taken to improve the services provided to the flying public. Author N73-32883* Civil Aeronautics Board. Washington. D.C. CURRENT PROBLEMS AND ISSUES IN AIR FREIGHT RATES Alfred R. Stout In MIT MIT-NASA Workshop on Airline Systems Analysis. Vol. 2 Jul. 1972 21 p CSCL 05C Actions of the Civil Aeronautics Board in determining air freight rates are discussed. The tariff filings by domestic airlines for making basic changes in domestic fares and rates are reported. The roles of the carriers and the Civil Aeronautics Board in establishing freight rates are defined. Specific examples of areas of controversy in establishing freight rates are included. Methods for improving the air cargo and freight rate situation are proposed. Author N73-32884* Massachusetts Inst. of Tech., Cambridge. Flight Transportation Lab. THE FUTURE OF THE US DOMESTIC AIR FREIGHT INDUSTRY Lewis M. Schneider In its MIT-NASA Workshop on Airlines Systems Analysis. Vol. 2 Jul. 1972 21 p refs CSCL 05A A research project on the future of U.S. domestic air freight operations was conducted. The two main subjects of the project were: (1) during the 1965 to 1969 time period, when the airlines introduced jet freighters into domestic service and air freight traffic growth continued at a high rate, what strategies were employed by management and with what results and (2) what are the opportunities and problems confronting the domestic air freight industry during the 1970 and 1980 time period. The results of the analysis are presented in the form of graphs and tables. Author N73-32881* Eastern Air Lines, Inc.. Miami. Fla. Cargo Sales and Services. THE ECONOMICS OF AIR CARGO N73-32885* Massachusetts Inst. of Tech.. Cambridge. TRENDS IN COMMUTER AIR CARRIER OPERATIONS William Swan In its MIT-NASA Workshop on Airline Systems Analysis._yol. 2 Jul. 1972 17 p 658 N73-32903 CSCL 05B The market for commuter air service is analyzed. Methods for reducing the costs of short haul air transportation are discussed. The problems facing the operators of short haul air transport services are identified. Proposed changes in commuter air carrier regulation are submitted. Author N73-32886* Civil Aeronautics Board. Washington, D.C. SERVICE TO SMALL COMMUNITIES Monte Lazarus In MIT MIT-NASA Workshop on Airline Systems Analysis. Vol. 2 Jul. 1973 10 p CSCL 05A The problems involved in the operation of low cost local service air carriers are analyzed. Four specific situations which created the operating difficulties of the local air carriers are defined. Proposals of federal and local subsidies for short haul air transportation are presented. Author N73-32887* Charles River Associates. Inc.. Cambridge. Mass. THE SHORT HAUL AIR TRAVEL MARKET: EVALUATION OF NEW FORMS OF SERVICE David A. Couts In MIT MIT-NASA Workshop on Airline Systems Analysis. Vol. 2 Jul. 1972 28 p refs CSCL 05C Aspects of the demand for air travel and an approach for incorporating them in evaluations of new services are discussed. The approach as described here is being used to evaluate the market for STOL aircraft in the 1980's but it could just as well be used to evaluate the market effects of schedule changes, equipment changes, and new routes, if certain basic data relating these changes to demand are available. A most important change in the market which is likely to take place in the next fifteen years, and which is already underway, is the increasing availabil- ity of alternative airports in major cities. Author N73-32888* George Washington Univ.. Washington, D.C. THIRD LEVEL AIR CARRIER SERVICE George Eads In MIT MIT-NASA Workshop on Airline Systems analysis. Vol. 2 Jul. 1972 28 p CSCL 05A A proposed Civil Aviation Board approach to regulating commuter air transportation services is discussed. Operating problems of specific air lines are used as examples. Inadequacies in the present service for short haul commuter air transportation are defined. Methods by which improvements in the commuter air transport service are proposed. Author N73-32894* Harvard Univ., Cambridge. Mass. Harvard Business School. THE FUTURE OF REGULATION IN THE AIRLINE IN- DUSTRY Paul W. Cherington and James J. Hill In MIT MIT-NASA Workshop on Airline Systems Analysis. Vol. 2 21 Jul. 1972 5 p CSCL OSA The Federal regulation of airlines is analyzed to predict the amount of regulation to be expected in the future. It is stated that the regulatory powers will increase because of the advantages that such regulation provides to the airlines. Six propositions are submined as guidelines for future airlines regulation. The loss of revenue experienced by the airlines is examined and methods for improving the economic situation are defined. Author N73-32895* Civil Aeronautics Board. Washington. D.C. MERGERS AND ANTI-TRUST ISSUES IN RECENT CAB CASES A. M. Andrews In MIT MIT-NASA Workshop on Airline System Analysis. Vol. 2 19 Jul. 1972 10 p CSCL OSA The airline industry is surveyed-particularly domestic trunk- lines-in relation to collective approaches to industry concerns. These actions are classified by the apparent degree of anti-trust issue present. Recent route merger cases are considered from the CAB staff viewpoint. Author N73-32899* Civil Aeronautics Board. Washington. D.C. INTERNATIONAL AIR TRANSPORT POLICY Charles Butler In MIT MIT-NASA Workshop on Airline System Analysis. Vol. 2 21 Jul. 1972 31 p CSCL OSA The actions of the Civil Aviation Board in providing assistance and advice to the State Department regarding international air transport policy are discussed. The policies and guidelines of the Civil Aviation Board are defined. The relationship with the policies of the Executive Branch of the Government and the interpretations of the Department of Transportation are re- ported. Author N73-32900* Aerospace Industries Association of America, Inc., Washington. D.C. COMMERCIAL A I R C R A F T DEVELOPMENT AND THE EXPORT MARKET Joseph Snodgrass In MIT MIT-NASA Workshop on Airline Systems Analysis, Vol. 2 20 Jul. 1972 20 p refs CSCL 05C The various factors which endanger the future of com- mercial aircraft development are defined. The factors discussed are: (Da decline in federally funded research and development programs, (2) a general decline in the economic health of the domestic airlines. (3) the increased cost of development which may be several times the net worth of the company, (4) the development overseas of common market and manufacturing consortia. and (5) foreign manufacturers receiving significant financial support from their national governments. It is stated that unless immediate and innovative solutions to combat these factors are found, the commercial aviation industry will be in serious difficulty. Author N73-32902* Department of Transportation, Washington D C INTERNATIONAL: A IR T R A N S P O R T AND FEDERAL POLICY Robert Henri Binder In MIT MIT-NASA Workshop on Airline Systems Analysis. Vol. 2 21 Jul. 1972 12 p CSCL OSA The Federal policy which establishes guidelines for future U.S. participation in the international air transportation industry is discussed. The policy issues discussed include the following: (1) aircraft hijacking, both foreign and domestic, (2) relationship of scheduled services and charter services, (3) capacity problems, and (4) rate regulation. Author N73-32903* Air Transport Association of America. Washington, D.C. UNITED STATES INTERNATIONAL AIR TRANSPORT POLICY, THE PROMISE AND THE REALITY James E. Landry and Gabriel Phillips In MIT MIT-NASA Workshop 659 N73-32905 on Airline Systems Analysis. Vol. 2 21 Jul. 1972 32 p CSCL 05A The United States international air transportation policy is discussed The major departure of the current policy lies in the relationship between scheduled and charter services. Various provisions of the transportation charter are analyzed to show the restrictions as well as the benefits the legislation holds for commercial aviation. It is stated that a group of full service carriers can meet the full spectrum of demands for air transporta- tion more efficiently than two or more groups. Author N73-32905*# Aerospace Corp.. El Segundo. Calif. Air Transportation Group. SYSTEMS EVALUATION OF LOW DENSITY AIR TRANS- PORTATION CONCEPTS R. W. Bruce and H. M. Webb Jul. 1972 96 p refs (Contract NAS2-6473) (NASA-CR-114484; ATR-73I998D-1) Avail: NTIS HC $7.00 CSCL 01E Methods were studied for improving air transportation to low-density population regions in the U.S. through the application of new aeronautical technology. The low-density air service concepts are developed for selected regions, and critical technologies that presently limit the effective application of low-density air transportation systems are identified. F.O.S. of simulation was achieved by having air flow external to and in the dry bays. The results of a wide 'ange of test conditions are presented. The overall conclusion of the investigation was that JP-8 fuel is less susceptible to fire and explosion induced by gunfire and should produce less aircraft structural damage-, than JP-4. Author IGRA) N73-32922 New York Univ.. N.Y. ANALYSIS OF THE LOW-SPEED FLOW OVER A SLENDER SHARP-EDGED DELTA WING AT ANGLES OF ATTACK Ph.D. Thesis Paul LeRoy Coe 1973 75 p Avail: Univ. Microfilms Order No. 73-19383 The phenomena of rolled-up vortex cores above the lee surface of slender bodies, at angle of attack, has been observed since the advent of the highly swept-wing aircraft. Investigations indicate that these vortices exhibit large effects on the longitudinal and lateral stability of these configurations. Because of its geometric simplicity, an untwisted, uncambered, thin, sharp-edged, slender delta wing in subsonic flow is considered. Experimental studies have established the essential features of this type of flow as follows: (1) separation of flow at the leading edges. (2) formation of rolled-up vortex cores above the lee surface. (3) entrainment of mass by the vortex cores. (4) strong axial velocities along the vortex cores and (5) conical flow over the major portion of the wing (with the exception of the apex and trailing edge). Dissert. Abstr. N73-32907# Joint Publications Research Service, Arlington. Va. ECONOMIC EVALUATION OF AIRCRAFT AND SPACE- CRAFT S. A. Sarkisyan and E. S. Minayev 24 Sep. 1973 188 p refs Transl. into ENGLISH from the book "Ekonomicheskaya Otsenka Letatel'nykh Apparatov" Moscow, Izdatel'stvo Mashinost- royeniye. 1972 177 p (JPRS-60104) Avail: NTIS HC $11.50 The report contains a study of the economic problems of the analysis and selection of optimal versions of complex technical systems (in the example of systems of aircraft and spacecraft). The characteristics features and significance of technical progress in the aerospace industry are discussed, and problems of systems analysis when forecasting technical progress are analyzed. Author N73-32917# Army Foreign Science and Technology Center. Charlottesville. Va. TECHNOLOGY AND ARMAMENT. NO. 1. JANUARY 1973 27 Jun. 1973 174 p refs Transl. into ENGLISH of Tekhn. i Vooruzhenie (Moscow), no. 1. 1973 (AD-763323; FSTC-HT-23-1864-73) Avail: NTIS CSCL 15/3 Articles written by Russian officer personnel and by Russian civilian scientific personnel are mainly on new scientific and technological advances. GRA N73-32920# Air Force Aero Propulsion Lab., Wright-Patterson AFB. Ohio VULNERABILITY OF DRY BAYS ADJACENT TO FUEL TANKS UNDER HORIZONTAL GUNFIRE Technical Report. Mar. 1966 - Jun. 1971 Robert G. Clodfelter Mar. 1973 102 p refs (AF Proj. 3048) (AO-764732: AFAPL-TR-72-83) Avail: NTIS CSCL 19/4 The report deals with the relative vulnerability to incendiary action of dry bays adjacent to fuel tanks as a function of fuel type. Cal .50 API horizontal gunfire was the threat: a high level N73-32923 Maryland Univ.. College Park. AERODYNAMIC FORCES ON OBJECTS IN THE NEARLY FREE MOLECULAR FLOW REGIME Ph.D. Thesis William Aaron Kuperman 1972 187 p Avail: Univ. Microfilms Order No. 73-18251 The drag of an object moving in a' rarefied gas is dis- cussed. The first (inverse) Knudsen number correction to the drag in the free molecular flow regime is determined by a set of collision integrals associated with the dynamics of two gas molecules in the presence of the object. These collision inte- grals are analogous to the three-particle collision integrals derived earlier for the transport properties of a moderately dense gas if one of the particles is replaced with the object. Collision integrals for a number of cases assuming a gas of hard sphere molecules which scatter diffusively with the object are calculated. For a sphere moving at low velocity the result is in agreement with Millikan's data for the drag coefficient of oil droplets. For a cylinder and a strip the coefficient of a term logarithmic in the expansion parameter is obtained. Dissert. Abstr. N73-32924*# Remtech. Inc., Birmingham. Ala. WING TIP VORTEX MEASUREMENTS WITH LASER DOPPLER SYSTEMS Charles E. Fuller. Ill Apr. 1973 79 p refs (Contract NAS8-25896) (NASA-CR-124444; RTR-002-3) Avail: NTIS HC $6.00 CSCL 01A The vortex velocity field produced by a rectangular wing in a subsonic wind tunnel was measured using two laser Doppler velocimeter systems. One system made three dimensional mean velocity measurements and the other made one dimensional turbulence measurements. The systems and test procedures are described and comparisons of the measurements are made. The data defined a strong spiral motion in the vortex formation process. Author N73-32926*# National Aeronautics and Space Administration. Ames Research Center. Moffett Field. Calif. AN EXPERIMENTAL INVESTIGATION OF THREE OBLIQUE 660 N73-32933 WING AND BODY COMBINATIONS AT MACH NUMBERS BETWEEN 0.60 AND 1.40 Lawrence A. Graham, Robert T. Jones, and Frederick W. Boltz Apr. 1973 173 p refs (NASA-TM-X-62256) Avail: NTIS HC $10.75 CSCL 01A An experimental investigation was conducted in an 11 - by 11-foot transonic wind tunnel to determine the aerodynamic characteristics of three oblique high aspect ratio wings in combination with a high fineness-ratio Sears-Haack body. The three wings had the same elliptical planform and base line curvature but had different airfoil sections. One wing had an airfoil section designed to have a lift coefficient of 1.0 at a Mach number of 0.7. another to have shock-free supersonic flow over the upper surface, and the other to have a lift coefficient of 1.3 at a Mach number of 0.6. Longitudinal and lateral-directional stability data were obtained at wing yaw angles of 0 deg. 45 deg. 50 deg. and 60 deg over a test Mach number range from 0.6 to 1.4 for angles of attack between minus 7 deg and 9 deg. Reynolds numbers for the study were 4 and 6 million per foot. Flow-visualization studies were made to examine the nature of the flow on the wing surfaces. Notable differences were found in the aerodynamic characteristics of the three wing-body combinations, particularly in the lateral-directional characteris- tics. Author N73-32927*# National Aeronautics and Space Administration. Ames Research Center, Moffett Field. Calif. AN EXPERIMENTAL INVESTIGATION OF AN OBLIQUE WING AND BODY COMBINATION AT MACH NUMBERS BETWEEN 0.60 AND 1.40 Lawrence A. Graham, Robert T. Jones, and Frederick W. Boltz Dec 1972 371 p refs (NASA-TM-X-622071 Avail: NTIS HC $20.75 CSCL 01A An experimental investigation was conducted in an 11- by 11-foot'wind tunnel to determine the aerodynamic characteristics of an oblique high aspect ratio wing in combination with a high fineness-ratio Sears-Haack body. Longitudinal and lateral- directional stability data were obtained at wing yaw angles from 0 deg to 60 deg over a test Mach number range from 0.6 to 1.4 for angles of attack between minus 6 deg and 9 deg. The effects of changes in Reynolds number, dihedral, and trailing-edge angle were studied along with the effects of a roughness strip on the upper and lower surfaces of the wing. Flow-visualization studies were made to determine the nature of the flow on the wing surfaces. Author N73-32929# Royal A i rc ra f t Establishment. Farnborough (England). Structures Dept. RELATIVE FREQUENCY OF OCCURRENCE OF DIFFERENT NORMAL ACCELERATIONS AT THE CENTRE OF GRAVITY OF AIRCRAFT IN TURBULENCE J. Taylor London Aeron. Res. Council 1973 60 p refs Supersedes RAE-TR-71 169; ARC-33503 (ARC-R/M-3714; RAE-TR-71169: ARC-33503) Avail: NTIS HC $5.00: HMSO C2.15: PHI $8.33 An examination is made of the relative frequency of occurrence of different normal accelerations, at points near the aircraft centre of gravity of 5 different aircraft, from about 200 hours of research flying sub-divided into about 12000 time periods mainly of about 1 minute. It is shown that the commonly used assumption of a Rayleigh distribution for vertical gust velocity maxima for each period gives poor estimates of the cumulative totals of all the periods for each aircraft. If. however, it is assumed that (1) the frequency of occurrence of different magnitudes of the maxima of the gust velocity vector is a Rayleigh distribution, and 12) the vector changes direction sufficiently slowly for the maxima of the components to occur at the safne. time as the maxima of the vector, hold for each period, the estimates of the cumulative totals of all the periods for each aircraft do not differ significantly from the measurements. Author (ESRO) N73-32930# National Physical Lab.. Teddington (England). Aerodynamics Div. AN EXPERIMENTAL INVESTIGATION OF WIND TUNNEL WALL CONDITIONS FOR INTERFACE FREE DYNAMIC MEASUREMENTS A. W. Moore and K. C. Wight London Aeron. Res. Council 1973 45 p refs Supersedes NPL-AERO-1307 N71-17085 ARC-31704 (ARC-R/M-3715: NPL-AERO-1307: ARC-31704) Avail: NTIS HC $4.25: HMSO t 1.70: PHI $6.75 Results are presented of dynamic tests on two model half- wings performing pitching oscillations in a tunnel which has a slotted roof and floor with perforations of variable size behind the slots. A porosity is found which gives small interference for all speeds in the range of Mach numbers from 0.40 to 1.05 and a method is suggested for selecting a wall porosity to give interference-free damping derivatives: interference-free stiffness derivatives are not simultaneously obtained and small corrections to measured values are required. Author (ESRO) N73-32931# National Physical Lab.. Teddington (England). Aerodynamics Div. ON THE EFFECTS OF VISCOUS INTERACTION FOR A FLAT DELTA WING AT INCIDENCE L. Davies London Aeron. Res. Council 1973 32 p refs Supersedes ARC-32117 (ARC-CP-1237; ARC-32117) Avail: NTIS HC $3.75; HMSO 55p; PHI $2.35 Equations are derived which enable the effects of viscous interaction on the normal force to be assessed for a flat delta wing at incidence. Author (ESRO) N73-32932# Bristol Univ. (England). Dept. of Aeronautical Engineering. DECAY OF TRAILING VORTICES E. H. Don London Aeron. Res. Council 1973 65 p refs Supersedes ARC-33215 IARC-CP-1238. ARC-33215) Avail. NTIS HC $5.25; HMSO € 1.05; PHI $4.05 Model wings of various planforms were plunged vertically into a water tank and the vortex patterns on the surface were studied. For each wing the wake drift rate was found to increase with incidence and to decrease with increasing core separation. The wake started off with discrete vortex cores which grew independently, maintained their initial separation, and had peak velocities which decayed as time to the minus one-half power. The edges of the cores ultimately came very close together, and thereafter separation distance between the core centers increased with time, and the peak velocities tended to decay at the reciprocal of time. Author (ESRO) N73-32933# Brussels Univ. (Belgium). Inst of Applied Mechanics. STUDY OF BUFFETING MOTION OF AIR CUSHION VEHICLES [ETUDE DU MOUVEMENT DE PILONNEMENT DES VEHICULES A COUSSAIN D'AIR] G. VandeSteen 1973 103 p refs In FRENCH (NT-33-1973) Avail: NTIS HC $7.25 An aerothermodynamical study of buffeting for three types of air cushion vehicle is presented: The main hypotheses are given. A theoretical study for the skirt type vehicle leads to a third order differential equation from which the stability criterion is derived. Experimental tests show the importance of fan characteristics, quasi uniform flow within the skirt, compressibility effects, and non-linear effects. The peripheral jet type may be represented by a second order linear system using a modified Crewe Eddington potential theory with a good approximation 661 N73-32934 The two pressure stage vehicle combines both types above. By combining experimental results and theory, a satisfactory approximation was obtained. In all three cases the transient response is damping coefficient lower than the criticial value. ESRO N73-32934*# National Aeronautics and Space Administration. Langley Research Center. Langley Station. Va. STOL TECHNOLOGY Washington 1972 516 p refs Conf. held at Moffett Field, Calif.. 17-19 Oct. 1972 (NASA-SP-320) Avail: NTIS HC S9.75 CSCL01C The proceedings of a conference on STOL technology are presented. The subjects discussed are: (1) short haul transportation systems. (2) aerodynamic characteristics. (3) aerodynamic loads. (4) flight dynamics, (5) operational aspects. (6) quiet STOL propulsion, and (7) jet powered-lift noise technology. N73-32935* National Aeronautics and Space Administration. Ames Research Center, Moffett Field. Calif SHORT-HAUL TRANSPORTATION IN THE 1980'S Leonard Roberts In its STOL Technol. 1972 p 1-8 refs CSCL 01C The requirements for short-haul air transportation services in the 1980 time period are analyzed. The identification of short takeoff and landing aircraft to perform this service is reviewed. The adequacy of technical programs for developing short-haul aircraft is examined. The characteristics of several candidate short-haul aircraft are described. A system analysis, to include the economic and environmental factors, is developed. Author N73-32936* National Aeronautics and Space Administration. Ames Research Center. Moffett Field. Calif. FUTURE SHORT-FIELD AIRCRAFT Thomas L Galloway In its STOL Technol. 1972 p 9-22 ref CSCL 01C The application of short takeoff and landing aircraft for improving short-haul air transportation is examined. The contracts with industry to study quiet turbofan short-field aircraft in the short-haul air transportation system are identified. Studies of appropriate propulsion systems are conducted in parallel with the aircraft studies. The objectives of the studies are to: ID determine economic and social viability of short-haul air transportation, (2) identify critical technology and technology- related problems, (3) define representative aircraft configurations and characteristics to include development and operational costs, and (4) to establish desirable technology advances for improving short-haul transportation systems. Author N73-32937* National Aeronautics and Space Administration. Ames Research Center. Moffett Field, Calif. ECONOMIC AND ENVIRONMENTAL ASPECTS OF STOL TRANSPORTATION Elwood C. Stewart In its STOL Technol. 1972 p 23-34 CSCL 05C A system study to analyze the question of the impact of advanced STOL aircraft in meeting the needs of short-haul air transportation systems is discussed. The study is concerned with the following aspects: (1) service to the passenger. (2) economic viability, and (3) economic criteria to include community noise, ground and air decongestion, and air pollution. The STOL aircraft parameters are defined. Preliminary conclusions concerning the feasibility of short-haul air transportation are presented. Author N73-32938* National Aeronautics and Space Administration Ames Research Center. Moffett Field. Calif. OVERVIEW OF TECHNOLOGY SESSIONS Bradford H Wick In its STOL Technol. 1972 p 35-42 CSCL QIC Short takeoff aircraft technology development related to the requirements for an expanded and improved short-haul air transportation system is discussed. Systems requirements are summarized, principal aircraft requirements are identified, the status of STOL technology is analyzed, and the scope of the technology efforts covered by the conference are outlined. Charts and diagrams are provided to explain system requirements, lift capability trends, and terminal airspace requirements Author N73-32939* National Aeronautics and Space Administration. Langley Research Center. Langley Station. Va. AERODYNAMIC AND PERFORMANCE CHARACTERISTICS OF EXTERNALLY BLOWN FLAP CONFIGURATIONS c01 William G. Johnson. Jr. In its STOL Technol. 1972 p 43-54 CSCL 01A The application of externally blown flaps for improving the performance of short takeoff aircraft is discussed. The characteris- tics of externally blown flap powered lift are examined. A method for predicting the aerodynamic performance of a part icular externally blown flap configuration is presented. The following specific effects are analyzed: |1| induced aerodynamics. (2) static turning. (3) flap span and deflection, and (4| engine size and chord flap. Author N73-32940* National Aeronautics and Space Administration Langley Research Center, Langley Station, Va. STABILITY AND CONTROL OF EXTERNALLY BLOWN FLAP CONFIGURATIONS Lysle P. Parlett In its STOL Technol. 1972 p 55-70 refs CSCL 01A The results of wind-tunnel investigations on the stability and control characteristics of externally blown jet-flap configurations are presented. Conventional wind-tunnel tests and free-flight model tests have shown that longitudinal trim and stability can be achieved by a properly located horizontal tail of sufficient size, and that lateral trim in the engine-out condition can be produced by combinations of differential flap, spoiler, and rudder deflection. Free-flight model tests have revealed a lightly damped Dutch roll lateral oscillation, and have shown that the oscillation can be stabilized by use of artificial damping. Author N73-32941* National Aeronautics and Space Administration. Ames Research Center. Moffett Field, Calif. AERODYNAMIC C H A R A C T E R I S T I C S OF A SWEPT AUGMENTOR WING David G. Koenig and Michael D. Falarski (Army Air Mobility R and D Lab.) In its STOL Technol. 1972 p 71-86 refs CSCL 01A A brief outline of augmentor wing research sponsored by Ames Research Center is presented and is followed by a discussion of large-scale wind-tunnel test results for a swept augmentor wing configuration. The results showed that the augmentor wing could be applied to high-speed swept wing designs with little adverse effect on either the basic performance of the augmentor or the longitudinal characteristics, including maximum lift and stall. Three lateral control devices were shown to be effective and ground effect was measured for several complete aircraft configurations. Author 662 N73-32948 N73-32942* National Aeronautics and Space Administration. Ames Research Center. Moffett Field. Calif. ADVANCED AUGMENTOR WING RESEARCH Thomas N. AiKen In its STOL Technol. 1972 p 87-96 refs CSCL 01A Results of research on advanced augmentors are discussed. Research concerned with performance has indicated that: (1) augmentors with lobe-type nozzles give higher thrust augmentation than those with slot-type primary nozzles. (2) the thrust of augmentor wings at forward speed is greater than that of internally blown flaps for the speed range of interest, and (3) the optimum augmentor geometry at forward speed may be different from the optimum static geometry. Analysis of augmentor-wing data has shown that the data may be correlated by accounting for the augmentation and entrainment in defining a net thrust coefficient Author N73-32943* Army Air Mobility Research and Development Lab.. Hampton. Va. AERODYNAMICS OF THE UPPER SURFACE BLOW FLAP Arthur E. Phelps. Ill In NASA Technol. 1972 p 97-110 refs Langley Res. Center STUL CSCL01A The results of some preliminary wind-tunnel investigations made to provide fundamental aerodynamic information on the upper surface blown jet-flap cpricept incorporating high-bypass- ratio turbofan engines are summarized. The results of the investigation have shown the concept to have aerodynamic performance generally similar to that of other externally blown high-lift systems. A few of the more critical problems associated with this concept have been identified and preliminary solutions- to some of these problems have been found. These results have proven to be Sufficiently encouraging to warrant continuation of fundamental research efforts on the concept. Author N73-32944* Army Air Mobility Research and Development Lab.. Hampton. Va. COMPARISON OF AERODYNAMIC PERFORMANCE OF SEVERAL STOL CONCEPTS Danny R Hoad In NASA. Langley Res. Center STOL Technol. 1972 p 111-120 CSCL 01 C. Wind tunnel tests to determine the aerodynamic characteris- tics of basically similar short takeoff aircraft were conducted. The investigations were designed to provide data for a systematic direct comparison of five of the concepts considered. The configurations of the five models are illustrated and described. The aerodynamic data are presented in the form of graphs. It was concluded that the most complex systems require the least amount of net thrust. Author of the flap system on this model. Since this was a boilerplate model, the only conclusion that can be drawn is that the possibility of large vibration loads must be considered for a flight-weight structure. The similarity of the unsteady pressure and flap response spectra for the wind-off and wind-on cases indicated that it may be possible to realistically test flight-weight flap structures on a static test stand rather than endure the extra costs and scheduling problems associated with large-scale wind-tunnel tests. There is a potential flap-temperature problem which if not resolved might preclude the use of materials such as aluminum and the composites in the flap structure. Author N73-32946* National Aeronautics and Space Administration. Langley Research Center. Langley Station. Va. EXTERNALLY BLOWN FLAP DYNAMIC LOADS Donald L Lansing. John S. Mixson. Thomas J. Brown (Army Air Mobility R and D Lab.. Hampton. Va.). and Joseph A. Drischler In its STOL Technol. 1973 p 131-142 CSCL 01A Some of the principal results obtained in three series of measurements of fluctuating surface pressures induced on externally blown flaps by jet impingment are presented. Large- and small-scale models and hot- and cold-flow tests are considered. The discussion sets forth scaling parameters and consistent features of the root-mean-square values and spectra of the loading. Implications of these results with regard to sonic fatigue are indicated. Author N73-32947* National Aeronautics and Space Administration. Flight Research Center. Edwards. Calif. SURVEY OF WING AND FLAP LOWER-SURFACE TEMPER- ATURES AND PRESSURES DURING FULL-SCALE GROUND TESTS OF AN EXTERNALLY BLOWN FLAP SYSTEM Donald L. Hughes In its STOL Technol. 1972 p 143-156 refs CSCL 01A Full-scale ground tests of an externally blown flap system were made using the wing of an F-111B airplane and a CF700 engine. Pressure and temperature distributions were determined on the undersurface of the wing. vane, and flap for two engine exhaust nozzles (conical and daisy) at several engine power and engine/wing positions. The tests were made with no airflow over the wing. The leading-edge wing sweep angle was fixed at 26 deg. the angle of incidence between the engine and the wing was fixed at 3 deg. and the tests were conducted with the flap retracted, extended and deflected 35 deg. and extended and deflected 60 deg. The integrated local pressures on the undersurface of the flap produced loads approximately three times as great at the 60 deg flap position as at the 35 deg flap position. With both nozzle configurations, more than 90 percent of the integrated pressure loads were contained within plus or minus 20 percent of the flap span centered around the engine exhaust centerline. The maximum temperature recorded on the flaps was 218 C (424 F) for the conical nozzle and 180 C (356 F) for the daisy nozzle. Author N73-32945* National Aeronautics and Space Administration. Langley Research Center. Langley Station. Va. AERODYNAMIC LOADS MEASUREMENTS ON EXTER- NALLY BLOWN FLAP STOL MODELS George C. Greene and Boyd Perry. Ill In its STOL Technol. 1972 p 121-130 CSCL 01A Small-scale-model data have shown large static loads on the flap system behind the engines. The large-scale-model tests confirmed the magnitude of these loads and indicated that the relative loading of each flap element depends on the engine-wing- flap geometry. Flap response measurements indicated that the unsteady pressure loading excited the natural vibration modes N73-32948* National Aeronautics and Space Administration. Langley Research Center. Langley Station. Va. SIMULATOR EVALUATION OF THE FLYING QUALITIES OF EXTERNALLY BLOWN FLAP AND AUGMENTOR WING TRANSPORT CONFIGURATIONS David A. Kier, Bruce G. Powers. William D. Grantham. and Luat T. Nguyen In its STOL Technol. 1972 p 157-800 refs CSCL 01A1 Concurrent simulations of powered-lift STOL transport aircraft having either an externally blown flap_configuration or an 663 N73-32949 augmentor wing configuration were conducted. The following types of simulators of varying sophistication were used: (1) a simple fixed-base simulation with a simple visual display. (2) a more complex fixed-base simulation using a realistic transport cockpit and a high-quality visual display, and (3) a six-degree-of- freedom motion simulator that had a realistic transport cockpit and a sophisticated visual display. The unaugmented flying qualities determined from these simulations were rated as unacceptable for both the externally blown flap and augmentor wing configurations. The longitudinal, lateral-directional, and single-engine-failure characteristics were rated satisfactory with extensive augmentation, including pitch and roll command systems, flight-path (or speed) augmentation, turn coordination, and effective yaw damping. However, the flare and landing characteristics from any approach glide-path angle in excess of 4 deg were rated as unsatisfactory but acceptable. Author N73-32949* National Aeronautics and Space Administration. Ames Research Center. Moffett Field, Calif. FLIGHT-PATH AND AIRSPEED CONTROL FOR THE STOL APPROACH AND LANDING James A. Franklin and Robert C. Innis In its STOL Technol. 1972 p 181-198 refs CSCL 01C Analytical investigations and piloted moving base simulator evaluations were conducted for manual control of flight path and airspeed for the approach and landing of a powered lift jet STOL aircraft. Flight-path and airspeed response characteristics were described analytically and were evaluated for the simulation experiments which were carried out on a large motion simulator. The response characteristics were selected and evaluated for a specified path and speed control technique. These characteristics were the initial flight-path response, flight-path overshoot, flight-path-airspeed coupling in response to a change in thrust, and the sensitivity of airspeed to pitch-attitude changes. Results are presented in the form of pilot opinion ratings and commentary, substantiated where appropriate by response time histories and aircraft states at the point of touchdown. Author N73-32950* National Aeronautics and Space Administration. Langley Research Center, Langley Station, Va. STUDY OF GROUND PROXIMITY EFFECTS ON POWERED LIFT STOL LANDING PERFORMANCE James L Hassell, Jr. and Joseph H. Judd In its STOL Technol. 1972 p 199-213 refs CSCL 01C Data from wind-tunnel measurements are presented to show the magnitude of adverse ground effects on the longitudinal aerodynamic coefficients of a powered-lift STOL airplane. A steady-state analysis shows the changes in thrust and angle of attack required during the landing approach and flare as the airplane flies close to the ground. The piloting problems that these ground effects may create were investigated with an in-flight simulator to find the consequences of lift loss during the landing-flare maneuver for a STOL transport. Flight tests were made using the variable stability Navion setup with STOL transport aerodynamics and control responses and were flown at design approach speeds and descent conditions. Author N73-32951* National Aeronautics and Space Administration. Langley Research Center. Langley Station. Va. STATUS OF STOL RIDE QUALITY AND-CONTROL D. William Conner and W. Elliott Schoonover. Jr. In its STOL Technol. 1972 p 215-226 refs CSCL 01C A STOL ride-control development program has been initiated with the objective of generating ride-control technology through development and evaluation of an active control system specifically designed to provide ride smoothing on a STOL vehicle. Although much can be learned through analysis, there are deficiencies in technology for translating analysis results into operating hardware. The general approach being followed is to select an existing STOL vehicle for trial and then carry out a study to establish feasibility of a control system or systems to smooth the ride and generate system trade-off data. Author N73-32952* National Aeronautics and Space Administration. Ames Research Center. Moffett Field. Calif. HEAD-UP DISPLAYS FOR STOL VISUAL APPROACHES Everett A. Palmer and Fred W. Cronn (San Jose State Univ.) In its STOL Technol. 1972 p 227-243 refs CSCL 010 A simulation study was conducted to determine the effective- ness of a simple head-up display in improving glide-slope tracking performance during steep visual approaches in a STOL aircraft. The head-up display featured an attitude-stabilized horizon bar and glide-slope reference bar parallel to and 7.5 deg below the horizon bar. On some approaches a flight-path marker symbol showing the projected ground impact point was also displayed. Half of the approaches were flown in a conventional mode in which the pilot changed pitch attitude to correct for height errors. The remaining approaches were flown in a direct-lift mode in which the pilot modulated thrust to change the flight-path angle without pitching the aircraft. Author N73-32953* National Aeronautics and Space Administration. Flight Research Center. Edwards, Calif. A FLIGHT EVALUATION OF CURVED LANDING AP- PROACHES S. W. Gee. M. R. Barber, and T. C. McMurtry In its STOL Technol. 1972 p 245-258 refs CSCL 01C The development of STOL technology for application to operational short-haul aircraft is accompanied by the requirement for solving problems in many areas. One of the most obvious problems is STOL aircraft operations in the terminal area. The increased number of terminal operations needed for an economi- cally viable STOL system as compared with the current CTOL system and the incompatibility of STOL and CTOL aircraft speeds are positive indicators of an imminent problem. The high cost of aircraft operations, noise pollution, and poor short-haul service are areas that need improvement. A potential solution to some of the operational problems lies in the capability of making curved landing approaches under both visual and instrument flight conditions. Author N73-32954* National Aeronautics and Space Administration. Ames Research Center, Moffett Field. Calif. PRELIMINARY RESULTS OF FLIGHT TESTS OF THE AUGMENTOR WING JET STOL RESEARCH AIRCRAFT Hervey C. Quigley and Richard F. Vomaske In its STOL Technol. 1972 p 259-282 refs CSCL 01C The Augmentor-Wing Jet STOL Research Aircraft has been developed and has started flight tests. The objectives of the program are to compare aerodynamic characteristics predicted from wind-tunnel data with data obtained in flight, to determine flight dynamic characteristics and limitations of the augmentor- 664 N73-32961 wing concepts, and to contribute to the development of STOL design and operational criteria. Initial flight test results have shown that the aerodynamic characteristics are close to values predicted from wind-tunnel tests. The lateral-directional stability and control characteristics are satisfactory for research STOL missions with stability augmentation, but the longitudinal control require improvement. STOL take-off distance over 11 m is about 290 m. and landing approach speeds are between 60 and 65 knots. The investigation of the STOL operational and performance characteristics is continuing. Author paths from a minimum set of input data and flies the aircraft along the paths according to a prespecified time schedule. The two major elements of a 4-0 guidance system are the trajectory synthesizer and the control law. Inputs to the trajectory synthesizer are the three-dimensional coordinates of way points, the turning radii, the speed ranges, the acceleration limits, and the arrival times at time control way points. First, the three-dimensional trajectory is computed by using circular arcs and straight lines. Then the airspeed profile, compensated for wind, is calculated to achieve the desired arrival times. The synthesized trajectory is stored as a time sequence of reference states which the aircraft is forced to track by using a linear feedback law. Author N73-32955* National Aeronautics and Space Administration. Ames Research Center. Moffett Field. Calif. COMPARISONS OF SIMULATOR AND FLIGHT RESULTS ON AUGMENTOR-WING JET STOL RESEARCH AIR- CRAFT Robert C. Innis and Seth B. Anderson In its Stol Technol. 1972 p 283-290 CSCL 01C The considerations involved in making a piloted simulator an effective research tool in the design and development of new aircraft are discussed. An assessment of the limitations of the simulator in depicting real flight as well as the problem of recognizing erroneous results when the simulator is supplied with incorrect input data is made. Examples of the ways in which the simulator is used to design and develop the augmentor-wing aircraft are presented. Four areas of investigation are: (1) to design the lateral control system for proper feel and response. (2) determine the effect of engine failure during approach. (3) develop the best technique for controlling flight path during approach, and (4) the significance of lift loss in ground effect and how to compensate for such loss. Author N73-32958* National Aeronautics and Space Administration. Ames Research Center. Moffett Field. Calif. TERMINAL-AREA STOL OPERATING SYSTEMS EXPERI- MENTS PROGRAM Donald W. Smith. DeLamar Watson, and Jay V. Christensen In its STOL Technol. 1972 p 333-343 ref CSCL 01 E A system study to determine the application of short takeoff aircraft for a high speed, short haul air transportation service was conducted. The study focused on developing information which will aid in choosing system concepts, design criteria, operating procedures, landing guidance systems, air traffic control systems, and airborne avionics and flight control systems. A terminal area STOL operating system experiments program was developed. The objectives, program approach, program schedule, typical experiments, research facilities to be used, and program status are discussed. Author N73-32956* National Aeronautics and Space Administration. Langley Research Center. Langley Station. Va. INTEGRATION OF STOL AIRPLANES INTO THE ATC SYSTEM Paul Peterson. Richard H. Sawyer, and Milton D. McLaughlin In its STOL Technol. 1972 p 291-306 Prepared in cooperation with FAA. Washington, D. C. CSCL 17G The study involving the STOL airplane and air traffic control is a joint NASA/FAA effort designed to examine the effects of introducing large numbers of STOL airplanes into a high-density terminal area. Simply stated, the objectives of the study are to determine the effects of the STOL airplane on the air traffic control (ATC) system and to determine the effects of the ATC system on the STOL airplane. More specifically, the study seeks to determine the airspace requirements and air traffic control equipment and handling techniques required to accommodate the STOL airplane in the ATC system and the design characteris- tics, avionics equipment, and flight procedures required to operate the STOL airplane in the air traffic control system. Author N73-32957* National Aeronautics and Space Administration. Ames Research Center, Moffett Field. Calif. FOUR-O GUIDANCE OF STOL AIRCRAFT IN THE TER- MINAL AREA Thomas Pecsvaradi and Heinz Erzberger In its STOL Technol. 1972 p 307-332 refs CSCL 17G The primary objective of advanced STOL aircraft is the improvement of the nation's air transportation system by the elimination of delays and congestions associated with today's air travel. A new guidance technique, referred to as 4-D guidance, is being developed to achieve this objective. The 4-D guidance technique synthesizes complex three-dimensional flight N73-32959* National Aeronautics and Space Administration. Ames Research Center, Moffett Field, Calif. PROGRAM PLAN TO DEVELOP AIRWORTHINESS STAND- ARDS FOR STOL AIRCRAFT Jack E. Cayot (FAA), Robert A. Chubboy (FAA), and Charles S. Hynes In its STOL Technol. 