IVND. J/S.IV. AERONAUTICAL ENGINEERING A SPECIAL BIBLIOGRAPHY WITH INDEXES Supplement 32 JUNE 1973 https://ntrs.nasa.gov/search.jsp?R=19730021261 2020-03-22T23:09:42+00:00Z ACCESSION N U M B E R RANGES Accession numbers cited in this Supplement fal l w i th in the following ranges: IAA (A-10000 Series) A73-21845—A73-24972 STAR (N-10000 Series) N73-17999—N73-19991 This bibliography was prepared by the NASA Scientific and Technical Information Facility operated for the National Aeronautics and Space Administration by Informatics 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 printing this periodical has been approved by the Director of the Office of Management and Budget through July 1, 1974. NASA SP-7037 (32) AERONAUTICAL ENGINEERING A Special Bibliography Supplement 32 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 May 1973 in • Scientific and Technical Aerospace Reports (STAR) • International Aerospace Abstracts (IAA). Scientific and Technical Information Office JUNE 1973 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION i. 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 372 reports, journal articles, and other documents originally announced in May 1973 in Scientific and Technical Aerospace Reports I STAR I or in International Aerospace Abstracts (I A 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, IAA Entries and STAR Entries,\n 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) < i i All publications abstracted in this Section are available from the Technical Information Service. American Institute of Aeronautics and Astronautics. Inc., (AIAA). 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 $1.00 per microfiche for documents-'identified by the # 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 as indicated: Currently Announced Documents. Facsimile (reproduced on demand) copies are sold for $3.00 plus 25 cents for every 5 pages over 20 pages, effective for all documents having the accession number N72-22991 (the first accession in 1972 STAR 14) or higher. The full price is shown in the citation. Printed NASA Documents. Documents such as NASA Technical Reports, Tech- nical Notes. Special Publications. Contractor Reports. Technical Memorandums (numbered below 50.000). and Technical Translations (below 8,000) are priced at $3.00 for documents of 300 pages or less: $6.00 for those in the 301 -600 page range; $900 for those having 601-900 pages; and individually priced above 900 > pages. Documents available from both the Superintendent of Documents (SOD). Government Printing Office, and from NTIS have the SOD price. All prices are shown in the citation. Documents Announced Between July 1970 and July 1972. All documents with accession numbers between N70-27805 and N72-22990 are sold at the previously announced standard price, whether printed copy or facsimile is supplied. If "Avail: NTIS" appears in the citation, the document is sold at $3.00. Any other price is shown in the citation. Documents Announced Prior to July 1970. A surcharge of $3.00 is applied to each document that.' as of STAR Issue 14. 1972. is two years old from the time of its an- .nouncement. i.e.. to all documents with an accession number lower than N70 27805 (the first accession number in Issue 14. 1970, of STAR), but not to more recently issued documents. Therefore, documents with older accession num- bers of 300 pages or less are priced at a total of $6.00. Since no surcharge is applied to documents with over 300 pages, documents in the 301- to 600;page range are also sold for $6.00 in hard copy, and those in the 601- to 900-page range are sold at $9.00. Those exceeding 900 pages are priced by NTIS on an individual^ basis, except when priced by SOD. These prices do not change with time. (DA microfiche is a transparent 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). Microfiche. Microfiche is available from NTIS at a standard price of 95 cents (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., ,38 cents) over individual requests. Inquiries concerning NTIS Selective Categories 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 SOD price if hard copy is requested. NTIS will also fill microfiche requests, at the standard 95 cent price, for those documents identified by a #symbol.) 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 (HC) 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: National Lending Library. Boston Spa. England. Sold by this organization at the price shown (If none is given, an inquiry should be addressed to NLL ) 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. VI ADDRESSES OF ORGANIZATIONS American Institute of Aeronautics and Astronautics Technical Information Service 750 Third Ave. New York. N.Y. 10017 Commissioner of Patents U.S. Patent Office Washington. D.C. 20231 Engineering Sciences Data Unit Ltd. 251-259 Regent Street London W1 R 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 PO Box 569. SE 1 London. England NASA Scientific and Technical Information Facility P.O. Box 33 College Park. Maryland 20740 National Aeronautics and Space Administration Scientific and Technical Information Office (KSD Washington. D.C. 20546 National Lending Library for Science and Technology Boston Spa. Yorkshire. England 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.O. Box 62 Oak Ridge. Tennessee 37830 Zentralstelle fur Luftfahrtdoku- mentatjon und-lnformation 8 Munchen86 Postfach 880 Federal Republic of Germany VII TABLE OF CONTENTS IAA Entries.. STAR Entries Page .183 .199 Subject Index Personal Author Index . Contract Number Index .A-1 .B-1 .C-1 TYPICAL CITATION AND ABSTRACT FROM STAR NASA SPONSORED DOCUMENT ACCESSION NUMBER- TITLE • AUTHORS CONTRACT- OR GRANT REPORT- NUMBER N73-10027*# Boeing Co.. Wichita. Kans.-« THE SIMULATION OF A JUMBO JET TRANSPORT AIRCRAFT. VOLUME 2: MODELING DATA -C. Rodney Hanke and Donald R. Nordwall. Sep 1970 506 p 2 Vol. ^ .(Contract NAS2-5524) (NASA-CR-114494; D6-30643-Vol-2) Avail: NTIS^HC $27 50 "CSCLOIB—- The manned simulation of a large transport aircraft is described. Aircraft and systems data necessary to implement the mathematical model described in Volume I 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 compared to flight test data and to the results obtained in a training simulator known to be satisfactory. Author AVAILABLE ON MICROFICHE - CORPORATE SOURCE PUBLICATION DATE -AVAILABILITY SOURCE COUTI CODE TYPICAL CITATION AND ABSTRACT FROM IAA NASA SPONSORED DOCUMENT AVAILABLE ON ' MICROFICHE ACCESSION- NUMBER AUTHORS _ -A73-10302 * # Optimum configurations for bangless sonic booms. W, D .^Hayes and F. B. Weiskope, Jr. (Princeton University, Princeton, Nj.). Quarterly of Applied Mathematics, vol. 30, Oct. 1972, p. 311-328. 13refs. Gram No. NGL 31-001-119. A number of optimization problem? 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 features of a non-local isoperimetric relation and of only an upper bound on a control variable. (Author) TITLE — AUTHORS' AFFILIATION • PUBLICATION DATE VIII AERONAUTICAL ENGINEERING A Special Bibliography (Suppf. 32) JUNE 1973 IAA ENTRIES A73-21947 . . , . : , Source selection process faces winds of change. J.T. Stewart (USAF, Aeronautical Systems Div., Wright- Patterson AFB, Ohio). Defense Management Journal, vol. 9, Jan. 1973, p. 13-.16. , > L . ... : • Experiences'! of the Aeronautical Systems Division of the Air Force Systems Command regarding the lightweight fighter acquisi- tion process are used to illustrate efforts to simplify requests for proposals ;(RF,P) and streamline the source selection • process. Straightforward RFPs are discussed together with benefits of limite'd size, data sources, questions of proposal scoring, and aspects of future use. - ' ' ; < . G.-R. A73-21992 Slender delta-wings for future subsonic passen- ger planes (Schlanke Delta-Flugel fur zukiinftige Unterschall- Verkehrsflugzeuge). M. Lichte (Vereinigte Flugtechnische Werke- Fokker GmbH, Bremen, West Germany). Plug Revue/Flugwelt International, Feb. 1973, p. 27-30, 35-37. In German. A73-22165 H Influence of regulated unequal guide-vane spacing on the alternating stress level in the working blades of a compressor (O vliiamii reguliruemoi raznoshagovosti v napra- vliaiushchem apparate na uroven' peremennykh napriazhenii 'v rabochikh lopatkakh kompressora). V. N. Tiulenev and V. A. Skibin (Tsentral'nyi Nauchno-lssledovatel'skii Institut Aviatsionnogo Moto- rostroeniia, Moscow, USSR). Problemy Prochnosti, vol. 4, Dec. 1972, p. 102-105. In Russian. A73-22166 // A case of failure of gas-turbine-engine turbine disks (Ob odnom sluchae razrusheniia turbinnykh diskov gazoturbin- nogo dvigatelia). Chi. L. Svetlakov, A. G. Makhnev, and V. F. Kozhevnikov. Problemy Prochnosti, vol. 4, Dec. 1972, p. 106-110. In Russian. • • ' Cracks were observed to form on the downstream'face of the rotor disk.-of a.low-power single-stage turbine,-.in a grove between two coaxialr circular ridges used to press'fit a! rotor bearing. An experimental investigation is described in which the stress distribu- tion and stress concentration factors at the center of the disk were determined by an optical polarization technique. The results led to an improved disk design in which the groove was eliminated. V.P. A73-22176 ceedings of the 1972 report to the aerospace profession; Pro- Sixteenth Symposium, Beverly Hills, Calif., September 28-30, 1972. Symposium sponsored by the Society of Experimental Test Pilots. Society of Experimental Test Pilots, Technical Review, vol. 11, no. 2, 1973. 256 p. Testing of the F-15 fighter, the autorotation characteristics of the AH-56A compound helicopter, the development and flight test of a digital fly-by-wire F-8, the role of the test pilot in evaluating automatic landing systems, and flight research to develop airworthi- ness standards for civil aircraft receive attention. The flutter-free flight envelope of the STOL Arava aircraft is studied; Results of Apollo 16 are given, and the joint US/USSR docking mission is' discussed, together with the Skylab project and the space shuttle program. • . F.R.L. A73-22177 ' Suryivable flight control system. C. P. Garrison (McDonnell Douglas Corp., St. Louis, Mo.). (Society of Experimental Test Pilots, Symposium, 16th, Beverly Hills, Calif., Sept. 28-30, 1972.1 tSociety of Experimental Test Pilots, Technical Review, vol. 11, no. 2, 1973, p. 1-19. Review of the design and flight test philosophy, present status and future trends of the projected survivable flight control system for fighter aircraft. A description of the test vehicle is followed by a discussion of the results of the flight test program. Observations regarding the future of redundant, full-authority, motion-feedback control systems conclude the review. M.V.E. A73-22178 F-15 air superiority fighter briefing. I. L. Burrows (McDonnell Douglas Corp., Edwards, Calif.). (Society of Experimental Test Pilots, Symposium, 16th, Beverly Hills, Calif., Sept. 28-30, 1972.1 Society of Experiments/ Test Pilots, Technical Review, vol. 11, no. 2, 1973, p. 21-28. Some pertinent events concerning the testing of the F-15 Eagle fighter are reviewed, and the aircraft and its systems are described. The air inlet system consists of a series of ramps plus a bypass door which are automatically scheduled to provide optimum shock wave and airflow control. The control system makes use of a high authority Control Augmentation System (CAS) superimposed on a mechanical system. The systems have been remarkably trouble free, and there have been no forced engine changes. Correlation with wind tunnel data has been good. F.R.L. A73-22179 AH-56A Compound Helicopter autorotation characteristics. D. R. Segner (Lockheed-California Co., Burbank, Calif.): (Society of Experimental Test Pilots, Symposium, 16th, Beverly Hills, Calif., Sept. 28-30, 1972.1 Society of Experimental Test Pilots, Technical Review, vol. 11, no. 2, 1973, p. 29-47. 5 refs. The AH-56A Compound Helicopter is described with emphasis on the .configuration items unique to this vehicle which afject autorotation characteristics. The Beta propeller, rigid rotor, and the wing are discussed in particular detail. The steady state autorotation descent performance is discussed with emphasis on the analysis and piloting task introduced by the addition of the propeller as an added variable in the performance definition. Autorotation entries are discussed in both the helicopter and compound modes of operation. 183 A73-22180 An engineering test pilot description of the flight test build-up program is presented including the logical engineering progression from entries in low power descents to increasingly critical entries, culminating in entries at maximum airspeed. (Author) A73-22180 * Development and flight test of a digital fly-by-wire F8. B. A. Peterson, G. E. Krier, and C. R. Jarvis (NASA, Washington, D.C.). (Society of Experimental Test Pilots, Sym- posium, 16th, Beverly Hills, Calif., Sept. 28-30, 1972.) Society of Experimental Test Pilots, Technical Review, vol. 11, no. 2, 1973, p. 57-71. The objective of the F-8 digital fly-by-wire program is to establish a technology base for the implementation of advanced flight control systems. The central element is the Apollo Lunar Guidance Computer (LGC). This versatile computer ran over 2000 hours in support of fly-by-wire without a failure. Difficulties encountered in the first flights were corrected rapidly and simply by changes in the erasable software memory. Control-configured ve- hicles offer significant weight-saving possibilities. F.R.L. A73-22181 A case for more qualitative flight testing. F. T. Bryan (U.S. Marine Corps., Naval Air Training Command, Patuxent River, Md.). (Society of Experimental Test Pilots, Symposium, 16th, Beverly Hills, Calif., Sept. 28-30, 1972.) Society of Experimental Test Pilots, Technical Review, vol. 11, no. 2, 1973, p. 73-81. In a complex 'numbers' oriented program, the art of qualitative flight testing in describing a new aircraft's flying qualities is essential, for without an accurate word picture of the flying qualities, the 'numbers' only serve to indicate specification compliance. Spin test programs provide excellent examples of qualitative flying qualities descriptions. Static longitudinal stability offers a good example of pilot comments 'documented with quantitative data. Many problems may not require extensive instrumentation systems. F.R.L. A73-22182 The role of the test pilot in evaluating auto landing systems. I. P. S. Norton (Lockheed Aircraft Corp., Burbank, Calif.). (Society of Experimental Test Pilots, Symposium, 16th, Beverly Hills, Calif., Sept. 28-30, 1972.) Society, of Experimental Test Pilots, Technical Review, vol. 11, no. 2, 1973, p. 83-100. Automatic Carrier Landing System (ACLS) operation, theory, and testing sequences are discussed and interpreted. The test pilot is intimately concerned with the cockpit and basic flight navigation instruments and displays since he is continually required to monitor the aircraft's position during the approach. He should have an appreciation for the operation of the entire system and become familiar with the operating characteristics and limitations of each component in this system. Although he is evaluating the aircraft's response and control, he can only observe, not affect it. The most valuable contribution the pilot can make is to offer his judgment and criteria to the engineer. F.R.L. A73-22183 The role of the test pilot in evaluating auto landing systems. II. W. F. Smith (Lockheed Aircraft Corp., Burbank, Calif.). (Society of Experimental Test Pilots, Symposium, 16th, Beverly Hills, Calif., Sept. 28-30, 1972.) Society of Experimental Test Pilots, Technical Review, vol. 11, no. 2, 1973, p. 101-114. In development of an automatic landing system, a test pilot assumes the two primary responsibilities of helping develop the most technically effective system possible and assuring that the system meets the real-life requirements demanded of it by the commercial airNne pilot. Paramount factors that govern the test pilot's assess- ments of the system, are, in order of importance, flight safety, as reflected by reliability and performance characteristics, and maintainability. Of nearly equal concern to the evaluating test pilot, however, is the requirement for optimum flight crew convenience. The growing complexity of advanced and sophisticated commercial aircraft, along with the drive toward full zei j-zero landing opera- tions, demand that every aspect of flight station layout and operating procedure be viewed through the eyes of the airline pilot who must fly the aircraft under all weather conditions on a routine, day-to-day basis. (Author) A73-22184 : Flight research to develop airworthiness standards for civil aircraft. D. A. Tuck (FAA, Washington, D.C.). (Society of Experimental Test Pilots, Symposium, 16th, Beverly Hills, Calif., Sept. 28-30, 1972.) Society of Experimental Test Pilots, Technical Review, vol. 11, no. 2, 1973, p. 115-122. 5 refs. The Headquarters Flight Test Branch of the FAA has been engaged in research programs to gain the knowledge and experience needed to establish the performance and flying qualities certification requirements for the next generation of civil aircraft such as the supersonic transports and STOL aircraft. The roles of the NASA flight simulator for advanced aircraft (FSAA) are described, as well as that of the USAF/Cornell Total in-Flight Simulator (TIPS). F.R'.L. A73-22185 STOL Arava - Flutter-free flight envelope. D. C. Levine (Israel Aircraft Industries, Ltd., Lydda, Israel). (Society of Experimental Test Pilots, Symposium, 16th, Beverly Hills, Calif., Sept. 28-30, 1972.)' Society of Experimental Test Pilots, Technical Review, vol. 11, no. 2, 1973, p. 123-125. The recording and measurement system of the 20-passenger Arava twin-engined STOL transport flutter flight test program is described in detail. The mainstay of the instrumentation system is the accelerometer, and the second important component is a conditioner with a built-in filter mounted on an electronic printed card. The excitation and oxygen systems, and the data reduction and analysis processes are discussed. Flutter flight tests are more hazardous than conventional developmental flights, and special precautions are needed. F.R.L. A73-22197 The nature of a fighter aircraft. P. Sprey. Interavia, vol. 28, Feb. 1973, p. 145-147. The characteristics of an air battle fighter are described. It is pointed out that a very high quality fighter can be built cheaply and easily if it is done correctly. However, despite its great utility in war no really superior fighter aircraft has been produced in the last 15 years by any nation. The basic traits that create a visual air battle fighter are considered, giving attention to lethality, maneuverability, stealth, range, battle persistence, visibility, presence (numbers), resilience, sortie rate, handling qualities, fire control system, and tactical doctrines. G.R. A73-22198 Report on the F-15 programme. I. L. Burrows (McDonnell Aircraft Co., St. Louis, Mo.). Interavia, vol. 28, Feb. 1973, p. 148, 149. The F-15 has a clean gross take-off weight of 40,000 Ib. Power is provided by two YF100 engines, the production version of which will be in the 25,000 Ib thrust class. The air inlet system consists of a series'of ramps, plus a bypass door, which are automatically scheduled to provide optimum shock wave and airflow control. The flight control system is discussed, together with the landing gear, the flaps the cockpit, and the speed brake. Preliminary results obtained with the aircraft are also considered. It was found that the control systems were extremely reliable. Adequate landing capabilities have been demonstrated under most of the failure modes possible within the control systems. G.R. A73-22201 Association Technique' Maritime et Aero- nautique. Session, 72nd, Ecole Nationale Superieure de Techniques Avancees, Paris, France, May 15-19, 1972, Proceedings. Association Technique Maritime et Aeronautique, Bulletin, no. 72, 1972. 616 p. In French. Brazing of special parts in a fluorided reducing atmosphere, self-contained submergeable energy sources, prediction of aeroelastic instabilities, and aspects of rotors and structures of helicopters are considered. Attention is given to drag reduction.by flexible walls and to French projects for hydrofoil vehicles. The transverse flow around an airfoil is calculated, taking account of the exact law of compressibility. A method for experimental study of transonic cascades of blades is developed, and unsteady flow around an airfoil or a cascade is studied. Optimization of gas turbine combustors, application of the finite element method to the study of elastic 184 A73 22216 buckling, and application of a singular perturbation method to the study of beginning cavitation are discussed. F.R.L. A73-22202 Study and realization of special parts for aerospace construction by brazing in a fluorided reducing atmo- sphere (Etude et realisation de pieces speciales de construction aerospatiale par brasage en atmosphere reductrice fluoree). P. Galmiche (ONERA, Chatillon-sous-Bagneux, Hauts-de-Seine, France). (Association Technique Maritime et Aeronautique, Session, 72nd, Paris, France, May 15-19, 1972.) Association Technique Maritime et Aeronautique, Bulletin, no. 72, 1972, p. 81-95; Discussion, p. 96. In French. The principle, general characteristics, and fields of application of the technique of brazing stainless steels in a fluorided atmosphere are discussed. Reducing treatment atmospheres fluorided to the reduc- tion equilibrium of metallic fluorides, most often chromous fluoride, are used. The technique requires an operating temperature of at least 700 C. It is not suitable for ceramic materials or for titanium or zirconium. Results on light refractory materials of impervious honeycomb structure, coatings for turbojet casings, graphite-graphite or graphite-metal assemblies, and on ultrarefractory structure parts in thin corrugated sheets of dispersed-phase alloys are given. F.R.L. A73-22204 Prediction of aeroelastic instabilities in turbines (Prevision des instability aeroelastiques dans les turbo- machines). J. Leclerc (ONERA, Chatillon-sous-Bagneux, Hauts-de- Seine, France). (Association Technique Maritime et Aeronautique, Session, 72nd, Paris, France, May 15-19, 1972.1 Association Tech- nique Maritime et Aeronautique, Bulletin, no. 72, 1972, p. 141-164; Discussion, p. 165. In French. A theoretical study is described which in principle makes it possible to predict a certain type of instability in undetached subsonic flow, and which can characterize the sensitivity to forced excitations while furnishing coefficients of aerodynamic damping. The importance of the concept of damping by interaction of the blades is shown. The problem of the determination of dampings for basic configurations has been solved in a slightly diverted com- pressible two-dimensional flow across an infinite rectilinear grill. Results which are of practical interest are given. F.R.L. A73-22205 Theoretical determination of the character- istics of helicopter rotors (Determination theorique des carac- teristiques des rotors d'helicopteres). R. Hirsch. (Association Tech- nique Maritime et Aeronautique, Session, 72nd, Paris, France, May 15-19, 1972.) Association Technique Maritime et Aeronautique, Bulletin, no. 72, 1972, p. 167-185; Discussion, p. 186-188. In French. The problem of the detailed calculation of the characteristics and performance of a helicopter rotor in horizontal translation is considered, making use of previously developed methods of calcula- tion of free or streamlined propellers. The configuration of the wake and induced velocities are discussed, and simplifying hypotheses are defined. Attention is given to the unsteady character of the problem. A wake model, effects of viscosity on the wake configuration and the circulation, the contribution of unsteady terms in local loads, and comparison of theory and experiment are presented graphically. F.R.L. A73-22206 Dynamic analysis of helicopter structures (Analyse dynamique des structures d'helicopteres). B. Simon (Societe Nationale Industrielle Aerospatiale, Paris, France). (Associa- tion Technique Maritime et Aeronautique, Session, 72nd, Paris, France, May 15-19, 1972.) Association Technique Maritime et Aeronautique, Bulletin, no. 72, 1972, p. 189-204; Discussion, p. 205. 8 refs. In French. Programs for calculation of structures by the displacement method constitute a means of determining the principal vibratory modes. They make possible a preliminary exploration of the dynamic characteristics of helicopters before the structure is available for test. Based on the theorems of energy applied to a modelization by finite elements, a general calculation program was developed. The calcula- tion is applied to an existing helicopter, and results are compared with those obtained from vibration tests on the ground. F.R.L. A73-22210 Calculation of the transonic flow around an airfoil, taking account of the exact law of compressibility (Calcul de I'ecoulement transonique autour d'un profil en admettant la loi de compressibility exacte). T. S. Luu, G. Coulmy, and A. Dulieu (CNRS, Laboratoire d'lnformatique pour la Mecanique et les Sciences de I'lngenieur, Chatillon-sous-Bagneux, Hauts-de-Seine, France). {Association Technique Maritime et Aeronautique, Session, 72nd, Paris, France, May 15-19, 1972.) Association Technique Maritime et Aeronautique, Bulletin, no. 72, 1972, p. 269-281; Discussion, p. 282-284. 12 refs. In French. The equation governing the velocity potential is established in a Poisson form, and the possibility of creating this potential by a distribution of singularities which allows translating the conditions to the limits by integral equations is demonstrated. A practical metho'd of solution of these equations by discretization of the distributions of singularities is developed. Different examples of application are given both for subcritical and supercritical regimes without shock, which makes it possible to appraise the validity and the possibilities of the method. F.R.L. A73-22212 Unsteady nonlinear flow around an airfoil or a blade cascade with emission of turbulent vortices (Ecoulement instationnaire non lineaire autour d'un profil ou d'une grille d'aube avec emission de tourbillons libres). T. S. Luu (CNRS, Laboratoire d'lnformatique pour la Mecanique et les Sciences de I'lngenieur, Chatillon-sous-Bagneux, Hauts-de-Seine, France) and J. Corniglion (Centre d'Etude Technique des Industries Metallurgiques, Paris, France). (Association Technique Maritime et Aeronautique, Session, 72nd, Paris, France, May 15-19, 1972.) Association Technique Maritime et Aeronautique, Bulletin, no. 72, 1972, p. 301-313; Discussion, p. 314, 315. 9 refs. In French. As a first phase of the program relating to passing blades with vortex escape, the problem of bidimensional flow with potential of an incompressible fluid around airfoils or cascades activated by any motion, in the case of a vortex escape, is treated. A method of calculation is developed which makes it possible, by the kinematic and dynamic application of the Kutta-Joukowsky condition, to determine the intensity of free vortices emitted at the trailing edge, and to determine the velocity of escape which is parallel either with the upper or lower surface of the wing, according to the sign of the vortex. F.R.L. A73-22213 Optimization of combustors of gas turbines (Optimisation des foyers de turbines a gaz). M. Barrere (ONERA, Chatillon-sous-Bagneux, Hauts-de-Seine, France). (Association Tech- nique Maritime et Aeronautique, Session, 72nd, Paris, France, May 15-19, 1972.) Association Technique Maritime et Aeronautique, Bulletin, no. 72, 1972, p. 337-363; Discussion, p. 364-368. 14 refs. In French. Study of the optimal combustor is carried out as a function of the length of the combustor and the efficiency of combustion, the fall of cutoff pressure across the combustor, wall cooling, and pollution. Two types of combustor are examined: one corresponds to the conventional type which equips present turbojets; the other approximates combustors used in liquid propellant rocket propul- sion. By schematization of combustion phenomena, the geometry of the combustion is determined as a function of the minimal toss of charge. The parameters acting on the efficiency of film cooling are considered. A combustion arrangement reducing the concentration of polluting substances is proposed. F.R.L. A73-22216 Aviation and atmospheric pollution - The real dimension of the problem and its solutions (Aviacion y contami- 185 A73-22233 nation atmosferica - Dimension real del problema y soluciones). J. A. Martinez Cabeza. Revista de Aeronautics y Astronautics, vol. 33, Jan. 1973, p. 5-20. I n Spanish. It is pointed out that the contribution of aviation to total planetary pollution is about 1 per cent. The percentage of aircraft- produced pollution is, of course, much higher at the airport. However, an investigation recently conducted at the London airport of Heathrow showed that the level of pollutants present would be considered admissible by any municipal standards. The principles of operation of a jet engine are discussed, together with the generation of engine emissions. The amount of air pollutants produced by an aircraft under certain performance conditions is shown in a graph for the time from 1950 to 1975. It is found that a very substantial decrease in pollutant emission was obtained with the introduction of more advanced types of engines. Approaches for reducing the amounts of harmful engine emissions even further are considered, and the consequences of the use of higher altitudes by the SST are examined. G.R. A73-22233 # Aircraft parameter identification - A varia- tions! procedure. R. E. Bach, Jr. (Northeastern University, Boston, Mass.), S. E. Post (U.S. Army, Air Mobility Research and Develop- ment Laboratory, Moffett Field, Calif.), and J. E. Tucker (U.S. Naval Postgraduate School, Monterey, Calif.). In: Annual Allerton Con- ference on Circuit and System Theory, 10th, Monticello, III., October 4-6, 1972, Proceedings. Urbana, Univer- sity of Illinois, 1972, p. 507, 508. Construction of a smoothing algorithm for aircraft parameter identification which is based on a variational optimization procedure. A convergent iterative procedure for estimating the desired param- eters from measurements which are such as to minimize a certain criterion is outlined, and a strategy for estimation of the states, parameters, and noise statistics is formulated. A.B.K. A73-22234 # Application of four methods for approxi- mating optimal feedback gains. J. H. Burghart (New York, State University, Buffalo, N.Y.), In: Annual Allerton Conference on Circuit and System Theory, 10th, Monticello, III., October 4-6, 1972, Proceedings. Urbana, University of Illinois, 1972, p. 520-529. 14refs. Investigation of the effects of various criteria for adjusting optimal feedback gains in the presence of parameter variations requiring such adjustment. Four different criteria for obtaining polynomial approximations for the optimal gains are considered. Three of these criteria are based on values of the cost function for various conditions of parameter va iation, while the fourth is a conventional curve-fitting criterion tor matching the optimal gains. The four criteria are applied to an example involving the longitudinal control of the X-15 aircraft during reentry. The results for all four criteria are superior to those of the functional expansion method. Conclusions regarding the effectiveness of the various criteria and the differences resulting from their application are discussed. A.B.K. A73-22349 # The aircraft and its natural and climatic environment (Samolet i prirodno-klimaticheskie usloviia). K. M. Shpilev and A. B. Kruglov. Moscow, Voenizdat, 1972. 176 p. 46 refs. In Russian. The effects of environmental factors on the operational fitness, systems performance, and maintenance and servicing requirements of modern aircraft are discussed on the basis of available Soviet and worldwide data. Particular attention is given to the adverse influences of the environment of other geographic regions in which aircraft designed for Europe are operated. Difficulties are considered which may arise when aircraft of European make are operated in polar regions, in African and Asian deserts, and the tropical portions of the Pacific and Atlantic. The adverse factors considered include air temperature and humidity, solar activity and insolation, atmospheric electricity and precipitation, topsoil strength and composition, dust and wind, topsoil and water salinization, and biological factors. Design and maintenance suggestions are given to cope with these problems. V.2. A73-22375 # Transport aircraft maintainability (Eksplua- tatsionnaia tekhnologichnost' transportnykh samoletov). N. N. Smirnov and I. K. Mulkinzhanov. Moscow, Izdatel'stvo Transport, 1972. 208 p. 49 refs. In Russian. Reliability, maintainability and servicing problems of existing and visualized transport aircraft are discussed with the emphasis on the reduction of labor, cost and time required for maintenance of operating aircraft without a quality tradeoff. Maintainability criteria are suggested for various inspection, and repair operations on aircraft components and systems. The topics also include the idle time due to maintenance work, maintenance cycle schedules, and maintenance procedures and practices adopted abroad. The theoretical and practical aspects of transport aircraft maintainability are considered. The book is intended for maintenance engineers and designers in the' aviation industry. V.Z. A73-22432 # Fluctuating lift and moment coefficients for cascaded airfoils in a nonuniform compressible flow. S. Fleeter (General Motors Corp., Detroit Diesel Allison Div., Indianapolis, Ind.). Journal of Aircraft, vol. 10, Feb. 1973, p. 93-98. 10 refs. USAF-supported research. The effects of compressibility on both the fluctuating lift and the fluctuating moment coefficients for cascaded airfoils due to an upstream nonuniformity are determined by obtaining a solution to the time-dependent, compressible, two-dimensional partial dif- ferential equation which describes the perturbation velocity potential. This is accomplished through an application of Fourier- transform theory, with the resulting integral solution equation evaluated numerically by a matrix-inversion technique. The results presented show the variation in both the fluctuating lift and the fluctuating moment coefficients over the mean cascade inlet Mach number range of 0.0 (incompressible) to 0.9 with the cascade solidity, cascade stagger angle, interblade phase angle and reduced frequency as parameters. (Author) A73-22433 # Calculation of forces on stores in the vicinity of aircraft. H. Serbin. Journal of Aircraft, vol. 10, Feb. 1973, p. 123, 124. The crossflow velocity field around the isolated aircraft is calculated. The cross section of the aircraft is mapped into a slit by a sequence of conformal transformations. The store itself is regarded as a slender body in the (nonuniform) flowfield of the aircraft. The vortices trailing from the lifting surfaces on the store are taken into account. The forces and moments are found by suitable integrations of the loading. G.R. A73-22434 ft Toward simpler prediction of transonic airfoil lift, drag, and moment. F. 0. Smetana and D. P. Knepper (North Carolina State University, Raleigh, N.C.). Journal of Aircraft, vol. 10, Feb. 1973, p. 124-126. 8 refs. A method utilizing semiempirical correlations of experimental data has been employed to predict the aerodynamic characteristics of wings in the case of operation at transonic speeds. The procedure includes a computation of the pressure distribution at M = 0, a computation of the pressure distribution at M = 1.0, a computation of pressure variations, and a computation of Reynolds number at the shock. G.R. A73-22435 # Correlation of wing-body combination lift data. L. M. Nicolai and F. Sanchez (U.S. Air Force Academy, Colorado Springs, Colo.). Journal of Aircraft, vol. 10, Feb. 1973, p. 126-128. 9 refs. An experimental investigation conducted shows that an equa- tion concerning the wing-body lift interference factor indicated by the theory of Pitts, Nielsen, and Kaattari (1959) is indeed valid. Delta wing-body combinations of various aspect ratio were studied at subsonic Mach numbers and supersonic Mach numbers of 1.44, 2.48, and 3.48. All of the wing-body configurations considered in the investigation were uncambered and untwisted. G.R. 186 A73-22569 A73-22447 ft Aeromechanical measurements in free flight on piloted aircraft (Masuratori aeromecanice in zbor liber pe avioane pilotate). A. Marinescu (Institutul de Mecanica a Fluidelor si Constructii Aerospatiale, Bucharest, Rumania). Transporturi Auto, Navale si Aeriene, vol. 2 (19), Oct. 1972, p. 546-554. 5 refs. In Rumanian. Review of methods of measuring the essential parameters of piloted aircraft in transonic flight. The methods discussed concern the measurement of pressure with the aid of pilot tubes and altimeters, the measurement of temperature and speed, the measure- ment of thrust by measuring the total static pressure and the temperature in the neighborhood of the engine jet or by measuring the static pressure in the free stream and the total static pressure and the temperature in the outlet section of the engine jet, the measurement of drag with the aid of accelerometers, the measure- ment of lift, and the measurement of the aircraft control and stability characteristics. A.B.K. A73-22502 A new digital pressure transducer. R. C. Meyer (United Aircraft Corp., Hamilton Standard Div., Windsor Locks, Conn.). In: Instrument Society of America, Annual Conference, 27th, New York, N.Y., October 9-12, 1972, Proceedings. Part 2. Pittsburgh, Instrument Society of America, 1972, p. 601.1-601.15. This paper discusses the design features of the Hamilton Standard digital pressure transducer. The vibrating cylinder pressure sensing element and its theory of operation are explored - i.e., how pressure changes the natural vibratory frequency of the sensing element and how this is converted into an electrical response signal. The many variations of signal output available from the digital transducer are discussed. Two interesting applications are discussed wherein the transducer was used to make a difficult measurement. One is that of nuclear reactor containment leakage testing, and the other is the use of the transducer in air inlet controls for high performance aircraft. (Author! A73-22504 * Development of a high temperature fatigue sensor. T. L. Wells, R. F. Canon, G. C. Rolls (Tracor, Inc., Austin, Tex.), and E. J. Wilson (NASA, Flight Research Center, Edwards, Calif.). In: Instrument Society of America, Annual Conference, 27th, New York, N.Y., October 9-12, 1972, Proceedings. Part 2. Pittsburgh, Instrument Society of America, 1972, p. 603.1-603.6. 11 refs. Contract No. NAS4-1796. An experimental program was conducted to extend the Tracor Safety Gauge (patent pending) to elevated temperature service. The Safety Gauge is based on a conductive composite device which can be fabricated to function as a fatigue sensor that undergoes an irreversible resistance increase which results from cumulative strain damage. Prototype sensors were developed which appear capable of 1000 deg F operation for short periods of time (approaching one hour); however, bonding difficulties currently limit their use to about 775 deg F. The resistance change of the sensor was generally on the order of 400% or greater as the fatigue life of a titanium alloy (Ti-5AI-2.5Sn) test specimen was approached. (Author) A73-22506 Pre-fab strain gage bridges. L. A. Watson (Vought Aeronautics Co., Dallas, Tex.). In: Instrument Society of America, Annual Conference, 27th, New York, N.Y., October 9-12, 1972, Proceedings. Part 2. Pittsburgh, Instru- ment Society of America, 1972, p. 615.1-615.4. Description of a system of strain gage bridge buildup designed to overcome such problems as those associated with inaccessibility to installation area, time schedules that do not permit the necessary downtime for instrumentation, and parts that are difficult to remove for instrumentation. Called the prefabricated strain gage bridge, the system has been successfully applied to various tasks involving time and environment restrictions. These tasks include horizontal tail vibration tests, wing load surveys, and tail boom gage installations. M.V.E. A73-22519 High modulus organic fibre composites in aircraft applications. J. W. Moore and D. L. G. Sturgeon (Du Pont de Nemours and Co., Inc., Carothers Research Laboratory/Wilmington, Del.). Composites, vol. 4, Jan. 1973, p. 34-38. 7 refs. PRD-49 is a high strength, high modulus, low density organic fiber developed by Du Pont, that combines the processibility normally associated with conventional textiles with the plastics- reinforcing performance previously available only with inorganic fibers such as glass and graphite. It is commercially available in the form of continuous yarns, rovings, fabrics and resin preimpregnated products including collimated tapes. PRD-49 is nonconductive, flame resistant, has high chemical and thermal stability, outstanding creep rupture characteristics, good fatigue performance, notch insensitivity and damage tolerance provided by its polymeric character. (Author) A73-22524 STOL Seminar, St. Louis, Mo., March 24, 1972, Record. Seminar sponsored by the Chamber of Commerce of Metropolitan St. Louis and St. Louis Research Council. St. Louis, Mo., St. Louis Regional Commerce and Growth Association. 1972. 118 p. $7.50. The prospects of short takeoff and landing aircraft and the promise they hold for future air travel are considered. Presently over fifty per cent of the air passenger traffic operates between points within a 500-mile radius of St. Louis. STOL is being designed to meet this short haul service. A broad overview of the present state of development of STOL is given and the R and D policies of the various countries as they may relate to financing or encouraging future STOL development are discussed. It is shown how the aerospace industry can provide the air vehicles and assist in the development of the short haul air transportation system which will interface with the total air and ground system of the future. G.R. A73-22567 ff Computer calculation of the characteristics of multistage gas turbines (Raschet na EVM kharakteristik mnogo- stupenchatykh gazovykh turbin). G. V. Zhukovskii, lu. N. Malyshev, and lu. I. Novichkov. Energomashinostroenie, vol. 18, Oct. 1972, p. 1-3. 10 refs. In Russian. Description of a computer program for calculating the flow and power characteristics of multistage gas turbines in both nominal and variable regimes. In the computer calculations the parameters along the mean radii of the stages are considered. In each of the calculated regimes a direct problem is solved for a given flow rate, a given rpm, and given inlet gas parameters. Using the solution obtained by successive approximations, the gas parameters at the turbine outlet are determined, and if analysis shows it to be necessary, a correction is made to the inlet parameters or the flow rate, and the calculation is repeated. A.B.K. A73-22568 it Thermal stresses in cooled gas turbine blade foils and roots with allowance for thermoelastic effects (Tempera- turnye napriazheniia v pere i khvostovike okhlazhdaemoi rabochei lopatki gazovoi turbiny s uchetom ikh vzaimnogo termouprugogo vliianiia). N. M. Gorelkin and I. A. Bogov. Energomashinostroenie, vol. 18, Oct. 1972, p. 10-12. 5 refs. In Russian. A73-22569 # Improvement of the calculation of the guide vanes of centrifugal pumps (Sovershenstvovanie rascheta napravlia- iushchikh apparatov tsentrobezhnykh nasosov). N. S. lalovoi. Ener- gomashinostroenie, vol. 18, Oct. 1972, p. 14-17. 11 refs. In Russian. Description of a method of calculating the inlet cross sections and the diffuser channels of guide vanes with allowance for nonuniformity and unsteadiness of the flow in the gap between the impeller and the guide vanes. Particular attention in this method is given to the problem of the correct choice of the relation between the expansion stage in the diffuser and the return channel and to the problem of choosing the basic geometrical dimensions of the diffuser channels of the guide vanes from the condition that the losses in the guide vanes be minimized. A.B.K. 187 A73-22715 A73-22715 ff Experimental method for analyzing the un- steady flow in a transonic aircraft compressor (Methode d'analyse experimentale de I'ecoulement instationnaire dans un compresseur aeronautique transsonique). R. Larguier (ONERA, Chatillon-sous- Bagneux, Hauts-de-Seine, France) and C. Ruyer. La Recherche Aerospatiale, Nov.-Dec. 1972, p. 353, 354. In French. Research supported by the Direction des Recherches et Moyens d'Essais. ; A method of probing the internal flow of a turbine to demonstrate its unsteady character is described. Information is acquired starting with a cylindrical, adjustable anemometric probe, the sensor being a piezoelectric pressure detector. The data process- ing includes extraction of the periodic part of the signals which are related to the passage of the rotor blades, after elimination of the random component. A precise description of the periodic fluctua- tions of the flow can be obtained. F.R.L. A73-22718 Current predictive models of the dynamic environment of transportation. J. T. Foley, M. B. Gens, and C. F. Magnuson (Sandia Laboratories, Albuquerque, N. Mex.). Journal of Environmental Sciences, vol. 16, Jan.-Feb. 1973, p. 18, 23-28. 31 refs. AEC-supported research. Models are developed which predict the dynamic environment experienced by cargo during transportation. A model is defined as a description of expected acceleration amplitudes vs frequency derived from measured data. Thus, a predictive model is a description of an environment which may be used to predict the levels of a specific environment which may be encountered at a given frequency or in a frequency band. In all the models described, level of environment is given as zero to peak acceleration. The dynamic environment in the transportation environment is complex. In the method of description it consists of a base of near-Gaussian, broadband, random, con- tinuous excitation with many types of discrete excitations either superimposed or intermixed with it. F.R.L. A73-22830 * Potentials and problems of hydrogen fueled supersonic and hypersonic aircraft. R. D. Witcofski (NASA, Langley Research Center, Hampton, Va.). In: Intersociety Energy Conversion Engineering Conference, 7th, San Diego, Calif., September 25-29, 1972, Proceedings. Washington, D.C., American Chemical Society, 1972, p. 1349-1354. 19 refs. A73-22947 Measurements of some hydrogen-oxygen- nitrogen compounds in the stratosphere from Concorde 002. J. E. Harries (National Physical Laboratory, Teddington, Middx., England). Nature, vol. 241, Feb. 23, 1973, p. 515-518. 30 refs. Research supported by the Committee on the Meteorological Effects of Stratospheric Aircraft. A73-22954 On the convergence of the Rayleigh-Ritz method in plane subsonic flow. H. Rasmussen (Danmarks Tekniske Hojskole, Lyngby, Denmark). Institute of Mathematics and Its Applications, Journal, vol. 11, Feb. 1973, p. 1-8. 9 refs. Research supported by the Science Research Council. The boundary value problem for plane compressible flow past an aerofoil can be formulated as a variational problem. It is shown that for subsonic flow approximate solutions obtained by the Rayleigh-Ritz method converge uniformly to the exact solution provided that the aerofoil is sufficiently smooth and the coordinate functions are properly chosen. The analysis applies also to certain other two-dimensional variational problems. (Author) A73-22975 # Visual systems for indicating approach slope during aircraft landing (Sisteme vizuale pentru indicarea pantei de apropiere la aterizarea avioanelor). E. Hladiuc. Transporturi Auto, Navale si Aeriene, vol. 2(19), Nov. 1972, p. 607-611. In Rumanian. Brief review of a widely used visual approach slope indicator system (called VASIS) and of several modifications of the basic system. The VASIS system is placed along the sides of the runway, in the threshold zone, and is intended for executing final approaches, thus enabling the pilot to maintain a correct predetermined slope and preventing landings which are too short or too long. This system, as well as the VASIS system with three bars and the T-VASIS system, are designed for use at airports serving international traffic. The use of any particular one of these systems is dictated by the type of aircraft and, in particular, by the vertical distance between the pilot's eyes and the wheels during the roundoff phase. Each of these systems in turn has a simplified counterpart called AVASIS, AVASIS with three bars, and AT-VASIS, respectively. These latter systems are designed for airports serving domestic traffic. A.B.K. A73-23036 Mode of thickening of a low morning con- vective layer in clear sky (Mode d'epaississement d'une basse couche convective matinale en ciel clair). R. Rosset, P. Mascart, H. Isaka, and R.-G. Soulage (Clermont-Ferrand, Universite, Aubiere, Puy-de-D6me, France). Academie des Sciences (Paris), Comptes Rendus, Serie B - Sciences Physiques, vol. 276, no. 6, Feb. 5, 1973, p. 223-226. 5 lefs. In French. A study of the characteristics of the upper front of the convective layer and of its ascent in the course of a morning was carried out. Thermodynamic measurements (pressure, temperature, humidity) and dynamic measurements were carried out using a light airplane. The airplane executed a succession of flights at various levels between the ground and 2000 m from dawn to the end of the morning. The convective low layers of the atmosphere appear to present in their upper part a 'convective front' which ascends in 'jumps,' at least in certain cases, depending on the stability and turbulence of thin sheets of the stable layer which it encounters. F.R.L. A73-23089 Flowfield calculations for some supersonic sections with ducted heat addition. E. G. Broadbent (Royal Aircraft Establishment, Farnborough, Hants., England). Ingenieur-Archiv, vol. 42, no. 2, 1973, p. 89-103. 