1972 p 345-351 refs CSCL01C A program plan to develop criteria for airworthiness standards for STOL transport aircraft is presented. Initially, three different STOL concepts are to be examined with a goal to arrive at a generalized set of standards. The Breguet 941 deflected-slipstream STOL has been initially evaluated on a piloted motion simulator and in flight. Confidence in establishing criteria for airworthiness standards for STOL transport aircraft has been obtained from these studies. Author N73-32961* National Aeronautics and Space Administration. Lewis Research Center. Cleveland. Ohio. QUIET STOL PROPULSION SESSION INTRODUCTORY REMARKS c28 Robert W. Schroeder In its STOL Technol. 1972 p 367-370 CSCL 20A Research activities, preliminary design activities, and system optimization studies in support of the development of advanced, quiet. STOL propulsion systems are discussed. Noise alleviation by means of controlling the source and by means of acoustical treatment receive considerable emphasis. A STOL airplane designed for a given payload has essentially double the installed thrust of a comparable CTOL airplane. Unless compensated for during the design process, this alone will tend to increase the source noise by 3 db. The propulsive lift introduces flap impingement noise or duct and flap scrubbing noise, noise sources not present in CTOL airplanes to any significant degree. These 665 N73-32962 additional noise sources are illustrated. Depending on the specific configuration, this will tend to increase the noise by several db or more. Although the propulsive lift characteristics of STOL airplanes will tend to increase source noise significantly, the proximity of STOL airfields to populated areas leads to STOL noise objectives considerably lower than those currently applicable to CTOL airplanes. " Author N73-32962* National Aeronautics and Space Administration. Lewis Research Center. Cleveland. Ohio. ENGINE NOISE TECHNOLOGY Roger W. Luidens. Donald R. Dietrich. James H. Dittmar. Richard G. Goldman. William A. Olsen. Jr.. and Brent A. Miller In its STOL Technol. 1972 p 371-412 refs CSCL21A The characteristics of aircraft engine noise are discussed. Data are provided to show the noise produced by the following aircraft components: (1) fan noise. (2) noise suppressing structures. (3) sonic inlets. (4) jet mixing noise due to nozzle flow, and (5) thrust reversers. Charts are developed to show the sound pressure level and the frequencies for each type of noise source. The. use of laminates and composite materials to dissipate acoustic power is examined. . Author N73-32963* National Aeronautics and Space Administration. Langley Research Center. Langley Station. Va. FLAP NOISE GENERATION AND CONTROL David Chestnut!. Domenic J. Maglieri. and Richard E. Hayden (Bolt. Beranek and Newman. Inc.) In its STOL Technol. 1972 p 413-426 refs CSCL 01A The characteristics of aerodynamic noise generated by the interaction of an airstream with a flap surface are discussed. The location and behavior of various noise sources were investigated to determine optimal quieting techniques. A schematic diagram of the jet-flap concepts being considered for integrated- powered-lift systems for short takeoff aircraft is shown. Each of the concepts has in common high velocity turbulent air flowing over relatively rigid surfaces with resultant production of interaction noise. The nature, location, and control of noise sources which involve the interactions of air flows with airfoil surfaces are examined. . Author N73-32964* National Aeronautics and Space Administration. Flight Research Center. Edwards. Calif. EXTERNALLY BLOWN FLAP IMPINGEMENT NOISE Paul L Lasagna and Terrill W. Putnam In its STOL Technol. 1972 p 427-441 refs CSCL 20A Tests of the noise produced by the impingement of the jet exhaust on the wing and flap for an externally blown flap system were conducted with a CF700 turbofan engine and an F-111B wing panel. The noise produced with a daisy nozzle installed on the engine was greater than that produced by a conical nozzle at the same thrust. The presence of the wing next to the test nozzles increased the noise, as did increasing the flap deflection angle.. Compared with the conical nozzle, the daisy nozzle produced slightly less noise at a flap deflection of 60 deg but produced more noise at the lower flap deflections tested. Tests showed that the single-slotted flap deflected 60 deg. produced less noise than the double-slotted flaps. Also, maintaining the maximum distance between the exit nozzle and flap system resulted in a. minor reduction in noise. Author MODELS AT FORWARD SPEED Michael D. Falarski (Army Air Mobility Res. and Develop. Lab.). Kiyoshi Aoyagi. and David G. Koenig In its STOL Technol. 1972 p 443-454 refs ' CSCL 20A Wind-tunnel investigations of the acoustic characteristics of the externally blown jet flap (EBF) and augmentor wing STOL concepts are discussed. The large-scale EBF model was equipped with a triple-slotted flap blown by four JT15D turbofan engines with circular, coannular exhaust nozzles. The large-scale augmen- tor wing model was equipped with an unlined augmentor'blown by a slot primary nozzle. The effects of airspeed and angle of attack on the acoustics of the EBF were small. Flap deflection had a greater effect on the acoustics of the augmentor wing than did airspeed. The total sound power was also significantly higher for landing indicating that turning in the augmentor generated acoustic energy. Airspeed produced a small aft shift in acoustic directivity with no significant change in the peak perceived noise levels or sound power levels. Small-scale research of the acoustics for the augmentor wing has shown that by blowing an acoustically treated augmentor with a lobed primary nozzle, the 95-PNdb noise level goal can be achieved or surpassed. Author N73-32966* National Aeronautics and Space Administration. Lewis Research Center. Cleveland. Ohio. EBF NOISE TESTS WITH ENGINE UNDER-THE-WING AND OVER-THE-WING CONFIGURATIONS Robert G. Dorsch and Meyer Reshotko In its STOL Technol 1972 p 455-473 * CSCL 20A Noise tests of externally blown flaps with the engine under the wing and engine over the wing configurations were conducted. Flap noise data obtained on a TF-34 aircraft are discussed. Noise data obtained during a free-jet forward-speed-effect analysis are presented. Noise sources associated with upper surface flap blowing are described. Results of a small scale configuration screening study and some large scale model test data are analyzed. The noise data for the engine over wing configurations are compared with the engine under the wing configurations.. Author N73-32967* National Aeronautics and Space Administration. Lewis Research Center. Cleveland. Ohio. STOL PROPULSION SYSTEMS Robert J. Denington. Robert W. Koenig. Michael R. Vanco. and David A. Sagerser In its STOL Technol. 1972 p 475-509 ref CSCL21A The selection and the characteristics of quiet, clean propul- sion systems for STOL aircraft are discussed. Engines are evaluated for augmentor wing and externally blown flap STOL aircraft with the engines located both under and over the wings. Some supporting test data are presented. Optimum engines are selected based on achieving the performance, economic, acoustic, and pollution goals presently being considered for future STOL aircraft. The data and results presented were obtained from a number of contracted studies and some supporting NASA inhouse programs, most of which began in early 1972. The contracts include: (1) two aircraft and mission studies. (2) two propulsion system studies. (3) the experimental and analytic work on the augmentor wing, and (4) the experimental programs on Q-Fan. Engines are selected and discussed based on aircraft economics using the direct operating cost as the primary criterion. This cost includes the cost of the crew. fuel, aircraft, and engine maintenance and depreciation. Author N73-32965* National Aeronautics and Space Administration. Ames Research Center. Moffett Field. Calif. ACOUSTIC CHARACTERISTICS OF LARGE-SCALE STOL N73-32968*# National Aeronautics and Space Administration. Lewis Research Center. Cleveland. Ohio. 666 N73-32974 FORWARD VELOCITY EFFECTS ON JET NOISE WITH DOMINANT INTERNAL NOISE SOURCE U. VonGlahn and J. Goodykoontz 1973 17 p refs Presented at 86th Meeting of Acoustical Soc. of Am.. Los Angeles. 30 Oct. - 2 Nov. 1973 (NASA-TM-X-71438; E-7694) Avail: NTIS HC $3.00 CSCL 20A Acoustic data, with and without forward velocity, were obtained with a circular nozzle using a quiet flow system and one dominated by a low frequency internal noise source (analogous to combustion noise). Forward velocity effects were obtained by installing the test nozzle in a free jet. Farfield noise data were obtained at jet pressure ratios from 1.3 to 1.7 and forward velocities op to 260 ft/sec. With a quiet flow system, jet noise is (educed .by forward velocity. With a dominant low frequency core noise source, the portion of the noise spectra dominated by this source was not appreciably affected by forward velocity. Author N73-32969*# National Aeronautics and Space Administration. Lewis Research Center, Cleveland, Ohio. FLAP NOISE PREDICTION METHOD FOR A POWERED LIFT SYSTEM B. Clark, R. Dorsch. and M. Reshotko 1973 15 p refs Presented at the Aero-Acoustic Specialists Conf.. Seattle. 15-17.Oct. 1973; sponsored by AIAA (NASA-TM-X-71449; E-7717) Avail: NTIS HC $3 00 CSCL 20A A method is presented for estimating the noise generated by deflection of the engine exhaust for under-the-wing and over-the-'wing versions of an externally blown flap configuration for powered lift. Correlation equations and curves are given for the overall sound pressure level and directivity and for spectra scaled to a high bypass 25.000-pound thrust size engine. Data are taken from TF34 engine tests and from large cold flow model tests. The correlations are empirical, and thus application of this prediction' procedure is limited to geometrically similar configurations. Application of the method is illustrated by calculated sample footprints. Author N73-32970*# National Aeronautics and Space Administration. Ames Research Center, Moffett Field. Calif. A FLIGHT STUDY OF THE USE OF DIRECT-LIFT-CONTROL FLAPS TO IMPROVE STATION KEEPING DURING IN- FLIGHT REFUELING Walter E. McNeill. Ronald M. Gerdes. Robert C. Innis. and Jack D. Ratcliff Washington Oct. 1973 30 p refs (NASA-TM-X-2936: A-4904) Avail: NTIS HC $3.00 CSCL 01C To investigate the effectiveness of fast-acting flaps as direct-lift-control (DLC) devices on a fighter airplane, the aileron servo systems of an F-100C variable-stability airplane were modified to provide symmetrical actuation of the surfaces. Initial flight tests using DLC indicated that the task of formation flying and, hence, in-flight refueling could be eased by actuating the DLC flaps through the conventional control stick, with the degree of improvement depending on the basic stability of the receiver aircraft. Results of refueling approaches and connections with U.S. Air Force tankers indicated a moderate overall improve- ment in vertical station-keeping performance (approximately 19 percent) and a sizeable overall decrease in receiver airplane motions and control activity (approximately 40 percent) with DLC. Author N73-32971# Boeing Commercial Airplane Co.. Seattle. Wash. THE 727 NOISE RETROFIT FEASIBILITY. VOLUME 3: UPPER GOAL FLIGHT TESTING AND PROGRAM SUM- MARY Final Report. Jul. 1971 - Dec. 1972 D. L. Hiatt and M. B. McKaig Jun. 1973 232 p refs (Contract DOT-FA71WA-2637) (FAA-RD-72-40-Vol-3; D6-60196-Vol-3) Avail: NTIS HC $13.75 Modifications performed on a Boeing 727 aircraft to obtain reduced aerodynamic noise are discussed. Level flyovers covering a wide range of thrusts and altitudes were recorded with a widely spaced microphone grid for the study of long range noise propagation. Acoustic, propulsion, and aerodynamic performance analyses were made, along with the physical effects of integrating the modifications on the aircraft. A direct operating cost analysis was prepared based on realistic retrofit installation cost estimates and aircraft performance analyses. Author N73-32972# Federal Aviation Administration. Washington. D.C. INTERRELATIONSHIP OF FAA-DOT NASA PROGRAMS RELATING TO AIRCRAFT CABIN MATERIALS FIRE Colin G. Simpson Sep. 1973 21 p refs (FAA-RD-73-146) Avail: NTIS HC $3.25 CSCL QIC Aircraft cabin materials fire hazards consisting of flammability. smoke emission, toxic gas emission and flash fire are discussed together with the work ongoing pertinent to these hazards by the FAA and other DOT administrations and the NASA. The relationships among these efforts are considered together with funding estimates for FY 1974. Author N73-32973*# National Aeronautics and Space Administration. Ames Research Center. Moffett Field. Calif. WIND TUNNEL INVESTIGATION OF A LARGE-SCALE UPPER SURFACE BLOWN-FLAP TRANSPORT MODEL HAVING TWO ENGINES Kiyoshi Aoyagi. Michael D. Falarski. and David G. Koenig Aug. 1973 69 p refs Prepared in cooperation with Army Air Mobility R and D Lab.. Moffett Field. Calif. (NASA-TM-X-62296) Avail: NTIS HC $5.50 CSCL QIC ' An investigation has been conducted to determine the aerodynamic characteristics of a large-scale subsonic jet transport model with an upper surface blowing flap system that would augment lift. The model had a 25 deg swept wing of aspect ratio 7.89 and two turbofan engines with the engine centerline located at 0.256 of the wing semispan. The lift of the flap system was augmented by turbofan exhaust impingement on the Coanda surface. Results were obtained for several flap deflections and engine nozzle configurations at jet momentum coefficients from 0 to 4.0. Three-component longitudinal data are presented with two engines operating. Limited longitudinal and lateral data are presented with an engine out. In addition, limited exhaust and flap pressure data are presented. Author N73-32974*# National Aeronautics and Space Administration. Ames Research Center. Moffett Field. Calif. WIND TUNNEL TESTS OF AN F-8 AIRPLANE MODEL EQUIPPED WITH AN OBLIQUE WING Lawrence A. Graham. Robert T. Jones, and James L. Summers Jun. 1973 72 'p refs (NASA-TM-X-62273) Avail. NTIS HC $5.75 CSCL QIC An experimental investigation was conducted in an 11- by 11-foot transonic wind tunnel to study the lift, drag and stability characteristics of a 0.087-scale model of an operational airplane fitted with an oblique wing. The model wing was of elliptical planform with an unswept aspect ratio of 12.7 and a thickness of 10 percent. All other external geometric features of the model were scaled to the basic full size operational airplane with the engine inlet faired closed. Longitudinal and lateral-directional stability data were obtained with the wing at sweep angles of 0 deg, 45 deg and 60 deg Test Mach numbers ranged from. 667 N73-32975 0.6 to 1.4 deg Angles of attack were between minus 4 deg and 8 deg at zero sideslip. Angles of sideslip were between plus and minus 4 degrees for two angles of attack depending upon the wing configuration. Tests were conducted at a Reynolds number of 6 million per foot except for a few runs when balance capacity limited the Reynolds number to 4 million per foot. Author N73-32975*# National Aeronautics and Space Administration. Ames Research Center. Moffett Field. Calif. NOISE MEASUREMENTS FROM A LARGE-SCALE LIFT FAN TRANSPORT IN THE 40- BY 80-FOOT WIND TUNNEL Adolph Atencio. Jr. (Army Air Mobility R and D Lab.) Mar. 1973 77 p refs (NASA-TM-X-62284) Avail: NTIS HC $6.00 CSCL01C Noise data measurements from a large scale lift fan transport model aircraft were made in the 40- by 80-foot wind tunnel. The model had two lift fans in deep inlets in the forward fuselage and two lift-cruise fans in pods on the aft fuselage. The noise data measurements are presented as listings and plots of sounds pressure level versus 1/3-octave center frequency. Author N73-32976*# National Aeronautics and Space Administration. Ames Research Center. Moffett Field. Calif. THEORETICAL STUDY OF LIFT GENERATED VORTEX SHEETS DESIGNED TO AVOID ROLL UP Vernon J. Rossow Sep. 1973 39 p refs (NASA-TM-X-62304) Avail: NTIS HC S4.00 CSCL 01A The random motions of the vortex elements behind a wing that sheds a disturbed,'translating array of vortices are analyzed. The analysis indicates -that the wake would diffuse and decay rapidly when viscosity is present and would produce small rolling moments on encountering aircraft. It was found that comparable results could also be achieved with an array consisting of vortices that are equal in magnitude but which alternate in sign. This observation indicates that random motion can probably be achieved with a variety of stepped loadings. Author N73-32977*# General Electric Co.. Cincinnati. Ohio. Aircraft Engine Group. A STUDY OF RAPID ENGINE RESPONSE SYSTEMS FOR AN ADVANCED HIGH SUBSONIC. LONG RANGE COM- MERCIAL AIRCRAFT J. H. Barber. G W. Bennett, and T. A. DeRosier Oct. 1973 43 p refs (Contract NAS3-15544) (NASA-CR-134496: R73AEG121) Avail: NTIS HC S4.25 CSCL 01C A dynamic model representing the characteristics of an advanced technology study engine (1985 certification time period) was constructed and programmed on an analogue/digital computer. This model was then exercised to study and evaluate a large number of techniques, singly and in combination, to improve engine response. Several effective methods to reduce engine accelerating time are identified. Author (DLR-MITT-72-05) Avail: NTIS HC S12.50: ZLDI. Munich 43,90 DM The application of artificial stabilizing devices to particular cases of instability in flight control is discussed. Based on a unified point of view, basically possible feedback control concepts were derived for aircraft with variable stability. The optimization of a control and damping system for fighter aircraft is described. The specification of a thrust control system for the Airbus A300B is presented. The role of an airborne computer in digital flight control systems is detailed. The DO-31 V/STOL aircraft's control system for vertical velocity regulation is described. The flight control system of the VAK 191 B VTOL fighter aircraft is presented. The design optimization of t.ne flight control systems for light helicopters is exemplified by the BO-105 helicopter. Some effects of artificial stability control are reviewed. N73-32979 Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt. Oberpfaffenhofen (West Germany). Inst. fuer Dynamik der Flugsysteme NONLINEAR C O N T R O L C O N C E P T S FOR VARIABLE STABILITY AIRCRAFT [NICHTLINEARE REGLERKONZEPTE FUER FLUGZEUGE VARIABLER STABILITAET] G. Gruebel (Bochum Univ.. West Ger.) In DGLR Flight Control Systems: Requirements and Design Probl. from the Flight Mech. Viewpoint Mar. 1972 p 7-16 In GERMAN Based on'a unified point of view, the basically possible feedback control concepts for aircraft with variable stability are derived and discussed. Treatment is limited to the general nonlinear case; the treatment of a linearized state for stationary flight results as a special case. It is shown that as the basis of the general nonlinear equations of motion of a reference aircraft and a model, the possible control structures can be simply derived, in which process the related control laws are determined by nonlinear equation systems. ESRO N73-32980 Bodenseewerk Geraetetechnik G.m.b.H.. Ueberlingen (West Germany). DESIGN OF A MODERN FIGHTER AIRCRAFT CONTROL SYSTEM USING QUADRATIC COST FUNCTIONS [AUSLEG- UNG EINES REGELSYSTEMS FUER MODERNE KAMPF FLUGZEUGE MIT HILFE QUADRATISCHER KOSTENFUNK- TIONEN] G. Schaenzer and R Stadler In DGLR Flight Control Systems: Requirements and Design Probl. from the Flight Mech. Viewpoint Mar. 1972 p 17-36 refs In GERMAN The optimization of a control and damping system for fighter aircraft is discussed. Essential specifications, such as gust and flight control behavior, and stability, can be described exactly by a single quadratic integral quality criterium (cost function). It is shown that the controller, optimized for minimal costs, gives an especially favorable performance related to flight control, disturbance, stability and parameter sensitivity. The investigation of parameter sensitivity produced indications for technical simplification of the control system structure. ESRO N73-32978 Deutsche Gesellschaft fuer Luft- und Raumfahrt. Cologne (West Germany). FLIGHT CONTROL SYSTEMS: REQUIREMENTS AND DESIGN PROBLEMS FROM THE FLIGHT MECHANICS VIEWPOINT [FORDERUNGEN AN FLUGREGELANLAGEN UND AUSLEGUNGSPROBLEME UNTER BESONDERER BERUECKSICHTIGUNG DER FLUGMECHANIK] Mar. 1972 209 p refs In GERMAN: ENGLISH summary Proc. of the DGLR Flight Characteristics and Flight Control Panels Meeting. Immenstaad. West Ger.. 28-29 Oct. 1971 N73-32981 Bodenseewerk Geraetetechnik G.m.b.H.. Ueberlingen (West Germany). DESIGN PROBLEMS OF THE AIRBUS A 300 B FORWARD THRUST REGULATOR [PROBLEME BEI DER AUSLEGUNG DES VORTRIEBSREGLERS FUER DEN AIRBUS A 300 B] P. Wuest and H. D. Buchholz In DGLR Flight Control Systems: Requirements and Design Probl. from the Flight Mech. Viewpoint Mar. 1972 p 37-70 refs In GERMAN The specification of a thrust control system for the Airbus A 300 B is discussed. This sub-system of the automatic pilot is a 668 N73-32987 further development of a similar system tested in a Lufthansa Boeing 707. The sub-system is to control the flight speed in relation to indicated air speed by operating the throttle. The following points are discussed, in the absence of disturbances, a specified flight speed should be reached: the system should be stable, when flying through gusts, throttle activity should not exceed a certain limit: in the case of wind shear the flight deviation should not exceed a certain limit: in the case of configuration changes, e.g. in lowering flaps or undercarriage, the flight deviation should not exceed a certain limit. ESRO N73-32982 Dornier-Werke G.m.b.H.. Friedrichshafen (West Germany). PROBLEMS OF AIRBORNE COMPUTER AIDED DIGITAL CONTROL SYSTEMS [BEITRAEGE ZUR PROBLEMATIK VON BORDRECHNERGESTUETZTEN DIGITALEN REGEL- UNGSSYSTEMEN] E. Kienzle and G. Schweizer In DGLR Flight Control Systems. Requirements and Design Probl. from the Flight Mech. Viewpoint Mar. 1973 p 71-95 In GERMAN The role of an airborne computer in digital flight control systems is discussed. The following problems in the design of such a system are detailed: (1) models of the processes to obtain adaptive properties in each separate phase, and desired flight characteristics by adaptive behavior in all flight phases: (2) integrated information presentation for observation of control and surveillance problems by the human operator: (3) integration of the operator in the total system; and (4) integration of the onboard computer in the total system. ESRO N73-32983 Dornier-Werke G.m.b.H., Friedrichshafen (West Germany). PROBLEMS OF AN INTEGRATED FLIGHT CONTROL AND REGULATION SYSTEM FOR LIFT FAN/VSTOL AIRCRAFT TAKING THE DO-31 VERTICAL VELOCITY REGULATOR AS AN EXAMPLE [ERLAEUTERUNG DER PROBLEME EINER INTEGRIERTEN FLUGSTEUERUNGS- UND REGELUNG SANLAGE FUER HUBBLAESER-VSTOL FLUGZEUGE AM BEISPIEL DES DO 31-VERTIKALGESCHWINDIGKEITSR EGLEHS] K. Daser In DGLR Flight Control Systems: Requirements and Design Probl. from the Flight Mech. Viewpoint Mar. 1972 p 97-110 In GERMAN The DO-31 V-STOL aircraft's integrated flight control system for vertical velocity regulation is discussed for the gliding and transition phase, as these phases have the highest requirements with regard to performance and reliability. It was found that in augmenting the demands on the flight control system of a VTOL aircraft, the signal processing effort increases. As long as the maximal hand forces of the pilot determine the force level to be processed, a mechanical signal processing will be the main contribution in weight to the control system. A remedy would be mechanical signal processing at low force level, something similar to servo control, or electro-hydraulic control with electric signal processing. ESRO Mar. 1972 p 111-144 refs In GERMAN The flight control system of the VAK 191 B VTOL fighter aircraft for gliding and transition flight phases, based on nonlinear feedback, is discussed. The main problems in flight control are unclearly defined requirements of the relation between aircraft and control systems, the mostly nonlinear parameter variations of the control circuit with the application conditions, and the desired high reliability of the system. The VAK 191 B is used as an example to show possible solutions to these problems. A parameter insensitive controller for a supersonic aircraft, as well as a parameter sensitive controller, are described. The problems of redundant systems and the related error disparity are touched upon. For all solutions, applicability to existing specifications is discussed. ESRO N73-32985 Messerschmitt-Boelkow-Blohm G.m.b.H . Ottobrunn (West Germany). DESIGN OPTIMIZATION AND TESTING OF FLIGHT CONTROL SYSTEMS FOR LIGHT HELICOPTERS [OPTI- MALE AUSLEGUNG UND ERPROBUNG VON FLUGREGE- LUNGSSYSTEMEN FUER LEICHTE HUBSCHRAUBER] Herbert Koenig In DGLR Flight Control Systems: Requirements and Design Probl. from the Flight Mech. Viewpoint Mar. 1972 p 145-170 refs In GERMAN '" Based on the flight dynamic properties of the BO 1-5 helicopter with hingeless rotor, characterized by very good controllability, the influence over several controller concepts was investigated. Flight control systems consisting of a fast controller (with authority limitation of the regulating distance) as attitude stabilizers, and a slow controller as automatic trimmers (with limitation of the regulating speed), were found to be the optimal controller concepts for this type of helicopter. A further optimal concept results from addition of an altitude control, which includes the trimmer system. The investigations and tests have shown that, with relatively little effort, pilot activity can be considerably simplified. ESRO N73-32986 Messerschmitt-Boelkow-Blohm G.m.b.H.. Ottobrunn (West Germany). EFFECT OF ARTIFICIAL STABILITY ON A I R C R A F T PERFORMANCES [EINFLUSS DER KUENSTLICHEN STABILITAET AUF DIE FLUGLEISTUNGEN] D. Reich In DGLR Flight Control Systems: Requirements and Design Probl. from the Flight Mech. Viewpoint Mar. 1972 p 171-186 In GERMAN Based on the control configured vehicle (CCV) concept, i.e. taking account of the flight control during the design phase, the effect of an artificial longitudinal stability on the performance of aircraft was investigated. In consequent application of the CCV concept, in the most favorable cases a decrease of about 15% in takeoff weight (for the same radius of action) or an increase of 11% in radius of action (for the same takeoff weight) can be achieved. For a fighter aircraft, it is shown that the advantages of an artificial longitudinal stability are obtained for high lift coefficients and for plane wing-body drag polars. ESRO N73-32984 Vereinigte Flugtechnische Werke-Fokker G.m.b.H.. Bremen (West Germany). THE VAK 191 B FLIGHT CONTROL SYSTEM AND RESULT- ING NEW DEVELOPMENTS FOR THE NEXT V/STOL FIGHTER AIRCRAFT GENERATION [DAS REGELUNQS- SYSTEM DER VAK 191 B UND DARAUS RESULTIERENDE NEUERE ENTWICKLUNGEN FUER DIE NAECHSTE GENER- ATION VON V/STOL-KAMPFFLUGZEUGEN] H.-H. VonSalzen and W. Sobotta In DGLR Flight Control Systems: Requirements and Design Probl. from the Flight Mech. Viewpoint N73-32987 Messerschmitt-Boelkow-Blohm G.m.b.H.. Ottobrunn (West Germany). FLIGHT MECHANICAL AND CONTROL TECHNICAL CONSIDERATIONS OF ARTIFICIAL STABILITY AIRCRAFT [FLUGMECHANISCHE UND REGELUNGSTECHNISCHE GESICHTSPUNKTE FUER FLUGZEUGE KUENSTLICHER STABILITAET] G. K Kissel In DGLR Flight Control Systems: Requirements 669 N73-32988 and design Probl. from the Flight Mech. Viewpoint Mar. 1972 P 187-196 In GERMAN The effects of artificial aircraft stability control on the damping behavior, and the recovery of static stability by means of controllers, are discussed. In designing aircraft the rule that static stability should be available to obtain airworthiness is of major- importance. If this rule is not maintained, a reduction of the induced trimming resistance and an increased maneuverability performance can be gained. Airworthiness should then be regained artificially using flight controllers. The improvements obtained in damping behavior are descirbed, and the possibilities of regaining static stability are surveyed. ESRO N73-32988 Bodenseewerk Geraetetechnik G.m.b.H.. Ueberlingen (West Germany). ' • : BASIC TECHNICAL DESIGN OF THE CONTROL SYSTEM FOR AN ARTIFICIAL STABILITY AIRCRAFT (GRUNDSAET ZLICHER TECHMSCHER ENTWURF DES STEUERUNGS- SYSTEMS FUER EIN FLUGZEUG MIT KUENSTLICHER STABILITAET] L Goumas In DGLR Flight Control Systems. Requirements and Design Probl. from the Flight Mech. Viewpoint Mar. 1972 p 197-209 In GERMAN . The fundamental design of a pitching axis control system for aircraft with artificial stability is discussed. This control system is based on the measurement of the angular deviation with an air current directional sensor. In order to. prevent.sensor failures and for consolidation of signals with disparities, the outputs of the air current directional sensor are blocked with supervisory circuits. The produced feedback signal was compared with the control branch signal, and the difference signal passed on to the pitch controller. A hydraulic actuator on the horizontal tail surface closes the feedback circuit. ESRO N73-32989# Deutsche Gesellschaft fuer Luft- und Raumfahrt. Cologne (West Germany). [AIRSHIPS: PAST. PRESENT. AND FUTURE] [BERICHT UEBER DAS LUFTSCHIFF-KOLLOQUIUM DER.DGLR] Aug. 1972 172 p refs In GERMAN; ENGLISH summary Proc. of the DGLR Airship Colloq., Stuttgart, 6 Apr. 1972 • (DLR-MITT-72-17) Avail: NTIS HC $10.75: ZLDI, Munich 36.15 DM . The technical and economic aspects of using airships for air transportation are discussed. The history of Zeppelin airships is presented. The cost effectiveness of airship passenger and freight transportation is analyzed. Details of the manufacture of flexible airships are presented and ground and loading operations surveyed. The aerodynamic drag and lift of airships is determined; and drag reduction possibilities discussed. The technical conditions for further airship development, based on present technology, are summarized. Graf Zeppelin in Friedrichshafen on 8 May 1937. as a result of which hydrogen gas filling was replaced by nonflammable helium. ESRO N73-32991 Deutsche Studiengemeinschaft fuer Luftschiffahrt. Frankfurt am Main (West Germany). POSSIBILITIES OF AND PROSPECTS FOR PASSENGER AND FREIGHT TRANSPORT BY AIRSHIPS [MOEGLICH- KEITEN UND AUSSICHTEN EINES P E R S O N E N - UND GUETERTRAN SPORTS MIT LUFTSCHIFFEN] Eckart Krueger In DGLB Airships: Past. Present, and Future Aug. 1972 p 27-39 In GERMAN The possibilities and perspectives of using airships for air transportation of passengers and cargo are discussed. Three conditions for successful realization of this concept are: (1) technical realization should be possible. (2) the level of costs involved in construction, manufacturing, and management should allow a selling price leading to a corresponding sales success, and (3) the new product should fit in to the broad spectrum of present offers, and have certain advantages. An important aspect is environment pollution, to which these airships will contribute little. Long-distance flights are seen as the best .use because of the airship's hotel-like character. . ESRO N73-32992 Wuellenkemper (Theodor) KG. Mulheim/Ruhr (West Germany). AIRSHIP MANUFACTURE IN MUELHEIM/RUHR [LUFT- SCHIFFBAU IN MUELHEIM/RUHR] Theodor Wuellenkemper In DGLR Airships. Past. Present, and Future Aug. 1972 p 41-48 In GERMAN Details concerning the manufacture of flexible airships 60 m in length and with a helium gas filling of 6000 cubic m are presented. These airships are to be used for transport of goods, especially in countries with bad roads. The payloads are between 2 and 2.5 tons. ESRO N73-32993 Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt, Oberpfaffenhofen (West Germany). Zentralabteilung Luftfahrttechnik. TECHNICAL ASPECTS OF AIRSHIP MANUFACTURE AND OPERATIONS [EINIGE TECHNISCHE FRAGEN ZUM LUFTSCHIFFBAU UND -BETRIEB] E. Urbatzka In DGLR Airships: Past, Present, and Future Aug. 1972 p 49-66 refs In GERMAN borne technical aspects of airship manufacture and ground and loading operations are dealt with. Details of possible carrier gases, and altitude control methods are reviewed. Ground handling and freighting operations are discussed. ESRO N73-32990 Deutsche Gesellschaft fuer Luft- und Raumfahrt, Cologne (West Germany). THE ZEPPELIN AIRSHIP, INITIATOR OF WORLD AIR TRAFFIC [ZEPPELIN. WEGBEREITER DES WELTLUFTVER- KEHRS] Hans VonSchiller In its Airships, Past, Present, and Future Aug. 1972 p 11-25 In GERMAN The history of Zeppelin airships is presented. The first Zeppelin dirigible flew for 18 minutes on July 1, 1900. The airship was used for civil and military aviation, the latter particularly during World War I. After World War I. the Zeppelin was introduced in the United States, and an Atlantic Ocean crossing was made in 1929. Civil flights to South America were interrupted after the catastrophe of the Hindenburg during the landing of the N73-32994 Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt. Porz (West Germany). Inst. fuer Angewandte Gasdynamik. PROBLEMS OF AIRSHIP AERODYNAMICS [PROBLEME DER LUFTSCHIFF-AERODYNAMIK] D. G. Papanikas In DGLR Airships: Past, Present, and Future Aug. 1972 p 67-113 refs In GERMAN; ENGLISH summary The possibilities of determining aerodynamic drag and lift on airships by means of known methods for aircraft aerodynamics were investigated. The effectiveness of boundary layer control by means of suction, and some propulsion problems are considered. On the basis of information gathered from an airship literature survey, speed and propulsion power ranges are discussed and compared with those of transport aircraft. ESRO 670 N73-33170 N73-32995 Deutsche Gesellschaft fuer Luft- und Raumfahrt. Cologne (West Germany). TECHNICAL CONDITIONS FOR A RESTART IN AIRSHIP TECHNOLOGY [TECHNISCHE VORAUSSETZUNGEN FUER EINEN NEUEN START IN DER LUFTSCHIFFTECHNIK] Wolfgang VonKirschbaum In its Airships. Past. Present, and Future Aug. 1972 p 115-172 In GERMAN I he technical conditions for the development of airships are summarized. The following main points are taken as a background: low structural weight by using carefully optimized modern light construction methods, lightweight propulsion systems with low consumption based on the state-of-the-art of propulsion system technology, and improved maneuverability from stationary and dynamic points of view. ESRO N73-32996# Lockheed-California Co.. Burbank EXPERIMENTAL PROGRAM FOR THE DEVELOPMENT OF IMPROVED HELICOPTER STRUCTURAL CRASHWORTHI- NESS ANALYTICAL AND DESIGN TECHNIQUES. VOL- UME 1: COMPUTERIZED UNSYMMETRICAL MATH- EMATICAL SIMULATION AND EXPERIMENTAL VERIFI- CATION FOR HELICOPTER CRASH WORTHINESS IN WHICH MULTIDIRECTIONAL IMPACT FORCES ARE PRESENT Final Technical Report Gilbert Wittlin and Max A. Gamon May 1973 224 p refs (Contract DAAJ02-71-C-0066; DA Proj. 1F1-62203-A-529) (AD-764985: USAAMRDL-TR-72-72A-Vol-1) Avail: NTIS CSCL O1/2 The results of a four-phase study to develop helicopter structural crashworthiness analytical and design techniques are presented.. The study consisted of the development of a computer program (KRASH) and the verification of a mathematical model to predict the dynamic response during a survivable accident in which combined vertical and lateral impact velocities are present. Included in the study were a literature survey and evaluation, a detailed analysis of 32 accident cases, a drop test of a UH-1H helicopter with ground impact conditions of 23 fps vertical velocity and 18.6 fps lateral velocity, and parameter studies. It is concluded that program KRASH is capable of accurately predicting the dynamic responses during a multi-directional accident and that the program is a valuable tool with which to perform design tradeoff studies. (Modified author abstract) GRA N73-32998# Deutsche Gesellschaft fuer Luft- und Raumfahrt. Cologne (West Germany). ELECTRONIC DISPLAYS IN AIRCRAFT PILOTING [ELEK- TRONISCHE DISPLAYS IN DER FLUGFUEHRUNG] Jul. 1972 42 p refs In GERMAN: ENGLISH summary Presented at the 12th DGLR Comm. Meeting on Human Factors Engineering. Meckenheim. West Ger. 5 Nov. 1971 (DLR-MITT-72-04) Avail: NTIS HC $4.25: ZLDI. Munich 8.65 DM Two problems are discribed in the application of electronic display systems to aircraft. The first problem is that of reinforcing the pilot's activity during fully automatic landings: this can be solved by four tasks for advanced displays, whether used for manual control or as a monitor device in automatic landings. The second is the use of predictive displays for manual path and position control of VTOL aircraft. Two displays are discussed and have been tested: an overground display for path control, and an artificial horizon for position control. N73-32999 Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt. Oberpfaffenhofen (West Germany). POINTS OF VIEW FOR THE INFORMATION DISPLAY IN AIRCRAFT [GESICHTSPUNKTE FUER DIE INFORMATION SDARSTELLUNG IN FLUGZEUGEN] V. Wilckens /n_P.GLR__ Electron. Displays in Aircraft Piloting Jul. 1972 p 7-21 refs In GERMAN; ENGLISH summary The problem of reinforcing the pilot's activity during fully automatic landings is discussed. The human problem in all-weather landings is analyzed with particular reference to consideration to a larger extent of the real abilities and weaknesses of human beings. Four tasks are discussed which should be fulfilled by advanced displays, whether they are used for manual control or as a monitor device in automatic landings. ESRO N73-33000 Forschungsinstitut fuer Anthropotechnik. Mecken- heim (West Germany). USE OF PREDICTIVE DISPLAYS IN THE MANUAL PATH AND POSITION CONTROL OF VTOL AIRCRAFT [DER EINSATZ VON VORANZEIGEN BEI DER MANUELLEN KURS- UND LAGEREGELUNG VON VTOL FLUGZEUGEN] G. Johannsen In DGLR Electron. Displays in Aircraft Piloting Jul. 1972 p 23-33 refs In GERMAN The role of prediction displays for manual control of VTOL aircraft is discussed. The systems investigated are based on the extrapolative method of prediction, and two-parameter control. Two displays are discussed: an overground display for path control, and an artificial, horizon for position control both for a simulated VTOL aircraft. A number of tests were carried out to determine the effectiveness of these prediction displays. Results of the overground display show that because of the control task difficulty, the learning phase should last a few days. In the case of the artificial horizon, a clear reduction of the control errors is found by using the predictive display. ESRO N73 331670 School of Aerospace Medicine. Brooks AFB. Tex. A CRITICAL ASSESSMENT OF GROUND BASED DEVICES FOR SPATIAL ORIENTATION TRAINING Preliminary Report. Sap. 1972 - Apr. 1973 Patrick J. Dowd Aug. 1973 18 p refs (AF Proj. 7930) (AD-764740: SAM-TR-73-23) Avail: NTIS CSCL 05/9 Comparisons are made of selected orientation training devices in relation to U.S. Air Force flight training in the T-38 airplane. Assessment categories are: motion parameters, illusions that each device can generate, type of instrumentation available to the -pilot-subject in relation to attitude and control, reaction capability provided in each device for the subject to recover or correct his attitude, capability to measure and evaluate '.the subject's performance in coping with disorienting maneuvers, invulnerability to weather, safety, and initial and operating costs. The USAFSAM spatial orientation trainer (SOT) far excels all other ground-based devices for both hardware- and pilot-oriented assessment criteria. The use and need of a SOT-type trainer are discussed. . Author (GRA) N73-33170 Minnesota Univ.. Minneapolis. THE FLUID MECHANICS OF THE HOLE TONE Ph.D. Thesis- • • Ram Kumar Malta 1973 171 p • , Avail: Univ. Microfilms Order No. 73-18133 The hole tone is a whistle which has been empirically developed as an efficient producer of discrete frequency sound. Two parallel plates with an orifice in each are situated a short distance apart. The jet formed by fluid flow through one orifice impinges centrally on the second orifice and. under certain conditions, gives rise to a pure tone. The sound is aerodynamically generated. The mechanism involves symmetric disturbances of the jet and vortex ring formation in the vortex sheet surroun- ding the free jet. A model is postulated to show how the energy of a free jet is converted into acoustically radiated energy. According to the model, a periodic disturbance is imposed on 671 N73-33174 the jet at exu trom the upstream orifice, resulting in the formation of a vortex ring street. The rings propagate downstream and mteract with the second orifice-plate giving rise to a periodic flow through the orifice. This unsteady flow is the source of sound and also provides the perturbation at the upstream orifice which, triggers the instability of the jet. The analytic model is found to correctly predict the qualitative characteristics of the hole tone and quantitative characteristics such as the tone frequency and pressure amplitude. Dissert. Abstr. N73-33174 Johns Hopkins Univ.. Baltimore. Md. EXPERIMENTS ON THE NEARLY ISOTROPIC TURBULENCE BEHIND A JET GRID Ph.D. Thesis Mohamed Abo-EI-Fath Mohamed Gad-EI-Hak 1973 231 p Avail: Univ. Microfilms Order No. 73-16642 Wind tunnel turbulence behind a parallel rod grid with jets evenly distributed along each rod is nearly isbtropic. Homogeneity improvement over prior related experiments'was attained by the use of controllable nozzles. Compared with the passive case, the downwind-jet active grid gives smaller static pressure drop across it and smaller turbulence level at a prescribed distance, from it. while the upwind-jet grid gives larger static pressure drop and larger turbulence level. Counterflow injection apparently increases the effective solidity, causing instability, larger turbulent energy and larger scales. If the inverse turbulent kinetic energy is approximated as a power law of distance, the exponent decreases with increasing downwind or upwind jet strength, corresponding to slower decay rates. No peculiar decay behavior occurs when the grid is self-propelled (net average fore i on it = 0). or when the static pressure drop across it is ze 3. The injection does not change the general behavior of the inergy spectra although the absolute spectra changes in as rr. ch as the turbulence kinetic energy changes. Dissen Abstr. and the far-field intensity is considered. The physical quantity used is the gradient of the pressure evaluated on a geometrical plane at the smallest possible radial distance from the jet axis, but outside the vortical region, in the area where the homogeneous wave equation is reasonably well satisfied. The numerical and experimental procedures involved have been checked out by using a known source. Results indicate that the acoustic power output per unit length of the jet, in the region from which the sound emanates, peaks at approximately 9 diameters downstream. The acoustic emission for a jet Strouhal number of about 0.3 exceeds the emission for all other Strouhal numbers nearly everywhere along the measurement plane. However, the far-field peak intensity distribution obtained from the contribution of each station was found to depend on the spatial extent of the region where sound emanates from the jet. which, in turn, depends more on the far-field angle than on the Strouhal number • Author N73-33184*# National Aeronautics and Space Administration. Lewis Research Center. Cleveland. Ohio. CALCULATION PROCEDURES FOR POTENTIAL AND VISCOUS FLOW SOLUTIONS FOR ENGINE INLETS J. A. Albers and N. 0. Stockman [1973] 34 p refs Proposed for presentation at 1974 Intern. Gas Turbine Conf., Zurich, 31 Mar. - 4 Apr. 1974; sponsored by ASME (NASA-TM-X-71457) Avail: NTIS HC $3.75 CSCL 20D The method and basic elements of computer solutions for both potential flow and viscous flow calculations for engine inlets are described. The procedure is applicable to subsonic conventional (CTOL). short-haul (STOL), and vertical takeoff (VTOL) aircraft engine nacelles operating in a compressible viscous flow. The calculated results compare well with measured surface pressure distributions for a number of model inlets. The paper discusses the uses of the program in both the design and analysis of engine inlets, with several examples given for VTOL lift fans, acoustic splitters, and for STOL engine nacelles. Several test support applications are also given. Author N73-33179*# National Aeronautics and Space Administration. Lewis Research Center, Cleveland, Ohio. ASSESSMENT OF JETS AS ACOUSTIC SHIELDS BY COMPARISON OF SINGLE- AND MULTITUBE SUPPRES- SOR NOZZLE DATA Vernon H Gray. Orlando A. Gutierrez, and David Q. Walker 1973 21 p refs Presented at the Aeroacoustic Specialists Conf., Seattle, 15-17 Oct. 1973: sponsored by AIAA (NASA-TM-X-71450: E-7690) Avail: NTIS HC S3.25 CSCL 20D Recent 1/4 scale and engine size nozzle acoustic data, for both 37-tube and single nozzles, were used to test the jet-shielding principle. At low jet velocities the multitube nozzle total sound power approaches the equivalent of 37 single tubes (no shielding), while near-sonic and above, the small equivalent number of single tubes compares well with a geometric model of lateral radiation from only about a third of the circumference of the outer jets (nearly complete shielding). At high jet velocities, the geometric shielding hypothesis is in excellent agreement with acoustic data from which the downstream coalesced jet. noise is excluded. Present results are compared with an existing correlation for single jets, and with previous publications on multijet shielding. Author N73-33181*# National Aeronautics and Space Administration. Langley Research Center, Uangley Station. Va. ON THE RELATIONSHIP BETWEEN ACOUSTIC ENERGY DENSITY FLUX NEAR THE JET AXIS AND FAR FIELD ACOUSTIC INTENSITY Lucio Maestrello Washington Oct. 1973 64 p refs (NASA-TN-D-7269: L-8871) Avail: NTIS HC $3.00 CSCL 20D By measurement and analysis, the relationship between the distribution of the outflow of acoustic energy over the jet boundary N73-3318B# Royal Aircraf t Establishment, Farnborough (England). THE KUTTA-JOUKOWSKY CONDITION IN THREE DIMEN- SIONAL FLOW Robert Legendre Jul. 1973 22 p refs Transl. into ENGLISH from Rech. Aerosp. (France), v. 5, 1972 p 241-248 Presented at 13th Congr. of IUTAM, Moscow, Aug. 1972 (RAE-Lib-Trans-1709; BR36990) Avail: NTIS HC $3.25 The separation line along which a vortex sheet is attached to a wing is not always limited to the conventional trailing edge. It may extend to the wing tips and even to parts of the leading edges. In the light of observations of the flow over models of marine propellers and delta wings, a discussion is initiated, aimed at improving the description of the flow over an arbitrary wing, with a view to formulating a better basis for an accurate calculation of the flow of an ideal fluid, as a point of reference for the consideration of real flows. Author N73-33187 Vereinigte Flugtechnische Werke G.m.b.H.. Bremen (West Germany). EXPERIMENTAL STUDY OF WING PROFILE WITH FOWLER FLAPS AND SLATS [EXPERIMENTAL-STUDIE AN EINEM PROFIL MIT FOWLERKLAPPE UND VORFLUEGEL] Juergen Barche In DFVLR Papers on Fluid Oyn. with Emphasis on Boundary Layer Theory, Part 1 9 Mar. 1972 p 7-44 refs In GERMAN; ENGLISH summary Aerodynamic forces, pressure distribution, and wake of a wing profile with leading edge slats and trailing edge flaps were measured in a subsonic wind tunnel (maximum velocity of over 70 m/s). The measurements were performed to establish a theory 672 N73-33510 on high lift devices for takeoff and landing. To this end. in addition to the classic representation of test results, special plots were drawn to indicate the conditions in separated flow ranges. ESRO N73-33194 Karlsruhe Univ. (West Germany). Inst. fuer Stroemungslehre und Stroemungsmaschinen. TURBULENT SHEAR STRESS IN BOUNDARY LAYERS AT PERIODIC STATIONARY FREE FLOW PRESSURE PERTUR- BATIONS [DIE TURBULENTE SCH U B SPA N N U NG IN GRENZSCHICHTEN BEI PERIODISCHEN STATIONAEREN STOERUNGEN DER AUSSENGESCHWINDIGKEIT] K. 0. Felsch and R. Oechow In DFVLR Papers on Fluid Dyn. with Emphasis on Boundary Layer Theory. Part 1 9 Mar. 1972 p 125-134 refs In GERMAN; ENGLISH summary I he behavior ot a turbulent flat plate boundary layer at small periodic perturbations of the free stream pressure was studied experimentally. In particular, the influence of these perturbations on the shape of the shear stress profiles was investigated. The investigations were carried out in a small boundary layer wind channel over a trajectory of 2m. A wooden sonic wave wall was used to produce the periodic pressure perturbations.