5 refs. A previous investigation of external heat addition at a free stream Mach number of 7.5 and in the flowfield of selected two-dimensional sections showed that, although the net pressure drag could be reduced, it was difficult to cancel it altogether. The present investigation shows how the use of a cowl allows this to be achieved with something to spare and how, if two intake shocks are used (rather than one), sectional lift coefficients of more than 0.07 can be attained at propulsive efficiencies of about 40%. The main parameter varied is the duct slenderness. • (Author) A73-23106 ft Graphoanalytic method of calculating plane potential flows (Metod grafoanaliticheskogo rascheta ploskikh potentsial'nykh techenii). A. L. Loktev. Akademiia Nauk SSSR, Izvestiia, Energetika i Transport, Sept.-Oct. 1972, p. 113-121. In Russian. An equation of a flow velocity equipotential is derived from an equation of a flow velocity potential which disregards the flow compression. A procedure based on a solution to the equation of equipotential is derived for the calculation of the characteristics of a plane potential flow in a flat channel of arbitrary width with an abrupt change in the wall curvature. Theoretical considerations are given concerning the applicability of this technique to turboengine ducts and to bodies in subsonic flows. V.Z. A73-23120 Aerial targets in use in the UK. J. S. Price (Ministry of Defence, London, England). (Royal Aeronautical Society, Symposium on Drones and Targets, London, England, Feb. 10, 1972.1 Aeronautical Journal, vol. 77, Jan. 1973, p. 1-3. Aerial targets may be converted aircraft, specially developed pi lot less drones, or towed targets. When airborne targets are used in assessing the performance of a weapons system two essential features are that the target be compatible with the guidance system, and that a scoring system be provided to assess the effectiveness of the firing. 188 A73-23255 If an airborne target is to exercise the weapons system adequately, it must have a radar signature which is comparable with the real thing, hence the radar echo must be amplified. F.R.L. A73-23121 The Stiletto project. F. P. Youens (Short Brothers and Harland, Ltd., Belfast, Northern Ireland). (Royal Aeronautical Society, Symposium on Drones and Targets, London, England, Feb. 10, 1972.) Aeronautical Journal', vol. 77, Jan. 1973, p. 3-15. The Stiletto air-launched supersonic target developed for Uk ranges is based on the American AQM 37A target. The AQM 37A is an expendable air launched vehicle powered by a liquid bipropellant rocket motor. The majority of AQM 37A operations are carried out using one of a number of possible trajectories, the appropriate program settings being made before the launch aircraft takes off. The main differences between the AQM 37A and Stiletto stem from three causes: (1) additional or alternative radio and radar equipment for compatibility with UK range equipment or with particular missiles, (2) changes in trajectory and flight termination procedures, and (3) improvements to enable specific trajectories to be flown to a higher degree of accuracy. F.R.L. A73-23122 The Turana drone system. S. S. Schaetzel (Hawker de Havilland Australia Pty., Ltd., Lidcombe, New South Wales, Australia). (Royal Aeronautical Society, Symposium on Drones and Targets, London, England, Feb. 10, 1972.1 Aeronautical Journal, vol. 77, Jan. 1973, p. 15-24. Preceding Australian activity on drones and guided weapons is briefly outlined, since the approach to various problems of the Turana system and the solution of certain difficulties depended on the experience gained with the Jindivik, Malkara, and Ikara. During development trials were carried out which proved the basic Turana performance and validated the simulation model. Turana was designed as a naval target drone capable of exercising the guns and guided weapons of Australian naval vessels. It is described in detail, and the method of operation is outlined. Turana may be launched from an Ikara ship launcher or from a simple portable lightweight launcher on board ship or on the ground. F.R.L. A73-23123 Co-existence of scheduled and charter services in public air transport. J. G. Thomka-Gazdik. Aeronautical Journal, vol. 77, Jan. 1973, p. 32-40. 15 refs. It is considered that there is a need to provide low cost air transportation for the substantial segment of the traveling public which is finding its requirements met by the so-called charter services. Equally there is a need to maintain regular line services on which governments, trade, and commerce inevitably rely. It is suggested that it is not feasible to regulate bilaterally two-thirds of public transport (scheduled services) while leaving the remainder under unilateral supervision or uncontrolled. Governments have a responsibility to devise a coherent and satisfactory framework for the regulation of all international air services. F.R.L. A73-23125 The rolling up of a trailing vortex sheet. R. R. Clements and D. J. Maull (Cambridge University, Cambridge, England). Aeronautical Journal, vol. 77, Jan. 1973, p. 46-51. 8 refs. Research supported by the Science Research Council. The way in which the vortex sheet can roll up under different loading conditions was studied. The investigation was oriented towards finding circulation distributions which alter the rolling up characteristics of the sheet in such a way as to retard the rolling up and decrease the vorticity finally contained in such rolled up vortex cores. The calculations of Westwater (1935) form the basis for the study. It is shown that improvements of the order of 13 to 15% in the strength of the tip vortices may be achieved for incurred drag penalties as low as 5%. F.R.L. A73-23224 ff Fundamentals of aviation (Osnovy aviatsii). G. A. Nikitin and E. A. Bakanov. Moscow, Izdatel'stvo Transport, 1972. 280 p. 15 refs. In Russian. The development of aviation is briefly reviewed, and the fundamentals of aerodynamics and flight theory of airplanes and helicopters are discussed. Various aircraft designs and designs of their principal components (wings, tail units, fuselages, landing gears) are studied, together with helicopter and VTOL and STOL aircraft designs. The theory of aircraft piston and jet engines is outlined. Aircraft deicing systems, hydraulic systems, electrical and communi- cations systems, and the principal aircraft instruments are examined. V.P. A73-23242 ff Emission spectrographic analysis of used aero engine oil - A tool of maintenance. R. S. Arbuckle (Canadian Armed Forces, Toronto, Canada) and G. B. Crump (Shell Research, Ltd., Chester, England). In: International Federation of Airworthiness Technology and Engineering, Symposium, Tunbridge Wells, Kent, England, August 31-September 2, 1972, Proceedings. Kingston on Thames, Surrey, England, International Federation of Airworthiness Technology and Engineering, 1972, p. 4.1-4.4. The scientific background of the Canadian Armed Forces Spectrometric Oil Analysis Program (SOAP) is described, and it is shown how the laboratory results have been applied to the detection of incipient engine failures. The wear metals measured routinely are iron, magnesium, copper, chromium, and silver. In order to ensure that the spectrographic measurements are as meaningful as possible, the used engine oils are analyzed alongside standards prepared by dissolving previously analyzed salts of the metals in question in synthetic ester oils of the type used in the J.79 engines. Of the first thirteen engines investigated from the commencement of the program, eleven supported the recommendation of the SOAP. Some case histories are given. F.R.L. A73-23243 ff Economic management. G. D. Peacock (Monarch Airlines, Ltd.; Airline Engineering, Ltd., Luton, Beds., England). In: International Federation of Airworthiness Technology and Engineering, Symposium, Tunbridge Wells, Kent, England, August 31-September 2, 1972, Proceedings. Kingston on Thames, Surrey, England, International Federation of Airworthiness Tech- nology and Engineering, 1972, p. 10.1-10.4. The subject is dealt with in terms of the operational and commercial pattern, the basic philosophy and objectives of produc- tion planning and control, the application of the principles to Airline Engineering Ltd., and budget control and analysis of results. It is recommended that every individual job be timed and controlled, and that material costings should never get more than twenty-four hours behind/ F.R.L. A73-23245 ff Air-traffic-control magnetic tape recorders in civil aviation (Dispetcherskie magnitofony grazhdanskoi aviatsii). V. K. Kachan, V. V. Sokol, and lu. V. Zinenko. Moscow, Izdatel'stvo Transport, 1972. 167 p. 29 refs. In Russian. Description of the design features and principles of operation of multichannel magnetic tape recording/reproducing equipment used in civilian ATC centers to monitor and preserve speech communica- tions between ground-based controllers and aircraft crewmembers. An initial exposition of magnetic recording theory covers funda- mentals of field impression on magnetic media, dc and ac magnetic biasing, signal reproduction, frequency compensation, head construc- tion, and tape transport design. The main text offers compre- hensively described circuit diagrams, mechanical design layouts, and operational specifications for individual subsystems and components of specific tape recording equipment. The provision of reference time-base channels is explained in terms of equipment and proce- dures employed. T.M. A73-23255 Artificial slow crack growth under constant stress - The R-curve concept in plane stress. D. Broek (Nationaal Luchtvaartlaboratorium, Amsterdam, Netherlands). Engineering Fracture Mechanics, vol. 5, Feb. 1973, p. 45^53. 8 refs. 189 A73-23293 A test program in which crack extension by means of sawing while the specimen was under constant load is described, and results are compared with conventional residual strength data. It was found that sawing under load could be continued far beyond the length of the crack that should be critical at the applied stress (on the basis of the residual strength curve). An energy-balance diagram is developed in terms of the energy release rate G and the crack growth resistance R. The shape of the R-curve can be determined experimentally from the G-values during slow growth, since the energy balance requires that G = R during stable crack propagation. The energy concept (R-curve) is compatible with the fact that crack growth under constant load leads to a larger critical crack length than monotonic loading. F.R.L. A73-23293 Advances in directional solidification spur usage in turbine airfoil shapes. D. N. Duhl, J. S. Erickson, and C. P. Sullivan (United Aircraft Materials Engineering and Research Labora-' tory. East Hartford, Conn.). Metal Progress, vol. 103,'Mar. 1973, p. 38-40. Discussion of a high rate solidification process which was developed to increase casting output in the production of advanced air-cooled turbine airfoils for commercial and military applications. Increased solidification rates are achieved in this process by employing a mold translation technique to enhance heat transfer. A multipart open-ended investment casting mold is attached to a water-cooled copper chill plate and is placed within a single-zone induction-heated cylindrical graphite susceptor. Hafnium additions to nickel-base superalloys enhance transverse ductility, particularly at 1,400 F. It is anicipated that the new process and Hf additions will be advantageous in the development of a wide variety of advanced alloy systems. . V.Z. A73-23295 Forging process halves material requirements. Metal Progress, vol. 103, Mar. 1973, p. 49, 50. Discussion of a gatorizing process for forging titanium-alloy and superalloy jet engine parts. The process takes advantage of the superplasticity exhibited by these materials under controlled temperature-strain rate conditions. Lower amounts of input material, reduced machining, one-step forging, and relatively easy-to-meet equipment requirements are noted as the advantages of this process. V.Z. A73-23296 Protecting metals in corrosive high- temperature, environments. F. M. Miller and N. T. Bredzs (Wall Colmonoy Corp., Detroit, Mich.). Metal Progress, vol. 103, Mar. 1973, p. 80, 82-84. Discussion of a group of fusion-bonded coatings - Nicrocoat materials - which proved effective in improving the performance and service life of jet engine components and in the economical salvaging of damaged parts. The coatings, applied to lower-cost base metals, are also potential alternatives to expensive superalloys in automotive gas-turbine, thermal-reactor, and exaust system parts. V.Z. A73-23360 # The efficiency of using the boundary layer as the working fluid (Ob effektivnosti ispol'zovaniia pogranichnogo sloia v kachestve rabochego tela). I. P. Mel'nichenko (Akademiia Nauk Ukrainskoi SSR, Institut Matematiki, Kiev, Ukrainian SSR). Prikladnaia Mekhanika, vol. 8, Oct. 1972, p. 129-132. In Russian. Determination of the efficiency of using the boundary layer as the working fluid in a ramjet engine in order to achieve high aircraft speeds. A comparison is made between a structure which uses the boundary layer as the working fluid and a structure which draws the working fluid into the nose section. Expressions are obtained for the external efficiency of both types of structures as a function of the boundary layer parameters and the flow rate. A.B.K. A73-23395 * Airborne visible laser optical communication experiment. J. L. Randall (NASA, Marshall Space Flight Center, Astrionics,Laboratory, Huntsville, Ala.). In: International Telemeter- ing Conference, Los Angeles, Calif., October 10-12, 1972, Proceed- ings. Woodland Hills, Calif., International Foundation for Telemetering, 1972, p. 395-406. A series of optical communication experiments between a high altitude aircraft at 18.3 km (60,000 ft) and a ground station are planned by NASA in the summer of 1972. The basic concept is that an optical tracker and transmitter will be located in,each terminal. The aircraft transceiver consists of a 5-mW HeNe laser .transmitter with a 30-megabit modulator. The ground station beacon is an argon laser operating at 488 nm. A separate pulsed laser radar is used for initial acquisition. The objective of the experiment is to obtain engineering data on the precision tracking and communication system performance at both terminals. Atmospheric effects on the system performance are of prime importance. (Author) A73-23443 # Compressible unsteady interactions between Made rows. C. Osborne (Cornell University, Ithaca, N.Y.). AIAA Journal, vol. 11, Mar. 1973, p. 340-346. 21 refs. USAF-supported research. The effects of compressibility on the unsteady forces generated by the aerodynamic interaction of blade rows in a jet engine are investigated. Both potential-flow interactions and viscous-wake inter- actions are treated, and the unsteady upwash distributions for these are found in a manner similar to the Kemp-Sears technique for the incompressible-flow problem. The unsteady forces are found from a recently developed theory (by the present author) in which the unsteady incompressible thin-airfoil theory of Sears was extended to the compressible case by using the Matched Asymptotic Expansions technique. The results for all the interactions indicate a significant decrease in the lift forces with increasing Mach number, M until M = 0.9 or. so, where the results tend to blow up due to the Prandtl-Glauert stretching involved in deriving the unsteady subsonic thin-airfoil theory. ' (Author) A73-23464 # Thermal conductivity of mixed-composition plasma-sprayed coatings.' R. L. Newman and W. C. Spicer (General Motors Corp., Detroit Diesel Allison Div., Indianapolis, \nd.).AIAA Journal, vol. 11, Mar. 1973, p. 401-403. 5 refs. Previously reported thermal conductivity data on plasma- sprayed mixed coatings, in general, and on multilayered graded coatings, in particular, are reviewed- and amplified. The graded coatings minimize compositional discontinuity and prevent spalling through application of multilayered coatings varying in composition from 100% metal at the interface to 100% ceramic at the outer layer. Environmental tests of these graded thermal barriers have success- fully demonstrated their ability to reduce heat transfer to coated turbine components and to survive the engine environment. M.V.E. A73-23467 H Locus of a one-dimensional shock front caused by a disturbance moving on a circle. F. Meyer (Aerospace Corp., El Segundo, Calif.). AIAA Journal, vol. 11, Mar. 1973, p. 408, 409. Batdorf (1972) concluded from geometric considerations that, the shock front resulting from a disturbance traveling at constant supersonic speed around a.circle is at any given time an involute of the sonic circle. This result has led to an improved technique for locating the shock front, in which direct plotting of the locus point by point is possible. F.R.L. A73-23468 » # Estimation of aerodynamics for slender bodies alone and with lifting surfaces at alpha's from 0 deg to 90 deg. L. H. Jorgensen (NASA, Ames Research Center, Moffett Field, Calif.). AIAA Journal, vol. 11, Mar. 1973, p. 409-412. 7 refs. Expressions are derived, according to a method developed by the author (1972), for bodies in which the cross-sectional shape (but not .necessarily the area) is constant along the longitudinal axis. For the more general case of a body alone or'with lifting surfaces where the cross-sectional shape varies along the length, a similar procedure is suggested. The specific case for an .elliptic cone with a triangular 190 A73-23682 wing is considered, and formulas for winged elliptic cross sections are- developed. For the limited test conditions shown, the agreement between computed and experimental results is very good. F.R.L. A73-23521 # Manufactured-in-house or subcontracted - Finding the economic balance. D. A. Lessware (SARMA, England). Aircraft Engineering, vol. 45, Feb. 1973, p. 4-8. The example of a mechanical flight control strut is used to demonstrate technical, financial, and other commercial advantages which may be gained by an aircraft manufacturer in subcontracting the fabrication of certain specialized components. Arguments in favor of subcontracting are based on several factors of interest to management. These include structural efficiency; reliability; safety; costs in development, design, tooling, and production; administrative aspects; cash flow considerations; and manpower requirements. T.M. A73-23522 # Resistant finishes. J. B. G. Lewin. Aircraft Engineering, vol. 45, Feb. 1973, p. 11, 12. Aircraft surface primers and finishes designed to withstand severe environmental conditions are described in terms of com- position, pretreatment, and application factors governing flexibility, adhesion, water resistance, hardness, and chemical stability: The properties of amine and polyamide cured epoxy primers are summarized along with important features of acrylic, epoxy, and polyurethane finishes. , T.M. nished the guidelines for the Microwave Landing System (MLS) development program. Details of the five-year development plan are discussed. G.R. A73-23653 * # Door to door short haul. F. R. Steven (NASA, Washington, D.C.). Astronautics and Aeronautics, vol. 11, Mar. 1973, p. 32-44. 7 refs. Present drawbacks to short-haul air transportation are partly related to passenger and baggage processing at air terminals and ground access difficulties. It is pointed out that the widely used automobile is the most inefficient mode of transportation. Various new developments in the field of ground transportation are con- sidered. It is suggested to develop an integrated transportation system which would replace the various competing modes of automobile, bus, rail, and air with a single system for moving people and goods from their origins to their destinations. The Intermodal Automated Transfer system discussed would treat the passenger, his baggage, and the seat in which he travels as a unit which would stay together throughout a trip, regardless of the carrier used. G.R. A73-23655 Development of maintenance policies in the operation of aircraft (Evolution des politiques de maintenance dans I'exploitation des materials aeriens). A. Mihail and G. Martin (Bureau Veritas, Paris, France). L'Aeronautique et I'Astronautique, Jan.-Feb. 1973, p. 21-31. In French. A73-23525 # Ram air turbines. P. W. Morris (Dowty Rotol, Ltd., Gloucester, England). Aircraft Engineering, vol. 45, Feb. 1973, p. 24, 25. 30. Description of the design, performance, and controls of a ram air turbine intended as an emergency power source on aircraft. The two-blade turbine described operates with a low pressure difference across the disk, passes a high mass flow, and is controlled by varying the blade pitch to give an incidence appropriate to the power demand and operating conditions. Curves show wind-tunnel perfor- mance characteristics, and the hydraulic system used for blade pitch control is explained. T.M. A73-23599 # Influence of a change in the throughput of the power turbine on the parameters of a dual-shaft gas turbine engine (Vliianie izmeneniia propusknoi sposobnosti silovoi turbiny na parametry dvukhval'nogo gazoturbinnogo dvigatelia). I. A. Barskii. Mashinostroenie, no. 11, 1972, p. 85-90. In Russian. A73-23636 Radio navigation (Funknavigation). H. C. Freiesleben and J.-P. Hach (Deutsche Lufthansa AG, Hamburg, West Germany). VDI-Z, vol. 115, no. 3, Feb. 1973, p. 214-219. 91 refs. In German. Various approaches for determining the position of a ship with the aid of a radio method are examined, giving attention to radar, the Omega navigation system, and Loran. Aspects of navigation with the aid of satellites are discussed together with inertia! navigation methods, integrated navigation systems, area navigation, and landing systems. Approaches for providing protection against collision in the case of ships and aircraft are considered along with problems of navigation during space flights. G.R. A73-23652 # MLS - On the beam for '76. J. W. Edwards (FAA, Washington, D.C.). Astronautics and Aeronautics, vol. 11, Mar. 1373, p. 24-30. « The standard VHF/UHF ILS is limited to a single approach path. Recognition of the deficiencies of the present system prompted the formation in December 1967 of Special Committee'117 (SC-117) to develop a precision guidance-system concept for approach and landing and an associated signal structure. SC-117 identified two techniques and signal formats as having the greatest potential for satisfying the requirements. The techniques include the conventional scanning beam and Doppler scanning. The recommendations fur- A73-23656 Take-off and landing trajectography (Trajec- tographie de decollage et d'atterrissage). A. Klopfstein (Centre de Documentation pour I'Armement, Paris, France) and C. Lefievre (Centre d'Essais en Vol, Bretigny-sur-Orge, Essonne; Centre de Documentation pour I'Armement, Paris, France). L'Aeronautique et I'Astronautique, Jan.-Feb. 1973, p. 32-43. In French. The magnitudes and accuracies of takeoff and landing trajec- tories are discussed with reference to their .applicability in-the certification of aircraft, the certification of automative approach systems and methods of short-distance trajectography are considered. Trajectography by cinStheodolites, a system of digital optical trajectography, an airborne system, and trajectography by an inertial and radiosonde system are described. F.R.L. A73-23657 Remarks on the ISO international standards relating to 'Terms and Symbols for Flight Dynamics' (Commentaires sur les normes internationales ISO relatives aux 'Termes et Symboles de la mecanique du vol'). P. Rebuffet. L'Aeronautique et I'Astro- nautique, Jan.-Feb. 1973, p. 55-59. In French. A73-23659 Air cushion landing gears for aircraft (Atter- risseurs d'avion a coussin d'air). G. Bruner and D. Laurent (Centre de Documentation pour I'Armement, Paris, France). L'Aeronautique et I'Astronautique, Jan.-Feb. 1973, p. 93-109. In French. Following an exposition of the principle of air cushion landing gears and of the methods of forecasting the peripheral jet stream performance and the dynamical behavior of the device, a description of the system tested on a modified LA-4 and of the system to be installed on the 'Buffalo' STOL is given. In conclusion, the advantages offered by this new kind of landing gear - especially as regards the transport aircraft - are detailed. (Author) A73-23662 * Helicopter main-rotor blade flutter in steady inclined flight (Flatter lopat wirnikow nosnych smiglowcow w ustalonym locie skosnym). L. Zerek. Instytut Lotnictwa, Prace, no. 52, 1972, p. 19-43. 7 refs. In Polish. A73-23682 # Aircraft of the future (Flugzeuge der Zu- kunft). I. Tolztych. (Grazhdanskaia Aviatsiia, no. 6, 1972, p. 18, 19.) ' Technisch-dkonomische Informationen der zivilen Luftfahrt, vol. 8, no. 9, 1972, p. 419-424. In German. (Translation). Evaluation of the technical and economic efficiency of types of aircraft likely to be developed in the coming decades. The problem 191 A73-23683 of evaluating the degree of structural maturity and perfection of passenger aircraft and their economic efficiency is discussed. Prob- lems connected with the development of increasingly high-speed subsonic aircraft, supersonic, and, ultimately, hypersonic aircraft are discussed, including engine designs, fuels, and noise reduction. In addition, the use of VSTOLs to provide more efficient transportation between airports and city centers is considered. A.B.K. A73-23683 § Duties and rights of the commander and crew on board civil aircraft - On the entry into effect of the order of the ministerial council of the German Democratic Republic of July 4, 1972 (Pflichten und Rechte des Kommandanten und der Besatzung an Bord ziviler Luftfahrzeuge - Zum Inkrafttreten der Verordnung des Ministerrates der Deutschen Demokratischen Republik vom 4. Juli 1972). K.-D. Giinter and F. Schlafert (Ministerium fur Verkehrs- wesen, Berlin, East Germany). Technisch-dkonomische Informs- tionen der zivilen Luftfahrt, vol. 8, no. 9, 1972, p. 425-428. 9 refs. In German. Concise summary of the political and legal significance of a recently promulgated document concerning measures to be taken by the commander and crew of a passenger aircraft to prevent or foil a highjacking attempt. The order in question grants the flight commander the right to carry out searches of passengers whose behavior arouses suspicion and to confiscate any items deemed incompatible with flight safety and, if necessary, to use force in carrying out these measures. A.B.K. A73-23697 Flow through moving cascades of lifting lines with fluctuating lift. W. R. Hawthorne (Cambridge University, Cambridge, Mass.). Journal of Mechanical Engineering Science, vol. 15, Feb. 1973, p. 1-10. 8 refs. The use of generalized functions to analyse the potential, two-dimensional, incompressible flow past singularities representing stationary and moving lifting lines is explained and developed. It is ihown that the time mean stagnation pressure change in the flow through a moving cascade with fluctuating lift is normally zero, except when the lift fluctuations are in phase with the motion, so that a stationary system of shed vortices is produced in the downstream flow (the stationary, phased, fluctuating lift case). Then the time mean stagnation pressure is a function of position in the absolute co-ordinate system. Expressions are obtained for the kinetic energy produced by the vortices shed off a row of blades with fluctuating lift. (Author) A73-23774 ff Productivity estimates of the strategic airlift system by the use of simulation. R. L. Nolan (Harvard University, Cambridge, Mass.) and R. Mastroberti (Anne Arundel Community College, Annapolis, Md.). Naval Research Logistics Quarterly, vol. 19, Dec. 1972, p. 737-752. 8 refs. An analysis of the strategic airlift system productivity function, using a large-scale simulation model, is described. The experimental design developed for the analysis consisted of full factorial design sets for a finite number of factors. This design made possible the overlapping of simulation runs to fill out the factorial design sets. In addition to estimating the airlift productivity function, several other findings are reported which tend to disprove previous assumptions about the nature of the strategic airlift system. M.V.E. A73-23775 ft A probabilistic evaluation of helicopter lift capability. D. R. Limaye and E. Levy (Decision Sciences Corp., Jenkintown, Pa.). Naval Research Logistics Quarterly, vol. 19, Dec. 1972, p. 761-775. 8 refs. This paper describes a technique for the calculation of the probability that a helicopter can lift a.specified load, or number of loads with a specified frequency distribution, in a given geographical region. This probability is computed by determining the bivariate altitude-temperature probability distribution for the specified region. The payload capability at any given temperature and altitude is calculated from standard performance equations. By integrating this over the altitude-temperature distribution, it is possible to obtain the probability distribution of payload capability, from which the required probabilities of lifting specific loads can be determined. (Author) A73-23784 Precision hover sensor for heavy-lift heli- copter. D: G. Herzog (RCA Advanced Technology Laboratories, Camden, N.J.). In: RCA advanced technology. Moorestown, N.J., Radio Corporation of America, 1972, p. 16-21. A helicopter stabilization system under development uses two newly developed sensor techniques - image-correlation tracking and pulsed sine-modulated laser ranging - which are combined with the best all-weather, day-night, pulsed-laser-illuminated gated imaging to measure position offsets and velocities using arbitrary scene refer- ences. Positional offsets can be measured in three dimensions to 0.6 in., and velocities as low as 1 in./sec at distances of 125 ft. The stabilization system is designed to freeze .the helicopter in mid-air over a designated cargo handling position even under wind gusts of 45 knots and in dusty environments. ••• (Author) A73-23759 ff The designer's view of aircraft maintenance. S. C. Caliendi (Hawker Siddeley Aviation, Ltd., Hatfield, Herts., England). (British Air Line Pilots Association, Technical Symposium on the Outlook on Safety, 13th, London, England, Nov. 14-16, 1972.1 Tech Air, vol. 29, Mar. 1973, p. 6-13. The interrelationship between aircraft maintenance and safety as viewed by the aircraft designer is reviewed. The high safety standard presently demanded may only be achieved if great attention is given to maintenance procedures and these are considered in detail during the design stage. The object of aircraft maintenance is to prevent deterioration of the inherent safety and reliability levels of the equipment and, if possible, to increase these levels by modification action as deficiencies are recognized during the operation of the aircraft. Aspects of human error, fault diagnosis, redundancy, maintenance analysis, service data, and equipment specification are discussed. . F.R.L. A73-23762 Comparison of conventional flight control systems with a modern integrated flight control system (Vergleich konventioneller Flugregelungssysteme mit einem modernen inte- grierten Flugregelungssystem). G. Schanzer (Bodenseewerk Gera'te- technik GmbH, tiberlingen, West Germany). Flug Revue/Flugwelt International, Mar. 1973, p. 25-30. In German. A73-23799 # Optimization and design of the rear fuselage of the A 300 B aircraft structure. D. Schulz (Messerschmitt-Bolkow- Blohm GmbH, Hamburg, West Germany). NATO, AGARD, Sympo- sium on Structural Optimization, 2nd, Milan, Italy, Apr. 2-4. 1973, Preprint 15 p. This report gives a description of a method for the automatically controlled calculation of a skin/stringer structure developed by MBB-UH. The method was programmed and applied for the first time for the development of the Airbus A 300 B. Input and output data for the calculations of statically indeterminate forces are used as. input data for structure dimensioning or strength analysis program. The structure dimensioning program iterativly modifies the originally defined wall thicknesses so that the reserve factors required to prevent failure under tensile, compression and shear loads are reached or only slightly exceeded in all critical load cases. The originally defined structural concept (stringer and frame spacing as well as stringer shapes) is not changed in this case: Final dimension- ing is influenced by manufacturing considerations. On completion of the dimensioning work the dimensions are laid down and the strength analysis is carried out in a single computer run. (Author) A73-23851 Annual review of fluid mechanics. Volume 5. Edited by M. Van Dyke and W. G. Vincenti (Stanford University, 192 A73-24001 Stanford, Calif.). Palo Alto, Calif., Annual Reviews, Inc., 1973. 453 p. $10.00. Longitudinal 'dispersion and turbulent mixing in open-channel flow, mathematical aspects of Prandtl's boundary-layer theory, and intermittency in large-scale turbulent flows are among the topics covered in papers concerned with fluid mechanics. Attention is given to the use of lasers for local measurement of velocity components, species densities, and temperatures; instability, transition, and turbulence in buoyancy-induced flows; and recent developments in the theory, experiment, and design of transonic airfoils. M.V.E. A73-23856 Transonic airfoils -Recent developments in theory, experiment, and design. G. Y. Nieuwland (Vrije Universiteit, Amsterdam, Netherlands) and B. M. Spee (Nationaal Luchtvaart- laboratorium, Amsterdam, Netherlands). In: Annual review of fluid mechanics. Volume 5. Palo Alto, Calif., Annual Reviews, Inc., 1973, p. 119-150. 61 refs. A73-23860* " Secondary flows • Theory, experiment, and application in turbomachinery aerodynamics. J. H. Horlock (Cambridge University, Cambridge, England) and B. Lakshmi- narayana (Pennsylvania State University, Philadelphia, Pa.). In: Annual review of fluid mechanics. Volume 5. Palo Alto, Calif., Annual Reviews, Inc., 1973, p. 247-280. 50 refs. Grant No. NGL-39-009-007. A73-23861 Noise from aircraft turbomachinery. J. E. McCune and J. L. Kerrebrock (MIT, Cambridge, Mass.). In: Annual review of fluid mechanics. Volume 5. • Palo Alto, Calif., Annual Reviews, Inc., 1973, p. 281-300. 32 refs. Review of recent research on supersonic jet noise due to turbomachinery, with special attention to the connection between noise production and performance measured in terms of thrust per unit of airflow and thrust per unit of engine weight. It is shown that the possibilities of noise abatement offered by reduction of the thrust per unit of airflow, as opposed to more direct noise-reduction techniques, such as duct treatment, and particularly jet suppressors, may as yet not have been fully appreciated. M.V.E. A73-23862 * Mixing-controlled supersonic combustion. A. Ferri (New York University, Bronx, N.Y.). In: Annual review of fluid mechanics. Volume 5. Palo Alto, Calif., Annual Reviews, Inc., 1973, p. 301-338. 57 refs. Grant No. NGR-33-016-131. The technology of supersonic combustion and its practical significance for hypersonic flight are reviewed. It is shown that this technology makes possible a good qualitative and quantitative understanding of the 'physical phenomena related to the process of supersonic combustion. Some of the more important, summarized aspects of this technology include the physical description of the supersonic combustion flame, trie chemical reaction rates and the diffusion process involved, the interaction between combustion and fluid dynamics, and the mathematical methods of supersonic combustion analysis. M.V.E. A73-23950 Improving reliability and eliminating main- tenance with elastomeric dampen for rotor systems. J. L. Potter (Lord Manufacturing Co., Erie, Pa.). American Helicopter Society, Journal, vol. 18. Jan.. 1973, p. 23-28. Elastomeric dampers are a new generation of dampers designed to prevent helicopter and/or VTOL rotor system instability. The damper employs a highly damped viscoelastic polymer, vulcanized and bonded to metallic members which in turn are connected to the rotor system. Deformation of the viscoelastic material'produces a total resisting force composed of a damping and an elastic com- ponent operating 90 deg but of phase due to the hysteresis inherent in the polymer. The damper service life can be in the range of 1500-2000 flight hours with no maintenance or lubrication required. (Author) A73-23964 Ballistic-tolerant helicopter flight control com- ponents from plastic composite materials. L. A. Fry (U.S. Army, Air Mobility Research and Development Laboratory, Fort Eustis, Va.), R. L. Van Auken, and V. A. Chase (Whittaker Corp., San Diego, Calif.). In: Reinforced plastics - Ever new; Proceedings of the Twenty-eighth Annual Conference, Washington, D.C., February 6-9, 1973. . New York, Society of the Plastics In- dustry, Inc., 1973, p. 12-A.1 to 12-A.6. The high vulnerability of present-day helicopter flight systems to ballistic damage from small arms fire has led to the investigation of new materials and design concepts to effectively reduce the damage incurred by a ballistic hit. A solution for the catastrophic failure incurred in the present metal hardware has been found in the development of lightweight flight control components made from fiberglass-reinforced composite materials. The ability to incorporate multiload paths reduces ballistic vulnerability, therefore improving aircraft survivability. The success of the initial developments has led to the investigation of low cost, high volume production methods to produce flight control component systems from fiberglass-reinforced composite material to replace the vulnerable metal components. (Author) A73-23969 Feasibility evaluation of graphite/epoxy com- posite materials to helicopter transmission housing. V. A. Chase, R. L. Van Auken (Whittaker Corp., San Diego, Calif.), and R. L. Rodgers (U.S. Army, Air Mobility Research and Development Laboratory, Fort Eustis, Va.). In: Reinforced plastics - Ever new; Proceedings of the Twenty-eighth Annual Conference, Washington, D.C., February 6-9, 1973. New York, Society of the Plastics Industry, Inc., 1973, p. 15-6,1 to 15-8,8. A73-23989 * § Intensive probing of a clear air convective field by radar and instrumental drone aircraft. J. R. Rowland (Johns Hopkins University, Silver Spring, Md.). Journal of Applied Meteo- rology, vol. 12, Feb. 1973, p. 149-155. 18 refs. USAF-NASA- supported research. An instrumented drone aircraft was used in conjunction with ultrasensitive radar to study the development of a convective field in the clear air. Radar data are presented which show an initial constant growth rate in the height of the convective field of 3.8 m/min, followed by a short period marked by condensation and rapid growth at a rate in excess of 6.1 m/min. Drone aircraft soundings show general features of a convective field including progressive lifting of the inversion at the top of the convection and a cooling of the air at the top of the field. Calculations of vertical heat flux as a function of time and altitude during the early stages of convection show a linear decrease in heat flux with altitude to near the top of the convective field and a negative heat flux at the top. Evidence is presented which supports previous observations that convective cells overshoot their neutral buoyancy level into a region where they are cool and moist compared to their surroundings. Furthermore, only that portion of the convective cell that has overshot its neutral buoyancy level is generally visible to the radar. (Author) A73-23991 ft A method for correcting airborne temperature data for sensor response time. J. McCarthy (Chicago, University, •Chicago, III.). Journal of Applied Meteorology, vol. 12, Feb. 1973, p. 211-214. NSF Grant No. GA-28190X1. Equations are developed which describe (1) the airborne temperature instrumentation response to an arbitrary ambient temperature profile, for a two-term exponential system; and (2) a numerical scheme which corrects the sensor data for this lag. When in-cloud temperature fluctuations are of the same order as the instrument fidelity, as in some cumulus cloud penetrations, serious discrepancies may result between the ambient profile and the sensor response, making a correction desirable. (Author) A73-24001 International Federation of Automatic Con- trol, World Congress, 5th, Paris, France, June 12-17, 1972, Proceedings. Part 2 - Transportation, aeronautics and space, ship 193 A7 3-24009 automation, and control components. Part 3 - Ecology and systems engineering; Large scale, sensitivity, optimization and adaptation theory. Part 4 - Education, feedback, regulators, linear and nonlinear systems; Identification, differential games, discrete and stochastic systems. Congress co-sponsored by the Union of International Engineering Organizations. Diisseldorf, International Federation of Automatic Control, 1972. Pt. 2, 404 p.; pt. 3, 488 p.; pt.'4, 457 p. Price of each part, $35. - New methods for synthesis and analysis of automatic control systems are described in papers dealing with applications in surface transport, aerospace vehicles, data handling, industrial process control, management of large-scale socioeconomic systems, and education. Topics considered include urban traffic control, space- craft stabilization and guidance, computer simulation of legged locomotion systems, aircraft flight control systems, transducer designs for control applications, stepping-motor characteristics, environmental management, biological control systems, national and regional economic systems, and management of industrial concerns. Extensive theoretical material is covered in areas of system optimiza- tion, sensitivity, adaptive control, estimation, identification, different tial games, and discrete automata. T.M. A73-24009 Theoretical 'and practical aspects of an auto- matic hover control system for an unmanned tethered rotorplatform. G. Schmidt and R. Swik (Dornier AG, Friedrichshafen, West Germany). In: International Federation of Automatic Control, World Congress, 5th, Paris, France, June 12-17, 1972, Proceedings. Part 2. Diisseldorf, International Federation of Auto- matic Control, 1972, p. 19.1.1-19.1.8. 5 refs. A73-24010 Automatic landing as a terminal control prob- lem, lu. P. Gus'kov. In: International Federation of Automatic Control, World Congress, 5th, Paris, France, June 12-17, 1972, Proceedings. Part 2. Dusseldorf, International Federation of Automatic Control, 1972, p. 19.2.1-19.2.6. Consideration of the synthesis of an efficient and simple law for a feedback-based control to implement the automation of aircraft landing maneuvers. The selection of the landing control law is based on the trajectory-termination or terminal-control requirements fora desirable aircraft contact with the ground at touchdown. The approach to the synthesis problem is characterized by introduction of terminal control discreteness into the feedback. M.V.E. A73-24011 * A control theoretic model for piloted ap- proach to landing. D. L. Kleinman and S. Baron (Bolt Beranek and Newman, Inc., Cambridge, Mass.). In: International Federation of Automatic Control, World Congress, 5th, Paris, France, June 12-17, 1972, Proceedings. Part 2. > Dusseldorf, Interna- tional Federation of Automatic Control, 1972, p. 19.3.1-19.3.8. 10 refs. Contract No. NAS2-5962. Using manned vehicle systems analysis, a model for manual approach to landing is developed. This model is developed and applied in the specific context of a problem of analytical evaluation of a pictorial display for longitudinal control of glide path errors. This makes it possible to discuss the model in concrete terms, and the availability of experimental data provides opportunities for checking the theoretical results obtained. M.V.E. A73-24012 • Dynamics of variable sweep wing aircraft in the course of changing geometry. V. P. Bulekov and E. D. Teriaev. In: International Federation of Automatic Control, World Congress, 5th, Paris, France, June 12-17. 1972, Proceedings. Part 2. Diisseldorf, International Federation of Automatic Control, 1972, p. 19.5.1-19.5.10. It is the purpose of this paper to investigate the dynamics of variable sweep wings aircraft in the course of changing geometry. It is proposed the mathematical techniques based on the pulse reaction to use for the analysis of the equations with time varying coefficients which describes apparatuses in the regime of the geometry change. It is investigated the possibility of decreasing the time of the geometry change. . (Author) A73-24092 # Contribution to the bonding of glass laminates and metals (Prispevek ke spojovani skelnych laminatu s kovy). J. Kobes. In: Intermetalbond '72; Conference on the Bonding of Metals, 5th, Boboty, Czechoslovakia, November 21-23, 1972, Pro- ceedings. . Bratislava, Dom Techniky SVTS, 1972, p. 62-73, 75. In Czech. Review of certain differences between metal/glass laminate bonding and metal/metal bonding, and evaluation of tests of various bonding materials for use in metal/glass laminate bonding. It is stressed that the decisive factor affecting the strength of a glass laminate bonded joint, assuming that an appropriate surface finish has been attained and that a high-quality bonding material is being used, is the interlaminar strength of the glass laminate. By increasing the interlaminar strength, the strength of the bonded joint can be increased. A.B.K. A73-24165 Investigation of iron content of lubricating oil using a ferrograph and an emission spectrometer. V. C. Westcott and W. W. Seifert (Trans-Sonics, Inc., Burlington, Mass.). Wear. vol. 23, Feb. 1973, p. 239-249. Contract No. N00014-72-C-0278. An investigation was carried out into the discrepancies in iron content of used oils as assessed by density readings of Ferrograms and determined by several emission spectrometers of the rotating disk type. It was concluded that used jet engine oil contains a significant number of iron particles so large that the spectrometer is not responsive to them and also contains a large total fraction of iron content in the form of nonmagnetic compounds which are not precipitated on the Ferrogram. (Author) A73-24363 § Calculation of the contact rigidity of cylindri- cal joints (O vychislenii kontaktnoi zhestkosti tsilindricheskikh soedinenii). A. B. Milov (Rizhskii Institut Grazhdanskpi Aviatsii, Riga, Latvian SSR). Problem/ Prochnosti, vol. 5, Jan. 1973, p. 70-72. 8 refs. In Russian. Relations for calculating elastic strains in overlapping joints of cylindrical tubes are derived on the basis of Shtaerman's (1949) analysis in which the, plane contact problem is reduced to the solution of an integrodifferential equation of the type of Prandtl's equation in the theory of a wing of finite span. The solution of this equation is simplified by approximating the law describing the pressure distribution over the arc of contact. V.P. A73-24386 ff Influence of the nonidentity of the antennas of a Doppler speed meter on the accuracy of its operation (Vliianie neidentichnosti antenn dopplerovskogo izmeritelia skorosti na tochnost' ego raboty). V. I. Baburin, L. N. Zakhar'ev, and A. A. Lemanskii. Radiotekhnlka, vol. 27, Dec. 1972, p. 94-96. In Russian. A73-24391 » Scaling aircraft noise perception. J. B. Ollerhead (Loughborough University of Technology, Loughborough, Leics., England). Journal of Sound and Vibration, vol. 26, Feb. 8, 1973, p. 361-388. 26 refs. FAA-NASA-supported research. Following a brief review of the background to the study, an extensive experiment is described which was undertaken to assess the practical differences between numerous alternative methods for calculating the perceived levels of individual aircraft flyover wounds. One hundred and twenty recorded sounds, including jets, turboprops, piston aircraft and helicopters were rated by a panel of subjects in a pair comparison test. The results were analyzed to evaluate a number of noise rating procedures, in terms of their ability to accurately estimate both relative and absolute perceived noise levels over a wider dynamic range (84-115 dB SPL) than had generally been used in previous experiments. Performances of the 194 A73-24556 different scales were examined in detail for different aircraft categories, and the merits of different band level summation procedures, frequency weighting functions, duration and tone corrections were investigated. (Author) A73-24474 Will this be the Aeritalia-Boeing (Sara questo il Boeing-Aeritalia). P. L. Guida, Aviazione di Linea, Difesa, e Spazio, vol. 11, Feb. 1973, p. 32-34. In Italian. Review of the probable design features of the 7X7 passenger aircraft being built as part of a project involving a family of three vehicles for short, medium, and long hauls. The QSH - quiet short haul - represents the aircraft of the original Aeritalia-Boeing agreement. From this, medium- and long-range versions have been derived. The 7X7 is to have a low wing and T tail - a fairly conventional configuration, were it not for the wing-mounted engines installed in this way for noise suppression. The capacity of the 7X7 will range from 180 to 200 passengers, and very likely more in the long-haul version. It is still not certain what the number of propulsion units will be. The final result could be either two engines in the short- and medium-haul versions and three in the long-range version, or possibly three and four engines, respectively. A.B.K. A73-24475 Visibility zero even for'helicopters (Visibilita zero anche per gli elicotteri). P. Marini. Aviazione di Linea, Difesa, e Spazio, vol. 11, Feb. 1973, p. 66, 67. In Italian. Description of a Doppler navigation system for helicopters which obtains data through a computer display method. The system in question is called TANS (Tactical Air Navigation System). The computer involved uses completely autonomous navigation sensors and is capable of providing not only a representation of cartographic data (indicating the position of the aircraft on a strip of cartographic paper) hut also an entire gamut of essential information. A.B.K. A73-24494 A method of measuring the thrust, the polar, and the performance of an aircraft on the basis of flight tests (Metodo per la misura della spinta, della polare e delle prestazioni di un aeromobile con prove di volo). M. Cassetti (Genio Aeronautico, Rome, Italy). L'Aerotecnica - Missili e Spazio, vol. 51, Dec. 1972, p. 375-380. In Italian. Aerospace and environmental studies consider aircraft noise and pollution reduction, safety, operations, and future systems. Aspects of energy demand and supply are treated, and a systems approach to anti-hijacking is presented. Complex target resolution with the random signal radar, and the evolution of commercial satellite communications systems are examined. Deficits in visual functions associated with laser irradiation are discussed. F.R.L. A73-24552 The DOT/NASA Civil Aviation Research and Development Policy Study. A. B. Linhares (U.S. Department of Transportation, Washington, D.C.). In: EASCON '72; Electronics and Aerospace Systems Convention, Washington, D.C., October 16-18^ 1972, Record. New York, Institute of Electrical and Electronics Engineers, Inc., 1972, p. 10-15. The Civil Aviation Research and Development (CARD) Policy Study was undertaken jointly by the Department of Transportation and the National Aeronautics and Space Administration in response to a recommendation by the Senate Committee on Aeronautical and Space Sciences (90th Congress). The Study evolved as a compre- hensive review of policies affecting civil aviation, of the problems confronting it, and of the potential it possesses for future contribu- tions to the Nation. The priority areas identified for R&D were environmental problems (noise and pollution), congestion, and low-density short-haul service and economics. The importance of long-haul aircraft R&D was also addressed. Significant actions which have been taken as a result of the study are also described. (Author) A73-24553 Aircraft noise abatement. C. R. Foster (U.S. Department of Transportation, Washington, D.C.). In: EASCON '72; Electronics and Aerospace Systems Convention, Washington, D.C., October 16-18, 1972, Record. New York, Institute of Electrical and Electronics Engineers, Inc., 1972, p. 16-21. The problem of aircraft noise and the individual noise sources are identified. The programs within the Federal Government ad- dressing aircraft noise abatement are delineated. The technology and its application for aircraft noise suppression as well as aircraft noise certification standards are presented. Pertinent federal laws and regulations pertaining to aircraft noise control are reviewed. (Author) A73-24542 Solving flight-path optimization problems on a minicomputer. F. Y. Thomasson (Babcock and Wilcox Co., Lynch- burg, Va.) and G. Cook (Virginia, University, Charlottesville, Va.). 1 Astronautics Acta, vol. 18, Feb. 1973, p. 45-51. Research sponsored by Teledyne. The problem of determining maximum-range flight paths for a jet transport during climb is investigated. The objective is to guide the aircraft so that it will reach a prespecified cruise altitude and velocity and obtain maximum range in the process. The amount of fuel to be used is prespecified. Motion is in a vertical plane with lift coefficient* being the control variable. The system of differential equations describing the motion of the plane is fifth order and nonlinear. The conjugate gradient procedure is used to solve the problem. The complexity is such that 36,000 storage locations are required for the most straightforward application of the procedure. Through various approximations this requirement is reduced to 250 locations. Simulations showed that performance is not degraded through the approximations. The magnitude of the problem is thus reduced to that which could be solved by an onboard minicomputer. This'is a major step toward the realization of optimal feedback control. The other requirement is that computation time be short enough to permit on-line solutions. (Author) A73-24551 EASCON '72; Electronics and Aerospace Systems Convention, Washington, D.C., October 16-18, 1972, Record. Convention sponsored by the Institute of Electrical and Electronics Engineers. New York, Institute of Electrical and Elec- tronics Engineers.'lnc., 1972. 200 p. Members, $12.50; nonmembers, $14.50. i s ' - A73-24555 * Jet aircraft engine noise reduction. E. W. Conrad and C. C. Ciepluch (NASA, Lewis Research Center, Cleve-/ land, Ohio). In: EASCON' 72; Electronics and Aerospace Systems Convention, Washington, D.C., October 16-18, 1972, Record. New York, Institute of Electrical and Electronics Engineers, Inc., 1972, p. 50-55. The major noise sources are considered together with the noise generation mechanisms involved and approaches for reducing or suppressing the generated noise. Important basic advances in engine noise reduction technology were made in connection with the NASA Quiet Engine program. The prospect for reducing the noise levels of future aircraft below that of the new wide-body jets is good. However, a significant penalty in the form of increased cost to the traveler is also to be expected as the aircraft noise levels are gradually decreased. G.R. A73-24556* Aircraft engine pollution reduction. R. A. Rudey (NASA, Lewis Research Center, Cleveland, Ohio). In: EASCON '72; Electronics and Aerospace Systems Convention, Washington, D.C., October 16-18, 1972, Record. New York, Institute of Electrical and Electronics Engineers, Inc., 1972, p. 56-63. 9 ref s. The effect of engine operation on the types and levels of the major aircraft engine pollutants is described and the major factors governing the formation of these pollutants during the burning of hydrocarbon fuel are discussed. Methods which are being explored to 'reduce these pollutants are discussed and their application to several experimental research programs are pointed out. Results showing 195 A73-24557 significant reductions in the levels of carbon monoxide, unburned hydrocarbons, and oxides of nitrogen obtained from experimental combustion research programs are presented and discussed to point out potential application to aircraft engines. An experimental program designed to develop and demonstrate these and other advanced, low pollution combustor design methods is described. Results that have been obtained to date indicate considerable promise for reducing advanced engine exhaust pollutants to levels significantly below current engines. (Author) A73-24557 Aircraft wake vortex avoidance systems. M. Gorstein, J. Hallock, and I. McWilliams (Transportation Systems Center, Cambridge, Mass.). In: EASCON '72; Electronics and Aerospace Systems Convention, Washington, D.C., October 16-18, 1972, Record. New York, Institute of Electrical and Electronics Engineers, Inc., 1972, p. 64-69. 10 refs. The functions performed by a wake vortex avoidance system include the detection of prediction of the current locus of the vortices in the air corridors near an airport and an indication of the hazard to a following aircraft. The characteristics of the vortices connected with the aircraft wake are considered together with the sensprs required to detect these vortices. Two preliminary designs for wake vortex avoidance systems are discussed. The designs are based upon the current assessment of the aircraft-vortex hazards. In order to establish the system coverage requirements for the wake vortex avoidance system, a computer simulation has been developed of the transport of vortices in the terminal environment. G:R. A73-24558 Aircraft initiation of lightning strikes. J. F. Shaeffer and G. L. Weinstock (McDonnell Aircraft Co., St. Louis, Mo.). In: EASCON '72; Electronics and Aerospace Systems Conven- tion, Washington, D.C., October 16-18, 1972, Record. New York, Institute of Electrical and Electronics Engineers, Inc., 1972, p. 70-76. 14 refs. Contract No. F33615-71-C-1581. Analytical results and lightning simulation testing show that an aircraft can trigger lightning when flying in a highly charged atmospheric environment. For such an environment, the electric field intensification of the aircraft is high enough to initiate lightning which may not have occurred naturally. It is shown that an external source of charge is required to support an aircraft initiated discharge. The electric fields surrounding an F-4 and B-52 aircraft were determined from the electrostatic integral field equations using an algorithm which included actual aircraft geometry, an external cloud electric field, and a net charge on the aircraft. Capacitance of the aircraft was determined, and consequently the charged vehicle potential and electrostatic field energy were obtained. The algorithm has also been used to obtain the maximum net charge an F-4 and B-52 aircraft can hold before self discharge corona begins. The effect on these parameters caused by varying aircraft size is discussed. A brief background of lightning phenomena is presented including cloud environments, wave forms, and breakdown. (Author) A73-24559 Transportation safety - Technology applica- tions: A systems approach to anti-hijacking. M. Lauriente (U.S. Department of Transportation, Washington, D.C.). In: EASCON '72; Electronics and Aerospace Systems Convention, Washington, D.C., October 16-18, 1972, Record. New York, Institute of Electrical and Electronics Engineers, Inc., 1972, p. 77-80. The elements of a total systems concept are offered as a solution to the hijack problem. The analysis considers evaluation of the threat, environments, and technology available. The goal is to achieve security with minimal interference with the high density passenger traffic. The purpose of this paper is to examine the United States Civil aviation security program, highlighting the anti-hijacking effort from a systems research and development point of view. It is hoped, in this way, to focus attention on what has been done and, especially, to draw attention to the needs now and in the future. (Author) A73-24562 * Community response to aircraft noise. R. P. Whitten (NASA, Washington, D.C.). In: EASCON '72; Electronics and Aerospace Systems Convention, Washington, D.C., October 16-18, 1972, Record. New York, Institute of Electrical and Electronics Engineers, Inc., 1972, p. 180-183. 8 refs. Organized community resistance to any plan of airport develop- ment has become so intense that noise exposure is a primary consideration in plans for new airports, runway extensions, and the introduction of new types of aircraft. Approaches for evaluating the amount of aircraft noise and the annoyance produced by it are discussed. The sociometric studies considered show that fear of crash is the strongest single variable. G.R. A73-24631 A mechanized eddy current scanning system for aircraft struts. C. R. Reeves (Lockheed-Georgia Co., Marietta, Ga.). American Society for Nondestructive Testing, National Fall Conference, Cleveland, Ohio, Oct. 16-19, 1972.) Materials Evalua- tion, vol. 31, Mar. 1973, p. 48-52. Description of the design and operation of a mechanized eddy current defect detection system used for scanning internal cylindrical surfaces. The single coil scanning apparatus traces a helical path. Cracks as small as 0.050 in. (1.27 mm) long by 0.020 in. (0.508 mm) deep can be reliably detected at scan rates up to 140 sq in. (910 sq cm) per minute. A unique electronic, audio/visual indicator is incorporated into the portable eddy current inspection system to provide recognizable defect indications at high speeds. A description of two specific applications on aircraft landing gear components is presented with data on operating parameters. A number of potential uses for this system are also discussed. (Author) A73-24646 Adrift on the air ocean - The future of air commerce /61st Wilbur and Orville Wright Memorial Lecture/. S. D. Browne. Aeronautical Journal, vol. 77, Feb. 1973, p. 69-73. The air transport system is discussed, taking into account all aspects from manufacturers, to carriers, passengers, shippers and governments. Particular attention is given to the future of mass transport, the international rates and fares problem, the international exchange of rights, questions of security, and the future of technology. The problem of continual progress has to be solved without polluting the environment. G.R. A73-24647 A new look at parachute opening dynamics. P. R. Payne. Aeronautical Journal, vol. 77, Feb. 1973, p. 85-93. 20 refs. Contract No. F33615-70-C-1420. An analysis is conducted as a basis for the development of a very simplified model of parachute opening from first principles, without any appeal to experimental measurements. It is found that risers, shroud and canopy cloth stiffness have a major effect on opening history and loads. Transient phenomena occur at much higher frequencies than that associated with the total opening cycle. The line stretch existing at commencement of opening has a major influece on opening time and loads. G.R. A73-24650 Selling high cost capital. equipment. H. B. Cundall (Rolls-Royce, Ltd., Derby, England). Aeronautical Journal, vol. 77, Feb. 1973, p. 107-119. 16 refs. A reasoned analysis is provided of the tasks, the functions, and the organization of a sales team. The marketing objectives are discussed together with the problems involved in launching a new product, the sales-campaign, and the sales costs.; General sales considerations are investigated, giving attention to nontechnical factors affecting sales, the understanding of business ethics, aspects of selling in the U.S., the Common Market effect on sales activities, and the national involvement in sales. G.R. A73-24671 # Some control problems for centrifugal blowers (Nekotorye voprosy regulirovaniia tsentrobezhnykh dut'evykh mashin). S. P. Livshits. Energomashinostroenie, vol. 19, Jan. 1973, p. 196 A73-24767 12-14. In Russian. Analysis of the effectiveness of flow twisting in front of the rotor as a control technique in centrifugal blower operation. Formulas are given to relate various parameters of the equipment and flow in centrifugal blowing processes with and without flow twisting. Criteria are proposed for the efficiency of centrifugal blowers. V.Z. A73-24707 Human threats to air safety; Proceedings of the Twentyrfifth Annual International Air Safety Seminar, Washington, D.C., October 16-18, 1972. Seminar sponsored by the Flight Safety Foundation. Arlington, Va., Flight Safety Foundation, Inc., 1972. 227 p. $10.00. Criminal threats to safety in air transport are discussed with reference to hijacking, piracy and extortion, sabotage, explosive containment, and preventive measures taken by airlines. Human factors involving personnel, passengers, design of equipment, airport design and operation, and ground damage are considered. Search, rescue, and survival systems are evaluated. Safety research and development concerning lightning, fire detection, refueling, and turbine rotor blade or disk burst are studied. Attention is given to pilot incapacitation. F.R.L. A73-24708 # An international review of civil aircraft damaged or destroyed by deliberate detonation of explosives /sabotage/ 1964-1972. E. Newton (Department of Trade and Industry, Accident Investigation Branch, London, England). In: Human threats to air safety; Proceedings of the Twenty-Fifth Annual International Air Safety Seminar, Washington, D.C., October 16-18, 1972. Arlington, Va., Flight Safety Foundation, Inc., 1972, p. 35-42. A73-24710 # Risk management, system safety and ground test programs. G. Sim (Lockheed-California Co., Burbank, Calif.). In: Human threats to air safety; Proceedings of the Twenty-fifth Annual International Air Safety Seminar, Washington, D.C., October 16-18, 1972. i i Arlington, Va., Flight Safety Foundation, Inc., 1972, p. 101-122. 10 refs. Some of the risks associated with today's advanced flying systems are examined, and it is shown how some recent advances in ground testing philosophy and techniques will contribute to enhanced safety in the coming generation of new airline equipment. The Visual Systems Simulator (VSS) for the TriStar is briefly described. Its planned purposes are to provide a tool for systems development, permit systems environmental testing, provide systems endurance cycling evaluation, assist in FAA certification, provide early maintainability and reliability data, and provide a permanent facility for systems support. Attention is given to the Avionic Flight Control System (AFCS). F.R.L. A73-24712 ff Significant elements of an effective search, rescue, and survival system. G. W. Heath (SAR-ASSIST, Inc., Greenwich, Conn.). In: Human threats to air safety; Proceedings of the Twenty-fifth Annual International Air Safety Seminar, Washington, D.C., October 16-18, 1972. Arlington, Va., Flight Safety Foundation, Inc., 1972, p. 137-147. An attempt is made to question what may be the significant elements of a rescue system with the intent that the whole subject receive the benefit of rethinking. Attention is given to equipment design, role allocation between survivor and rescue team, and to the regulatory philosophy and specific requirements to which design, selection, and carriage of equipment necessarily must respond. Some future steps to improve performance are suggested. F.R.L. A73-24713 ff ' •• . Deficient airfields - Still today's problem-child. M. G. Williams (Court Line Aviation, Ltd., London, England). In: Human threats to.air safety; Proceedings of the Twenty-fifth Annual International Air Safety Seminar, Washington, D.C., October 16-18, 1972. Arlington, Va., Flight Safety Foundation, Inc., 1972, p. 150-154. A satisfactory airfield must have runways of adequate length and strength for the proposed traffic with no obstructions within the approach and takeoff paths. The runways must be adequately drained, and preferably should be grooved to aid drainage and assist braking. The worst deficiency in any airfield is the lack of glide slope information, especially at night. The next major problem is the lack of static-free radio aids. It is suggested that the best cure for deficient airfields is strong government legislation. Another cure would be concerted action by the aircraft operators themselves. F.R.L. A73-24714 ff Influence of airport design and management on ground damage to aircraft. C. W. Pace, Jr. (FAA, Airports Service, Washington, D.C.). In: Human threats to air safety; Proceedings of the Twenty-fifth Annual International Air Safety Seminar, Washington, D.C., October 16-18, 1972. Arlington, Va., Flight Safety Foundation, Inc., 1972, p. 155-162. FAA Rule FAR Part 139 requires that each airport serving CAB-certificated air carriers meets prescribed minimum safety standards. These standards are examined to show how each will improve airport safety levels. The rules are concerned with pavement and safety areas, marking and lighting, fire fighting and rescue services, Navaids, airport condition assessment and reporting, fueling arrangements, and many other aspects. Steps being taken by the FAA to correct the deficiencies are discussed. F.R.L. A73-24715 # Air carrier ground damage - Typical incidents and patterns. E. B. Perry (Flight Safety Foundation, Inc., Arlington, Va.). In: Human threats to air safety; Proceedings of the Twenty- fifth Annual International Air Safety Seminar, Washington, D.C., October 16-18, 1972. Arlington, Va., Flight Safety Foundation, Inc., 1972, p. 170-179. A few examples of damage to aircraft on the ground are described, and the cost of repairs and out-of-service time that results from these mishaps is discussed. In addition to the cost of aircraft damage, damage to ground equipment is expensive to repair and operations suffer when that equipment is out of service. An attempt is made to combine some common information from selected air carriers on a worldwide basis to arrive at probable ground mishap averages. F.R.L. A73-24716 tt Optimization of maintenance manuals to minimize error. E. L. Brown, A. A. Burrows, and W. L. Miles (Douglas Aircraft Co., Long Beach, Calif.). In: Human threats to air safety; Proceedings of the Twenty-fifth Annual International Air Safety Seminar, Washington, D.C., October 16-18, 1972. Arlington, Va., Flight Safety Foundation, Inc., 1972, p. 180-190. 7 refs. Fault isolation information for the DC-10 is contained in two manuals: (1) the fault isolation (Fl) manual designed for in-flight use, and (2) the turn-around fault isolation (TAFI) manual designed for use by the mechanic during troubleshooting to identify the faulty line replaceable unit (LRU). All the information in these manuals is based on a very complete engineering analysis. The FI /TAFI information presentation philosophy and techniques are discussed, as well as FI/TAFI testing and operational experience. The advanced maintenance information (AMI) job package concept is described. F.R.L. A73-24767 Assessing the cost effectiveness of planned improvements. S. B. Poritzky (Air Transport Association of America, Washington, D.C.). Journal of Air Traffic Control, vol. 15, Man-Apr. 1973, p. 5-10. The criteria for evaluating the cost-effectiveness of planned improvements in the aviation system are considered. The financial situation is discussed together with questions regarding ATC automa- tion vs terminal aids, the noise problem, noise control by procedures, the replacement of ancient ground facilities, a higher capacity ATC 197 A73-24768 system, the automation base, terminal area ATC capacity improve- ments, and the enroute situation. Other subjects investigated include approaches for establishing cost-'effectiveness and the cost- effectiveness of high-cost improvements. G.R. A73-24768 Considerations for future approach operations. A. S. Crossfield (Eastern Air Lines, Inc., New York, N.Y.). Journal of Air Traffic Control, vol. 15, Mar.-Apr. 1973, p. 11-13. A two-segment approach has been designed to reduce the approach noise impact upon colocated airport communities. A technique for reducing human errors in approach altitude interpreta- tion and interpolation is reported. Category I, II, and III approaches are considered together with a number of new approach classes, aspects of cost and safety, a number of precision approaches, and some nonprecision approaches. G.R. A73-24842 Hydrodynamic visualization of unsteady flows (Visualisation hydrodynamique d'ecoulements instationnaires). H. Werle (ONERA, Chatillon-sous-Bagneux, Hauts-de-Seine, France). In: Recent research on unsteady boundary layers; Symposium, Quebec, Canada, May 24-28, 1971, Proceedings. Volume 2. Quebec, Presses de I'Universite Laval, 1972, p. 1422-1443. 40 refs. In French. Techniques for the study of flow patterns about models, based on flow visualization in water, are described, and the potentialities and limitations of these techniques are reviewed with respect to their application to unsteady flows. It is shown that,, is spite of their imperfect similarity conditions due to low Reynolds numbers, these experimental techniques are at the origin of numerous results of considerable importance for pure and applied research reaching into several aerospace and industrial areas of interest. M.V.E. A73-24875 Boeing sells a thousand 727s - and hopes to sell plenty more. J. P. Geddes. Interavia, vol. 28, Mar. 1973, p. 245-247. The origins of the Boeing 727 design and the manufacturer's plans to follow up the 727 later in the decade through the 7X7 study program and cooperation with foreign companies are outlined. The ultimate 727 configuration with three engines in the rear was a compromise between a series of conflicting views in the airline industry. The most difficult development problems were surges in the inlet ducts, which caused engine failure, and structural and aerodynamic difficulties with the T-tail. Various modifications and improvements to the original 727 are discussed. Present plans 6n the proposed 7X7 are based on entering the intermediate market through joint ventures with Italy and Japan if there are firm airline commitments. F.R.L. A73-24915 Symmetrical airfoils optimized for small flap deflection. F. X. Wortmann (Stuttgart, Universitat, Stuttgart, West Germany). Aero-Revue, Mar. 1973, p. 147-150. Wind-tunnel data obtained with aerodynamic control surfaces designed not as symmetrical but as cambered airfoils with a deflected flap are examined. Flap configurations providing optimum velocity distributions are discussed. V.P. Discussion of the theory and implementation of civil aviation network planning and management procedures, covering their ap- plications in aircraft maintenance, air traffic control, airport opera- tions, labor and materials distribution, aircraft production, opera- tions management, and cost analysis. Details are given on the application of network diagrams in a number of specific aircraft maintenance and servicing operations. Computer applications and the potential of the diagrammatic method as an instrument of optimiza- tion are also considered. V.Z. A73-24925 ft Gas turbine systems for engines with split exhaust gas discharge (Gazoturbinnye sistemy dvigatelei s razdelen- nym vypuskom gazov). M. G. Makhan'ko. Moscow, Izdatel'stvo Mashinostroenie, 1972. 120 p. 17 refs. In Russian. Description of turbocharging systems for piston engines employing separate high- and low-pressure exhaust ports for each cylinder. The high-pressure exhaust ports are located in the cylinder wall and become uncovered by the piston at the end of its downward stroke, while the low-pressure ports are located in the head and act during the exhaust stroke. Systems are classified and analyzed on the basis of the manner in which the two exhaust ducts are applied to turbine stages driving the intake compressor. T.M. A73-24949 Helo camera mount eases 80-million square mile job. V. O. McColley and W. W. Grass (U.S. Navy, Combat Camera Group, San Diego, Calif.). Signal, vol. 27, Apr. 1973, p. 20 23. The advantages of the Nelson Tyler camera mount lie in the complete isolation of engine and airframe vibration from the camera. The delicate balance between camera and counter-balance enables the photographer to keep his picture horizon smooth and level despite any erratic changes in aircraft attitude. The operation of the mount is discussed and attention is given to questions of the mobility of the device. G.R. A73-24965 Effectiveness of diffusion metallizing as a means of increasing the life of gas turbine blades. P. T. Kolomytsev, P. P. Lebedev, and L. A. Kostina (Voenno-Vozdushnaia Inzhenernaia Akademiia, Moscow, USSR). (Zashchitnye Pokrytiia na Metallakh, no. 4, 1971, p. 257-263.) Protective Coatings on Metals, vol. 4, 1972, p. 193-197. Translation. Illustration of the use of diffusion metallization by chromium and aluminum to increase the longevity of parts made of heat- resistant materials at a comparatively low operating temperature (750 C). The efficiency of the turbine blades of the VK-1A engine is estimated from the results of full-scale tests of the endurance of uncoated and chromoaluminized blades after various times of operation on the engine. It is shown that in-vacuum chromoaluminiz- ing significantly increases the operating life of these turbine blades, the endurance limit being increased from 650 to 1300 hr. A.B.K. A73-24916 Electronic developments for high-performance glider flight. I (Elektronische Entwicklungfiir den Leistungssegelflug. I). I. Westerboer. (Organisation Scientifique et Technique Interna- tionale du Vol a Voile, Congress, 13th, Vrsac, Yugoslavia, July 9-22, 1972.1 Aero-Revue, Mar. 1973, p. 150, 151 .-In German. Two electronic systems that will compensate the total energy of a rate-of-climb indicator are described. Some practical aspects of time-constant compensation and altitude (pressure decrease) error compensation are examined. V.P. A73-24924 ff Network planning and control of air trans- portation (Setevoe planirovanie i upravlenie na vozdushnom trans- porte). A. V. Miroshnikov, A. S. Kravets, and A. N. Khizhniak. Moscow, Izdatel'stvo Transport, 1971. 112 p. 12 refs. In Russian. 198 STAR ENTRIES N73-18001*# National Aeronautics and Space Administration. Ames Research Center, Moffett Field. Calif. A METHOD FOR PREDICTING SHOCK SHAPES AND PRESSURE DISTRIBUTIONS ON TWO DIMENSIONAL AIRFOILS AT LARGE ANGLES OF ATTACK George E. Kaattari Washington Mar. 1973 49 p refs (NASA-TN-D-7197; A-4564) Avail. NTIS HC $3.00 CSCL 01A A method is presented for determining shock envelopes and pressure distributions for two-dimensional airfoils at angles of attack sufficiently large to cause shock detachment and subsonic flow over the windward surface of the airfoil. Correlation functions obtained from exact solutions are used to relate the shock standoff distance at the stagnation and sonic points of the body through a suitable choice for the shock shape. The necessary correlation functions were obtained from perfect gas solutions but may be extended to any gas flow for which the normal shock-density ratio can be specified. Author N73-18003*# Bell Aerospace Co.. Buffalo. N.Y. DEVELOPMENT AND APPLICATIONS OF SUPERSONIC UNSTEADY CONSISTENT AERODYNAMICS FOR IN- TERFERING PARALLEL WINGS Kan Appa and G. C. C. Smith Washington NASA Mar. 1973 57 p refs (Contract NAS1 -10880) (NASA-CR-2168) Avail: NTIS HC $3.00 CSCL 01A The analytical development of unsteady supersonic aerody- namic influence coefficients for isolated and nearly parallel interfering coplanar and noncoplanar wings is described. Numerical formulations based on triangular discretizations of wings and diaphragms are handled in a kinematically consistent manner. Examples of isolated wing cases are compared with respect to aerodynamic influence coefficients and flutter boundaries. Aerodynamic influence coefficients for interfering wings are compared where corresponding results are available. Author N73-18004$ Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt. Goettingen (West Germany). Abteilung Aerodynamik. INFLUENCE OF THE TRAILING EDGE SHAPE ON THE DRAG OF A RECTANGULAR WING IN THE MACH NUMBER RANGE FROM FREE STREAM MACH .5 TO 2.2 M. Tanner 1971 93 p refs In GERMAN: ENGLISH summary (DLR-FB-71-85) Avail: NTIS HC $6.75; DFVLR Porz-Wahn: 28.80 DM Drag and lift measurements were performed on two rectangular wings with an aspect ratio of 2 in the Mach number range from free stream Mach 0.5 to 2.2. The one wing had a sharp trailing edge and the other a blunt trailing edge. The shape of the blunt trailing edge and its thickness was varied. By using a broken trailing edge shape the drag of the wing with a blunt trailing edge was remarkably reduced. The total drag was split up in its components in order to show the magnitude of the various drag components. Author N73-18005# Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt. Brunswick (West Germany). Inst. fuer Aerodynamik. THEORETICAL PARAMETER STUDIES OF WING- FUSELAGE-COMBINATIONS Horst Koerner 1972 40 p refs In GERMAN; ENGLISH summary (DLR-FB-72-63) Avail: NTIS HC $4.00; DFVLR Porz: 11 DM A parameter study is presented concerning the influence of the main geometry parameters on the aerodynamic characteristics of a wing-fuselage-combination in incompressible flow. For this study a prediction-method for wing-fuselage-combinations with cylindrical fuselages developed by H. Korner is used. The parameters investigated within this study are body-diameter, wing-position, sweep, planform-taper, and aspect ratio. Results are given for the lift slope and the aerodynamic centre of the total arrangement, in some cases also trie local values along the span. Author N73-18006# Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt. Goettingen (West Germany). (AVA)- Abteilung Aeroelastik. CALCULATION OF THE UNSTEADY PRESSURE DISTRIBU- TIONS ON HARMONICALLY OSCILLATING SLENDER CRUCIFORM WING AND CYLINDRICAL BODY COMBINA- TIONS K. L. Chao 1971 96 p refs In GERMAN; ENGLISH summary (DLR-FB-71-87) Avail: NTIS HC $7.00; DFVLR Porz-Wahn: 28.80 DM Based upon the Slender-Body-Theory the theoretical relations for an analytical determination of the pressure distributions on harmonically oscillating slender cruciform wing and cylindrical, body combinations in compressible flow are presented. For the analytical solution of the Laplace equation the method of conformal mapping has been applied, where the cross-section geometry is transformed into a straight line. The mutual interference effects of the cruciform wings and the influences of the fuselage body are investigated in detail for heaving, pitching and rolling oscillations. Author N73-18007# Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt, Goettingen (West Germany). Inst. fuer Aeroelastik. UNSTEADY PRESSURE MEASUREMENTS ON A HARMON- ICALLY OSCILLATING WING MODEL IN THREE DI- MENSIONAL COMPRESSIBLE FLOW H. Triebstein 1972 135 p refs In GERMAN; ENGLISH summary (DLR-FB-72-55) Avail: NTIS HC $8.75; DFVLR Porz-Wahn: 43.20 DM Measurements of the unsteady pressure on a harmonically oscillating rectangular half wing model with control surface in three-dimensional compressible flow have been carried out at numerous parameter variations. For these measurements, which took place in the Transonic Wind Tunnel of DFVLR-AVA in Goettingen. a new test set-up has been developed. The model was performing pitching oscillations about the 1/4- and the half chord axis in the Mach regime Ma = 0.5 until 1.2: the Reynolds number regime was Re = 1.3 x 10 to the 6th power until 4.8 x 10 to the 6th power. The investigations have been carried out with reduced frequencies omega * = omega 1/2V = 0.051 up to 0.218. The experimental results are compared with corresponding theoretical results stemming from three-dimensional lifting surface theory and with relating experimental results from Nationaal Lucht- en Ruimtevaartlaboratorium. Amsterdam. In particular, the effects of the vibration amplitude, the angle of attack and the Reynolds number upon the unsteady pressure distributions were investigated in detail. Author N73-18008# Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt. Goettingen (West Germany). (AVA)- Abteilung. FORCE AND PRESSURE DISTRIBUTION MEASUREMENTS ON A WING-BODY COMBINATION WITH WING OF LOW ASPECT RATIO IN COMPRESSIBLE FLOW 199 N73 18010 W. Stahl. K. Hartmann. and W. Schneider 1972 39 p refs In GERMAN; ENGLISH summary (DLR-FB-72-08) Avail: NT|S HC $4.00: DFVLR Porz-Wahn: 12; DM In the transonic wind tunnel of the Aerodynamische Versuchsanstalt Goettingen experimental investigations were carried out on a wing-body combination with a delta wing of low aspect ration (Lambda = 0.52). The wing extended along most of the body, which was a circular cylinder with an ogival nose. Mach numbers ranged from Ma = 0.5 to 2.2, covering the transonic regime. Normal forces and pitching moments were measured as well as spanwise pressure distributions in several sections on the pressure and suction sides. Oil-flow and smoke pictures gave some insight into the flow field. The Reynolds number, formed with 2/3 of the length of the wing was held constant at Re = 2.700.000 for all Mach numbers. The influence of the Reynolds number was investigated at Mach numbers Ma = 0.5, 1.0 and 1.8. Angles of incidence varied from alpha approximates 0 deg to alpha approximates 30 deg. For comparison purposes the results of the wing alone were available: they had been obtained at AVA in earlier investigations. Author N73-18010*# National Aeronautics and Space Administration. Lewis Research Center. Cleveland. Ohio. THEORETICAL AND EXPERIMENTAL INTERNAL FLOW CHARACTERISTICS OF A 13.97 CENTIMETER-DIAMETER INLET AT STOL TAKEOFF AND APPROACH CONDITIONS James A. Albers Washington Mar. 1973 23 p refs. (NASA-TN-D-7185; E-7237) Avail: NTIS HC $3.00 CSCL 01A The theoretical and experimental internal flow characteristics of a 13.97-cm-diam inlet with centerbody retracted and extended are presented at STOL takeoff and approach operating conditions. The theoretical results were obtained from incompressible potential flow corrected for compressibility and boundary layer. Comparisons between theoretical internal surface static-pressure distributions and experimental data are presented for free-stream velocities of 0. 24, 32. and 45 m/sec for a range of inlet incidence angles from 0 to 50 deg. Surface static-pressure distributions are illustrated at circumferential locations of 0. 60, 120. and 180 deg. Surface Mach number distributions from the stagnation point to the diffuser exit are presented along with turbulent boundary-layer shape factors. In general, good agreement was found between the theoretical and experimental surface static pressure distributions. Author N73-18011*# Hamilton Standard, Windsor Locks. Conn. ANALYTICAL PARAMETRIC INVESTIGATION OF LOW PRESSURE RATIO FAN NOISE F. B. Metzger. D. B. Hanson, R. W. Menthe. and G. B. Towle Washington NASA Mar. 1973 118 p refs (Contract NAS1-10896) (NASA-CR-2188; HSER-5990) Avail: NTIS HC $3.00 CSCL 01 B The results of an analytical study are reported which shows the effect of various physical and operating parameters on noise produced by low pressure ratio propulsive fans operating at subsonic top speeds. Acoustical duct lining effects are included in the study. The concepts used to develop the noise theory used in the study, as well as the correlation between the theory and model test results are also presented. It is shown that good correlation has been established between theory and experiment. Using the theory, it is shown that good aerodynamic design, maximum acceptable fan solidity, low tip speed operation and use of few blades and vanes leads to the lowest noise levels. Typical results of the study indicate that a fan operating at 1 2 fan pressure ratio and 700 ft/second tip speed with 12 blades and 7 vanes and including modest acoustic treatment on the duct wall would produce levels allowing a 100.000 Ib. STOL aircraft to meet a noise level objective of 95 Pndb at 500 ft at takeoff. Author N73-18012*# National Aeronautics and Space Administration. Lewis Research Center. Cleveland. Ohio. EFFECTS OF VANE-INDUCED ROTATION ON DIFFUSER FLOW DISTORTION IN AN AXISYMMETRIC MIXED- COMPRESSION INLET Edward T. Meleason Washington Feb. 1972 36 p refs (NASA-TM-X-2752; E-7245) Avail: NTIS HC $3.00 CSCL 20D An investigation of vane-induced flow rotation to modify distorted steady-state total-pressure patterns in the subsonic diffuser of a supersonic mixed-compression inlet was conducted. Radial static-pressure gradients generated by the rotation were the mechanism used to modify the total-pressure distributions. Significant redistribution of circumferential distortion patterns into more compatible radial patterns was realized, but flow problems near the duct walls reduced the general effectiveness of the technique. Total-pressure losses associated with the swirl vanes were slight. Limited turbulence data indicated that vane installa- tion resulted in reduced turbulence levels Author N73-18013*# National Aeronautics and Space Administration. Flight Research Center. Edwards. Calif. MEASUREMENTS OF SURFACE-PRESSURE FLUCTUA- TIONS ON THE XB-70 AIRPLANE AT LOCAL MACH NUMBERS UP TO 2.45 Thomas L. Lewis, Jules B. Dods. Jr.. and Richard D. Hanly Washington Mar. 1973 35 p refs (NASA-TN-D-7226: H-714) Avail: NTIS HC $3.00 CSCL 01C Measurements of surface-pressure fluctuations were made at two locations on the XB-70 airplane for nine flight-test conditions encompassing a local Mach number range from 0.35 to 2.45. These measurements are presented in the form of estimated'power spectral densities, coherence functions, and narrow-band-convection velocities. The estimated power spectral densities compared favorably with wind-tunnel data obtained by other experimenters. The coherence function and convection velocity data supported conclusions by other experimenters that low-frequency surface-pressure fluctuations consist of small-scale turbulence components with low convection velocity. Author N73 18016# East Anglia Univ.. Norwich (England). School of Mathematics and Physics. CALCULATION OF THE EFFECT OF BLOWING FROM THE LEADING EDGES OF A SLENDER DELTA WING J. E. Barsby London Aeron. Res. Council. 1972 79 p refs Supersedes RAE-TR-71077: ARC-33029 Sponsored by Win. of Defence (ARC-R/M-3692: RAE-TR-71077: ARC-33029) Avail. NTIS HC $6.00; HMSO £ 2.75: PHI $10.80 The thin-jet model, applied to the study of the jet flap, is combined with the vortex-sheet model, applied to the study of leading-edge separation, to study the effect of blowing from the leading edges of a delta wing at incidence. A jet-vortex supporting a pressure difference related to the curvature of the streamlines in it. leaves the leading edge in a direction tangential to the wing plane and rolls up into a spiral above the wing. The inner part of the spiral is replaced by an asymptotic representation and the properties of this configuration are calculated by slender-body theory for the case of conical flow. The effect of the three basic parameters: the coefficient of blowing momentum, the initial angle between the jet streamlines and the leading edge, and the ratio of the angle of incidence to the apex angle of the wing, are covered in the calculations. Blowing is shown to increase the lift on the wing and to increase the circulation about the vortex, while displacing it upwards and outboard. Comparisons with experimental results are encouraging. Author (ESRO) N73-18018# Royal Aircraft Establishment, Farnborough. (Eng- land). Aerodynamics Dept. THE MEASUREMENT AND ANALYSIS OF THE PROFILE DRAG OF A WING WITH A SLOTTED FLAP I. R. M. Moir. 0. N. Foster, and D. R. Holt (Hawker Siddeley Aviation, Brough. Engl.) London Aeron. Res. Council 1972 37 p refs Supersedes RAE-TR-71158: ARC-33663 (ARC-CP-1233; RAE-TR-71158. ARC-33663) Avail: NTIS HC $4.00; HMSO 60 p: PHI $2.65 200 (M73-18024 Measurements of lift. drag, and pitching moments were made on a wing section for a range of flap deflections under conditions which were as close as possible to two-dimensional flow. The corrected data are presented together with the results of a semi-empirical analysis of sectional profile drag. It is shown that a consistent analysis can be made of the results over a range of flap angles and incidence, limited by a requirement for acceptable wing and flap boundary layer conditions, precluding significant flow separations. Under these conditions it appears that such an approach could serve as a general basis for correlating and interpreting experimental data on high-lift mechanical flap arrangements. Author (ESRO) N73-18019*# Youngstown State Univ.. Ohio. William Rayen School of Engineering. A SOLID STATE CONVERTER FOR MEASUREMENT OF AIRCRAFT NOISE AND SONIC BOOM Final Report. 1 Sep. 1971 - 31 Aug. 1972 Allan J. Zuckerwar 30 Nov. 1972 61 p refs (Grant NGR-36-028-004) (NASA-CR-112260) Avail: NTIS HC $5.25 CSCL 20A The problems inherent in present systems of instrumentation for measuring aircraft noise and sonic boom include limited frequency response, expensive connecting cables, sensitivity to cable length and type, high sensitivity to environmental conditions, and additional limitations of individual system components. Furthermore, differing requirements have resulted in the use of two different systems for aircraft noise and sonic boom measurements respectively. To alleviate these difficulties a unified system of instrumentation suitable for both types of measurements was developed. The system features a new solid state converter connected to a zero drive amplifier. The system was found insensitive to cable length and type up to at least 1000 ft and requires no impedance matching networks. The converter itself has flat frequency response from dc to 28 kHz (- 3 db). dynamic range of 72 db. and noise floor of 50 db in the band 22.4 Hz to 22.4 kHz. Author W73-18020*# California Inst. of Tech.. Pasadena. EXPERIMENTAL STUDY OF FLOW ABOUT A STALLED TWO-DIMENSIONAL AIRFOIL Semiannual Status Report. Jun. - Dec. 1972 D. Coles. A. Wadcock. and B. Cantwell Jan. 1973 25 p (Grant NGL-05-002-229) (NASA-CR-130919; SASR-2; SASR-3) Avail. NTIS HC $3.25 CSCL 01C Wind tunnel tests to determine the flow characteristics of a stalled wing are described. The advantages of the plane wing over the ring wing for wind tunnel investigations are presented. The general flow pattern for stalled ring airfoils is developed. Photographs of the test equipment and installation are provided. Author N73-18021*# National Aeronautics and Space Administration. Ames Research Center. Moffett Field. Calif. INITIAL FLIGHT AND SIMULATOR EVALUATION OF A HEAD UP DISPLAY FOR STANDARD AND NOISE ABATE- MENT VISUAL APPROACHES Kent Bourquin, Everett Palmer, George Cooper, and Ronald Gerdes Feb. 1973 39 p refs (NASA-TM-X-62187) Avail. NTIS HC $4.00 CSCL 01B A preliminary assessment was made of the adequacy of a simple head up display (HUD) for providing vertical guidance for flying noise abatement and standard visual approaches in a jet transport. The HUD featured gyro-stabilized approach angle scales which display the angle of declination to any point on the ground and a horizontal flight path bar which aids the pilot in his control of the aircraft flight path angle. Thirty-three standard and noise abatement approaches were flown in a Boeing 747 aircraft equipped with a head up display. The HUD was also simulated in a research simulator. The simulator was used to familiarize the pilots with the display and to determine the most suitable way to use the HUD for making high capture noise abatement approaches. Preliminary flight and simulator data arc presented and problem areas that require further investigation are identified. Author N73-18022»# Boeing Co.. Seattle. Wash. FLIGHT TEST MEASUREMENTS AND ANALYSIS OF SONIC BOOM PHENOMENA NEAR THE SHOCK WAVE EXTREMITY George T. Haglund and Edward J. Kane Washington NASA Feb. 1973 178 p refs (Contract NAS1-10992) (NASA-CR-2167: D6-4O758) Avail: NTIS HC $3.00 CSCL 20A The sonic boom flight test program conducted at Jackass Flats. Nevada, during the summer and fall of 1970 consisted of 121 sonic-boom-generating flights over the 1500ft instrumented BREN tower. This test program was designed to provide information on several aspects of sonic boom, including caustics produced by longitudinal accelerations, caustics produced by steady flight near the threshold Mach number, sonic boom characteristics near lateral cutoff, and the vertical extent of shock waves attached to near-sonic airplanes. The measured test data, except for the near-sonic flight data, were analyzed in detail to determine sonic boom characteristics for these flight conditions and to determine the accuracy and the range of validity of linear sonic boom theory. The caustic phenomena observed during the threshold Mach number flights and during the transonic acceleration flights are documented and analyzed in detail. The theory of geometric acoustics is shown to be capable of predicting shock wave-ground intersections, and current methods for calculating sonic boom pressure signature away from caustics are shown to be reasonably accurate. Author W73-18023# Advisory Group for Aerospace Research and Development. Paris (France). TECHNICAL EVALUATION REPORT ON FLUID DYNAMICS PANEL SPECIALISTS MEETING ON FLUID DYNAMICS OF AIRCRAFT STALLING R. C. Pankhurst (Royal Aircraft Estab, Teddington. UK) Nov. 1972 11 p refs Conf. held at Lisbon. 