- ESRO N73-33229# Council for Scientific and Industrial Research, Pretoria (South Africa). Chemical Engineering Research Group. PRESSURE DROP IN AIR FLOW ACROSS BANKS OF FIN-TUBES WITH VARYING PITCH L. Sherman Mar. 1973 28 p refs (PB-220315/6; CSIR-SR-CENG-003) Avail: NTIS HC $3.00 CSCL 13A Air was blown isothermally across a bank of helically wound L-type fin tubes containing 6 tube rows. Six banks, each with a different triangular tube pitch, were investigated. The generally accepted Robinson 'and Briggs correlation underestimated the measured friction factor by about 20%. This is attributed to insufficient recognition of the effect of fin tube dimensions in this correlation, which also underestimates the effect of pitch, at least for the tubes used in these experiments. GRA N73-33230# Air Force Systems Command, Wright-Patterson AFB. Ohio. Foreign Technology Div. EFFECT OF INLET CONDITIONS ON THE OPTIMAL SHAPE OF A DIFFUSER D. I. Morozov 6 Aug. 1973 14 p refs Transl. into ENGLISH from Energ. Mashinostr. (USSR), no. 11, 1971 p 61-65 (AD-765577; FTD-HT-23-841-73) Avail: NTIS CSCL 20/4 The research is based on the application to short diffusers of the approximation theory of potential flow of a fluid in channels and the Bur single-parameter theory of a turbulent boundary layer. GRA beam, is made equal to the amplified output of the two strain-gauges bridges on the sting, by means of two attenuators. Thus the outputs from the sting amplifiers due to inertia are made zero, and when the wind is on the true oscillatory aerodynamic forces can be measured. To measure the steady state forces, the dc output of the sting due to weight is set at zero by means of a potentiometer when the wind is off. Author N73-33381# Honeywell. Inc.. Minneapolis. Minn. Systems and Research Div. AN INVESTIGATION OF A I R B O R N E D ISPLAYS AND CONTROLS FOR SEARCH AND RESCUE (SAR). VOL- UME 7. NAVY COMBAT SAR AVIONICS CAPABILITY STUDY (1972 - 1974 ERA) Final Report, Jun. 1972 - Jan. 1973 A. L. Jones and James W. Wingert Feb. 1973 53 p refs (Contract N00014-69-C-0460: NR Pro). 213-072) (AD-764914: HONEYWELL-12609-FR1-Vol-7: JANAIR-730702-Vol-7) Avail: NTIS CSCL 06/7 The report presents results of a study to assess the avionics capability of the present generation Navy combat search and rescue helicopters (HH-3A's). The study used interviews of experienced combat SAR pilots. Analyses were performed to evaluate the baseline HH-3A avionics and presently available avionic equipments against various search and environmental conditions. The most cost-effective improvement to the present HH-3A avionic capability for search and rescue was found to be Night-Vision Goggles for the pilot and a crew member. Author (GRA) N73-33502*# National Aeronautics and Space Administration. Lewis Research Center, Cleveland, Ohio. EXPERIMENTAL AND THEORETICAL INVESTIGATION OF HT-S/PMR-PI COMPOSITES FOR APPLICATION TO ADVANCED AIRCRAFT ENGINES M. P. Hanson and C. C. Chamis [1973] 33 p refs Proposed for presentation at 29th Reinforced Plastics Tech. and Manage- ment Conf., Washington, D. C., 5-8 Feb. 1974: sponsored by Reinforced Plastics/Composites Inst. of the Soc. of the Plastics Ind., Inc. (NASA-TM-X-71459; E-7700) Avail: NTIS HC $3.75 CSCL 110 Investigations were performed in order to: (1) demonstrate that high quality angleplied laminates can be made from HT-S/PMR-PI (PMR in situ polymerization of monomeric reactants), (2) characterize the PMR-PI material and to determine the HT-S unidirectional composite properties required for composite micro and macro-mechanics and laminate analyses, and (3) select HT-S/PMR laminate configurations to meet the general design requirements for high-tip-speed compressor blades. The results of the investigation show that HT-S/PMR laminate configurations can be fabricated which satisfy the high-tip-speed compressor blade design requirements when operating within the temperature capability of the polyimide matrix. Author N73-33366# Sydney Univ. (Australia). Dept. of Aeronautical Engineering. AN INSTRUMENT FOR MEASURING STEADY AND OSCILLATORY AERODYNAMIC FORCES L. Stellema Nov. 1973 53 p refs (ATN-7101) Avail: NTIS HC $4.75 An instrument to measure the steady and oscillatory aerodynamic forces on a sting-mounted model, using the forced oscillatory technique is described. The sting is oscillated in a sinusoidal motion of known amplitude and frequency. A flexible reference beam., situated outside the wind tunnel is oscillated in phase with the sting. A strain-gauge bridge bonded to the reference beam provides a phase reference signal. With the wind off, the amplified output of the strain-gauge bridge, on the reference N73-33510# Air Force Systems Command, Wright-Patterson AFB, Ohio. Foreign Technology Div. A P P A R A T U S FOR THERMOMECHANICAL SURFACE TREATMENT OF ORGANIC GLASS. ITS EFFECT. INSTRUC- TIONS AND PRACTICAL TESTING N. V. Skripnik. B. N. Blinov, and V. I. Prosvnrin 30 Jul 1973 18 p Transl. into ENGLISH from Eksplutatsionnaya Nadezhnost. Kachestvo i Svoistva Samoletnogo Organicheskogo Stekla (USSR), no. 177. 1971 p 79-93 (AD-764972; FTD-MT-24-438-73) Avail: NTIS CSCL 11/2 In designing equipment which removes the silver (crazing) on aircraft glass one must consider that such operations will be performed under civil aviation repair shop conditions as well as airport conditions. For this reason two items were designed: 673 N73-33518 one with an electrical drive, which is intended for repair shop conditions: one with a pneumatic drive, intended for both airport conditions and repair shop conditions. GRA N73-33518# Royal Aircraft Establishment. Farnborough (England). Structures Dept. THE PREDICTION OF INSTABILITIES OF LINEAR DIF- FERENTIAL EQUATIONS WITH PERIODIC COEFFICIENTS R. J. Davies London Aeron. Res. Council 1973 34 p refs Supersedes RAE-TM-Struct-794; ARC-33260; RAE-TR-67161: ARC 29 (ARC-R/M-3713; RAE-TM-Struct-794; ARC-33260; RAE-TR-67161: ARC-29) Avail: NTIS HCS3.75: HMSO t 1.32; PHI $5.30 The stability of the solutions of a system of differential equations with periodic coefficients has been examined using Floquet's theorem and a general method of solution has been programmed in ICL 1900 FORTRAN. The application of the method is illustrated by the solution of two dynamical systems, both of which are unsymmetrical rigid rotors in unsymmetrical bearings, and the program has been used to obtain solutions for up to six simultaneous second-order differential equations with periodic coefficients. Author (ESRO) N73-33522# Joint Publications Research Service. Arlington. Va. ANALYSIS OF METEOROLOGICAL CONDITIONS FOR AVIATION K. G. Abramovich. ed. 25 Sep. 1973 69 p refs Transl. into ENGLISH of the publ. "Analiz Meteorologicheskikh Usloviy dlya Aviatsii" Leningrad. Gidrometeoizdat. 1972 63 p (JPRS-60114) Avail: NTIS HC $5.50 Results are presented of studies conducted on weather phenomena which can limit aircraft landings and flights along air lanes. The effects of the spatial variability of the wind in the stratosphere on the accuracy of maintaining a flight trajectory by a supersonic transport at a given altitude are also discussed. N73-33523 Joint Publications Research Service. Arlington. Va. ANALYSIS OF VISIBILITY CONDITIONS WHEN LANDING AN AIRCRAFT IN A RADIATION FOG Yu G. Konovalov and M. Ya. Ratsimor In its Analysis of Meteorol. Conditions for Aviation (JPRS-60114) 25 Sep. 1973 p 2-8 refs Transl. into ENGLISH from the publ. "Analiz Meteorologiches- kikh Usloviy dlya Aviatsii" Leningrad. Gidrometeoizdat. 1972 P 3-9 A procedure is presented Tor calculating tne slant visibility range of ground objects for transparency of the atmosphere which is different with respect to altitude. The calculations were performed for a two-layer atmosphere: the layer of radiation fog and the layer above with relatively high transparency. It was demonstrated that the significant altitude of detection of the ground objects during observation at a high angle to the horizon can confuse the pilot of an aircraft making the approach for a landing with respect to visibility conditions when descending into a layer of fog. Author N73-33525 Joint Publications Research Service. Arlington. Va. TURBULENCE NEAR THE TROPOPAUSE IN THE PRESENCE OF HIGH ALTITUDE WAVES G. S. Buldovskiy In its Analysis of Meteorol. Conditions for Aviation (JPRS-60114) 25 Sep. 1973 p 17-27 refs Transl. into ENGLISH from the publ. "Analiz Meteorologicheskikh Usloviy dlya Aviatii" Leningrad. Gidrometeoizdat, 1972 p 17-27 A study was made of the distribution of the recurrence rate of cases of buffeting of different intensity in the troposphere, the layer of the tropopause and the lower stratosphere (to 18km) under the conditions of high altitude waves. It was established that for the occurrence of moderate or severe turbulence near the tropopause. in addition to the high altitude waves it is necessary also to have significant vertical shifts of'the wind vector, usually observed near the maximum in the vertical profile of the wind velocity. The probability of turbulence near the tropopause is greater, the deeper the inversion in the tropopause layer. An analysis was made of thedataof individual flights under the conditions of high altitude waves. Author N73-33528 Joint Publications Research Service. Arlington. Va. CONDITIONS OF ICING OF MODERN T R A N S P O R T AIRCRAFT FROM ROUTINE FLIGHT DATA O. K. Trunov and S. P. Khachatryan In its Analysis of Meteorol. Conditions for Aviation (JPRS-60114) 25 Sep. 1973 p 45-51 refs Transl. into ENGLISH from the publ. "Analiz Meteorologishes- kikh Usloviv diva Aviatsii" Leningrad. Gidrometeoizdat. 1972 p 45-51 The results of analyzing the statistical data on the icing conditions of modern transport aircraft completing flights from Moscow along the international air lane are presented. A study was made of the data on the recurrence rate of the icing zones as a function of the air temperature, the flight altitude, the form of the clouds, the time of year also the extent of the icing zones and the intensity of icing of the aircraft. Author N73-33529 Joint Publications Research Service. Arlington. Va. ADMISSIBLE SCALE OF SPATIAL AVERAGING OF THE VALUES OF THE GEOPOTENTIAL IN THE STRATOSPHERE CONSIDERING THE EFFECT OF THE WIND ON THE FLIGHT OF A SUPERSONIC AIRCRAFT S. V. Solemn and G. I. Mazurov In its Analysis of Meteorol. Conditions for Aviation (JPRS-60114) 25 Sep. 1972 p 52-61 refs Transl. into ENGLISH from the publ. "Analiz Meteorologiches- kikh Usloviy dlya Aviatsii" Leningrad. Gidrometeoizdat. 1972 p 52-61 A study was made ot the effect of the spatial variability of the wind in the stratosphere on the accuracy of maintaining the flight trajectory of a supersonic transport (SST) at a given altitude. On the basis of simulating the flights with different supersonic velocities on the level of the 100 millibar isobaric surface, admissible scales of spatial averaging of the data on the baric field were established as a function of the significance of the air space. The accuracy of maintaining the given route under different aerosynoptic conditions when using integral corrections is analyzed. The conclusion is drawn regarding the admissible scales of spatial averaging of the values of the geopotential for meteorological servicing of the SST flights. Author N73-33565 Ohio State Univ.. Columbus. CONSTRUCTION AND VALIDATION OF DECISION- THEORETIC MODELS OF LOW-LEVEL PILOTING AND NAVIGATIONAL BEHAVIOR Ph.D. Thesis Don Carl Hutcherson 1973 500 p Avail: Univ. Microfilms Order No. 73-18907 An attempt was made to determine whether or not decision and value theory concepts can be used as elements of a model to explain the behavior of a military decision maker in the heat of battle, under severe time constraints, and in the face of the enemy. The decision task selected for analysis is that faced by a helicopter pilot in planning a route to be followed during an attack upon a target. The results indicate that considerable variation exists between subjects so that it may be impossible to develop a single route selection model that is completely acceptable to all individuals. However, the decision behavior of a predominant class of decision makers is apparently described 674 N73-33741 to an acceptable degree by the route planning model, if the threat perception model known as Model One is used to measure perceived threat. Unfortunately, the model does not describe decision behavior equally well in all route selection situations. Furthermore, the data collected so far are not sufficient to determine whether or not the model can be used to predict the type of at tack a decision maker will conduct in a specific situation. Dissert. Abstr. on the 1980 time frame. The analysis was limited to specified North Atlantic and Pacific oceanic regions. The report presents detailed descriptions of the study assumptions, the cost indicator model, and the evaluation techniques, as well as a number of ancillary results regarding the technical and institutional environment of the oceanic aviation support system and the data base requirements encountered in performing the study. Author N73-33568# National Aviation Facilities Experimental Center. Atlantic City, N.J. EVALUATION OF LARGE SCREEN DISPLAY IN THE AUTOMATED OCEANIC ATC ENVIRONMENT Final Report, Jan. • Jul. 1973 Anthony J. Spingola and Robert L. Giordano Oct. 1973 45 p refs (FAA Proj. 102-150-020) (FAA-ND-73-75: FAA-RD-73-136) Avail: NTIS HC $4.25 Tests were conducted utilizing a representative traffic sample within an ocean sector incorporating the northern half of the Oakland Flight Information Region (FIR). The large Screen Display (LSD) was evaluated as a subsystem of the Oceanic Air Traffic Control Experimental Automation System. All test subjects controlled the same traffic sample and performed all of the interactions appropriate to a normal ocean sector operation. The LSD was used to portray all the required oceanic ATC data. A questionnaire was completed by each test subject immediately after completion of each test. There was no intention to evaluate the automated functions as they existed in the experimental system, nor was any consideration given to the cost or technical aspects of this LSD. Analysis of controller questionnaire responses indicates generally that the LSD was an acceptable method of displaying information: however, an individual cathode ray tube was preferred Author N73-33569# National Aviation Facilities Experimental Center. Atlantic City, N.J. OPERATIONAL EVALUATION OF THE ARTS 2 R A D A R ALPHANUMERIC DISPLAY SUBSYSTEM (RADS) James F. Akers and Robert A. Clark Oct. 1973 27 p (FAA Proj. 142-175-020) (FAA-NA-73-77; FAA-RD-73-1491 Avail: NTIS HC $3.50 A programmable, nontracking beacon Automated Radar Terminal System (ARTS II A) was installed in a TRACON configuration at the National Aviation Facilities Experimental Center. The operational suitability of the Radar Alphanumeric Display Subsystem (RADS) was evaluated. The RADS displays were evaluated over a 2-week period through the collection of subjective data obtained from controller questionnaires. It was concluded that the RADS consoles are suitable for use in air traffic control facilities. Modifications to the FOCUS control, MAP ILLUM control, A/N GAIN control, and Data Block Offset Switch are recommended. Author N73-33570# Computer Sciences Corp., Falls Church. Va. STUDY OF OCEANIC AIRSPACE AND GROUND NETWORK CONFIGURATIONS IN SATELLITE SYSTEMS Final Report S. A. Klein Washington FAA Jul. 1973 203 p refs (Contract DOT.-FA72WA-3102) (FAA-RD-73-59: Rept-4183-1) Avail: NTIS HC $12.25 The final results of a study of oceanic airspace and ground network configurations in satellite systems are presented. The purpose of the study was to investigate the restructuring of oceanic ATC airspace jurisdictional boundaries in the presence of a satellite system and to identify those future ATC jurisdictional configurations and ground facilities networks which most effectively utilize the satellite capability to obtain ground segment cost savings. The study was exploratory in nature and focused N73-33571# Mitre Corp.. McLean. Va. E X T R A P O L A T E D METHODOLOGY USED IN THE LOS ANGELES BASIN STANDARD TRAFFIC MODEL Final Report Frank Maginnis and Saul Cohen Washington FAA Apr. 1973 20 p refs (Contract DOT-FA70WA-2448) (AD-765153: MTR-6386; FAA-RD-73-86) Avail: NTIS CSCL 01/2 The Los Angeles Basin Standard Traffic Model is a computer model of the air traffic expected in the basin in 1982. The report explains the methodology used to project into the 1982 time frame a similar model of 1972 traffic. A technique known as time compression was used to make the projection. This report also defines the two types of models produced, the snapshot and scan-by-scan models, and it explains how the former was extracted from the later (Modified author abstract) GRA N73-33579 American Airlines. Inc.. Tulsa, Okla. Maintenance and Engineering Center. RADIATION SAFETY IN AIRLINE MAINTENANCE Warren J. Weldon In Bur. of Radiol. Health Radiation Safety and Protect, in Ind. Appl. Oct. 1972 p 137-147 The use of radiation technology and equipment for nondestruc- tive tests of airframes are discussed. The specific application is to the servicing of commercial aircraft during ground maintenance periods. The hazards encountered and the precautions to be observed during radiological inspections are reported. Specific actions followed by the airlines to protect personnel from radiation hazards are explained. P.N.F. N73-33740# Air Force Systems Command, Wright-Patterson AFB, Ohio. Foreign Technology Div. AN ELECTRICAL FIELD IN THE RESERVOIR OF A FUEL TANK AS IT IS FILLED WITH ELECTRIFIED FUEL B. K. Makaimov, A. A. Obukh, A. A. Navatskii, and V. A. Mokryshev 27 Jul. 1973 11 p refs Transl. into ENGLISH from the book "Tekh. Vysokikh Napryazh.- USSR, 1972 p 138-142 (AD-764941; FTD-HT-23-793-73) Avail: NTIS CSCL 21/4 Aviation fuel (kerosene, gasoline) is highly electrified during passage along pipes and through filters. Charged fluid, filling a reservoir, is a source of an electrical field in a vapor-air space. If the magnitude of the field reaches disruptive strength, a spark discharge will occur. The discharge can be the cause of the ignition of the fuel. The article shows the calculated and graphic dependences, which make it possible to quickly evaluate the components of a three-dimensional electrical field in a vapor-air space an example of which is the TZ-16 fuel tank. The illustrated results may be used for any other reservoir configuration which does not differ significantly from rectangular. GRA N73-33741*# National Aeronautics and Space Administration. Lewis Research Center. Cleveland, Ohio. HIGHLY NOISE SUPPRESSED BYPASS 6 ENGINE FOR STOL APPLICATION W. L. Jones. L. J. Heidelberg, and R. G. Goldman 1973 21 p 675 N73-33742 refs Presented at Aeroacoustic Specialists Conf.. Seattle, 15-17 Oct 1973: sponsored by AIAA (NASA-TM-X-71448) Avail. NTIS HC $3.25 CSCL21E A TF-34 engine with an acoustically treated ground test nacelle was built and tested to determine the feasibility of suppressing fan.and core engine noise to the stringent levels required for STOL or short-haul commercial aircraft. The design incorporates wall treatment for the fan and core plus three treated splitter rings in the inlet and two treated splitters in the aft fan duct. Maximum suppression of fan tone noise of 40-45 db was obtained from both the inlet and aft fan treatment. At rated fan speed, overall noise was reduced by 21 PNdb to a value of 94 PNdb on a 500-foot sideline. The overall noise reduction value was limited by the jet noise floor. Thrust losses due to the acoustic treatment are also discussed. Author N73-33742*# National Aeronautics and Space Administration. Lewis Research Center. Cleveland, Ohio. NOZZLE GEOMETRY AND FORWARD VELOCITY EFFECTS ON NOISE FOR CTOL ENGINE-OVER-THE-WING CON- CEPT U. VonGlahn, J. Goodykoontz. and J. Wagner 1973 30 p refs Presented at 86th Meeting of the Acoustical Soc. of Am., Los Angeles. 30 Oct. - 2 Nov. 1973 (NASA-TM-X-71453: E-7730) Avail: NTIS HC $3.50 CSCL 21E Acoustic shielding benefits for jet noise of engine-over-the- wing for conventional aircraft (CTOL) application were studied with and without forward velocity for various small-scale nozzles. These latter included convergent, bypass and mixer, with and without forward ejector, nozzles. A 13-inch free jet was used to provide forward velocity. Farfield noise data were obtained for subsonic jet velocities from 650 to 980 ft/sec and forward velocities from zero to 360 ft/sec. The studies showed that although shielding benefits were obtained with all nozzles, the greatest benefits were obtained with mixer nozzles. The absolute magnitude of the jet noise shielding benefits with forward velocity was similar to the variation in nozzle-only noise with forward velocity. Author N73-33743*# National Aeronautics and Space Administration. Lewis Research Center. Cleveland. Ohio. DISPERSION AND DILUTION OF JET AIRCRAFT EXHAUST AT HIGH-ALTITUDE FLIGHT CONDITIONS James D. Holdeman [1973] 10 p refs Proposed for presentation at the 12th Aerospace Sci. Meeting. Wash.. D. C.. 30 Jan. 1 Feb. 1974: sponsored by AIAA (NASA-TM-X-71451: E-7720) Avail: NTIS HC $3.00 CSCL 21E A method is presented for estimating the dispersion and dilution of jet aircraft exhaust from aircraft passage through times on the order of weeks thereafter. In the near wake of the aircraft, the solution is that for round turbulent jets in a parallel flow. More rapid dispersion due to atmospheric effects begins when the scale-dependent eddy viscosity becomes larger than the turbulent jet eddy viscosity. In the far wake region, the solution approaches that for scale-dependent dispersion from a point source moving with the aircraft. Calculations are presented for supersonic aircraft at high altitude flight conditions. Author N73-33744*# National Aeronautics and Space Administration. Lewis Research Center, Cleveland, Ohio. NUMERICAL SIMULATION OF NOISE PROPAGATION IN JET ENGINE DUCTS Kenneth J. Baumeister and Edward C. Bittner Washington Oct. 1973 50 p refs (NASA-TN-D-7339: E-7217) Avail: NTIS HC $3.00 CSCL 20A A finite difference formulation is presented which is useful in the study of acoustically treated inlet and exhaust ducts used in turbofan engines. The difference formulation can readily handle acoustic flow field complications, such as axial variations in wall impedance and cross-sectional area, that would occur in a sonic inlet. In formulating the difference solutions, the continuous acoustic field is lumped into a series of grid points spread uniformly throughout the field. At each point, the pressure is separated into its real and imaginary terms. Example solutions are presented for sound propagation in a one-dimensional straight hard-wall duct and in a two-dimensional straight soft-wall duct without steady flow. Author N73-33748*# General Electric Co.. Cincinnati. Ohio. Aircraft Engine Group. A STUDY OF ENGINE VARIABLE GEOMETRY SYSTEMS FOR AN ADVANCED HIGH SUBSONIC LONG RANGE COMMERCIAL AIRCRAFT M. A. Compagnon Oct. 1973 112 p refs (Contract NAS3-15544) (NASA-CR-134495: R73AER185) Avail: NTIS HC$7.75 CSCL 21E Several variable geometry high Mach inlet concepts, aimed at meeting a system noise objective of 15 EPNdB below FAR pan: 36. for a long range. Mach 0.9 advanced commercial transport are assessed and compared to a fixed geometry inlet with multiple splitters. The effects of a variable exhaust nozzle (mixed exhaust engine) on noise, inlet geometry requirements, and economics are also presented. The best variable geometry inlet configuration identified is a variable cowl design which relies on a high throat Mach number for additional inlet noise suppression only at takeoff, and depends entirely on inlet wall treatment for noise suppression at approach power. Relative economic penalties as a function of noise level are also presented. Author N73-33755# Deutsche Gesellschaft fuer Luft- und Raumfahrt. Cologne (West Germany). BEHAVIOR OF TURBOJETS Jan. 1973 114 p refs In GERMAN: ENGLISH summary Proc. of the DGLR Airbreathing Propulsion Committee Meeting. Darmstadt. West Ger., 24 May 1972 (DLR-MITT-73-05) Avail: NTIS HC $7.75: ZLDI. Munich 23,95 DM The influence of combustion chambers, compressors, and afterburners, and their mechanical configuration, on the static performance of two-cycle turbojet engines, with a high bypass ratio was investigated. Some examples are given to show the influence of the variation of both nozzle surfaces and fuel throughput at given thrust on the parameters of the same engines without primary and secondary flow mixing. The performance of arbitrarily switched gas turbines was calculated by simulation with building block system on a digital computer. The effects of a partly oil-filled converter for a turbine engine used to supply starting power to the main engines were investigated. For individual titles, see N73-33756 through N73-33759 ESRO N73-33756 Motoren- und Turbinen-Union Muenchen G.m.b H. (West Germany). EFFECT OF SINGLE COMPONENTS AND THEIR MECHANI- CAL LAYOUT ON THE STATIC PERFORMANCE OF TWO-CYCLE TURBOJET ENGINES [EINFLUSS EINZELNER KOMPONENTEN UND IHRER MECHANISCHEN ANORD- NUNG AUF DAS STATIONAERE BETRIEBSVERHALTEN VON 2-KREIS-TRIEBWERKEN] Hubert Grieb In DGLR Behavior of Turbojets Jan. 1973 p 7-50 In GERMAN The influence of combustion chambers, compressors and afterburners, and their mechanical configuration, on the static nerformance of twg-cvcle turbojet engines with a high bypass 676 N73-33920 ratio was investigated. As a basis for comparison of the thermodynamic cycling processes, maximal thrust with and without afterburning at sea altitude and a flight Mach number of 0.9 were chosen. The following conclusions were drawn with regard to the type of engine investigated: (1) within certain limits, a desired performance can be obtained with several thermodynamic designs: 12) the influence of the mechanical configuration of the turbopan in the static performance is small: (3) the technological state-of-the-art of the components is essential for the quality of stationary operating characteristics: (4) the optimal tuning of the compressor characteristics to the expected load lines has considerable influence on the operation: (5) the design of low pressure compressor transition to medium pressure compressor and (6) bypass channel needs special attention besides mechanical conception. ESRO N73-33757 Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt. Brunswick (West Germany). Inst. fuer Luftsaugende Anthebe. PERFORMANCE BEHAVIOR OF A TWO-CYCLE TURBOJET ENGINE FOR M U LTIP A R AM ETER CONTROL [DAS LEISTUNGSVERHALTEN EINES ZWEISTROMTRIEBWERKS BEI MEHRGROESSENREGELUNG] Heinrich Oissen In DGLR Behavior of Turbojets Jan. 1973 p 55-72 In GERMAN Some examples are given to show the influence of the variation of both nozzle surfaces and fuel throughput at given thrust and other boundary conditions on the engine parameters of a two-cycle turbojet engine with large bypass ratio without primary and secondary flow mixing. To this end, a computation method was developed for describing the performance of engines with multiparameter control. The advantages of multiparameter control are summarized. The disadvantages are: the system is more complicated, adjustable nozzles add to the engine weight, and accurate measurements are necessary for determining the engine parameters. ESRO (Contract NAS4-1845) (NASA-CR-127490) Avail: NTIS HC S9.75 CSCL 01C An investigation to provide the analyses, data, and hardware required to experimentally validate the beaded panel concept and demonstrate its usefulness as a basis for design of a Hypersonic Research Airplane (HRA) wing is reported. Combina- tions of the beaded panel structure, heat shields, channel caps and corrugated webs for ribs and spars were analyzed for the wing of a specified HRA to operate at Mach 8 with a lifespan of 150 flights. Detailed analyses were conducted in accordance with established design criteria and included aerodynamic heating and load predictions, transient structural thermal calculations, extensive NASTRAN computer modeling, and structural optimiza- tion. Optimum beaded panel tests at 922 K (1200 F) were performed to verify panel performance. Close agreement of predicted and actual critical loads permitted use of design procedures and equations for the beaded panel concept without modification. Author N73-33887*# Grumman Aerospace Corp.. Bethpage. N.Y FLUTTER ANALYSIS AND TESTING OF PAIRS OF AERODY- NAMICALLY INTERFERING DELTA WINGS Final Report Richard R. Chipman and Frank J. Rauch Washington NASA Nov. 1973 95 p refs (Contract NAS1-10635-7) (NASA-CR-2331) Avail: NTIS HC $3.75 CSCL 018 To examine the effect on flutter of the aerodynamic interference between pairs of closely spaced delta wings, several structurally uncoupled 1/80th-scale models were studied by experiment and analysis. Flutter test boundaries run in a 26-in transonic blowdown wind tunnel were compared with subsonic analytical results generated using the doublet lattice method. Trends for several combinations of vertical and longitudinal wing separation showed that flutter speeds can be significantly lowered in closely spaced configurations. For some configurations, a new flutter mechanism, characterized by coupling of the flexible modes from both surfaces at a distinctive flutter frequency, was predicted and observed. Author N73-33761# Pratt and Whitney Aircraft, East Hartford. Conn. INFLUENCE OF VARIABLE TURBINE GEOMETRY ON ENGINE INSTALLATION LOSSES AND CYCLE SELECTION Final Technical Report. Apr. 1971 - Nov. 1972 Robert J. May, Jr. and William F. Zavatkay Jun. 1973 34 p Presented at 8th JANNAF/AIAA/SAE Propulsion Joint Specialist Conf.. New Orleans. La.. 27 Nov. - 1 Dec. 1972 Sponsored by AF (AF Proj. 3066) (AD-765533; AFAPL-TR-73-18) Avail: NTIS CSCL 21/5 The trend in military aircraft is toward increasing thrust loading for improved maneuverability coupled with a requirement for extended subsonic cruise range at low power settings. Conven- tional turbine engines designed to meet these requirements must operate over large ranges of airflow between maximum power and cruise. As a result, the inlets and nozzles designed for these engines cannot perform efficiently with the low airflow rates typical of subsonic cruise operation. Variable turbine geometry, however, offers a promising approach for obtaining both high thrust loading and efficient cruise performance by permitting large amounts of thrust modulation at constant airflow rates. As an example, the performance of a turbojet engine, which provides efficient high-thrust maneuvering and supersonic operation, can be improved by variable turbine geometry to the point where it is competitive with a fixed-turbine- geometry turbofan engine in the low-thrust subsonic cruise regime. (Modified author abstract) GRA N73-33919*# Aerospace Corp.. El Segundo. Calif. SYSTEM COST/PERFORMANCE ANALYSIS (STUDY 2.3). VOLUME 1: EXECUTIVE SUMMARY Final Report. 1 Sep. 1972 - 31 Aug. 1973 T. Kazangey 28 Sep. 1973 31 p (Contract NASw-2472) (NASA-CR-135903: ATR-74(7333)-1-Vol-1) Avail: NTIS HC $3.75 CSCL 14A The relationships between performance, safety, cost, and schedule parameters were identified and quantified in support of an overall effort to generate program models and methodology that provide insight into a total space vehicle program. A specific space vehicle system, the attitude control system (ACS), was used, and a modeling methodology was selected that develops a consistent set of quantitative relationships among performance, safety, cost, and schedule, based on the characteristics of the components utilized in candidate mechanisms. These descriptive equations were developed for a three-axis, earth-pointing, mass expulsion ACS. A data base describing typical candidate ACS components was implemented, along with a computer program to perform sample calculations. This approach, implemented on a computer, is capable of determining the effect of a change in functional requirements to the ACS mechanization and the resulting cost and schedule. By a simple extension of this modeling methodology to the other systems in a space vehicle, a complete space vehicle model can be developed. Study results and recommendations are presented. Author N73-33883*# Martin Marietta Corp., Denver. Colo. HYPERSONIC WING TEST STRUCTURE DESIGN. ANALY- SIS. AND FABRICATION Final Report P. P. Plank and F. A. Penning Aug. 1973 154 p refs N73-33920*# Aerospace Corp.. El Segundo. Calif. SYSTEM COST/PERFORMANCE ANALYSIS (STUDY 2.31. VOLUME 2: STUDY RESULTS Final Report. 1 Sep. 1972 677 N73-33921 31 Aug. 1973 T Kazangey 28 Sep. 1973 376 p ref (Contract NASw-2472)(NASA-CR-135902: ATR-74(7333)-1-Vol-2) Avail: NTIS HC S21 00 CSCL 14A The relationships between performance, safety, cost, and schedule parameters were identified and quantified in support of an overall effort to generate program models and methodology that provide insight into a total space vehicle program. A specific space vehicle system, the attitude control system (ACS), was used, and a modeling methodology was selected that develops a consistent set of quantitative relationships among performance, safety, cost, and schedule, based on the characteristics of the components utilized in candidate mechanisms. These descriptive equations were developed for a three-axis, earth-pointing, mass expulsion ACS. A data base describing typical candidate ACS components was implemented, along with a computer program to perform sample calculations. This approach, implemented on a computer, is capable of determining the effect of a change in functional requirements to the ACS mechanization and the resulting cost and schedule. By a simple extension of this modeling methodology to the other systems in a space vehicle, a complete space vehicle model can be developed. Study results and recommendations are presented. Author N73-33921# RAND Corp.. Santa Monica. Calif. TRANSPORTATION AND ENERGY W. E. Mooz Jun. 1973 23 p refs Presented at the 1st Annual Illinois Energy Conf.. Chicago, 13-15 Jun. 1973 (Grant NSF GI-44) (P-5025) Avail: NTIS HC $3.25 CSCL 21D The use of energy in the transportation sector is discussed. Transportation in the United States presently uses about 25 percent of the total annual energy budget, and the use of energy in the sector is increasing at an average annual rate of about 4 percent per year. Over 95 percent of this energy is supplied by petroleum fuels, and the biggest users are motor vehicles. Differences in modal efficiencies are shown, with motor vehicles and aircraft the least efficient energy users. The growth in energy use by transportation is shown to be due to increasing modal energy intensiveness. shifts in traffic from low intensiveness modes to high intensiveness modes, and increasing per capita use of transportation. One may expect to see more small cars, shifts from air and highway modes to buses, trains, and pipelines, and changes in personal transportation habits. Author Infrared Countermeasures. White Oak. Md.. 10 Apr. 1973 Sponsored By AEC (SLA-73-5271: Conf-730428-1) Avail: NTIS HC $3.50 The AIRVAL program has conducted a survey to determine the extent of past infrared (IR) signature measurements on high-performance jet aircraft. The results of this survey have been used to categorize broadly aircraft signatures and to indicate areas requiring further signature measurement. Measure- ments on the F-102 are now underway at Naval Weapons Center The results of these measurements will be compared to signature predictions of the F-102 as calculated by Grumman Aircraft Corp. Additional IR signature measurements will be made this calendar year on the A-3, A-4, A-7, F-4, F-5. and F-14 by the measurement groups at the Naval Missile Center and Eglin AFB using advanced instrumentation and techniques. The results of these measurements will be combined with target vulnerabil- ity models and missile guidance, fuze, and warhead characteris- tics in a computer model to determine the predicted outcome of missile/target encounters. The results of a drone firing program will be compared to the computer model predictions. Author (NSA) N73-33930# Eurosat S.A.. Geneva (Switzerland). AIMS. PROSPECTS, ORGANISATION. AND FINANCING Aug. 1972 30 p Avail: NTIS HC $3.50 The aims, prospects, organization, and financing of EUROSAT S.A. are presented. EUROSAT S.A. was founded in January 1972 to cooperate with public authorites to ensure economical use of the possibilities offered by space techniques. Emphasis was placed on satisfying European requirements in ATC, navigation, and meteorological and communication satellites. ESRO N73-33928# Committee on Science and Astronautics (U. S. House). SHORT TERM ENERGY SHORTAGES Washington GPO 1973 928 p refs Hearings before Comm. on Sci. and Astron., 93d Cong., 1st Sess.. No. 7. 3. 8 and 17 May 1973 Avail: Subcomm. on Energy Congressional hearings are given on the causes and implica- tions of impending shortages of gasoline, heating oil, diesel fuel, jet engine fuel, and electricity. The immediate energy shortages and policy options are discussed in three parts: (1) the character of the present energy crisis, (2) the relationship of energy growth and economic growth, and (3) the relationship of short-run measures and long-term objectives. Short term fuel shortages are given along with their effects on the electric utilities. The hearings take into account the regulated energy industries and the effect of the present situation on energy research and development. A gas field identification list is included, T.M.R. N73-33929# Sandia Labs., Albuquerque. N.Mex. A IRVAL: DOO PROGRAM TO EVALUATE AIR-TO-AIR MISSILE EFFECTIVENESS T. E. Latta Mar. 1973 30 p Presented at 11th Symp. on 678 SUBJECT INDEX AERONAUTICAL ENGINEERING / A Special Bibliography (Suppl. 