26-28 Apr. 1972 (AGARD-AR-49) Avail: NTIS HC $3.00 An evaluation of the fluid dynamics of aircraft stalling is presented. The aerodynamic characteristics of the aircraft stall at both low and high speeds are discussed. Particular reference is made to the design and operation of combat and transport aircraft, including buffet penetration and post-stall behavior. Major subject areas concern flight experience, flight testing, wind tunnel measurements, and theoretical prediction methods. The effects of three dimensional flow, the influence of sweep back, and the design and performance of light lift devices are analyzed. Author N73-18024*0 United Aircraft Corp.. Stratford. Conn. Sikorsky Aircraft Div. ACTIVE TRANSMISSION ISOLATION/ROTOR LOADS MEASUREMENT SYSTEM Final Report Irwin J. Kenigsberg and John J. DeFelice 1 Mar. 1973 139 p refs Sponsored in part by Army Air Mobility Res. and Devel. Lab (Contract NAS1-11549) (NASA-CR-112245; SER-50821) Avail: NTIS HC $9.00 CSCL 01B Modifications were incorporated into a helicopter active transmission isolation system to provide the capability of utilizing the system as a rotor force measuring device. These included: (1) isolator redesign to improve operation and minimize friction. (2) installation of pressure transducers in each isolator, and (3) load cells in series with each torque restraint link. Full scale vibration tests performed during this study on a CH-53A helicopter airframe verified that these modifications do not degrade the systems wide band isolation characteristics. Bench tests performed on each isolator unit indicated that steady and transient loads can be measured to within 1 percent of applied load. Individual isolator vibratory load measurement accuracy was determined to be 4 percent. Load measurement accuracy was found to be independent of variations in all basic isolator operating characteris- tics. Full scale system load calibration tests on the CH-53A airframe established the feasibility of simultaneously providing wide band vibration isolation and accurate measurement of rotor loads. Principal rotor loads (lift, propulsive force, and torque) were measured to within 2 percent of applied load. Author 201 N73-18025 N73-18025*# North Carolina State Univ., Raleigh. AN ANALYTICAL STUDY OF THE RESPONSE OF A CONSTANT-ATTITUDE AIRCRAFT TO ATMOSPHERIC TURBULENCE Frederick 0. Smetana and Ronald K. Garden Washington NASA Mar. 1973 51 p refs (Contract NAS1-9603) (NASA-CR-2204) Avail: NTIS HC $3.00 CSCL01B A light airplane equipped with an automatic control system which drives large wing flaps and the stabilator so as to produce a constant pitch attitude in all flight modes was analyzed for its response to a specific gust. The aircraft was also equipped with a bank-angle steering, zero sideslip automatic control system which wes studied for its effectiveness in suppressing a specific lateral gust. The gusts were assumed to be comprised of 200 lateral and 400 vertical sinusoids. Each was used to excite the controlled aircraft, and the time response to the sum of all sinusoids was plotted. The assumption was that the gust may be treated as stationary in space but variable in time rather than the reverse. Results indicate that such a control system can suppress vertical gusts up to the limit of control authority. Either the lateral accelerations or the yawing velocity response to lateral gusts -can be suppressed with this system but not both simultaneously. Author W73-18026# Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt, Stuttgart (West Germany). Inst. fuer Drehfluegelflugzeuge. CALCULATION OF THE FLAPWISE BENDING. EDGEWISE BENDING AND TORSIONAL VIBRATIONS OF ROTOR BLADES WITH COUPLED NATURAL MODES AND FRE- QUENCIES Hans Oette 1971 82 p refs In GERMAN; ENGLISH summary (DLR-FB-71-108) Avail: NTIS HC $6.25: DFVLR Porz: 18.50 DM The natural mode method is expanded from one to two degrees of freedom for three coupled degrees of flapwise bending, edgewise bending and torsion. For the coupled natural modes known, the orthogonal relations are arranged and the differen- tial equations for the generalized degrees of freedom are derived. The theory is still extended by adding the moment of inertia due to the extension of the blade across to its axis and applying a flapping coordinate system. For the numerical examples the following items are taken into account: The forward flight data of the S-61 -helicopter, coupled natural modes computed by the multihinge articulated blade method, and schematized nonstationary aerodynamic coefficient curves. Author W73-18027# Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt, Goettingen (West Germany). Inst. fuer Aeroelastik. DYNAMIC AND AEROELASTIC PROBLEMS OF STOP- ROTORS AND THEIR ANALYTICAL TREATMENT. PART 1: ANALYTICAL DETERMINATION OF THE NATURAL VIBRATIONS OF ROTOR BLADES AND THE STEADY AND UNSTEADY AIRLOADS ON THE BLADE DURING STOPPING AND RETRACTING H. Foersching and G. Kotowski 1972 133 p refs In GERMAN; ENGLISH summary (DLR-FB-72-66-Pt-1) Avail: NTIS HC $8.75; DFVLR Porz-Wahn: 42 DM Some dynamic and aeroelastic problems of stop-rotors of V/STOL-aircraft. occurring during retracting and stowing the blades, are treated in detail. In the first part of the investigations presented in this report first the physical background of rotor dynamic phenomena is discussed by means of some typical experimental results. Then, for an analytical treatment of these problems, the basic elastomechanical and aerodynamic relations are elaborated, in particular, methods for calculating the char- acteristic vibration behavior of rotor blades with initial twist, the generalized dynamic equations, and the aerodynamic loads on the blade during stopping and retracting. As a typical example the calculation of the natural vibrations of a rotor blade is presented in an appendix. , Author W73-18028# Toronto Univ. (Ontario). Inst. for Aerospace Studies. A DETERMINISTIC MODEL OF SONIC BOOM PROPAGA- TION THROUGH A TURBULENT ATMOSPHERE B. H. K. Lee and H. S. Ribner Ottawa Natl. Res. Council of Can. Nov. 1972 24 p refs Sponsored by Natl. Res. Council of Can. (NRC-12981; LR-566) Avail: NTIS HC $3.25 The propagation of a. weak normal shock wave- through a turbulent atmosphere is studied in terms of an idealized model. The turbulent field is assumed to be weak anti represented by the superposition of two inclined shear waves of opposite inclination to the mean flow. The resulting flow is of a cellular nature. The cells are rectangular in shape and the sense of rotation of the flow alternates from cell to cell. If the angles made by the normal of the incident shear waves with the direction of the mean flow are greater than some critical value, an exponentially decaying pressure wave is generated behind the shock. Spiked or rounded waveforms are obtained by adding or subtracting this pressure wave from the steady state pressure field. An illustrative example for a mean flow Mach number of 1.0005 is considered. This gives a steady state overpressure of 2.45 pounds per square foot across the shock which is typical of the overpressure in a sonic boom. Author N73-18029# Cranfield Inst. of Technology (England). Coll. of Aeronautics. A COMPARATIVE ASSESSMENT OF THREE METHODS OF MEASUREMENT OF PRESSURE ERROR CORRECTIONS M. E. Eshelby Jun. 1972 25 p refs (CRANFIELD-AERO-11) Avail: NTIS HC $3.25 Three methods of evaluating the pressure error of an aircraft pilot-static system are presented. The relative merits of each method are compared. In particular the determination of static pressure error by a trailing cone is considered as a method suitable for use on light aircraft and comparison is made between the pressure error measured by the cone and the other methods. Author N73-18030# Advisory Group for Aerospace Research and Development, Paris (France). RECENT DEVELOPMENTS IN FLIGHT FLUTTER TESTING IN THE UNITED STATES. SUPPLEMENT TO THE MANUAL ON AEROELASTICITY. VOLUME 4. CHAPTER 10 E. F. Baird (Grumman Aerospace Corp.) and W. B. Clark (Grumman Aerospace Corp.) Dec. 1972 27 p refs Presented at 34th AGARD Struct, and Mater. Panel Meeting, Lyngby. Denmark. 11 Apr. 1972 (AGARD-R-596) Avail: NTIS HC $3.50 Advances in the rapid and accurate determination of flutter characteristics through the use of high speed computers are discussed. Comments are presented on some flight flutter testing procedures in use and under development. A model matching technique is described. This technique reduces data analysis time and is compatible with relatively fast data acquisition. Results of model matching when applied to theoretical response data are presented and compared with actual flight flutter testing. Author N73-18031°# National Aeronautics and Space Administration. Ames Research Center. Moffett Field, Calif. TAKEOFF CERTIFICATION CONSIDERATIONS FOR LARGE SUBSONIC AND SUPERSONIC TRANSPORT AIRPLANES USING THE AMES FLIGHT SIMULATOR FOR ADVANCED AIRCRAFT C. Thomas Snyder, Fred J. Drinkwater. III. Emmett B. Fry, and Raymond D. Forrest (FAA, Washington. D. C.) Washington Mar. 1973 76 p refs Prepared in cooperation with FAA. Washington, D. C. (NASA-TN-D-7106; A-3778) Avail: NTIS HC $3.00 CSCL 018 Data for use in development of takeoff airworthiness standards for new aircraft designs such as the supersonic transport (SST) and the large wide-body subsonic jet transport are provided. An advanced motion simulator was used to compare the performance and handling characteristics of three representative large jet transports during specific flight certification tasks. Existing regulatory constraints and methods for determining rotation speed were reviewed, and the effects on takeoff performance of variations 202 N73-18039 in- rotation speed/ pitch attitude, and pitch attitude rate during the rotation maneuver were analyzed. A limited quantity of refused takeoff information was obtained. The aerodynamics, wing loading, and thrust-to-weight ratio of the subject SST resulted in takeoff speeds limited by climb (rather than lift-off) considerations. Take-off speeds based on U.S. subsonic transport requirements were found unacceptable because of the criticality of rotation- abuse effects on one-engine-inoperative climb performance. Adequate safety margin was provided by takeoff speeds based on proposed Anglo-French supersonic transport (TSS) criteria, with the limiting criterion being that takeoff safety speed be at least 1.16 times the one-engine-inoperative zero-rate-of-climb speed. Various observations related to SST certification are presented. Author N73-18032# Aeronautical Center. Oklahoma City. Okla. Flight Standards Technical Div. A SUMMARY OF CRASHWORTHINESS INFORMATION FOR SMALL AIRPLANES Feb. 1973 125 p refs IFAA-TR-FS-70-592-120A) Avail: NTIS HC $8.25 An analysis of parameters affecting the safety of occupants of light aircraft in the event of a crash is presented. The data involves: (1) airframe design, (2) interior components. (3) restraint systems, (4) protective padding, and (5) types of hazards encountered. The test facilities and research programs for simulating aircraft accidents to determine extent of aircraft damage and nature of the forces developed are described. Human tolerance to impact deceleration forces and the extremity strike envelope for the human body under various types of restraint are analyzed. • P.N.F. N73-18033I Cranfield Inst. of Technology (England). AEROPLANE DESIGN STUDY STOL AIRLINER (A71). PART 2: DETAIL DESIGN FEATURES D. Howe Jul. 1972 33 p refs (AERO-13-Pt-2) Avail: NTIS HC $3.75 Detail design features of a short takeoff and landing commercial aircraft are presented. The design of the structures and systems is conventional in most respects. The need to provide a long stroke undercarriage for STOL operations incurred a large weight penalty. The design has demonstrated an inability to cope with engine failure and gusting cross wind conditions. The effect of the STOL requirement on the overall airframe construction is analyzed. Author N73-18034*# Lockheed-California Co., Van Nuys. Rotary Wing Div. VIBRATION AND LOADS IN HINGELESS ROTORS. VOLUME 1: THEORETICAL ANALYSES G. A. Watts and' R. J. London Sep. 1972 278 p refs Sponsored in part by Army Air Mobility Res. and Develop. Lab. 2 Vol. (Contract NAS2-5168) (NASA-CR-114562) Avail: NTIS HC $16.00 CSCL01C Analytic methods are developed for calculating blade loads and shaft-transmitted vibratory forces in stiff bladed hingeless rotors operating at advance ratios from mu = .3 to mu = 2.0. Calculated shaft harmonic moments compared well with experimental values when the blade first flap frequency was in the region of two-per-revolution harmonic excitation. Calculated blade bending moment azimuthal distributions due to changes in cyclic pitch agreed well with experiment at radial stations near the blade root at values of the ratio of first flap frequency to rotor rotation rate from 1.5 to 5.0. At stations near the blade tip good agreement was only obtained at the higher values of frequency ratio. Author N73-18035*# Lockheed-California Co.. Van Nuys. Rotary Wing Div. VIBRATION AND LOADS IN HINGELESS ROTORS. VOLUME 2: EXPERIMENTAL DATA G. A. Wans and R. J. London Sep. 1972 272 p refs Sponsored in part by Army Air Mobility'Res. and Develop. Lab. 2 Vol. (Contract NAS2-5168) (NASA-CR-114568) Avail: NTIS HC $15.75 CSCL 01C Descriptions, geometry, and technical data covering three rotor systems are presented. Tables of experimental data gathered during wind tunnel testing of two of the systems are included. Both analyzed experimental data, ready for comparison with theory, and the basic reduced data from which they were obtained are reported. • Author N73-18036*# LTV Aerospace Corp.. Hampton. Va. A STUDY OF THE EFFECTS OF AEROELASTIC DIVER- GENCE ON THE WING STRUCTURE OF AN OBLIQUE-WING SUPERSONIC TRANSPORT CONFIGURATION Jan. 1973 17 p refs (Contract NAS1-10900) (NASA-CR-112262) Avail: NTIS HC $3.00 CSCL 018 The aerodynamic characteristics of transport aircraft with oblique wing flying at supersonic speeds are discussed. Aeroelastic divergence of the forward swept portion of the wing is analyzed. The effect of aspect ratio as a method for avoiding aeroelastic divergence is examined. A relatively low aspect ratio appears necessary for an oblique wing when constructed of conventional aluminum alloy materials. The aspect ratio may be increased by increasing the wing thickness ratio and by utilizing materials with higher moduli of elasticity and rigidity. Author N73-18037*# North Carolina State Univ.. Raleigh. A DESIGN STUDY FOR A SIMPLE-TO-FLY. CONSTANT ATTITUDE LIGHT AIRCRAFT Frederick 0. Smetana. Douglas E. Humphreys, Rafael J. Montoya, William W. Rickard. and Ivan E. Wilkinson Washington NASA Mar. 1973 322 p refs (Grant NGR-34-002-086) (NASA-CR-2208) Avail: NTIS HC $6.00 CSCL 01B The activities during a four-year study by doctoral students to evolve in detail a design for a simple-to-fly. constant attitude light airplane are described. The study indicated that such aircraft could materially reduce the hazards to light airplane occupants which arise from the high pilot work load and poor visibility that occur during landing. Preliminary cost studies indicate that in volume production this system would increase the cost of the aircraft in roughly the same fashion that automatic transmis- sion, power steering, power brakes, and cruise control increase the cost of a compact car. Author N73-1B038*# Boeing Co.. Seattle. Wash. CONCEPTUAL DESIGN STUDIES OF CANDIDATE V/STOL LIFT FAN COMMERCIAL SHORT HAUL TRANSPORT FOR 1980 - 1986 V/STOL LIFT FAN STUDY W. M. Eldridge. J. A. Ferrell. J. W. McKee. J. E. Wayne. Jr.. and J. M. Zabinsky Washington NASA Feb. 1973 100 p refs (Contract NAS2-6563) (NASA-CR-2183) Avail: NTIS HC $3.00 CSCL 01C Conceptual designs of V/STOL lift fan commercial short haul transport aircraft for the 1980-85 time period were studied to determine their technical and economic feasibility. The engine concepts included both integral and remote fans. The scope of the study included definition of the hover control concept for each propulsion system, aircraft design, aircraft mass properties, cruise performance, noise and ride qualities evaluation. Economic evaluating was also studied on a basis of direct operating costs and route structure. Author N73-18039*# National Aeronautics and Space Administration. Lewis Research Center, Cleveland. Ohio. PRELIMINARY STUDY OF SUPERSONIC-TRANSPORT CONFIGURATIONS WITH LOW VALUES OF SONIC BOOM James F. Dugan. Jr. Washington Mar. 1973 36 p refs (NASA-TM-X-2746; E-6770) Avail: NTIS HC $3.00 CSCL QIC A parametric study of low-boom supersonic transport airplanes with conventional configurations was made.to identify the features of specific configurations that promise relatively low sonic boom overpressures (less than 47.9 N/sq m). The range of values considered was gross weight from 28.300 to 170.000 kg: cruise Mach numbers, of 2 to 3.2: and wing loadings of 1436, 2870. and 4309 N/sq m. Fuselage length was varied from 49.1 to 203 N73-18040 102.4 m and fuselage diameter from 2.75 to 3.98 m. A nominal Mach 2 configuration weighing 56.700 kg and having a wing loading of 2870 N/sq m was selected: and its gross geometric, aerodynamic, and structural features were estimated. At a cruise altitude of 18.300 m. lift-drag ratio was estimated to be 7.35. while sonic boom overpressure was 41.7 N/sq m. Takeoff thrust loading using four afterburning turbojet engines at maximum dry thrust was 6.32. Payload for a 4440-km range was 16.7 percent of gross weight, giving a direct operating cost of 0.82 cents per seat / statute mile. Author N73-18040*# National Aeronautics and Space Administration. Lewis Research Center. Cleveland. Ohio. ALUMINUM RUNWAY SURFACE AS POSSIBLE AID TO AIRCRAFT BRAKING C. David Miller and I. Irving Pinkel ' Washington Mar. 1973 33 p refs (NASA-TN-D-7186; E-7046) Avail: NTIS HC $3.00 CSCL DIE . Several concepts are described for use singly or in combination to improve aircraft braking. All involve a thin layer of aluminum covering all or part of the runway. Advantage would derive from faster heat conduction from the tire-runway interface. Heating of tread surface with consequent softening and loss of friction coefficient should be reduced. Equations are developed indicating that at least 99 percent of friction heat should flow into the aluminum. Preliminary test results indicate a coefficient of sliding friction of 1.4. with predictably slight heating of tread. Elimination of conventional brakes is at least a remote possibility. Author N73-18041*# National Aeronautics and Space Administration. Ames Research Center. Moffett Field. Calif. ACOUSTIC CHARACTERISTICS OF A SEMISPAN WING EQUIPPED WITH AN EXTERNALLY BLOWN. JET FLAP INCLUDING RESULTS AT FORWARD SPEED Michael D. Falarski Washington Mar. 1973 84 p refs Prepared in cooperation with Army Air Mobility R and D Lab., Moffett Field. Calif. (NASA-TM-X-2749: A-4469) Avail:. NTIS HC $3.00 CSCL 01B A wind-tunnel investigation was made of the noise characteris- tics of a 14.5-ft semispan. externally blown jet flap model. The model was equipped with a single 30-in. diameter, ducted fan with a 1.03 pressure ratio. The effects of flap size, fan vertical location, and forward speed on the noise characteristics were studied. With the ducted fan mounted 0.79 or 1.24 diameters below the wing and a flap chord greater than 50 percent, the peak perceived noise level increased 2 to 3 Pndb when the flap was deflected to 90 deg. The jet scrubbing noise .increased 3 to 4 db when the flap was deflected 90 deg. Installation of the fan on the wing was responsible for 1 to 2 db of this change. Forward speed did not have a significant effect on the perceived noise level, although it did cause a reduction in the sound pressure levels of the first and second fan harmonics. Author i N73-18042*# Michigan Univ.. Ann Arbor. A STUDY OF THE DYNAMIC TIRE PROPERTIES OVER A RANGE OF TIRE CONSTRUCTIONS G. H. Nybakken. R. N. Dodge, and S. K. Dark Washington NASA Mar. 1973 35 p refs Revised ' (Grant NGL-23-005-010)' (NASA-CR-2219; Rept-056080-19-T-Rev) Avail: NTIS HC $3.00 CSCL 01C The dynamic properties of four model aircraft tires of various construction were evaluated experimentally and compared with available theory. The experimental investigation consisted of measuring the cornering force and the self-aligning torque developed by the tires undergoing sinusoidal steering inputs while operating on a small scale, road-wheel tire testing apparatus. The force and moment data from the different tires are compared with both finite- and point-contact patch string theory predictions. In general, agreement between finite contact patch theory and experimental observation is good. A modified string theory is also presented in which coefficients for cornering force and self-aligning torque are determined separately. This theory improves'the correspondence between the experimental and analytical data, particularly on tire's with relatively high self-aligning torques. . Author N73-18044# Dornier.-Werke G.m.b.H., Friedrichshafen (West Germany). RESULTS AND KNOWLEDGE GAINED IN AERODYNAMIC JET INTERFERENCE FROM THE VSTOL JET TRANSPORT AIRCRAFT DO 31 AND THEIR APPLICATION TO FUTURE VSTOL DEVELOPMENTS [ERGEBNISSE UNO ERFAHRUN- GEN ZUR AERODYNAMISCHEN STRAHLINTERFERENZ BEIM VSTOL-STRAHLTRANSPORTFLUGZEUG DO 31 UND IHRE ANWENDUNG AUF ZUKUENFTIGE VSTOC- ENTWICKLUNGEN] '• Dieter Welte Bonn Bundeswehramt 1972 183 p refs In GERMAN: ENGLISH summary Sponsored by Bundesmin. filer Verteidigung ' • . (BMVg-FBWT-72-22) Avail: NTIS HC $11.25: Bundeswehramt 25 DM The most important results concerning jet interference effects for the Do-31 aircraft, resulting from wind tunnel model measurements and flight tests, are presented, and an estimation is given of jet interference effects for future VSTOL project studies. Calculations are based on a single semi-empirical method for determination of jet-induced lift-loss in hovering for simple configurations such as the Do-31. and it is possible to calculate the lift-loss to within 1 percent accuracy. The investigation of the jet-induced flow field around the Do-31 during hovering with ground effect'and in the transition flight regime yielded a rough estimation of the jet interference effects for future VSTOL studies. ESRO N73-18O45# Dornier-Werke G.m.b.H.. Friedrichshafen (West Germany). ' SOUND RADIATION IN THE SHORT AND LONG RANGE OF THE VSTOL, JET TRANSPORT AIRCRAFT DO 31 AND NOISE REDUCTION POSSIBILITIES FOR FUTURE V/STOL DEVELOPMENTS [SCHALLABSTRAHLUNG IM NAH- UND FERNFELO DiS VSTOL-STRAHLTRANSPORTERS DO 31 UND LAERMMINDERUNGSMOEGLICHKEITEN BEI ZU- KUENFTIGEN VSTOL-ENTWICKLUNGEN] > Peter Bartels Bonn Bundeswehramt 1972 167 p refs In GERMAN: ENGLISH summary Sponsored by Bundesmin. der Verteidigung :(BMVg-FBWT-72-23) Avail: NTIS HC $10.50: Bundeswehramt 25 DM Results of theoretical and experimental investigations of noise in the near and far field of the VSTOL jet transport aircraft Do 31 are presented in .condensed form. Particular attention was given to the problem of aircraft noise reduction in the vicinity of existing airports, which is already possible with the Do 31, and to the noise and noise reduction of existing and future VSTOL concepts. The high flexibility in the selection of flight procedures makes the VSTOL aircraft the only vehicle adaptable to local circumstances. This is important not only from a military point of view, but more generally for optimal economy and noise reduction. > Author (ESRO) N73-18046# Dornier-Werke G.m.b.H., Friedrichshafen (West Germany). THE DO 31 LANDING LOADS DURING VERTICAL LANDING AND THEIR CONSEQUENCES FOR FUTURE VSTOL DEVELOPMENTS [DIE LANDELASTEN DER DO 31 BEI VERTIKALLANDUNGEN UND FOLGERUNGEN FUER ZUKUENFTIGE VSTOL-ENTWICKLUNGEN] Wolfgang Schoernack Bonn Bundeswehramt 1972 72 p refs In GERMAN: ENGLISH summary Sponsored by Bundesmin. der Verteidigung' ' (BMVg-FBWT-72-24) Avail: NTIS HC $5.75: Bundeswehramt 25 DM The results of 83 vertical landings carried out during the Do 31 VSTOL Experimental Program are reported. During 23 landings, undercarriage reactions, as well as sinking speeds were measured: of the remaining 60 landings only sinking speeds could be evaluated. Undercarriage reaction factors and sinking 204 N73-18053 speeds are plotted as frequency distributions and discussed. The result of the evaluation of the landing experiments can be summarized as follows: VTOL airplanes of a conception similar to the Do 31 and using manual control during the end of descent would experience considerably higher sinking speeds than conventional aircraft. Furthermore, a typical jumping of the airplane after touchdown and a following second impact prove unfavorable, this second impact resulting in higher undercarriage reactions than the first one: The horizontal lo'ads occurring with vertical landings are smaller than expected. Author (ESRO) N73-18047# Honeywell. Inc.. Minneapolis. Minn. Systems and {Research Div. . . . AN INVESTIGATION OF AIRBORNE DISPLAYS AND CONTROLS FOR SEARCH AND RESCUE (SARI. VOLUME 6: AVIONICS REQUIREMENTS FOR THE HH-53C HELICOP- TER Final Report. Sep. 1971 - Jan. 1972 0. Herbert LJndquist. B. A. Olson. A. Jones, and James W. Wingert May 1972 103 p refs (Contract N00014-69-C-0406; NR Proj. 213-072) (AD-752625; HONEYWELL-12609-FR1-Vol-6; JANAIR-720902-Vol-6) Avail: NTIS CSCL 06/7 An analytical study was conducted to define the avionics system and the display and controls concept required for the HH-53C helicopter so that it could accomplish the USAF's all-weather SAR mission. The study tasks included development of an avionics concept based on a representative mission scenario, avionics and sensor package selection, a man/machine function allocation and crew workload analysis. A recommended avionics configuration was defined. The HH-53C can be upgraded by an avionics configuration, within the cost constraints, to perform the all-weather SAR mission. This upgraded HH-53C can be operated by the crew within their workload limitations. Author (GRA) N73-18048# Air Force Systems Command. Wright-Patterson AFB, Ohio. Foreign Technology Div. DETERMINATION OF THE OPTIMUM REVERSING COEF- FICIENT OF THRUST REVERSALS FOR THE ENGINES OF PASSENGER AIRCRAFT A. G. Gilerson 7 Nov. 1972 11 p refs Transl. into ENGLISH from Tr. Aviats. Inst. (Kazan), no. 127. 1970 p 28-34 (AD-752814; FTD-MT-24-1482-72) Avail: NTIS CSCL 01/2 A simple empirical method is proposed for determining the overall required negative thrust and the required coefficient of reversal based on average statistical data on the magnitude of the reversible thrust capacity (ratio of the overall thrust of the reverser to the weight of the aircraft) of modern passenger airplanes with thrust reverser. This ratio for various types of aircraft ranges from 0.24 to 0.30 (the larger figures apply to number of engines with thrust reverser as a function of the coefficient of reversal). Author (GRA) N73-18049# Naval Aerospace Medical Research Lab.. Pensacola. Fla. MAJOR ORIENTATION-ERROR ACCIDENTS IN REGULAR ARMY UH-1 AIRCRAFT DURING FISCAL YEAR 1969: ACCIDENT FACTORS W. Carroll Hixson. Jorma I. Niven. and Emil Spezia Oct. 1972 39 p refs Prepared in cooperation with Army Aeromed. Res. Lab.. Fort Rucker. Ala. (MF51524005) (AD-753208: NAMRL-1169; USAARL-73-2) Avail: NTIS CSCL 01/2 The report is the third dealing with pilot disorientation/vertigo problem in Regular Army UH-1 helicopter operations. Individual case history data extracted from the USABAAR master aircraft accident files are presented on 44 major orientation-error accidents that occurred in UH-1 aircraft during fiscal year 1969. Summary data listings involving a variety of operational and pilot-related accident factors are presented for each of the cases. Author (GRA) N73-18050# Naval Air Development Center. Warminster. Pa. Air Vehicle Technology Dept. PRELIMINARY DESIGN AND COST STUDY OF RECIRCULA- TING CHROMATE RINSE SYSTEM FOR A IRCRAFT CORROSION CONTROL K. G. ClaVk and W. C. Hallow 2 Nov. 1972 20 p refs (AD-753214: NADC-72183-VT) Avail: NTIS CSCL 01/3 Aircraft rinse facilities are presently employed to remove corrosive salt deposits from aircraft operating in salt laden environments. While water rinsing has been effective in reducing corrosion, the rate of attack can be further reduced by introducing a small amount of corrosion inhibitor, such as potassium dichromate. into the rinse water. The report presents a preliminary design and cost study for such a recirculating chromate rinse system. GRA N73-18051# Pennsylvania State Univ.. University Park. Dept. of Aerospace Engineering. A NUMERICAL SOLUTION FOR AN UNSTEADY TWO- DIMENSIONAL JET-FLAPPED WING Glen E. Potter Nov. 1972 81 p refs (Grant DA-ARO(D)-31-124-G13) (AD-752928: AROD-9334-1-E) Avail: NTIS CSCL 01/3 A numerical solution of the two-dimensional jet-flapped airfoil utilizing discrete vortices to represent airfoil and jet vortex distributions is presented for two time-dependent cases. The first concerns an instantaneous deflection of the jet exit angle and the second case involves continuous oscillation of the jet angle. • Author (GRA) N73-18052$ • Naval Air Development Center. Warminster. Pa. Systems Analysis and Engineering Dept. OPTIMAL CONTROL OF THE F-8C IN A FULLY AUTOMATIC CARRIER APPROACH Final Report ' Roger J. Bannett 7 Nov. 1972 142 p refs • ' (AD-753010: NADC-SD-7153) Avail: NTIS CSCL 01/2 The report presents a detailed exposition of the problems associated with landing high performance jet fighter aircraft on board a moving aircraft carrier along with a new procedure for designing a fully automatic flight control system tailored to the aircraft carrier approach. Included in the development is a brief description of the present SPN-42 ACLS (Aircraft Carrier Landing System) and the probable reason for its very limited success. Possible alternatives to the SPN-42 system have suggested a more sophisticated ACLS configuration, in particular, the AMOAC (Automatic Multiloop Optimal Approach Controller) developed herein. The use of an AMOAC system in actual carrier approaches should yield a substantial improvement to present automatic carrier landing capability. Author (GRA) N73-18053# United Aircraft Corp.. East Hartford. Conn. Research Labs. INVESTIGATION OF AIRFOIL DYNAMIC STALL. AND ITS INFLUENCE ON HELICOPTER CONTROL LOADS Final .Report Franklin 0. Carta. Gerald L Commerford. Raymond G. Carlson, and Robert H. Blackwell Sep. 1972 209 p refs (Contract DAAJ02-71-C-0003: DA Proj. 1 F1-62204-A-139) (AD-752917; USAAMRDL-TR-72-51) Avail: NTIS CSCL 01/3 Measurements were made of the unsteady normal force and pitching moment on an NACA 0012 airfoil model oscillated both sinusoidally and nonsinusoidally over a range of incidence angles, including a substantial penetration into stall. The sinusoidal normal force and pitching moment data were reduced and tabulated as functions of the angle of attack, the angular velocity parameter, and the angular acceleration parameter. This generalized form of the data was used to reconstruct the measured sinusoidal aerodynamic response of the model airfoil with excellent results. Additional correlations were made using nonsinusoidal pitch schedules which included periodic ramp changes in angle of attack and a flexured angular blade response to a one-per-rev sinusoidal incidence angle change typical of that for a helicopter blade. The agreement between predicted and measured normal force and moment loops was very good for the ramp motion. Author (GRA) 205 N73-18054 N73-18054/J/ Air Force Systems Command. Wright-Patterson •AFB. Ohio. Foreign Technology Div. FLOW AROUND WING PROFILE WITH THE PRESENCE ON THE SURFACE OF A SYSTEM OF SOURCES AND SINKS B. S. Baev and V. N. Zhuravlev 20 Oct. 1972 12 p refs Transl. into ENGLISH of Teplo- i Massoperenos (USSR), no. 12. 1969 p 383-386 (FTD Pro). T70-01-12) (AD-752686; FTD-HT-23-834-72) Avail: NTIS CSCL 01/3 The article examines the determination of aerodynamic characteristics during flow around a profile by a plane-parallel flow of an incompressible, ideal fluid for the following arrange- ments: a sink and source in a single plane: a sink and source in different planes: a sink on the upper surface. The solution is carried out by applying the theory of the function of a complex variable and by the method of the conformal transformation of a unit circle onto the profile. Author (GRA) N73-18066# Schjeldahl (G. T.) Co.. Northfield. Minn. Advanced Programs Oiv. DESIGN AND MANUFACTURE OF A 670,000 CUBIC FOOT NATURAL SHAPE BALLOON FOR PROJECT POBAL Final Report, Oct. 1971 - Aug. 1972 James B. Munson 15 Sep. 1972 62 p refs (Contract F19628-72-C-0108) (AD-753086; SER-0159: AFCRL-72-0614) Avail: NTIS CSCL 01/3 The configuration and manufacture of a 670.000 cubic foot, natural, shape, zero pressure, free flight balloon is described. Requirements, design calculations, documentation, fabrication, testing and inspection are discussed. Author (GRA) N73-18056# Environmental Health Lab., Kelly AFB, Tex. NOISE SURVEY. F-105 OVERFLIGHTS. WICHITA MOUN- TAINS WILDLIFE REFUGE AND VICINITY. FORT SILL, OKLAHOMA Ah/in R. Frazier Sep. 1972 70 p refs (AD-753113: EHL(K)-72-21) Avail: NTIS CSCL 06/6 A noise survey quantitated the environmental noise levels which would be produced by F-105 aircraft flights over the Quanah Weapons Range located on Fort Sill. Data were obtained at a nearby Job Corp Center, Camp Boulder located on the adjoining Wichita Mountains Wildlife Refuge and the cities of . Cache and Indiahoma. Adverse effects on the environment are predicted to be minimal and serious interference with present or future land uses is not expected. After serious consideration of many factors, the benefits to be gained through the proposed joint use of this existing artillery range outweigh the minimal adverse effects that would develop because of the flyby noise. Author (GRA) N73-18067# Logistics Management Inst.. Washington. D.C. OPTIMUM SERVICE LIFE DETERMINATION TECHNIQUE Nov. 1972 70 p refs (Contract SD-271: SD Pro). 271-168) (AD-752747: LMI-72-12) Avail: NTIS CSCL 01/3 The report describes efforts by LMI to determine feasible methods of attaining the following dual interrelated objectives: to improved long-range predictions of the safe remaining structural life of groups of Naval aircraft (e.g.. all Navy F-4Bs) to be used statistically to facilitate and support decisions regarding major structural modification programs, programmed aircraft model service life and service life extensions, and planning of the future military role to be filled by given aircraft models, and to improved short-range predictions of the structural condition of individual Naval aircraft, which can be used to develop a maintenance strategy (e.g., inspection intervals) which would increase the probability of aircraft meeting operational commit- ments without major structural problems. Author (GRA) N73-18058# Northrop Corp., Palos Verdes Peninsula. Calif. Electronics Div. UN-1 TEST BED PROGRAM, VOLUME 1 Final Report Robert R. Butcher. Russell Kirby. Jr.. John Nakakihara. and T. C. Watkins Jun. 1972 418 p refs (Contract DAAJ01-70-C-0828: DA Proj. 1F1-64204-DC-32) (AD-752890: NORT-71-293A-Vol-1: USAAVSCOM-TR-72-19-Vol-1) Avail: NTIS CSCL 01/3 The UH-1H helicopter test bed program was accomplished at the U.S. Army Aeronautical Depot Maintenance Center (ARADMAC). Corpus Christ i.'Texas, during the period 4 October 1970 through 17 December 1971. The program objective was to determine the capability of state-of-the-art hardware to automatically accomplish inspection, diagnostic and prognostic maintenance functions on selected subsystems of the UH-1H helicopter. Northrop's hardware for the program is identified as a Maintenance Reporting System (MRS). Helicopter components, both serviceable and degraded, were run and monitored for malfunction discrimination by the MRS in ARADMAC test cells and in two UH-1 H aircraft. Trending for prognosis was attempted while accumulating flight time on two additional UH-1H aircraft utilizing serviceable components. The test results demonstrated the objectives of the test bed program. Author (GRA) N73-18059# Northrop Corp.. Palos Verdes Peninsula. Calif. Electronics Div. UH-1 TEST BED PROGRAM. VOLUME 2 Final Report Robert R. Butcher. Russell Kirby. Jr.. John Nakakihara. and T. C. Watkins Jun. 1972 111 p (Contract DAAJ01-70-C-0828) (AD-752891: NORT-72-220A-Vol-2: USAAVSCOM-TR-72-19-Vol-2) Avail: NTIS CSCL 01/3 The document presents accomplishments during Phase E of the UH-1H Helicopter Test Bed Program for an Automatic Inspection. Diagnostic and Prognostic System conducted at the U.S. Army Aeronautical Depot Maintenance Center (ARADMAC). Corpus Christi. Texas, from 1 October 1971 through 17 December 1971. , Author (GRA) N73-18060# Hamilton Standard. Windsor Locks. Conn. UH-1H AIDAPS TEST BED PROGRAM. VOLUME 1 Final Report. 4 Oct. 1970 - 17 Dec. 1971 James Provenzano. John Games. Al Wyrostek. Art Ostheimer. and Jack Young 31 Aug. 1972 347 p (Contract DAAJ01-70-C-0827; DA Proj. 1F1-64204-DC-32) (AD-752893: HSER-6080-Vol-1; USAAVSCOM-TR-72-18-VOI-1) Avail: NTIS CSCL 01/3 The UH-1H helicopter Test Bed Program was accomplished at the U.S. Army Aeronautical Depot Maintenance Center, Corpus Christi. Texas, during the period 4 October 1970 through 17 December 1971. The program objective was to determine the feasibility of state-of-the-art hardware to automatically accomplish inspection, diagnostic and prognostic maintenance functions on selected subsystems of the UH-1H helicopter. The Hamilton Standard hardware for the program is identified as Airborne Integrated Diagnostic System (AIDS). Helicopter components, both serviceable and degraded, were run and monitored for malfunction discrimination by the AIDS in ARADMAC test cells and in two UH-1H aircraft. Trending for prognosis was attempted while accumulating flight time on two additional UH-1H aircraft utilizing serviceable components. Author (GRA) N73-18061# Hamilton Standard. Windsor Locks. Conn. UH-1H AIDAPS TEST BED PROGRAM, VOLUME 2 Final Technical Report James Provenzano. John Games, Al Wyrostek. Art Ostheimer. and Jack Young Aug. 1972 345 p (Contract DAAJ01-70-C-0827; DA Proj. 1F1-64204-DC-32) (AD-752894; HSER-6080-Vol-2: USAAVSCOM-TR-72-18-Vol-2) Avail. NTIS CSCL 01/3 The report contains a description of airborne checkout sensors, their installation points, and their checkout parameters.. Included is a computer aided analysis of the checkout procedures and results obtained. GRA N73-18062# Northrop Corp.. Palos Verdes Peninsula. Calif. Electronics Div. CONCEPT FORMULATION STUDY FOR AUTOMATIC INSPECTION. DIAGNOSTIC AND PROGNOSTIC SYSTEMS (AIDAPS). VOLUME 1: SUMMARY Final Report Sep. 1972 72 p refs 206 N73-18069 (Contract DAAJ01-71-C-0503) (AD-752882: NORT-71-292A-Vol-1; USAAVSCOM-TR-72-20-VOI-1) Avail: NTIS CSCL 01/3 The report presents the results of a concept formulation study for an Automatic. Inspection. Diagnostic and Prognostic System (AIDAPS) for Army aircraft. The purpose of the study was to satisfy the prerequisites of contract definition as defined in the life cycle management model for Army systems. The study results conclusively demonstrate that these prerequisites were satisfied. Author (GRA) N73-18063# Northrop Corp.. Palos Verdes Peninsula. Calif. Electronics Div. CONCEPT FORMULATION STUDY FOR AUTOMATIC INSPECTION. DIAGNOSTIC AND PROGNOSTIC SYSTEMS(AIDAPS). VOLUME 2: AIDAPS DESIGN AND TRADE STUDIES Final Report Sep. 1972 623 p (Contract DAAJ01-71-C-0503) (AD-752883; NORT-71-292A-Vol-2; USAAVSCOM-TR-72-20-Vol-2) Avail: NTIS CSCL 01/3 The objective of this study is to determine the most cost effective approach to the Army requirement for an Automatic Inspection ' Diagnostic and Prognostic System (AIDAPS). The system must automatically diagnose mechanical malfunctions, warn of impending mechanical failures, and eliminate unneces- sary inspections or part removals. It must also permit the change of aircraft components on an on-condition basis instead of a time change basis. The ultimate goals of the program are to reduce aircraft life cycle ownership costs, increase aircraft availability and improve aircraft safety. Author (GRA) N73-18064| Northrop Corp.. Palos Verdes Peninsula, Calif. Electronics Div. CONCEPT FORMULATION STUDY FOR AUTOMATIC INSPECTION. DIAGNOSTIC AND PROGNOSTIC SYSTEMS (AIDAPS). VOLUME 3: TECHNICAL PROPOSAL RECOM- MENDED DEVELOPMENT PLAN Final Report Sep. 1972 128 p (Contract DAAJ01-71-C-0503) (AD-752884; NORT-71-292A-Vol-3; USAAVSCOM-TR-72-20-VOI-3) Avail: NTIS CSCL 01/3 The report presents a proposed plan for. the development and deployment of the Universal Modular AIDAPS prepared in accordance with the Army Data Item. DI-S-1803. The end items of the systems are defined: work breakdowns, milestone schedules and PERT networks are given for the development efforts. Schedules and PERT networks for the adaptation, data collection, operational testing and deployment for all the aircraft types which are included are suggested; an AIDAPS maintenance plan and a product assurance plan are submitted: development costs and costs for ten years beyond project go-ahead are tabulated: an Integrated Logistics Support plan is suggested: development documentation requirements and schedules for submittal are established: and the anticipated duties, tasks and capabilities of AIDAPS- related Army personnel are discussed. Author (GRA) N73-18065# Northrop Corp.. Palos Verdes Peninsula. Calif. Electronics Div. CONCEPT FORMULATION STUDY FOR AUTOMATIC INSPECTION. DIAGNOSTIC AND PROGNOSTIC SYSTEMS (AIDAPS). VOLUME 4: AIDAPS GENERAL SPECIFICATION Final Report Sep. 1972 29 p (Contract DAAJO1-71-C-0503) (AD-752885: NORT-71-292A-Vol-4; USAAVSCOM-TR-72-20-Vpl-4) Avail: NTIS CSCL 01/3 The specification establishes the technical and mission requirements for the Automatic Inspection. Diagnostic and Prognostic System (AIDAPS) as an entity, allocates requirements to functional areas, and defines the interfaces between or among the functional areas. This specification is based on parameters developed during the concept formulation phase and shall be used to establish the general nature of the AIDAPS to be further defined during the development phase. Author (GRA) N73 18066# Northrop Corp., Palos Verdes Peninsula. Calif. Electronics Div. - - CONCEPT FORMULATION STUDY FOR AUTOMATIC INSPECTION. DIAGNOSTIC AND PROGNOSTIC SYSTEMS (AIDAPS). APPENDIX C: AIDAPS COMPUTER MODELS Final Report Sep. 1972 157 p (Contract DAAJ01 -71 -C-0503) (AD-752886; NORT-71-292-App-C; USAAVSCOM-TR-72-20-App-C) Avail: NTIS CSCL 01/3 The appendix presents the computer models developed to perform the AIDAPS Concept Formulation Study Program. The three models used are the AIDAPS Procurement Cost Model. AIDAPS/Aircraft Maintenance Analysis Model, and the AIDAP System Cost Benefit Model. The AIDAPS Procurement Cost Model is utilized to compute the cost factors used to calculate the cost of implementing AIDAPS into the Army system which includes all substantial initial investment and ownership costs. The AIDAPS/Aircraft Maintenance Analysis Model is used to calculate the effectiveness achieved by AIDAPS application. The AIDAP System Cost Benefit Model computes AIDAPS life cycle costs, cost savings, and benefits derived from using AIDAPS. and develops the net savings and benefits. Author (GRA) N73-18067# Northrop Corp.. Palos Verdes Peninsula. Calif. Electronics Div. CONCEPT FORMULATION STUDY FOR AUTOMATIC INSPECTION. DIAGNOSTIC AND PROGNOSTIC SYSTEMS (AIDAPS). APPENDIX D: COMPUTER OUTPUT DATA Final Report Sep. 1972 381 p (Contract OAAJ01-71-C-0503) (AD-752887; NORT-71-292-App-D; USAAVSCOM-TR-72-20-App-D) Avail: NTIS CSCL 01/3 The computer runs used in the AIDAPS tradeoffs are included in this appendix. These runs were programmed according to the model discussed in Appendix C. AIDAPS/Aircraft Computer Models. Section 1 contains computer printouts for the Unique AIDAPS configurations for each of the aircraft. Section 2 contains the computer runs for the Group and Universal AIDAP system's. An explanation of the information contained in each of the four distinctive printouts is presented here. A sample of each of the four printouts, numbered in accordance with the following discussion, is included. Author (GRA) N73-18068# Northrop Corp.. Palos Verdes Peninsula. Calif. Electronics Div. CONCEPT FORMULATION STUDY FOR AUTOMATIC INSPECTION. DIAGNOSTIC AND PROGNOSTIC SYSTEMS (AIDAPS). APPENDIX E: UH-1 MAINTENANCE DATA TABULATIONS Final Report Sep. 1972 727 p (Contract DAAJ01 -71 -C-0503) (AD-752888: NORT-71-292-App-E: USAAVSCOM-TR-72-20-App-E) Avail: NTIS CSCL 01/3 Computer tabulations reflecting the maintenance history as reported under The Army Maintenance Management System (TAMMS). formerly (TAERS). for the aircraft being considered are presented in this report. These tabulations provide the reported maintenance requirements at Organizational. Direct Support IDS). General Support (GS) and Depot levels of maintenance. Author (GRA) N73-18069# Northrop Corp.. Palos Verdes Peninsula. Calif. Electronics Div. ' CONCEPT FORMULATION STUDY FOR AUTOMATIC INSPECTION. DIAGNOSTIC AND PROGNOSTIC SYSTEMS (AIDAPS). APPENDIX F: AIDAPS PARAMETER LISTS Final Report Sep. 1972 66 p (Contract DAAJ01-71-C-0503) (AD-752889: NORT-71-292-App-F: USAAVSCOM-TR-72-20-App-F) Avail: NTIS CSCL 01/3 A Concept Formulation Study to determine the impact of AIDAPS on the maintenance of selected Army aircraft has been performed. The Study was conducted in three phases. In Phase 207 N73-18070 A the feasibility of the AID APS. concept was confirme'd; in Phase B practical AIDAP Systems were identified and cost effective- ness mathematical models were formulated: and in Phase C the models were operated and using Army maintenance and cost data, the optimum AlDAPS .configurations and the potential life-cycle cost savings as a result of the application of AIDAPS were determined. The Study showed that the combat effectiveness of Army aircraft 'can be increased through the application of Modular Universal AIDAPS and that its use will be overwhelm- ingly life-cycle cost effective for the AH-1/UH-1. OV-1, CH-47 and CH-54 type aircraft. Combat effectiveness will be increased for the U-21, OH-6 and OH-58 type aircraft but AIDAPS will not provide sufficient return on investment to be considered cost effective. ; . ,'Author (GRA) N73-18070| Boeing Co.. Philadelphia. Pa. Vertol Div. AN INVESTIGATION OF NOISi GENERATION ON A HOVERING ROTOR. PART 2 Final Report. 1 Feb. 1971 - 31 Jul. 1972 H. Sternfeld, C. Bobo, D. Carmichael, T. Fukushima. and R. Spencer Nov. 1972 107 p refs (Contract DAHC04-69-C-0087) (AD-753397: D210-10550-1-Pt-2; AROD-8704-3-E-Pt-2) Avail: NTIS CSCU 20/1 The study is a natural extension of the program to investigate noise generation on a hovering rotor reported in a previous investigation. That program acquired data on a large (60 ft.) diameter rotor operating on a whirl tower, and evaluated that data in the light of established analytical procedures. The work described in this report compares available data in order to investigate the effects of variations in rotor design. This data which was available from other test programs included variations in number of blades of similar airfoil, airfoil, and platform. Also included is an evaluation of model testing by comparison of the results of the full size helicopter rotor with a one-eleventh scale model. Author (GRA) N73-18071# Army Aviation Systems Test Activity. Edwards. AFB. Calif. FLIGHT EVALUATION ELLIOTT LOW-AIRSPEED SYSTEM Final Report. 21 Jun. - 15 Nov. 1971 Albert L. Winn and James S. Kishi Sep. 1972 39 p < refs ' (AD-753343: USAASTA-71-30: FR-1) Avail: NTIS CSCL 01/4 Airspeed calibration tests were conducted on an experimental model of the Elliott low-airspeed system to determine its suitability for use as a helicopter'airspeed instrument. The airspeed system was mounted in various locations on the UH-1C helicopter. Emphasis was placed on the low-speed flight regimes where the sensor operated in rotor downwash. The evaluation required 13.7 productive test flight hours. The system provides reliable, accurate airspeed data from hover to 120 knots in the direction for which the sensor is mounted. ,and results indicate an omnidirectional system is feasible. The system is simple, is highly reliable, should be relatively inexpensive in production quantities, and has high potential for development into a standard aircraft instrument. : Author (GRA) N73-18072# Bolt. Beranek. and Newman. Inc.. Cambridge. Mass. STUDY OF IMPULSIVE SOUND GENERATED BY ROTOR TIPS ACCELERATING NEAR THE SONIC SPEED Final Report. 25 Jun. 1969 - 24 Jun. 1971 Richard H. Lyon 1 Nov. 1972 23 p Revised (AD-752301: AROD-8705-2-E) Avail. NTIS CSCL 20/1 The principal results obtained are summarized as follows: Compressibility effects at the rotor tip during high speed forward flight are an important noise source. An acoustical model appears to give reasonable predictions of observed sound levels and directionality. Thickness radiation generally dominates lift radiation. By modifying the tip planform, section, and chord, sound level reductions can be achieved of the order of 10 db or more. The thickness distributions as derived appear suf- ficiently smooth so that they should be aerodynamically well behaved. Author (GRA) N73-18073# Massachusetts Inst. of Tech.. Cambridge. Flight Transportation Lab. A SYSTEMS STUDY OF NOISE REQUIREMENTS AND EXPERIMENTAL INVESTIGATION OF NOISE SOURCES FOR V/STOL AIRCRAFT Final Report. 24 Jun. 1969 - 23 Jun. 1972 Robert W. Simpson. Sep. 1972 ,13 p refs (Contract DAHC04-69-C-0086) (AD-752447; AROD-8713-3-E) Avail: NTIS CSCL 01/3 The report presents a summary of the problems studied and the results and conclusions reached in an investigation of the effect of noise problems and constraints on V/STOL aircraft design and operation, with the emphasis on helicopters. Author (GRA) N73-18074# Naval Postgraduate School, Monterey. Calif. EXPLORATORY STUDY OF THE TURNING CHARACTERIS- TICS OF A COANDA-OPERATED JET FLAP M.S. Thesis James Houston Blakeney Sep. 1972. -76 p refs (AD-753618) Avail: NTIS CSCL 01/3 An exploratory investigation of the jet deflection characteristics of a jet-flapped airfoil with Coanda deflection surfaces was performed. Velocity distribution and flow angle measurements were made with the jetflap in static operation. Flow visualization tests were used to determine the turning characteristics in incompressible flow. . Author (GRA) N73-18075# Cornell Aeronautical Lab.. Inc., Buffalo, N.Y. COLLECTION AND ANALYSIS OF SINK SPEED DATA AS PART OF THE X-22A FLIGHT RESEARCH PROGRAM Final Report John L Beilman 15, Nov. 1972 38 p (Contract N00019-71-C-0044) (AD-753852; CAL-TB-3011-F-1) Avail: NTISi CSCL 01/3 Very little experimental data exists on the landing impact loads encountered during landings of V/STOL airplanes. Develop- ment of criteria .for predicting these loads has been initiated with the collection of data on the X-22A flight research program. Special instrumentation has been installed in the X-22A to measure sink rate data during landing approaches. The in- strumentation was calibrated before and during the flight tests. Data was obtained for 31 landings, and statistical analyses Were performed. Because of the small number of landings involved in this program.. a firm statistical data base cannot be obtained, but certain trends are apparent. Histograms of the pertinent parameters are presented to show these trends, and tables of data obtained for each flight are included. Author (GRA) N73-18O76| Air Force,Inst. of Tech.. Wright-Patterson AFB. Ohio. School of Engineering. INVESTIGATION OF STABILITY AND CONTROL CHARAC- TERISTICS OF AC130 LINEAR MODELS M.S. Thesis Robert G. Lorenz Mar. 1972 92 p refs . , (AD-753388: GAM/AE/72-5) Avail: NTIS CSCL 01/4 Mathematical models of the AC130A and, AC130E aircraft are proposed. The models are developed from linearized equations and are referred to trim conditions of level turning flight. The proposed AC130E model is compared to an existing model to ascertain whether any significant differences exist between the two. A qualitative comparison is conducted by investigating each model's response to control deflections. The proposed AC130A model is used to predict general trends and probable values for stability derivatives and selected mode parameters over an extensive flight envelope. . Author (GRA) N73-18O770 Hughes Tool Co.. Culver City. Calif. Aircraft Div. OH-6A PHASE 2 QUIET HELICOPTER PROGRAM Final Report. Apr. 1970 - Apr. 1971 William H. Barlow. William C. McCluskey. and Harold W. Ferris Sep. 1972 69 p refs ' •' (Contract DAAJ02-69-C-0078: ARPA Order 1321) (AD-753646; HTC-AD-71-102; USAAMRDL-TR-72-29) Avail: NTIS CSCL 01/3 The report presents the results of the Phase 2 Quiet Helicopter Program. A Hughes OH-6A Light Observation Helicopter was extensively modified to obtain a maximum of quieting. The 208 N73-18246 purpose was to apply the latest known sound-suppression techniques available to industry to an actual helicopter and then to measure the results. An acoustic goal was set which required a balanced treatment of each noise-producing source throughout the full-frequency range. Noise reductions ranged from 14 to 20 db depending on the flight conditions. The report describes the detailed configuration changes, the test and development programs, and the final sound level measurements compared to the standard OH-6A. Author (GRA) N73-18081# Advisory Group for Aerospace Research and Development, Paris (France). TECHNICAL EVALUATION REPORT ON 39TH PROPULSION AND ENERGETICS PANEL MEETING ON ENERGETICS FOR AIRCRAFT AUXILIARY POWER SYSTEMS R. H. Johnson, (AFAPL). C. E. Oberly (AFAPL). and R. E. Quigley, Jr. (AFAPL) :Nov. 1972 11 p refs Conf. ,held at Colorado Springs. 12-15 Jun. 1972 , (AGARD-AR-50) Avail: NTIS HC $3.00 An evaluation of a conference to discuss current and future developments in aircraft electrical and auxiliary power systems is. presented. Superconductivity phenomena as related to power generation are emphasized. The anticipated requirements imposed on weight, volume, and performance of auxiliary power systems which .must operate in a high temperature environment are analyzed. Author a generalization of likelihood ratio testing between paris of hypotheses, is developed and applied to a specific problem. The problem arises in connection with an amplitude comparison monopulse system in an Air Traffic Control application. In particular, it is desired to measure target' azimuth in a beacon system in the presence of interference and multipath. The multiple hypotheses relate to the presence or absence of a desired signal, with or without either of two kinds of interfering signal. The analysis leads to a new technique of data editing., or processing, to detect the presence of interference. ' Author N73-18176# Lincoln Lab.. Mass. Inst. of Tech., Lexington. ATC SURVEILLANCE/COMMUNICATION ANALYSIS AND PLANNING Quarterly Technical Summary, 1 Sep. - 30 Nov.. 1972 1 Dec. 1972 46 p refs (Contracts DOT-FA72WAI-242: F19628-70-C-0230) (FAA-RD-72-136) Avail: NTIS HC S4.50 , Analysis and planning activities reported include: (1) analyses of S/C requirements, near miss/collision data, desirable weather data processing end display systems, recorded data from an operational ATCRBS/ARTS-3 site; (2) a quasi-step-scen radar technique potentially capable of improving the clutter rejectign performance of existing ATC radars; and (31 the status of a test program to obtain and analyze data on the effects .of cyclically switching between transponder antennas. > Author N73-18082*# National Aeronautics and Space Administration. Lewis Research Center. Cleveland. Ohio. - EXPERIMENTAL TEST RESULTS OF A GENERALIZED PARAMETER FUEL CONTROL Peter G. Batterton and Harold Gold Washington Mar. 1973 29 p refs ' : (NASA-TN-D-7.198; E-7254) Avail: NTIS HC $3.00 CSCL 21D .. • i Considerable interest has been generated recently in low cost jet propulsion systems. One of the more complicated components of jet engines is the fuel control. Results of an effort to develop a simpler hydromechanical fuel control are presented. This prototype fuel control was installed on a J85-GE-13 jet engine. Results show that the fuel control provided satisfactory engine performance at sea level static conditions over its normal nonafterburning operating range, including startup. Results of both bench and engine tests are presented: the difficulties encountered are described. Author N73-18168# National Academy of Sciences-National Research Council, Washington. D.C. PROCEEDINGS OF A SYMPOSIUM ON AN APPRAISAL OF HALOGENATED FIRE EXTINGUISHING AGENTS,, , 1972' 350 p refs Conf. held at Washington, D.C., 11-12 Apr. 1972 ' ' (AD-753218) Avail: NTIS CSCL 13/12 The report'presents the papers given at the symposium and consists essentially of two groups: Toxicology and Performance. The topics covered include: Principles and procedures for toxicologic and physiologic evaluation of the Safety of Materials: Use of human volunteers; inhalation injuries in fires; Toxicology of pyrolysis products of halogenated agents: Toxicology of Halon 1211; Halon 1301'. Cardiovascular and nervous system effects of Bromotrifluoromethane: Use of Halon 1301 in surface and deep-seated fires, aircraft1 cabin, and cargo fires, gasoline fires, shipboard fires, submarine fires, and explosions and propellant fires: and the Use of Halon 1211 in hand extinguishers and fixed systems. GRA i . i • • ' . . '. ' N73-18173# Lincoln Lab.. Mass. Inst. of Tech., Lexington. A MAXIMUM-LIKELIHOOD MULTIPLE-HYPOTHESIS TESTING ALGORITHM. WITH AN APPLICATION TO MONOPULSE DATA i E. J. Kelly Feb. 1973 27 p refs (Contracts DOT-FA72WAI-261; F19628-73-C-0002; FAA Proj. 034-241-012) (TN-1973-7) Avail:''NTIS HC $3.50 A simple algorithm for multiple-hypothesis testing, based on N73-18179# Lockheed Missiles and Space Co.. Palo Alto. Calif. INDEPENDENT RADAR SYSTEMS. CHAPTER 6 D. S. Kontorov and lu. S. Golubov-Novozhilov [1972] 15 p refs Transl. into ENGLISH from the book "Vvedenie v Radiolokats- ionnuiu Sistemotekhniku" Sovetskoe Radio, Moscow, 1971 p 167-184 Avail: NTIS HC $3.00: National Translations Center, John Crerar Library, Chicago, III. 60616 The design and construction of independent radar systems to determine target motion and nonkinematic parameters are discussed. The system is comprised of a peripheral information source, a central information processor, and a communication subsystem, together with a correlation matrix to measure target parameter error. It is concluded that independent systems using circular scan radars are apparently the most feasible, and the most practical application is found in air traffic control systems. J.M.M. N73-18223*# Martin Marietta Corp., Denver, Colo. STUDY OF FEASIBILITY OF SOLID-STATE ELECTRIC SWITCH GEAR FOR AIRCRAFT AND SPACECRAFT Final Report^ E. Buchanan and D. Waddington Mar. 1973 154 p refs (Contract NAS3-15824) (NASA-CR-121140;MCR-72-327) Avail: NTIS HC$9.76 CSCL 09A The design of a solid-state circuit breaker that can be interconnected to a second breaker to form a transfer switch is presented. The breaker operates on a nominal 270-V dc circuit and controls power to loads of up to 15 A. Automatic overload trip is provided as a function of excess energy measured through the breaker and/or excess current through the breaker. After an overload trip, up to nine preprogrammable attempts to reclose may be tried with programmable delays between each attempt, j The breaker or switch is remotely controllable. Test data on, performance in the laboratory over temperatures from -45 to 100 C are provided. The feasibility'of solid-state switch gear, has been established. . Author N73-18246# Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt. Porz (West Germany). Inst. fuer Angewandte Gasdynamik. TEMPERATURE MEASUREMENTS IN WIND TUNNELS J. Baete 1972 59 p refs In GERMAN: ENGLISH summary (DLR-Mitt-72-27) Avail: NTIS HC $5.00; DFVLR PORZ: 17,30 DM A survey is given on methods used for the measurement of temperature in wind tunnels of the DFVLR Institute for Applied Gas Dynamics by means of electric contact thermometers. It is 209 N73-18247 followed by indications on possible measuring errors and by an estimation of the accuracy. References of special methods on thermometry are mentioned on reports with a detailed description of these problems. Author N73-18247# National Research Council of Canada. Ottawa (Ontario). Div. of Mechanical Engineering. SNOW ACCUMULATIONS ON AIR CUSHION VEHICLE TRACK SECTIONS T. R. Ringer and R. D. Price Oct. 1972 47 p refs (NRC-12939; DME-MD-52) Avail: NTIS HC $4.50 Snow accumulations have been observed on a number of different shaped beams that may be employed for guided air cushion train tracks. At low wind velocities the snowfall accumulation was similar on all horizontal surfaces; however at high wind velocities the beams with a plane upper horizontal Surface accumulated much lower quantities of snow. The vertical member of the inverted Tee track acts as a 100% density snow fence for snowfall with a crosswind. Author N73-18248# Weapons Research Establishment. Salisbury (Australia). THE DATA ACQUISITION SYSTEM FOR THE WRE S-1 WIND TUNNEL R. E. Kane Oct. 1972 41 p refs (WRE-TN-784IWR/D)) Avail: NTIS HC $4.25 The first phase became operational in May 1972 when the system was connected to the S-1 tunnel, a continuous flow Subsonic/supersonic tunnel operating in the Mach number range 0.3 to 1.0 and 1.4 to 2.8. The system, based on a PDP15/20 Computer, acquires analog and digital data from the tunnel and records them on compatible magnetic tape. It can be used for On-line or off-line reduction and manipulation of the data and for display of raw or processed data. The computer is also used for setting and controlling the attitude of a model and for accurately positioning a probe in the flow field. An outline of the system design, expected performance and interfacing design is given. • Author N73-18250# Advisory Group for Aerospace Research and Development, Paris (France). AERODYNAMIC TEST SIMULATION: LESSONS FROM THE PAST AND FUTURE PROSPECTS Julius Lukasiewicz, ed. (Carleton Univ.) Dec. 1972 89 p refs Presented at AIAA 10th Aerospace Sci. Meeting Panel Discussion. San Diego. Calif.. 19 Jan. 1972 (AGARD-R-603) Avail: NTIS HC $6.50 Developments in aerodynamic test facilities used by govern- ment, university, and industry are discussed. The following topics are reported: (1) assessment of past experience, (2) present status and future prospects of aerodynamic and air breathing propul- sion testing in all speed regimes, (3) ground test and flight comparisons. (4) free flight test techniques, and (5) the development of aerodynamic testing. A review of the major West European wind tunnels and a discussion of aerodynamic test facilities in the United States are included in two appendices. Author N73-18256# Little (Arthur D.), Inc.. Cambridge. Mass. EVALUATION OF AUXILIARY AGENTS AND SYSTEMS FOR AIRCRAFT GROUND FIRE SUPPRESSION, PHASE 1 Final Report. 29 Nov. 1971 - 13 Mar. 1972 S. Atallah. Ashok S. Kalelkar. and John Hagopian Wright- Patterson AFB, Ohio ASD Aug. 1972 90 p refs (Contract F33657-72-C-0422) (AD-753069; ADL-74159; ASD-TR-72-75) Avail: NTIS CSCL 13/12 The program was conducted with the ultimate objective of reducing the number and types of auxiliary extinguishing agents and systems used for aircraft ground fire suppression at military airports. This phase was devoted to the definition of auxiliary agent/system requirements and to the review of existing knowledge on the performance of various agents and systems under particular fire and environmental conditions likely to be encountered at military airports. Where knowledge was lacking. a series of environmental and small scale fire tests were conducted, the latter on three mockups simulating fires in an aircraft engine, fuel running along the incline of an aircraft wing and in a ruptured fuel tank containing reticulated foam. Author (GRA) N73-18262# Environmental Health Lab., McClellan AFB, Calif NOISE ENVIRONMENTS OF CONTROL TOWERS Final Report Robert A. Capell Jan. 1972 19 p (AF Proj. NBF-133) (AD-752535; EHL-M-72M-1) Avail: NTIS CSCL 13/2 Noise surveys were made at the control towers of two Air Force bases. Measurements of the indoor and outdoor sound pressure levels during aircraft take-offs and other operations were recorded. These data are presented so that an' evaluation of the communication environments can be made by using certain operational data from each base. An evaluation of the noise attenuation provided by'each tower is also made. Author (GRA1 N73-18263# Defense Documentation Center, Alexandria. Va. LANDING FIELDS AND RUNWAYS. VOLUME 1 Report Bibliography. Jan. 1969 - Feb. 1972 Oct. 1972 169 p refs : (AD-751400; DDC-TAS-72-59-Vol-1) Avail: NTIS CSCL 01/5 The bibliography contains unclassified references on Landing Fields and Runways. These references deal with design, configuration, construction, pavement evaluation, rapid preparation sites, paints and coatings, composite materials, maintenance and repair of landing fields and runways. Four computer generated indexes are included. Author (GRA) N73-18264*# ' Vanderbilt Univ., Nashville, Tenn. Dept of Mechanical Engineering. ANALYSIS OF THE FLOW FIELD GENERATED NEAR AN AIRCRAFT ENGINE OPERATING IN REVERSE THRUST M.S. Thesis Walter Andrew Ledwith. Jr. Aug. 1972 95 p refs (Grant N6R-43-002-034) (NASA-CR-121147) Avail: NTIS HC $6,75 CSCL 20D A computer solution is developed to the exhaust gas reingestion problem for aircraft operating in the reverse thrust mode on a crosswind-free runway. The computer program determines the location of the inlet flow pattern, whether the exhaust efflux lies within the inlet flow pattern or not. and if so. the approximate time before the reversed flow reaches the engine inlet. The program is written so that the user is free to .select discrete runway speeds or to study the entire aircraft deceleration process for both the far field and cross-ingestion problems. While developed with STOL applications in mind, the solution is equally applicable to conventional designs. The inlet and reversed jet flow fields involved in the problem are assumed to be noninteracting. The nacelle model used in determining the inlet flow field is generated using an iterative solution to the Neuman problem from potential flow theory while -the reversed jet'flow'field is adapted using an empirical correlation from, the literature. Sample results obtained using the program, are included. Author N73-18269*# Iowa State Univ. of .Science and Technology, Ames. NUMERICAL CALCULATION OF FLOW FIELDS ABOUT RECTANGULAR WINGS OF FINITE THICKNESS IN SUPERSONIC FLOW Ph.D. Thesis Jerald Milo Vogel 1973 181 p refs (Grant NGR-16-002-029) (NASA-CR-130985) Avail: NTIS HC $11.25 CSCL 20D The calculation of the outer inviscid flow about a rectangular wing moving at supersonic speeds is reported. The inviscid equations of motion governing the flow generated by the wing form a set of hyperbolic differential equations. The flow field about the rectangular wing is separated into three regions consisting of the forebody. the afterbody, and the wing wake. Solutions for the forebody are obtained using conical flow techniques while the afterbody and the wing wake regions are 210 N73-18320 treated as initial value problems. The numerical solutions are compared in the two dimensional regions with known exact solutions. Author N73-18276# Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt. Porz (West Germany). Inst. fuer Luftstrah- lantriebe. CALCULATION OF PRESSURE DISTRIBUTION OF AERO- FOILS IN CASCADES FOR TWO-DIMENSIONAL. INCOM- PRESSIBLE FLOW WITH BOUNDARY-LAYER SEPARATION IN THE REGION OF TRAILING EDGES W. Geller 1972 121 p refs In GERMAN; ENGLISH summary (DLR-FB-72-62) Avail: NTIS HC $8.25; DFVLR Porz-Wahn: 34,40 DM A singularity method for calculating the flow through cascades with boundary layer separation is given. The contours of the blades are replaced by vortex sheets. Source distributions in the region of separation are used for simulating the displacement effect of separated wake. The source distributions are determined by satisfying the condition of constant static pressure on the blade contours in the full region between separation point on the upper and lower surface. The position of separation points is found by boundary layer calculation. As shown by comparison of theoretical and experimental results, calculated pressure distributions and flow deflection angles are generally well agreeing with measured data while the corresponding drag coefficients agree satisfactorily. Author N73-18289*# National Aeronautics and Space Administration. Ames Research Center. Moffett Field. Calif. ON THE INVISCID ROLLED-UP STRUCTURE OF LIFT GENERATED VORTICES Vernon J. Rossow Jan. 1973 22 p refs (NASA-TM-X-62224) Avail: NTIS HC $3.25 CSCL 200 A simple form is presented of the relationships for the inviscid, fully developed structure of lift-generated vortices behind aircraft wings. The method is then extended to arbitrary span-load distributions by inferring guidelines for the selection of rollup centers for the vortex sheet, along with rules for calculating the fully developed structure of the resulting multiple vortices. These techniques yield realistic estimates of the rolled-up structure of vortices produced by a wider variety of span-load distributions than possible with the original form of the theory. Author N73-18293| Cambridge Univ. (England). Dept. of Engineering. THE OFF-DESIGN ANALYSIS OF FLOW IN AXIAL COM- PRESSORS H. Daneshyar and M. R. A. Shaalan London Aeron. Res. Council 1972 51 p refs Supersedes ARC-32727 (ARC-CP-1234; ARC-32727) Avail: NTIS HC $4.75: HMSO 80 p; PHI $3.55 The existence and uniqueness of the solutions obtained from the streamline curvature method of calculating flow through turbomachines are examined for several operating points of Rolls-Royce compressors. It is shown that under certain conditions the truncation errors in the numerical solution can become large and hence give rise to the violation of the uniqueness conditions. The computer program may then give wrong answers to the physical problem. The conditions for existence and uniqueness may be violated when the meridional velocities are small (e.g.. near stall) or when there are regions of choked flow. Flow for an operating point in the stall region is computed by suitable modifications to minimize the truncation errors and hence to obtain a unique solution. This is compared with the results of the previously reported actuator disk theory and experiment. The effect of variation of losses on the calculation is examined together with the effect of a correction term due to a dissipative body force, which should be included in the momentum equation when losses are introduced. Author (ESRO) N73-18297$ California Inst. of Tech., Pasadena. THE STRUCTURE OF TURBULENT LINE VORTICES P. G. Saffman 13 Oct. 1972 38 p refs (Grant AF-AFOSR-2092-71; AF Proi. 9783) (AD-753131; AFOSR-72-2283TR) Avail: NTIS CSCL 20/4 A theory is given to explain the observed dependence on Reynolds number of the decay of. turbulent line vortices. The discussion considers first the self-similar vortex, in which all quantities are assumed to depend only on the circulation at infinity, the Reynolds number, and the time from a virtual origin. It is argued that the turbulent line vortex has a triple structure: an outer vortex of given radius, an inner vortex, and a viscous core. The axial velocity in the core, produced by growth of a trailing vortex shown to be Reynolds number dependent. Author (GRA) N73-18304# Air Force Inst. of Tech.. Wright-Patterson AFB. Ohio. School of Engineering. AN APPLICATION OF THE METHOD OF LINES TO THE TRANSONIC AIRFOIL PROBLEM M.S. Thesis John Richard McCracken Dec. 1971 62 p refs (AD-753390; GAM/AE/72-7) Avail: NTIS CSCL 20/4 The development and evaluation are presented of a numerical solution to the transonic airfoil problem. The scope is restricted to symmetrical airfoils at zero incidence angle in an inviscid 'low field. The small perturbation relationship and the irrotation- ality condition are selected for the set of governing equations and the set is reduced to a system of ordinary differential equations by the method of lines. Solutions to this system are compared to experimental data on subcritical, critical, and supercritical airfoils and against the exact solutions to the subsonic and supersonic infinite wavy wall. GRA N73-18305# Tennessee Technological Univ.. Cookeville. Dept. of Engineering Science. PRELIMINARY INVESTIGATION OF HIGH-VELOCITY LIQUID IMPACT DAMAGE Ray Kinslow, Vireshwar Sahai. and John Peddieson. Jr. Dec. 1972 159 p refs (Contract DAAH01-72-C-0375) (AD-753381; TTU-ES-72-2) Avail: NTIS CSCL 11/6 The research reported has been directed toward an under- standing of the mechanics of rain erosion of materials traveling at very high velocities. An analysis of the motion of raindrops in a hypersonic shock layer is described. A high-speed jet impinge- ment analogy of the impact of liquid drops on solid surfaces is used to analytically determine the cavity profile. The effect of stress waves generated by liquid impact is discussed. It is shown that internal damage and spallation resulting from stress waves is often much greater than the material failure in the impact area itself. Experiments have demonstrated that water-drop impact can be closely simulated by the use of a high-speed water jet. Craters formed in the laboratory by the jet are compared with those of a radome surface after a led test in a rainfield. Author (GRA) N73-18319# Air Force Inst. of Tech.. Wright-Patterson AFB. Ohio. School of Engineering. FLOW FIELD ON THE LEE SIDE OF A DELTA WING M.S. Thesis Robert Gene Christophel Dec. 1971 59 p refs (AD-753389; GAM/AE/72-6) Avail: NTIS CSCL 20/4 A procedure is developed which utilizes the method of characteristics to solve a portion of the flow field on the lee side of a flat plate delta wing with supersonic leading edges at angle of attack but at zero- yaw. •The procedure requires input conditions of a free stream Mach number, an angle of attack and a sweep angle. The procedure is applied to three sets of input conditions and the resulting data are compared to published experimental and analytical data for the same set of input conditions. The comparisons indicate that the procedure may be useful in predicting the flow field in the pseudo-elliptic region and- the position of the internal shock wave on the lee side of the wing. Author (GRA) N73-18320# Air Force Inst. of Tech.. Wright-Patterson AFB, Ohio. School of Engineering. AN ANALYSIS OF THE FLOW FIELD AROUND A 2-D BODY 211 N 7 3-18439 OF ARBITRARY SHAPE M.S. Thesis Ellie B. Underwood. Jr. Dec. 1971 87 p refs (AD-7S3387: GAM/AE/72-2) Avail: NTIS CSCL 20/4 An analytical study of the two-dimensional viscous, incom- pressible steady flow over an airfoil of arbitrary shape was made. Theodorsen's method was used to analyze the potential flow around the airfoil, providing edge velocities for the boundary layer equations, which were then solved by the Karman- Pohlhausen method. The resulting boundary layer displacement thickness was then added to the original airfoil shape to obtain a better potential flow solution. Iteration was continued in this manner until the desired accuracy was obtained. A computer program was written to effect this airfoil analysis technique. GRA N73 18439# Advisory Group for Aerospace Research and Development. Paris (France). DISPLAYS FOR APPROACH AND LANDING OF V/STOL AIRCRAFT Nov. 1972 17 p (AGARD-AR-51) Avail: NTIS HC $3.00 CSCL01B An analysis of the display systems required for approach and landing of V/STOL aircraft was conducted. The various factors considered in the analysis are: (1) operational factors and ground environment. (2) guidance requirements. (3) relation between control and display sophistication. (4) information requirements. (5) human factors engineering, and (6) current display devices. Diagrams of proposed instrument panels and display devices are included. Author (Contract DAAJ02-70-C-0062: DA Proj. 1F1-62203-A-150) (AD-752918; GER-15518; USAAMRDL-TR-72-28) Avail: NTIS CSCL 11/9 The purpose of the program was to select and characterize the most efficient discontinuous fiber glass-epoxy composite for use in ballistically tolerant flight control components. The effects of various constituent parameters on the extent of damage and residual tensile load capacity were determined after tumbled caliber .30 ball M2 projectile impact at 0-degree obliquity and 1800 ft/sec. These parameters included fiber glass and resin types, interfacial properties, fiber length, and fiber content. The three most promising composites for further study were identified as 1-inch S-2 glass fibers in an epoxy novalac matrix. 1/2-inch S-2 glass fibers in an epoxy novalac matrix, and 1-inch E glass in a flexibilized epoxy matrix. Author (GRA) N73-18605# Air Force Inst. of Tech.. Wright-Patterson AFB. Ohio. School of Engineering. NUCLEAR THERMAL VULNERABILITY OF HONEYCOMB RADOME MATERIALS M.S. Thesis Michael V. Bell Dec. 1972 86 p refs (AD-753666: GNE/PH/73-1) Avail: NTIS CSCL 17/9 The thermal vulnerability levels of honeycomb sandwich radome panels were determined by using quartz iodide lamps to irradiate the panels in a wind tunnel the lamps and wind tunnel simulated a thermal pulse on a flying aircraft. The radome panels were tested with lampblack, neoprene, and polyurethane coatings. Peak flux and 94.3 cal/sq cm total fluence. Author N73-18464# Naval Air Development Center, Warminster, Pa. Air Vehicle Technology Dept. EVALUATION OF THE -S/N- FATIGUE LIFE GAGE UNDER CONSTANT AND VARIABLE AMPLITUDE LOADING Final Report Maurice S. Rosenfeld and Sidney Scheindlinger 5 Sep. 1972 141 p refs (ZFXX412) (AD-753800; NADC-72071-VD Avail: NTIS CSCL 01/3 An experimental program was conducted to evaluate the -S/N- Fatigue Life Gage and a number of gage installations was evaluated for constant and variable amplitude loading. The test results demonstrated that while there was a qualitative relation between gage resistance change and specimen life expended, a usable quantitative correlation was not attainable. Test results also proved that the fraction of specimen life to initial detectable crack was a better indicator of the time for retirement of a structure than was the fatigue life gage, although no estimate of the damage incurred can be obtained prior to crack detection. Author (GRA) N73-18491$ Air Force Systems Command. Wright-Patterson AFB, Ohio. Foreign Technology Div. GLUING ALUMINUM ALLOY PARTS (SELECTED POR- TIONS) 22 Nov. 1972 24 p Transl. into ENGLISH from the monograph "Osnovy Konstruirovaniya v Samoletostroenii" Moscow. 1971 p 171-184 (AD-753513; FTD-MT-24-1073-72) Avail: NTIS CSCL 13/8 Given are methods for designing and calculating typical elements of aircraft construction, such as beams, joint units, rivet, welded, glue and gluewelded connections. Taken into account are the basic requirements of aviation construction; namely, minimum weight and sufficient durability. Author (GRA) N73-18584# Goodyear Aerospace Corp., Akron. Ohio. DEVELOPMENT OF BALLISTIC-DAMAGE-TOLERANT FLIGHT CONTROL COMPONENTS MOLDED OF A SHORT- FIBER REINFORCED COMPOSITE MATERIAL PHASE 1 SUMMARY REPORT: COMPOSITE MATERIAL FORMA- TION, EVALUATION. AND CHARACTERIZATION Summary Report, Jun. 1970 - Dec. 1971 Donald C. Cully. Robert V. Kolarik. T. J. Boiler, and W. F. Conley Sep. 1972 276 p refs N73-18655# Nevada Univ., Reno. Lab. of Atmospheric Physics. DESIGN AND CONSTRUCTION OF A NEW CLOUD PARTICLE REPLICATOR FOR USE ON A PRESSURIZED AIRCRAFT Final Report. 18 May 1970 - 29 Feb. 1972 John Hallett. Richard W. Hanaway. and Peter B. Wagner 31 May 1972 44 p refs (Contract F19628-70-C-0279) (AO-753091: AFCRL-72-0410) Avail: NTIS CSCL 04/2 A continuous particle replicator for cloud drops and ice crystals has been constructed for use on a pressurized aircraft, the C130 of Air Force Systems Command. Hanscom Field. A design is described which has the following capabilities: produces a uniform replica over a wide range of aircraft operating conditions; gives eight speeds of film transport enabling the particle concentration on the film to be adjusted depending on the concentration in the cloud and flight speed; gives inflight viewing of the replica: and enables the film to be stopped and started in flight. Preliminary flight results show that at air speeds around 100 m/sec crystals smaller than 100 micrometers and drops smaller than 40 micrometers are replicated without serious problems, larger particles break up or shatter, although larger ice crystals, up to several mm, may still be identified. Author (GRA) N73-18661# Atmospheric Sciences Lab.. White Sands Missile Range. N.Mex. HELICOPTER DOWNWASH APPLIED TO FOG CLEARING: A STATUS SUMMARY Walter S. Nordquist, Jr. and David H. Dickson Oct. 1972 S3 p refs (DA Proj. 1TO-61102-B-53A) (AD-753357; ECOM-5465) Avail: NTIS CSCL 04/2 The report summarizes the results of a literature search and a survey of helicopter pilots concerning the use of helicopter- induced downwash to effect temporary clearings in fog. While the technique has been unsuccessfully applied in a variety of situations, the available information indicates that the criteria for determining the probability of successful application of this method is yet to be completely established. In general larger helicopters, such as the CH-54, can be successfully used for clearing fogs of 500-600 foot depth: however, smaller helicopters, such as the UN-1. do not work well for fogs of depths over 100-300 feet. Author (GRA) 212 N73-18806 N73-18664# National Aviation Facilities Experimental Center. Atlantic City, N.J. TACAN-DME FALSE DISTANCE LOCK-ON Final Report, Aug. 1971 - Jul. 1972 George Hartranft, Matthew Naimo. and Harold Postel Feb. 1973 63 p IFAA Pro). 041-306-05X) (FAA-NA-72-65; FAA-RD-72-98) Avail: NTIS HC $5.25 The results of laboratory and field tests of various Tacan ground station modifications designed to minimize the false DME problem are presented. An airborne and ground data collection package was designed to record the percentage of false replies synchronous with an aircraft interrogation. The modifications tested included a modified GRN-9 Tacan receiver, a tighter decoder tolerance modification, a jittering dead time gate, and a retriggerable long dead time gate. Although all modifications were successful in reducing the percentage of false DME. the retriggerable long dead time gate modification was the most successful in eliminating all false DME caused by multipath air-to-ground interrogations. Author N73-18704*# Massachusetts Inst. of Tech.. Cambridge. Dept. of Aeronautics and Astronautics. A SYSTEMATIC STUDY OF SUPERSONIC JET NOISE Final Report Jean F. Louis Dec. 1971 74 p refs (Grant NGL-22-009-383; Contract DOT-TSC-142) (NASA-CR-130964; DOT-TSC-142-1; PB-211954) Avail: NTIS HC $5.75 CSCL21E Acoustic fields associated with two different nozzle configura- tions, a rectangular and a circular, are studied. Both nozzles were designed with the same exit Mach number and have an identical momentum and energy flux. So far tests have been made in the range of 1000-5000 degrees R. for different levels of expansion and an exit Mach number of 2.7. In comparing the two nozzles, it is found that the rectangular nozzle is indeed quieter than the circular nozzle. Author (GRA) N73-18706#' Air Force Inst. of Tech.. Wright-Patterson AFB, Ohio. A METHOD TO COMPARE THE POTENTIAL OF A FLOWING LIQUID HYDROCARBON TO GENERATE STATIC ELEC- TRICITY M.S. Thesis Valentine L. Denninger Jun. 1972 81 p refs (AD-753386; GA/ME/72-4) Avail. NTIS CSCL 20/3 The study examines static charge generation in hydrocarbon fuels during flow through pipes. Particular emphasis is placed on the effect of linear velocity, pipe diameter and length, and the liquid solid interface. A parameter was developed which may be of use to system designers as a basis for comparing static electric charge generating characteristics of various fuel-container material combinations. Laboratory scale apparatus for the measurement of conductivity and charge density in the flowing fluid was designed, constructed and instrumented. A by product of this work was the development of a fully guarded parallel plate conductivity cell which indicates some improvement over other designs. GRA N73-18798# Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt. Brunswick (West Germany). Inst. fuer Luftsaugende Antrieb. THE RECIRCULATION FLOW PATTERN OF A VTOL LIFT ENGINE E. Schwantes 1972 165 p refs In GERMAN: ENGLISH summary (DLR-FB-72-50) Avail: NTIS 'HC $10.25: DFVLR Porz-Wahn: 29 DM A method is presented to predict theoretically the increase of temperature due to wind-recirculation in the inlet of a VTOL lift engine exhausting normally to the ground. It is shown how to calculate with the potential-theory the velocities in the recirculation flow and how to determine the temperatures with the laws of spread of buoyant plumes. Many model-investigations are done to check these results. During this, the three regions of a VTOL propulsion jet, the free jet. the wall jet. and the zone of separation of the wall jet from the ground, due to wind effects and buoyancy forces are investigated at model-jets with critical nozzle pressure ratio and temperatures up to 1000 C. Author N73-18799$ National Aerospace Lab., Tokyo (Japan). DIGITAL CONTROL OF JET ENGINES. 1: CONTROL SYSTEM AND PRELIMINARY EXPERIMENTS Kenji Nishio. Masanori Endo. Nanahisa Giyama. Takeshi Koshinuma. Toshimi Hata. Yukio Matsuda, Akira Yoshida. and Susumu Nakayama 1972 60 p refs In JAPANESE; ENGLISH summary (NAL-TR-281) Avail: NTIS HC $5.00 The application of integrated circuit technology to the electronic control of jet engines is discussed. The analog and digital types of control systems are compared on the basis of flexibility, reliability, manufacturing costs, and producibility. The software and hardware involved in a jet engine control system using a digital computer are described. Author N73-18803*# National Aeronautics and Space Administration. Lewis Research Center. Cleveland, Ohio. ANALYTICAL AND EXPERIMENTAL PERFORMANCE OF OPTIMAL CONTROLLER DESIGNS FOR A SUPERSONIC INLET John R. Zeller. Bruce H.ehtinen. Lucille C. Geyser, and Peter G. Batterton Washington Mar. 1973 87 p refs (NASA-TN-D-7188; E-7173) Avail: NTIS HC $3.00 CSCL 20D The techniques of modern optimal control theory were applied to the design of a control system for a supersonic inlet. The inlet control problem was approached as a linear stochastic optimal control problem using as the performance .index the expected frequency of unstarts. The details of the formulation of the stochastic inlet control problem are presented. The computational procedures required to obtain optimal controller designs are discussed, and the analytically predicted performance of controllers designed for several different inlet conditions is tabulated. The experimental implementation of the optimal control laws is described, and the experimental results obtained in a supersonic wind tunnel are presented. The control laws were implemented with analog and digital computers. Comparisons are made between the experimental and analytically predicted performance results. Comparisons are also made between the results obtained with continuous analog computer controllers and discrete digital computer versions. Author N73-18804# Von Karman Inst. for Fluid Dynamics, Rhode-Saint- Genese (Belgium). THE SUPERSONIC COMPRESSOR RESEARCH AT THE VON KARMAN INSTITUTE FOR FLUID DYNAMICS Frans A. E. Breugelmans Jun. 1972 46 p refs (Grant AF-AFOSR-2104-71; AF Proj. 7065) (AD-752583: ARL-72-0179) Avail: NTIS CSCL 21/5 The basic principles of the supersonic cascade and wheel are described. A series of blade profiles and supersonic wheels developed at the VKI are discussed and the progress due to the research effort is emphasized. Author (GRA) N73-18805# Von Karman Inst. for Fluid Dynamics. Rhode-Saint- Genese (Belgium). THE LOW HUB-TIP RATIO SUPERSONIC AXIAL-FLOW COMPRESSOR. VOLUME 1 Final Report. 1 Jul. 1971 - 30 Jun. 1972 Frans A. E. Breugelmans Jun. 1972 52 p refs (Grant AF-AFOSR-2104-71: AF Proj. 7065) (AD-752585: VKI-IN-40-Vol-1: ARL-72-0180) Avail: NTiS CSCL 21/5 The report describes the test results of a supersonic axial flow compressor stage with a tip Mach number of 2.0. Volume I discusses especially the inlet stall, the associated flow field and the stage performance. Methods are proposed to eliminate the stall problem. Author (GRA) N73 18806# Naval Air Propulsion Test Center. Trenton. N.J. Propulsion Technology and Project Engineering Dept. STATE-OF-THE-ART REVIEW OF TURBINE ENGINE INLET 213 N73-18809 NOISE Final Technical Report Robert B. Benham Nov. 1972 160 p refs (AD-753000; NAPTC-PE-6) Avail: NTIS CSCL 21/5 The report points out that turbine-type engine design is evolving in a direction which will make fan and compressor turbomachinery noise continually more obstrusive. The TF34 engine is representative of state-of-the-art high bypass ratio subsonic turbofan technology. It contains no inlet noise- suppression design and the inlet noise exceeds Federal Air Regulation Part 36 take-off sideline noise limits by about 6PNdb. There are descriptions and 'theoretical presentations explaining the principal mechanisms producing the three inlet noise contributors; interaction tones, combination tones, and broad- band radiation. It is shown that noise control can be affected either at the rotor-stator source or with nacelle installation attenuation. Author (GRA) N73-18809$ Air Force Systems Command. Wright-Patterson AFB. Ohio. Foreign Technology Div. GAS-DYNAMIC VERIFICATION CALCULATION OF AXIAL FLOW MULTISTAGE COMPRESSORS ON EDC A. P. Tunakov and S. G. Ibragimov 1 Nov. 1972 22 p refs Transl. into ENGLISH from Tr. Aviats. Inst. (Kazan).- no. 114. 1970 p 31-47 (AD-753519; FTD-MT-24-1501-72) Avail: NTIS CSCL 21/5 An algorithm for testing the gas dynamic design of axial-flow compressors, particularly in the final adjustment phase, is proposed. Particularly well suited for calculating the parameters of blade rings, the procedure is suitable for use in the design phase if data on the loss coefficients in empirical formulas have been established. Author (GRA) N73-18890* Kaman Aerospace Corp.. Bloomfield. Conn. A FLYING EJECTION SEAT c02 R. H. Hollrock and J. J. Barzda In NASA. Lyndon B. Johnson Space Center The 7th Aerospace Mech. Symp. Nov. 1972 p 275-286 CSCL 06G To increase aircrewmen's chances for safe rescue in combat zones, the armed forces are investigating advanced escape and rescue concepts that will provide independent flight after ejection and thus reduce the risk of capture. One of the candidate concepts is discussed: namely, a stowable autogyro that serves as the crewman's seat during normal operations and automatically converts to a flight vehicle after ejection. Discussed are (1) the mechanism subsystems that the concept embodies to meet the weight and cockpit-packaging constraints and (2) tests that demonstrated the technical feasibility of the stowage, deployment, and flight operation of the rotor lift system. Author N73-18935# Stuttgart Univ. (West Germany). Inst. fuer Statik und Dynamik der Luft- und Raumfahrtkonstruktionen. CONSTRUCTION. SCOPE AND USE OF THE TEST FACILITIES AT THE ISO Final Report [AUFBAU, UMFANG UND ANWENDUNG DER VERSUCHSANLAGEN IM ISD] John H. Argyris, Werner Aicher, Klaus Eberle. and Wolfram Haug Feb. 1972 57 p refs In GERMAN; ENGLISH summary (Contract RFF-4019) (ISD-119) Avail: NTIS HC $5.00 Computational methods for accurate determination of the behavior of engineering structures, including deformations, dynamic response, ultimate load, and service life are described. These methods take advantage of modern computers. The methods have been applied to structures in all fields of engineering. Large scale structural tests and experimental material investigations are required for further development of analytical methods. Author (ESRO) N73-18960*# National Aeronautics and Space Administration. Lewis Research Center. Cleveland. Ohio. PERFORMANCE GAINS BY USING HEATED NATURAL-GAS FUEL IN AN ANNULAR TURBOJET COMBUSTOR Nicholas R. Marchionna Washington Mar. 1973 20 p refs (NASA-TM-X-2742; E-7236) Avail: NTIS HC $3.00 CSCL 21E A full-scale annular turbojet combustor was tested with natural gas fuel heated from ambient temperature to 800 K (980 F). In all tests, heating the fuel improved combustion efficiency. Two sets of gaseous fuel nozzles were tested. Combustion instabilities occurred with one set of nozzles at two conditions: one where the efficiency approached 100 percent with the heated fuel: the other where the efficiency was very poor with the unheated fuel. The second set of nozzles exhibited no combustion instability. Altitude relight tests with the second set showed that relight was improved and was achievable at essentially the same condition as blowout when the fuel temperature was 800 K (980 F). Author N73-18975# Air Force Aero Propulsion Lab.. Wright-Patterson AFB. Ohio. ASSESSMENT OF POLLUTANT MEASUREMENT AND CONTROL GOALS FOR MILITARY AIRCRAFT ENGINES William S. Blazowski and Robert E. Henderson Nov. 1972 72 p refs (AF Proj. 3048; AF Proj. 3066) (AD-753095: AFAPL-TR-72-102) Avail: NTIS CSCL 13/2 The problem of mass emissions from aircraft gas turbine engines is briefly reviewed and the aspects of this problem which are unique to military aircraft operation are discussed. Pollutant measurement technology and the existing data base are summarized and candidate control techniques are identified. Proposed Environmental Protection Agency regulations for aircraft engine emissions are'examined in terms of their impact on and application to military engines. It is concluded that the special considerations, both performance and otherwise, which must be afforded to military aircraft prohibit direct application of the EPA regulations. The report concerns Air Force emission limitation goals established in light of these efforts. Maximum allowable idle combustion inefficiency, oxide of nitrogen emission (1bm/1000 Ibm fuel), and smoke number are specified. The rationale behind using these parameters, and the means by which the numerical goals were derived are discussed. Author (GRA) N73-18978*# Tracer. Inc.. Austin. Tex. EVALUATION OF NOISE POLLUTION LEVEL BASED UPON COMMUNITY EXPOSURE AND RESPONSE DATA Richard D. Edmiston 1 Dec. 1972 114 p refs (Contract NASw-2304; TRACOR Pioj. 076-166) (NASA-CR-130920; T-72-AU-9086-U) Avail: NTIS HC $7.75 CSCL 05K The results and procedures are reported from an evaluation of noise pollution level as a predictor of annoyance, based on aircraft noise exposure and community response data. The measures of noise exposure presented include composite noise rating, noise exposure forecast, noise and number index. A proposed measure as a universal noise exposure measure for noise pollution level (L sub NP) is discussed. F.O.S. N73-18981*# National Aeronautics and Space Administration. Lewis Research Center. Cleveland. Ohio. AIR-CUSHION TANKERS FOR ALASKAN NORTH SLOPE OIL John L. Anderson Washington Mar. 1973 30 p refs (NASA-TM-X-2683; E-7210) Avail: NTIS HC $3.00 CSCL 01C A concept is described for transporting oil from the Arctic to southern markets in 10.000-ton, chemically fueled air-cushion vehicles (ACV's) configured as tankers. Based on preliminary cost estimates the conceptual ACV tanker system as tailored to the transportation of Alaskan North Slope oil could deliver the oil for about the same price per barrel as the proposed trans-Alaska pipeline with only one third of the capital investment. The report includes the description of the conceptual system and its operation: preliminary cost estimates; an appraisal of ACV tanker development; and a comparison of system costs, versatility, vulnerability, and ecological effect with those of the trans-Alaska pipeline. Author 214 N73-19004 N73-18983# Aviation Advisory Commission. Washington. D.C. THE LONG RANGE NEEDS OF AVIATION: TECHNICAL ANNEX TO THE REPORT OF THE AVIATION ADVISORY COMMISSION. VOLUME 1 Jan. 1973 598 p refs 2 Vol. (PB-215803) Avail: NTIS .HC $12.50 The findings and recommendations of the Aviation Advisory Commission are presented. In the process of arriving at these findings and recommendations, the Commission took into consideration, among other things, an extensive body of information developed for it by its staff, consultants, contractors, and many informed and concerned persons who communicated directly with the Commission or participated in discussions and conferences sponsored by the Commission on matters of particular interest. The purpose of this technical annex is to provide, for those interested in the additional depth and detail of the foundation underlying the Commission's studies, the more significant background material developed by the various sources of information. Author N73-18984$ Aviation Advisory Commission. Washington. D.C. THE LONG RANGE NEEDS OF AVIATION: TECHNICAL ANNEX TO THE REPORT OF THE AVIATION ADVISORY COMMISSION. VOLUME 2 Jan. 1973 471 p refs 2 Vol. (PB-215804) Avail: NTIS HC $10.60 Special issues and problems involved in the long range needs of aviation are analyzed. The subjects discussed are (1) noise problems created by aircraft operation. (2) air service to small and isolated communities, (3) general aviation requirements, and (4) financial aspects of the aerospace industry. P.N.F. N73-18994# Aeronautical Research Labs.. Melbourne (Australia). THE AERODYNAMIC BEHAVIOUR OF A TWO- DIMENSIONAL AEROFOIL FITTED WITH SEMICIRCULAR AND SQUARE BLUNT .BASES AT MACH NUMBERS UP TO 1.20 N. Pollock Jun. 1972 28 p refs Original contains color illustrations (ARL/A-Note-336) Avail: NTIS HC $3.50 Transonic wind tunnel tests on a two-dimensional airfoil fitted with square and convex semi-circular blunt bases have been conducted over Mach number range of 0.5 to 1.2 at a base height Reynolds number of 4.2 x 1.000. A drag comparison showed that the semi-circular base had equal or greater drag than the square base in the range 0.5 to 0.96 and less drag in the range 0.96 to 1.20. At sonic speed the drag advantage of the semi-circular base reached 20 percent Schlieren observations of the vortex shedding from the semi-circular base showed a number of acoustic resonances and some unusual photographs illustrating this phenomena are included. Author N73-18995*# United Aircraft Corp.. Stratford. Conn. Sikorsky Aircraft Div. WIND TUNNEL SIMULATION OF FULL SCALE VORTICES James B. Rorke and Robert C. Moffitt Washington NASA Mar. 1973 115 p refs (Contract NAS1-10446) (NASA-CR-2180) Avail: NTIS HC $3.00 CSCL01A An experimental investigation has been conducted to determine the important scaling parameters for the flow in the core region of a vortex generated by a rectangular wing tip. Tht effect of an unconventional planform. the ogee tip. on the tip vortex is also determined. For rectangular planform wings, the measured vortex core diameter to chord ratios, peak tangential velocity ratios, and axial velocity ratios are shown to be functions only of wing lift coefficient and elapsed time from vortex formation, and appear to be independent of both Mach number and Reynolds number. The peak tangential velocities in the diffuse vortex generated by the ogee tip are only 25 percent of those in the vortex generated by the rectangular wing. Author N73-18996*# United Aircraft Corp.. Stratford. Conn. Sikorsky Aircraft Div. ANALYSIS OF HELICOPTER MANEUVER-LOADS AND ROTOR-LOADS FLIGHT TEST DATA Edward A. Beno Washington NASA . Mar. 1973 94 p refs (Contract NAS1-11049) (NASA-CR-2225) Avail: NTIS HC $3.00 CSCL01C A study was conducted in which available airload and blade response data for the NH-3A and CH-53A rotors were analyzed in an attempx to provide greater insight into the sources of rotor vibratory loads in both level and maneuvering flight. Primary emphasis in the study was placed on examining and understanding causes of high-frequency rotor control loads. Secondary objectives were: (1) to examine the effect of number of rotor blades on hub vibratory shear forces and (2) to assess which of the many terms appearing in the hub vibratory shear force expression were of most significance. Author N73-18999$ National Gas Turbine Establishment. Farnborough (England). ON THE SUB-CRITICAL STABILITY OF VARIABLE RAMP INTAKES AT MACH NUMBERS AROUND 2 S. A. Fisher. M. C. Neal, and A. J. Brooks London Aeron. Res. Council 1972 38 p refs Supersedes NGTE-R31 1; ARC-32910 (ARC-R/M-3711; NGTE-R311: ARC-32910) Avail: NTIS HC $4.00; HMSO £1.38; PHI $5.80 The need to minimize the pre-entry drag of supersonic intakes is discussed with particular emphasis on the shock pattern in the region of the cowl lip and aerodynamic instability resulting from shear zones generated in the supersonic compression field entering the subsonic diffuser. Observations of flow instabilities made under experimental conditions are described to show instability in variable ramp intakes at Mach numbers of about 2. The two forms of instability observed in the tests are analyzed. A design technique is suggested which offers the prospect of achieving minimum pre-entry drag with freedom from instabilities induced by shear zones. Author (ESRO) N73-19000# Loughborough Univ. of Technology (England). Dept. of Transport Technology. A REVIEW OF WIND TUNNEL TESTS ON CIRCULATION CONTROL DEVICES FOR AIRCRAFT CONTROL F. G. Maccabee. B. R. Hilton, and J. I. Marsh London Aeron. Res. Council 1972 87 p refs Supersedes ARC-33456; TT-71-R-04 (ARC-CP-1232; ARC-33456; TT-71-R-04) Avail: NTIS HC $6.50; HMSO £1.35; PHI $5.30 The results of wind tunnel tests made during 1968-1971 in an experimental study of blowing applied to sections of circular cylinders are reviewed. The study was aimed at exploring the possibility of producing aircraft controlling and braking forces at low speeds. Various aspect ratios and blowing arrangements were examined, including the use of two cylinders producing mutual interference effects. ESRO N73-19003# Aerospace Research Labs., Wright-Patterson AFB. Ohio. EFFECT OF TWO DIMENSIONAL SUCTION FLOWS INTO DOUBLE INTAKES ON THE UPPER SURFACE OF A JOUKOWSKI AIRFOIL K. S. Nagaraja Nov. 1972 25 p refs (Contract AF Proj. 7064) (AD-754208; ARL-72-0146) Avail: NTIS CSCL 20/4 Fan-in-wmg type vertical take-off and landing aircraft are under investigation in the development cycle of new classes of aircraft for military and civilian missions. In view of inadequate theoretical and experimental information available, some preliminary analyses of two-dimensional problems are explored. The effect of suction flow alone on the aerodynamic characteristics of an airfoil exhibit certain novel features such as invalidation of Kutta condition for high values of intake to free stream velocity ratio. With a view to understand the flow characteristics when two intakes are located on the upper surface of a Joukowski airfoil, the two-dimensional potential flow theory is applied. Author (GRA) N73-190O4* National Aeronautics and Space Administration. Washington, D.C. AIRCRAFT CONTROL SYSTEM Patent 215 N73-19005 Paul S. Rempfer. Alan J. Robertson. Uoyd E. Stevenson, and Joseph S. Koziol. Jr.. inventors (to NASA) Issued 16 Jan. 1973 8 p Filed 13 Jul. 1970 Supersedes N70-36052 (08 - 19. p 3471) (NASA-Case-ERC-10439; US-Patent-3.711.042; US-Patent-Appl-SN-54271; US-Patent-Class-244-77D; US-Patent-Class-244-17.13; US-Patent-Class-318-489) Avail: US Patent Office CSCL01C An aircraft control system is described which is particularly suited to rotary wing aircraft. Longitudinal acceleration and course rate commands are derived from a manual control stick to control translational velocity of the aircraft along a flight path. In the collective channel the manual controls provide vertical velocity commands. In the yaw channel the manual controls provide sideslip or heading rate commands at high or low airspeeds, respectively. The control system permits pilots to fly along prescribed flight paths in a precise manner with relatively low work load. Official Gazette of the U.S. Patent Office N73-190O5# Deutsche Gesellschaft fuer Luft- und Raumfahrt, Cologne (West Germany). REPORT ON THE THIRD MEETING OF THE DGLR SYMPOSIUM, FLIGHT TESTING TECHNOLOGY: RELIA- BILITY OF RESULTS DERIVED FROM SIMULATION IN COMPARISON WITH RESULTS OF ACTUAL FLIGHT Oct. 1972 98 p refs Meeting held at Bremen. 