39) JANUARY 1974 Typical Subject Index Listing BIDBOCiBBOl [ L Conservation of fossil fuels in coiaercial aviation by using hydrogen BASA-CB-112204 NOTATION OF CONTENT OH TITLE 1 REPORT NUMBER |H73-11Q19| The subject heading is a key to the subject content of the document. The Notation of Content (NOC). rather than the title'of the document, is usually used to provide a more exact description of the subject matter. (In some cases AIAA uses the title in lieu of an NOC.) The report number helps to indicate the type of document cited (e.g.. NASA report, translation. NASA contractor report). The accession number is located beneath and to the right of the Notation of Content, e.g.. N73-11019. Under any one subject heading, the accession num- bers are arranged in sequence with the IAA accession numbers appearing first. A-7 AIRCRAFT Design, development, and evaluation of automatic departure prevention system and stall inhibitor for A-7 aircraft f*D=76«7671 S73-31972 AC GENERATORS 1C starter generator featurintj variable-to=constant frequency conversion by cycloconverters as switching device for use with aircraft engines A73-45154 Fixed installation ground electrical power supply system for aircraft service, discussing motor-alternators, plant control cubicles, selector and busbar switchboxes and fault protection devices A73-tt5156 ACCBIER&TIOB (PHYSICS) 3elative frequency of occurrence of different normal accelerations at the center of gravity of aircraft in turbulence f ABC=P/H-37141 N73=32929 ACOUSTIC DOCTS A difference theory for noise propagation in an acoustically lined duct with mean flow, fJIAA PAPSH 73-.10071 A73-4«8!!') The influence of aerodynamic flow noise in turbofan engines FlIAi PAP13B 73-10161 A73-44848 Automatic control system for in=duct cancellation of spinning modes of sound CNiSi-CR-1323171 N73-32540 1COOSTIC FSTIGOB Acoustic fatigue resistance of aircraft structures at elevated temperatures, r&IAf. PAP3P T3-99B1 A73-44829 ACOUSTIC HEASOBEBEHTS Ewirlinq flow effect on let noise suppression based on acoustic field and enqine thrust measurements with and without stationary swirl vanes in exhaust nozzle T A I A J . PAPER 73-T1031 A73-KQ836 Noise comparisons from full-scale fan tests at N A S A lewis Research Center f & I A A PAPER 73-10171 A73-44349 The effects of modulated blade spacinq on static rotor acoustics and performance- T A I U PAP?P 73-1C2P1 A73-44852 Acoustic investigation of the enqine=over-the=wing concept using a D=shaped nozzle f A I A A PSP^S 73-1C3C1 A73-9486C A new device for neasnring local acoustic power output of subsonic lets, f A I A A PAPBH 73-10421 A73-44866 Calculation procedures for predicting noise-time histories and noise contours for various types of aircraft rNASA-CR-1106491 H73-31945 Computer programs for predicting the noise=time histories and noise contours for five types of aircraft rRASA-CR-1146501 N73-31946 Acoustic measurements of aerodynamic noise produced by inpinqement of let exhaust on wing and flap of externally blown flap system installed on F-111 aircraft N73-32964 Aerodynamic noise characteristics of short takeoff aircraft with externally blown flaps and engines mounted over and under winq N73-32966 Forward velocity effects on let noise with dominant internal noise source rHASA-TH-X-714381 H73-32968 Method for predictinq noise qenerated by deflectinq enqine exhaust for under-the-winq and over-the-winq versions of externally blown flap configuration rNASA-TH-X-714191 H73-32969 ACODSTIC PROPiGiTIOH Effect of a slipstream on the acoustic radiation of ultrasonic annular lets A73-45358 ACOUSTIC PROPERTIES Subsonic and supersonic lets and supersonic suppressor characteristics, TAIAA PAPER 73-9991 473=44834 Far field noise reduction of tiltinq rotor aircraft based on performance and weight tradeoffs to improve acoustic signatures CHASA-CR-1146481 N73-31937 Theory for predictinq sonic boom intensity and techniques for sonic boom suppression fFia-RD-73-4 1 H73-31944 Calculation procedures for predictinq noise-time histories and noise contours for various types of aircraft fNASA-CS-1146491 H73-31945 Computer proqrams for predictinq the noise-time histories and noise contours for five types of aircraft r NASA-CR-1146501 H73-31946 Analysis of let engine noise to show sources of noise, noise spectra, and use of laminates and composite materials for noise reduction H73-32962 Characteristics of aerodynamic noise generated by interaction of airstrean with flap surface to show location and control of noise sources S73-32963 Bind tunnel tests to determine acoustic properties of externally blown flap and anqmentor winq for short takeoff aircraft confiqurations 117 3-32965 Method for predicting noise qenerated by deflectinq enqine exhaust for under-the-winq and over-the-winq versions of externally blown flap configuration fNASA-IB-X-714491 N73-32969 Bind tunnel tests to determine acoustic properties of larqe scale lift fan transport aircraft model rNASA-TB-X-622841 N73-32975 Relationship between distribution of outflow of acoustic enerqy over let boundary and far-field intensity fNASA-TN-D-72691 N73-33181 S-1 1COUSTIC TELOCITY SUBJECT IBDBX ACOUSTIC VELOCITY Acoustic velocity and sound propagation differences in incompressible and compressible flaids related to Bach cone formation and sonic boom effects 173-95269 ADAPTIVE COHTEOL Sensitivity, adapt!vity and optimality; Proceedings of the Third Symposium, Ischia, Italy, June 18-23, 1973- A73-43277 Design of mnltivariable adaptive model following control systems A73-43288 ADHESITE BORDIHG Adhesive bonding of structures and composite materials on advanced turbofan engines N73-32470 AERODTB1HIC CHARACTERISTICS Aerodynamic vind tunnel perforaance of high bypass pressure ratio fan engine for STOL aircraft [HASA-TH-X-71445] N73-31931 Wind tunnel tests to determine static and dynamic stability coefficients for circular cone with various nose bluntness configurations fAD-7651641 H73-31934 Computer program for analyzing characteristics of parachute-payload system during deployment and trajectory H73-31936 Wind tunnel tests of high harmonic circulation control rotary wing model to show instruments reguired and data acguisition procedures fAD-7653201 H73-31984 Thrust augmentation, lift forces, and mixing properties of two-phase flow propulsion and lift system for ground effect machines fAD-7653321 N73-32208 Aerodynamic characteristics of flow around elliptic cones at large angles of attack fAD-764945] N73-32209 Rind tunnel tests to determine aerodynamic characteristics of three oblique, high aspect ratio wing and body combinations at Hach numbers between 0,60 and 1•40 fNASA-TH-X-622561 1173-32926 Hind tunnel tests to determine aerodynamic characteristics of obligne wing and body combination at Hach numbers between 0,60 and 1,40 CHASA-TH-X-622071 N73-32927 Oblectives and findings of study to determine applicability of short takeoff aircraft for short-haul air transportation systems H73-32936 Rind tunnel tests to determine aerodynamic characteristics of upper surface blown let-flap concept incorporating high-bypass-ratio tnrbofan engines H73-32943 Development and evaluation of active control system to provide ride smoothing on short . takeoff aircraft H73-32951 .Transonic wind tunnel tests to determine lift, drag, and stability characteristics of F-8 aircraft model with obligne wing fHASA-TH-X-622731 H73-32974 Transonic wind tunnel tests to determine effects on flutter of aerodynamic interference between pairs of closely spaced delta wings fNASA-CP- 23311 H73-33887 AEHODISABIC COEFFICIENTS Airfoil theory calculation of bent thin foil lift coefficient and longitudinal moment characteristics at arbitrary flow separation point location A73-43720 Aerodynamic characteristics of augmentor wings and .analysis of augmentation and entrainnent in defining a net thrust coefficient H73-32942 Rind tunnel tests to determine magnitude of adverse ground effects on longitudinal aerodynamic coefficients of powered-lift short takeoff aircraft H73-32950 ABBODIIAHIC CORFIGUBATIOIS Dirigible airship design, operations, payloads, cargo transportation and surveillance applications A73-44223 Roise comparisons from full-scale fan tests at HASA Lewis Research Center. tAIAA PAPEB 73-1017] A73-44849 Acoustic investigation of the engine-over-the-wing concept using a D-shaped nozzle, TAIAA PAPBR 73-i03«i A73-44860 Hind tunnel tests to determine flow distribution at inlet locations on aircraft nodel for various aerodynamic configurations and airspeeds CHASA-TH-D-73641 S73-31929 Procedure for evaluating relative economic value of technology factors affecting design, configuration, and operation of hypersonic cruise transport CHASA-CH-22861 N73-31953 Flight tests of modified F-1C6 aircraft to determine installation effects of two aft underwing nacelles housing afterburning J-85 engines rHASA-TM-X-714391 N73-31959 Aerodynamic design of inlet stage for two-stage compressor and performance comparison for axial, mixed flow, and centrifugal stage configurations fHASA-CH-120943] N73-32610 Hind tunnel tests to determine aerodynamic characteristics of obligue wing and body combination at Hach numbers between 0.60 and 1.40 fHASA-TH-X-622071 H73-32927 Aerodynamic and performance characteristics of short takeoff aircraft equipped with externally blown flaps H73-32939 Rind tunnel tests to determine stability and control characteristics of externally blown let-flap configurations H73-32940 Aerodynamic characteristics of angmentor wings and analysis of augmentation and entrainment in defining a net thrust coefficient H73-32942 Rind tunnel tests to determine aerodynamic characteristics of five configurations of short takeoff aircraft wind tunnel models N73-32944 Flight tests of augmentor-wing let STOL research aircraft to compare vind tunnel data with flight data for dynamic characteristics and limitations H73-32954 Hind tunnel tests to determine acoustic properties of externally blown flap and augmentor wing for short takeoff aircraft configurations H73-32965 Aerodynamic noise characteristics of short takeoff aircraft with externally blown flaps and engines mounted over and under wing H73-32966 Flight tests of Boeing 727 aircraft to determine effects of modifications on reduction of aerodynamic noise rFAA-BD-72-40-VOL-3] H73-32971 Effect of inlet conditions on optimal shape of diffuser based on theory of potential flow of fluid in channels rAD-7655771 H73-33230 ABRODIIAHIC DBAG Aerodynamic drag and lift of airships, noting boundary layer control by suction H73-32994 Technical conditions for airship development, noting weight redaction, propulsion system performance, and maneuverability improvement H73-32995 ABBODTIAHIC FOBCBS Analysis of aerodynamic drag on object moving in rarefied qas under nearly free molecular flow conditions H73-32923 On the effects of viscous interaction for a flat delta wing at incidence ' . rABC-CP-1237] B73-32931 Development of instrument to measure steady and oscillatory aerodynamic forces on sting-mounted model using forced oscillation technique fATH-71011 H73-33366 A-2 SDBJBCT IVDBX AIB COOLIHG AEPODTHABIC IHTBRFBRBHCB Slotted transonic wind tunnel tests on pitchinq delta winq enable selection of porpous vails for interference free damping derivatives UBOR/H-37151 . , H73-32930 ABRODYHABIC LOADS Calculation of the deformations of a propeller blade in fliqht A73-43724 A theoretical and experimental study of sound attenuation in an annular duct fAIAA PAPBF 73-10P51 A73-«4838 ABRODTHABIC HOISB Supersonic let noise generated by larqe scale disturbances- UIAA PAPER 73-9921 A73-44827 Subsonic and supersonic lets and supersonic suBpressor characteristics- fATAA PAP3H 73-9991 A73-44834 \ difference theory for noise propagation in an acoustically lined duct with mean flow, UIAA PAPER 73-10071 A73-44840 The influence of aerodynamic flow noise in turbofan enqines fAIJSA PAPER 73-10161 A73-48848 Progress in source noise suppression of subsonic tip speed fans, fAIAi PAPER 73-10321 A73-44861 Comparison of results obtained vith various sensors used to measure fluctuating quantities in lets TAIAA PAPER 73-1?431 A73-44867 Emission of sound from a rectangular plate vibratinq under the action of pressure pulsations in a turbulent boundary layer A73-44899 Far field noise reduction of tiltinq rotor aircraft based on performance and weight tradeoffs to improve acoustic signatures CHASA-CR-1146481 H73-31937 Characteristics of aerodynamic noise generated by interaction of airstream with flap surface to show location and control of noise sources H73-32963 Acoustic measurements of aerodynamic noise produced by impinqement of let exhaust on winq and flap of externally blown flap system installed on P-111 aircraft N73-32964 Hind tunnel tests to determine acoustic properties of externally blown flap and auqmentor winq for short takeoff aircraft configurations H73-32965 Method for predicting noise qenerated by deflectinq enqine exhaust for nnder-the-vinq and over-the-winq versions of externally blown flap configuration' f NASA-IB-X-7H491 N73-32969 Fliqht tests of Boeing 727 aircraft to determine effects of modifications on reduction of aerodynamic noise rFAA-HD-72-»0»VOL-31 H73-32971 Wind tunnel tests to determine acoustic properties of larqe scale lift fan transport aircraft model fNASA-TM-![=622841 ' H73-32975 Fluid mechanics of hole tone whistle desiqned as efficient producer of discrete frequency sound H73-33170 ABRODYHABIC STALLING Design, development, and evaluation of automatic departure prevention system and stall inhibitor for A-7 aircraft fAD-7647671 H73-31972 ABRODIHAHICS Aircraft aerodynamics problems covering slender body theory, atmospheric turbulence and boundary layers, wind tunnel contractions, radiator blocks, vortex induced oscillations, etc A73-4469Q A comparison of the overall and broadband noise characteristics of full-scale and model helicopter rotors, A73-45264 ABBOELASTICIir Calculation of the deformations of a propeller blade in fliqht ''••'• A73-43724 AEROHAOTICAL EIGIHBBBIHG Fabrication techniques for 11 alloys in aerospace applications, discussing hot forming, electron beam and diffusion welding under vacuum and stress relaxation annealinq A73-43911 Banaqement and control of commercial fliqht test programs. A73-44057 Management and control of military and commercial fliqht test programs at Bell Helicopter Company. A73-44058 Air Force Prototype Program management. A73-44061 The role of a military flight test engineer in test management, A73-44062 The capabilities of army test facilities. A73-44064 Naval test and evaluation- capabilities for aircraft, emphasizing organizational relationships A73-44066 ABBOHAOTICS Research Aviation Facility collected aircraft data processing, merging and enhancement problems, software development and future resource requirements A73-45088 Economic evaluation of aircraft and spacecraft fJPBS-601041 H73-32907 ABBOSFACB BHGIHBBRIHG Economic evaluation of aircraft and spacecraft [ JPRS-601041 H73-32907 AFTBRBDRIIHG Fliqht tests of modified F-106 aircraft to determine installation effects of two aft nnderwinq nacelles housing afterburning J-85 enqines [HASA-TB-X-714391 H73-31959 Influence of combustion chamber, compressor, and afterburner confiquration on static performance of two-cycle turbojet engines with high bypass ratio H73-33756 AIR BREATHING EHGIHES Hypersonic wind tunnel tests of air breathing engines : H73-32158 Combustion process for airbreathing propulsion using fixed geometry ramjets N73-32626 AIB CABGO Land-air-sea intermodal cargo container movement procedures and equipment design standardization to meet air transportability requirements [ASHB PAPER 73-ICT-301 A73-43493 Dirigible airship design, operations, payloads, cargo transportation and surveillance applications A73-44223 Proceedings of conference on air transport industry with emphasis on economics, market demand, airlines regulation, and international transportation policy - Vol. 2 CHASA-CB-1356351 N73-32875 Analysis of economic factors involved in air cargo operations and air cargo market development H73-32881 Analysis of factors involved in developing market for air cargo services H73-32882 Analysis of air freight rate problems to define roles of Civil Aviation Board and domestic air carriers H73-32883 Research project to determine factors involved in expansion of air freight traffic and prospects for future expansion H73-32884 Application of airships to air transportation, noting cost effectiveness H73-32991 AIB COOLIH6 Thermodynamics of an air-cooled gas-turbine stage A73-43733 The problem of extrapolating test data on the efficiency of turbine-blade coolinq to actual conditions A73-43741 1-3 MB FLO" SOBJBCT XBDBX AIB FLOB Emissions from and within an Allison J-33 comlmstor, II --The effect of inlet air temperature, A73-43327 Beasucement of flov parameters in nidspan double-circular-arc section of stator in subsonic flow and comparison with conputed performance rHASA-TH=D-74251 H73-31932 Shock wave pattern and stability in axial flov supersonic compressor asinq sinnlated rotating cascade test facility H73-32196 lerodynaoic desiqn of inlet stage for two-stage compressor and performance comparison for axial, mixed flow, and centrifugal stage configurations fHASA-CR-120943] H73-32610 Characteristics of low speed air flow over slender, sharp edged delta wing at various angles of attack and effects on longitudinal and lateral stability H73-32922 Characteristics of aerodynamic noise generated by interaction of airstream with flap surface to show location and control of noise sources H73-32963 Relationship between distribution of outflow of acoustic energy over let boundary and far-field intensity CNASA-TN-D-72691 H73-33181 Pressure drop in air flow isothermally across bank of helically wound, L-type fin tubes tPB-220315/61 H73-33229 AIB IBTAKBS Experimental investigation of large scale, two dimensional, mixed compression inlet system fNASA-TH-D-74451 H73-31928 Adjustable airfoil for reversable cowl flap inlet thrust augmentation CHASA-CASE-ARC-10754-11 H73-32624 Characteristics of variable geometry high Bach inlet concepts to reduce let engine noise on subsonic, long range commercial aircraft fHASA-CS-1344951 H73-33748 AIB BATI6ATIOB The development of civil air navigation in the People's Republic of China -'Agreements with other states as well as the tasks and the position of the China Civil Aviation Corporation /CAAC/ A73-45346 AIB FIBACT 'Air piracy' and the latest work of ICAO on this subject A73-45345 AIB POUOTIOH Potential of hydrogen fuel for future air transportation systems- rASBE PAPEB 73-ICT-1041 A73-43499 Research prelects to determine effects of exhaust products from aircraft operating in stratosphere on global and local climatic conditions tUCRL-513361 B73-32296 Effect of inlet air humidity on exhaust gas emissions of nitrogen oxides in gas turbine combustor fNASA-TH-D-73961 N73=32822 AIB TO AIB BISSILBS Infrared signatures of high performance let aircraft and evaluation of air to air missile effectiveness fSLA-73-52711 873-33929 AIB TRAFFIC Public air transportation service needs for nonurban areas, considering low traffic density problem, operational requirements and future trend fASHE PAPER 73-ICT-721 A73-43t98 Effects of transition from conventional to guiet takeoff and landing air traffic, noting introduction of microwave ILS and area navigation rHBB-OH-05-73-01 H73-32525 International civil aviation organization for air traffic forecasting and airport development H73-32865 Proceedings of conference on air transport industry with emphasis on economics, market demand, airlines regulation, and international transportation policy - Vol. 2 tHASA-CB-1356351 1173-32875 Organization, responsibilities, and functions of Civil Aeronautics Board in determining award of air routes to air lines H73-32880 AIB TRAFFIC COBTBOL BAFBC test facilities. A73-44063 Aviation law development regarding ATC influence on legal liability for aircraft accidents, analyzing controller error influence on liability determination A73-45444 numerical analysis of curved approach paths and landing sequence for multiple aircraft using same terminal facilities to provide maximum system performance H73-31935 Analysis and simulation of intermittent positive control of air traffic by fully automated ground facility H73-32511 Evaluation of air traffic control beacon alphanumeric system for automatic operation in low density airport towers and terminal facilities fFAA-HA-73-541 H73-32516 Air traffic control evaluation to determine feasibility of combining smaller aircraft into gaps on flow of normal traffic to increase effectiveness of terminal facilites fFAA-AFS-500-11 ' H73-32517 Performance and environmental tests of Rational Air Space Enroute Stage air traffic control system fFAA-HA-73-551 H73-32518 Air traffic control problems created by introduction of large nusbers of STOL aircraft into high density terminal area H73-32956 Development and characteristics of 4-D guidance system for traffic control of STOL aircraft operating in congested areas H73-32957 Systems analysis of problems created in terminal area by application of short takeoff aircraft for providing high speed, short haul air transportation service H73-32958 Evaluation of large screen display for automated oceanic air traffic control applications TFAA-HD-73-751 N73-33568 Operational evaluation of ARTS 2 radar alphanumeric display subsystem fFAA-NA-73-771 H73-33569 Restructuring of oceanic air traffic control airspace Inrisdictional boundaries in presence of satellite system fFAA-HD-73-591 H73-33570 Computer model of Los Angeles, California air traffic control situation to predict conditions expected by 1982 fAD-7651531 H73-33571 AIB TRABSPOBTATIOB Land-air-sea intermodal cargo container movement procedures and egnipment desiqn standardization to meet air transportability reguirements fASHE PAPER 73-ICT-301 A73-43493 Public air transportation service needs for nonurban areas, considering low traffic density problem, operational reguirements and future trend fASHE PAPER 73-ICT-721 A73-43498 Short takeoff and landing /STOL/ aircraft technology developments for high density air transport, discussing lift system, handling, airfoil design, acoustics and operating economics A73-4352C Dirigible airship design, operations, payloads, cargo transportation and surveillance applications A73-40223 The translantic charter policy of the Onited states, A73-44575 Economics, traffic demand, and community acceptance of short haul air transportation system in California Corridor - Vol0 1 CHASA-CR-1146341 N73-32842 A-4 SDBJBCI XIDBl AIBCB1FT DBSIGB Economic factors, financial management, prodnction and marketing for air transport industry fBASA-CB-1356301 B73-32808 Federal Government participation in development of OS air transportation system B73-32850 Harketinq and cost effectiveness in air transportation economics 873-32855 Economic efficiency in pricinq of air transport services H73-32856 Demand factors in air transportation marketinq B73-32863 Analytical forecasting methods for air passenqer traffic 873-32860 Patterns of behavior of airlines and air travellers in air transportation network and effects on nse of satellite airports H73-32876 Airport establishment and operation with emphasis on reqional planning, social factors, and economic forces H73-32877 Procedures for conducting air traffic forecasts vith emphasis on socio-economic and demoqraphic characteristics of population B73-32879 Orqanization, responsibilities, and functions of Civil Aeronautics Board in deternining award of air routes to air lines H73-32880 Analysis of economic factors involved in air cargo operations and air cargo market development H73-32881 Analysis of factors involved in developing market for air cargo services 873-32882 Analysis of air freight rate problems to define roles of Civil Aviation Board and domestic air carriers N73-32883 Evaluation of new forms of air transport service for improving short haul air travel market B73-32887 Federal policy establishing guidelines for OS participation in international air transportation services H73-32902 Improving air transportation to low density population reqions fNASA-CB-11 H4801 , H73-32905 Proceedinqs of conference on short takeoff and landing aircraft to determine aerodynamic characteristics and short haul transportation applications CHASA-SP-3201 873-32930 Analysis of short-haul air transportation requirements to include aircraft development programs, economic factors, and environmental considerations N73-32935 Technical and economic aspects of airship transportation fDLB-HITT-72-171 H73-32989 Application of airships to air transportation, notinq cost effectiveness H73-32991 Use of energy in transportation and implications for future fP-5^251 S73-33921 . 1IBB08BB BQOIFBBIT Land-air-sea internodal carqo container movement procedures and equipment design standardization to Beet air transportability requirements r»SRB PAPEB 73-ICT-301 A73-03093 Annual variations of Garda Lake surface teooerature nsinq airborne bolometric equipment and earth based infrared video equipment Cm-STB-231 H73-32298 Diqital synchronization of airborne collision avoidance systems rDGtB-PAPEH-73-P121 H73-32319 AIBBOBBB/SPACBBOBBB COHPOTBES Airborne computer role in diqital fliqht control systems, notinq systems model, man machine '"terface, and inteqration N73-32982 AIBCBAFT Aviation law development reqardinq ATC influence on leqal liability for aircraft accidents, analyzing controller error influence on liability determination A73-05000 Statistical analysis of aircraft accidents occurring in OS Civil Aviation during calenadar year 1972 --Issue 5 [HTSB-BA-73-71 873-31902 Aircraft accident involving Boeinq 707 aircraft following aborted takeoff at Kennedy International Airport, Bew York, on 13 August, . 1972 tBTSB-AAH-73-71 873-31903 Analysis of flight crew errors contributing to aircraft accidents on p-3 and F-4 aircraft for improved air safety [AD-7608681 B73-31979 Test data and description of nnsymnetrical crash analysis computer program for improved helicopter structural crashworthiness analytical and design techniques -Vol..2 [AD-764986] B73-31986 Computer program and mathematical model for . predicting dynamic response of helicopter .in accident involving vertical and lateral impact tAD-7609851 B73-32996 AIBCBAFT AHTBBHAS Dielectric lightweight aircraft radar antenna array fAD-760685] 873-32131 AIRCBAFT CABBIBHS The translantic charter policy of the United States. A73-00575 AIBCBAPT COHPABTHBHTS Dynamic buckling of an azially compressed cylindrical shell with discrete rings and stringers. A73-00377 Besearch and development projects concerning fire hazards in aircraft cabins and design of aircraft compartments to provide greater passenqer snrvivability rFAA-BD-73-106] B73-32972 AIRCBAFT COBPIGOBATIOBS Airport runway and taxiing surfaces modifications for heavy and supersonic aircraft demonstrated by aircraft static and dynamic landing loads and physical dimensions A73-05199 Theory for predicting sonic boom intensity and techniques for sonic boom suppression fFAA-BD-73-0 1 B73-31900 Bozzle geometry and forward velocity effects on noise for CTOL enqine-over-vinq concept fBASA-TH-X-710531 H73-33702 AIBCBAFT COBTBOL Design of mnltivariable adaptive model following control systems. A73-03288 Closed loop linear control system synthesis possibility under condition of incomplete information on state vector with application to aircraft longitudinal motion A73-40329 Total In-Flight Simulator for X-22A aircraft based on variable stability-and-control system concept for reliability design A73-05153 Blectronic display devices in aircraft control, noting pilot activation and VTOL control rDLH-HITT-72-00] H73-32998 Extrapolation predictive displays for manual path and position control of VTOL aircraft 873-33000 AIBCBAPT DBSZSI On the application of a new version of lifting surface theory to nonslender and kinked wings.. 173-03210 Designing a slender-ving-tvpe cantilever plate under conditions of unsteady creep A73-0372B On problems of fliqht over an extended angle-of-attack range, A73-00692 i-S AIBCBAFT BHGIHBS SUBJECT IIDBX F-14 replacement for Phantom aircraft for escort missions, fleet defence, interdiction and close support, discassinq airborne refuelling capability and composite materials applications A73-44695 A study to determine the feasibility of a lov sonic boon supersonic transport, rilSA PAPBE 73-1035] A73-44863 Application of short takeoff aircraft for short haul air transportation with identification of critical technology, economics, and social viability rHASA-CB-135481] H73-31941 Procedure for evaluating relative economic value of technology factors affecting design, configuration, and operation of hypersonic cruise transport rHASA-CH-22861 H73-31953 Design parameters for optimal cost/cruise performance of subsonic jet transport N73-32853 Analysis of short-haul air transportation requirements to include aircraft development programs, economic factors, and environmental considerations H73-32935 Objectives and findings of study to determine applicability of short takeoff aircraft for short-hanl air transportation systems H73-32936 Economic and environmental aspects of short takeoff aircraft used for short-haul air transportation systems H73-32937 Short takeoff aircraft technology development related to requirements for expanded and improved short-hanl air transportation system capabilities H73-32938 Characteristics and performance of piloted simulator for application as research tool in design and development of experimental aircraft H73-32955 Program plan to develop criteria for airworthiness standards applied to short takeoff aircraft used as transport service H73-32959 AIBCHAFT EHGIHBS Technological change measurement methodology for cost and production estimates vith application to aircraft turbine engine development A73-44219 Lov fregnency noise generation within aircraft gas turbine engine core portion, discussing sources prediction, model and full scale engine tests, and future technology fAIAA PAPEE 73-10271 A73-44858 AC starter generator featuring variable-to-eonstant freguency conversion by cycloconverters as switching device for use vith aircraft engines A73-45154 Aircraft gas turbine engines with single crystal blades to avoid conventional casting grain boundary weakness and premature damage A73-45155 Bam air turbine vith hydraulic pitch change servo regulated speed as emergency power source for aircraft control in event of main engine failure A73-45475 Research projects to determine effects of exhaust products from aircraft operating in stratosphere on global and local climatic conditions fOCBL-513361 H73-32296 Rind tunnel tests to determine aerodynamic loads on flap systems behind engines and vibration modes of flap system H73-32945 Design and development of quiet, clean propnslion systems for short takeoff aircraft vith emphasis on engine noise reduction H73-32961 Analysis of jet engine noise to show sources of noise, noise spectra, and use of laminates and composite materials for noise reduction H73-32962 Selection criteria and characteristics of gniet, clean propulsion systems for use vith short takeoff aircraft H73-32967 Computer program for evaluating techniques to improve aircraft engine response systems for application to long range commercial aircraft [HASA-CB-134496] H73-32977 Investigations of HT-S/PHB-PI composites for applications to advanced aircraft engines CHASA-TH-1-714591 H73-33502 AIBCBAFI EQOIPHEHT Aircraft accident involving Boeing 707 aircraft following aborted takeoff at Kennedy International Airport, Hew York, on 13 August, 1972 rBTSB-AAB-73-7] H73-31943 Besearch and development-projects concerning fire hazards in aircraft cabins and design of aircraft compartments to provide greater passenger snrvivability fFAA-BD-73-1461 H73-32972 Systems analysis of avionics and aircraft equipment for search and rescue helicopters to determine cost effective improvements = Vol, 7 rAD-7649141 H73-33381 Equipment for removing silver crazing on aircraft glass rAD-764972) H73-33510 AIBCBAFT FUELS Potential of hydrogen fuel for future air transportation systems. fASHE PAPEB 73-ICT-1C4] A73-43499 AIBCBAFT IHDDSTHI Production forecasting for aircraft manufacturer H73-32872 AIBCBAFT IRSTBOHBHTS Performance tests of hemispherical flow-direction sensor mounted on F-104 aircraft to develop Hacb number position error calibration curve fNASA-TN-D-74611 H73-31956 Logic and design procedures for multifunction mode switching controls in jet aircraft cockpits tAD-7646171 H73-32141 AIBCBAFT LAHDIHG Optimal landinq flare control of aircrafts vith sensitivity consideration, A73-43284 Numerical analysis of curved approach paths and landing seguence for multiple aircraft using sane terminal facilities to provide naximum system perfornance H73-31935 Flight paths for short takeoff aircraft landing approach consistent with pilot preference passenger comfort, and microwave landing system limitations fHASA-TH-D-7298] H73-31949 Display devices for short takeoff aircraft landing tDGLB-PAPEB-73-038] N73-31961 Flight control for steep approach landing rDGLB-PAPBB-73-027] H73-31962 Flight control problems of steep approach landing with direct lift control, exemplified by HFB-320 aircraft rDGLB-PAPBB-73-0241 B73-31965 Cockpit layouts in view of new landing approach methods fHBB-DH-07-73-01 H73-31966 Automatic flight control system for curved flight path profiles fDGLB-PAPEB-73-0301 H73-31970 Computerized simulation of DC-8 aircraft during landing approach under wind shear conditions fAD-764697] H73-31975 Development and characteristics of air cushion landing system for remotely piloted vehicles fAD-7647741 H73-31985 Digital computer-generated contact analog landing display tAD-7647641 H73-32162 Evaluation of approach and landing performance of inertial navigation system with Hainan filter installed in CV-340 aircraft fHASA-TH-D-73021 873-32515 Aircraft landinq problems under low visibility weather conditions fDGLB-PAPEB-73-0151 H73-3252C A- 6 SUBJECT IIDBI AIBCBAFT SAFBTT Description of sector-Tacan and DBS-supported instrument landing systems fDGLB-73-019] H73-32523 Coipatible ILS, using microwave frequencies, and precision ILS, using antenna arrays, as improved standard instcament landinq svstess rDSLB-PAPBB-73-018] H73-32524 Flight simulation to determine aanaal control of flight path and airspeed for approach and landing of powered lift let short takeoff aircraft H73-32949 Pilot activation in automatic landing by display devices H73-32999 Meteorological and weather effects on aircraft landings and flights along air lanes and stratospheric wind effects on supersonic transports fJPBS-601141 H73-33522 Determination of visibility slant range when landing aircraft in radiation fog H73-33523 AIBCBAFT HAIJTBHAICE Application of radiation technology and equipment for nondestructive analysis of commercial aircraft structures during aircraft maintenance periods H73-33579 AIRCRAFT BOISE Short takeoff and landing /STOL/ aircraft technology developments for high density air transport, discussing lift system, handling, airfoil design, acoustics and operating economics A73-43520 The effects of modulated blade spacing on static rotor acoustics and performance- fAIAA PAPEB 73-1P2C1 A73-44852 Multiple pure tone noise generation and control, fAIAA PAPER 73=10211 A73-44853 Inlet geometry and axial Hach number effects on fan noise propagation fAIAA PAPEB 73-1P221 A73-44854 Turbofan engine core noise prediction and measurement, considering sources from flow passage obstructions, combustion chamber and turbine noise due to interaction with upstream turbulence TATAR PAPEE 73-1?26l A73-44857 Mechanisms of externally blown flap noise, fAIAA PAPEB 73-10291 A73-44859 Comparison of aircraft noise measured in flight test and in the NASA Ames 10" by 80-foot wind tunnel. TAIAA PAPEB 73-101171 A73-44871 f. comparison of the overall and broadband noise characteristics of full-scale and model helicopter rotors A73-45264 Maplin airport planning history, noise reduction features and government surveys, noting future air traffic trends and planning alternatives A73-45373 Aircraft noise reduction alternatives for operational aircraft, noting noise generation upstream of final nozzle, reengining, refanning and suppressor technigues A73-45374 Calculation procedures for predicting noise-time histories and noise contours for various types of aircraft CHASA-CB-1146191 H73-31945 Computer programs for predicting the noise-time histories and noise contours for five types of aircraft rNASA"CP-11465ni H73-31946 AIBCRAFT PBBFORHAVCE Potential of hydrogen fuel for future air transportation systems: TASME PAPEfi 73-ICT-1041 A73-43499 Takeoff and landing performance characteristics and field length requirements for let short takeoff transport aircraft with full span, externally blown flaps rNASA=TN-D-7Uft1l H73-31939 Kind tunnel tests to determine low speed characteristics of large scale•model of F-14A aircraft with emphasis on high lift configuration stability rNASA-TM-X-622441 N73-3194Q Mathematical model for real tine simulation of tilt rotor aircraft to evaluate aircraft performance and handling qualities CHASA-CR-114601] H73-31947 Flight test of structural mode control system installed in XB-70•aircraft to deteraine effectiveness of system under turbulent conditions f HASA-TH-B-7420] . H73-31950 Stability and control characteristics of XB-70 - aircraft at airspeeds op to Hach 3.0 and addition of lateral bobweight as auxiliary stabilization device fHASA-TH-I-29331 H73-31958 Botary wing aircraft steep instrument approach limits fHBB-OD-101-73-0] H73-31969 Design, development, and evaluation of automatic departure prevention system and stall inhibitor for A-7 aircraft tAD-764767] . H73-31972 Pilot rating of fighter aircraft in precision heading task using mathematical model for predicting aircraft performance fAD-764695] H73-31973 Mathematical model for predicting pilot rating of aircraft in pitch tracking under gust conditions fAD-764698] H73-31976 Flight simulation to determine manual control of flight path and airspeed for approach and landing of powered lift jet short takeoff aircraft H73-32949 Characteristics and performance of piloted simulator for application as research tool in design and development of experimental aircraft 1173-32955 Effect of artificial longitudinal stability on aircraft performance, based on control configured vehicle concept H73-32986 AIBCBAFT PBODOCTIOI Analysis of factors affecting future of commercial aircraft development to show effects on overall airline operations H73-32900 AZBCBAFT RELIABILITY Management and control of flight test programs at U.S. Army Aviation Systems Command. A73-44054 Program plan to develop airworthiness standards ' for STOL aircraft. A73-44994 Program plan to develop criteria for airworthiness standards applied to short takeoff aircraft used as transport service H73-32959 AIBCBAFT SAFETY DSA government and industry efforts on aircraft midair collision avoidance systems technology advancement, comparing cost effectiveness between airborne and ground based options TASMB PAPER 73-ici-49] A73-43495 •Air piracy1 and the latest work of ICAO on this sublect A73-45345 Bam air turbine with hydraulic pitch change servo regulated speed as emergency power source for aircraft control in event of main engine failure A73-45475 Program plan to develop criteria for airworthiness standards applied to short takeoff aircraft used as transport service N73-32959 Electrified kerosene and gasoline aviation fuel during passage through pipes and filters of fuel tank reservoir fAD-7649411 H73-33740 Relationships between performance, safety, cost, and schedule parameters to generate program models for total space program fNASA-CR-135903] H73-33919 Relationships between performance, safety, cost, and schedule parameters to generate program models for total space program tHASA-CB-135902] H73-33920 A-7 AIBCBAPT SPECIFICATION SUBJECT IHDBI AIBCBAFT SPECIPICITIOHS F-14 replacement foe Phantom aircraft for escort •lesions, fleet defence, interdiction and close support, discussing airborne refuelling capability and composite materials applications 173-49695 AIBCBAPT STABILITY. 1 study of a fluidic open loop damping flight stability augmentation system, 173-43396 Total In-Plight Simulator for X-22A aircraft based on variable stabilityand-control system concept for reliability design 173-45153 Flight test of structnral mode control system installed in XB-70 aircraft to determine effectiveness of system tinder turbulent conditions CHASA-TH-D-7420] H73-3.1950 Stability and control characteristics of IB-70 aircraft at airspeeds op to Bach 3.0 and addition of lateral bobveight as auxiliary stabilization device tHASA-TB-X-29331 H73-31958 Jet aircraft flight tests for stability derivative determination comparing various measuring techniques rBH7G-PB«T-73-121 H73-31971 Computer program for predicting pilot rating of pitch stability of T-33 aircraft under vertical turbulence conditions ClD-7646961 R73-31974 Computerized simulation of DC-8 aircraft during landing approach under wind shear conditions fAD-7646971 B73-31975 Hatheoatical model for predicting pilot rating of aircraft in pitch tracking under gust conditions flD-7646981 H73-31976 Development and evaluation of active control system to provide ride smoothing on short takeoff aircraft H73-32951 Requirements of flight control systems with regard to aircraft stability and attitude control rDLB-HITT-72-051 H73-32978 Nonlinear feedback control concepts for variable stability aircraft K73-32979 Effect of artificial longitudinal stability on aircraft performance, based on control configured vehicle concept H73-32986 Effects of artificial aircraft stability control on damping, and static stability recovery by controllers H73-32987 Design of pitching axis control system for aircraft with artificial stability H73-32988 1IBCB1PT SIBOCTOBES The effect of variable environment temperature on heat transfer in extended surfaces. A73-43296 Environmental effects on fracture resistant and biaxial fatigue design of aircraft structures, 173-43811 Icoustic fatigue resistance of aircraft structures at elevated temperatures. [1111 PIPES 73-994) 173-44B29 B and D efforts for various aircraft construction materials, considering steels, alloys and fiber-containing laminates 173-45198 1IBCB1PT TIBBS Design regnirements and characteristics of toroidal, continuous vonnd aircraft tire i; 10-7648881 H73-31977 1IBCB1PT flKBS Sound generation by wake cutting. tllll P1FBB 73*10191 173-44851 Analysis of ranSon motions of vortex elements , behind aircraft wing and design of vortex arrays to reduce wake-vortex to snail aircr&ft fBm-TH-X-623041 H73-32976 1XBIOXL PBOJIL1S Short takeoff and landing /STOL/ aircraft technology developments for high density air transport, discussing lift system, handling, airfoil design, acoustics and operating economics 173-43520 1IBPOILS Broadband noise generation by aerofoils and axial flow fans, fllll P1PEB 73-10181 173-44850 Sound generation by wake cutting. fllll PIPES 73-10191 173-44851 Some results from tests in the B1E high Reynolds number two-dimensional test facility on shockless and other airfoils. 