28 Apr. 1972 (DLR-Mitt-72-18) Avail: NTIS HC $7.00; ZLDI Munich: 20.80 DM The proceedings of a conference on flight testing tech- nology are presented. The theme of the conference was the reliability of the results derived from flight simulators as compared with the results of actual flight tests. The subjects discussed are: (1) simulation and flight test of automatic STOL landing, (2) precision of aerodynamic coefficients for flight simulation, (3) selected problems for constructing simulation models, (4) the reliability of results obtained by captive tests, and (5) the influence of the methods of flight test and simulation on the reliability of simulation results. N73-19006 Bodenseewerk Geraetetechmk G.m.b H., Ueberlingen (West Germany). COMPARISON OF SIMULATION AND FLIGHT TEST FOR AUTOMATIC STOL LANDINGS [VERGLEICH VON SIMULA- TION UND FLUGVERSUCH BEI AUTOMATISCHEN STOL - LANDUNGEN] H. Boehret In DGLR Rept. on the 3d Meeting of the DGLR-Symp.. Flight Testing Technol. Oct. 1972 p 7-28 In GERMAN The comparison of simulation and flight test results for automatic STOL landings is presented. The subjects discussed are: (1) description of flight control system, (2) control of flight path during approach, (3) control of aerodynamic flow conditions, (4) description of simulator. (5) influence of nonlmearity. and (6) application of radar for altitude measurement. Author N73-19007 Dornier-Werke G.m.b H. Friedrichshafen (West Germany). OBSERVATIONS ON THE VALIDITY OF SIMULATION STUDY RESULTS IN COMPARISON WITH RESULTS FROM REAL FLIGHT TESTS [BETRACHTUNGEN ZUR GUELTIG- KEIT VON ERGEBNISSEN AUS SIMULATIONSUNTERSU- CHUNGEN IM VERGLEICH ZU DEN ERGEBNISSEN ECHTER FLUGVERSUCHE] U. Schulz and H. Seelmann In DGLR Rept. on the 3d Meeting of the DGLR-Symp., Flight Testing Technol. Oct. 1972 p 29-52 refs In GERMAN A comparison of the validity of results obtained by flight simulation with results obtained from actual flight tests is .presented. The background for the development of the simulator is discussed. The techniques for conducting the simulation are outlined. Examples of flight simulation operations are developed. Results of the comparison indicate good correlation between simulation and flight test data. Authoi N73-19008 Vereinigte .Flugtechnische Werke-Fokker G.m.b.H., Bremen (West Germany). ON THE ACCURACY OF AERODYNAMIC PARAMETERS FOR SIMULATION [USER DIE GENAUIGKEIT DcR AERODYNAMISCHEN BEIWERTE FUER DIE SIMULATION] B. Haftmann In DGLR Rept. on the 3d Meeting of the DGLR-Symp., Flight Testing Technol. Oct. 1972 p 53-66 In GERMAN ' The procedure for developing the aerodynamic parameters for use in flight simulator research projects is described. Emphasis is placed on wind tunnel measurements to determine aerodynamic coefficients. Sources of error in wind tunnel measurements -are analyzed. Procedures for compensating for errors arising during, wind tunnel tests are explained. Results of .a typical investigation' are presented as graphs. Author N73-19009 Vereinigte Flugtechnische Werke-Fokker G.m.b.H.. Bremen (West Germany). SELECTED PROBLEMS OF SIMULATION MODEL FUNC- TION [AUSGEWAEHLTE PROBLEMS DER BILDUNG. VON SIMULATIONSMODELLENl K. H. Unterreiner In DGLR Rept. on the 3d Meeting of the OGLR-Symp., Flight Testing Technol. Oct. 1972. P 67-78 In GERMAN i .. . . Selected problems in the formation of simulation models are presented.. The construction of a flight control system for a V/STOL aircraft simulator is used as the example. Sources of errors in the construction of the system are explained. Diagrams of typical systems are provided. Graphs of response curves and a table of performance data are included. Author N73-19010 Vereinigte Flugtechnische Werke-Fokker G.m.b.H.. Bremen (West Germany). ON THE RELIABILITY OF DORN TEST RESULTS FOR FREE FLIGHT TESTS [UEBER DIE VERLAEBLICHKEIT VON ERGEBNISSEN AUS DEM DORNVERSUCH FUER FREIF- LUGVERSUCHE] H. Goerlich In DGLR Rept. on the 3d Meeting of the DGLR-Symp., Flight Testing Technol. Oct. 1972 p 79-92 In GERMAN The determination of aerodynamic characteristics of aircraft while mounted on a fixed column is discussed. The construction of the test equipment to measure pitching and rolling moments is described. The advantages of using such a method as a complement to flight tests are outlined. Specific examples of tests conducted and the results obtained during captive tests are analyzed. . Author N73-19011 Vereinigte Flugtechnische Werke-Fokker G.m.bX. Bremen (West Germany). THE EFFECT OF SIMULATION RESULT RELIABILITY ON FLIGHT TEST AND SIMULATION METHODOLOGY [ZUM EINFLUSS DE VERLAESSLICHKEIT DER SIMULATIONS- RE SULTATE AUF DIE, METHODIK VON FLUGVERSUCH UND SIMULATION] R. Kaestner In DGLR Rept. of the 3d Meeting of the DGLR-Symp., Flight Testing Technol. 'Oct. 1972 p 93-99 In GERMAN Various methods of flight simulation are described and a comparison of the results obtained by flight simulators with flight tests are discussed. The VAK 191B aircraft is used as an example of typical takeoff and landing performance for STOL aircraft. Diagrams of the aircraft attitude control during transition phases following takeoff and during land approach are provided. Techniques used by the test pilot in conducting the flight tests are described. Author N73-19012*# National Aeronautics and Space Administration. Ames Research Center. Moffett Field, Calif. A SUMMARY OF WIND TUNNEL RESEARCH ON TILT ROTORS FROM HOVER TO CRUISE FLIGHT Philippe Poisson-Quinton (ONERA) and Woodrow L. Cook Paris ONERA 1972 18 p refs (NASA-TM-X-68948; ONERA-TP-1133) Avail: NTIS HC $3.00 CSCL01C . An experimental research program has been conducted on 216 N73-19020 a series of tilt rotors designed for a range of blade twist in various wind tunnel facilities. The objective was to obtain precise results on the influence of blade twist and aeroelasticity on tilt rotor performance, from hover to high speed cruise Mach number of about 0.7. global forces on the rotor, local loads and blade torsional deflection measurements were compared with theoretical predictions inside a large Reynolds-Mach. envelope. Testing techniques developed during the program are described. Author N73-19013*# 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 Feb. 1973 11 p ref (NASA-TM-X-62235) Avail: NTIS HC $3.00 CSCL01C Information which will aid in the choice by the U.S. Government and industry of system concepts, design criteria, operating procedures for STOL aircraft and STOL ports. STOL landing guidance systems, air traffic control systems, and airborne avionics and flight control systems. Ames has developed a terminal-area STOL operating systems experiments program which is a part of the joint DOT/ NASA effort is discussed. The Ames operating systems experiments program, its objectives, the program approach, the program schedule, typical experiments, the research facilities to be used, and the program status are described. Author N73-19014*# Linguistic Systems, Inc.. Cambridge. Mass. PREDICTION OF HELICOPTER ROTOR LOADS J. Gallot Washington NASA Mar. 1973 18 p rets Transl. into ENGLISH of the preprint "Calcul des Charges sur Rotor d'Helicoptere" Aerospatiale, Div. Helicopters. Etablissement de Marignane. Marseille. 1972 p 3.1 - 3.8 (Contract NASw-2482) (NASA-TT-F-14845) Avail: NTIS HC $3.00 CSCL01C The correct design of a rotor requires a precise knowledge of the alternating loads to which blade and hub are submitted. The problem of the stress evaluation, from the early design stage, may lead to very sophisticated methods, because the blade is operating in a very complex environment. Nevertheless simplified methods may give sufficiently precise results to set up correctly the dimensions of the main elements of the rotor. The method described supposes simple aerodynamics, independent of blade elastic deformations. The degree of simplification achieved in this theoretical method seems to be justified by the correlation obtained with experimental airloads measured on a model rotor at the Modane Wind Tunnel, and stresses recorded on the same rotor, or a full-scale semi-articulated rotor. Author N73-19015# National Transportation Safety Board, Washington. - D.C. SPECIAL STUDY: ACCIDENTS INVOLVING ENGINE FAILURE/MALFUNCTION US GENERAL-AVIATION 1965- 1969 29 Nov. 1972 220 p (NTSB-AAS-72-10) Avail: NTIS HC $13.00 The record of engine failure/malfunction accidents for fixed-wing aircraft which occurred in all operations of U.S. General Aviation during, the period 1965-1969 is presented. It includes a comparison of the engine-failure accident rates for single-engine and multi-engine aircraft. Analyses are included concerning causes and related factors of engine-failure accidents by selected makes and models of aircraft and engines. Injury tables, analytic tables, and cause/factor tables are presented for all fixed-wing aircraft along with single-engine and multi-engine fixed-wing aircraft. Author N73-19016*# Astro Research Corp., Santa Barbara, Calif. GROUND AND FLIGHT TEST PROGRAM OF A STOKES- FLOW PARACHUTE: PACKAGING, DEPLOYMENT. AND SOUNDING ROCKET INTEGRATION Final Report P. G. Niederer and D. J. Mihora 27 Sep. 1972 86 p refs (Contract NAS1-10947) (NASA-CR-112251) Avail: NTIS HC $6.50 CSCL01C The current design and hardware components of the patented 14 sqm Stokes flow parachute are described. The Stokes-flow parachute is a canopy of open mesh material, which is kept deployed by braces. Because of the light weight of its mesh material, and the high drag on its mesh elements when they operate in the Stokes-flow flight regime, this parachute has ah extremely low ballistic coefficient. It provides a stable aerodynamic platform superior to conventional nonporous billowed parachutes, is exceptionally packable, and is easily contained within the canister of the Sidewinder Areas or the ROT and E rockets. Thus, it offers the potential for gathering more meteorological data, especially at high altitudes, than conventional billowed parachutes. Methods for packaging the parachute are also recommended. These methods include schemes for folding the canopy and for automatically releasing the pressurizing fluid as the packaged parachute unfolds. Author N73-19017*# Aerospace Corp.. El Segundo. Calif. STUDY OF V/STOL AIRCRAFT IMPLEMENTATION. VOLUME 1: SUMMARY W: J. Portenier and H. M. Webb Washington NASA Mar. 1973 89 p refs (Contract NAS2-6473) (NASA-CR-2227) Avail: NTIS HC $3.00 CSCL01C A high density short haul air market which by 1980 is large enough to support the introduction of an independent short haul air transportation system is discussed. This system will comple- ment the existing air transportation system and will provide relief of noise and congestion problems at conventional airports. The study has found that new aircraft, exploiting V/STOL and quiet engine technology, can be available for implementing these new services, and they can operate from existing reliever and general aviation airports. The study has also found that the major funding requirements for implementing new short haul services could be borne by private capital, and that the government funding requirement would be minimal and/or recovered through the airline ticket tax. In addition, a suitable new short haul aircraft would have a market potential for $3.5 billion in foreign sales. The long lead times needed for aircraft and engine technology development will require timely actions by federal agencies. Author N73-19018*# General Electric Co.. Cincinnati, Ohio. REMOTE LIFT FAN STUDY PROGRAM. VOLUME 1 Aug. 1972 47 p refs (Contract NAS3-14408) (NASA-CR-120970-Vol-1: R72AEG242-Vol-1) Avail: NTIS HC $4.50 CSCL01C A summary of the concepts for achieving low noise levels for future V/STOL aircraft is presented. The combined system noise for 12 lift fan units operating at 10,000 Ibs of lift (each) was not to exceed 100 PNdb at a 500 ft sideline. The candidates selected for evaluation, lift unit characteristics, weight comparison, and comparison of ga-- generator components are tabulated. F.O.S. N73-19019*# General Electric Co.. Cincinnati, Ohio. REMOTE LIFT FAN STUDY PROGRAM, VOLUME 2 Aug. 1972 104 p refs (Contract NAS3-14408) (NASA-CR-120970-Vol-2: R72AEG2A2rVol-2) Avail: NTIS HC $7.25 CSCL01C The engine cycle and configuration study with emphasis on the design requirements is reported. The preliminary concept survey, evaluation of selected candidates, and acoustic analysis are presented. It is concluded that single-stage tip turbines offer the best system potential with lift unit fan pressure ratios in the range 1.20 to 1.25. A compressor pressure ratio of 14/1 for the turbojet generator is recommended as the most advantageous design. F.O.S. N73-19020*$ General Electric Co.. Cincinnati, Ohio. REMOTE LIFT FAN STUDY PROGRAM. VOLUME 3 Aug. 1972 467 p refs (Contract NAS3-14406) (NASA-CR-120972; R72AEG242-Vol-3) Avail: NTIS HC 217 N73-19021 $25.50 CSCL01C The preliminary aerodynamic and mechanical design of the selected gas generator and li'( unit components are reported. The design features for the 1.25 and 1.2 pressure ratio lift units selected for the preliminary design are discussed along with the turbojet and turbofan gas generators. The preliminary design layout, design analysis, and gas ducting design are described. F.O.S. N73-19021*# National Aeronautics and Space Administration. Lewis Research Center, Cleveland, Ohio. STATUS OF CURRENT DEVELOPMENT ACTIVITY RELATED TO STOL PROPULSION NOISE REDUCTION R. J. Rulis 1973 28 p refs Presented at Natl. Air Transportation Meeting; Miami. Fla., 24-26 Apr. !S73: sponsored by SAE (NASA-TM-X-68195; E-7350) Avail: NTIS HC $3.50 CSCL 01C The noise goal of 95 PNdb for STOL aircraft imposes severe technology demands on propulsion systems. Effects of this goal on the design of the propulsion system are reviewed. Results from recent development programs associated with STOL noise reduction, such as high bypass fan tests, 25 PNdb acoustic suppression tests, sonic inlets, and powered lift system noise tests, are presented. Integrated propulsion system designs for the blown flap and augmentor wing powered lid systems capable of meeting the noise goal are shown and the performance, installation, and economic penalties assessed. Author N73-19022# Dornier-Werke G.m.b.H., Friedrichshafen (West Germany). VSTOL AIRCRAFT STABILITY AND CONTROL EXPERI- ENCED FROM METHODS AND RESULTS OF Do 31 FLIGHT TESTS [STABILITAET UNO STEUERBARKEIT VON VSTOL-FLUGZEUGEN NACH VERFAHREN UNO ERGEBNIS- SEN AUS DER DO 31-FLUGERPROBUNG] Horst Wuennenberg Bonn Bundeswehramt 1972 99 p refs In GERMAN; ENGLISH summary Sponsored by Bundesmin. der Verteidigung (BMVg-FBWT-72-25) Avail: NTIS HC $7.00; Bundeswehramt. Bonn: 25 DM The problems of stability and control of V/STOL aircraft are discussed. Though the V/STOL handling qualities criteria in AGARD-Rep. 577 and US-MIL-F-83300 correspond to a certain extent to the flight test results of the Do 31, the MIL-Spec. in particular is not applicable to jet lift V/STOL aircraft with attitude stabilization systems. As far as AGARD-Rep. 577 is concerned, additional information seems to be necessary in order to include the special problems of this category of V/STOL aircraft. The principles of control and stabilization used for the Do 31 have proved its validity and have even enabled the pilots to perform simulated IFR-transitions up to hovering flight. However, for an operational aircraft, improvements to simplify handling and further automation of the landing approach are essentially necessary for all-weather operations. Author (ESRO) W73-19023# Dornier-Werke G.m.b.H., Friedrichshafen (West Germany). RESULTS OF VSTOL JET TRANSPORT AIRCRAFT Do 31 GROUND EROSION TESTS AND THEIR SIGNIFICANCE FOR VSTOL TECHNIQUES [ERGEBNISSE ZUR BODENERO- SION BEIM VSTOL-STRAHLTRANSPORTFLUGZEUG DO 31 UNO IHRE BEDEUTUNG FUER DIE VSTOL-TECHNIK] Joerg Muench Bonn Bundeswehramt 1972 130 p refs In GERMAN; ENGLISH summary Sponsored by Bundesmin. der Verteidigung (BMVg-FBWT-72-26) Avail: NTIS HC $8.50; Bundeswehramt. Bonn: 25 DM The theoretical and experimental investigations on ground erosion, carried out in connection with the development of the V/STOL transport aircraft Do 31. are summarized. A mobile test rig with a one stream Orenda 14 jet engine was developed for the experiments. The resistance, which is dependent on jet intensity, was tested of wet and dry grassland at Memmingen and Oberpfaffenhofen, conventional concrete, special concrete, asphalt, synthetic coating, and ground reinforced by water-glass. The movement of particles in the wall jet was also investigated. Reduction of the lift jet intensity and special methods of STOL to avoid ground erosion are considered. Author (ESRO) W73-19024# Dornier-Werke G.m.b.H., Friedrichshafen (West Germany). HOT GAS RECIRCULATION IN THE VSTOL JET TRANSPORT AIRCRAFT Do 31 AND ITS SIGNIFICANCE FOR FUTURE VSTOL DEVELOPMENTS [HEISSG ASREZIFIKU LATION BEIM VSTOL-STRAHLTRANSPORTFLUGZEUG DO 31 UND IHRE BEDEUTUNG FUER ZUKUENFTIGE VSTOL- ENTWICKLUNGEN] Peter Dick and Peter Kuehl Bonn Bundeswehramt 1972 97 p refs In GERMAN; ENGLISH summary Sponsored by Bundesmin. der Verteidigung (BMVg-FBWT-72-29) Avail: NTIS HC $7.00; Bundeswehramt, Bonn: 25 DM Investigations on the reingestion of hot engine exhaust gases carried out during development of the Do 31 with models and original equipment and extending over a period of five years (1964-1969) are described. The following partial objectives were met step by step: (1) determination of volume and character of the recirculation problem: (2) determination of similar characteris- tics in order to transfer the various model results to the full-size equipment; (3) establishment of take-off procedures: (4) optimization of safety requirements, and (5) simplification of take-off and landing procedures. With these results, the problem may be regarded as being solved for the Do 31. Further investigations to determine recirculation problems of future VSTOL jet aircraft with advanced engines revealed that certain con- figuration-related predictions can be made. Author (ESRO) W73-1902B# Dornier-Werke G.m.b.H.. Friedrichshafen (West Germany). VSTOL TRANSITION FLIGHT TECHNIQUES AND PRO- BLEMS OF THE JET TRANSPORT AIRCRAFT Do 31 AND THEIR SIGNIFICANCE FOR VSTOL TECHNIQUES [TECH- NIK UND PROBLEMATIK DES VSTOL- UEBERGANGSFLUGES BEIM STRAHLTRANSPORTFLUG- ZEUG Do 31 UND IHRE BEDEUTUNG FUER DIE VSTOL- TECHNIK] Heribert Friedel Bonn Bundeswehramt 1972 303 p refs In GERMAN; ENGLISH summary Sponsored by Bundesmin. dar Verteidigung (BMVg-FBWT-72-30) Avail: NTIS HC $17.24; Bundeswehramt. Bonn: 25 DM The techniques of VSTOL transition flight are explained using the Do 31 as an example. The problems presented by formulation and control of the transition flight path and their influence on transition performance are discussed in detail. The results of the Do 31 flight tests mainly concern the operation of V/STOL-aircraft. They are: take off transition is relatively easy; landing transition is very difficult and therefore uneconomic. The V/STOL operation can be improved by-installation of a double control stick and an autopilot, maximum available deceleration can then be used, which is a positive safety factor in the case of an engine failure. Author (ESRO) N73-19026# Army Cold Regions Research and Engineering Lab.. Hanover, N.H. PRELIMINARY ECOLOGICAL EVALUATION OF THE EFFECTS OF AIR CUSHION VEHICLE TESTS ON THE ARCTIC TUNDRA OF NORTHERN ALASKA Warren Rickard Sep. 1972 29 p refs (ARPA Order 1615) : (AD-751741; CRREL-SR-182) Avail: NTIS CSCL 13/6 Of prime concern in the Arctic is the need for an efficient means of transportation over both frozen and unfrozen arctic terrain. As. part of the effort to develop such a means, the Advanced Research Projects Agency established a program to determine the potential for using an air cushion vehicle (ACV). Studies on the effects of ACV tests were conducted in two areas at Barrow. Alaska. One area was a drained lake bottom with a fairly homogeneous vegetation cover and soil type. The second area, much drier than the first, consisted of low-centered polygons composed of a wet tundra soil and a varying vegetation 218 N73-19040 complex. The initial effects of the ACV tests in both areas were quite similar. Author N73-19027# Army Alaska. APO Seattle, Wash. 98749. REPORT OF AN EXPERIMENT EXAMINING THE AIR CUSHION CONCEPT IN A LOGISTICAL ROLE IN THE ARCTIC , Final Report W. J. Thompson Dec. 1972 87 p (AD-753527) Avail: NTIS CSCL01/3 The Surface Effects Vehicle (SEV) concept experiment was • conducted at Fort Greely, Alaska during the period February to September 1972. The objective of the experiment was to determine if the air cushion vehicle could be employed in a military logistical role in an Arctic environment. Air cushion vehicles have the mobility required to perform in a military logistical role in an Arctic environment in both summer and winter. The SEV can be operated and maintained in the severe Arctic environment by military personnel with aircraft maintenance skills. Author (GRA) N73-19028# Bolt. Beranek. and Newman, Inc.. Canoga Park. Calif. NOISE FROM AIRCRAFT OPERATIONS, US NAVAL AIR STATION, LEMOORE, CALIFORNIA Aug. 1972 36 p refs (Contract N62474-72-C-0344) (AD-754111; BBN-2225) Avail: NTIS CSCL 20/1 The report provides descriptions of the aircraft noise environment for land areas on or in the vicinity of the Naval Air Station, Lemoore, California. The noise resulting from aircraft operations at NAS Lemoore is considered in some detail from the point of view of land use, and also with respect to potential hearing damage in maintenance areas on the station. Author (GRA) N73-19029# Aeronautical Systems Div.. Wright-Patterson AFB, Ohio. CRITERIA FOR PREDICTING SPIN SUSCEPTIBILITY OF FIGHTER-TYPE AIRCRAFT Robert Weissman Jun. 1972 102 p refs (AD-753905: ASD-TR-72-48) Avail: NTIS CSCL 01C An investigation was conducted to determine if there is a correlation between lateral-directional static stability characteris- tics and spin susceptibility. The effects of longitudinal static stability and adverse or proverse yaw were also considered. The motion of an airplane entering the high angle of attack, low speed flight regime is analyzed in six degrees of freedom. The Cn beta, dynamic, and aileron-alone divergence parameters are calculated for four aerodynamic cases. Results show that these parameters have promise as criteria for predicting spin susceptibili- ty of fighter-type aircraft in the early stages of design and development. An airplane whose Cn beta, dynamic, and • aileron-alone divergence parameters are both negative at near-stall angles of attack tends to be susceptible to spinning and an airplane with positive values for these parameters tends not to be susceptible to spinning. Author (GRA) N73-19030+ Advisory Group for Aerospace Research and Development. Paris (France). ENERGETICS FOR AIRCRAFT AUXILIARY POWER SYS- TEMS A. E. Fuhs, ed. (Naval Postgraduate School) Dec. 1972 314 p refs Mostly in ENGLISH: partly in FRENCH Proc. of 39th Meeting of the AGARD Propulsion and Energetics Panel held at Colorado Springs. 12-15 Jun. 1972 (AGARD-CP-104) Avail: NTIS HC $17.75 The proceedings of a conference on the use of superconduc- tivity technology for electrical power generation in aircraft and missiles are presented. The advantages of superconductivity for power generation are described. The subjects discussed include: (1) behavior of composite superconducting materials, (2) superconducting generators in aircraft. (3) cryogenic and inductive energy storage. (4) advanced airborne auxiliary power systems. (5) extraction of auxiliary power from air breathing propulsion systems. (6) electrical generation and distribution systems for supersonic aircraft, and (7) non radiating superconduc- ting coils for energy storage. Line drawings, diagrams, charts, tables, and graphs are included to clarify the theoretical aspects. N73-19036 Cranfield Inst. of Technology (England). PROSPECTS FOR SUPERCONDUCTING GENERATORS IN AIRCRAFT J. T. Hayden In AGARD Energetics for Aircraft Auxiliary Power Systems Feb. 1972 7 p refs : A review is given of the characteristics of present conventional alternators and aircraft electrical power systems. Preliminary considerations in the use of superconducting windings in 400 Hz alternators indicate that it is difficult to argue a case in favour of using superconducting machines for typical systems in use at present. Futher, there is probably a minimum size of 400 Hz generator for which it is practical to introduce superconducting windings below which there is no significant reduction in weight. If systems requiring powers of a few megawatts are considered, then the case for superconducting machines is much more promising providing that some cryogen (such as liquid nitrogen or liquid hydrogen) is already in the aircraft and available for cooling intermediate heat shields. Continued development in lightweight airborne helium refrigerators is also needed. Author N73-19038 Ferranti-Packard Electric. Ltd.. Toronto (Ontario). LIGHTWEIGHT SUPERCONDUCTION MAGNET FOR AIRBORNE MHD GENERATORS David L Atherton In AGARD Energetics for Aircraft Auxiliary Power Systems Feb. 1972 9 p refs Sponsored by USAF Aeropropulsion Lab. and Canadian Defence Res. Board A large lightweight saddle-coil superconducting dipole magnet for airborne MHD generators is described. The magnet has a room temperature bore of 27.7 cm, a winding bore of 33 cm, a design field of 4.5 tesla. a magnetic length of 105 cm and a mass of 450 kilograms. The dipole field is generated by pancake winding whose cross sectional outline approximates overlapping circles. Lightweight necessitates high current density, 2,100a in a 2 mm. square conductor containing 200 twisted Nb-Ti filaments in a copper matrix. The Lorenz repulsive force between opposite sides of the magnet is 3850 kilogauss per centimeter of coil length. There are also large compressive forces on the former and repulsive forces between the ends. The mechanical struc- ture therefore uses a highly stressed lightweight structure of filament wound epoxy glass composite. The dewar uses superinsulation and vapour cooled radiation shields. Vibration and shock analysis and pressure vessel design criteria determine the minimum mass dewar design. Author N73-19039 Magnetic Corp. of America. Cambridge, Mass. SUPERCONDUCTING GENERATORS Z. J. J. Stekly (Tex. Univ. Austin) and H. H. Woodson In AGARD Energetics for Aircraft Auxiliary Power Systems Feb. 1972 14 p refs Sponsored by United Aircraft Corp. and AFAPL The development of alternating current machines using superconducting windings is discussed. The design 'philosophy and details of specific experimental generators are examined. The characteristics of the field winding based on electromagnetic, electromechanical, structural, and cryogenic effects are described. The design criteria resulting fiom the interaction of these parameters are developed, the results of a study of size and weight as a function of power level and frequency are presented. Author N73-19040 Westinghouse Electric Corp.. Pittsburgh. Pa. Research Labs. SUPERCONDUCTING ELECTRICAL MACHINERY C. J. Mole. J. H. Parker, Jr.. and L. R. Lowry In AGARD Energetics for Aircraft Auxiliary Power. Systems Feb. 1972 15 p refs (Contract F33615-71-C-1591) The more important types of superconducting machines, the 219 N73-19045 features and problems inherent in such machines, and the more promising applications are reviewed. Both ac and dc superconduc-' ting machines are discussed with particular emphasis on the application of ac machines for aircraft use. Recent and current developments in the field'are reported. Author N73-19045 AiResearch Mfg. Co.. Phoenix. Ariz. ' " ADVANCED AIRBORNE AUXILIARY POWER SYSTEM D. F. Swenski. L W. Norman, and A. D. Meshew In AGARD Energetics for Aircraft Auxiliary Power Systems Feb. 1972 12 p ref An advanced auxiliary power unit (APU) was combined with an accessory drive system to form an auxiliary power system (APS). This APS was used as an exploratory development test, bed for the development of advanced technology components. The APS included a 300 equivalent shaft horsepower. APU configured to furnish bleed air from a split flow impeller and shaft power at 130 F, sea level ambient conditions. The APS was designed to provide standby power separate from the.' accessories and engine .drive train., checkout, engine* starting, and emergency power through a high-speed torque converter. The design of the APS was intended to form a test bed representing the optimum configuration as determined . from a systems analysis, with a high degree of flexibility such that the components thus developed may be applicable to many other future APS designs. ' Author ! N73-19046 Kloeckner-Humboldt-Deutz A.G.. Oberursel (West Germany). , AUXILIARY POWER UNITS FOR SECONDARY POWER SYSTEMS Erwin Schnell In AGARD Energetics for Aircraft Auxiliary Power Systems Feb. 1972 9 p The design principles for the auxiliary power units of .a secondary power system for use in aircraft are presented. The single shaft turbine is compared with the free power turbine for auxiliary power unit applications. The equipments operated by the auxiliary power unit is discussed and the components of the electrical system are analyzed. ! Author N73-19047 Messerschmitt-Boelkow G.m.b.H.. Munich (West Germany). PULSE JET ENGINE AS A SOURCE OF ENERGY: FOR AUXILIARY POWER UNITS: PULSE GAS TURBINE WITHOUT COMPRESSOR W. K. Eick In AGARD Energetics for Aircraft Auxiliary Power Systems Feb. 1972: 12 p , A short survey of the elements of an intermittent pulse jet engine, open on both sides, which has been tested up to the supersonic speed is presented. The results show that such an airbreathcng unit can also be used as a gas generator acting upon a turbine rotor for taking off mechanical power. The basic design of the engine consists of a thin-walled welded steel construction of conical and cylindrical shape, without any mechanically moved, rotating or oscillating parts. A spark plug for intermittent external ignition for starting and a fuel control device belong to the basic version of the engine. The turbine is driven by the hot gases which are intermittently expelled from the combustion chamber. The power unit can also be selectively used after diversion as a propulsion engine. The low costs of, manufacturing and maintenance for such engines' are pointed out. The influence of the most important parameters is explained. The auto-ignition, based on the principle of residual gas including shock wave rate, is an important functional feature of-the pulse jet engine. Author N73-19048 Air Force Aero Propulsion Lab., Wright-Patterson AFB, Ohio. Auxiliary Power Units. DUAL1 MODE AUXILIARY POWER UNIT FOR HIGH MACH AIRCRAFT Bury I L McFadden. Jr. and Richard E. Quigley, Jr. In AGARD Energetics for Aircraft Auxiliary Power Systems Feb. 1973 9 p refs Advanced high performance aircraft are projected to employ ramjet, turboramjet. and rocketramjet engines. Since ramjet engines do not incorporate rotating members, they cannot provide shaft horsepower for aircraft accessories and flight control systems. Therefore, some form of auxiliary power source will be required to furnish'the hydraulic, electric, pneumatic, and shaft power'for the various aircraft systems during flight, thus the auxiliary power source must become the prime and only source of shaft power during high'speed flight. Various power source configurations to accomplish this are reviewed with emphasis on the potential of a single dual' mode power source sized to provide all flight vehicle power throughout the entire operating ' regime of the aircraft including ground standby. Since they are totally independent, such a configuration will permit design optimization of both the main propulsion engines and the power system. Author: N73-19049 British Aircraft Corp., Preston (England). Military Aircraft Div. INTEGRATION OF AUXILIARY POWER SYSTEMS WITH THE MULTI-SPOOL ENGINE ' . Len. W. Milsom In AGARD Energetics for Aircraft Auxiliary Power Systems Feb. 1973 8 p As engine technology advances certain engine/airframe interface problems arise with aircraft auxiliary power systems. Using a modern strike aircraft as the principal example, this paper examines the difficulties in meeting the airframe mechanical power requirements of generating excessive wasted energy in air bleed systems and of dissipating the waste heat from engine and airframe accessories. Much closer collaboration between airframe and engine contractors at the early stage of an aircraft project, in order to develop a combined approach to the solution of these problems, is recommended. Author N73-19050 Motoren-Und Turbinen-Union Muenchen G.m.b.H. (West Germany). EXTRACTION OF AUXILIARY POWER FROM AIRBREATH ING PROPULSION SYSTEMS Klaus Bauerfeind In AGARD Energetics for Aircraft Auxiliary Power Systems Feb. 1973 13 p The characteristics of gas turbine engines for use as auxiliary power sources are discussed. The direct supply of mechanical power and pressurized air from turbines is examined. The most important criteria for the auxiliary power sources are identified as: (1) maximum possible power delivery points, (2) compressor surge margins, (3) effect on handling characteris- tics of aircraft, and (4) effect on windmilling characteristics of turbine engine. Data are presented in the form of igraphs to show interrelationships of turbine engine, parameters. Author. N73-19051 Politecnico di Milano (Italy). 1st. di Macchine. A METHOD FOR PRELIMINARY ANALYSIS OF MHD GENERATOR PERFORMANCE | C. Casci, A. Coghe, and U. Ghezzi In AGARD Energetics for Aircraft .Auxiliary Power Systems Feb. 1972 12 p refs The characteristics of magnetohydrodynamic generators for aircraft and spacecraft applications are discussed. A method for analyzing the parameters of a magnetohydrodynamic generator is developed. The analysis is obtained by fixing the total enthalpic difference between the inlet and outlet sections of the duct and by examining the various possibilities through which such a condition may be achieved. Thermodynamic and electromagnetic quantities are studied in relation to the velocity difference between the inlet and outlet sections ot the duct and by some other parameters/ such as expansion ratio and form factor of the duct. Author , t N73-19052 Air Force Aero Propulsion Lab., Wright-Patterson AFB, Ohio. DEVELOPMENTS IN AIRCRAFT ELECTRICAL POWER SYSTEMS Robert H. Johnson In AGARD Energetics for Aircraft Auxiliary 220 N73-19266 Power Systems Feb. 1972 7 p refs A summary of Air Force research and development pro- grams in aircraft electrical power systems and components is presented. The planning process used to validate research programs is discussed with emphasis on the resultant motivation to develop specific classes of technology. Specific programs discussed are:'(1) solid state power controllers. (2) gate controlled switch technology, (3) solid state electric power simulator tests, and (4) high temperature electrical generators, wire, and connectors. Author N73-19053 Vought Aeronautics. Dallas, Tex. APPLICATION OF SOLID STATE SWITCHING AND MULTIPLEXING TO AIRCRAFT ELECTRICAL SYSTEMS Clyde W. Jones (AFAPL) and Jim Courier In AGARD Energetics for Aircraft Auxiliary Power Systems Feb. 1973 9 p The application of solid state switching, multiplexing, and electrically 'programmable logic to aircraft electrical systems is discussed. The effects of the use of solid state switching technology on electrical system weight, reliability, electromagnetic interference, and quality of power delivered to loads are analyzed. A summary of problems encountered with proposed solutions, during a program in which a completely solid state electrical system for an A-7 aircraft was evaluated, is included. Areas of improvement and expanded capability are also enumerated. Author N73-19054 Royal Aircraft Establishment, Farnborough (England). Engineering Physics Dept. ELECTRICAL GENERATION AND DISTRIBUTION SYSTEMS FOR FUTURE SUPERSONIC AIRCRAFT A. Bainbridge In AGARD Energetics for Aircraft Auxiliary Power Systems Feb. 1972 7 p refs The size of the total electrical load and the temperature range over which some components will have to operate make it necessary to study new generation and distribution techniques to satisfy the demands of future aircraft flying in the supersonic or hypersonic range. This paper is restricted to supersonic aircraft and discusses recent proposals for. improved distribution systems incorporating solid state .switching and using remote control of protective devices through a multiplexed system. The scope for high temperature wiring, is briefly discussed and a few recent developments in generators and power cables are described, since the generating system is particularly vulnerable to extreme environmental conditions. . Author t N73-19056 British Aircraft Corp.. Weybridge (England). ' PNEUMATICS IN SUPERSONIC ENERGETICS1 ' John Wotton In AGARD Energetics for Aircraft Auxiliary Power Systems Feb. 1973 15 p : I ; • A pneumatics orientated integrated system concept developed for subsonic civil aircraft is examined in its relation to supersonic operation. The principle of waste heat extraction for the generation of auxiliary power supplies is found to' be even more viable due to greater cabin pressure differential during cruise, and the level of engine compressor tapping required in consequence. The economics of engine bleed are examined'in the light of virtually free electrical generation in the method employed. Pneumatic power conversion is shown to be at least competitive with hydraulic and other equivalents, and the requirements of power flying controls to be satisfactorily met. - Author N73-19254# Air Force Academy. Colo. ROCK-CABLE. A COMPUTER PROGRAM TO SIMULATE AIRCRAFT TO MISSILE CABLE DYNAMICS Terry D. Hinnerichs and Steven A. Crist Oct. 1972 43 p refs (AD-753907; USAFA-RR-72-4) Avail: NTIS The report describes the development of a FORTRAN computer program that simulates the response, i.e.. cable velocities and position vs. time of a cable being deployed from a missile as it flies out and away from the aircraft that the cable is attached to. The main objective of this program is to point out what conditions might allow the cable to wrap around the aircraft as the missile is deploying cable. The. program is quite general in that any flightpath for the aircraft or missile.can be directly employed into their respective subroutines and the state of the entire cable is then calculated as a function of time. The longitudinal shapes of the cable between the aircraft and missile have been plotted for two missile flightpaths and for various tensions imposed on the cable by the missile as -it deploys the cable. . ' . Author (GRA) N73-19255# Air Force Academy. Colo. DYNAMICS OF CABLES TOWED FROM AIRCRAFT James G. R. Hansen and Steven A. Crist Oct. 1972 94 p refs • (AD-753909: USAFA-RR-72-8) Avail: NTIS CSCL 09/5 The report describes a lumped-mass computer simulation of a trailing wire system.towed by an orbiting aircraft. The USAF U-10 aircraft flight conditions were used as applied to three flightpaths: constant altitude circular, constant altitude elliptical, and non-constant altitude circular orbit. These flightpaths were flown in no wind and 30 knot wind conditions. Wire lengths of 4000 ft and 8000 ft were used where the free end was attached to a circular sphere of 25 and 100 Ibs. The results from 12 orbiting trailing wire configurations are tabulated and/or plotted. One of the main objectives in this analysis was to determine how yo-yo of the free end of the wire in wind might be alleviated or at least minimized. Author (GRA) N73-19256# Air Force Academy. Colo. STEADY STATE SHAPE OF ORBITING TRAILING WIRE SYSTEM Terry D. Hinnerichs and Steven A. Crist Oct. 1972 37 p refs (AD-753908; USAFA-RR-72-7) Avail: NTIS CSCL 09/5 The computer program described in this report simulates the spiral curve of a wire being towed behind an orbiting aircraft after steady state conditions have developed. Taking the case of a wire and drogue device towed by an aircraft in a constant orbit at a constant altitude, the authors divided the wire into n segments. Then each segment was treated as being in static equilibrium. Starting at the drogue end where all forces are known, general equations were derived which could be applied to each cable segment proceeding up to the aircraft. These equations were then programmed in FORTRAN 4 language. The results of this program's simulation of a USAF T-29 towing a wire are shown. • Author (GRA) N73-192S9 Virginia Polytechnic Inst. and State Univ.. Blacksburg. FOLLOWING THEORY WITH APPLICATIONS Ph.D. Thesis Wilbert Edward Wilhelm 1972 203 p Avail: Univ. Microfilms Order No. 72-24462 The concept' of following was established and shown to explain a number of phenomena. A theory was provided which describes such processes as feedback controls. Markov processes, and the flow of automobiles and aircraft. Two types of stochas- tic following situations were considered. One demonstrated a mode of following in which entities influence each other through mutually repelling forces. The other exemplified the affect of acceleration noise in a mode of following associated with rectilinear motion. Mathematical analogies among queueing processes, car following models, and feedback controls were established. A derivation of the transient and steady state solutions to an alternating renewal process resulted from these analogies Dissert. Abstr. N73-19266# Federal Aviation Administration, Washington. D.C. Office of Systems Engineering Management. ENGINEERING AND DEVELOPMENT PROGRAM PLAN: AIRPORT PAVEMENT Oct. 1972 -42 p (FAA-ED-08-2) Avail: NTIS HC $4.25 A research program for upgrading airport pavement technology by a coordinated contractor/in-house/industry effort is presented. Data cover: (1) design guidance and criteria using current methodology to meet current and future pavement load requirements with available materials, at reasonable cost with adequate life span, (2) pavement material and construction 221 N73-19269 standards to insure that design criteria are realized, (3) test methods and standards for evaluating performance of new pavement and predicting the life span of existing pavements. (4) methods for improving, repairing, and rehabilitating existing pavement and surfaces to improve effectiveness and extend service life, and (5) rational pavement structural design criteria procedures based upon a mathematical model capable of simulating pavement load response. Author N73-19269*# Washington Univ.. Seattle. WIND TUNNEL INTERFERENCE FACTORS FOR HIGH-LIFT WINGS IN CLOSED WIND TUNNELS Ph.D. Thesis - Princeton Univ. Robert G. Joppa Washington NASA Feb. 1973 126 p refs (Grant NGL-48-002-010) (NASA-CR-2191) Avail: NTIS HC $3.00 CSCL 14B A problem associated with the wind tunnel testing of very slow flying aircraft is the correction of observed pitching moments to free air conditions. The most significant effects of such corrections are to be found at moderate downwash angles typical of the landing approach. The wind tunnel walls induce interference velocities at the tail different from those induced at the wing, and these induced velocities also alter the trajectory of the trailing vortex system. The relocated vortex system induces different velocities at the tail from those experienced in free air. The effect of the relocated vortex and the walls is to cause important changes in the measured pitching moments in the wind tunnel. Author N73-19288 Messerschmitt-Boelkow-Blohm G.m.b.H.. Ottobrunn (West Germany). TURBULENT PRESSURE MEASUREMENTS ON ENGINE INLET FLOWS [MESSUNG VON DRUCKTURBULENZEN IN TRIEBWERKSEINLAEUFEN] W. Habig In DGLR Report on the 3d Meeting of the DGLR-Sci. Comm. on Flow Mech. Test Tech. Oct. 1972 p 87-91 refs In GERMAN Total pressure measurements for the cross section of a supersonic diffuser inlet flow model show that: (1) time fluctuations in total pressure are usually distributed over a frequency region less than or equal to 1000 Hz with local variations in effective turbulence values: (2) time fluctuations for measured static flow pressure are about 10 times lower than total pressure when acoustic waves are absent. Static pressure fluctuations can reach up to 50% of total pressure under certain conditions: (3) time variations in flow density are proportional to measured static pressure fluctuations: and (4) acoustic wave and axial flow velocity variations in the turbulent field can be determined by correlating total pressure propagation time, static pressure, and flow density. Transl. by G.G. N73-19291 Messerschmitt-Boelkow-Blohm G.m.b.H., Ottobrunn (West Germany). CONSTRUCTION METHODS FOR AEROELASTIC MODELS IN RATIONAL FLUTTER STUDIES [BAUWEISEN AERO- ELASTISCHER MODELLE FUER EINE RATIONELLE FLAT- TERUNTERSUCHUNG] Heinz Hoenlinger In DGLR Report on the 3d Meeting of the DGLR-Sci. Comm. on Flow Mech. Test Tech. Oct. 1972 p 159-185 refs In GERMAN A combinatorial numerical-experimental flutter analysis method is reported for the development of airplanes with variable geometries. Designs of various aeroelastic flutter model geometries for wind tunnel simulations consider velocity limitations, oscillatory loads, and flexibility and stiffness matrices of beam network structures. Transl. by G.G. N73-19311# Northrop Corp., Hawthorne. Calif. Aircraft Div. THE CALCULATION OF THREE DIMENSIONAL SUPER- SONIC FLOWS AROUND SPHERICALLY-CAPPED SMOOTH BODIES AND WINGS. VOLUME 1: THEORY AND APPLICATION Final Report. 1 Dec. 1971 - 3 Jul. 1972 Chong-Wei Chu and Sidney A. Powers Sep. 1972 88 p refs (Contract F33615-72-C-1429: AF Proj. 1366) (AD-753695: NOR-72-87-Vol-1; AFFDL-TR-72-91-Vol-1) Avail: . NTIS CSCL 20/4 The report describes the theories, the numerical methods and the computer programs developed for determining the inviscid three-dimensional flow about smooth shapes at supersonic speeds. Volume 1 describes trie theoretical and numerical approaches and compares two sample cases with experiment: a blunted 15 deg cone at 20 deg angle of attack in helium at M = 14.9, and a 70 deg slab delta wing at 15 deg angle of attack in air at M = 9.6. The numerical results, are in close agreement with the experimental data. Author (GRA| N73-19318# Massachusetts Univ.. Amherst. School,;of. Engineering. • r.i-^v 3 CALCULATION Of INLET FLOWS BY MEANS OF A CLOSED VORTICITY DISTRIBUTION APPLIED TO DUCTEQtPRQ-j PELLERS "u,;. r,.. Ronald J. Weetman and Duane E. Cromack Dec. 1972 106-p refs (Contract N00014-68-A-0146: NR Proj. 200-016) (AD-754114; UM-72-11) Avail: NTIS CSCL 20/4 The investigation concerns inlet flow calculations applied to ducted propellers. The' analysis is classified as that of an inlet flow since the ducted propeller wake is assumed to be at a constant diameter. A closed distribution of ring vortices is used to describe the duct and wake. By forming a closed distribution, the velocity can be equated directly to the vorticity. With this representation, singular integral equation of the first kind is formulated for the vorticity in terms of the streamline enclosing the duct and wake. Several techniques incorporated in the numerical solution of this integral equation are presented. This analysis provides a needed solution for ducted propellers operating at low speeds and statically, as well as at high speeds. Author (GRA) N73-19423 Princeton Univ., N.J. AIR SPEED MEASUREMENT WITH THE ION BEAM OF THE POSITIVE CORONA DISCHARGE Ph.D. Thesis Willard Francis Burke 1972 269 p Avail: Univ. Microfilms Order No. 72-24669 A beam of ions is a sensitive probe with which' low air speeds may be accurately measured. The influence of transverse air flow on a beam of ions produced in the positive corona discharge is discussed. Beam deflection is proportional to air speed and depends on gas'density and impurity concentrations in air. Sensors are linear in range between .3 m/s and 60 m/s. Error is determined from the quality of the accompanying electronic circuits and meters to be approximately 2%. The problem is how to keep the ratio of deflection to speed constant in a changing environment. An air speed measurement technique is derived which is independent of environmental influences. Air speed is measured independent of gas mass density and humidity. The measurement technique is derived for geometries like those with fine wire or thin needle sources which have relatively low corona thresholds and high current densities. Dissert. Abstr. N73-19621*# Martin Marietta Corp.. Denver. Colo. AUTOMATED DESIGN AND OPTIMIZATION OF FLEXIBLE BOOSTER AUTOPILOTS VIA LINEAR PROGRAMMING. VOLUME 1 Final Report Francis D. Mauser Dec. 1972 136 p refs (Contract NAS8-28482) (NASA-CR-124124: MCR-72-282-Vol-1) Avail: NTIS HC $9.00 CSCL 17G A nonlinear programming technique was developed for the automated design and optimization of autopilots for large flexible launch vehicles. This technique, which resulted in the COEBRA program, uses the iterative application of linear programming. The method deals directly with the three main requirements of booster autopilot design: to provide (11 good response to guidance commands: (2) response to external disturbances (e.g. wind) to minimize structural bending moment loads and trajectory dispersions: and (3) stability with specified tolerances on the vehicle and flight control system parameters. The method is applicable to very high order systems (30th and greater per flight condition). Examples are provided that demonstrate the successful application of the employed algorithm to the design of autopilots for both single and multiple flight conditions. Author 222 N73-19643 N73-19622*# Martin Marietta Corp.. Denver. Colo. AUTOMATED DESIGN AND OPTIMIZATION OF FLEXIBLE BOOSTER AUTOPILOTS VIA LINEAR PROGRAMMING. VOLUME 2: USER'S MANUAL Francis D. Mauser. Glen D. Szollosi. and W. Stevens Lakin Dec. 1972 171 p refs (Contract NAS8-28482) (NASA-CR-124125: MCR-72-282-Vol-2) Avail: NTIS HC $10.75 CSCL 17G COEBRA. the Computerized Optimization of Elastic Booster A'iitopilots. is an autopilot design program. The bulk of the design criteria is presented in the form of minimum allowed gain/phase stab'ility"margins. COEBRA has two optimization phases: (1) a phase' to maximize stability margins; and (2) a phase to optimize structural bending moment load relief capability in the presence of minimum requirements on gain/phase stability margins. Author N73-19623# Deutsche Gesellschaft fuer Luft- und Raumfahrt. Cologne (West Germany). REPORT ON THE DGLR-SYMPOSIUM ON AIR TRAFFIC OPERATION H. G. Nuesser Dec. 1972 66 p In GERMAN: ENGLISH summary Symp. held at Cologne. 