173-44995 Designing axial compressor airfoils with camber lines of arbitrary shape flD-7651651 B73-32636 AIBFBABBS Application of reliability analysis to aircraft structures sub-|ect to fatigue crack growth and periodic structural inspection riD-764775] H73-32383 Application of radiation technology and egnipment for nondestructive analysis of commercial aircraft structures during aircraft maintenance periods H73-33579 AIBLIBB OPBBATIORS lir carrier and general aviation airports system planning with emphasis on economic analysis of operation, ownership and finance fASBE PAPEH 73-ICT-33] 173-4349C Dual lane runway configuration design and operational characteristics investigation by real tioe computer simulation for solution to airport capacity problem flSHE PIPES 73-ICT-611 173-43496 Public air transportation service needs for nonurban areas, considering low traffic density problem, operational regnirements and future trend flSKB PIPER 73-ICT-721 173-43498 The translantic charter policy of the United States, 173-44575 The development of civil air navigation in the People's Republic of China - Agreements with other states as well as the tasks and the position of the China Civil Aviation Corporation /CllC/ 173-45346 Aircraft noise reduction alternatives for operational aircraft, noting noise generation upstream of final nozzle, reengining, refanning and suppressor technigues A73-45374 Liability and insurance in international air traffic A73-45443 Application of short takeoff aircraft for short haul air transportation with identification of critical technology, economics, and social viability fNlSA-CB-1354811 N73-31941 Aircraft landing problems under low visibility weather conditions tDGLB-PAPBB-73-0151 H73-3252C' New type of instrument landing systems, according to ICAO regnirements rDSLB-PAPEfi-73-0111 K73-32522 Economics, traffic demand, and community acceptance of short haul air transportation system in California Corridor - Vol. 1 fNASA-CB-1146341 N73-32842 Forecast model for predicting economic factors involved in short haul air transportation in California Corridor - Vol. 2 fSASA-CR-114634(1)1 H73-32843 Hethod for estimating airline operating costs H73-32851 Formula for computing operating cost of turbine powered transport aircraft H73-32852 Differential pricing policy in airline operations B73-32857 Competition effects on air transportation industry economics N73-32858 Financial sources and airline operations N73-32859 Estimated costs for additional aircraft in air transport industry B73-3286C Financial requirements of air transportation industry H73-32861 1-8 SUBJECT IIDBZ AIRSHIPS Economic market structure of airline industry. B73-32869 Functional models for airline operations H73-32870 Excess capacity in airline industry and operational and financial problems H73-32871 Production forecasting for aircraft manufacturer H73-32872 Consumer marketing for airline industry B73-32873 Concepts of expanding airline marketing strategies B73-32874 Proceedings of conference on air transport industry vith emphasis on econoaics, market demand, airlines regulation, and international transportation policy - Vol 2 mSA=CR-135635l B73-32875 Patterns of behavior of airlines and air travellers in air transportation network and effects on use of satellite airports H73-32876 Development and operation of cost accounting system for airport functions to show application of data processing equipment 873=32878 Procedures for conducting air traffic forecasts with emphasis on socio-economic and demographic characteristics of population B73-32879 Organization, responsibilities, and functions of Civil Aeronautics Board in determining award of air routes to air lines B73-32880 Analysis of economic factors involved in air cargo operations and air cargo market development H73-32881 Analysis of factors involved in developing market for air cargo services B73-32882 Analysis of air freight rate problems to define Coles of Civil Aviation Board and domestic air carriers B73-32883 Research prelect to determine factors involved in expansion of air freight traffic and prospects for future expansion 873=32884 Analysis of commuter air transportation services to define problems and identify methods for improvements in cost effective operations B73-32885 Operation of low cost local air 'service carriers to show methods for improving transportation services 873=32886 Evaluation of new forms of air transport service for improving short haul air travel market H73-32887 Actions by Civil Aviation Board to regulate and improve commuter air transportation services B73-32888 Characteristics of Federal regulation of airline operations and predictions for type and extent of future regulation B73-32899 Actions of Civil Aviation Board with respect to monopolies and mergers of domestic airline operations 873=32895 Advice and assistance provided by Civil Aviation Board to State Department on matters of international air transportation policy B73-32899 Analysis of factors affecting future of commercial aircraft development to show effects on overall airline operations B73-32900 Federal policy establishing guidelines for DS participation in international air transportation services B73-32902 International air transportation policy and application of policy to scheduled and chartered airline services H73-32903 Economic and environmental aspects of short takeoff aircraft used for short-haul air transportation systems B73-32937 Short takeoff aircraft technology development related to reguirerents for expanded and improved short-haul air transportation system capabilities H73-32938 Short haul aircraft operations in terminal area with concurrent conventional aircraft operations to show methods for improved utilization of facilities B73-32953 Systems analysis of problems created in terminal area by application of short takeoff aircraft for providing high speed, short haul air transportation service B73-32958 Restructuring of oceanic air traffic control airspace lurisdictional boundaries in presence of satellite system fPAA-HD-73-59] H73-33570 AIBPOBT PLABBII6 Air carrier and general aviation airports system planning with emphasis on economic analysis of operation, ownership and finance fiSBB PAPER 73-ICT-33] A73-43494 Dual lane runway configuration design and operational characteristics investigation by real time computer simulation for solution to airport capacity problem fASHB PAPER 73-ICT-61] A73-43496 The role ground transportation can play in the airport site selection process. riSHB PAPER 73-ICT-70] A73-43497 Airport runway and taxiing surfaces modifications for heavy and supersonic aircraft demonstrated by aircraft static and dynamic landing loads and physical dimensions A73-45199 Baplin airport planning history, noise reduction features and government surveys, noting future air traffic trends and planning alternatives A73-45373 Regional airport planning in Germany C BGLH-PAPEH-73-0351 B73-32159 Patterns of behavior of airlines and air travellers in air transportation network and effects on use of satellite airports B73-32876 Airport establishment and operation with emphasis on regional planning, social factors, and economic forces B73-32877 AIRPORT TOIBHS Evaluation of air traffic control beacon alphanumeric system for automatic operation in low density airport towers and terminal facilities fPAA-BA-73-5K1 B73-32516 AIBPORTS Airport establishment and operation vith emphasis on regional planning, social factors, and economic forces B73-32877 Development and operation of cost accounting system for airport functions to show application of data processing equipment B7 3-32878 Procedures for conducting air traffic forecasts with emphasis on socio-economic and demographic characteristics of population B73-32879 AIRSHIPS Dirigible airship design, operations, payloads, cargo transportation and surveillance applications A73-44223 Technical and economic aspects of airship transportation ' fDI.B-BITT-72-171 B73-32989 History of Zeppelin airships to show uses for civil and military purposes H73-32990 Application of airships to air transportation, noting cost effectiveness B73-32991 Flexible airship manufacturing 873-32992 1-9 M.LOCUXOIS SOBJBCT IBOBI Technical aspects of airship manufacture and ground and loading operations H73-32993 lerodynamic drag and lift of airships, noting boundary layer control by suction H73-32994 Technical conditions for airship development, noting veight redaction, propulsion system perfornance, and maneuverability improvement H73-32995 1LLOC1TIOIS Differential pricing policy in airline operations H73-32857 JLOHIHDH 1LLOTS Improvement of the corrosion-fatigue strength of aluminum alloys by exposure of the medium to a •agnetic field £73-43466 The effect of composition changes on the fracture toughness of an 11-Zn-Hg-Cu-Hn forging alloy, 473-44025 Hot forging of aluminum alloy structural parts C1D-7646181 N73-32384 1BGIB 0? 1TTJCK On problems of flight over an extended angle-of-attack range:, 173-44692 Aerodynamic characteristics of flov around elliptic cones at large angles of attack I" 10=764 9451 H73-32209 1HGUL1B HOHBHTDH Havier-Stokes egaation forinlation in parabolic coordinates for flow in trailing vortex, obtaining asymptotic expansions for stream function and angular momentum 173-43205 1HHD1L V1BIITIOBS annual variations of Garda Lake surface temperature using airborne bolonetric egnipment and earth based infrared video equipment riPS-STE-23J H73-32298 1BBUL1B PLOW Effect of a slipstream on the acoustic radiation of ultrasonic annular lets 173-45358 Jet noise emission and reduction by secondary cold annular flo* for SST and military aircraft H73-32543 1HTEHH1 1BB1TS Dielectric lightweight aircraft radar antenna array f 10-7646851 H73-32131 1PPB01CH Longitudinal stability of Boeing 707 aircraft during steep approach, for noise reduction rDGLB-PlPBB-73-0231 H73-31963 Boise reducing approach and takeoff profiles for • short takeoff aircraft f BBB-OH-06-73-01 H73-31968 lutomatic flight control system for curved flight path profiles tD6LB-PlPEB-73-0301 B73-31970 Flight control display device for producing curved approach profiles in microwave instrument landing systems tDGLH-PlPBR-73-016] H73-32526 IPPROICH COITBOL Flight paths for short takeoff aircraft landing approach consistent with pilot preference passenger comfort; and microwave landing system limitations tHlSl-TH-D-72981 H73-31949 Flight control for steep approach landing fDGLR-PlPBB-73-0271 H73-31962 Pilot display for monitoring of automatic steep approach fDGLH-PlPBB-73-0311 H73-31964 Cockpit layouts in view of new landing approach methods . rHBB-DH-07-73-01 H73-31966 lircraft landing problems under low visibility weather conditions fDGLR-PlPBB-73-0151 H73-32520 Hew type of instrument landing systems, according to IC10 regnirements rDGLR-PlPBB-73-0111 H73-32522 Compatible ILS, using microwave fregnencies, and precision ILS, using antenna arrays, as improved standard instrument landing systems rDGLB-PlPBB-73-018] H73-32524 Plight simulation to determine manual control of flight path and airspeed for approach and landing of powered lift let short takeoff aircraft H73-32949 Flight simulation to determine effectiveness of , head-up display for improving glide-slope tracking performance during steep visual approach of short takeoff aircraft H73-32952 1BB1 H1TIG1TIOH Effects of transition from conventional to guiet takeoff and landing air traffic, .noting introduction of microwave ILS and area navigation [BBB-UB-05-73-01 H73-32525 1SPBCT B1TIO On the application of a new .version of lifting surface theory to nonslender and kinked wings. 173-43210 1STHPTOTIC SBBIBS Bavier-Stokes eguatioc formulation in parabolic coordinates for flow in trailing vortex, obtaining asymptotic expansions for stream function and angular momentum 173-43205 1THOSPBEBIC BODHD1BI L1IBB lircraft aerodynamics problems covering slender body theory, atmospheric turbulence and boundary layers, wind tunnel contractions, radiator blocks, vortex induced oscillations, etc 173-44690 1THOSPHBBIC PHYSICS Research projects to determine effects of exhaust products from aircraft operating in stratosphere on global and local climatic conditions COCBL-513361 H73-32296 1THOSPHEBIC TURBOLBHCB lircraft aerodynamics problems covering slender body theory, atmospheric turbulence and boundary layers, wind tunnel contractions, radiator blocks, vortex induced oscillations, etc 173-44690 atmospheric turbulence near tropopause over mountainous terrain N73-33525 1TOBZZIHG Some comments to mathematical interpretation of performance characteristics of let engine combustion chambers. 173-45381 1TTITODB COBTBOL X study of a fluidic open loop damping flight stability augmentation system. 173-43396 Regnirements of flight control systems with regard to aircraft stability and attitude control f DLH-HITT-72-051 K73-32978 10TOH1TIC COHTBOL Pilot display for monitoring of automatic steep approach tDGLR-PlPBR-73-0311 N73-31964 Similitude theory for design optimization of automatic control systems for aircraft gas turbine engines flD-7646831 N73-32631 10TOH1TIC FLIGHT COBIBOL lutomatic flight control system for curved flight path profiles fDGLR-P1PER-73-030} H73-3197C IUTOH1TIC L1HDIHG COBTBOL Optimal landing flare control of aircrafts with sensitivity consideration. 173-43284 Electronic display devices in aircraft control, noting pilot activation and VTOL control fDLH-HITT-72-041 ' H73-32998 Pilot activation in automatic landing by display devices H73-32999 1DTOH1TIC PILOTS Specification of thrust control system for lirbus 1 300 B, tested in Boeing 707 873-32981 1VIOHICS H1FEC test facilities. 173-44063 Applications of spread spectrum communications technigues to avionics -systems .--• • ' H73-32058 1-10 SDBOBCT inn C1B1D1 Systems analysis of avionics and aircraft equipment for search and rescue helicopters to determine cost effective improvements - Vol. 7 flD-7649141 B73-33381 COBPBBSSXOB LOiOS Dynamic buckling of an axiallT compressed cylindrical shell vith discrete rinqs and strinqers, 173-40377 IXIIL FLOS Shock vave pattern and stability in axial flov supersonic coipressor using simulated rotating cascade test facility H73-32196 Desianinq axial coipressor airfoils vith camber lines of arbitrary shape riD-7651651 S73-32636 1SI1L FLOI TOHBIBBS Total pressare loss distribation in viscous gas flov throaqh annular cascades of axial flov compressors, examining three diiensional flov effects on boundary layer development 173-44916 1XI1L STHBSS Environmental effects on fracture resistant and biaxial fatigue desiqn of aircraft structures, 173-43811 1XISIRHBTBIC F101 Classification of methods for solving the direct problem of axisymmetric flov calculation in turboenqines 173-43736 B B-70 1IBCB1FT Flight test of structural node control system installed in XB-70 aircraft to determine effectiveness of systea under turbulent conditions rHlSl-TH-D-74201 S73-31950 Stability and control characteristics of XB-70 aircraft at airspeeds up to Hach 3,0 and addition of lateral bobveiqbt as auxiliary stabilization device fHlSl-TH-I-29331 B73-31958 B1I10DT Proceedings of symposiam to determine requirements and configurations of emerqency election systems for helicopter crevs flGlBD-lR-621 B73-31954 BILL BE1BXRGS Fatigue life tests of ball motion and sliding friction in arched outer race ball bearing under thrust load fBHSl-TH-X-714421 B73-32375 B1SB PBBSSORB t. theoretical and experimental study of sound attenuation in an annular duct, ClIAt P1PBB 73-10051 173-44838 BB1BIBGS Study and calculation of the vibrations of a rotatinq rotor vith allovance for clearances in the bearinqs 173-43725 BBLL 1XBCB1PT Ranaqenent and control of military and commercial flight test proqrans at Bell Helicopter Company, 173-44056 BBIDXIG BOHBSTS Determination of the deflections and stresses in a small-aspect-ratio vinq by the displacement method 173-43723 BBBDXBG VIBB1TIOB Natural, fleiural and torsional vibration frequencies and modes for helicopter tail rotor blades 173-45245 BIBLXOGB1PHIBS Bibliography of technical reports of helicopter enqines and rotary vinqs r&D-7649<301 H73-31981 BIT SIBCBBOIIZ1TIOB Digital synchronization of airborne collision avoidance systems fDGI.R-PiPBR-73-0121 B73-32519 BL1DB TIPS Capacitive method for measuring blade tip clearance in runninq turbocompressors B-72'001 H73-32628 BO-105 HBLICOPTBB Desiqn optimization and testing of flight control systems for light helicopters, applied to BO-105 helicopter H73-32985 BODIBS OF BB70LOTIOV Universal equations for the laminar boundary layer on a body of revolution in oblique flov 173-45529 Determination of the impulses and moments imparted by shock vaves to bodies of revolution 173-45542 BODY-BIBG COBFIGOB1TIOBS Bind tunnel tests to determine aerodynamic characteristics of three oblique, high aspect ratio ving and body combinations at Hach numbers betveen 0.60 and 1.40 tBlSl-TH-X-62256] H73-32926 BOBIIG 707 IIBCH1FT lircraft accident involving Boeing 707 aircraft following aborted takeoff at Kennedy International lirport. Hew York, on 13 luqust, 1972 [HTSB-11B-73-7] B73-31943 Lonqitudinal stability of Boeing 707 aircraft during steep approach, for noise reduction rDGtH-PlPBB-73-023] B73-31963 Specification of thrust control system for lirbns 1 300 B, tested in Boeing 707 B73-32981 BOBIBG 727 1IBCB1FT Flight tests of Boeing 727 aircraft to determine effects of modifications on reduction of aerodynamic noise CF11-BD-72-40-VOL-3) B73-32971 BOOBD1BT L1YBB COBIBOL lerodynamic drag and lift of airships, noting boundary layer control by suction B73-32994 BODBD1BT L1T2B BQUJTI08S Universal equations for the laminar boundary layer on a body of revolution in obligue flov 173-45529 BOOBD1BI L1IEB FLOB Flov interference betveen supersonic intake and airframe to show three dimensional separation of boundary layer B73-32194 Turbulent shear stress profiles in boundary layer flov at sine vave pressure perturbations B73-33194 BOOBD1BT L1TBB SEP1B1IIOB Flov interference betveen supersonic intake and airframe to shov three dimensional separation of boundary layer H73-32194 BB1ZIBG lluminum brazed titanium honeycomb sandwich structure -•1 nev system. 173-44000 BB010B1BO 1 comparison of the overall and broadband noise characteristics of full-scale and model helicopter rotors. 173-45264 BUFFBTIBG lerothermodynamic study of air cushion vehicles buffeting noting dynamical stability, nonlinear behavior, and similitude lav [BT-33-1973] B73-32933 BUBBIBO B1TB Burning rate studies of fuel air mixtures at high pressures. 173-45162 Fuel combustion rate and turbulent diffusion induced self ignition in pulsejet engine combustion chamber from schlieren photography and pressure distribution measurements 173-45377 C1B1D1 Pilot knee election clearances for Canadian military aircrafts r DC IE H-93 6] B73-31938 1-11 CAITILBVBB PLATES SUBJECT IBDBI C1BTILEVBB PUTBS Designing a slender-sing-type cantilever plate under conditions of unsteady creep A73-43728 CAPACITY Excess capacity in airline industry and operational and financial problems H73-32871 C1SCIDB FLO" Total pressure loss distribution in viscous gas flow through annular cascades of axial flov compressors, exaaining three diiensional flov effects on boundary layer development A73-44916 Shock nave pattern and stability in axial flov supersonic compressor using simulated rotating cascade test facility H73-32196 CAVITATIOB FLOW Approximate calculation of the cavitation flov past low-aspect-ratio sings A73-45540 CAVITY RESOBATOBS PDF 8/1 data acquisition and averaging program for synchronous hot-vire measurements in month of flov excited cavity resonator fAD-7648511 N73-32357 CBBTBIFV6AL POBPS Synchronized operation of a positive-displacement gear pump and a vane pump vithin the lubricant oil delivery system of a let engine 473-43742 CBBIOB On the process of precipitation in Hg=Ce alloy, 473-44155 CBBTXFICATIOB Hanagement and control of flight test programs of the Hestern Region F44, 473-44053 Hanagement and control of flight test programs at D. S<, Army Aviation Systems Command, A73-44054 CBABBBL FLOV Piecevise-one-dimensional models of supersonic combustion and psendoshock in a channel 473-44702 CHBHICAL COBPOSXCTOI The effect of composition changes on the fracture toughness of an Al-Zn-Hg-Cu-Hn forging alloy. 473-44025 CHBHICAL PBOPEBTIBS Physical and chemical properties of JP-4 let fuel for 1972 fAD-7646901 B73-32605 CIRCUIT PBOTBCTIOI Fixed installation ground electrical pover supply system for aircraft service, discussing motor-alternators, plant control cubicles, selector and busbar svitchboxes and fault protection devices A73-45156 CIRCOLAB POLABIZATIOI Improvement of instrument landing systems vith respect to multipath propagation effects and surface reflections fDGLH-PAPBB-73-0171 H73-32521 CITIL AVIATIOH Public air transportation service needs for nonnrban areas, considering lov traffic density problem, operational reguirements and future trend fASHB PAPEB 73-ICT-721 A73-43498 The development of civil air navigation in the People's Republic of China - Agreements vith other states as veil as the tasks and the position of the China Civil Aviation Corporation /CAAC/ 473-45366 Statistical analysis of aircraft accidents occurring in OS Civil Aviation during calenadar year 1972 - Issue 5 rHTSB-BA-73-71 173-31942 International civil aviation organization for air traffic forecasting and airport development H73-32865 Application of airships to air transportation, noting cost effectiveness B73-32991 Acgnisition of conditions of icing on modern civil transport aircraft from flight data H73-33528 CLBARABCBS Pilot knee ejection clearances for Canadian military aircrafts [DCIEH-936] .- H73-31938 Capacitive method for measuring blade tip clearance in running tnrbocompressors rDLB-FB-72-401 H73-32628 COAHD4 EFFECT Rind tunnel tests of high harmonic circulation control rotary ving model to show instruments regnired and data acgnisition procedures T4D-7653201 H73-31984 Bind tunnel tests of large scale subsonic let transport vith upper surface bloving flap system for lift angaentation rHASA-TH-X-622961 H73-32973 COCKPITS Cockpit layouts in viev of nev landing approach methods [HBB-DH-07-73-0] H73-31966 Logic and design procedures for multifunction mode svitching controls in let aircraft cockpits fJD-7646171 H73-32141 COLLISIOH AVOIDAHCB DS& government and industry efforts on aircraft midair collision avoidance systems technology advancement, comparing cost effectiveness betveen airborne and ground based options fASHE PAPEB 73-ICT-49] 473-43495 Digital synchronization of airborne collision avoidance systems fDGLB-PAPEB-73-0121 H73-32519 Evaluation of large screen display for automated oceanic air traffic control applications fFAA-HD-73-751 H73-33568 COHBAT Remotely piloted vehicle /RPV/ for reconnaissance, electronic varfare systems, target acguisition, veapon delivery, air-air combat and different combinations A73-45399 COHBUSTIBLB FLOI Piecevise-one-dimensional models of supersonic combustion and psendoshock in a channel A73-44702 COHBDSTIOH CHABBBHS Emissions from and vithin an Allison J-33 combustor, II - The effect of inlet air temperature, 473-43327 Tnrbofan engine core noise prediction and measurement, considering sonrces from flov passage obstructions, combustion chamber and turbine noise due to interaction vith upstream turbulence TAIAA P4PBB 73-10261 473-44857 Some comments to mathematical interpretation of performance characteristics of let engine combustion chambers. 473-45381 Combustion process for airbreathing propulsion using fixed geometry ramjets H73-32626 Emission abatement in aircraft gas turbine combnstor vith lov mass emissions fAD-7649871 573-32638 Forvard velocity effects on let noise vith dominant internal noise source fBASA-TH-1-714381 H73-32968 Influence of combustion chamber, compressor, and afterburner configuration on static performance of two-cycle turbojet engines vith high bypass ratio H73-33756 COBBHSTIOH BFFICIEBCT Some comments to mathematical interpretation of performance characteristics of 1st engine combustion chambers. A73-45381 COBBDSTIOB PRODUCTS Burn-up of the high temperature products of incomplete combustion in a supersonic flov by a second injection of oxidizer A73-45076 A-12 SUBJECT ITOBI COBFBBBBCBS Besearch prelects to determine effects of eihaast products fron aircraft operating in stratosphere on global and local climatic conditions fOCBL-513361 H73-32296 Sensory odor tests of exhaust from turbo-fet enqine coibnstor operating at simulated idle conditions fSASA-TB-1-714291 H73-32613 COBBOSTIOI VIBB1TIOB Boise generation by turbulent combustion, discussing sound power, spectral content, enclosure effect, and importance in tnrbopropnlsion system core engine noise rilli PAPBB 73-10231 A73-44855 COBHEBCI1L HBCBiFT Management and control of commercial flight test programs: A73-44057 Development of OS commercial air transport industry H73-32849 Federal Government participation in development of OS air transportation system H73-32850 Proceedings of conference on air transport industry with emphasis on economics, market demand, airlines regulation, and international transportation policy - Vol. 2 rNASA-CH=1356351 H73-32875 Analysis of factors affecting future of commercial aircraft development to show effects on overall airline operations H73-32900 Application of radiation technology and equipment for nondestructive analysis of commercial aircraft structures during aircraft maintenance periods N73-33579 COBHOBICATIOB BQUIPBBHT Applications of spread spectrum communications techniques to avionics systems H73-32058 COBHOBICiTIOH SATELLITES Kims, prospects, organization, and financing of EDBOSAT S,A. N73-33930 COHBOBIC1TIOH TBEOBY Applications of spread spectrum communications techniques to avionics systems H73-32058 COBPBTITIOB Competition effects on air transportation industry economics N73-32858 COBPOSITE BATEBIiLS F-1« replacement for Phantom aircraft for escort missions, fleet defence, interdiction and close support, discussing airborne refuelling capability and composite materials applications A73-44695 Toward reliable composites - An examination of design methodology £73-45144 Adhesive bonding of structures and composite materials on advanced turbofan engines H73-32470 Investigations of HT-S/PBB-PI composites for applications to advanced aircraft engines fNASA-TH-I-714591 H73-33502 COHPBBSSIBLB FLUIDS Acoustic velocity and sound propagation differences in incompressible and compressible fluids related to Bach cone formation and sonic boon effects A73-05269 COBPBBSSOB BL1D2S Investigations of HT-S/PHR-PI composites for applications to advanced aircraft engines rNASA-T(l-X-7ia591 H73-33502 COBPPBSSOH BOTOBS Effects of blade tip clearance and leading edqe sweepback of compressor rotor blades on indncer performance and blade pressure loading fNASA-CR-727121 H73-31930 COBPOTATIOH Formula for computing operating cost of turbine powered transport aircraft H73-32852 COBPOTBB PBOGBABS Besearch Aviation Facility collected aircraft data processing, merging and enhancement problems, software development and future resource requirements A73-45088 Computer program for analyzing characteristics of parachute-payload system during deployment and tralectory B73-31936 Computer programs for predicting the noise-time histories and noise contours for five types of aircraft CHASA-CB-1146501 B73-31946 Test data and description of nnsymmetrical crash analysis computer program for improved helicopter structural crashworthiness analytical and design technigues -Vol. 2 TAD-7649861 B73-31986 POP 8/1 data acquisition and averaging program for synchronous hot-wire measurements in month of flow excited cavity resonator [AD-764851] B73-32357 Computerized design of axial compressor [AD-7647331 B73-32633 Computer program for desiqn of axial compressor [AD-7647341 B73-32634 Computer program for evaluating techniques to improve aircraft engine response systems for application to long range commercial aircraft fNASA-CR-1344961 H73-32977 Computer program and mathematical model for predicting dynamic response of helicopter in accident involving vertical and lateral impact CAD-7649851 B73-32996 Computer solutions for potential and viscous flov calculations for engine inlets [HASA-TB-X-714571 H73-33184 COBPOTBBIZED DBSI6B Computerized design of axial compressor [AD-7647331 H73-32633 Computer program for design of axial compressor . fAD-764734] H73-32634 COBPDTBBIZBD SIBOLATIOB Dual lane runway configuration design and operational characteristics investigation by real time computer simulation for solution to airport capacity problem fASHE PAPEB 73-ICT-61] A73-43496 Computerized simulation of DC-8 aircraft during landing approach under wind shear conditions [AD-764697] B73-31975 Computerized simulation of interactions of VTOL aircraft taking off from or landing on deck of . ship moving in irregular or random seaway fAD-764865} H73-31980 Computer model of Los Angeles, California air traffic control situation to predict conditions expected by 1982 [AD-765153] N73-33571 COBPBBEHCES Sensitivity, adaptivity and optlmality; Proceedings of the Third Symposium, Iscbia, Italy, June 18-23, 1973. A73-43277 Society of Flight Test Engineers, National Symposium, 3rd, Arlington, Tex., September 11-14, 1972, Proceedings. A73-44052 Proceedings of symposium to determine requirements and configurations of emergency election systems for helicopter crews rAGlBD-AE-62] B73-31954 Proceedings of conference on air transport industry with emphasis on economics, market demand, airlines regulation, and international transportation policy - -Vol. 2 CH1SA-CH-1356351 B73-3287S "Proceedings of conference on short takeoff and landing aircraft to determine aerodynamic characteristics and short haul transportation . applications fBASA-SP-3201 H73-32934 Beqnirements of flight control systems with regard to aircraft stability and attitude control [DLB-BITT-72-05] H73-32978 Technical and economic aspects of airship transportation fDLE-BITT-72-17] B73-32989 1-13 COBGBBSS SUBJECT IIDBX Electronic display devices in aircraft control, noting pilot activation and VTOL control tDLB-HITT-72-OIIJ H73-32998 Tnrbo1et and turbine engine performance optimalization by configuration variations, and auxiliary turbine engine converter problem [DLB-HITT-73-05] H73-33755 COB6BBSS Congressional bearings on causes and implications of impending shortages of gasoline, beating oil, diesel fuel, let fuel, and electricity H73-33928 COBICAL BODIES Wind tunnel tests to determine static and dynamic stability coefficients for circular cone vitb various nose bluntness configurations [AD-765168] H73-3193K Aerodynamic characteristics of flov around elliptic cones at large angles of attack riD-7649!»51 B73-32209 COBSTBOCTIOB HATBBIAIS low-pressure prepregs as structural material for light-construction designs A73-H0887 8 and D efforts for various aircraft construction materials, considering steels, alloys and fiber-containing laminates A73-H5198 Research and development prelects concerning fire hazards in aircraft cabins and design of aircraft compartnents to provide greater passenger snrvivability rFAA-BD=73-1tt6l H73-32972 COBSOHEBS Consumer marketing for airline industry B73-32873 Concepts of expanding airline marketing strategies H73-3287K COBT&IBBBS land-air-sea intermodal cargo container movement procedures and equipment design standardization to meet air transportability requirements f&SHB PAPER 73-ICT-30] A73-»3«93 COBTBACT HABA6EHEHT Management and control of flight test programs at D.S> Army Aviation Systems Command, A73-HU05I1 Hanagement and control of flight test programs of the Baval Air Systems Command, A73-4Q056 Hanagement and control of military flight test programs at McDonnell Douglas St, Louis, Bissouri- A73-44059 Flight test programs management and control, considering weapon systems performance tests relative to contractual requirements, personnel allocation and supporting facilities A73-W060 COBTBOL TBBOBT Sensitivity, adaptivity and optimality; Proceedings of the Third Symposium, Ischia, Italy, June 18-23, 1973, A73-43277 Closed loop linear control system synthesis possibility under condition of incomplete information on state vector with application to aircraft longitudinal motion A73-H4329 COOLI16 performance evaluation of model energy separators rAD-7665851 H73-32381 COOLIBG STSTEHS Thermodynamics of an air-cooled gas-turbine stage A73-H3733 The problem of extrapolating test data on the efficiency of turbine-blade cooling to actual conditions A73-43761 COBE FLOW Rake development on models of elliptic, rectangular, swept and delta planforns when plunged in water fABC-CP-1238] B73-32932 COBBOSIOH BESISTABCB Improvement of the corrosion-fatigue strength of aluminum alloys by exposure of the medium to a magnetic field A73-43Q66 Aluminum brazed titanium honeycomb sandwich structure -4 new system. A73-40000 COST A1ALTSIS Development and operation of cost accounting system for airport functions to show application of data processing equipment B73-32878 Operation of low cost local air service carriers to show methods for improving transportation services H73-32886 Optimization of control and damping system for fighter aircraft with gnadratic cost function B73-32980 Relationships between performance, safety, cost, and schedule parameters to generate program models for total space program FBASA-CB-135903] B73-33919 Relationships between performance, safety, cost, and schedule parameters to generate program models for total space program rHASA-CB-135902] 873-33920 COST EFFECTIVBBBSS OSA government and industry efforts on aircraft midair collision avoidance systems technology advancement, comparing cost effectiveness between airborne and ground based options fASHE PAPEB 73-ICT-49] A73-»3«95 Design parameters for optimal cost/cruise performance of subsonic let transport H73-32853 Principles of functional economic analysis N7 3-32854 Differential pricing policy in airline operations H73-32857 Financial sources and airline operations N73-32859 Application of airships to air transportation, noting cost effectiveness N73-32991 COST BSTIHATES Technological change measurement methodology for cost and production estimates with application to aircraft turbine engine development A73-44219 Hethod for estimating airline operating costs N73-32851 Formula for computing operating cost of turbine powered transport aircraft N73-32852 Estimated costs for additional aircraft in air transport industry B73-32860 CBACK PBOPAGATIOH Fatigue crack growth retardation after single-cycle peak overload in Ti-6Al-4V titanium alloy, A73-438P9 Application of reliability analysis to aircraft structures snblect to fatigue crack growth and periodic structural inspection fAD-7647751 H73-32383 CBACKIH6 (FBACTOBIBG) Fracture analysis of surface- and through-cracked sheets and plates. A73-43813 CBEEP PBOPBBTIBS Designing a slender-wing-type cantilever plate under conditions of unsteady creep A73-W3728 CBEBP BDPTOBE STBBBGTB Aluminum brazed titanium honeycomb sandwich structure - A new systes, A73-44000 CBITICAI LOADIBG Fatigue crack growth retardation after single-cycle peak overload in T1-6A1-4V titanium alloy, A73-43809 CBITICAL VELOCITY Increasing the critical rotational speed of the tail rotor drive shaft in SB-1 and SH-2 helicopters A73-45195 CBTOGBBICS Flight tests of cryogenically cooled hygrometer (AD-7647181 H73-32354 A-14 SOBJBCT IIDBI OIUBIC STABILITY. CRYSTAL LATTICES Determination of the temperature fields of turbine disks and blades, using .irradiated diamond indicators 173-44291) CT-340 1IBCH1FT Evaluation of approach and landing performance of inertial navigation system with Kalian filter installed in CV-340 aircraft fBlSl-TH-D-7302] B73-32515 CYCLIC LOADS Fatigue crack growth retardation after sinqle-crcle peak overload in Ti-6Al-4V titanium alloy, 173-43809 CTLIHDBICAL SHELLS Dynamic buckling of an axially compressed cylindrical shell vith discrete rinqs and stringers, A73-44377 DATA iCQOISITIOH Rind tunnel tests of high harmonic circulation control rotary wing model to shov instruments required and data acquisition procedures flD-7653201 H73-31984 Dill H1BAGBHBHT Research Aviation Facility collected aircraft data processing, merging and enhancement problems, software development and future resource reguirements 173-45088 D1T1 PROCESSING Research Iviation Facility collected aircraft data processing, merging and enhancement problems, software development and future resource reguirements 173=45088 D1T1 PROCBSSIBG BQUIFHEBT Development and operation of cost accounting system for airport functions to show application of data processing egnipment R73-32878 DC 8 AIBCBAFT Computerized simulation of DC-8 aircraft during landing approach under wind shear conditions riD-764697] H73-31975 DECISIQB H1KIHG Utilization of decision and value theory concepts by helicopter pilots to plan attacks N73-33565 DELTA WIBGS Characteristics of low speed air flow over slender, sharp edged delta wing at various angles of attack and effects on longitudinal and lateral stability 1173=32922 On the effects of viscous interaction for a flat delta wing at incidence ritBC-CP=1237l H73-32931 Transonic wind tunnel tests to determine effects on flutter of aerodynamic interference between pairs of closely spaced delta wings fS1S&-CB-23311 H73-33887 DEH1BD (BCOBOHICS) Demand factors in air transportation marketing H73-32863 DI1HOHDS Determination of the temperature fields of turbine disks and blades, using irradiated diamond indicators 173-44294 DIFFEBBHTIAL BQOATIOBS The prediction of instabilities of linear differential equations with periodic coefficients URC-B/B-3713] H73-33518 DIFFOSBES Effect of inlet conditions on optimal shape of diffuser based on theory of potential flow of fluid in channels rtD-7655771 B73-33230 DIPFOSIOH BBLDIIG Fabrication technigues for Ti alloys in aerospace applications, discussing hot forming, electron bean and diffusion welding under vacuum and stress relaxation annealing 173-43911 DILOTIOI Dispersion and dilation of jet aircraft exhaust at high altitudes tHlSl-TH-1-71451] H73-33743 DIBBCT LIFT COITBOLS Flight control problems of steep approach landing vith direct lift control, exemplified by HFB-320 aircraft FDGLR-PAPBB-73-024] H73-31965 DISPBBSIBG Dispersion and dilation of let aircraft exhaust at high altitudes miSl-TH-1-71451) H73-33743 DISPLII DBVICBS Display devices for short takeoff aircraft landing [DGLB-P1PBB-73-038] H73-31961 Pilot display for conitoring of automatic steep approach fDSLB-PiPBS-73-031] 873-31964 Cockpit layouts in view of new landing approach methods rHBB-OH-07-73-0) H73-31966 Fliqht control display device for producing curved approach profiles in microwave instrument landing systems fDGLB-PAPEB-73-016] H73-32526 Electronic display devices in aircraft control, noting pilot activation and VTOL control fDLB-HITT-72-04] H73-32998 Pilot activation in automatic landing by display devices H73-32999 Extrapolation predictive displays for manual path and position control of VTOL aircraft H73-33000 Evaluation of large screen display for automated oceanic air traffic control applications fFll-BD-73-75] H73-33568 Operational evaluation of 1BTS 2 radar alphanumeric display subsystem CF11-B1-73-77] H73-33569 DISTAHCE HB1SDBIHG BQDIFHBHT Description of sector-Tacan and DDE-supported instrument landing systems [DGLB-73-019] B73-32523 Capacitiye method for measuring blade tip clearance in running turbocompressors rDLB-FB-72-401 H73-32628 DISTOBTIOH Stability effects of steady state circumferential distortions of inlet total temperature and pressure fBlSl-TH-1-714311 H73-32614 DO-31 1IBCB1FT DO-31 aircraft integrated flight control system for vertical velocity regulation in gliding, noting signal processing regnirements N73-32983 DOPFLBB EFFECT •ing tip vortex measurements with laser Doppler velocimeter fHASl-CB-124444] N73-32924 DB16 BBDUCTIOB Aerodynamic drag and lift of airships, noting boundary layer control by suction B73-32994 DDCTED FLOW 1 difference theory for noise propagation in an acoustically lined duct with mean flow. fAIll PIPES 73-1007] 173-44840 Theoretical studies of sound emission from aircraft ducts, C1I11 PIPER 73-1012) 173-44844 Finite difference theory of noise propagation in tnrbofan engine ducts CH1S1-TH-D-7339] S73-33744 DIB1HIC BBSPOBSB Dynamic response of short haul aircraft to gust loads fFOK-K66] H73-31960 DTB1HIC STABILITY lerothermodynamic study of air cushion vehicles buffeting noting dynamical stability, nonlinear behavior, and similitude lav TBT-33-1973) B73-32933 1-15 DIH1BIC STBOCTDBAL ABALTSIS SOBJECT ZHDBX DYBAHIC SIBOCT0BAL AH11ISIS Dynamic backlinq of an axially compressed cylindrical shell with discrete rings and stringers A73-44377 ECOHOHIC AHALYSIS &ir carrier and general aviation airports system planning with eophasis on economic analysis of operation, ownership and finance f&SHB PAPEB 73-ICT-331 A73-43494 Forecast model for predicting economic factors involved in short haul air transportation in California Corridor -:Vol, 2 f NASA-CB-114634 (1) 1 H73-32843 Economic factors, financial management, production and marketing for air transport industry fBASA-CB-1356341 B73-32848 Principles of functional economic analysis H73-32854 Marketing and cost effectiveness in air transportation economics H73-32855 Economic efficiency in pricing of air transport services R73-32856 Competition effects on air transportation industry economics B73-32858 Economic risk analysis for propeller STOL transport market H73-32866 Characteristics of Federal regulation of airline operations and predictions for type and extent of future regulation N73-32894 Analysis of factors affecting future of commercial aircraft development to show effects on overall airline operations H73-32900 ECOBOBIC PSCTOBS Procedure for evaluating relative economic value of technology factors affecting design, configuration, and operation of hypersonic cruise transport fNASA-CE-22861 • N73-31953 Economic market structure of airline industry N73-32869 Analysis of short-haul air transportation requirements to include aircraft development programs, economic factors, and environmental considerations H73-32935 Technical and economic aspects of airship transportation • rDLB-HITT-72-171 H73-32989 ECOBOHICS Airport establishment and operation vith emphasis on regional planning, social factors, and economic forces B73-32877 Analysis of economic factors involved in air cargo operations and air cargo market development H73-32881 Analysis of factors involved in developing market for air cargo services R73-32882 Economic evaluation of aircraft and spacecraft fJPBS-601041 B73-32907 EIOEH7ALDB3 Stability of a potential vortex vith a non-rotating and rigid-body rotating top-hat let core, A73-05309 BJKTIOH SEATS Pilot knee election clearances for Canadian military aircrafts fDCIBH-9361 B73-31938 Proceedings of symposium to determine requirements and configurations of emergency election systems for helicopter crevs [AGABD-AB-621 B73-319S4 EJBCTOBS Static tests of cylindrical ejectors using afterburning turbolet gas generators f HASA-TH-X-525651 B73-32622 ELASTIC BABS Vibrations of turbo-jet-engine components containing structural dampers of the type of sandvich rods A73-43735 ELASTIC DEFOEHATIOB Calculation of the deformations of a propeller blade in flight A73-43724 BLBCTBIC FIELDS Electrified kerosene and gasoline aviation fuel during passage through pipes and filters of fuel tank reservoir fAD-7649411 B73-33740 BLECTHIC POIBB SUPPLIES Fixed installation ground electrical power supply system for aircraft service, discussing motor-alternators, plant control cubicles, selector and busbar switchboxes and fault protection devices A73-45156 ELBCTBIC SWITCHES Fixed installation ground electrical power supply system for aircraft service, discussing motor-alternators, plant control cubicles, selector and busbar switchboxes and fault protection devices A73-45156 BLBCTBIC 1IBE Thermal aging of plastic insulated silver-plated copper aircraft electrical wire rAD-764731] H73-32135 ELECTBICAL BESISTIVITI On the process of precipitation in Hg-Ce alloy. A73-14155 BLECTBICITI Congressional hearings on causes and implications of impending shortages of gasoline, heating oil, diesel fuel, let fuel, and electricity N73-33928 BLECTBOB BEAH BBLDIHG Fabrication technigues for Ti alloys in aerospace applications, discussing hot forming, electron beam and diffusion welding under vacuum and stress relaxation annealing A73-43911 BIBCTBOBIC COOBTBBHBASDBES Bemotely piloted vehicle /BPV/ for reconnaissance, electronic warfare systems, target acguisition, weapon delivery, air-air combat and different combinations A73-U539S BLLIPTICITI Aerodynamic characteristics of flow around elliptic cones at large angles of attack fAD-7649451 H73-32209 BBEB6T COIVEBSIOB EFFICIBBCI The problem of extrapolating test data on the efficiency of turbine-blade cooling to actual conditions A73-43741 BBBB6I DISSIPATIOB Vibrations of turbolet-engine components containing structural dampers of the type of sandwich rods A73-43735 BBEBGI METHODS Determination of the deflections and stresses in a small-aspect-ratio wing by the displacement method A73-43723 Application of energy concepts for prediction of pavement system performance B73-32153 BBBBGI BBQDIBBHBBTS Dse of energy in transportation and implications for future rP-50251 B73-33921 BHGISB DBSI6B Acoustic investigation of the engine-over-the-wing concept using a D-shape4 nozzle. fAIAA PAPEB 73-10301 A73-44860 Aircraft gas turbine engines with single crystal blades to avoid conventional casting grain boundary weakness and premature damage A73-45155 Similitude theory for design optimization of automatic control systems for aircraft gas turbine engines fAD-7646831 B73-32631 1-16 SUBJECT IIDEI EITERBALLT. BL01B FLIPS Design and development of quiet, clean propuslion systems for short takeoff aircraft with emphasis on engine noise reduction H73-32961 BBGIBE FlILOHB Principal failures of turbines during, turbine engine operation A73-45196 BBGIBE ISLETS Inlet geometry and axial Hach number effects on fan noise propagation, fAIAA PAPER 73-10221 A73-44854 Computer solutions for potential and viscous flow calculations for engine inlets CHASA-TH-1-714571 B73-33184 Characteristics of variable geometry high Hach inlet concepts to reduce let engine noise on subsonic, long range commercial aircraft mASA-CB-134495] B73-33748 BIGIHB BOBITOBIBG IHSTBOHEBTS Dtili?ation of seniartificial thermocouples in gas-tarbine engine tests A73»43743 BBGIBE BOISE Swirling flow effect on let noise suppression based on acoustic field and engine thrust measurements with and without stationary swirl vanes in exhaust nozzle fAIAA PAP28 73-10031 A73-44836 Noise generation by turbulent combustion, discussing sound power, spectral content, enclosure effect, and importance in tnrbopropulsion system cope engine noise fAI!lA PAP3B 73-10231 A73-44855 Turbofan engine core noise prediction and measurement, considering sources from flow passage obstructions, combustion chamber and turbine noise due to interaction with upstream turbulence fAIAA PAPER 73-10261 A73-44857 Low freguency noise generation within aircraft gas turbine engine core portion, discussing sources prediction, model and full scale engine tests, and future technology fAIAA PAPBB 73-10271 A73-54858 Aircraft noise reduction alternatives for operational aircraft, noting noise generation upstream of final nozzle, reengining, refanning and suppressor techniques A73-45374 Acoustic tests of supersonic tip speed fan with acoustic treatment and rotor casing slots and its performance in reducing engine noise THASA-CP.-13B5511 . H73-32608 Boise comparison of two STOL pressure ratio fans with 15 and 02 rotor blades rHASA-TH-X-2891] H73-32609 Effect of noise constraints on engine cycle optimization for long"haul transports rnASA=TH-1-714671 H73-32620 Analysis of let engine noise to show sources of noise, noise spectra, and use of laminates and composite materials for noise reduction H73-32962 Characteristics of variable geometry high Bach inlet concepts to reduce let engine noise on subsonic, long range commercial aircraft fNASA-CR-1340951 H73-33748 EIGIHB PABTS Adhesive bonding of structures and composite materials on advanced tnrbofan engines H73-32470 BBGIBB STABTBBS AC starter generator featuring variable-to-constant frequency conversion by cycloconverters as switching device for use with aircraft engines A73-45154 BSGIHE TSSTS Utilization of sealertificial thermocouples in gas«-turbine engine tests A73-43743 Low frequency noise generation within aircraft gas turbine engine core portion, discussing sources prediction, model and full scale engine tests, and future technology fAIAA PAPEE 73-1C271 A73-44858 BJSIIBBBIIG HABAGBHBIT Hanagement and control of flight test programs of the Bestern Begion FAA. A73-44053 Hanaqement of Air Force test and evaluation activities. A73-44055 The role of a military flight test engineer in test management. A73-44062 BBVIBOBBBBT EFFECTS The effect of variable environment temperature on heat transfer in extended surfaces. A73-43296 Environmental effects on fracture resistant and biaxial fatigue design of aircraft structures. _ A73-43811 EBVIBOHBBHTAL LABOBATOBIES HAFEC test facilities. A73-44063 ESVIBOHHEBTAL TESTS Perforoance and environmental tests of Rational Air Space Bnroute Stage air traffic control system tFAA-HA-73-55] H73-32518 EFOZI BESISS Besponse of glass-fiber-reinforced epoxy specimens to high rates of tensile loading.. A73-43385 EQOATIOHS OF BOTIOB Hathenatical model for predicting pilot rating of aircraft in pitch tracking under gust conditions tAD-764698] H73-31976 Egnations of motion formulated to compute transient response of multi-mass flexible rotors rHASA-CR-2300] H73-32374 BQDIPHBBT SPECIFICATIONS Selection criteria and characteristics of quiet, clean propulsion systems for use with short takeoff aircraft B73-32967 ESCAPE STSTBBS Proceedings of symposium to determine requirements and configurations of emergency ejection systems for helicopter crews rAGABD-AB-62] B73-31954 BOBOPBAB SPACE PBOGBABS Aims, prospects, organization, and financing of EDHOSAT So A. B73-33930 EXHAUST GASES Emissions from and within an Allison J-33 combnstor, II --The effect of inlet air temperature. A73-43327 Research prolects to determine effects of exhaust products from aircraft operating in stratosphere on global and local climatic conditions fUCBL-51336] B73-32296 Sensory odor tests of exhaust from turbojet engine combnstor operating at simulated idle conditions fHASA-TH-1-71429 J B73-32613 Exhaust emission measurements on turbojet engine plume at simulated supersonic flight rAD-764717] B73-32632 Emission abatement in aircraft gas turbine combustor with low mass emissions fAD-7649871 B73-32638 Wind tunnel tests to determine aerodynamic loads on flap systems behind engines and vibration modes of flap system B73-32945 EXHAUST BOZZLES Assessment of jets as acoustic shields by comparison of single and multitube suppressor nozzle data fBASA-TH-1-71450] B73-33179 EZBADST SISTEHS Theoretical studies of sound emission from aircraft ducts, TAIAA PAPBB 73-1012] 173-44844 EXTBBIALLT BLOBB FLAPS Bechanisms of externally blown flap noise. fAIAA PAPBB 73-1029] A73-44859 Takeoff and landing performance characteristics and field length .requirements for jet short takeoff transport aircraft with full span, externally blown flaps tBASA-TB-B-74411 B73-31939 i-17 BITBiPOLATIOH SOBJECT IIDEZ Evaluation of low speed flying qualities of short takeoff aircraft with externally blown flap winq or auqmentor winq usinq fliqht simulator rHASA~TH=D-7<*5<»l N73-31951 Aerodynamic and performance characteristics of short takeoff aircraft equipped with externally blown flaps H73-32939 Bind tunnel tests to determine stability and control characteristics of externally blown let-flap confiqurations N73-32940 Hind tunnel tests to determine aerodynamic loads on flap systems behind enqines and vibration modes of flap system N73-329K5 Heasnrement of fluctuatinq surface pressures induced on externally blown flaps by let impinqement and relationship to sonic fatigue of airframes H73-329«6 Pull-scale qround tests of externally blown flap system on F-111 aircraft winq to determine pressure and temperature distributions on undersurface of winq, vane, and flap N73-32947 Simulations of powered-lift STOL transport aircraft with either externally blown flap confiquration or auqmentor winq configuration »73-329«3396 Closed loop linear control system synthesis possibility under condition of incomplete information on state vector with application to aircraft longitudinal motion A73-UP.329 feedback control for rotary winq aircraft steep approach profiles [ HBB-OFE-1021-01 N73-31967 Nonlinear feedback control concepts for variable stability aircraft N73-32979 A-18 SUBJECT INDEX FLIGHT OPTIHIZATIOH FIGHTER AIRCRAFT Pilot rating of fiqhter aircraft in precision heading task using mathematical nodel for predicting aircraft performance UD-76Q6951 N73-31973 Optimization of control and damping system for fighter aircraft with quadratic cost function N73-32980 VAK 191 B V/STOL fighter aircraft nonlinear feedback flight control system for gliding flight phase K73-3298I) FILABEHT elBDIRG Design requirements and characteristics of toroidal, continuous wound aircraft tire fAD-76118881 N73-31977 FINANCIAL HAHAGEHBNT Sir carrier and general aviation airports system planning with emphasis on economic analysis of operation, ownership and finance CASHE P*P?F 73-ICT-331 A73-«3«90 Economic factors, financial management, production and marketing for air transport industry rNASA-ca-13563Hl N73-328H8 Financial sources and airline operations N73-32859 Financial requirements of air transportation industry N73-32861 Bank financing in commercial let aircraft export S73-32862 ?xcess capacity in airline industry and operational and financial problems H73-32871 Analysis of air freight rate problems to define roles of Civil Aviation Board and domestic air carriers S73-32883 FINITE DIFFERENCE THEORY A difference theory for noise propagation in an acoustically lined duct with mean flow TAIAA PAPEP 73-10071 . A73-»lt8H(J Finite difference theory of noise propagation in turbofan engine ducts rn»SA-TN-D»73391 N73-337UB FINITE ELEHBHT HETHOD Theoretical studies of sound emission from aircraft ducts TAI'.A PUPBP 73-10121 A73-B480II FIHS The effect of variable environment temperature on heat transfer in extended surfaces, A73-43296 Pressure drop in air flow isothermally across bank of helically wound, L'type fin tubes rPB-22r315/6l N73-33229 FLiBBABILITY Research and development projects concerning fire hazards in aircraft cabins and design of aircraft compartments to provide greater passenger survivability r?J.A-SD"73-1»61 N73-32972 FLAPS (CONTROL SURFACES) Evaluation of low speed flying qualities of short takeoff aircraft with externally blown flap wing or auqmentor wing using flight simulator r NASA--TN-D' 7^51'1 N73-31951 Ad-justable airfoil for reversable cowl flap inlet thrust augmentation THiSA-CASS-AEC-mSI*-!! N7 3-32620 Flight tests of modified F-1CO aircraft to determine effectiveness of fast-acting flaps as direct=lift--control devices to improve station keeping rNASA'T1'-X"29361 N73-32970 FLAT SDRFACBS On the effects of viscous interaction for a flat delta winq at incidence C"FC-CP-12371 N73-32931 FLEXIBLE BODIES Equations of motion formulated to compute transient response of multi-mass flexible rotors r Nf.SA-C?.-23'>?1 N73-323760 Air Force Prototype Program management, A73-»l!061 The role of a military flight test engineer in test management, f.73-K A73-M025 FREE FLOW A theoretical and experimental study of sound attenuation in an annular duct. f A I A A PAPEE 73-10051 A73-44838 FHEE JETS Comparison of results obtained with various sensors used to measure fluctuating quantities in jets.;' ' ' fAIAA PAPER 73-10131 A73-44867 FBEE 7IBBATIOH Natural, flexural and torsional vibration freguencies and nodes for helicopter tail rotor blades A73-45245 FREIGBT COSTS Analysis of economic factors involved in air cargo operations and air cargo market development N73-32881 Analysis of factors involved in developing market for air cargo services H73-32882 Analysis of air freight'rate problems to define roles of Civil Aviation Board and domestic air carriers ' B73-32883 Research project to determine factors involved in expansion of air freight traffic and prospects for future expansion H73-32884 FRBQOBBCY COHVBBTBES - AC starter qenerator featuring variable-to-constant frequency conversion by cycloconverters as switching device for use with aircraft engines A73-4515H FBBQDBHCY DISTRIBOTIOH Relative frequency of occurrence of different normal accelerations at the center of gravity of aircraft in turbulence URC-R/B-37141 H73-32929 POBL COHBDSTIOB Burning rate studies of fuel air mixtures at hiqh pressures, 173-45162 Fuel combustion rate and turbulent diffusion induced self iqnition in pnloejet engine combustion chamber from schlieren photography and pressure distribution measurements A73-45377 Incendiary vulnerability of dry bays adjacent to let fuel tanks under gunfire r&D-76«7321 S73-32920 Electrified kerosene and gasoline aviation fuel dnrinq passage through pipes and filters of fuel tank reservoir riD-76»9IHl H73-33740 FOIL COHSOaPTXOH . Use of energy in transportation and implications for future fP-5025] H73-33921 A-21 POBL IHJBCTIOH SDBJBCT IHDEI FUBL IHJECTIOH Burn-up of the high temperature products of incomplete combustion in a supersonic flow by a second inlection of oxidizer • . A73-H5C76 FOEL OILS Congressional hearings on causes and implications of impending shortages of gasoline, heating oil, diesel fuel, let fuel, and electricity H73-33928 FOBL TESTS : Burning rate studies of fuel air mixtures at high Pressures A73-H5162 FOEL-IIB BATIO Burning rate studies of fuel air mixtures at high pressures A73-H5162 FDLL SCALE TESTS Noise comparisons from full-scale fan tests at NASA Lewis Pesearch.Center r a i A A PAPBH 73-10171.. . . A73-»»869 Lov freguency noise generation within aircraft gas turbine engine core portion, discussing sources Prediction, model and full scale engine tests, and future technology fAIAA PAPEB 73-10271 A73-4U858 A comparison of the overall and broadband noise i characteristics of full-scale and model helicopter rotors: A73-4526H GAHE TBEOBI Game theory mathematical model for optimal control of glide modes in conflict situation A73-43263 GAS FLOW . Universal equations for the laminar boundary layer . on a body of revolution in obligue flow A73-45529 Flow field over pointed wedges in isoenergetic flow of thermally and calorically perfect gases with nonuniform incident supersonic flow, noting attached shock formation B73-45547 GAS GEBEBATOBS Static tests of cylindrical electors using afterburning turbolet gas generators fNASA-TH-X-525651 N73-32622 GAS TEHPEBATOBE Affect of the circumferential nonuniformity of a tenperature field in front of a turbine on the vibrational stresses in the turbine blades A73-43740 GAS TOBBIHE ENGINES Otilization of semiartificial thermocouples in gas-turbine engine tests A73-JI3743 Determination of the temperature fields of turbine disks and blades, using irradiated diamond indicators A73-44294 Low frequency noise generation within aircraft gas turbine engine core portion, discussing sources prediction, model and full scale engine tests, and future technology fAI!U PAPEF 73-15271 A73-44858 Aircraft gas turbine engines with single crystal blades to avoid conventional casting grain boundary weakness and premature damage A73-H5155 Principal failures of turbines during turbine engine operation A73-45196 Effect of inlet air humidity on exhaust gas emissions of nitrogen oxides in gas turbine • combustor l"HASi=TN-D"73961 N73- 32822 GAS TUHBHBS Thermodynamics of an air-cooled gas-turbine stage £73-83733 Designing axial compressor airfoils with camber lines of arbitrary shape fAD-765165.1 : H73-32636 Emission abatement in aircraft gas turbine . .combustor with low mass emissions rAD-7649871 H73-32638 Turbojet and turbine engine performance optinalization by configuration variations, and auxiliary turbine engine converter problem fDLB-MITT-73-051 N73-33755 GASOLIHB . : Electrified kerosene and gasoline aviation fuel during passage through pipes and filters of fuel tank reservoir . f AD-764941 1 N73-337i'.r Congressional. hearings on causes and implications of impending shortages. of gasoline, heating oil, diesel fuel, let fuel, and .electricity.' * ' S73-33928 GBBHABT Begional airport planning in Germany rDGLR-PAPEB-73-0351 N73-32159 GLASS : Equipment for removing silver crazing on aircraft glass • fAD-76-76ft618l N73-3238I? HOT WORKIRG Fabrication technigues for Ti alloys in aerospace applications; discussing hot forming, electron beam and diffusion welding under vacuum and stress relaxation annealing A73-B3911 HOT- II BE AREROHETBBS PDF 8/1 data acquisition and averaging program for synchronous hot-wire measurements in mouth of flow excited cavity resonator rAD-76»8511 • N73-32357 HDHAR FACTORS BHGIHEEBIRG Pilot knee election clearances for Canadian military aircrafts rDCIEH-9361 N73-31938 Analysis of flight crew errors contributing to aircraft accidents on P-3 and F-n aircraft for improved air safety . rAD-7618681 N73-319"'9 HDHIDITY • Effect of inlet air humidity on exhaust qas emissions of nitrogen oxides in gas turbine combustor • - flIASA-TH-D-73961 ' ' N73-32822 A-23 BYDBAOLIC COHTBOL SUBJECT IHDBX HIDB10LIC COBTBOI Ban air turbine Kith hydraulic pitch change servo requlated speed as emerqency power scarce for aircraft control.in event of main engine failure A73-45475 BIDBOGEH FDELS Potential of hydroqen fuel for future air transportation systems USWS PiPEB 73-ICT-1041 173-431199 BTGBOHETEBS Fliqht tests of cryoqenically cooled hygrometer rAD-76»7181 H73-32354 HIPEBSOHIC AIBCBAPT Design analysis and fabrication of hypersonic wing test structure fNASA CB 127B9(-'1 . N73-33883 HYPBBSOHIC FLOi A theoretical and experimental study of sound attenuation in an annular duct: '. " : rAIJU PAPEB 7-3-10051 A73-44838 Hypersonic flow about a spatial body with an attached shock wave A73-B5172 HTPEBSOHIC SPEED . Procedure for evaluatinq relative economic value of technology factors affecting design, configuration, and operation of hypersonic cruise transport f NASA-CP-22861 N73-31953 HTPBBSOHIC BIHD TOHHELS Hypersonic wind tunnel tests of air breathing engines N73-32158 ICE FOBBATIOI Acquisition of conditions of icing on modern civil transport aircraft from flight data N73-33528 IGHITIOH Fuel combustion rate and turbulent diffusion induced self ignition in pulselet engine combustion chamber from schlieren photography and pressure distribution measurements A73-45377 IB-FLIGBT HOHITOHIHG Total In-Flight Simulator for X»22f. aircraft based on variable stability and-control system-concept for reliability design A73-45153 IBCOHPBESSIBLE FLUIDS Jcoustic velocity and sound propaqation differences in incompressible and compressible fluids related to Hach cone formation and sonic boom effects . A73-45269 IH2BTIAL BAVIGATIOR Evaluation of approach and landing performance of inertial navigation system with Kalman filter installed in CV-31"" aircraft • ri>?.SA-TN=D-73r21 H73-32515 IHFLATABLE STBOCTDBES Design requirements and characteristics of toroidal, continuous wound aircraft tire TAD-7508831 H73-31977 IBFBARED SPECTFA Infrared signatures of high performance let aircraft and evaluation of ait to air missile effectiveness rSLA-73-52711 H73-33929 IHLBT PlOW Pmissions from and within an Allison J-33 combustor. II - The effect of inlet air temperature A73-»3327 Effect of the circumferential nonuniformity of a temperature field in front of a turbine on the vibrational stresses in the turbine blades : 173-43749 wind tunnel teats to determine Clow distribution at inlet locations on aircraft nodel for various aerodynamic configurations and airspeeds r NASA-TN-D-736m H73-31929 Flow interference between supersonic intaXe and airframe to show three dimensional separation of boundary layer .. . • • • H73-32194 Aerodynamic design of inlet stage for two~staqe compressor and performance comparison for axial, mixed flow, and centrifugal stage configurations rHASA-CB- 1209431 873-32610 Effect of inlet conditions on optimal shape of diffnser based on theory of potential flow of fluid in channels fAD-7655771 R73-33230 Characteristics of variable geometry high Bach inlet concepts to reduce jet engine noise on subsonic, long range commercial aircraft rHASA-CB-1344951 H73-33748 IHLET PBBSSDBE Bind tunnel tests to determine flow distribution at inlet locations on aircraft model for various aerodynamic configurations and airspeeds . r BASA-TH-D-736B1 H73-31929 Flow interference between supersonic intake and . airframe to show three dimensional separation of boundary layer H73-3219H IBSIBDHEBI APPBOACH Botary wing aircraft steep instrument approach limits f BBB-OD-101-73-01 H73=31969 IBSTBDBEHT BBBOBS Errors produced by the influence of unsteady heating in strain measurement by wire-type resistance strain gages A73-44292 IBSTBOBBBT LABDIB6 STSTEHS Badio freguency interference tests of VHF omnirange system, localizer, and glideslope receiving equipment to determine geographical separation reguirements - Vol, 2 Book 2 f FAA-BD-73-1-VOL-2-BK-21 N73-32513 Improvement of instrument landing systems with respect to multipath propagation effects and surface reflections f DGLB-PAPER-73-0171 H73-32521 New type of instrument landing systems, according to ICAO reguirements rDGLB-PAPEB=73-011l N73-32522 Description of sector-Tacan and DHE-supported instrument landing systems rDGLB-73-0191 B73-32523 Compatible ILS, using microwave frequencies, and precision ILS, using antenna arrays, as improved standard instrument landing systems fDGLB-PAPSB-73-0181 H73-32524 Effects of transition from conventional to quiet takeoff and landinq air traffic, noting introduction of microwave ILS and area naviqation riJBB-DH-05-73-01 H73-32525 Fliqht control display device for producing curved approach profiles in microwave instrument landinq systems rDGLB=PAPEB-73-0161 H73-32526 IHSTBOBBHTS Development of instrument to measure steady and oscillatory aerodynamic forces on sting-mounted model using forced oscillation technique F ATN-7101 1 B73-33366 IHTAKE SISTEHS Theoretical studies of sound emission from aircraft ducts. FAIAA PAPEB 73-10121 A73-K484D Experimental investigation of large scale, two dimensional, nixed compression inlet system rHASA-TB-D-74H51 H73-31928 Effects of blade tip clearance and leading edge sweepback of compressor rotor blades on inducer performance and blade pressure loading rUASA-CB-727121 H73-31930 Stability effects of steady state circumferential distortions of inlet total temperature and pressure f HiSi-TH-X-7ia31l H73-326H Effect of inlet air humidity on exhaust qas emissions of nitrogen oxides in qas turbine combustor rt!iSA-TH-D-73961 H73-32822 XHTBBR1TXOIIL COOPBBATIOB Program plan to develop airworthiness standards for STOL aircraft. 'Air piracy' and the latest work of ICAO on this subject A73-B53H5 A-24 SOBJECT IBDEX JIT KtXIBG FLOS The development of civil air navigation in the People's Republic of China - agreements with other states as well as the tasks and the position of the China Civil Aviation Corporation/caac/ A73-IJ5366 Liability and insurance in international air traffic A73-1S54U3 International civil aviation organization for air traffic forecasting and airport development N73-32865 advice and assistance provided bv Civil aviation Board to State Department on matters of international air transportation policy N73-32899 aims, prospects, organization, and financing of SOROSAT S,A- H73-33930 IHTBBHATIOHAL TRADE Bank financing in commercial let aircraft export N73-32862 IHVISCID FLOi analysis of inviscid flow field around rectangular wing of finite thickness in supersonic flow N73-32166 ISOTEOPIC TOHBOLEHCE Experimental analysis of nearly isotropic turbulence behind -Jet grid N73=3317l» IT1IY annual variations of Garda Lake surface temperature using airborne bolometric eguipment and earth based infrared video equipment fIFa-STH-231 H73-32298 J=33 EHGIBE Emissions from and within an Allison J-33 combustor II - The effect of inlet air temperature A73-»3327 J-85 EHGIBB Flight tests of modified F-106 aircraft to determine installation effects of two aft anderwing nacelles housing afterburning J-85 engines rHASa-T!1=-X=7in391 K73-31959 JET AIRCRAFT Jet aircraft flight tests for stability derivative determination comparing various measuring technignes rBHVG-FBBT-73-121 N73-31971 Hathematical model for predicting pilot rating of aircraft in pitch tracking under gust conditions rAD-7fB6981 873=31976 Performance evaluation of model energy separators rAD-76«5851 N73-32381 Feasibility study for use of YF-12 aircraft as scientific instrument platform for observing 1970 solar eclipse rNASA-CS-135B92l N73-32735 Bank financing in commercial let aircraft export N73-32862 Dispersion and dilution of let aircraft exhaust at high altitudes rNasa-TH-X'711511 N73-337U3 Infrared signatures of high performance let aircraft and evaluation of air to air missile effectiveness rSLA-73-52711 N73-33929 JET AIRCRAFT BOISE Subsonic and supersonic lets and supersonic suppressor characteristics r a i A A PAPBP. 73-9991 z73-«i»83!! The influence of aerodynamic flow noise in turbofan engines ra iaa PAPSB 73-1M61 A73=ais8i'.8 Acoastic investigation of the engine-over-the-wing concept using a D-shaped nozzle. raiaa PAPER 73» 10301 a73-92C Congressional hearings on causes and implication: s of impending shortages of gasoline, heating oi:1, diesel fuel, let fuel, and electricity N73-3.3928 JET BBGIBES Some comments to mathematical interpretation of performance characteristics of let engine combustion chambers- ' i S73- -, • i i . ', H ,73-329 acousti c power output of subsonic lets, FAiaa PAPER 73-10«2l / A73-l>l!S66 Stability of a potential vortex 'with a •' non-rotating and rigid-body ro.tating 'top-hat 1st core, i Experimental analysis of nearly isotrcjpic turbulence behind let grid ' ' ' •' V73-3317M Relationship between distribution of 'outflow of acoustic energy over let boun;3arv and far-field intensity • rNASA-TN-D-72691 i ' B73-33191 JET IBPISGESEHT. . , . • Measurement of fluctuating surf ace .pressures induced on externally blown flaps; by let impingement and relationship ! to :sonic fatigue of airframes : ,: N73-32?»e JET HIXIBG FLOB > Introduction of the viscous force .sensing fluctuating probe technigue, wij th measurement in the mixing zone of a circular 1 et, i73-»i'863 a-25 , 1ST POHPS SUBJECT IHDEX JUT POHPS Synchronized operation of a positive-displacement dear p u m p and a vane pump within the lubricant oil delivery system of a let enqine 473-K37I12 JP--0 JET FOEL Physical and chemical properties of JP-S let fuel for 19721 f Ari-7658 BABAGBBEHT PLAHBIHG Society of Fliqht Test Engineers, National Symposium, 3rd, irlington, Tex., September 11-14, 1972, Proceedings. 473-44052 Management of Air Force test and evaluation activities, 473=411055 Management and control of flight test programs of the Naval Air Systems Command, 473-44056 Economics, traffic demand, and community acceptance of short haul air transportation system in California Corridor - Vol, 1 ruASA-CP- 1146341 H73-32842 Procedures for conducting air traffic forecasts with emphasis on socio-economic and demographic characteristics of population H73-32879 BABEUVEBABILITY Technical conditions for airship development, noting weight reduction, propulsion system performance, and maneuverability improvement N73-32995 BAHUF4CTDRING Flexible airship manufacturing H73-32992 Technical aspects of airship manufacture and qround and loading operations N73-32993 BASKET RESEARCH Concepts of expanding airline marketing strategies N73-32871' BARKBTING Economic factors, financial management, production and marketing for air transport industry f NASA-CR-1356341 N73-32848 Marketinq and cost effectiveness in air transportation economics N73-32855 Economic efficiency in pricinq of air transport services H7 3-32856 Differential pricing policy in airline operations S73-32857 Demand factors in air transportation market ing N73-32963 Economic risk analysis for propeller STOL transport market N73-32866 Economic market structure of airline industry N73-32869 Consumer marketing for airline industry H73-32873 MATERIALS HANDLIHG Flexible airship manufacturing H73-32992 BATSBIALS SCIENCE Low-pressure prepregs as structural material for liqht-constructioh designs 473-n'4fi87 BATBEMATICAL MODELS Game theory mathematical model for optimal control of qlide modes in conflict situation 473-43263 Design of multivariable adaptive model following control systems, 473-43256 Classification of methods for solving the direct problem of axisymmetric flow calculation in turboengines Piecewise~one-dimensional models of supersonic combustion and pseudoshock in a channel 473-44702 A-27 HCDOHSELL DOUGLAS AIRCRAFT SUBJECT IHDEI Supersonic let noise generated by larqe scale disturbances CALM PAPSE 73-9921 A73-«6827 Mathematical model for real time simulation of tilt rotor aircraft to evaluate aircraft performance and handling qualities rNASA-CF.-11H6C'1 1 N73-319«7 Airborne computer role in digital flight control systems ,. noting systems model, man machine interface, and integration N73-32982 BC00HHELL DODGLAS AISCEiFT Hanagement and control of military flight test programs at McDonnell Douglas St, Louis, Missouri i73-l»«059 MEASURING INSTRUMENTS Comparison of results obtained with various sensors used to measure fluctuating quantities in -lets. fAIAA PAPER 73«10n3l A73-HU867 Introduction of the viscous force sensing fluctuating probe technique, with measurement in the mixing zone of a circular let r.».IAA PAP*E 73-1? Vol 2 Ff D---76«9861 N73-31986 Systems analysis of avionics and aircraft equipment for search and resc'ue helicopters to determine cost effective improvements - Vol- 7 r4D<-7SK91l»l 1173-33381 BIIITiRI TECHNOLOGY The role of a military flight test engineer in test management 473=1(1)1562 Naval test and evaluation capabilities for aircraft, emphasizinq orqanizational relationships HISSIOH FLASHING Relationships between performance, safety, cost, and schedule parameters to generate program models for total space program m&SA~CR-1359031 N73-33919 Relationships between performance, safety, cost, and schedule parameters to generate program models for total space program fHASS-CR-1359021 H73-33920 HOHBBTOM TRABSFEB Determination of the impulses and moments imparted by shock waves to bodies of revolution A73=t(55 1 N73-319flB Longitudinal stability of Boeing 777 aircraft during steep approach, for noise reduction r!)GLF.--PAPEE-73~0231 N73-31963 Noise reducing approach and takeoff profiles for short takeoff aircraft f NBB-UH-^6'73-01 S73-31968 Automatic control system for in-duct cancellation of spinning nodes of sound rt)f.SACH-1323171 R73-325HC Jet noise emission and reduction by secondary cold annular flow for SST and military aircraft B73-325H3 Acoustic tests of supersonic tip speed fan with acoustic treatment and rotor casing slots and its performance in reducing engine noise rr»ASA CR-13K5M1 N73-326P8 Effect of noise constraints on engine cycle ontimization for long-haul transports m».SA TN-X-71DH71 N73-32629 Analysis of let engine noise to show sources of noise, noise spectra, and use of laminates and composite materials for noise reduction N7 3-32962 Flight tests of .Boeing 727 aircraft to determine effects of modifications on reduction of aerodynamic noise rm-ED-72--70L-31 N73-32971 Assessment of lets as acoustic shields by comparison of single and mnltitube suppressor nozzle data f NASA-TB-X-71B501 H73-33179 Fan and core engine noise suppression for STOL aircraft rBASA-TH-X-71BB8l H73-337B1 HOISE SPECTRA Noise coaparisons from full-scale fan tests at NASA Lewis Research Center, fAIAA PAPER 73-10171 A73-BB84S Low freguency noise generation within aircraft gas turbine engine core portion, discussing sources prediction, model and full scale engine tests. and future technology fAIAA PAPER 73-10271 A73-BD858 Hechanisms of externally blown flap noise, C.AIAA PAPER 73-10291 A73-W859 Progress in source noise suppression of subsonic tip speed fans, fAIAA PAPER 73-10321 A73-OB861 Spectral trends in rotor noise generation- TAIAA PAPER 73-10331 A73-B.B862 Comparison of aircraft noise measured in flight test and in the NASA Ames BO- by 80-foot wind tunnel. fAIAA PAPER 73-10B71 A73=««871 A comparison of the overall and broadband noise characteristics of fall-scale and model helicopter rotors, A73-B526B BOHOGBAPHS Reliability estimation for repairable and nonrepairable flight vehicles, considering nomographs for failure rate and probability of defined reguirements satisfaction A73-15197 NONDESTRDCTIVE TESTS Test results and evaluation procedure for nondestructive tests of airfield pavements fAD=76B7871 N73-32382 Application of radiation technology and eguipment for nondestructive analysis of commercial aircraft structures during aircraft maintenance periods N73-33579 NONLINEAR FEEDBACK Nonlinear feedback control concepts for variable stability aircraft N73=32979 NONLINEAR SYSTEHS Aerothermodynamic study of air cushion vehicles buffeting noting dynamical stability, nonlinear behavior, and similitude law rKT-33-1973] N73-32933 NONSYHCHEONIZATION Air traffic control radar beacon system interference in terminal areas fllTR-62391 H73-32512 NONDHIFORH FLOW Flow field over pointed wedges in isoenergetic flow of thermally and calorically perfect gases with nonuniform incident supersonic flow, noting attached shock formation A73-tt5517 NOZZLB DBSIGH Acoustic investigation of the engine-over-the-winq concept using a D-shaped nozzle, f A I A A PAPER 73-10301 A73-UH860 HOZZLB QEOHBTRI Nozzle geometry and forward velocity effects on noise for CTOL engine-over-vinq concept fNASA-TH-It-7111531 H73-337»2 ODOBS Sensory odor tests of exhaust from turbojet engine combustor operating at simulated idle conditions r NASA-Id-Jt-710291 H73-32613 OBB DIHBBSIOB1L FLOS Piocewise-one-diuensional models of supersonic combustion and pseadoshock in a channel A73-HU702 OPBBITXOHS RESEARCH . Functional models for airline operations H73-32870 i-29 OPTIHiL COHTBOL SUBJECT IHDEI Fesearch prelect to determine factors involved in expansion of air freight traffic and prospects for future expansion N73-3288U Analysis of commuter air transportation services to define problems and identify methods for improvements in cost effective operations H73-32885 Evaluation of new forms of air transport service for improving short haul air travel market N73-32887 Actions by Civil Aviation Board to regulate and improve commuter air transportation services N73-32888 OPTIHiL COHTEOI Game theory mathematical model for optimal control of qlide modes in conflict situation A73-A3263 Sensitivity, adaptivity and optimality; Proceedings of the Third Symposium, Ischia, Italy, June 18-23, 1973, A73-K3277 Optimal landing flare control of aircrafts Kith sensitivity consideration A73-4328K OPTIHIZAYIOH Similitude theory for design optimization of automatic control systems for aircraft gas turbine engines rAD=76l«6831 N73=32631 Optimization of control and damping system for fighter aircraft with guadratic cost function N73-32980 Design optimization and testing of flight control systems for light helicopters, applied to BO-105 helicopter N73-32985 OVEBPBESSDPE A study to determine the feasibility of a low sonic boom supersonic transport fAIAA PAPER 73=10351 A73-H4863 OIIDIZEBS Burn-up of the high temperature products of incomplete combustion in a supersonic flow by a second inflection of oxidizer A73-a5076 OZONE Heridional distribution of tropospheric ozone from measurements aboard commercial airliners. A73-K3859 P-3 AIRCRAFT Analysis of flight crew errors contributing to aircraft accidents on P-3 and F-B aircraft for improved air safety fAD-7648681 N73-31979 PARACHDTE DESCENT Computer program for analyzing characteristics of parachute-payload system during deployment and tralectory H73-31936 PASSENGER AIRCRAFT Analysis of commuter air transportation services to define, problems and identify methods for improvements in cost effective operations N73=32885 Operation of low cost local air service carriers to show methods for improving transportation services H73-32886 Actions by Civil Aviation Board to regulate and improve commuter air transportation services H73-32888 PASSENGERS Analytical forecasting methods for air passenger traffic N73-3286? PAVBBENTS Application of energy concepts for prediction of pavement system performance H73-32153 Test results and evaluation procedure for nondestructive tests of airfield pavements fAD-7687871 N73-32382 PERFORHANCB PREDICTION Some comments to mathematical interpretation of performance characteristics of let engine combustion chambers, A73-K5331 Pilot rating of fighter aircraft in precision heading task using mathematical model for predicting aircraft performance fAD-76K6951 H73-31973 Computer program for predicting pilot rating of pitch stability of T-33 aircraft under vertical turbulence conditions rAD-76t>6961 N73-3197K Application of energy concepts for prediction of pavement system performance N7 3-32153 Development of mechanical eguipment reliability prediction technigues TAD-7653671 N73-3239C Design parameters for optimal cost/cruise performance of subsonic let transport H7 3-32853 International civil aviation organization for air traffic forecasting and airport development N7 3-32865 Functional models for airline operations N73-3287r PERFOBHANCE TESTS The effects of modulated blade spacing on static rotor acoustics and performance, fAIAA PAPES 73-1P2P1 A73-«l(852 A new device for measuring local acoustic power output of subsonic lets. fAIAA PAP^B 73-101(21 A73-4K866 Effects of blade tip clearance and leading edge sweepback of compressor rotor blades on inducer performance and blade pressure loading CHASA-CH-727121 S73-3193C Performance and environmental tests of National Air Space Enroute Stage air traffic control system fFAA-NA-73-551 N73-32518 Relationships between performance, safety, cost, and schedule parameters to generate program models for total space program TNASA-CF-1359031 H73-33919 Relationships between performance, safety, cost, and schedule parameters to generate program models for total space program rNASA-CB-1359021 N73-3392? PERIODIC FONCTIOHS The prediction of instabilities of linear differential eguations with periodic coefficients r ABC-B/H-37131 H73-33518 PERSONNEL MANAGEMENT Flight test programs management and control, considering weapon systems performance tests relative to contractual reguirements, personnel allocation and supporting facilities The capabilities of army test facilities A73-lilsr>6 A73=»3210 Analysis of inviscid flow field around rectangular wing of finite thickness in supersonic flow N73-32166 BEBNTBY PHYSICS A theoretical and experimental study of sound attenuation in an annular duett fAIAA PAPEE 73-10051 A73-M836 BEENTBY VEHICLES Wind tunnel tests to determine static and dynamic stability coefficients for circular cone with various nose bluntness configurations fAD-76516»l N73-3193I! EEFEBEHCE SISTBHS Design of multivariable adaptive model following control systems. A73-H3288 REGIONAL PLANKING Regional airport planning in Germany fDGLR-PJ.PER-73-0351 N73-32159 REGULATIONS International air transportation policy and application of policy to scheduled and chartered airline services N73-32903 BBIHFORCED SHELLS Dynamic buckling of an axially compressed cylindrical shell with discrete rings and stringers, A.73-K4377 RELIABILITY ANALYSIS Reliability estimation for repairable and nonrepayable flight vehicles, considering . . nomographs for failure rate and probability of defined reguirements satisfaction A73-K5197 A-32 SUBJECT IHDBX BOTOBS Application of teliability analysis to aircraft structures sublect to fatigue crack qrowth and periodic structural inspection rAD-76«7751 N73-32383 PBLIiBILITT EBGIREEBIIG Toward reliable coaposites - An ezaaination of design methodoloqy- &73-45W Total In~?liqht Siaulator for X-22A aircraft based on variable stabilitv-and-control system concept for reliability design A73-H5153 Aircraft qas turbine engines with single crystal blades to avoid conventional casting drain boundary weakness and premature damaqe i73=«5155 Development of mechanical equipment reliability prediction techniques fAD-7653671 H73-32390 BEHOTB BEGIOHS Public air transportation service needs for nonurban areas, considerinq low traffic density problem, operational reguireaents and future trend raSBE PAPER 73-ICT-721 A73-a3l(98 RBHOTBLY PILOTED VESICLES Pemotely piloted vehicle /BPV/ for reconnaissance, electronic warfare systems, target acquisition, weapon delivery, air-air combat and different combinations A73-K5399 Development and characteristics of air cushion landing system for remotely piloted vehicles CAD 766~73- 01 H73-31968 Noise comparison of two STOL pressure ratio fans with 15 and 12 rotor blades fHt?A-T.1-X-2891 1 1173=32609 Economic risk analysis for propeller STOL transport market H73-32866 Proceedings of conference on short takeoff and landing aircraft to determine aerodynaaic characteristics and short haul transportation applications rstSA-SP-3201 N73-3293B Oblectives and findings of study to determine applicability of short takeoff aircraft for short-haul air transportation systems N73-32936 Economic and environmental aspects of short takeoff aircraft used for short-haul air transportation systems B73-32937 Short takeoff aircraft technology development related to reguirements for expanded and improved short»haul air transportation system capabilities 1173-32938 Aerodynamic and performance characteristics of short takeoff aircraft eguipped with externally blown flaps N73-32939 Wind tunnel tests to determine aerodynamic characteristics of five configurations of short takeoff aircraft wind tunnel models N73-329HI* Simulations of powered^lift STOL transport aircraft with either externally blown flap configuration or augmentor wing configuration H73-32948 Flight simulation to determine manual control of flight path and airspeed for approach and landing of powered lift let short takeoff aircraft 873-329H9 wind tunnel tests to determine magnitude of adverse ground effects on longitudinal aerodynamic coefficients of powered-lift short takeoff aircraft 873-32950 Development and evaluation of active control system to provide ride smoothing on short takeoff aircraft 1173-32951 Flight simulation to determine effectiveness of head'Up display for improving glide-slope tracking performance during steep visual approach of short takeoff aircraft N73-32952 Flight tests of augmentor-wing let STOL research aircraft to compare wind tunnel data with flight data for dynamic characteristics and limitations M73-32954 Air t r a f f i c control problems created by introduction of large numbers of STOL aircraft into high density terminal area 873-32956 Development and characteristics of 4-D guidance system for traffic control of STOL aircraft operating in congested areas H73-32957 Systems analysis of problems created in terminal area by application of short takeoff aircraft for providing high speed, short haul air transportation service H73-32958 Program plan to develop criteria for airworthiness standards applied to short takeoff aircraft used as transport service 873-32959 Design and development of quiet, clean propnslion systems for short takeoff aircraft with emphasis on engine noise redaction H73-32961 Characteristics of aerodynamic noise generated by interaction of airstream with flap surface to show location and control of noise sources H73-32963 Rind tunnel tests to determine acoustic properties of externally blown flap and aagmentor wing for short takeoff aircraft configurations 1173-32965 Aerodynamic noise characteristics of short takeoff aircraft with externally blown flaps and engines mounted over and under winq N73-32966 Selection criteria and characteristics of guiet, clean propulsion systems for use with short takeoff aircraft H73-32967 Fan and core engine noise suppression for STOL aircraft rHASA-TH-X-714481 873-33741 SIGHAL PBOCESSIHG DO-31 aircraft integrated flight control system for vertical velocity regulation in gliding, noting signal processing requirements H7 3-32983 SIGHiL BEFLBCTION Improvement of instrument landinq systems with respect to multipath propagation effects and surface reflections rDGLB=PiPEH-73=P17l H73-32521 SIMILITUDE LAW Similitude theory for design optimization of automatic control systems for aircraft gas turbine engines tAD-7646831 H73-32631 Aerothermodynamic study of air cushion vehicles buffeting noting dynamical stability, nonlinear behavior, and similitude law rm-33-19731 1173-32933 SIDE WAVES Turbulent shear stress profiles in boundary layer flow at sine wave pressure perturbations H73-33194 SIBGLE CBTSTALS Aircraft gas turbine engines with single crystal blades to avoid conventional casting grain boundary weakness and premature damage S73-45155 SIHGDLAE IHTBGBAL BQOiTIOHS Approximate calculation of the cavitation flow past low-aspect-ratio wings A73-45540 SLBBDEB BODIES Aircraft aerodynamics problems covering slender body theory, atmospheric turbulence and boundary layers, wind tunnel contractions, radiator blocks, vortex induced oscillations, etc 173-44690 Analysis of sonic boom characteristics based on second order solutions for flow distribution around slender bodies in supersonic flow -Part 1 rSASA-CE-23391 873-31927 SLBHDBB COBBS A theoretical and experimental study of sound attenuation in an annular duct. fAIAA P4PER 73-10051 A73-H4838 SLBIDBB WIHOS Designing a slender-wing-type cantilever plate under conditions of unsteady creep A73-43728 Hypersonic flow about -a.spatial body with an attached shock wave A73-45172 A-35 SLIDIH6 FBICTIOH SUBJECT IHDEI SLIDIHG FBICTIOB Fatigue life tests of ball motion and sliding friction in arched outer race ball bearing under thrust load rBASA-TH-X~71««2l H73-32375 S1IPSTEB&BS Effect of a slipstream on the acoustic radiation of ultrasonic annular lets A73=l»5358 SLOTTED SIBD TOHHSLS Slotted transonic wind tunnel tests on pitching delta wing enable selection of porpons walls for interference free damping derivatives rARC-R/B-37151 N73-32930 SBALL FBBTDBBATIOB FLOW The effect of walls on the lifting force of a , solid-foil wing : A73-03722 Hypersonic flow about a spatial body with an attached shock wave A73-IJ5172 Turbulent shear stress profiles in boundary layer flow at sine wave pressure perturbations N73-3319t SOCIOLOGY Airport establishment and operation with emphasis on regional planning, social factors, and economic forces N73-32877 SOLAS ECLIPSES Feasibility study for use of YF-12 aircraft as scientific instrument platform for observing 1970 solar eclipse tNASA-C5-1355821 N73-32735 SOBIC BOOBS A study to determine the feasibility of a low sonic boon supersonic transport, CAIAA PAPER 73-1fl35l A73-«tt863 . Acoustic velocity and sound propagation differences in incompressible and compressible fluids related to Hach cone formation and sonic boom effects A73-45269 Analysis of sonic boom characteristics based on second order solutions for flow distribution around slender bodies in supersonic flow - Part 1 fHASA-CR-23391 N73-31927 Theory for predicting sonic boom intensity and technigues for sonic boom suppression rFAA-FD~73-in H73-3196I( SODHD FIELDS Sound generation by wake cutting, • fAIAi PAPER 73-1M91 A73=ft«851 Emission of sound from a rectangular plate vibrating under the action of pressure pulsations in a turbulent boundary layer A73=»»899 SODBD GENERATORS Sound generation by wake cutting, fAIAA PAPER 73-10191 . A73~n»851 Fluid mechanics of hole tone whistle designed as efficient producer of discrete freguency sound N73-3317P SOUHD PEBSSDBE The effects of modulated blade