15 Sep. 1972 (DLR-Mitt-72-24) Avail. NTIS HC $5.50; ZLDI Munich: 14,30 DM . The proceedings of a symposium on flight operations and air traffic control are presented. The present situation and problems affecting airports, general aviation, air traffic controllers, and governmental agencies for air navigation are discussed. Actions being taken by various segments of the air transportation organization are included. N73-19624 Arbeitsgemeinschaft Deutscher Verkehrsflughaefen. Stuttgart (West Germany). THE TRAFFIC LANDING FIELDS TODAY [DIE VERKEHR- SLANDEPLAETZE HEUTE] c11 Kurt Siebenwurst In DGLR Report on the DGLR-Symp. on Air Traffic Operation Dec. 1972 o 7-14 In GERMAN The characteristics and functions of various types of aircraft landing fields are discussed. The organization for the construction, control, and operation of airfields is described. A statistical analysis of the growth of air traffic in Germany is developed to show the basic cause for many of the air traffic problems. Plans for the development of airports and the expected benefits to flight safety are included. Transl. by P.N.F. N73-19625 Arbeitsgemeinschaft Deutscher Verkehrsflughaefen. Stuttgart (West Germany). AIRPORTS TODAY: SIGNIFICANCE AND PROBLEMS OF AIRPORTS IN TODAYS AIR TRAFFIC [FLUGHAEFEN HEUTE BEDEUTUNG UND PROBLEME DER FLUGHAEFEN IM HEUTIGEN LUFTVERKEHR] c11 Udo Wolffram In DGLR Report on the DGLR-Symp. on Air Traffic Operation Dec. 1972 p 15-24 In GERMAN A summary of airports constructed in various European countries and England which comprise a commercial air traffic net is presented. The functions performed by commercial airports are described. The effects of airport operations on the environment are analyzed. The preliminary planning of airports to insure their ability to accomodate the transportation demands is discussed. Methods for improving flight operations and the application of new technologies to airport development are examined. Transl. by P.N.F. N73-19626 Deutscher Aeroclub e.V., Frankfurt am Main (West Germany). FLIGHT OPERATIONS FROM THE VIEWPOINT OF GEN- ERAL AVIATION [FLUGBETRIEB AUS DER SIGHT DER ALLGEMEINEN LUFTFAHHT) Wolfgang Tnnkaus In DGLR Report on the DGLR-Symp. on Air Traffic Operation Dec. 1972 p 25-31 In GERMAN The problems of traffic control of general aviation aircraft in Germany are discussed. A statistical analysis of general aviation flying in Germany to include the number of licensed pilots, the number and types of aircraft, and the extent of flying activity is presented. The present methods for controlling general aviation aircraft to avoid aircraft accidents are explained. The control of general aviation aircraft in the United States is reported to show possible applications to the control of German aircraft activities. Transl. by P.N.F. N73-19627 Deutsche Lufthansa Aktiengesellschaft. Frankfurt am Main (West Germany). FLIGHT OPERATIONS FROM THE VIEWPOINT OF COM- MERCIAL AIRLINES [FLUGBETRIEB AUS DER SIGHT EINER LUFTVERKEHRSGESELLSCHAFT] Rolf Bebber In DGLR Report on the DGLR-Symp. on Air Traffic Operation Dec. 7972 p 33-48 In GERMAN A statistical analysis of the growth of commercial airlines in Germany during the.past 20 years is presented. The problems in air traffic control which have resulted from this expansion are described. The functions of an operations control center to provide safer flying conditions and more efficient operation are explained. The efforts of German airlines to meet the four basic requirements of: (1) safety. (2) passenger comfort. (3) schedule adherence, and (4) economy are reported. The anticipated extent and nature of civil aviation activities in Europe in the near future are included. Transl. by P.N.F. N73-19628 Verband Deutscher Flugleiter e.V., Frankfurt am Main (West Germany). FLIGHT SAFETY PROBLEMS FROM THE VIEWPOINT OF THE AIR TRAFFIC CONTROLLER [FLUGSICHER- UNGSPROBLEME AUS DER SICHT DER FLUGLOTSEN] c02 Wolfgang Kassebohm In DGLR Report on the DGLR-Symp. on Air Traffic Operation Dec. 1972 p 49-54 In GERMAN The requirements for air traffic control procedures in German airspace which arise from the operation of commercial, military, and general aviation aircraft are described. A statistical analysis of the overall increase.in air traffic over Germany from foreign and domestic operations is presented. A reformed system for air traffic procedures is developed. The continued importance of the air traffic controller for the safe operations of the system is emphasized. Transl. by P.N.F. N73-19635 Joint Publications Research Service, Arlington. Va. CONDITION OF DRIFT INVARIANCE OF TWO-STAGE GYROSCOPE WITH ARBITRARY GAS-LUBRICATED MAIN BEARINGS TO ACTIVE ACCELERATIONS c14 S. G. Dadayev and G. A. Zavyalov In its Inertial Systems 7 Feb. 1973 p 13-17 refs The conditions are determined under which the drift of a two-stage gyroscope with arbitrary gas-lubricated main rotor bearings in the presence of arbitrary accelerations is equal to zero. Author N73-19642# Sperry Rand Corp.. St. Paul. Minn. Defense Systems Div. KNOXVILLE ASSOCIATIVE PROCESSOR EVALUATION Final Report B. G. Dietzler Nov. 1972 324 p (Contract DOT-FA70WA-2289) (PX-6406-Rev-A; FAA-RD-73-17) Avail: NTIS HC $18.25 An evaluation of the associative processor (API in performance of the tracking and conflict detection functions in a real-time terminal ATC environment is reported. Design data for the 1230 conflict resolution program and for all AP programs are included. A summary of the results is included. . F.O.S. N73-19643# Stanford Research Inst.. Menlo Park, Calif. COMPUTER-AIDED TRAFFIC/AIRWAY/VORITAC) NET- WORK METHODOLOGIES. PART 1: TECHNIQUES OF AIR ROUTE NETWORK DESIGN (TASKS 1-3) Final Report. Feb. 1971 - Aug. 1972 Waheed Siddiqee Aug. 1972 153 p refs (Contract DOT-FA71WA-2547; SRI Proj. 1096) •223 N73-19644 (FAA-RD-72-118-1-PM) Avail: NTIS HC $9.75 The development of a computer-aided air route network design methodology is discussed. The subjects presented are: (1) establishment of route intersection points and angles, (2) establishment of various network attributes. (3) merging and bending routes, and (4) computer and plot programs. Mathematical models are presented to analyze the parameters which affect the computer program. . Author N73-19644# Stanford Research Inst.. Menlo Park. Calif. COMPUTER-AIDED TRAFFIC/AIRWAY/VOR(TAC) NET^ WORK METHODOLOGIES. PART 2: TECHNIQUES OF VORTAC GRID DESIGN (TASK 4) Final Report. Feb. 1971 - Aug. 1972 Waheed Siddiqee Aug. 1972 101 p refs (Contract DOT-FA71WA-2547: SRI Proj. 1096) (FAA-RD-72-118-2-Pt-2) Avail: NTIS HCS7.25 The development of a systematic methodology and associated computer programs for the optimal design of a national grid of high altitude V O R / V O R T A C facilities is described. Various techniques, models, and computer operations are presented. The subjects include the following: (1) project scope, ground rules, and problem formulation. (2) the family of VORTAC grid attribute models. (3) design methodologies and techniques, and (4) program to implement a preliminary pattern shifting method- ology. Author N73-19645# Ohio Univ., Athens. Avionics Engineering Center. INSTRUMENT LANDING SYSTEM IMPROVEMENT PRO- GRAM GRADIENT CLEARANCE MONITOR Final Report. 1 Jul. 1971 - 1 Oct. 1972 Michael J. Stefanik Oct. 1972 90 p refs (Contract DOT-FA69WA-2066) (FAA-RD-72-147) Avail: NTlS HC $6.50 Selected monitoring techniques to obviate the need for glide slope clearance flight checks have been identified. Of those investigated, the gradient clearance monitor concept appears to be the most promising technique for practical solution to the problem of ascertaining glide slope clearance signal. Feasibility is demonstrated through Fresnel zone commonality analysis and the design, fabrication, and experimental, evaluation of the proposed monitor in operation with null-reference, glide-slope system. The results of this study are reported. Details include the development of three methods for the evaluation of gradient clearance monitor data involving both manual and computer solutions. Flight measurements to verify the monitoring of controlled, system faults have been used to investigate monitor credibility. A preliminary theoretical investigation indicates this monitoring concept is also compatible with sideband-reference and capture-effect systems. Results of this study support the concept of a far-field, environmental, glide-slope monitor. Author N73-19646# Mitre Corp.. McLean. Va. CONTROLLER PRODUCTIVITY STUDY Final Report R. A. Rucker. R.' D. Parlow. P. R. Sterfels. and D. S. Mayer Feb. 1973 128 p refs (Contract DOT-FA70WA-2488) (MTR-6110: FAA-EM-73-3) Avail: NTIS HC $8.50 An analysis of the effects of automation on the productivity of air traffic control and flight services staffs over the next 10 to 20 years. It is concluded that an aggregate five percent per year productivity gain is achievable. The improvement will depend on an aggressive development and implementation plan. Author N73-19651# Ohio Univ., Athens. Dept. of Electrical Engineering. DESIGN, CONSTRUCTION AND DEMONSTRATION OF AN AIRBORNE, LOW FREQUENCY. PHASE-STABLE RECEIVER Frederick J. Kiko Oct. 1972 90 p refs (Contract DAAB07-68-C-0084) (AD-754027: EER-16-8: ECOM-0084-S-1) Avail: NTIS CSCL 17/7 . ' Aircraft navigation using direct-ranging radio methods relies upon the processing of the carrier phase delay information accrued between a transmitter and a user. The first requirement following reception of the carrier wave is to raise its amplitude to a useable value. An 'RF filtering and-amplification scheme using analog methods is invariably used whether detection and further processing is achieved by analog or digital methods. The primary design requirement for a navigation receiver for direct-ranging applications is throughput phase stability. In the elected design a fixed-tuned TRF cascade of LC filters and integrated circuit gain blocks exhibits a stability of one electrical degree in the LF band at 300 kHz with a one sigma standard deviation. Measured performance includes a 3 db overall bandwidth of 1.9 kHz, a noise figure of 6 db and a maximum voltage gain of 70 db. Author (GRA) I N73-19666# National Aeronautical Establishment. Ottawa (Ontario). A SIMPLE MODEL OF SHOCK CELL NOISE GENERATION AND ITS REDUCTION Y. Y. Chan Oct. 1972 46 p refs (NRC-12923: LR-564) Avail: NTIS HC $4.50 Based on the data of near field surveys of the sound pressure from a choked jet. a simple model is proposed for the mechanism of the screech generation. A convected wave propagates downstream along the jet boundary and is modulated by its interactions with the shock-expansion waves of the jet. These interactions generate strong dipole radiations. Using this model, an excellent reproduction of the essential features of the experimental results is obtained. By preventing the formation of shock waves inside the jet. the strong dipole radiation and hence the screech noise can be eliminated. Design data for perforated nozzles to achieve full expansion of the'jet are provided. This avoids the mechanical complication of an adjustable convergent- divergent nozzle. Author N73-19697*# Virginia Univ.. Chartottesville. Research Labs, for the Engineering Sciences. DRAG COEFFICIENTS FOR SPHERES IN FREE MOLECU- LAR FLOW IN O AT SATELLITE VELOCITIES John W. Boring and Robert R. Humphris Washington NASA Mar. 1973 39 p refs (Contract NAS1-2538) (NASA-CR-2233) Avail: NTIS HC $3.00 CSCL 20H The drag coefficients for the Echo 1 and Explorer 24 spherical surfaces in an 0 environment were experimentally determined over an energy range of 4 to 200 eV. The experiment was performed by generating a beam of atomic oxygen ions of the proper energy, neutralizing a portion of the beam, and then allowing only the neutral 0 particles to 'strike a very sensitive torsion balance. The momentum transferred to the surface was determined from the deflection of the torsion balance. At the lower energies, the more intense ion beam had to be used instead of the neutral beam. The drag coefficients are found to be slightly greater than 2 at energies corresponding to satellite velocities. Author N73-19793* National Aeronautics and Space Administration. Lewis Research Center, Cleveland, Ohio. GAS TURBINE ENGINE FUEL CONTROL Patent Harold Gold, inventor (to NASA) Issued 30 Jan. 1973 12 p Filed:28 May 1971 Supersedes N72-10824 (10 - 01, p 0121) (NASA-Case-LEW-11187-1; US-Patent-3.713.290; US-Patent-Appl-SN-147922: US-Patent-Class-60-39.28R) Avail US Patent Office CSCL 21E ' A variable orifice system is described that is responsive to compressor inlet pressure and temperature, compressor discharge pressure and rotational speed of a gas-turbine engine. It ia incorporated into a hydraulic circuit that includes a zero gradient pump driven at a speed proportional to the speed of the engine. The resulting system provides control of fuel rate for starting, steady running, acceleration and deceleration under varying altitudes and flight speeds. Official Gazette of the U.S. Patent Office N73-19794$ Advisory Group for Aerospace Research and Development, Paris (France). BOUNDARY LAYER EFFECTS IN TURBOMACHINES J. Surugue. ed. (ONERA. Chatillon-sous-Bagneux. France) Dec. 1972 473 p refs In ENGLISH; partly in FRENCH (AGARD-AG-164; AGARDograph-164) Avail: NTIS HC $25.75 224 N73-19812 Studies dealing with the role of boundary layers in tur- bomachine design and operation are reported. The areas of investigation include subsonic, supersonic, and transonic flow machines. ' N73-19798 Deutsche Forschungs-.und Versuchsanstalt fuer Luft- und Raumfahrt, Brunswick (West Germany). Inst. fuer Aero- dynamik. INFLUENCE OF THE DEGREE OF TURBULENCE ON THE AERODYNAMIC COEFFICIENTS OF CASCADES c12 R. Kiock In AGARD Boundary Layer Effects in Turbomachines Dec. 1972 p 73-88 refs , An inviscid degree of turbulence is calculated from the circumferential distribution of .the potential flow velocity behind a rotating cascade. This is compared with measurements of the degree, of turbulence at a stator inlet of a multi-stage axial compressor. Extensive measurements on the influence of the turbulence level on the aerodynamic coefficients of several two-dimensional compressor cascades were carried out. These contained wake traverses, boundary layer measurements and pressure distribution on the profiles. These investigations were carried out in incompressible flow in the. range of Reynolds numbers between 90,000and 270.000 both in alow speed and a high speed cascade wind tunnel. ' Author N73-19803 Office National d'Etudes et de Recherches Aerospa- tiales. Paris (France). INFLUENCE OF ANGLE OF ATTACK AND DEFLECTION ON BOUNDARY LAYER FLOW IN UPRIGHT CASCADE BLADES [INFLUENCE DE L'ANGLE D'ATTAQUE ET DE LA DEFLEXION SUR LE DECOLLEMENT DE LA COUCHE LIMITE DANS UNE GRILLE D'AUBES DE REDRESSEUR] c12 Jacques Paulon In A G A R D Boundary Layer Effects 'in Turbomachines Dec. 1972 p 187-201 refs In FRENCH Cascade blade performance, as affected by boundary layer flow incidence and strong deflection, is examined. Trailing edge flow, backflow. and static pressure degradation are analyzed in detail. Transl. by E.H.W. N73-19804 Technische Universitaet, Brunswick (West Germany). Inst. fuer Stroemungsmechanik. THE EFFECT OF AXIAL VELOCITY RATIO ON THE AERODYNAMIC COEFFICIENTS OF A COMPRESSOR CASCADE IN VISCOUS FLOW c12 U. Stark In AGARD Boundary Layer Effects in Turbomachines Dec. 1972 p 205-220 refs Both theoretical and experimental investigations of the effect of axial velocity ratio on the aerodynamic coefficients of two compressor cascades with NACA 65-( 10)06 profiles are described. For the potential flow calculations the Pollard-Horlock method was selected. Boundary-layer calculations were performed based on the potential .flow velocity distributions. The aerodynamic coefficients were calculated from the boundary-layer parameters at the blade trailing edge. The experimental investigations were carried out, in a low-speed cascade tunnel. Both the theoretical and experimental results show a considerable effect of .the axial velocity ratio on the aerodynamic performance of compressor cascades. The agreement between theory and experiment is quite satisfactory in as far as no severe flow separation occurs. Author N73-19805 Motoren- und Turbmen-Union Muenchen G.m.b.H. (West Germany). THE INFLUENCE OF AXIAL VELOCITY DENSITY RATIO ON COMPRESSOR .CASCADE PERFORMANCE IN COM- PRESSIBLE FLOW . c12 W. Heilmann , In AGARD Boundary Layer, Effects in Tur- bomachines Dec. 1972 p 221-240. refs Results of theoretical and experimental investigations on the influence of the ratio between the axial velocity density upstream and that downstream on the performance of plane compressor cascades in compressible flow are presented. Tests were performed in a 7-inch transonic wind tunnel where upstream turbulence levels were varied. It could be demonstrated that the change in cascade performance with the axial velocity density ratio substantially depends upon'the blade boundary layer behaviour. At fully turbulent boundary layers the axial velocity density ratio influences only the separation point positions. At laminar-turbulent boundary layers in addition the transition point position from which the separation point positions depend will be influenced. Boundary layer calculations conducted in the theoretical part of the investigation have qualitatively confirmed the experimentally achieved results as far as the influence of the axial velocity density ratio on the transition and separation point position is concerned. Total pressure loss at various axial velocity density ratios was calculated by applying an approximative method of determining the characteristic boundary layer values in sepa- rated flow and then comparing with the test results. Author N73-19809 Institute TNO for Mechanical Constructions, Delft (Netherlands). MEASURED AND CALCULATED TURBULENT BOUNDARY LAYER FLOW IN A VANELESS RADIAL DIFFUSER c12 C. B. V. D. Voorde and J. Bos In AGARD Boundary Layer Effects in .Turbomachines Dec. 1972 p 293-310 refs A method is presented for predicting two-dimensional flow through a radial diffuser with flat parallel walls. The method is based on the integral entrainment method and is valid until the flow is fully developed. Equations are given for: prediction of the velocity distribution across the diffuser width at any arbitrary station, prediction of the radial distribution of the static pressure recovery, and calculation of the diffuser efficiency from the predicted and measured flow. An experiment conducted for validation of the prediction method is described. During the experiment very accurate measurements were made of the velocity distribution across the constant .diffuser width at various stations along a diffuser radius. The experimental values concurred well with predicted values. D.L.G. N73-19811 Von Karman Inst. for Fluid Dynamics, Rhode-Saint- Genese (Belgium). SECONDARY FLOW RESEARCH AT THE VON KARMAN INSTITUTE c12 J. W. Salvage In AGARD Boundary Layer Effects in Tur- bomachines Dec. 1972; p 333-361 refs '• Experimental work in cascade secondary flows accomplished in the past ten years is reviewed with the objective of pointing out difficulties common to the field. Investigations included tip clearance effects, low aspect ratio effects, and the beginnings of basic research on the influence of blade loading and inlet boundary layer characteristics on common compressor blade profiles. The objective of current investigations is to select critical configurations for in-depth study of the end-wall boundary layer development through the cascade with a view toward refining the experiment for use in the truly three-dimensional environment of a stator row. An initial experiment on end-wall flows is outlined and typical data shown. An improved technique is discussed, including test apparatus and probes to be used. Other topics discussed include an interesting method of reducing secondary flow josses (partial blade slotting) and the critical analysis of a simple, but geometrically limited, theory predicting secondary flow losses at high blade loading conditions. Author N73-19812 Princeton Univ.. N.J. THE PREDICTION OF AXIAL COMPRESSOR PERFORM- ANCE WITH EMPHASIS ON THE EFFECT OF ANNULUS WALL BOUNDARY LAYERS G. L Mellor and T. F. Balsa In AGARD Boundary Layer Effects in Turbomachines Dec. 1972 p 363-374 refs Current results are summarized in the development of a computer program to simulate axial compressor performance. .The program incorporates a new theory of annulus wall boundary layers which predicts annulus boundary-layer development and losses. Aside from the work involved with the construction of 225 N73-19813 the program, considerable effort is being expended to diagnose existing multistage data in terms of the rather simple parameters associated with the annulus boundary-layer theory. Author N73-19813 Cambridge Univ. (England). PREDICTION OF ANNULUS WALL BOUNDARY LAYERS IN AXIAL FLOW TURBOMACHINES c12 M. Daneshyar, J. H. Horlock. and H. Marsh In AGARO Boundary Layer Effects in Turbomachines Dec. 1972 p 375-392 refs Various existing integral boundary layer methods have been examined and their predictions are compared with a wide range of experimental data. The sensitivity of the boundary layer calculations to the mainstream data input has been examined. Author N73-19816 Von Karman Inst. for Fluid Dynamics. Rhode-Saint- Genese (Belgium). SHOCK WAVE BOUNDARY LAYER INTERACTION IN CASCADES c12 H. Griepentrog In A G A R D Boundary Layer Effects in Turbomachines Dec. 1972 p 441-456 refs Experimental data obtained with compressor cascades were analyzed to determine the main parameters that affect the shock boundary layer interaction region. These parameters were found to include: (1) the displacement thickness of the boundary layer upstream of the shock. (2) the shock intensity, and (3) the pressure gradient downstream of the shock. Taking these parameters into account, a simple model of the interaction was designed. The model only considers the external effects, such as pressure distribution on the blade surface. The model presented is considered only a tentative one and further research is indicated to understand the interaction of a quasi-normal shock with a turbulent boundary layer in compressor cascades. D.L.G. N73-19819*# National Aeronautics and Space Administration. Langley Research Center. Langley Station. Va. CASCADE PLUG NOZZLE Patent Application Blake W. Corson. Jr.. inventor (to NASA) Filed 13 Feb. 1973 21 p(NASA-Case-LAR-10951-1: US-Patent-Appl-SN-331759) Avail: NTIS HC $3.25 CSCL21E An exhaust nozzle for a jet aircraft providing jet noise suppression is described. The nozzle includes a number of coaxial airfoil ring segments which are spaced serially along the longitudinal axis of the nozzle to define annular coaxial channels. The diameters of the segments progressively decrease downstream along this axis. The radial depths of the channels are small compared with the axial distance between adjacent noncoplanar channel exits, so noise is emitted nonsimultaneously from the channel exits as a series of weakened pulses staggered in time. The boattail angles of the outer surfaces of the ring airfoil segments increase' in magnitude with increasing distance downstream to reduce drag. Author N73-19820*# American Airlines. Inc.. New York. AN AIRLINE STUDY OF ADVANCED TECHNOLOGY REQUIREMENTS FOR ADVANCED HIGH SPEED COM- MERCIAL TRANSPORT ENGINES. 1: ENGINE DESIGN STUDY ASSESSMENT G. Phillip Sallee Mar. 1973 110 p 3 Vol. (Contract NAS3-15572) (NASA-CR-121132) Avail: NTIS HC $7.50 CSCL 21E The advanced technology requirements for an advanced high speed commercial transport engine are presented.The results of the phase 1 study effort cover the following areas: (1) statement of an airline's major objectives for future transport engines. (2) airline's method of evaluating engine proposals. (3) description of an optimum engine for a long range subsonic commercial transport including installation and critical design features. (4) discussion of engine performance problems and experience with performance degradation. (5) trends in engine and pod prices with increasing technology and objectives for the future. (6) discussion of the research objectives for composites, reversers. advanced components, engine control systems, and devices to reduce the impact of engine stall, and (7) discussion of the airline objectives for noise and pollution reduction. Author N73-19821*# American Airlines. Inc.. New York. AN AIRLINE STUDY OF ADVANCED TECHNOLOGY REQUIREMENTS FOR ADVANCED HIGH SPEED COM- MERCIAL TRANSPORT ENGINES. 2: ENGINE PRE- LIMINARY DESIGN ASSESSMENT G. Phillip Sallee Mar. 1973 78 p 3 Vol. (Contract NAS3-15572) (NASA-CR-121133) Avail: NTIS HC $6.00 CSCL21E The advanced technology requirements for an advanced high speed commercial transport engine are presented. The results of the phase 2 study effort cover the following areas: (1) general review of preliminary engine designs suggested for a future aircraft. (2) presentation of a long range view of airline propulsion system objectives and the research programs in noise, pollution, and design which must be undertaken to achieve the goals presented, (3) review of the impact of propulsion system unreliability and unscheduled maintenance on cost of operation, (4) discussion of the reliability and maintainability requirements and guarantees for future engines. Author N73-19822*# American Airlines. Inc., New York. AN AIRLINE STUDY OF ADVANCED TECHNOLOGY REQUIREMENTS FOR ADVANCED HIGH SPEED COM- MERCIAL TRANSPORT ENGINES. 3: PROPULSION SYS- TEM REQUIREMENTS G. Phillip Sallee Mar. 1973 85 p 3 Vol. (Contract NAS3-15572) (NASA-CR-121134) Avail: NTIS HC $6.25 CSCL21E The advanced technology requirements for an advanced high speed commercial transport engine are presented. The results of the phase 3 effort cover the requirements and objectives for future aircraft propulsion systems. These requirements reflect the results of the Task 1 and 2 efforts and serve as a baseline for future evaluations, specification development efforts, contract/ purchase agreements, and operational plans for future subsonic commercial engines. This report is divided into five major sections: (1) management objectives for commercial propulsion systems, (2) performance requirements for commercial transport propulsion systems. (3) design criteria for future transport engines, (4) design requirements for powerplant packages, and (5) testing. Author N73-19824*# National Aeronautics and Space Administration. Lewis Research Center. Cleveland. Ohio. DESIGN AND EVALUATION OF COMBUSTORS FOR REDUCING AIRCRAFT ENGINE POLLUTION Robert E. Jones and Jack Grobman 1973 19 p refs Presented at 41st Meeting of AGARD/ Propulsion and Energetics Panel. London. 9-13 Apr. 1973 (NASA-TM-X-68192; E-7334) Avail: NTIS HC $3.00 CSCL 21E Efforts in reducing exhaust emissions from turbine engines are reported. Various techniques employed and the results of testing are briefly described and referenced for detail. The experimental approaches taken to reduce oxides of nitrogen emissions include the use of: (1) multizone combustors incorporat- ing reduced dwell times, (2) fuel-air premixing. (3) air atomization. (4) fuel prevaporization, and (5) gaseous fuel. Since emissions of unburned hydrocarbons and carbon monoxide 'are caused by poor combustion efficiency at engine idle, the studies of fuel staging in multizone combustors and air assist fuel nozzles have indicated that large reductions in these emissions can be achieved. Also, the effect of inlet-air humidity on oxides of nitrogen was studied as well as the very effective technique of 'direct water injection. The emission characteristics of natural gas and propane fuels were measured and compared with those of ASTM-AI kerosene fuel. Author N73-19826*# National Aeronautics and Space Administration. Lewis Research Center. Cleveland. Ohio. - INSTANTANEOUS DISTORTION INVESTIGATION James E. Calogeras 1972 19 p Presented at the Tech. Interchange Meeting of Air Inlets and Diffusers Panel. Naval 226 N73-19968 Aeroballistics Comm., Dahlgren, Va.. 19 Sep. 1972 (NASA-TM-X-68189; E-7329) Avail: NTIS HC $3.00 CSCL 21E The results obtained in an inlet-engine compatibility test run in the 10x10 SWT of the NASA-Lewis Research Center are reviewed. This program was run to measure the time-variant distortions produced in a supersonic inlet and to relate a unique distortion peak, occurring in an instant of time, to the origin of stall in a compressor. The major stumbling block in this type of effort is the determination of a proper increment of time over which to average pressures before computing distortions. It is reasonable to expect that the proper averaging time is related to the particular compressor in question. The most significant point reported is that the proper averaging time may not be solely dependent on a particular compressor, and. in fact, may vary with operating conditions, even for the same inlet-engine combination. Author N73-19826*# National Aeronautics and Space Administration. Lewis Research Center. Cleveland. Ohio. PRELIMINARY STUDY OF AN INTEGRAL FAN LIFT/CRUISE ENGINE FOR A 100 PASSENGER VTOL TRANSPORT Kestutis C. Civinskas Jan. 1973 36 p refs Prepared in cooperation with Army Air Mobility R and D Lab., Cleveland (NASA-TM-X-68186; E-7304) Avail: NTIS HC $4.00 CSCL 21E A simplified mission analysis was performed to determine an optimum engine cycle for a 100-passenger VTOL transport with a range of 500 statute miles. The aircraft had a total of eight integral fan lift engines, three of which serve as cruise engines. Fan pressure ratio was varied from 1.2 to 1.3, overall pressure ratio from 7 to 13. and turbine inlet temperature from 2460 to 2860 R. Bypass ratio was selected to meet a 500-foot altitude flyover noise goal of 95 PNdB. Airplane gross weight and direct operating cost (DOC) were calculated. The lowest' DOC of 1.82 cents per seat-mile was achieved with a fan pressure ratio of 1.3, overall pressure ratio of 12. and turbine inlet temperature of 2860 R. Author N73-19910 Oklahoma Univ.. Norman. DYNAMIC BUCKLING OF AN AXIALLY COMPRESSED CYLINDRICAL SHELL WITH DISCRETE RINGS AND STRINGERS Ph.D. Thesis Gary Andrew Fisher 1972 134 p Avail: Univ. Microfilms Order No. 72-23094 The structural response of light aircraft to crash loadings as a basis for crashworthy aircraft design is discussed. The investigation is based on an analysis of the dynamic buckling of discretely stiffened shells. The primary loading is identified as a suddenly applied axial compression loading of short to medium time duration. Appropriate nonlinear strain-displacement relations and equations of motion for the assumed modal shapes were developed. Response curves were plotted in the form of maximum radial deflection as a function of time. Because of the nature of dynamic buckling, the criterion was established that shell buckling occurred when a large increase in radial deflection was observed for a particular loading condition. Dissert. Abstr. N73-13942# Defence Research Establishment Valcartier (Quebec). ILLUMINANCE MEASUREMENTS OF AIRBORNE FLARES CFB COLD LAKE 1970 D. Pleiter Aug. 1972 81 p refs (DREV-R-673/72) Avail: NTIS HC $6.25 During tests of two types of flares simultaneous recordings were made of the ground illuminance at two separate locations. In the case of 11 flares of the first type and 4 of the second, effective values of the luminous intensity were obtained by combining the illuminance measurements with theodolite meas- urements of flare position. The effective values ranged from 10 to 20 percent lower than the intensities ascribed to the flares. In addition, some subjective observations were made of the spectra of the flares and of tactical scenes viewed through a low-light-level television system. Author N73-19947# Bureau of Mines. Bartlesville. Okla. Energy Research Center. EMISSION CHARACTERISTICS OF AN AIRCRAFT AUXIL- IARY POWER UNIT F. W. Penn and W. F. Marshall 1973 16 p Sponsored in part by EPA (BM-RI-7735) Avail: NTIS HC $3.00 An aircraft auxiliary power unit (APU) was used as an exhaust source for evaluation and refinement of sampling and analytical procedures for gas turbine engines. The unit was also used to determine the emission characteristics of APU's in service and to study the effect of fuel composition and combustor design on exhaust emissions. Carbon monoxide, carbon dioxide, oxides of nitrogen, hydrocarbons, aldehydes, paniculate loading, and odor were measured at engine operating modes representing the duty cycle encountered in airline operation. Analyses showed good repeatability, and adequate sensitivity was attained in these experiments. Smoke opacity measurements were not taken owing to the lack of a high-sensitivity smokemeter. Results showed that the minimum emission levels occurred with the standard combustor and jet A fuel. Emission rates were highly dependent on test mode, but emission patterns as a function of test mode were similar for all fuels and combustors tested. A comparison of three identical design production combustors showed a variation in average emission rates of less than 5 percent. Author N73-1S949*# National Aeronautics and Space Administration. Lewis Research Center. Cleveland, Ohio. EFFECTS OF PREVAPORIZED FUEL ON I EXHAUST EMISSIONS OF AN EXPERIMENTAL GAS TURBINE COMBUSTOR Carl T. Norgren and Robert D. Ingebo 1973 25 p refs Presented at Spring Meeting of the Central States Sect, of the Combust. Inst.. Urbana. III.. 27-28 Mar. 1973 (NASA-TM-X-68194. E-7336) Avail. NTIS HC $3.25 CSCL 21B Effects of fuel vaporization on the exhaust emission levels of oxides of nitrogen (NOX). carbon monoxide, total hydrocarbons, and smoke number were obtained in an experimental turbojet combustor segment. Two fuel injector types were used in which liquid ASTM A-1 jet fuel and vapor propane fuel were in- dependently controlled to simulate varying degrees of vaporization. Tests were conducted over a range of inlet-air temperatures from 478 to 700 K (860 to 1260 R), pressures from 4 to 20 atmospheres, and combustor reference velocities from 15.3 to 27.4 m/sec (50 to 90 ft/sec). Converting from liquid to complete vapor fuel resulted in NOX reductions as much as 22 percent and smoke number reductions up to 51 percent. Author N73-19968 .Air Force Systems Command, Wright-Patterson AFB. Ohio. Flight Environments Branch. AIR-TO-GROUND TARGET ACQUISITION WITH FLARE ILLUMINATION c23 Robert L. Hilgendorf IN AGARD Air to Ground Target Acquisition Nov. 1972 11 p refs I This paper is concerned with the results from three recent experiments. Experiment 1 dealt with the effect of shielding e 25.000.000-lumen flare source and determining the optimal number of flares to be used for a given target area. No statistically significant effect was found due to flare shielding. For the given target area simulated, it appeared that there was no additional benefit derived from igniting more than two flares over a simulated area of about 1.5 kilometers by 5 kilometers. Experiment 2 dealt with shielding of a 60,000.000-lumen source, and again, no statistically significant effect was found due to the flare shielding. Experiment 3 dealt with the visual acuity under simulated flare light. In this experiment, each of eight groups of five subjects performed simulated observer altitude ranging in 152-meter increments from 152 to 1,219 meters. For t!.,: slant ranges simulated (1.029 to 1.587 meters), 610 meters was the best altitude for visual performance. Like the other findings, this could have significant impact <"•?- tactical planning for night missions. The parameters of this study have now been blown-up to real-world size and the Aerospace Medical Research Laboratory,- in conjunction with the Air Force Armament Laboratory, is conducting flight tests to validate the altitude d.-na of the experimental simulations. Author 227 N73-19970 N73-19970 Army Electronics Command. Fort Monmouth, N.J. Avionics Lab. A DESIGN CONCEPT FOR A DUAL HELICOPTER NIGHT SCOUT SYSTEM William J. Kenneally In AGARD Air to Ground Target Acquisition Nov. 1972 11 p refs Limited but promising operational experience with helicopter- borne night vision systems (both low light level TV and forward looking infrared) has spurred an interest in the application of night vision technology to second generation airborne systems. The limited quantitative performance data on these first generation systems, coupled with the significant advances in night vision technology made during the intervening period, place severe restrictions on the system designer attempting to make logical system tradeoffs. The scope of the paper is to examine various relevant data on the subject and to develop a design concept for such a second generation scout system. . Author N73-19984* Jet Propulsion Lab.. Calif. Inst. of Tech.. Pasadena. Guidance and Control Div. HELICOPTER VISUAL AID SYSTEM c23 R. L Baisley In its JPL Quart. Tech, Rev.. Vol. 2. No. 4 1973 p-72-86 ref CSCL 20F The results of an evaluation of police helicopter effectiveness revealed a need for improved visual capability. A JPL program developed a method that would enhance visual observation capability for both day and night usage and demonstrated the feasibility of the adopted approach. This, approach made use of remote pointable optics, a display screen, a slaved covert searchlight, and a coupled camera. The approach was proved feasible through field testing and by judgement against evaluation criteria. Author N73-19988# Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt. Porz (West Germany). [ORGANIZATION OF DFVLR AND RESEARCH ACTIVITIES DURING 1971] Annual Report. 1971 1971 494 p refs In GERMAN Avail: NTIS HC $26:75 The organization and management of the society are outlined and research work is reported in the following faculties: fluid mechanics, aeromechanics and flight control, solid materials and construction methods, propulsion and energy, electronics, aerospace physics, space simulation, and aerospace medicine. Transl. by G.G. 228 SUBJECT INDEX AERONAUTICAL ENGINEERING / A Special Bibliography (Suppl. 32) JUNE 1973 Typical Subject Index Listing I 1 SUBJECT HEADING I BIDSOCABBOI PDBLS] ' ' ' ["Conservation of fossil fuels in coanercial L aviation by usinq hydrogen INASA-C8-112201j |M73-11019| 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.I 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. 4-300 AIBCBAFT Optimization and design of the rear fuselage of the A 300 B aircraft structure. A73-23799 »C GEBEBATOBS Characteristics of conventional alternators and aircraft electrical pover systems and comparison with electric systems using superconductors N73-19036 Characteristics of superconducting electric generators to show effect of electromechanical, electromagnetic, and cryogenic parameters on design N73-19039 &CCELEBATIOH (PHYSICS) Condition of drift invariance of two-staqe gyroscope with arbitrary gas-lubricated main bearings in active accelerations N73-19635 ACOUSTIC HEASOBEHENTS Performance characteristics of solid state converter system for measuring aircraft noise and sonic boom [NASA-CR-112260] 1173-18019 Heasurement of noise levels produced by F-105 aircraft and analysis of effects on environment and land use tAD-753113] N73-18056 Application of sound suppression techniques to OH-6 helicopter and measurement of resultant noise reduction rAD-753646] H73-18077 Measurement of indoor and outdoor sound pressure levels at airport control towers during aircraft takeoff and landing [AD-7525351 N73-18262 Evaluation of aircraft noise pollution level as a predictor of annoyance [NASA-CH-130920] H73-18978 Analysis of aircraft noise environment for land areas in vicinity of military air bases [AD-751111] 1173-19028 ACOOSTIC PROPERTIES Effect of various physical and operating parameters on noise produced by lov pressure ratio propulsive fans operating at subsonic speeds CNASA-CB-2188] N73-18011 Hind tunnel tests to determine acoustic properties of semispan wing with externally blown let flap to include effects of flap size, vertical location and forward speed [NASA-TH-X-2719] H73-180U1 ADHESIVE BOHDIHG Adhesive metal/glass laminate bonding, discussing materials, tests and interlaminar strength effects A73-21092 AEHIAL EIPLOSIOHS An international review of civil aircraft damaged or destroyed by deliberate detonation of explosives /sabotage/ 1961-1972. A73-2U708 AEBIAL PHOTOGBAPBY Nelson Tyler helicopter camera mount for aerial reconnaissance photography providing camera balance and motion stability under combat flight conditions , A73-21919 AEBIAL BECONNAISSASCE Nelson Tyler helicopter camera mount for aerial reconnaissance photography providing camera balance and motion stability under combat flight conditions A73-2U919 AEBODIHAHIC CHABACTBBISTICS Theoretical determination of the characteristics . of helicopter rotors A73-22205 Toward simpler prediction of transonic airfoil lift, drag; and moment. A73-22131 Aerodynamic forces and moments estimation for slender bodies of circular and noncircnlar cross section without and with lifting surfaces at 0-90 degree angles of attack A73-23168 Technique for predicting shock envelopes and pressure distributions for two dimensional airfoil at angles of attack producing shock detachment and subsonic flov fNASA-TN-D-7197] N73-18001 Analysis of influence of main geometry parameters on aerodynamic characteristics of wing-fuselage combination in incompressible flow CDLS-PB-72-63] H73-1800S Evaluation of fluid dynamics of aircraft stalling to determine effects of three dimensional flow, wing sweep back, and high lift devices [AGAHD-AH-19] N73-18023 Aeroelastic divergence of transport aircraft flying at supersonic speeds and desiqn techniques to eliminate adverse effects [NASA-CR-112262] N73-18036 Numerical analysis of aerodynamic characteristics of unsteady, two-dimensional, jet-flapped wing [AD-752928] N73-18051 Aerodynamic characteristics of flow around wing profiles fAD-752686] N73-18051 Calculation of outer inviscid flow about rectangular wing moving at supersonic speeds [NASA-CB-130985] B73-18269 Numerical analysis of inviscid, fully developed structure of lift-generated vortices behind aircraft wings and extension to aruJl L-ary span-loaded distributions [NASA-TH-X-62221] N73-18289 Comparison of validity of results obtained by flight simulation with results obtained from actual flight test of short takeoff aircraft N73-19007 A-1 ABBODYBAHIC COBFPICIEHTS SUBJECT IBDEI Determination of aircraft aerodynamic characteristics under captive flight conditions and description of test equipment H73-19010 Hind tunnel tests to determine effects of blade tvist and aeroelasticity of rotary wings on tilt rotor performance from hover to Bach 0.7 speed [NASA-TB-X-68948] 1173-19012 Computerized simulation of aerodynamic characteristics fox trailing vile system towed by orbiting aircraft [4D-753909] N73-19255 Computerized simulation of spiral curve of wire being toned behind orbiting aircraft tAD-753908) H73-19256 AEBODIHABIC COEPFICIEHTS fluctuating lift and moment coefficients for cascaded airfoils in a nonuniform compressible flow. A73-22U32 A method of measuring the thrust, the polar, and the performance of an aircraft on the basis of flight tests A73-2H191 Supersonic aerodynamic influence coefficients for isolated and parallel interfering coplanar and noncoplanar vings [HASA-CB-216BJ S73-18003 transonic wind tunnel tests of two dimensional airfoil fitted with square and convex semicircular blunt bases to determine aerodynamic drag coefficients [ABL/A-HOTE-336J B73-18994 Procedure for developing aerodynamic parameters for use in flight simulator research projects with emphasis on wind tunnel measurements S73-19008 Drag coefficients for Echo 1 and Explorer 21 spherical surfaces in atomic oxygen over energy range from 4 to 200 eV CHASA-CR-2233] H73-19697 Influence of degree of turbulence on aerodynamic coefficients of cascades N73-19798 Effect of axial velocity ratio on aerodynamic coefficients of compressor cascade in viscous flow B73-19804 ABBODIBAHIC COHFIGOBATIOBS Symmetrical airfoils optimized for small flap deflection. A73-2H915 Development of takeoff airworthiness standards for new aircraft designs using motion simulators to compare performance and handling characteristics [NASA-TH-D-7106] ' B73-18031 Detail design features of short takeoff and landing commercial aircraft and impact on design caused by STOL reguirement - Part 2 fAEBO-13-PT-2l N73-18033 Design, development, and manufacture of natural shape free flight balloon to include requirements, documentation, testing, and inspection CiD-753086] B73-18055 Analysis of effects of rotary wing configuration on aerodynamic noise generation during hovering flight [AD-7533971 H73-18070 Numerical analysis of inviscid, fully developed structure of lift-generated vortices behind aircraft wings and extension to arbitrary span-loaded distributions [HASA-TH-X-62224} N73-18289 Hind tunnel tests to determine effects of blade twist and aeroelasticity of rotary wings on tilt rotor performance from hover to Hach 0.7 speed F.SASA-TH-X-689H81 H73-19012 Analysis of reguirements for turbofan engines for high speed commercial transport aircraft - Tol. 1 fNASA-CB-121132] H73-19820 Mission analysis of VTOl passenger transport aircraft to determine optimum engine cycle for minimum direct operating cost rBASA-m-X-68186] N73-19826 AEBODIBAHIC DBAG Transonic wind tunnel tests of two dimensional airfoil fitted with sguare and convex semicircular blunt bases to determine aerodynamic drag coefficients [AB1/A-BOTE-336] S73-1899« Flow instabilities of supersonic variable ramp inlets at Hach 2 discussing Concorde aircraft intake riBC-B/H-3711] H73-18999 AEBODIBAHIC FORCES Calculation of forces on stores in the vicinity of aircraft. A73-22U33 Compressibility effects on unsteady forces generated by jet engine blade rows aerodynamic interference, considering potential flow and viscous wake interactions A73-23443 Helicopter main-rotor blade flutter in steady inclined flight A73-23662 Hodifications to helicopter active transmission isolation system to provide method for measuring forces on rotary wing of CH-53 helicopter [SASA-CB-112245] H73-1802 - . . • [40-753513] '. N73-18491 AIEIIHE OPEBATIOHS Co-existence of scheduled and charter services in public air transport. . 473-23123 Charter air fleet maintenance economic management, discussing budget, manpower, time and materials control ' ' ' ' ' ,473-23243 Short haul air travel with Intermodal Automated Transfer systea for integrating ground transportation to allow passenger to stay in seat from origin to destination ' 473-23653 Development of maintenance policies'in the operation of aircraft A73-23655 Airlines flight safety management,' discussing ^visual systems simulator /VSS/ for Tristar 'sys'tems environmental and cycling .endurance ground tests ' ''' " - 473-24710 Cost effectiveness of planned aviation system' improvements, considering ATC automation vs terminal aids, noise control,, ground facilities, capacity and enroute situation 473-24767 Analysis of special problems and issues involved in long range needs of aviation with emphasis on ooise pollution created by aircraft operation -' Vol. 2 . ; ' . ' • ' ' H73.