spacing on static rotor acoustics and performance- CAIAA PAP3F 73-10201 A73-35l A73-44863 Effect of spatial variability of wind in . * • •/ ; • stratosphere on fliqht of supersonic rtransports H73-33529 SDBFACE CBACKS Fracture analysis of surface- and through-cracked sheets and plates, '' '' A73-43813 SOEPACB TBHPBBATOBB Annual variations of Garda Lake surface temperature usinq airborne bolometric equipment ' and earth based infrared video equipment fIFA-STB-231 H73-32298 SWEPT IIHGS Rake development on models of elliptic, ! rectanqular, swept and delta planforms when plunged in water fAHC-CP-12381 • N73-32932 Rind tunnel tests to determine basic performance of swept auqmentor winq confiquration and effect on longitudinal characteristics of aircraft H73-32941 SilBLIHG Swirling flow effect, on let noise'suppression ' based on acoustic field and enqine thrust measurements with and without stationary swirl vanes in exhaust nozzle fAIAA PAPER 73-1P931 A73-««836 SWITCHES Logic and desiqn procedures for multifunction mode switching controls in let aircraft cockpits fAD-76K617l ,H73-32iai SIITCHIHG CIBCOITS AC starter qenerator featuring variable-to-constant freguency conversion by cycloconverters as switching device for use with • . aircraft engines A73-«515« STSTBH BFFECTIVBHESS . < Hanaqement of Air Force test and evaluation activities, - .; •• • A73-6H055 STSTEHS AHALTSIS Development and evaluation of active control system to provide ride smoothinq on short takeoff aircraft H73-32951 STSTEHS EHGIHEEBIHG Hanaqement and control of fliqht test proqrams of the Naval Air Systems Command. i73-!li|C'56 SISTEBS STABILITY The prediction of instabilities of linear • differential equations with periodic coefficients rABC-B/M=3713l N73-33518 T-33 AIBCBAFT Computer program for predicting pilot rating 'of pitch stability of T-33 aircraft under vertical turbulence conditions rAD-76K6961 K73-3197I! T-38 AIBCBAFT Ground-based devices for spatial orientation training in T~38 aircraft fAD-76K7«01 N73-33157 TACAH Description of sector-Tacan and DMS-supported • - instrument landing .systems fDGLE-73-P19l S73-32523 TACTICS Utilization of decision and value theory concepts by helicopter pilots to plan attacks . . ' S7 3-3 3 56 5 TAIL ASSEHBLIES Increasing the critical rotational speed of the tail rotor drive shaft in SH-1 and SN-2 helicopters . • A73-45195 TAKEOFF Noise reducing approach and takeoff profiles for short takeoff aircraft CHBB-OH-06-73-01 H73-31969 TAKEOFF BDHS . Pulsated over-heated water rocket /POHHAEO/ thrust augmentation system for combat aircraft takeoff ' runs from short runways under severe weather conditions • - • • ' . A73-H5391 A-37 TECHNOLOGICAL FOBBCASTIBG SOBJECT IBDBX Aircraft accident involving Boeinq 707 aircraft following aborted takeoff at Kennedy International airport, New York, on 13 August, 1972 rNTSB-AAR-73-71 N73-319Q3 TECHBOLOGICil FOBBCASTIBG Technological change measurement methodology for cost and production estimates with application to aircraft turbine enqine development Hesearch Aviation Facility collected aircraft data processing, .merging and enhancement problems, software development and future resource reguirements A73-45Q88 TBCHBOLOGY ASSBSSBEBT OS1 government and industry efforts on aircraft midair collision avoidance systems technology advancement, comparing cost effectiveness between airborne and ground based options fASHE Pi^PEB 73-ICT-»91 A73-U3<»95 Public air transportation service needs for nonnrban areas, considering lov traffic density problem, operational requirements and future trend fASHB PAPBB 73-ICT-72V A73-43U98 Banaqement of Air Force test and evaluation activities A73-UK055 TBCHBOLOGY. OHLIZJTIOB Improvinq air transportation to low density population regions rNASA=CP-im8in N73-32905 TEBPEBATDBB DISTBIBDTIOH Effect of the circumf erential nonuniformity of a temperature field in front of a turbine on the vibrational stresses in the turbine blades A73-«37«Q Determination of the temperature fields of turbine disks and blades, usinq irradiated diamond indicators A73-«lt29fl Full-scale qround tests of externally blown flap system on F-111 aircraft winq to determine pressure and temperature distributions on undersurface of winq, vane, and flap N73-329H7 TEBPB8ATOBB EFFECTS The effect of variable environment temperature on heat transfer in extended surfaces, A73-43296 Emissions from and within an Allison J-33 combustor II - The effect of inlet air temperature. A73-43327 Errors produced by the influence of unsteady heatinq in strain measurement by wire-type resistance strain qaqes A73-04292 TSHPEBATUBB BBASOBIBG IHSTBOHBNTS Determination of the temperature fields of turbine disks and blades, usinq irradiated diamond indicators TBHSILE STBES3 Fracture analysis of surface- and throuqh-cracked sheets and plates, A73-03813 TSBSIIB TESTS Pesponse of qlass-fiber-reinforced epozy specimens to hiqh rates of tensile loading, A73-43385 TBBBIBAL FACILITIES Numerical analysis of curved approach paths and landing sequence for multiple aircraft usinq same terminal facilities to provide maximum system performance N73-31935 Analysis and simulation of intermittent positive control of air traffic by fully automated ground facility B73-32511 Air traffic control radar beacon system interference in terminal areas fHTR-62391 N73-32512 Evaluation of air traffic control beacon alphanumeric system for automatic operation in low density airport towers and terminal facilities fFAA-RA-73-5IM H73-32516 Air traffic control evaluation to determine ". , feasibility of combining smaller aircraft into qaps on flow of normal traffic to increase effectiveness of terminal facilites TFAA-AFS-50C-1 1 N73-32517 Patterns of behavior of airlines and air travellers in air transportation network and effects on use of satellite airports N73-32876 Short haul aircraft operations in terminal area with concurrent conventional aircraft operations to show methods for improved utilization of facilities N7 3-32953 Air traffic control problems created by introduction of larqe numbers of ST01 aircraft into hiqh density terminal area N73-32956 Development and characteristics of O-D guidance system for traffic control of STOL aircraft operating in congested areas N73-32957 Systems analysis of problems created in terminal area by application of short takeoff aircraft for providinq hiqh speed, short haul air transportation service N73-32958 TEST EQUIPMENT Development of instrument to measure steady and oscillatory aerodynamic forces on stinq-mounted model using forced oscillation technique rATN-71011 N73-33366 TEST FACILITIES Society of Flight Test 3nqineers, national Symposium, 3rd, Arlington, Tex,, September 11-1IS, 1972, Proceedings, A7 Flight test programs management and control, considering weapon systems performance tests relative to contractual requirements, personnel allocation and supporting facilities N1FEC test facilities, The capabilities of army test facilities A73-HM163 A73-fll)"6B Naval test and evaluation capabilities for aircraft, emphasizing organizational relationships A73-««'.i66 Some results from tests in the NAB hiqh Reynolds number two-dimensional test facility on shockless and other airfoils, A73-HU995 TF-34 EHGIBE Fan and core enqine noise suppression for STOL aircraft rNASA-TM-I-7W81 N73»337l»1 TBEBBAL BUCKLIRG Acoustic fatigue resistance of aircraft structures at elevated temperatures, fAIAA PAPEB 73-99K1 A73-DHS29 THEBHAL DBGSADATIOH Thermal aging of plastic insulated silver-plated copper aircraft electrical wire rAD-76»7311 N73-32135 TBEBBAL IHSDLATIOH Thermal aqinq of plastic insulated silver-plated copper aircraft electrical wire TAD-7647311 N73-32135 THBBHOCOOPLB PIBOBETBBS Utilization of semiartificial thermocouples in gas-turbine enqine tests J73"l53'":-3 TBEBBOOIBABIC EFFICIENCY Thermodynamics of an air-cooled qas-turbine stage A73-03733 TBIB AIRFOILS Airfoil theory calculation of bent thin foil lift coefficient and lonqitudinal moment characteristics at arbitrary flow separation point location ».7 3- '1 37 2C THIN BIBGS On the application of a new version of lifting surface theory to nonslender and kinked wings-. H73-H321' Determination of the deflections and stresses in a snail-aspect-ratio winq by the displacement method H73-"3723 A-38 SUBJECT IBDBI TUBBIHB BLADES THREE DIBBBSIOML FLOB Classification of methods for solvinq the direct problem of axisymmetric flow calculation in tnrboenqines A73-B3736 Total pressure loss distribution in viscous qas flow through annular cascades of axial flow compressors, examininq three dimensional flov effects on boundary layer development A73-44916 Hypersonic flow about a spatial body with an attached shock wave A73-45172 Determination of the impulses and moments imparted by shock waves to bodies of revolution A73-45542 Inviscid, isentropic, three-dimensional flow theory for rotatinq thin blade row in cylindrical duct 873-32193 Kutta^Joukowski condition for describinq three dimensional flow over arbitrary winq fRfF-LIB-TRANS-17"9 1 N73-33185 TBBDST IDGBEHTITIOH Pulsated over-heated water rocket /POHRARO/ thrust auqmentation system for combat aircraft takeoff runs from short runways under severe weather conditions A73-45391 Adjustable airfoil for reversable cowl flap inlet thrust auqmentation rflASA"CASE*\FC"1r75l:-n N7 3= 32 624 TBBOST COHTBOL Specification of thrust control system for Airbus A 3*0 B, tested in Boeinq 707 S73-32981 THBOST BEASOBBBEHT Swirlinq flow effect on let noise suppression based on acoustic field and enqine thrust measurements with and without stationary swirl vanes in exhaust nozzle fMA" PAPER 73-K031 £73-44836 TILTIHS ROTOBS Far field noise reduction of tiltincr rotor aircraft based on performance and weiqht tradeoffs to improve acoustic siqnatures rn».SA-CS- 11W81 N73-31937 nathematical model for real time simulation of tilt rotor aircraft to evaluate aircraft performance and handlinq dualities rHASA-CR-11D-7633231 N73-32917 UNSTEADY PLOB Broa'dband noise qeneration by aerofoils and axial flow fans fATSA PAP33 73-IMS 1 , A73-<14850 U8BAH TBiHSPOBTATIOB •-! • „ The role qround transportation can play in the airport site selection process- ff.SMP PAPBP 73-ICT--701 A73-43t!97 Use of energy in transportation and implications for future fP-5'1251 S73-33921 V/STOt AIBCRAFT Mathematical model for real time simulation of tilt rotor aircraft to evaluate aircraft performance and handlinq qualities rUf.SA • c?.- 11l>er1l H73-319tt7 V«K 191 E V/S70L fiqhter aircraft nonlinear feedback flight control system for gliding fliqht phase N73-3298B VARIABLE GEOMETRY STRUCTURES Variable turbine qeometry effect on engine installation and thrust modulation rAD'765S331 H73-33761 VABIABLE THBDST Variable turbine qsometry effect on engine installation and thrust modulation r?D-765*331 N73-33761 VELOCITY BBASUHBBEHT Hinq tio vortex measurements with laser Doppler velocineter T f?,Sl-C?" 12WHI 1 N73-32924 VERTICAL TAKEOFF AIRCRAFT Computerized simulation of interactions of VTOL aircraft taking off from or landinq on deck of ship novinq in irreqular or random seaway nE-76»8651 N73-31980 Electronic display devices in aircraft control, notinq pilot activation and VTOL control rDL?-.1IT'.72.'-li1 " N73-32998 Fxtrapolation predictive displays for manual path and position control of VTOL aircraft N73-330CO VHP OBHIBAHGB NAVIGATION Fadio frequency interference tests of VHF onniranoe system, localizer, and qlideslope receiving equipment to determine qeoqraphical separation requirements •• Vol 2 Book 2 rFJA-F.D-'I3- 1-VOL-2-BK-21 H73-32513 7IEBATIOR D1SPIKG A .study of a fluidic open loop damping flight stability augmentation system A73-l»3396 Study and calculation of the vibrations of a rotating rotor with allowance for clearances in the bearings J73-U3725 VIBB1TIOH ISOLATOBS Vibrations of turbolet-enqine components containing structural dampers of the type of sandwich rods A73-«3735 7IBB1TIOH HODS natural, flexural and torsional vibration frequencies and modes for helicopter tail rotor blades A73-«52«5 VIBRATIOH TESTS Increasing the critical rotational speed of the tail rotor drive shaft in SB-1 and SB-2 helicopters i73=»5195 VIBRATIOHAL STBESS Effect of the circumferential nonuniforoity of a temperature field in front of a turbine on the vibrational stresses in the turbine blades A73-K37BO TIDED EQDIPMEHT Annual variations of Garda Lake surface temperature using airborne bolometric equipment and earth based infrared video egnipment riFA-STB-231 H73-32298 VISCOSITY On the effects of viscous interaction for a flat delta wing at incidence r ABC~CP-=12371 1173=32931 VISCOUS FLOW Computer solutions for potential and viscous flow calculations for engine inlets rNAS&-TH-X-71l!57l H73-33W VISIBILITY Determination of visibility slant range when landing aircraft in radiation fog N73-33523 VOBTICES Navier-Stokes equation formulation in parabolic coordinates for flow in trailinq vortex, obtaining asymptotic expansions for stream . function and angular momentum S73-»3205 Aircraft aerodynamics problems coverinq slender body theory, atmospheric turbulence and boundary layers, wind tunnel contractions, radiator blocks, vortex induced oscillations, etc A73-H4690 Stability of a potential vortex with a non-rotating and riqid-body rotatinq top-hat let core. &73-45309 Characteristics of low speed air flow over slender, sharp edged delta winq at various anqles of attack and effects on longitudinal and lateral stability U73-32922 Hake development on models of elliptic, rectangular, swept and delta planforms when plunqed in water rABC-CP-12381 H7 3-32932 Analysis of random motions of vortex elements behind aircraft vinq ana desiqn of vortex arrays to reduce wake-vortex to small aircraft rNASA-TK-X-623041 N73-32976 w W1KBS Hake development on models of elliptic, rectangular, swept and delta planforms when plunged in water rABC-CP-12381 S73-32932 RAIL PLOR The effect of vails on the lifting force of a solid-foil vinq A73-U3722 WIAPOH SYSTBB HAHAGEBBHT Management of Air Force test and evaluation activities. A73-44055 Management and control of flight test programs of the Naval Air Systems Command, &73-K4036 A-41 REAPOH SYSTEHS SUBJECT IHDEX Hanaqement and control of military flight test programs at McDonnell Douqlas St- Lonis, Missouri, A73-OH059 Plight test programs management and control, considering weapon systems performance tests relative to contractual requirements, personnel allocation and snpporting facilities &73-44960 HBiPOH SISTERS Remotely piloted vehicle /SPV/ for reconnaissance/ electronic warfare systems, target acquisition, veapon delivery, air-air combat and different combinations A73-B5399 HEATHER Aircraft landing problems under low visibility weather conditions rDGLR-PAP2R=73-C151 N73-32520 Meteorological and weather effects on aircraft landings and flights along air lanes and stratospheric wind effects on supersonic transports fJPES-6?11IH N73-33522 HEDGE not Flow field over pointed wedges in isoenergetic flow of thermally and calorically perfect gases with nonuniform incident supersonic flow, noting attached shock formation A73-U55U7 «TO TOBUB!. BODEI.S Rind tunnel tests to determine low speed characteristics of large scale model of F-14A aircraft with emphasis on high lift configuration stability f NASA-Til- X-622H41 H73-31940 Wind tunnel tests to determine aerodynamic characteristics of three obligne, hiqh aspect ratio wing and body combinations at Hach numbers between 0-60 and 1 40 fNASA-TH-X-622561 N73-32926 Rind tunnel tests to determine aerodynamic characteristics of obligne wing and body combination at Hach numbers between 0,60 and 1,4C fNASA-TH- 1-622071 N73-32927 Bind tunnel tests to determine aerodynamic characteristics of five configurations of short takeoff aircraft wind tunnel models N73-329B4 SinS ttitsiiel tests of larqe scale subsonic -tet transport with upper surface blowing flap system for lift augmentation niASA-TS-X-622961 H73-32973 Transonic wind tunnel tests to determine lift, drag, and stability characteristics of F-8 aircraft model with obligne wing fNASA-TB-X-622731 N73-3297D Hind tunnel tests to determine acoustic properties of laroe scale lift fan transport aircraft model rSf-SA-TH»X- 6228111 H73-32975 Development of instrument to measure steady and oscillatory aerodynamic forces on sting-mounted model using forced oscillation technique rATH-71011 H73-33366 RIHD TCSHEL STABILITY TESTS Rind tunnel tests to determine stability and control characteristics of externally blown let-flap configurations HMD TOHSBL TESTS Aircraft aerodynamics problems covering slender body theory, atmospheric turbulence and boundary layers, wind tunnel contractions, radiator blocks, vortex induced oscillations, etc A73-BH690 On problems of flight over an extended angle-of-attack range A73-««692 Comparison of aircraft noise measured in flight test and in the HASA Ames HC- by 80-foot wind tunnel, fAIAA PAPEF. 73-10071 A73-44871 Rind tunnel tests to determine flow distribution at inlet locations on aircraft model for various aerodynamic configurations and airspeeds f HASA-TH-D-736B1 N73-31929 Rind tunnel tests to determine low speed characteristics of large scale model of ?-1»A . aircraft with emphasis on high lift : configuration stability rn»SA-TH-X-622l»IM B73=3V9ft,Q Rind tunnel tests of high harmonic circulation .. , control rotary wing model to show instruments required and data acquisition procedures fAD-7653201 N73-3198') Hypersonic wind tunnel tests of air breathing engines H73-32158 Rind tunnel tests to determine basic performance of swept auqmentor winq configuration and effect on longitudinal characteristics of aircraft N73-32941 Rind tunnel tests to determine aerodynamic characteristics of upper surface blown let-flap concept incorporating high-bypass-ratio turbofan engines N73-329D3 Wind tunnel tests to determine aerodynamic characteristics of five configurations of short takeoff aircraft wind tunnel models N73-329«li Transonic wind tunnel tests to determine effects on flutter of aerodynamic interference between pairs of closely spaced delta wings fHASA-CE-23311 H73-33887 WTO SOHHZL UU.S Slotted transonic wind tunnel tests on pitching delta wing enable selection of porpous walls for interference free damping derivatives rAHC-B/M-37151 H73-32930 BIHD TONHELS Development of wind tunnel with self correcting apparatus based on sensors to determine flow conditions on tunnel surfaces and method for varying wall geometry rAD-7649571 N73-32161 RIHD VARIATIONS Effect of spatial variability of wind in stratosphere on flight of supersonic transports N73-33529 HIHG FLAPS Flight tests of modified F-1P9 aircraft to determine effectiveness of fast-actinq flaps as direct-lift-control devices to improve station keeping rNASA-TH-1-29361 H73-32970 RIHG LOADIRG Determination of the deflections and stresses in a small-aspect-ratio winq by the displacement method A?3-«3723 RIHG PAHBLS Design analysis and fabrication of hypersonic wing test structure rNASA=CE-127«9fil N73-33383 HIHG PLAHFORBS Hind tunnel tests to determine aerodynamic characteristics of three oblique, high aspect ratio wing and body combinations at Mach numbers between 0-6C and 1.QO rNASA-TH-X-622561 S73-32926 Hind tunnel tests to determine aerodynamic characteristics of oblique winq and body combination at Hach numbers between C-6P and 1,1i) TSJsSA-TB-11-622911 S73-32927 Aerodynamic characteristics of auqmentor winqs and analysis of anqmentation and entrainmsnt in defininq a net thrust coefficient N73-329I*2 Simulations of powered-lift STOL transport aircraft with either externally blown flap configuration or auqmentor winq configuration S73-32998 Fliqht tests of auqmentor-wing let STOL research aircraft to compare wind tunnel data with flight data for dynamic characteristics and limitations N73-32951; Hind tunnel tests to determine acoustic properties of externally blown flap and auqmentor winq for short takeoff aircraft configurations N73-32965 HIBG PROFILES The effect of walls on the lifting force of a solid-foil winq 473-U3722 A-«2 SUBJECT IHDBX Z-22 HECEiFT Aerodynamic forces, pressure distribution, and wakes of wind profile with trailing edqe flaps and leadinq edqe slats H73-33187 ilHG TIPS Winq tip vortei measurements with laser Doppler velocimeter rN»SA-CP'12P1T1 N73-32929 9IHGS Kutta Joukowski condition for describing" three dimensional flow over arbitrary winq TFAS-1IB-TESHS-17P91 H73-33185 X-22 ilECfiiFT Total In-Fliqht Simulator for X-22A aircraft based on variable stability-and-control system concept for reliability desiqn J73-H5153 PERSONAL AUTHOR INDEX AERONAUTICAL ENGINEERING / A Special Bibliography (Suppl. 39) JANUARY 1974 Typical Personal Author Index Listing BLAH*. B. jf| l~t PERSONAL AUTHOR ["plight and wind tunnel inTestiqation of the I effects of Bevnolds number on installed boattail 1 drag at subsonic speeds .BASA-TB-X-68162. ^73-11007, TITLE | 1 REPORT NUMBER 1 NASA ACCESSION NUMBER _J Listings in this index are arranged alphabetically by personal author. The title of the document provides the user with a brief description of the subject matter. The report number helps to indicate the type of document cited (e.g.. NASA report, translation. NASA contractor report). The accession number is located beneath and to the right of the title, e.g.. N73-11007. Under any one author's name the accession numbers are arranged in sequence with the IAA accession numbers appearing firsi. ABBAHOVICH, K. 6. Analysis of meteorological conditions for aviation fJPBS-601141 H73-33522 AIKBH, I. B. Advanced augmentor-wing research B73-32942 AKBHS, J. F. Operational evaluation of the ABTS 2 Radar alphanumeric Display Subsystem (BADS) rFAA-HA-73-771 N73- 33569 ALBBBS, a. 1. Calculation procedures for potential and viscous flow solutions for engine inlets fNASA-TB-X-714571 N73-33184 ALBXANDB8. A. J. Heasurinq technoloqical chanqe - Aircraft turbine enqines. A73-1(1(219 ALTEHKIBCH, B. 1. Emissions from and within an Allison J-33 coubnstor. II - The effect of inlet air temperature. 173-43327 ALVABBZ, H. C. Compressibility and sonic boon A73-45269 AHDEBS. B. Boise reducing nethods for SIOL aircraft approach and take-off rHBB-OH-06-73-01 B73-31968 AHDEBSOB, S. B. Comparisons of simulator and fliqht results on augmentor-vinq let STOI research aircraft N73-32955 ABDBBSOH, i. B. Experimental investigation of a larqe-scale, two-dimensional, mixed-compression inlet systeo: Internal performance and draq at transonic conditions, free stream Hach equals 0.6 to 1.28 [BASA-TB-D-74451 B73-31928 AHDBBBS, 1. a. Herqecs and anti-trust issues in recent CAB cases B73-32895 AIIKIH, A. IA. Utilization of seeiartificial thermocouples in qas-tarbine engine tests A73-43743 AHTL, B. J. The effect of noise constraints on engine cycle optimization for long-haul transports fNASA-TH-I-714471 H73-32620 AOTAGI, K. Acoustic characteristics of large-scale STOL models at forward speed H73-32965 lind tunnel investigation of a larqe-scale upper surface blown-flap transport model having two enqines rNASA-IB-X-622961 N73-32973 ABHBNAKAS. 1. B. Besponse of glass-fiber-reinforced epoxy specimens to high rates of tensile loading. A73-43385 ABBISTBAD, K. H. Flight calibration tests of a nose-boom-mounted fixed hemispherical flow-direction sensor rNASA-TN-D-74611 H73-31956 ABHOLD, J. D. An improved method of predicting aircraft longitudinal handling gualities based on the minimum pilot rating concept fAD-7646961 N73-31974 ASADA, B. On the process of precipitation in Bq-Ce alloy. A73-44155 ASHBI, ». O. Evaluation of existing VOR, localizer and glideslope receiving equipment, volume 2, book 2 (FAA-BD-73-1-VOL-2-BK-21 N73-32513 ATBHCIO, 1. . JB. Comparison of aircraft noise measured in flight test and in the NASA Ames 40- by 80-foot wind tunnel. fAIAA PAPEB 73-10471 A73-44871 Noise measurements from a larqe-scale lift fan transport in the 40- by 80-foot wind tunnel r NASA-IB-X-622841 N7 3-32975 AOGOSTI8B, J. G. Air traffic forecasting at the Port Authority of New York and New Jersey 117 3-32879 B BiBBASHIH, B. F. Determination of the temperature fields of turbine disks and blades, using irradiated diamond indicators A73-44294 BABBBB, J. H. A study of rapid engine response systems for an advanced high subsonic, long range commercial aircraft fNASA-CR-1344961 H73-32977 BABBEB, B. B. A flight evaluation of curved landing approaches N73-32953 BABCHE, J. Experimental study of wing profile with Fowler flaps and slats N73-33187 BAOGHBAH, F. H. flanagement and control of flight test programs of the Naval Air Systems Command. A73-44056 BAOBBISIBB, K. J. A difference theory for noise propagation in an acoustically lined duct with mean flow. fAIAA PAPEB 73-10071 A73-44840 Numerical simulation of noise propagation in let engine ducts fNASA-TN-D-73391 N73-337t>« B-1 BAZZBIB, 1. F. PBBSOBAL AOTHOB IHDBZ BAZZ8IB, A. F. The effect of real properties of air on parameters of flow near an elliptic cone, Aerodynamic characteristics of elliptic cones at larqe anqles of attack rAD-7649451 H73-32209 BBILHiH, J. I. X-22A - The total in-fliqht simulator. 473-45153 BBBBEB. H. S. A fixed-base simulation study of two STOL aircraft flvinq curved, descending instrument approach paths f NASA-TN-0-7298] N73-31949 BBHHETT. G. I. A study of rapid enqine response systems for an advanced hiqh subsonic, lonq ranqe commercial aircraft fNASA-CB-134496] H73-32977 BEHZAKBIB, H. J. Multiple pure tone noise generation and control. FAIAA PAPBB 73-10211 A73-44853 BEET, C. i. Dynamic buckling of an aziallv compressed cylindrical shell vith discrete rinqs and strinqers. A73-40377 BIDiELL, L. S, Thermal aqinq of silver-plated copper aircraft electrical wire fAD-7647311 H73-32135 BIHDEB, R. B. International air transport and Federal policy N73-32902 BITTHBB, B. C. Numerical simulation of noise propaqation in let enqine ducts fNASA-TN-D-73391 N73-33744 BLINOV, B. H. Apparatus for thermomechanical surface treatment of orqanic qlass, its effect, instructions and practical testinq fAD-7609721 H73-33510 BOBBBET, H. Problems involved in developing an integrated fliqht control system with emphasis on curved fliqht path profiles fDGLR-PAP5R-73-03C] H73-31970 BOGOBOLOV, B. H. Thermodynamics of an air-cooled qas-turbine staqe A73-43733 BOGOVAIA, L. I. Universal equations for the laminar boundary layer on a body of revolution in oblique flow A73-45529 BOBB, T. ' Fliqht operations and quide beam systems fDGLB-PAFSB-73-0111 H73-32522 BOLTZ, F. 8. f.n experimental investigation of three oblique-vinq and body combinations at Hach numbers between 0.60 and 1.40 fNASA-TB-X-622561 H73-32926 An experimental investiqation of an oblique-winq and body combination at Nach numbers between 3,60 and 1,40 fNASl-TB-X-622071 N73-32927 BOIHEB, T. P., JB. Potential of hydrogen fuel for future air transportation systems. fASHS PAPER 73-ICT-1041 A73-43499 BBAITHBAITB, 1. B. The effects of inlet temperature and pressure distortion on turbolet performance rSASA-TH-X-714311 H73-32614 BROCKHAOS, B. Plight control problems reqardinq steep approach rDGLR-PAP3R-73-9271 N73-31962 BEOHS, D. Some results from tests in the NAB high Reynolds number two-dimensional test facility on shockless and other airfoils. A73-44995 BB08H, T. J. Externally blown flap dynamic loads H73-32946 BBDCB, B. 8. Systems evaluation of lov density air ' - transportation concepts " - fHASi-CB-114484] H73-32905 BBDBBIH6, G. • • ' Longitudinal lotion of an air liner during steep approach rDGLB-PAPEB-73-023] ' H73-31963 BBDIBBB, D. Present status of all-weather landing:- Problems and limits tDGLB-PAPBB-73-015] H73-32520 BBICB. C. A. Advanced two-stage compressor program design of inlet staqe fHASA-CB-120943] 1173-32610 BDCBBIJDBB, A. .. Airport economics: Management control financial reportinq systems H73-32878 BOCHHOLZ, B. D. Design problems of the Airbus A 300 B forward thrust regulator H73-32981 BOLDOVSKII, G. S. Turbulence near the tropopanse in the presence of hiqh altitude waves H73-33525 BOBIS, D. 0. Alternating current starter generators. A73-45154 BOILBB, C. International air transport policy H73-32899 BDTZB, B. P. Odor intensity and characterization studies of exhaust from a turbojet engine combustor fHASA-TH-X-71429] ' H73-32613 CABH, C. B. Spread spectrna applications and state of the art equipments H73-32058 CABSOB. T. H. Flight results from a study of aided inertial navigation applied to landing operations fHASA-TN-D-7302] H73-32515 CAIOT. J. E. Program plan to develop airworthiness standards for STOL aircraft H73-32959 CHAUIS, C. C. Experinental and theoretical investigation of BT-S/PHB-PI composites for application to advanced aircraft engines rNASA-TH-X-71459] H73-33502 CBAUDBOBI, S. B. Fundamental research on advanced techniques for sonic suppression tFAA-BD-73-4] H73-31944 CHBLISHB7A, I. P. The effect of real properties of air on parameters of flov near an elliptic cone. Aerodynanic characteristics of elliptic cones at large angles of attack [AD-764945] H73-32209 CBBB, B. X. B. Development and evaluation of an automatic departure prevention system and stall inhibitor for fighter aircraft fAD-764767] H73-31972 CBBBG, D. T. Introduction of the viscous force sensinq fluctuating probe technique, with measurement in the aixinq zone of a circular let. TAIAA PAPEB 73-1044] A73-44868 Beversed cowl flap inlet thrust angmentor r HASA-CASE-ABC-10754-1] H73-32624 CBBBIHGTOB, P. B. The future of regulation in the airline industry H73-32894 CHBSTHDTT, D. Flap noise generation and control N73-32963 PBBSOBAL AOTBOB IBDBX DISSBH, B. CHIPBAH, B. B. Flatter analysis and testing of pairs of aerodynaiically interfering delta wings [HASA-CB-2331] 1173-33887 CHOPIB, B. B. The effects of nodulated blade spacing on static rotor acoustics and performance. [AIAA PAPBB 73-1020] A73-44852 CBBXSTBBSBB, J..V. Teminal-area STOL operating systems experiments program H73-32958 CBDBBOT. B. A. Proqram plan to develop airworthiness standards for STOI aircraft, A73-44994 Proqram plan to develop airworthiness standards for SIOI aircraft H73-32959 CHOBCH. J. P. Flight testing of a cryoqenically cooled hygrometer fAD-764718] H73-32354 CLASH, B. Flap noise prediction method for a powered lift system fBASA-TB-X-71449] S73-32969 CLABK, B. 1. Field evaluation of ABTS 2 b (TBACAB) fFAA-HA-73-54] H73-32516 Operational evalnation of the ABTS 2 Badar Alphanumeric Display Subsystem (BADS) fFAA-BA-73-77] H73-33569 CLODPBLIBB, B. G. Vulnerability of dry bays ad-jacent to fuel tanks under horizontal gunfire fAD-760732] H73-32920 COCKBBBAB, S. G.. The capabilities of army test facilities. A73-44064 COB, P. L. Analysis of the low-speed flow over a slender sharp-edged delta wing at angles of attack H73-32922 COHBH, S. Extrapolated methodology used in the Los Angeles basin standard traffic model fAD-765153] N73-33571 COLACIBO, B. Thermal surveys on Garda Lake using infrared egnipment [IFA-STB-231 H73-32298 COLOSSI, D. 1. Future direction in airline marketing N73-32874 COBPA6BOB, B. A. A study of engine variable geometry systems for an advanced high subsonic long range commercial aircraft fHASA-CH-134495] H73-33748 COHHBB, D. B. Status of STOL ride gnality and control N73-32951 COBBAD, B. Flight results from a study of aided inertial navigation applied to landing operations rHASA-TB-D-7302] . N73-32515 COOBS, L. L. Study of induced load and stress, volume 3 fKASA-CR-72712] N73-31930 COOBIIOL, B. Design of multivarisble adaptive model following control systems, A73-43288 COOTS, D. A. The short haul air travel market: Evaluation of new forms of service H73-32887 CBAiFOHD, C. C., JB. flanagement and control of flight test programs at OiS. Army Aviation Systems Command. A73-44054 CBABFOBD, V. System integration and system shakedown tests, HAS enroute stage A model A3d1 rFAA-HA-73-551 H73-32518 CBBSSBAI, P. i. Election clearances in Canadian forces aircraft n>CXEH-9361 H73-31938 CHOBH, F. B. Bead-up displays for STOL visual approaches N73-32952 CBOiLBI, K. C. Aircraft noise source and computer programs - Oser's guide rHASA-CB-1146501 N73-31946 COFFBL, B. F. Comparison of results obtained with various sensors used to measure fluctuating quantities in jets. fAIAA PAPER 73-1043] A73-44867 COLLBI, B. Viscous interaction in integrated supersonic intakes N73-32194 DAFFBB, G. B. Simulation of the compatibility of an air capable ship and a VTOL aircraft fAD-764865] S73-31980 DABLBB, B. I. Some experiments on the noise emission of coaxial jets N73-32543 DASEB, K. Problems of an integrated flight control and regulation system for lift fan/VSTOL aircraft taking the DO-31 vertical velocity regulator as an example N7 3-32983 DAVIBS, L. On the effects of viscous interaction for a flat delta winq at incidence fARC-CP-1237] N73-32931 DATIBS. B. J. The prediction of instabilities of linear differential equations with periodic coefficients fABC-R/B-37131 N73-33518 DAVIS, B. A. Aluminum brazed titanium honeycomb sandwich structure - A new system. A73-44000 DBCBOB, B. Turbulent shear stress in boundary layers at periodic stationary free flow pressure perturbations N73-33194 DEHBOFVILLB, B. Concentration of airline operations at individual airports N73-32876 DBHIBGTOB, B. J. STOL propulsion systems N73-32967 DBBOSIBB, T. A. A study of rapid engine response systems for an advanced high subsonic, long range commercial aircraft rsASA-CE-13«»96l N73-32977 DBSAHTIS, G. C. An analysis of the relationship between the parachute system parameters and their effect on the system in flight N73-31936 DBSBPAHDB, B. V. Stability of a potential vortex with a non-rotating and rigid-body rotating top-hat let core. DIBDBBIKS-VBBSCBOOB, I. B. P. Liability and insurance in international air traffic 1173-451)1)3 DIBBL, L. A. Effect of inlet-air humidity, temperature, pressure, and reference Bach number on the formation of oxides of nitrogen in a gas turbine combnstor mSA-TH-D-73961 S73-32822 DIBTBICB, D. H. Engine noise technology N7 3-32962 DISSBB, B. Performance behavior of a two-cycle turbolet engine for multiparameter control N73-33757 B-3 DITTBiE, J. H. PBBSOH1L &UTHOB IBDBI DITTHAB, J. H. Engine noise technoloqy H73-32962 DOBSCH, B. 6. . BBF noise tests vith enqine ander-the-»inq and over-the-winq confiqurations H73-32966 Flap noise prediction method for a powered lift system rH?.SA-TH=X-71l>I!9l IP3-32969 DOUGLAS, G. Problems of excess capacity H73-32871 D08D. P. J, A critical assessment of qround-based devices for spatial orientation training r10-7607901 N73-33157 DBISCBLBB, J. i, Externally blown flap dynamic loads N73-32946 DOHB, D. 6, Aircraft noise source and contour estimation rNASA-CB-1106491 N73-31945 DORHEB, 1. liechanical reliability prediction pilot study fAD-7653671 B73-32390 DZVOHIK, L. I. Hypersonic flow about a spatial body with an attached shock wave A73-45172 EiDS, G. Third level air carrier service H73-32888 S73-32523 BCKEBT, K. D. Details of DLS and SETAC landinq aids rDGLB-73=019l BCFEBT, •. T. Low-speed wind-tunnel investiqation of the lonqitudinal characteristics of a larqe-scale variable winq-sweep fiqhter model in the hiqh-lift confiquratiori rHiSA-TM-X-6221141 H73-31940 BDSABDS, F. G. SFTB Symposium 12 October 1972. A73-44060 EFBEBOV, I. I. Approximate calculation of the cavitation flow past low-aspect-ratio winqs A73-45540 EISEBBAHB, J. R, Toward reliable composites * An examination of desiqn raethodoloqy. A73-45144 ELDEB, S. A. AVR6: A PDP 8/T data acquisition and averaqinq program for synchronous hot wire measurements rAD-7608511 573-32357 SLROD, S. D. Aluminum brazed titanium honeycomb sandwich structure - A new system, A73-94000 EHGLISB, B. S, Continuous wound toroidal aircraft'tire TAD-76148881 B73-31977 EPZBEEGER, B. Four-D quidance of 5TOL aircraft in the terminal area H73-32957 ERIHG, H. S. The effects of modulated blade spacing on static rotor acoustics and performance, FAIAA PAPBE 73-1?20l ' A73-44852 FABIiH. P . ' ' . _ ' • Beridional"distribution of'tropospheric ozone from measurements aboard commercial airliners, A73-43859 FALAESKI, a. D, Aerodynamic characteristics of a swept auqnentor winq N73-32941 Acoustic characteristics of large-scale STOL^ .: .' •odels at forward speed ' ' . ' ' .H73-32965 lind tunnel investiqation of a large-scale:upper surface blown-flap transport model havinq(two engines fHASl-TH-X-622961 . H73-32973 FAD1KHBB, H. B. . , ' ' . , The ATA-67 formula for direct operating cost B73-32852 PEILBB. C. B. .'.'"".'' Uoise comparisons from full-scale fan tests'at NASA Lewis Research Center. " filAA PAPBB 73-10171 LA73-««8»9 FBLSCH, K..0. ' ' . Turbulent shear stress in boundary layers at periodic stationary free flov pressure . • perturbations . . -H7 3-3319* FETTEEHAH, D. B. Potential of hydrogen fuel for future air ' transportation systems. F A S H E PAPEB 73-ICT-104] .A73-43899 PIHK, H. B. . Mechanisms of externally blown flap noise;' UIAA PAPBB 73-1029] A73-44859 PISBBB. C..1. . Dynamic buckling of an axially compressed ; cylindrical shell with discrete rings and ' stringers. A73-44377 FOBH, P.. . • Diqital synchronization for time synchronous : collision avoidance systems in aviation fDGLB-PAPER-73-012] B73-32519 POBSITH, P. J. B. The effect of composition changes on the fracture touqhness of an Al-Zn-Rq-CD-Hn forging alloy. ' A73-44025 PB1IKLIB, J. A. Flight-path and airspeed control for the STOL approach and landing ' H73-32949 FBIBDBAH, B. Acoustic investigation .of the engine-over-the-»ing concept using a D-shaped nozzle. fAIAA PAPEB 73-1030] ' A73-44860 FB1BDRICB, H. . Comparison of methods for flight tests and'their evaluation for the determination of characteristics and performance of modern let aircraft . .' ' f BHVG-FBBT-73-121 7^3-31971 FBILKE, H. Possibilities for improving the conventional instrument landing system (ILS) fDGLR-PAPEB-73-0171 H73-32521 PBOBBEB, D. D. Environmental effects on fracture resistant and biaxial fatigue desiqn of aircraft structures. A73-43811 FBOST, G. B. . - • • ' , ' The desiqn of axial compressor airfoils using arbitrary camber lines fAD-765165] H73-32636 POJITI. B. Sound generation by wake cutting. fAIAA PAPBB 73-10191 ' A73-44851 FDLLBE, C. B., Ill . King tip vortex measurements with laser Dbppler. systems ' ' ' fHASA-CB-1244441 B73-32924 GSCHBGOV. B. I. . . :, Effect of the circumferential nonnniformity of a temperature field in front of a turbine on the,, vibrational stresses in the turbine blades : ' A73-43740 GAD-EL-BAR, H. A. B. Experiments on the nearly isotropic turbulence behind a let qrid B73-33174 GALLOIAI. T. L. ... Future short-field aircraft ' ' "' H73-32936 B-4 PBBSOIAL AUTHOB IHDBZ GUTIBRBEZ, 0. I. GABON, B. . A. Experimental program for the development of iaproved helicopter struct oral crashworthiness analytical and design.techniques, Volume 2: Test' data and description of an unsymmetrical crash analysis computer program, including a user's guide and sample case fAD-7649861 ' N73-31986 Experimental program for the development of improved helicopter structural crashworthiness analytical and design techniques. Volume 1: Computerized unsymmetrical mathematical simulation and experimental verification for helicopter crashworthiness in which . multidirectional impact forces are present rID-7649851 H73-32996 GABS, G. ' ' Present status and development trends in the processing of titanium A73-43911 GBBBABDT. J. B. Differential pricing policy H73-32857 GEE, S. B. A flight evaluation of curved landing approaches N73-32953 GELBBBAN, I. Concentration of airline operations at individual airports ' ' • . H73-32876 GBBDBS, .B. B. . A flight study of the use of direct-lift-control flaps to improve station keeping during in-flight refueling fNASA-TB-X-29361 N73-32970 GBB1SD, B. P. ' • ' . Core engine noise. fAIAA PAPER 73-10271 A73-4B858 GBBHAN, B. C. Heasnrement of exhaust emissions from a 185-GE-5B engine at simulated high-altitude supersonic free-stream flight conditions fAp-7647171 H73-32632 GIBBOBS, J. 1. Analytical study of takeoff and landing performance for a let STOL transport configuration with full-span, externally blown, triple-slotted flaps : .f NASA-TN-D-74411 . ". N73-31939 GIBS, J. ' ,. Noise ,reduction of a tilt-rotor .aircraft including effects on weight and performance fNASA-CR-1146481 H73-31937 GIORDANO, B. 1. Evaluation of large screen display in the, automated oceanic ATC environment fFAA-ND-73-751 N73-33568 GIOBGI, B. . , Thermal,surveys on Garda Lake using infrared equipment riFA-STR-23] N73-32298 GLASBB, F. V. Hoise comparison of two 1.2-pressure-ratio fans with 15 and 42 rotor blades fNASA-TH-X-28911 N73-32609 GOBTBBBT, B. B. . Fundamental research on advanced technigues for sonic suppression rFAA-RD-73-41 N73-31944 GOLDHiH, B. G. . Engine noise technology _ . . . H73-32962 Highly noise suppressed bypass 6 engine for STOL application '- fNASA-TH-X-714481 * R73-33741 GOLOBOBOD'KO, I. I,, A generalization of thin foil theory A73-43720 GOODIKOOHTZ, J. Forward"velocity effects on let noise with dominant internal noise source , CHiSA-TH-X-714381 . R73-32968 Rozzle geometry and forward velocity effects on noise for CTOL engine-over-the-wing concept rHISA-TH-X-714531 H73-33742 GOBAHSSOH, 0. G. Environmental effects on fracture resistant and biaxial fatigue design of aircraft structures^ A73-43811 GOOBAS, 1. Basic technical design of the control system for an artificial stability aircraft N73-32988 GBABEB, B. J., JB. The effects of inlet temperature and pressure distortion on turbolet performance . fHASA-TH-X-714311 H73-32614 GBABAB, D. K. Cockpit switching study: Logic and design procedure development for multifunction node switching controls fAD-7646171 . N73-32141 GBABAB. L. A. An experimental investigation of three obligue-wing and body combinations at t!ach numbers between 0.6G and 1.40 fHASA-TH-X-622561 ' N73-32926 An experimental investigation of an obligue-wing and body combination at Bach numbers between 0.60 and 1.40 fHASA-TB-X-622071 H73-32927 Bind tunnel tests of an P-8 airplane model eguipped with an obligne wing CHASA-TH-X-622731 N73-3297Q GBAHDB, E. Core engine noise. fAIAA PAPER 73-10261 R73-«B857 GBAHTHAB. B. D. Simulator evaluation of the flying gualities of externally blown flap and augmentor wing transport configurations N73-329B8 6BAT. V. B. Assessment of lets as acoustic shields by comparison of single- and multitnbe suppressor . nozzle data rHASi-TH-X-714501 N73-33179 GREEHE, G. C. Aerodynamic loads measurements oh externally blovn flap STOL models H73-329t(5 GBIEB, B. . Effect of single components and their mechanical layout on the static performance of two-cycle turbolet engines N73-33756 GBIGOB'ET, L. S. Utilization of semiartificial thermocouples in gas-turbine engine tests A73-43743 GRIGOB'BVA, T. P. Determinate systems on modal control theory. A73-44329 GROEBEL, G. nonlinear control concepts for variable stability aircraft S73-329"'9 GBOSCHKA, H. Fundamental research, on advanced techniques for sonic suppression FFAA-BD-73-41 N73-319UB GBOSZCZTBSRT, B. Hodern structural materials in aviation A73-45198 GBZIIACZ, B. Preparation of airport surfaces for heavy and supersonic' aircraft . &73-45199 GDAHDABASSI, G. Sensitivity, adaptivity and optimality; Proceedings of the Third Symposium, Ischia, Italy, June 18-23, 1973. 173-43277 GOILLADHB, G. •Air piracy' and the latest work of ICAO on this sublect A73-453U5 GDHTBR, B. J. Nonlinear transient analysis of multi-mass flexible rotors - theory and applications fNASA-CB-23001 N73-3237!» GUTIERREZ, 0. A. Assessment of lets as acoustic shields by .... comparison of single- and nmltitube suppressor nozzle data fNASA-TH-X-714501 N73-33179 B-5 BADJI-OBAHBS, B. PBBSOB1L AUTHOR IHDBI H HADJX-OBARES, B. Stability of a potential vortex with a non-rotatinq and riqid-bodv rotating top-hat jet core, A73-45309 HAEOSBR Effects, and their significance of new approach methods on cockpit design rMBB-DH-07-73-01 H73-31966 H&GE, B. B. The future for STOL, A73-43520 BALL, J. 8., JB. Nondestructive testing of pavements: Final test results and evaluation procedure fAD-7647871 H73-32382 BABROCK, B. J. Ball notion and sliding friction in an arched outer race ball bearing rNASA=TM-X-714B2l H73-32375 BAHKE, D. Flight mechanical problems in landing approach with direct lift control, exemplified by BFB 320 Hansa rDGLE-PAPEB=73-P2«1 H73-31965 BARSOH, B. P. Experimental and theoretical investigation of HT-S/PI1P.-PI composites for application to advanced aircraft engines fHASA-TII-X-714591 H73-33502 HABBIHGTOH, H. i. The design and development of an automatic control system for the in-duct cancellation of spinning modes of sound rNASA-CB-1323171 N73-32540 BASSELL, J. L. , JB, Study of ground proximity effects on powered-lift STOL landing performance H73-32950 BATDER, B. E. Flap noise generation and control H73-32963 HBABSET, B. H. A computer program for axial compressor design. Volume 1: Theory descriptions, and users instructions TAD-76C7331 H73-32633 A computer program for axial compressor design. Volume 2: Program listing and program use example f AD-76I*731» 1 N73-3263Q HEEEE, W. P. Liability and insurance in international air traffic A73-45443 HEGABTI, D. B. Flight results from a study of aided inertial navigation applied to landing operations FNAFA-TN-D-73P21 N73-32515 RBID2LBERG, L. J, Highly noise suppressed bypass 6 engine for STOL application CllASA=T!i-X-71IJ48l R73-33741 BEIDHARR. H. F. Noise comparisons from full-scale fan tests at Vt.SK Lewis Research Center- fAIAA PAPER 73-1?17l A73-44849 HIATT, D. L. The 727 noise retrofit feasibility. Volume 3: Upper goal flight testing and program summary rFJ.A-RT3-72-49-VOL-31 R73-32971 BIGGIHS, T. P. Study of quiet turbofan STOL aircraft for short haul transportation rtlASA-C?-1351)811 R73-31941 HIGH, H. D. Heasurement of exhaust emissions from a 185-6E-SB engine at simulated high-altitude supersonic free-stream flight conditions UD-7647171 R73-32632 BIGHTBB, 8. B. The application of energy concepts to pavements H73-32153 Bill, J. J. The future of regulation in the airline industry R73-32894 HIBSIHGEB, F. Performance optimization for supersonic ramjet theoretical and experimental studies H73-32626 HOAD, D..B.. Comparison of aerodynamic performance of several STOL concepts R73-32944 HOEFGBH, 6. Improvement of standard ILS while retaining compatibility rDSLB-PAPBB-73-0181 R73-32524 HOGGB, B. D. Theoretical studies of sound emission from aircraft ducts. , [AIAA PAPEB 73-1012] .A73-44844 HOLDBBAB, J. ..D. . Dispersion and dilution of let aircraft exhaust at high-altitude flight conditions fRASA-TH-X-71451] H73-33743 HOLOOBBK, F. , A study of a flnidic open loop damping flight stability augmentation system. A73-43396 HOLSTEIH, H. . Desiqn study of an electronic landinq display for STOL aircraft fDGLB-PAPEB-73-0381 'H73-31961 HOPE-GILL, C. D. later-augmented vehicle (WAVE) study -phase 1 fAD-7653321 H73-32208 HDBBABD, B. B. The economic effect of competition in the air transportation industry H73-32858 HUGHES, D. L. Survey of winq and flap lower-surface temperatures and pressures during full-scale ground tests of an externally blown flap system H73-329K7 HOHBEL, T. L. A digital computer-qenerated contact analog landinq display rAD-764760] H73-32162 HDHGBHBEBG, H. A non-contact method for supervision and measurement of the effective gap between rotor blades and casinq of turbomachine durinq operation fDLB-FB-72-BOJ B73-32628 HOST, J. B. The many uses of the diriqible. A73-K4223 HDHTLET, S. C. Thrust and pumping characteristics of cylindrical ejectors using afterbnrninq turbojet gas generator fHASA-TB-X-525651 H73-32622 HOTCHBBSOH, D. C. Construction and validation of decision-theoretic models of low-level piloting and navigational behavior H73-33565 HIRES, C. S.. Program plan to develop airworthiness standards for STOL aircraft H73-32959 IHNIS, B. C., Flight-path and airspeed control for the 3IOL approach and landing N73-32949 Comparisons of simulator and flight results on auqmentor-winq jet SIOL research aircraft H73-3295S A flight study of the use of direct-lift-control flaps to improve station keeping daring in-fliqht refueling rHASk-Tn-X-2936] R73-32970 IOSIFOV, B. D. Classification of methods for solving the direct problem of axisynnetric flow calculation in tarboengines A73-a3736 ISABAH, B..H. Remarks before the Third Rational Symposium Society of Flight .Test Engineers 13 September 1972. A73-44066 B-6 PBBSOWAL 10THOR IHDEX KLBIH. S. 1. JABGBB, B. 1. Aircraft noise source and computer programs - User's guide fNASA-CR-11465r] N73-31946 JAHBS, G. S. Capital requirements for the air transport industry N73-32860 JABCZTK. i. Increasing the critical rotational speed of the tail rotor drive shaft in SH-1 and SH-2 helicopters A73-45195 JAZBIHSKI, J. Reliability calculations for flight vehicles A73-45197 JOBABNSBB, 6. Use of predictive displays in the manual path and position control of VT01 aircraft N73-3300P JOHNSON, B. B. Predicting pitch task flying gnalities using paper pilot flLD-7646981 H73-31976 JOHNSON, V. G., JB. Aerodynamic and performance characteristics of externally blown flap configurations N73-32939 JOHNSTON, T. S. Peducing the threat of mid-air collisions. fASHE PAPER 73-ICT-491 A73-43495 JOSES, A. L. An investigation of airborne displays and controls for Search And Rescue (SAR). Volume 7: Navy combat Sf.R avionics capability study (1972 - 197C ERA) rAD-76«91 ' . An electrical field in the reservoir of a fuel tank as it is filled with electrified fuel fAD-7649411 H73-33740 BOKBZrSZCZIK, B. Principal failures of turbines during turbine engine operation A73-45196 BOLL, A.. Liability and insurance in international air traffic A73-45443 BOLLBHKOF, P. A. . F/STOL tilt rotor aircraft study mathematical model for a real time simulation of a tilt rotor aircraft (Boeing Vertol Bodel 222), volume 8 r»ASA-CB-114601l S73-31947 BOOBB, A. f. An experimental investigation of wind-tunnel wall conditions for interface-free dynamic measurements fABC-B/B-37151 H73-32930 HOOZ. V. B. Transportation and energy fP-5025] H73-33921 BOHGEHTBALEB, J. B. Water-augmented vehicle (RAVE) study - phase 1 rAD-7653321 ' , H73-32208 BOBOZOV, D. I. Effect of inlet conditions on the optimal shape of a diffuser ; fAD-7655771 H73-3323C BOBRIS, P. i., BAT has hydraulic pitch change servo. A73-45475 BOBSE. F. The many uses of the dirigible. •;' A73-44223 BUGBIDGE, B. D. ' " Broadband noise generation by aerofoils and axial flow fans. fAIAA PAPER 73-10181 A73-44850 BUHSBB, H. J. Comparison of methods for flight tests and their evaluation for the determination of characteristics and performance of modern let aircraft f:BBVG-FBWT-73-12l N7 3-31971 N BADIB, S. Nonuniforo supersonic flow past wedges. A73-45547 HAGABAlSn, H. T. Subsonic and supersonic lets and supersonic suppressor characteristics. TAIAA PAPER 73-9991 A73-44834 HAGEL, B. T. Inlet geometry and axial Bach number effects on fan noise propagation. f A I A A PAPER 73-10221 A73-44854 HABBA, B. Small disturbance theory of rotating subsonic and transonic cascades N73-32193 MAVATSKII, A. A. . An electrical field in the reservoir of a fuel tank as it is filled with electrified fuel fAD-7649411 H73-33740 HEISS, J. A. Economics of airport system planning. fASBE PAPEB 73-ICT-331 A73-43494 HBLSOH, J. B. Heasuring technological change - Aircraft turbine engines. 173-44219 B-10 PBBSOBAL AOTHOB IBDBI •.POREBS, B. 6. BBOHABB, 0. Lou-pressure prepreqs as structural material for light-construction designs A73-44887 •EiBLL. F. D. Development and evaluation of an autoaatic departure prevention system and stall inhibitor for fighter aircraft TAD-76B7671 B73-31972 BBtHIB, J. C., JB. Fracture analysis of surface- and throuqh-cracked sheets and plates, 473-43813 •GOYBB, L. 1, Simulator evaluation of the flying qualities of externally blown flap and auqmentor vinq transport configurations B73-32948 HIKOLiEHKO. V. A. Determination of the temperature fields of turbine disks and blades, using irradiated diamond indicators A73-44294 BOBBAB, s. D. Some considerations for air transportation analysis to non-urban areas, fASME PAPER 73-ICT-721 A73-43498 OBOKH, i. A. An electrical field in the reservoir of a fuel tank as it is filled with electrified fuel rAD-76t»9B.n B73-33740 OHHAH, L. H. Some results from tests in the MAE high Reynolds number two-dimensional test facility on shockless and other airfoils, A73-44995 OHTA, H. Optimal landing flare control of aircrafts with sensitivity consideration, A73-43284 OLSEB. «. A.. JB. Engine noise technology H73-32962 OLSOS, S. A. t. methodology for hypersonic transport technology planning fNASi-CP.-22861 B73-31953 OHOBI, G. On the process of precipitation in Hq=Ce alloy. A73-44155 OOB, E. H. Decay of trailing vortices f»SC-CP-12381 N73-32932 OSTOSLA7SKII, I. V, A generalization of thin foil theory, A73-4372C OSBN, P, B. The aerodynamics of aircraft and other things /Fifteenth Lanchester Memorial LectureA A73-44690 PAINB. C. J. Advanced two-stage compressor program design of inlet stage rHASA-CS-1209031 N73-3261C PALMER, B. A. Head»up displays for STOL visual approaches R73-32952 PAB, T. S. Fundamental research on advanced technigues for sonic suppression fFAA-BD-73-41 B73-31944 PAPAHIKAS, D. G. Problems of airship aerodynamics B73-32994 PABIETT, L. P. Stability and control of externally blown flap configurations S73-32940 PABB, T, Evaluation of close-in/short turn on patterns (IIS) r FAA-iFS=5PC=1 1 B73-32517 PABTHASABATBI, S. P. Comparison of results obtained with various sensors used to measure fluctuating quantities in lets. tAIAA PAPBB 73-10431 A73-44867 PAOLOB. J. Study of shock waves patterns in an axial supersonic compressor B73-32196 PEABT, B. A. Aircraft noise source and contour estimation fBASA-CB-114649] B73-31945 PECSVABADI, T. . Four-D guidance of STOL aircraft in the terminal area B73-32957 PEEL, C. J.. The effect of composition changes on the fracture toughness of an Al-Zn-Bg-Cu-Bn forging alloy. A73-44025 PBIBCB, B. B. Flight testing of a cryogenically cooled hygrometer tAD-7647181 B73-32354 PEBDLEBDBY, E. , H. The application of adhesive bonded structures and composite materials on advanced turbofan engines B73-32470 PBBBIBG, F. A. Hypersonic wing test structure design, analysis, and fabrication fSASA-CR-127490] H73-33883 PEBBOBE, G. L. Advanced two-stage compressor program design of inlet stage fBASA-CB-1209431 B73-32610 PBBBY. B., III Aerodynamic loads measurements on externally blown flap STOL models B73-32945 PETEBSOB, P.. Integration of STOL airplanes into the ATC system B73-32956 PETBOf, D. A. The use of single crystal blades. A73-45155 PBDKEB, G. , Details of DLS and SETAC landing aids fDGLB-73-0191 B73-32523 PHELPS, A. E., Ill Aerodynamics of the upper surface blow flap B73-32943 PHILLIPS. G. United States international air transport policy, the promise and the reality H73-32903 PLABK, P. P. Hypersonic wing test structure design, analysis, and fabrication fBASA-CB-1274901 B73-33883 PLOHBLEB, H. B. A theoretical and experimental study of sound attenuation in an annular duct. fAIAA PAPEB 73-10051 A73-44838 PBOBLI, D. The effect of variable environment temperature on heat transfer in extended surfaces. A73-B3296 POLLABD, J. S. A comparison of the overall and broadband noise characteristics of full-scale and model helicopter rotors, A73-45264 POTTS, J. K. The role of a military flight test enqineer in test management. A73-44062 P08EBS, B. G. Simulator evaluation of the low-speed flying qualities of an experimental STOL configuration with an externally blown flap wing or an auqmentor winq fBASA-TN-D-7454] B73-31951 Simulator evaluation of the flying qualities of externally blown flap and auomentor ving transport configurations H73-32948 B-11 PBIAKBXH, I. I. PEBSOBAL AOTHOB IHDBX PHIAKHIH, I. I. Inprovement of the corrosion-fatique strength of aluminum alloys by exposure of the medium to a magnetic field &73-U3D66 PBOSVBBIB, V. I. apparatus for thermonechanical surface treatment of organic qlass, its effect, instructions and . practical testing [AD-76B9721 N73-33510 PBOCBBIERICZ, P. G. Beridional distribution of tropospheric ozone from measurements aboard commercial airliners, A73-H3859 PUl'KIS. K. S. Determination of the temperature fields of turbine disks and blades, using irradiated diamond indicators A73-4H29U P0TBAB, T. B. Externally blovn flap impingement noise N73-3296B Q QOIGLBY. B. C. Preliminary results of fliqht tests of the anqmentor-winq let STOL research aircraft N73-3295« BADE, B. Steep approach limits for rotary winq aircraft fHBB-OD-101-73-01 N73-31969 BiDDCHEL, B. Determinants of market structure and the airline industry H73-32869 BAKBAL'SKII. V. A. Synchronized operation of a positive-displacement qear pump and a vane pump within the lubricant oil delivery system of a jet engine A73-43702 BABSOBE, B. American Airlines propeller STOL transport economic risk analysis H73-32866 BATCLIFF, J. D. A fliqht study of the use of direct-lift-control flaps to improve station keeping during in-flight refueling fHASA-TH-X-29361 . N73-32970 BATSIBOB, fl. I. Analysis of visibility conditions when landing an aircraft in a radiation fog H73-33523 BAOCB, F. J. Flutter analysis and testing of pairs of aerodynamically interfering delta winqs fNASA-CB-23311 N73-33887 BEDDECLIFF, J. fl. Study of induced load and stress, volume 3 fNASA-CR-727121 H73-31930 SEED, D. I. Toward reliable composites - An examination of design methodology. A73-H51IH! BBICH, D. Effect of artificial stability on aircraft performances H73-32986 EBPIC, B. H. A methodology for hypersonic transport technology planning CHASA-CS-22861 H73-31953 BBSHOTKO, H. Acoustic investigation of the enqine-over-the-winq • concept using a D-shaped nozzle, fAIAA PJPBP 73-10301 173-B»860 EBF noise tests with engine under-the-vinq and over-the-winq configurations 1173-32966 Flap noise prediction method for a powered lift system rHASl-T!J-X-7W91 H73-32969 BBSTIVO, T. F. Principles of incremental forging: Phase 3 riD-76»618l F73-3238K BICE, B. J. A difference theory for noise propagation in an acoustically lined duct with mean flow. TAIAA PAPSB 73-1C071 A73-»I!8«C BICBABDS, C. B. .!'" Hanaqement and control of fliqht test programs of the Western Beqion FAA. A73-40053 BICBABDS, B. B., JB. - Evaluation of close-in/short'turn on patterns (ILS) fFAA-AFS-500-11 S73-32517 BIBALDI, S. Sensitivity, adaptivity and optimality; Proceedings of the Third Symposium, Ischia, Italy, June 18-23, 1973. , A73-H3277 BITZI, E. B. ' Theoretical studies of sound emission from aircraft ducts. fAIAA PAPBB 73-10121 A73-«K8»« BOBEBTS. I. Short-haul transportation in the 1980's : S73-32935 BOBIHSOH, C. E. Heasurement of ezhaust emissions from a 185-G5-5B engine at simulated high-altitude supersonic free-stream fliqht conditions rAD-76«717l N73-32632 B06EBS, D. F. Simulation of the compatibility of an air capable ship and a TTOL aircraft rAD-76»8651 N73-3198" BOGEBS, R. D., JB. Boute award considerations N73-32880 BOBZIB, V. D. Effect of the circumferential nonuniformity of a temperature field in front of a turbine on the vibrational stresses in the turbine blades A73-13711'; BOSEBSTEIB, H. V/ST01 tilt rotor aircraft study mathematical model for a real tine simulation of a tilt rotor aircraft (Boeing Vertol Model 222), volume 8 rNASA-CB-1ie601l N73-319K7 BOSSOR, 7. J. Theoretical study of lift generated vortex sheets designed to avoid roll up *• rNASA=TH-X-62308 BDF, B. Comparison of methods for fliqht tests and their evaluation for the determination of characteristics and performance of modern let aircraft rBHVG-FBWT-73-121 H73-31971 BDFF, G. Tasks of regional airports and resulting ground facilities requirements rDGLE-PAPKB-73-0351 N73-32159 BOBWBDBL, B. Flight safety, air traffic control, and liability A7 BOSAK, A. B. Burn-up of the high temperature products of incomplete combustion in a supersonic flow bv a second in lection of oxidizer * M W W W K * « h « V W I U M U B W A W U Al l ,9 OU second inflection of oxidizer SABOEOV, I. S. Burn-up of the high temperature products of inconplete combustion in.a supersonic flow by a 'A73-K5076 B-12 PEBSOBAl 10TBOB IBDBI SIDDOB, I. E. SAGBBSEB. D. A. STOL propulsion systems H73-32967 SAHABICB. H. B. Thrust and panpinq characteristics of cylindrical electors using afterburning turbojet gas generator CHASA-TH-1-525651 B73-32622 SABABIH, 1. A. Vibrations of turbo-fet-engine components containing structural dampers of the type of sandvich rods 673-43735 SABGEB. §. L. Two-dimensional analytical and experimental performance comparison for a compressor stator section with D-factor of 0.47 f NASA-7N-D-7B251 H73-31932 SABKISTAB. S. 4. Economic evaluation of aircraft and spacecraft rJPRS-eniOttl N73-32907 SAOBDEBS, S. C. Application of reliability analysis to aircraft structures subject to fatigue crack qrowth and periodic structural inspection CAD-76C7751 S73-32383 SiVBIl, C. T. Multiple pure tone noise qeneration and control, f&IAt PAPEB 73-1C211 A73-44853 Si BIBB, F. H. ' In-plane and out of plane stability derivatives of slender cones at Hach 11) fAD-7651641 R73-31934 SiitBE, B. B. , A fixed-base simulation study of two STOL aircraft flyinq curved, descending instrument approach paths rN»SA-TN-D-72931 H73-31949 Integration of STOL airplanes into the ATC system B73-32956 SCBAERZEB, G. Plight path control equipment for producinq curved fliqht path profiles in microwave landinq systems rDGLF-PAPEE-73-0161 N73-32526 ,Design of a modern fiqhter aircraft control system using quadratic cost functions H73-32980 SCHAFRABEK, D. Longitudinal motion of an air liner during steep approach fDGLK-PAPEF-73-0231 H73-31963 SCHADEB, J. J. The effects of modulated blade spacing on static rotor acoustics and performance, fAISA PAPSS 73-1«201 A73-44852 SCBELBORB, A. E. Development and evaluation of an automatic departure prevention system and stall inhibitor for fiqhter aircraft f AD-"7607671 H73-31972 SCBEBK, H. Monitor display for automatically controlled steep approach rDGLS-PAPFE-73-0311 H73-31964 SCHEI, J, A. Principles of incremental forging: Phase 3 fAD-7606181 H73-32384 SCBHIDT, D. K, Optimal multiple aircraft control for terminal area approach H73-31935 SCBHIDT, S. F. Flight results fro in a study of aided inertial navigation applied to landing operations m»SA-TN-D-73?21 H73-32515 SCBHBIDB8, C. I. Acoustic fatigue resistance of aircraft structures at elevated tenperatures, Cm* PUPEF 73-99«1 173-41)829 SCHHBIDBB, L. R. The future of the US domestic air freight industry R73-32884 SCHOBHBBROBB, F. Hixed CTOL/QTOl traffic rHB8-OH-P5-73-01 H73-32525 SCBOBBIABD. B. Low-pressure prepregs as structural material for light-construction designs 473-80887 SCHOPIBLD, B. 1. A lightweight, low-profile antenna for airborne station-keeping application [AD-7646851 B73-32131 SCHOOBOVEB, I. B., JB. Status of STOL ride quality and control B73-32951 SCHBOBDEB, B. H. Quiet STOL propulsion session introductory remarks 1173-32961 SCHDBEK, 0. Some comments to mathematical interpretation of performance characteristics of let engine combustion chambers. A73-45381 SCHIABTZ, I. B. Jet noise suppression by swirlinq the let flow. fAIAA PAPEB 73-10031 A73-44836 SCHfBIZEB, 6. Problems of airborne computer aided digital control systems S73-32982 SCIAHHABBLLA. C. A. Besponse of qlass-fiber-reinforced epoxy specimens to high rates of tensile loading. A73-43385 SEABS, B. B. Self-correcting wind tunnels fAD-7649571 H73-32161 SEH'BZBOV, A. R. Errors produced by the influence of unsteady heating in strain measurement by wire-type resistance strain gages A73-44292 SHAHADI, F. A. The effects of nodulated blade spacing on static rotor acoustics and performance. TAIAA PAPBH 73-1020] A73-44852 SHAIKHIHDBOVA, L. F. Burn-up of the high temperature products of incomplete combustion in a supersonic flow by a second injection of oxidizer A73-45076 SHAIKHOTDIBOV, Z. 6. Burn-up of the hiqh temperature products of incomplete combustion in a supersonic flow by a second injection of oxidizer A73-45076 SHABHOH, B. H. Human factors approach to aircraft accident analysis fAD-7648681 H73-31979 SHATABT, V. G. Desiqninq a slender-winq-type cantilever plate under conditions of unsteady creep A73-43728 SBCBETIBKOV, B. S. Piecewise-one-dimensional models of supersonic combustion and psendoshock in a channel A73-44702 SHBEB. B. E., JB. Subsonic and supersonic lets and supersonic suppressor characteristics. TAIAA PAPER 73-9991 A73-48834 SHBBHAB, L. Pressure drop in air flow across banks of fin-tubes with varyinq pitch TPB-220315/61 H73-33229 SHBVBLL, B.,S. Studies in short haul air transportation in the California corridor: Effects of design runway length; community acceptance: impact of return on investment and fuel cost increases, volume 1 mm-CB-114634) R73-32842 Studies in short haul air transportation in the California corridor: Effects of design runway length; coonunity acceptance; iopact ot return on investment and fuel cost increases, volume 2: Appendices r"iSH-CP-114634 (1)1 B73-32843 SHVBTS', 0. I. effect of a slipetrean on the acoustic radiation of ultrasonic annular lets 173-45358 SIDDOB, T. B. & new device for measuring local acoustic power output of subsonic lets, Mill P1FBS 73-10421 173-44866 B-13 SIHBIBSKII, D. F. PEBSOBAL AOTHOH IHDEI SIHBIBSKII, 0. F. Utilization of semiartificial thermocouples in gas-turbine enqine tests A73-H3743 SIHPSOH, C. 6. Interrelationship of FAA-DOT-NASA .programs relating to aircraft cabin materials fire rFAA-BD-73-1461 H73-32972 SIHPSOH, B. B. . An analysis of airline costs, Lecture notes for HIT courses. The 16.73 airline management and marketing . ' . N73-32851 Technology for design of transport aircraft. ...... Lecture notes for .HIT courses: .Seminar 1.61 freshman seminar in air transportation and .. graduate course 1.201, transportation systems analysis H73-32853 SKBIPHIK, H. V. Apparatus for thermomechanical surface treatment of organic glass, its effect, instructions and practical testing fAD-7699721 N73-33510 SHALL, B. 0. Potential of.hydrogen fuel for future air transportation systems. . . ••• fASHB PAPEB 73-ICT-1041 A73-43499 SBITH, D. 8. Terminal-area STOL operating systems experiments program H73-32958 SHITB, 6. I. Flight results from a study of aided inertial navigation applied to landing operations fHASA-TJI-D-73021 H73-32515 SBITH, H. J. T. - Rush-kits or new fans. A73-45374 SHITH, S. Performance evaluation of Foa internal energy separators •-. tAD~76«5851 1173-32381 SHODGBASS, J. Commercial aircraft, development and the export market ; H73-32900 SOBOTTA, t, . . The VAK 191 B flight control system and resulting • new developments for the next V/STOL fighter aircraft generation . ' H73-32984 SODEBHAH, P. T. Comparison of aircraft noise measured in flight test and in the NASA Ames HO- by 80-foot wind tunnel. TAIAA PAPEB 73-10471 A73-44871 SOLOHIB,,S. V. Admissible scale of spatial averaging of the values of the geopotential in the stratosphere considering the effect of the wind on the flight of a supersonic aircraft . . H73-33529 SOBBBSBB, P. D. Conceptual design of a air cushion landing system for an unmanned aircraft CAD-76077B1 ' H73-31985 SOBOKA, B. A. Approximate calculation of the cavitation flow past low-aspect-ratio wings A73-45540 SOOLIEH, C, The S-4 Hodane hypersonic wind-tunnel: Its use for air breathing engine tests H73-32158 SPAI6LEB, B. H. . . HAFBC test facilities, A73-44063 SPBHCEB, B. Noise reduction of a tilt-rotor aircraft including effects on weight and performance .rHASA-CB-1106tt8l H73-31937 SPIHGOLA, A. J. -. Evaluation of large screen display in the • automated oceanic ATC environment r.FAA-HD-73-751 ' H73-33568 STAPLES, B. Design of a modern fighter aircraft control system using quadratic cost functions N73-32980 SIAHBLBB, I. A review of the American BPV scene. A73-45399 STEFFBH, F. I. Wind tunnel tests of a 20 inch diameter 1.15' - pressure ratio fan engine model rHASA-TH-X-7W51 N73-31931 STEHLIHG. K. B. The many uses of the dirigible. A73-4U223 STBLLBHA, L. An instrument for measuring steady and oscillatory aerodynamic forces fATH-71011 "'• H73-33366 STBPHIBBSKI, B. Hoise reduction of a tilt-rotor aircraft including effects on weight and performance - rHASA-CH-1ia6ll81 N73-31937 STBBABT, B. C. ' Economic and environmental aspects of STOL transportation •': N73-32937 STBWABT, B. H. Conceptual design of a air cushion landing system for an unmanned aircraft • - • fAD-7647741 N73-31985 STOBIB, I. C. Burning fate studies of fuel air mixtures at high pressures, A73-D5162 STOCKHAH, H. 0. Calculation procedures for potential and viscous flow solutions for engine inlets fHASA-TH-I-71»57l F73-33W STOHE, B. B. Higher harmonic circulation control rotor model - model instrumentation and data acquisition TAD-7653201 N73-3198« STODT, A. B. Current problems and issues in air freight rates N73-32883 STOUT, B. 6. Study of guiet turbofan STOL aircraft for short haul transportation fHASA-CB-135*811 N73-31911 STBAHLE, B. C. . • A review of combustion generated noise. fAIAA PAPEB 73-10231 "' A73-«l»e55 STEEIT, J. P. Management of Air Force test and evaluation-' activities. A73-HH055 STDKOHIS, H. Principal failures of turbines during turbine engine operation A73-15196 SDGIOBA, I. Optimal landing flare control of aircrafts with sensitivity consideration. A73-K328H SDHHEBS, J. L. Bind tunnel tests of an F-8 airplane model eguipped with an obligue wing rNASA-TH-X-622731 N73-3297K S8AH, B. Trends in commuter air carrier operations N73-32865 SWBBT, H. S. Study of guiet turbofan STOL aircraft for short haul transportation rHASA-CB-1354811 - H73-3191I1 TAB, C. K. B. Supersonic 1et^ noise generated by large scale disturbances^. fAIAA PAPEB 73-992V A73-I«H827 TAB, K. K. A note on the flow in a trailing vortex, 173-U3205 TAHBJA, H. Development of the air transport industry H73-32849 B-14 PBBSOBAL AOTBOB IRDSZ BALCHHEB, 0. The market demand for air transportation H73-32863 Techniques for forecasting air passenger traffic H73-32864 TATLOB, C. B. Predicting heading task flying qualities with paper pilot . .: FAD-7646951 F73-31973 TlYLOB, J. ' . Pelative frequency of occurrence of different normal accelerations at the centre of gravity of . aircraft in turbulence f ARC-R/H-371P1 H73-32929 THOHAS, H. B. B. B, . ., On problems of flight over an extended angle~of-attack range. A73-44692 tBOHAS, J. Monitor display for automatically controlled steep approach ... fDGLB-PAPBB-73-P3n 87.3-31.960 TIDEHAH, T. H. Basic economic principles N73-32854 TIEFEHAD, H. K. .. . .. Heridional distribution of tropospheric ozone from measurements aboard commercial airliners, . " A73-43859 TOPOHOV, 1. B. Classification of methods for solving the direct problem of axisymmetric flow calculation in turboengines A73-43736 THIVETT, L. G. . ' Design and investigation of a wind-shear-proof control system for automatic landing . fAD-76fl6971 " R73-31975 TROTH, D. L. . Investigation of aircraft gas turbine combustor having low mass emissions , r f.D-76119871 .: H73-32638 TROUT,.A. H. . ' Affect of inlet-air humidity, temperature, pressure, and reference Hach number on the formation of oxides of nitrogen in a gas turbine combustor rNASA-TK-D-73961 . . N73-32822 TBOHOV, 0. K. Conditions of icing of modern transport aircraft from routine flight data- 1 N73-33528 TROSOVA, 0. H. . The effect of real properties of air on.parameters of flow near an elliptic cone. Aerodynamic characteristics of elliptic cones at large angles o f attack . • " • " ' ' . fAD-7€l>9K51 N73- 32209 TSABEVA, G. A, Errors produced by the influence of unsteady heating in strain measurement by wire-type resistance strain gages A73-44292 TO, R. 1C. Advanced two-stage compressor program design of " ' inlet stage .. rNiSA-CB-12?9»31 . H73-32610 TOHAHOV, A. T, The use of single crystal blades.. A73-45155 TOTTLB, J. H. Emissions from and within an Allison .J-33 combustor. II - The effect of inlet air temperature- A73-43327 TOTTLB, B. L. Wanaqement and control of military flight test programs at HcDonnell Douglas St. Louis, Bissouri, i73-««059 VABTH, J. G. The aany uses of the dirigible. A73-H9223 VAICO, R. B. STOL propulsion systems H73-32967 7AHDESTBEH, G. . Study of buffeting motion of air cushion vehicles fHT-33-19731 H73-32933 7BBDOOB, A. J. - Investigation of aircraft gas turbine combnstor having low mass emissions rAD-76»9871 H73-32638 7BHKAHP, F. J. Investigation of aircraft gas turbine combastor having low mass emissions fAD-7649871 H73-32638 VITTBK, J. F. . Proceedings of the HASA/HIT Workshop on Airline Systems Analysis, volume 1 fBASA-CE-13563"] H73-32808 The role of the Federal Government in the development of the DS air transportation system H73-32850 Basic finance • H73-32859 VIVOHA, F. R. Thermal surveys on Garda Lake using infrared equipment fIFA-STB-23] H73-32298 - 70GEL, J. H. ' numerical calculation of flow fields about rectangular wings of finite thickness in . . supersonic flow H73-32166 VOBASKE, B. F. . Preliminary results of flight tests of the angmentor-wing let STOL research aircraft H73-329511 VOHGLAHH, 0. Forward velocity effects on let noise with dominant internal noise source rHASA-TH-1-714381 S73-32968 Nozzle geometry and forward velocity effects on noise for CTOL engine—over-the-winq concept rRASA-TK-X-714531 H73-33742 VOHKIBSCHBADB, B.. Technical conditions for a restart in airship technology • . ' . . S73-32995 VONBBIBB, 0. Comparison of methods for flight tests and their evaluation for the determination of characteristics and performance of modern let aircraft rBH7G-FB»T-73-121 H73-31971 VOHSALZEB, H. The VAK 191 B flight control system and resulting new developments for the next V/STOL fighter aircraft generation • H73-32984 VOHSCHILLBH, H. The Zeppelin airship, initiator of world air traffic - H73-32990 w u DBBATZKA, B. ' Technical aspects of,/airship manufacture and operations ' . , H73-32993 HUG, «. L. Human factors approach to aircraft accident analysis FAD-764 86 81 H73-31979 HIGHER. J. Fozzle geometry and forward velocity effects on noise for CTOL engine-over-the-wing concept fHASA-TH-X-714531 N73-33742 BALBOBS, D. B. Conceptual design of a air cushion landing system for an unmanned aircraft ' fiD-7647741 ' H73-31985 BALCHHBH, O. In-plane and out of plane stability derivatives of slender cones at Mach 14 [AD-7651641 N73-31934 B-15 WALK8B. D. Q. PBBSOBAL 1DTBOB IHDBI ilLKBB, D. Q. Assessment of lets as acoustic shields by comparison of single- and multitabe suppressor nozzle data rBASA-TB=X-71450l N73-33179 •ASHIBGTOB, B. P. Analytical study of takeoff and landing performance for a let STOL transport configuration with full-span, externally blown, triple-slotted flaps rHASA=TR-D-7l»l»1l B73-31939 MTSOB, D. Terminal-area STOL operating systems experiments program H73-32958 •AZYBIAK. J. A. Boise comparison of two 1.2-pressure-ratio fans with 15 and 42 rotor blades TBASA-TH-1-28911 H73-32609 WEBB, H. B. Systems evaluation of low density air transportation concepts fBASA-CH-1144841 B73-32905 •EBB. L. D. Flight calibration tests of a nose-booa-mounted fixed hemispherical flow-direction sensor CHASA-TB-D-74611 B73-31956 •BIBGABTBB, J. L. Closing the air transport gap on intermodal containers, fASBE PAPER 73-ICT-301 S73-43493 SEISE. K. Boise reducing methods for STOL aircraft approach and take-off CHBB-UH-06-73-01 H73-31968 •BLDOB, a. J. Radiation safety in airline maintenance H73-33579 1EHBELL, A. B. Study of induced load and stress, volume 3 fBASA-CR-727121 H73-31930 BBBHEBSTBOB, A. Jo . The design of axial compressor airfoils using arbitrary camber lines TAD-7651651 H73-32636 IBSOKT. B. L. Bind tunnel tests of a 20 inch diameter 1. 15 pressure ratio fan engine model f BASA-TB-X-714451 H73-31931 BE IBP, B. A non-contact method for supervision and measurement of the effective gap between rotor blades and casing of tnrbomachine during operation fDLB-FB-72-401 H73-32628 WBBELOCK, B. H,. Banagement and control of military and commercial flight test programs at Bell Helicopter Company, A73-44058 BHBLA8, B. B. Air Force Prototype Program management. A73-44061 BHIim, R. Performance evaluation of Foa internal energy separators fAD-7645851 B73-32381 BBITTMBB, I. C. , Application of reliability analysis to aircraft structures subject to fatigue crack growth and periodic structural inspection f»D-7647751 H73-32383 WICK, B. B. Overview of technology sessions H73-32938 BIBHEBI8JCZTK, B. Beliability calculations foi flight vehicles A73-45197 WIGHT, K. C. An ezperinental investigation of wind-tunnel vail conditions for interface-free dynamic neasnrements r»BC-B/H-3715] B73-32930 BI1CKBBS, V. Points of vie* for the information display in Aircraft H73-32999 IILCOI, ?. A. Comparison of ground and flight test results using a modified F106B aircraft rBm-!D-X>714391 H73-31959 BILEI, J. Planning, management, and economics of airport operation H73-32877 BILKIBS, D. J. Toward reliable composites - An examination of design methodology. A73-45144 BILSOS, H. F-14. A73-K4695 BIHGBBT, J. B. An investigation of airborne displays and controls for Search And Rescue (SAB). Volume 7: Davy >;- combat SAR avionics capability study (1972 - 1974 ERA) fAD-7649141 H73-33381 BHTLIB, 6. Experimental program for the development of improved helicopter structural crashworthiness analytical and design techniques. Voluae 2: : Test data and description of an unsymmetrical crash analysis computer program, including a user's guide and sample case fAD-7649861 B7 3-31986 Experimental program for the development of improved helicopter structural crashworthiness analytical and design techniques. Volume 1: • Computerized nnsymmetrical mathematical simulation and experimental verification for helicopter crashworthiness in which multidirectional impact forces are present TAD-7649851 H73-32996 BOJCICKI, S. The combustion process in a pulselet engine A73-45377 BOJCIBCHOBSKI, J. J. Continuous wound toroidal aircraft tire fAD-7648881 H73-31977 BOLOBICZ, C. B. Summary of stability and control characteristics of the XB-70 airplane fHASA-TH-X-29331 B73-31958 BOB6, B. D. Experimental investigation of a large-scale, two-dimensional, mixed-compression inlet system: Internal performance and drag at transonic conditions, free stream Bach equals C. 6 to 1.28 fNASA-TN-D-74451 N73-31928 BOODBARD, B. P. Boise comparison of two 1.2-pressure-ratio fans with 15 and 42 rotor blades fNASA-TB-X-28911 N73-32609 BRI6BT, S. B. Spectral trends in rotor noise generation. TAIAA PAPER 73-10331 A73-44862 BUBLLBHKBBPEE, T. Airship manufacture in Muelheim/Ruhr H7 3-32992 BDEHBEHBBHG, B. Comparison of methods for flight tests and their evaluation for the determination of characteristics and performance of modern let aircraft rBHVG-FBBT-73-121 H73-31971 BDBST, P. Design problems of the Airbus A 300 B forward thrust regulator H73-32981 BIKBS, J. B. Flight investigation of a structural mode control system for the XB-70 aircraft rBASA-TK-D-74201 H73-3195P IABCBI, B. B. Summary of stability and control characteristics of the IB-70 airplane rSAS»-TH-X-29331 N73-31958 IBB, J. T. I new device for le&suring local acoustic power output of subsonic lets. ClXAl PAPER 73-10421 A73-4K866 IFF, J. . Rational calculation of design gust loads in relation to present and proposed airworthiness regoirenents TFOK-K661 873-31969 B-16 PEBSOHAt AOTHOH IHDBX ZIBBBBBiH, H. ». TODHG. 8. B. Study of induced load and stress, volune 3 CHASA-CB-727121 H73-31930 I ZAKBBS, J. P. Field evaluation of ARTS 2 b (TH1C&B) rF&A-HA-73-591 K73-32516 ZilDBEBGBH, P. J. On the application of a new version of lifting surface theory to nonslender and kinked vinqs, A73-4321C ZAVATUI, 8. P. Influence of variable turbine geometry on enqine installation losses and cycle selection fAD-7655331 H73-33761 ZBLiZHT, S. 8. Hater-auqmented vehicle (RAVE) study - phase 1 TAD-7653321 H73-32208 ZIHHBBHAH, e. «. Banaaement and control of comnercial flight test programs, A73-«»057 B-17 CONTRACT NUMBER INDEX AERONAUTICAL ENGINEERING / A Special Bibliography (Suppl. 39) JANUARY 1974 Typical Contract Number Index Listing |HAS3-12430| I—' iB73-117991 Listings in this index are arranged alphanumerically by contract number. Under each contract number, the accession numbers denoting documents that have been produced as a result of research done under that contract are arranged in ascending order with the IAA accession numbers appearing first. The accession number denotes the number by which the citation is identified in either the IAA or STAR section. AF PHOJ. 683H H7 3-32382 AF PEOJ. 1369 N73-31977 N73-31985 AF PEOJ. 3048 N7 3-32 605 N73-32920 AF PBOJ. 3066 N73-32633 H73-32634 H73-33761 AF PEOJ. 4600 B73-32131 AP PEOJ. 6670 H73-32354 AF PROJ. 7064 1173-31934 AF PEOJ. 7065 U7 3-32633 H73-32634 N7 3-32636 AF P80J. 7351 , N73-32135 N73-32383 AF PBOJ. 7930 K73-33157 AF PBOJ. 8219 H7 3- 3 1972 AF PSOJ. 8225 H73-31972 AF-4FOSE-2365-72 J73-44855 AFS PEOJ. 600-72-3 N73-32517 ABO PEOJ. PA038 H73-32632 ABO PBOJ. PB038 H7 3-32632 DA PBOJ. 1F1-62203-A-529 N73-31986 N73-32996 DA PEOJ. 1G1-62207-AA-71 H73-32638 DA&J02-71-C-0066 1173-31986 H73-32996 DAAJ02-72-C-0005 H73-32638 DOT-AS-20024 N73-32632 DOT-FA70BA-2260 N73-31944 DOT-FA70BA-2448 H73-32512 K73-33571 DOX-FA71BA-2637 B73-32971 DOT-FA72BA-2772 H73-32513 DOT-FA72BA-3102 B73-33570 3Pi-B-801284 A73-43327 FA4 PEOJ. 102-150-020 N73-33568 FAi PBOJ. 142-175-020 N73-33569 F29601-71-X-0004 H73-32382 F33615-70-C-1775 N73-31977 F33615-71-C-1134 H73-32383 F33615-71-C-1533 A73-43385 F33615-72-C-1141 A73-44829 F33615-72-C-1162 H73-31972 F33615-72-C-1769 N73-31985 F33615-72-C-2026 H73-32633 N73-32634 F44620-7C-C-0105 H73-32162 NASI-2412 H73-32848 H73-32875 MASd-2472 N73-33919 H73-33920 HAS1-6024 H73-31953 HAS1-10472 A73-44838 NAS1-10635-7 S73-33887 HAS1-11877 A73-44863 HAS2-6473 H73-32905 NAS2-6598 H73-31947 SAS2-6784 N73-31937 NAS2-6969 H73-31945 H73-31946 H4S2-6995 S73-31941 HAS2-7199 H73-32842 N73-32843 BAS3-11216 B73-31930 HAS3-12430 A73-44853 H7 3-32608 NAS3-15324 H73-32610 NAS3-15544 H73-32977 H73-33748 NAS4-1845 B73-33883 BAS7-100 A73-44867 BAS8-25896 H73-32924 SGL-39-009-121 B73-32540 BG1-47-005-050 B7 3-32374 NGE-05-0 17-033 B73-32624 NGE-33-0 11-009 B73-32735 BGB-52- 120-001 B73-31927 HE PSOJ. 061-199 H73-32161 BE PBOJ. 213-072 H73-33381 BE PBOJ. 213-088 B73-32141 BE PROJ. 215-208 B73-31980 BE PBOJ. 259-097 873-32208 BBC A-5228 A73-43205 NSF GI-44 H73-33921 HSP GK-32544 A73-44855 .BSF 6K-35790 A73-44827 H00014-69rC-0460 . . H73-33381 HOOO14-72-C-0102 H73-32161" H00014-72-G-0191 873-32141 H00014-72-C-0306 H73-32208 H00014-72-C-0531 H73-31980 HOOO19-72-C-0084 H73-32384 HOOO19-72-G-O122 H73-32381 H00600-73-C-0562 H73-32390 B-7405-EHG-48 H73-32296 115-17-01-07-00 H73-32515 136-62-01-01-00-21 H73-32970 501-04 H73-33744 501-04-01-01 H73-33181 501-06-05-00 H73-31958 501-24 H73-31932 H7 3-32609 H73-32822 501-24-05-01-00-21 H73-31928 501-26-01-00 N73-31951 501-38-16-00 H73-31956 501-38-18-00 H73-31949 502-22-01-01 H73-31953 502-32-02-03 B73-33887 743-36-22-00 B73-31950 760-02 H73-32973 760-62-01 H73-32975 760-65-01-00-21 H73-31929 760-67-01 H73-31940 769-89-01-00 H73-31939 C-1 1. Report No. NASA SP-7037 (39) 4. Title and Subtitle 2. Government Accession No. AERONAUTICAL ENGINEERING A Special Bibl iography (Supplement 39) 7. Author(t) 9. Performing Organization Name and Address National Aeronautics and Space Administ rat ion Washington, D. C. 20546 12. Sponsoring Agency Name and Address -- 3. Recipient's Catalog No. 5. Report Dale January 197^ 6. Performing Organisation Code 8. Performing Organization Report No. 10. Work Unit No. 11. Contract or Grant No. 13. Type of Report and Period Covered 14. Sponsoring Agency Code IS. Supplementary Notes 16. Abstract This spec! a bibl iography l is ts 417 reports, a r t i c les , and other documents introduced into the NASA sc ient i f ic and technical information system in December 1973. 17. Key' Word! (Suggested by Authof(sJ) Aerodynamics Aeronautical Engineer Aeronautics Bibl iographles 19. Security Ctaalt. (of thl» report) Unc lass i f ied 18. Distribution Statement "9 Unc lass i f ied - Un l im i ted - 20. Security CltnU. (of this page) 21. No. of Pages 22. Price* Unc lass i f ied 131 $3.00 HC For salabv thi National Technical Information Service. Sorinoflaid, Virginia 221S1 U.S. GOVERNMENT PRINTING OFFICE: 1974—739-169/103 PUBLIC COLLECTIONS OF NASA DOCUMENTS DOMESTIC NASA distributes its technical documents and bibliographic tools to ten special libraries located in the organizations listed below. Each library is prepared to furnish the public such services ai reference assistance, interlibrary loans, photocopy service, and assistance in obtaining copies of NASA documents for retention. MASSACHUSETTS Massachusetts Institute of Technology. Cambridge CALIFORNIA University of California. Berkeley COLORADO University of Colorado. Boulder DISTRICT OF COLUMBIA Library of Congress GEORGIA Georgia Institute of Technology. Atlanta ILLINOIS The John Crerar Library. Chicago MISSOURI Linda Hall Library. Kansas City NEW YORK Columbia University. New York PENNSYLVANIA Carnegie Library of Pittsburgh WASHINGTON University of Washington. Seattle NASA publications (those indicated by an "*" following the accession number) are also received by the following public and free libraries: CALIFORNIA Los Angeles Public Library San Diego Public Library COLORADO Denver Public Library CONNECTICUT Hartford Public Library MARYLAND Enoch Pratt Free Library. Baltimore MASSACHUSETTS Boston Public Library MICHIGAN Detroit Public Library MINNESOTA Minneapolis Public Library MISSOURI Kansas City Public Library St. Louis Public Library NEW JERSEY Trenton Public Library NEW YORK Brooklyn Public Library Buffalo and Erie County Public Library Rochester Public Library New York Public Library OHIO Akron Public Library Cincinnati Public Library Cleveland Public Library Dayton Public Library Toledo Public Library OKLAHOMA Oklahoma County Libraries. Oklahoma City TENNESSEE Memphis Public Library TEXAS Dallas Public Library Fort Worth Public Library WASHINGTON Seattle Public Library WISCONSIN Milwaukee Public Library An extensive collection of NASA and NASA-sponsored documents and aerospace publications avail- able to the public for reference purposes is maintained by the American Institute of Aeronautics and Astronautics. Technical Information Service. 750 Third Avenue. New York. New York. 10017. EUROPEAN An extensive collection of NASA and NASA-sponsored publications is maintained by the British Library Lending Division. Boston Spa. Wetherby. Yorkshire. England. By virtue of arrangements other than with NASA, the British Library Lending Division also has available many of the non-NASA publications cited in STAR. European requesters may purchase facsimile copy or microfiche of NASA and NASA-sponsored documents, those identified by both the symbols "#" and "*". from: ESRO/ELDO Space Documentation Service. European Space Research Organization, 1 14, av. Charles de Gaulle. 92-Neuilly-sur-Seine, France. NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON. D.C. 2O546 OFFICIAL BUSINESS PENALTY FOR PRIVATE USE *3OO SPECIAL FOURTH-CLASS RATE BOOK POSTAGE AND FEES PAID NATIONAL AERONAUTICS AND SPACE ADMINISTRATION 4S1 POSTMASTER : If Undeliverable (Section 158Postal Manual) Do Not Retur "The aeronautical and space activities of the United States shall be conducted so as to contribute . . . to the expansion of human knowl- edge of phenomena in the atmosphere and space. The Administration shall provide for the widest practicable and appropriate dissemination of information concerning its activities and the results thereof." —NATIONAL AERONAUTICS AND SPACE ACT OF 1958 NASA SCIENTIFIC AND TECHNICAL PUBLICATIONS TECHNICAL REPORTS: Scientific and technical information considered important, complete, and a lasting contribution to existing knowledge. TECHNICAL NOTES: Information less broad in scope but nevertheless of importance as a contribution to existing knowledge. TECHNICAL MEMORANDUMS: Information receiving limited distribution because of preliminary data, security classifica- tion, or other reasons. Also includes conference proceedings with either limited or unlimited distribution. CONTRACTOR REPORTS: Scientific and technical information generated under a NASA contract or grant and considered an important contribution to existing knowledge. TECHNICAL TRANSLATIONS: Information published in a foreign language considered to merit NASA distribution in English. SPECIAL PUBLICATIONS: Information derived from or of value to NASA activities. Publications include final reports of major projects, monographs, data compilations, handbooks, sourcebooks, and special bibliographies. TECHNOLOGY UTILIZATION PUBLICATIONS: Information on technology used by NASA that may be of particular interest in commercial and other non-aerospace applications. Publications include Tech Briefs, Technology Utilization Reports and Technology Surveys. Details on the availability of these publications may be obtained from: SCIENTIFIC AND TECHNICAL INFORMATION OFFICE NATIONAL A E R O N A U T I C S A N D S P A C E A D M I N I S T R A T I O N Washington, D.C. 20546

Aeronautical Engineering: A special bibliography with indexes, supplement 39

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