-18983 , Findings and recommendations of Aviation 4dvisbry Commission on long range needs of aviation. - Vol. 1 ; ' - S73-18984 Analysis of system concepts, design criteria, operating procedures, and terminal facilities for short haul transportation aircraft and supporting systems [NAS4-TH-I-62235] . H73-19013 Economic analysis of high density short haul .air market to, show aircraft requirements, engine, development, an'd funding sources ' [NASA-CB-2227] ' N73-19017 Analysis of problems in air traffic control caused by expansion of commercial and civil aviation in Germany and. proposed actions for improved safety and efficiency ' H73-19627 Requirements for air traffic 'co'ntrol in jGerjaan air operations and recommendations for improved air traffic control procedures .... ' , N73-19628 AIRPOBT PLABB1HG , ' . " ' Community response to aircraft noise. t 473-24562 Airfield requirements for flight safety enhancement, considering approach and takeoff path obstructions, runway conditioning, glide slope information and radio aids 173-24713 Airport design and management for safe* aircraft ground handling, discussing FAA rules on '. . ., , pavement and safety areas, marking and lighting, fire fighting, etc 173-24714 Cost effectiveness of planned aviation system . improvements, considering ATC automation vs terminal aids,, noise control, ground facilities, capacity and enroute situation 473-24767 Characteristics and functions of various types of aircraft landing fields in Germany and development of airfields for improved air safety" 'H73-19624 Analysis of airport operations to show importance to community, effect on environment, and application of new technologies for airport development H73-19625 A-8 SUBJECT IHDEX ATBOSPHEBIC TOBBULEHCE Analysis of airport operations to show importance to community, ,effect on environment, and application of new technologies for airport development N73-19625 AIBPOBT TOIEBS ,J , ., .. . . Beasurement of indoor and outdoor sound pressure levels at airport control towers'during'aircraft takeoff and landing CAD-752535] S73-18262 1IBPOHTS ' Aviation and atmospheric pollution - The real dimension of the problem and its solutions ' ' ' ; ; ' ' ' 473-22216 Reduction in auxiliary extinguishing agents and systems for aircraft ground fire suppression at military airports fAD-753069] ' . ' '. '' ' H73-18256 Structural design guidance and construction standards for upgrading and extending service life of airport paveuents tFAA-BD-08-2] K73-19266 Characteristics and functions of various types of aircraft landing fields in Germany and development of airfields for improved air safety - N73-19624 Analysis of airport operations to show importance to community, effect on environment, 'and application of new technologies for airport development N73-19625 Analysis of airport operations to show importance to community, effect pn environment, and application of new technologies for airport development . . • - - ' • N73-19625 AIBSFEEO Flight test of instrument for determining low ' ' airspeeds to evaluate suitability for helicopter airspeed indicator . [AD-7533U31 H73-18071 Heasurement of low airspeeds with ion beam produced in positive corona discharge based on beam deflection properties H73-19*23 ALASKA Air-cushion tankers for transporting Alaskan rNorth Slope oil fHASA-TB-X-2683] ' • I • H73-18981 ALGOBITHHS Convergent iterative smoothing algorithm for aircraft stability parameter identification from measurement, using variational optimization, procedure . | A73-22233 Development of algorithm for multiple hypothesis testing with application to amplitude comparison monopulse radar system in air traffic control operations CTN-1973-7] ' N73-18173 ALl-BBATHBB AIB HAVIGATIOH All-weather aircraft landing automation, discussing efficient optimal feedback control law selection based on trajectory termination or terminal control reguirements 1 ' A73-2H010 ALOHIHOB ALLOTS , ' ' Bethods for designing and developing aircraft structural components by riveting, welding, and gluing aluminum alloys parts CAD-753513] R73-18H91 ALOHIHOH COATIBGS Evaluation of aluminum runway surface concepts as possible aid to aircraft braking fNASA-TH-D-7186] H73-18040 AHG1E OF ATTACK Aerodynamic forces and moments estimation for slender bodies of circular and noncircular cross . . section without and with lifting surfaces at 0-90'degree angles of attack 'A73-23468 ASBOLAB PL01 Prediction of annulus wall boundary layers in" axial flow turbomachines 1 . • • N73-19813 ABTENA BADIATIOI PATTBBHS Influence of the nonidentity of the antennas of a Doppler speed meter on the accuracy of its operation A73-2«386 ABTEHHAS Computerized simulation of aerodynamic characteristics for trailing wire system € towed by orbiting aircraft [AD-753909] , ', N73-19255 APPROACH COHTBOL Comparison of conventional flight control systems . with a modern integrated flight control system A73-23762 Banned vehicle systems analysis techniques application to manual approach-to-landinq phase of aircraft flight, developing analytical control model A73-21011 Noise abatement two-segment, precision and category I, II and III approaches considerations .covering altimetry, cost and safety problems in ATC , ' A73-2U768 Analysis of aircraft instruments and display devices for approach control and landing of V/STOL aircraft - fAGABD-AH-51] N73-18139 Development of gradient clearance monitor concept to ascertain glide slope clearance signal , [FAA-BD-72-1U7] N73-19615 APPBOACH INDICATORS . , . ., Visual systems for indicating approach slope during aircraft landing , . A73-22975 Automatize approach systems certification and , short distance takeoff and landing tra^ectography by cinetheodolites, digital optical, airborne and inertial/radiosonde eguipment A73-23656 Development of gradient clearance monitor concept to ascertain glide slope clearance signal [FAA-RD-72-1*7] H73-196»5 ABCTIC BEGIOHS Effects of ground effect vehicle tests on ecology of arctic tundra in northern Alaska [AD-7517U1] H73-19026 Cold weather tests to determine application of gr'ound effect machines for military, logistic purposes in Arctic regions . CAD-753527] ' H73-19027 ASPECT BATIO Trailing,vortex sheet roll-np behind finite aspect ratio wings for different loading conditions, discussing' drag penalties for tip vortices strength improvements A73-23125 Drag reduction of rectangular wing with blunt trailing edge CDLB-FB-71-85] ' N73-18004 ATBOSPHEBIC ATTEHOATIOH , . . . Development of'model for analyzing propagation of weak normal shock wave through turbulent atmosphere and application to sonic boom characteristics [NEC-12981] H73-18028 ATBOSPHEBIC TEBPEBATOBB Airborne atmospheric temperature measurements correction for sensor response lag, deriving^ numerical scheme based on sensing systems wind tunnel calibration A73-23991 ATBOSFHEBIC TDEBOLBHCE . Development of model for analyzing propagation of . weak normal shock wave through turbulent atmosphere and application to sonic boon characteristics [BBC-12981J N73-18028 A-9 IdTOBAIIC COBTBOL SOBJECT IBDBX AOTOHAXTC COHTBOL International Federation of Automatic Control, Borld Congress, 5th, Paris, France, Jane 12-17, 1972, Proceedings. Part 2 - Transportation, aeronautics and space, ship automation, and control components. Part 3 - Ecology and systems engineering; Large scale, sensitivity, optimization and adaptation theory. Part 4 - Education, feedback, regulators, linear and nonlinear systems; Identification, differential games, discrete and stochastic systems. 473-2 , N73-19813 Shock wave boundary layer interaction in compressor cascades N73-19816 BOUNDARY VALUE PBOBLEHS Bayleiqh-Bitz solution of boundary value problem for plane compressible subsonic flow past aerofoil notinq converqence A73-2295K BRAKING Hind tunnel tests of blowinq on circular cylinders applied to aircraft control and braking at low speeds fABC-CP-1232] N73-19000 6BAZING Study and realization of special parts for aerospace construction by brazinq in a flnorided reducing atmosphere A73-22202 BUCKLING Analysis of structural response of light aircraft to crash loadinqs based on dynamic buckling of discretely stiffened shells N73-19910 C-130 ilBCBAFT Development of mathematical models for C-130 aircraft to predict; qeneral trends and probable values for stability derivatives and node parameters .over flight envelope ' [AD-753388] . N73-18076 CABLES (ROPES) Computerized simulation of spiral curve of wire beinq towed behind orbiting aircraft fAD-753908] B73-19256 CAPTIVE TESTS Determination of aircraft aerodynamic characteristics under captive fliqht conditions and description of test equipment N73-19010 CASCADE FLOi Unsteady nonlinear flow around an airfoil or a blade cascade with emission of turbulent vortices : A73-22212 Fluctuating lift and moment coefficients for cascaded airfoils in a nonuniform compressible flow. A73-22H32 Flow through movinq cascades of liftinq lines with fluctuatinq lift. A73-23697 Secondary flows - Theory, experiment, and application in turbomachinery aerodynamics. ' A73-23860 Calculation of flow through airfoils in cascade to show pressure distribution under conditions of two dimensional incompressible flow with boundary layer separation at trailing edge CD1B-FB-72-62] N73-18276 Influence of degree of turbulence on aerodynamic coefficients of cascades ' N73-19798 Effect of axial velocity ratio on aerodynamic coefficients of compressor cascade in viscous flow 873-19804 influence of axial velocity density ratio on compressor cascade performance in compressible flow • ' . r N73-19805 Experiments with cascade secondary flows H73-19811 Shock wave boundary layer interaction in • compressor cascades ' { N73-19816 CASCADES Development of supersonic cascade and wheel i structure for axial flow compressor [AD-752583] N73-18801I Effects of boundary layer flow patterns on upright cascade blade performance B73-19803 CASING i Feasibility evaluation of qraphite/epoxy composite materials to helicopter transmission housing. A73-23969 CEBTBIFOGiL POBPS Improvement of the calculation of the guide vanes of centrifugal pumps A73-22569 Flow twisting in front of rotor for centrifugal blower operation control, predictinq efficiency criteria A73-2U671 CEBAHIC COATINGS Thermal conductivity of mixed-composition plasma-sprayed coatings. A73-2346U CERTIFICATION Antomative approach systems certification and short distance takeoff and landing trajectoqraphy by cinetheodolites, digital optical, airborne and inertial/radiosonde equipment A73-23656 Aircraft noise reduction technology and certification standards, reviewing federal laws and regulations A73r2<1553 A-11 CHBOHIOB ALLOTS SUBJECT INDSI CflBOHIOH ALLOTS Protecting metals in corrosive high-temperature environments.- A73-23296 CIBCOIT BBEAKEBS Feasibility of solid state electric switch gear for aircraft and•spacecraft pNASA-CB-121140] • N73-18223 CIBCOLAB CTLIHDEBS Hind tunnel tests of bloving on circular cylinders applied to aircraft control and braking at low speeds (AHC-CP-1232] N73-19000 CIBCOLAB SHELLS Noise intensities of rectangular and circular supersonic nozzle geometries [NASA-CB-13096tt] N73-18701 CIBCOLAB IOBES Circular cylindrical tube lap joints elastic strain relations based on plane contact problem reduction to Prandtl type eguation in finite-span wing theory 1 ' - A73-2U363 CIVIL AVIATION Flight research fco develop airworthiness standards for civil aircraft. A73-2218H Bussian book on multichannel magnetic tape recorders in civil aviation ATC for speech communication uionitoring and preservation covering design and operation principles ' A73-232U5 Civil- transport aircraft future design trends, discussing subsonic, supersonic, hypersonic and V/S1OL aircraft, engine design, fuels and noise reduction '• A73-23682 The DOT/NASA Civil Aviation Besearch and : Development Policy Study. ' ' ' ' A73-2H552 Transportation safety - Technology applications: A systems approach to anti-hijacking. I ' A73-24559 Commercial air transportation projections,' discussing mass transportation, international - fkre structure and exchange of rights, security and technology ' ' '• '• A73-246II6 An international review of civil aircraft damaged or destroyed by deliberate detonation of explosives /sabotage/*196by expansion of commercial and civil aviation in Germany and proposed actions for improved safety and efficiency N73-19627 Beguirements for air traffic control in German air operations and recommendations for improved air traffic control procedures ! H73-19628 CLEAB AIB TDBBOLEHCE Intensive probing of >a clear air convective field by radar and instrumental drone aircraft'. A73-23989 CLIBATE Bussian book on aircraft natural-climatic environmental factors covering geographic region adverse effects on design, performance and maintenance A73-22349 CLIHBIHG FLIGHT Haximnn range flight path during climb with specified fuel supply and variable lift coefficient, solving differential eguations system by conjugate gradient procedure A73-24542 CLOOD COVEB Continuous particle replicator for cloud drops and ice crystals onboard pressuri'zed aircraft fAD-753091] N73-18655 COAHDA .EFFECT ' Jet deflection characteristics of jet-flapped airfoil with Coanda deflection surfaces based on velocity distribution and flow angle measurements for static operation CAD-753618] H73-18071 COLO BEATHEB TESTS Cold weather tests to determine application of ground effect machines for nilitary 1'oqistic purposes in Arctic regions [AD-753527] N73-19027 COLLISION AVOIDANCE Development of computer programs' for design of air route networks for improved flight safety - Part 1 fFAA-BD-72-118-1-PT-1] N73-19643 COHBAT Application of night vision technology helicopter night scouts ' ; N73-19970 COHBDSTIOH CHAHBEBS Gas turbine combnstor optimization dependence on combustion length and efficiency, cutoff pressure fall, wall cooling and pollution A73-22213 Combnstor design effect on jet aircraft engine exhaust pollutants reduction during hydrocarbon fuel burning . A73-24556 Combustion efficiency of annular turbojet combustor using heated natural gas as fuel tNASA-TH-X-2712] . . N73-18960 COHBOSTIOH EFFICIEHCT - , ' _ ' . Comhnstion efficiency of ansalar turbojet combustor using heated natural gas as fuel [NASA-T8-X-27U2] . N73-18960 COBBOSTIOB PHYSICS Effect of preyaporization of jet fuels on exhaust emission levels produced in turbojet combnstor segment ;• ' ' : [NASA-TH-I-681911] H73-199U9 COHBOSTIOH PBODOCTS Analysis of air pollution caused by exhaust from military aircraft engines;and development of technology for pollutant.measurement to meet EPA standards [AD-753095] . N73-18975 Development of techniques'for reducing exhaust emissions from turbine engines ' [NASA-TH-X-68192] ' ' N73-1982lt COBBAHD AHD COHTBOL Command and control of stability of Do-31 aircraft by landing and hovering ' ' ' , rBBVG-FBIT-72-25] N73-19022 COBBBBCE Capital equipment marketing, discussing industry-customer-government interface, marketing and sales techniques and functions, products initiation, etc A73-2U650 COBBEBCIAL AIBCBAFT ' ,1972 report to the aerospace profession; Proceedings of the Sixteenth Symposium, Beverly Hills, Calif., September 28-30,-1972. ' ' ' ' • [ 473-22176 Detail design features of short takeoff and landing commercial aircraft and impact on design caused by STOL reguirement' - 'Part 2 [AEBO-13-PT-2] N73-18033 Development of empirical method for^determining optimum reversing coefficient of thrust reversal of jet engines on passenger aircraft (AD-75281flJ N73-18048 Proceedings of'symposium on flight operations and air traffic control to show problems affecting airports, general aviation, air traffic controllers, and governmental agencies rDlB-JUTT-72-24] N73-19623 Analysis of problems in air traffic control caused by expansion of commercial and civil aviation in Germany and proposed actions for inproved safety and efficiency N73-19627 Analysis of requirements for turbofan engines for hiqh speed commercial transport aircraft - Vol. 1 rNASA-CB-121132] S73-19820 A-12 SUBJECT IIDEX COHFBBEHCES Preliminary design assessment of turbofan engines for installation on high speed commercial transport aircraft - Vol. 2 rNASA-CB-121133] . H73-19821 Propulsion system requirements for aircraft engines installed in high speed commercial transport aircraft - Vol..3 . [NASA-CB-121134] ' , H73-19822 COBPOIEHT BELIABILITI Ballistic-tolerant helicopter flight control , ., components from plastic composite materials. • , . A73-2396i( COHPOSITB HATEBIALS Terminal ballistic performance,of fiber glass epbxy composite material for aerodynamic control surfaces fAD-752918] H73^18584 COBPOSITB STBOCTOBES ' Bigh modulus organic fibre composites in aircraft applications. A73-22519 Bethods for designing and developing aircraft structural components by riveting, welding, and , gluing aluminum alloys parts [AD-753513] H73-18491 COBPOUHD HELICOPTBBS AH-56A rigid rotor .compound helicopter configuration and handling gualities under , autorotatibn conditions, discussing flight test program, piloting,descent performance • A73-22179 COBPBESSIBILIir EFFECTS Calculation of the transonic flow around an airfoil, taking account of the.exact lav of compressibility . > > • . A73-22210 Fluctuating lift afld moment coefficients for cascaded airfoils in a nonuniform compressible flow. A73-22432 Compressibility effects on unsteady forces generated by jet engine blade rows aerodynamic interference, considering potential flow and viscous wake interactions A73-23443 COBPBBSSIBLE FLO» ' u , • Analytical determination of pressure distributions on harmonically oscillating slender cruciform . wing and' cylindrical body combinations in compressible flow .[DLH-FB-71-87] \. N73-18006 Force and pressure distribution measurements on .' wing-body combination with wing of low aspect ratio in compressible flow ^ tDLB-FB-72-08) .H73-18008 Influence of.axial velocity density ratio on compressor' cascade performance in compressible .flow ' ' , N73-19805 C08PBESSOB BLADES .. ' Influence, of,'regulated unequal guide-vane spacing on the alternating stress level in the working blades of a compressor A73-22165 Experimental method for analyzing the unsteady flow in a transonic aircraft compressor "' . A73-22715 Development .'.of supersonic cascade and wheel structure for axial flow compressor [AD-752583J , H73-18804 Development of algorithm for testing gas dynamic design of axial flow compressors with multiple stages ' ; ! CAD-753519] . K73r18809 Effects of"boundary layer flow patterns on upright "cascade blade performance N73-19803 Effect.of axial velocity ratio.on aerodynamic , coefficients of compressor cascade in viscous flow . ' ' , ' • ' , , N73-19804 COBPBESSOB BOTOBS ' . Development of supersonic cascade and wheel 'structure for axial flow compressor tAD-752583] . ' ' ' 873^ 188011 COBPOTEB PBOGBABS Application of computer technigues for - • determination of flutter characteristics of aircraft and comparison with model matching data analysis [A6ABD-B-596] H73-18030 Computer models for application to automatic inspection, diagnostic, and prognostic,system . for maintenance of military aircraft - Appendix C [AD-752886] N73-18066 Computer output data for automatic inspection, diagnostic, and prognostic system for maintenance of military aircraft - Appendix D [AD-752887] H73-18067 Computer program for analyzing flow field generated near aircraft engine operating in reverse thrust [HASA-CB-121147] • . N73-18264 COBPOTBB lECHHIQOBS Computer calculation of the characteristics of multistage gas turbines . A73-22567 Application of integrated circuit technology and digital computer technignes to electric control of ^et engines . tNAL-TB-281] . H73-18799 Computer technigues and test facilities for structural engineering at German university institute . . t CISD-119) H73-18935 COMPUTERIZED DESIGB Optimization and design of the rear fuselage of the A 300 B aircraft structure. I A73-23799 COBP0TEBIZED SIBULATIOH Productivity estimates of the strategic airlift system by the use of simulation. A73-23774 Aircraft wake vortex avoidance systems with current locus detection and/or prediction capability, discussing design based on hazard assessment and computer simulation for performance A73-24557 Computerized simulation of longitudinal cable shapes during deployment from missile away from flying aircraft ; [AD-7,53907] ; , N73-192S4 Computerized simulation of aerodynamic ; characteristics for trailing wire system towed • by orbiting aircraft ' CAD-753909] , , N73-19255 Computerized simulation of spiral curve of wire .- . being towed behind orbiting aircraft rAD-753908] N73-19256 COHCBETES ' i , ': Ground erosion on grassland and concrete by "vertical takeoff of Do-31 aircraft tBHVG-FBWT-72-26] H73-19023 COHFEBEBCES ' , 1972 report to the aerospace profession; , Proceedings of the Sixteenth Symposium, Beverly Bills, Calif., September 28-30, 1972. , , : A73-22176 Association Technigue Baritime et Aeronautique, Session, 72nd, Ecole Rationale Snperieure de Techniques Avancees, Paris, France, Hay 15-19, 1972, Proceedings.. A73-22201 STOL Seminar, St. Louis, Bo., Barch 24, 1972, , fiecord. A73-22524 International Federation of Automatic Control, World Congress, 5th, Paris, France, June 12-17, 1972, Proceedings. Part 2 - Transportation, aeronautics and space, ship automation, and control components. Part 3 - Ecology and^systems engineering; Large scale, sensitivity, optimization and adaptation theory. Part 4 - Education, feedback, regulators, linear and nonlinear .systems; Identification, differential games, discrete and stochastic systems. • A73-24001 EASCON '72; Electronics and Aerospace Systems Convention, Washington, D.C., October 16-18, 1972, Becord. A73-24551 A-13 COHSTBDCTIOB BATEBIALS SOBJECT IHOKZ Human threats to air safety; Proceedings of the Twenty-fifth Annual International Air Safety Seminar, Washington, D.C., October 16-18, 1972. 173-21*707 Papers presented at conference on halogenated fire extinguishing agents tAD-753218] ' N73-18168 Proceedings of conference on flight test technology to analyze results of flight test and comparison with data obtained using flight simulators for short takeoff aircraft [DLB-HITT-72-18] . 'H73-19005 proceedings of conference on application of superconductivity techniques to auxiliary power systems for aircraft and missiles [AGABD-CP-104] 'N73-19030 proceedings of symposium on flight operations and air traffic control to show problems affecting airports, general aviation, air traffic controllers, and governmental agencies CDLR-HITT-72-24J N73-19623 COHSIBDCTIOH BATEBIALS Structural design guidance and construction standards for upgrading and extending service life of airport pavements rFAA-ED-08-2} H73-19266 COHTIHOOH FLOi Data acquisition system for S-1 wind tunnel with continuous subsonic/supersonic flow t«BE-TB-78U(SB/D) } 873-182*8 COHTBACT HAH4GEHEBT DSAF experience in lightweight fighter aircraft acquisition as illustration of requests for industrial proposals simplification and source selection process streamlininq 473-21947 COSTBOL EQOIPDEST performance tests of hydromechanical fuel control system for J-85 engine [NASA-IH-D-7198] K73-18082 COilBOI TBBOBT international Federation of Automatic Control, world Congress, 5th, Paris, France, Jane 12-17, 1972, Proceedings. Part 2 - Transportation, aeronautics and space, ship automation, and control components. Part 3 - Ecology and systems engineering; Large scale, sensitivity, optimization and adaptation theory. Part 4 - Education, feedback, regulators, linear and nonlinear systems; Identification, differential games, discrete and stochastic systems. A73-24001 Manned vehicle systems analysis techniques application to manual approach-to-landing phase of aircraft flight, developing analytical control model A73-24011 Application of optimal control theory to design of control system for supersonic inlet of turbojet engine [SASA-TN-D-7188] N73-18803 COHTB01LED ATBOSPHEBES Study and realization of special -parts for aerospace construction by brazing in a fluorided reducing atmosphere A73-22202 COBVECTIOH CDBBEHTS Bode of thickening of a low morning convective layer in clear sky } 473-23036 Intensive probing of a clear air convective field by radar and instrumental drone aircraft. A73-23989 CONVEBGBHCE Bayleiqh-Bitz solution of boundary value problem for plane compressible subsonic flow past aerofoil noting convergence A73-22951I COHVEBTEBS performance characteristics of solid state converter system for measuring aircraft noise and sonic boom fUASA-CB-112260] N73-18019 COPLIHG Thermal stresses in cooled gas turbine blade foils and roots with allowance for thermoelastic effects A73-22568 COBEOSIOH PBETENTIOB Protecting metals in corrosive high-temperature environments. A73-23296 Aircraft corrosion prevention by addition of potassium dichromate to rinse water [AD-753214] " N73-18050 COST ANALYSIS Development of maintenance policies in the operation of aircraft . .. A73-23655 Aircraft and ground equipment damage during ground handling operations, discussing repair costs and out-of-service time A73-24715 COST EFPECTITBHESS Cost effectiveness of planned aviation system improvements, considering ATC automation vs terminal aids, noise control, ground facilities, capacity and enroute situation A73-24767 Noise abatement two-segment, precision and category I, II and III"'approaches considerations coverinq altimetry, cost and safety problems in ATC A73-24768 Cost effectiveness of automatic inspection, diagnostic, and prognostic maintenance system for military aircraft - Appendix F t 40-752889} ' '- ' N73-18069 COST EEDDCTIOH Hot die forging /gatorizing/ technique for Ti and heat resistant alloys jet engine parts, emphasizing material and cost savings 473-23295 CBiCK PBOPAGATIOH Artificial slow crack growth under constant stress - The B-curve concept in plane stress, A73-23255 CBACKS A mechanized eddy current scanning system for aircraft struts. ' A73-24631 CBITICAL LOADING Artificial slow crack growth under constant stress . - The E-curve concept in plane stress. A73-23255 CROSS SECTIOBS Aerodynamic forces and moments estimation for slender bodies of circular and noncircular cross section without and with lifting surfaces at 0-90 degree angles of attack - 473-23468 CBCCIFOBB BUGS Analytical determination of pressure distributions on harmonically oscillating" slender cruciform wing and cylindrical body combinations in compressible flow fDLB-FB-71-87] N73-18006 CBDDE OIL Air-cushion tankers for transporting 41askan North Slope oil rNASA-TH-X-2683] N73-18981 CUMULATIVE DAMAGE High temperature fatigue sensor based on"- ' conductive composite device irreversible ' ' resistance increase resulting from cumulative strain damage A73-22504 COHVE FITTING ; Existence and unigueness of solutions obtained from streamline curvature method of calculating flow through turbomachines for several operating points of Bolls-Boyce compressor TABC-CP-1234] H73-18293 D4BAGB Aircraft and ground equipment damage during ground handling operations, discussing repair costs and out-of-service time • ' 473-24715 DATA ACQDISITION Data acquisition system for S-"1 wind tunnel with continuous subsonic/supersonic"flow C»BE-TR-784(BB/D) ] N73-18248 A-14 SUBJECT IBDEX DB1G DATA COBBELiTIOH Independent radar systems asinq information processing, data correlation, and telecommunication H73-18179 Dili LIHKS Systems planning for improved airport surveillance radar equipment usinq dual airborne antenna switching for air traffic control [FAA-BD-72-136] N73-18176 Dili PBOCESSIHG Application of computer techniques for determination of flutter characteristics of aircraft and comparison with model matching data analysis [AGABD-H-596] H73-18030 Dili PBOCESSIHG EQOIPHEHT Development of automatic inspection diagnostic and prognostic systems for maintenance of military helicopters - Vol. 1 fAD-7528931 H73-18060 Development of automatic inspection diagnostic and prognostic systems for maintenance of military helicopters - Vol. 2 CAD-752894] N73-18061 Formulation of automatic inspection, diagnostic, and prognostic system for maintenance of army .aircraft - Vol. 1 [AD-752882] H73-18062 Desiqn and tradeoff studies applied to automatic inspection, diaqnostic, and prognostic maintenance system for military aircraft - Vol. 2 [AD-752883J N73-18063 Technical proposal and development plan for automatic inspection, diaqnostic, and prognostic maintenance system for military aircraft - Vol. 3 rAD-752884] N73-18064 General specification for automatic inspection, diagnostic, and prognostic maintenance system for military aircraft - Vol. 4 CAD-752885], H73-18065 Computer models for application to, automatic inspection, diagnostic, and prognostic system for maintenance of military aircraft - Appendix C fAD-752886] I N73-18066 Computer output data for automatic inspection, diagnostic, and prognostic system for maintenance of military aircraft - Appendix D fAD-752887] H73-18067 Maintenance data tabulations for automatic inspection, diagnostic, and prognostic systems for military aircraft maintenance - Appendix E fAD-752888] N73-18068 DATA SBOOTHIHG Convergent iterative smoothing algorithm for aircraft stability parameter identification from measurement, using variational. optimization procedure A73-22233 Dili STSIEHS Development of algorithm for multiple hypothesis testing with application to amplitude comparison monopulse radar system in air traffic control operations CTH-1973-7] N73-18173 DBCISIOH HAKIHG Development of alqorithm for multiple hypothesis testinq vith application to amplitude comparison monopulse radar system in air traffic control operations [TN-1973-7] N73-18173 DELIA BIHGS Slender delta-wings for future subsonic passenger planes , A73-21992 Correlation of King-body combination lift data. A73-22135 Vortex sheet and increased lift caused by bloving from leading edges of slender delta King rARC-H/H-36921 , H73-18016 Method of characteristics solution of flow field on lee side of flat plate delta wing with supersonic leading edges fAD-753389] N73-18319 Methods for determining inviscid three dimensional flov about smooth shapes at supersonic speeds CAD-753695] N73-19311 DEPIOTHEBT Computerized simulation of longitudinal cable shapes during deployment frou missile away from flying aircraft [AD-753907] N73-19254 DIGITAL COBHAND SYSTEHS F-8 digital fly by »ire control system development and flight testing, usinq Apollo lunar guidance , computer and inertial measurenent unit, for > anqular rates and accelerations A73-22180 DIGITAL COHPOTBBS Application of integrated circuit technology and digital computer techniques to electric control of jet engines [HAL-TB-281] H73-18799 DIGITAL TECHNIQUES Digital pressure transducer based on vibrating cylinder frequency response to pressure changes, discussing operational principles and applications A73-22502 DISOBIEHTATIOB Investigation of correlation between pilot disorientation and UH-1 helicopter accidents IAD-753208] N73-18049 DISPEBSIHG Helicopter dotrnvash for dispersing fogs of 500 to 600 feet in depth fAD-753357] N73-18661 DISPLAT DEVICES Analysis of aircraft .instruments and display devices for approach control and landing of V/STOL aircraft [AGARD-AR-511 S73-18439 DISTANCE BBAS0BIBG EQOIPHENT Performance tests of various Tacan ground station modifications designed to minimize false distance measuring equipment indications fFAA-NA-72-65] H73-18664 DO-31 AIBCBAFT Results of aerodynamic iet interference tests for Do-31 aircraft and application to future VSTOL development for lift-loss calculation I rBMVG-FBBT-72-22] ' N73-18044 Far and near sound fields of Do-31 aircraft, and noise reduction for future VSTOL aircraft tBMVG-FBWT-72-23] ; N|73-18045 Landing loads of Do-31 aircraft in vertical landing, noting undercarriage reactions and' sinking speed [BHVG-FBHT-72-24] N73-18046 Command and control of stability of Do-31 aircraft by landing and hovering [BHVG-FBKT-72-251 , H73-19022 Ground erosion on grassland and concrete, by vertical takeoff of Do-31 aircraft fBHVG-FBWT-72-26] N73-19023 , Hot gas recirculation in Do-31 aircraft from scale model to aircraft and trends for future developments of V/STOL aircraft fBHVG-FBWT-72-29] N73-19024 Hathematical model of transition flight and application to Do-31 aircraft rBHVG-FB»T-72-30J H73-19025 DOPPLEB EFFECT Influence of the nonidentity of the antennas of a Doppler speed meter on the accuracy of its operation A73-24386 DOPPLEB NAVIGATION Doppler TACAH navigation system for helicopters obtaining data through computer display method A73-2U475 DOBHTIBE Aircraft and ground eguipment damage during ground handling operations, discussing repair costs and out-of-service time A73-24715 DOBHBASB Helicopter downwash for dispersing fogs of 500 to 600 feet in depth TAD-753357] N73-18661 DRAG Drag coefficients for Echo 1 and Explorer 24 spherical surfaces in atomic oxygen over energy range from 4 to 200 eV rNiSA-CR-2233] B73-19697 i-15 DRAG BEASOBEBEBT SUBJECT INDEX DBAS HEAS0RBNENT Drag reduction of rectanqular wing with blunt trailing edqe fDLB-FB-71-85] N73-18001 Beasurement of lift, draq, and pitching moments in winq section for range of flap deflections under two-dimensional flow conditions fAHC-CP-1233] 873-18018 DBIFT (IBSTBOHEHTATION) Condition of drift invariance of two-stage qyroscope vith arbitrary gas-lubricated main bearings in active accelerations N73-19635 DBOHE AIBCBAFT Aerial tarqets for weapon systems performance testing, discussing converted aircraft, pilotless drones and towed targets A73-23120 Turana drone system design and development for Australian naval guns and guided weapons exercises, describing construction and operational details A73-23122 DOCTED FLOI Flowfield calculations for some supersonic sections with ducted heat addition. A73-23089 DYBAHIC CHARACTERISTICS Prediction models for surface and air transportation dynamic environments, considering broadband and single frequency continuous and recurrent and intermittent discrete excitation modes A73-22718 Parachute opening dynamic analysis, taking into account risers, shrouds and canopy cloth elastic properties on opening history and loads A73-24647 Dynamic testing and structural modeling of aircraft tire properties [NASA-CB-2219] N73-18042 DfBABIC BODELS Prediction models for surface and air transportation dynamic environments, considering broadband and single frequency continuous and recurrent and intermittent discrete excitation modes A73-22718 Theoretical and practical aspects of an automatic hover control system for an unmanned tethered rotorplatform. A73-24009 DtHABIC STBOCTDEAL AHAITSIS Association Technique Baritime et Aeronautigue, Session, 72nd, Ecole Mationale Saperienre de Techniques Avancees, Paris, France, Bay 15-19, 1972, Proceedings. A73-22201 Dynamic analysis of helicopter structures A73-22206 Dynamic structural design of aeroelastic wind tunnel models using combinatorial flutter analyses N73-19291 Analysis of structural response of light aircraft to crash loadings based on dynamic buckling of discretely stiffened shells N73-19910 ECHO 1 SATELLITE Drag coefficients for Echo 1 and Explorer 24 spherical surfaces in atomic oxygen over energy range from 4 to 200 eV rSASA-CB-2233] N73-19697 ECOBOHIC FACTORS Charter air fleet maintenance economic management, discussing budget, manpower, time and materials control A73-23243 ECOHOBICS Economic analysis of high density short haul air market to show aircraft requirements, engine development, and funding sources CHASA-CB-2227] S73-19017 SDDI COEBE1TS A mechanized eddy current scanning system for aircraft struts. A73-24631 EFFECTIVE PERCEIVED BOISE LEVELS Perceived level calculation methods for aircraft flyover noise scaling, rating Jets, turboprops, piston aircraft and helicopters with frequency weighting functions, duration and tone corrections V73-2K391 EJECTION SEATS Aircrew escape autogyro ejector seat/flight vehicle H73-18890 ELASTIC DABPIHG Improving reliability and eliminating maintenance with elastomeric dampers for rotor systems. A73-23950 ELASTIC DEFOEBATIOB Circular cylindrical tube lap joints elastic strain relations based on plane contact problem reduction to Prandtl type equation in finite-span wing theory A73-2U363 ELASTIC PBOPBSTIES Parachute opening dynamic analysis, taking into account risers, shrouds and canopy cloth elastic properties on opening history and loads A73-2U6U7 ELASTOHERS Improving reliability and eliminating maintenance with elastomeric dampers for rotor systems. &73-23950 ELECTRIC BRIDGES Prefabricated strain gage bridge instrumentation for flight testing under time and environment installation restrictions, including tail vibration, wing load and tail boom tests A73-22506 ELECTRIC COBTBOL Application of integrated circuit technology and digital computer techniques to electric control of jet engines [HA1-TB-281 ] "> N73-18799 ELECTRIC COROIA Measurement of low airspeeds with ion beam produced in positive corona discharge based on beam deflection properties H73-19123 ELECTRIC EQOIPHENT Characteristics of supercondnctinq electric generators to show effect of electromechanical, electromagnetic, and cryogenic parameters on design N73-19039 ELECTRIC FIELD STRENGTH Breakdown criteria for streamer formation, electrostatic field analysis and laboratory high ' voltage experiments on aircraft initiation of lightning strikes A73-24558 ELECTRIC GENERATORS Features and characteristics of superconducting electrical machines and design of synchronous electric generator for airborne use S73-19040 ELECTRIC POflER SUPPLIES Evaluation of conference to investigate current and future development in aircraft electrical and auxiliary power systems fAGAHD-AH-50 ] H73-18081 Proceedings of conference on application of superconductivity techniques to auxiliary power systems for aircraft and missiles CAGABD-CP-104] K73-19030 Characteristics of conventional alternators and aircraft electrical power systems and comparison with electric systems using superconductors H73-19036 Characteristics of superconducting electric generators to show effect of electromechanical, electromagnetic, and cryogenic parameters on design N73-19039 Features and characteristics of superconducting electrical machines and design of synchronous electric generator for airborne use H73-19040 Characteristics of auxiliary power unit combined with accessory drive to form auxiliary power system for aircraft electric power supply H73-19C45 A-16 SDBJBCT IBDBI EEEOE COEBBCTIHG DEVICES Design principles of auxiliary power units of secondary power system for operation of aircraft equipment 1173-190*6 Analysis of interface between aircraft mechanical power requirements and performance requirements of auxiliary power systems ., '.. H73-19049 Analysis of qas turbine enqine requirements and performance when main propulsion system furnishes auxiliary power source H73-19050 Air Force research and development proqrams in aircraft electrical power systems to show planninq process for developinq specific classes of technoloqy H73-19052 Application of solid state switchinq, multiplexing, and electrically proqrammable loqic to aircraft electrical systems 1173-19053 Development of electrical qeneration and distribution systems for supersonic aircraft usinq solid state switchinq and remote control of protective devices B73-1905H E1ECTBICAL PAOLTS Breakdown criteria for streamer formation, electrostatic field analysis and laboratory hiqh voltage experiments on aircraft initiation of liqhtninq strikes A73-24558 E1ECTEICAL BESISTIVITT High temperature fatiqne sensor based on conductive composite device irreversible . resistance increase resultinq from cumulative strain damaqe A73-22504 EIECTBOHIC BQDIPHEHT Electronic systems for time constant and altitude error compensation of rate of climb indicator used in hiqh performance qlider flight A73-2U916 EHISSIOH SPECTBA Measurements of some hydrogen-oxyqen-nitroqen compounds in the stratosphere from Concorde 002. A73-22947 EHGIHE COBTBOL Application of inteqrated circuit technoloqy and diqital computer techniques to electric control of jet enqines rNAL-TB-281] B73-18799 EHGIHE DESIGH Influence of a chanqe in the throuqhput of the power turbine on the parameters of a dual-shaft gas turbine enqine A73-23599 Combustor design effect on jet aircraft engine exhaust pollutants reduction durinq hydrocarbon fuel burning A73-21556 Enqine cycle, configuration, and design requirements CNASA-CE-120970-VOL-2] H73-19019 Analysis of requirements for turbofan engines for high speed commercial transport aircraft - Vol. 1 rNASA-CB-121132] N73-19820 Preliminary design assessment of turbofan engines for installation on hiqh speed commercial transport aircraft - Vol. 2 [BASA-CB-1211331 N73-19821 Propulsion system requirements for aircraft enqines installed in high speed commercial transport aircraft - Vol. 3 fNASi-CB-121134] H73-19822 Development of techniques for reducinq exhaust emissions from turbine engines fllASA-TH-X-681921 N73-19824 EHGIBE FAILOHE Investigation of iron content of lubricating oil using a ferrograph and an emission spectrometer. A73-21165 Statistical analysis of engine failure/malfunction accidents for OS fixedwing aircraft of general aviation category during 1965 to 1969 tHTSB-AAS-72-10] K73-19015 EHGIBE ISLETS Analysis of internal flow conditions of inlet with centerbody retracted for short takeoff and landing aircraft takeoff and approach operations [SASA-TH-D-71851 N73-18010 Application of optimal control theory to design of control system for supersonic inlet of turbojet engine [HASA-TH-D-7188] . S73-18803 Suppression of turbine enqine inlet noise [AD-753000] S73-18806 EHGIBE HOISE Aircraft turboengine noise, discussing noise level/power output relations A73-23861 Jet aircraft engine noise reduction. A73-21555 Suppression of turbine enqine inlet noise [ AD-753000] H73-18806 Analysis of aircraft noise environment for land areas in vicinity of military air bases [AD-754111] N73-19028 EHGIHE PABTS Hot die forqing /gatorizing/ technique for Ti and heat resistant alloys jet engine parts, emphasizing material and cost savinqs A73-23295 EBVIBOBHEBT EFFECTS Bussian book on aircraft natural-climatic environmental factors covering geographic region adverse effects on design, performance and maintenance A73-22319 EHVIBOBHEBT BODELS Prediction models for surface and air transportation dynamic environments, considering broadband and single frequency continuous and recurrent and intermittent discrete excitation modes A73-22718 EBVIBOBHEHT POLLOTIOH Effects of qround effect vehicle tests on ecoloqy of arctic tundra in northern Alaska TAD-75171H] B73-19026 EHVIBOHHEHT SIHOIATOBS Airlines flight safety management, discussinq visual systems simulator /VSS/ for Tristar systems environmental and cyclinq endurance ground tests A73-24710 EHVIBOHHEBTAL TESTS Thermal conductivity of gixed-composition plasma-sprayed coatinqs. ' A73-23464 EPOII BESIBS Feasibility evaluation of qraphite/epoxy composite materials to helicopter transmission honsinq. A73-23969 EQUATIONS OF HOTIOB Development of empirical method for determininq optimum reversinq coefficient of thrust reversal of jet enqines on passenger aircraft [AD-752810] B73-18018 EQOIPHEBT SPECIFICATIONS Aircraft maintenance for safety and reliability, considering design requirements, human errors, fault diagnosis, redundancy, failure mode analysis, service data statistics and equipment specifications A73-23759 EQOIPOTEBTIALS Graphoanalytic method of calculating plane potential flows A73-23106 EBOSIOH Ground erosion on grassland and concrete by vertical takeoff of Do-31 aircraft CBSVG-FBKT-72-26] N73-19023 EBBOB AHALYSIS Analysis of three methods for evaluation of pressure error in aircraft pitot-static systems rCBAKFIELD-AEBO-11] • U73-18029 BBBOB COBBECTIHG DEVICES Airborne atmospheric temperature measurements correction for sensor response lag, deriving numerical scheme based on sensing systems wind tunnel calibration A73-23991 A-17 ESCAPE SYSTBHS SOBJECT IHDBI ESCAPE SISTEHS Aircrew escape autogyro ejector seat/flight vehicle H73-18890 BOBOPBAB IIBBDS Optimization and design of the rear fuselage of the A 300 B aircraft structure. A73-23799 BIHAOST GASES Aviation and atmospheric pollution - The real dimension of the problem and its solutions A73-22216 Combustor design effect on jet aircraft engine exhaust pollutants reduction during hydrocarbon fuel burning A73-21556 Analysis of air pollution caused by exhaust from military aircraft engines and development of technology for pollutant measurement to meet EPA standards fAD-753095] H73-18975 Development of techniques for reducing exhaust emissions from turbine engines [BASA-TH-I-68192] N73-1982U Development of sampling and analytical procedures for gas turbine engine exhaust using aircraft auxiliary poner unit as emission source [BH-BI-7735] N73-19947 Effect of prevaporization of jet fuels on exhaust emission levels produced in turbojet combnstor segment [SASA-TB-X-68191] N73-199U9 EXHAUST HOZZLES Jet aircraft exhaust nozzle for noise reduction tHASA-CASE-LAB-10951-1] H73-19819 BIPBB1HBBTAL DBS1GH Productivity estimates of the strategic airlift system by the use of simulation. A73-23774 BXPLOBEB 21 SATELLITE Drag coefficients for Echo 1 and Explorer 24 spherical surfaces in atomic oxygen over energy range from 1 to 200 eV CHASA-CB-2233) N73-19697 EITEBBAL STOBES Calculation of forces on stores in the vicinity of aircraft. A73-22433 EITEBBALLI BLOBH FLAPS Hind tunnel tests to determine acoustic properties of semispan ving with externally blown jet flap to include effects of flap size, vertical location and forward speed fHASA-Tli-X-27l»9] N73-18011 F-8 AIBCBAFT F-8 digital fly by wire control system development and flight testing, using Apollo lunar guidance computer and inertial measurement unit for angular rates and accelerations A73-22180 Flight control improvement of F-8 aircraft relative to carrier takeoff and landing CAD-753010] N73-18052 P-15 AIBCBAFT F-15 air superiority fighter aircraft flight testing, describing air inlet, flight control, landing gear, flaps, speed brake and cockpit layout A73-22178 F-15 fighter aircraft development, discussing design and functional features of power plant, flight control system, landing gear, flaps, speed brakes and cockpit A73-22198 F-105 AIBCBAFT- S Reasurement of noise levels produced by F-105 aircraft and analysis of effects on environment and land use fAD-753113] N73-18056 FABBICAIIOH Aircraft structural components in-house or subcontracted fabrication, discussing technical performance, economic and manpower aspects A73-23521 FACTOBIAL DESIGI Productivity estimates of the strategic airlift system by the use of simulation. A73-23774 FAIL-SAFE SISTEHS Artificial slow crack growth under constant-stress - The B-curve concept in plane stress. A73-23255 Bam air turbines for aircraft emergency power supply, discussing design, performance and control 'A73-23525 FAILOBS ANALYSIS Aircraft maintenance for safety and reliability, considering design reguirements, human errors, fault diagnosis, redundancy, failure mode analysis, service data statistics and equipment specifications A73-23759 FATIGUE (HATEBIALS) High temperature fatigue sensor based on conductive composite device irreversible resistance increase resulting from cumulative strain damage A73-2250H FATIGOE LIFE Evaluation of airframe fatigue life gage under constant and variable amplitude loading [AD-753800] N73-1846<( FEEDBACK COHTBOL Application of four methods for approximating optimal feedback gains. A73-22234 All-weather aircraft landing automation, discussing efficient optimal feedback control law selection based on trajectory termination or terminal control requirements A73-24010 Following theory for feedback controls, Harkov processes, and flow of automobiles and aircraft N73-19259 FIBEB STBEBGTH Sigh modulus organic fibre composites in aircraft applications. A73-22519 FIGHTEB AIBCBAFT OSAF experience in lightweight fighter aircraft acquisition as illustration of requests for industrial proposals simplification and source selection process streamlining A73-21947 Fighter aircraft survivable flight control system design and flight test philosophy, present status and trends, considering fly-by-wire and power-by-wire systems A73-22177 Air battle fighter aircraft design, discussing reguired performance characteristics in terms of lethality, maneuverability, range, visibility, handling qualities, sortie rate, repairability and fire control A73-22197 Correlation between lateral-directional static stability characteristics and spin susceptibility fAD-753905] N73-19029 FIBISHES Aircraft surface primers and finishes composition, pretreatment and application, discussing epoxy, acrylic and polyurethane primers mechanical and chemical properties A73-23522 FIBE EITIHGDISHEBS Papers presented at conference on halogenated fire extinguishing agents [AD-753218] N73-18168 Seduction in auxiliary extinguishing agents and systems for aircraft ground fire suppression at military airports [AD-753069] S73-18256 FLAPS (COBTBOL SDBPACBS) Symmetrical airfoils optimized for small flap deflection. A73-2M915 FLABES Illuminance measurement of two types of airborne flares [DHEy-B-673/72] N73-19942 Air-to-ground target acguisition with flare illumination H73-19968 A-18 SOBJECT IHDEX FLIGHT SIHOLAIOBS - FLAT PLATES Method of characteristics solution of flow field on lee side of flat plate delta wing vith ' supersonic leading edges fAD-753389] . N73-18319 FLIGHT CHARACTERISTICS Test pilots cole in aircraft flying qualities evaluation, discussing spin and longitudinal stability testing • A73-22181 Flight research to develop airworthiness standards for civil aircraft. 473-22184 Air battle fighter aircraft design, discussing reguired performance characteristics in terns of lethality, maneuverability, range, visibility, handling qualities, sortie rate, repairability and fire control A73-22197 Application of computer techniques for determination of flutter characteristics of aircraft and comparison vith model matching data analysis fAGARD-R-596] N73-18030 PLIGHT COHTSOL F-15 air superiority fighter aircraft flight testing, describing air inlet, fliqht control, landing gear, flaps, speed brake and cockpit layout A73-22178 F-15 fighter aircraft development, discussing design and functional features of power plant, flight control system, landing gear, flaps, speed brakes and cockpit A73-22198 Comparison of conventional flight control systems with a modern integrated flight control system A73-23762 Ballistic-tolerant helicopter flight control components from plastic composite materials. A73-23964 International Federation of Automatic Control, Borld Congress, 5th, Paris, France, June 12-17, 1972, Proceedings. Part 2 - Transportation, aeronautics and space, ship automation, and control components. Part 3 - Ecology and systems engineering; Larqe scale, sensitivity, optimization and adaptation theory. Part 4 - Education, feedback, regulators, linear and nonlinear systems; Identification, differential games, discrete and stochastic systems. A73-24001 Dynamics of variable sweep wing aircraft in the course of changing geometry. A73-24012 Flight control improvement of F-8 aircraft relative to carrier takeoff and landing tAD-753010] N73-18052 Development of integrated control system for supersonic aircraft based on pneumatic power generation N73-19056 FLIGHT CEBiS Civil aircraft commander and crew duties and rights in air piracy cases, discussing international agreements and national legal provisions A73-23683 Aircrew escape autogyro ejector seat/flight vehicle N73-18890 FLIGHT HAZARDS Analysis of factors affecting crashworthiness of light aircraft to show nature of damage to aircraft and hazards to flight crews fFAA-TE-FS-70-592-120A] H73-18032 FLIGHT BECEAHICS Remarks on the ISO international standards relating to 'Terns and Symbols for Flight Dynamics' A73-23657 FLIGHT PATHS Haiimun range flight path during climb with specified fuel supply and variable lift coefficient, solving differential eguations system by conjugate gradient procedure A73-24542 Evaluation of head-up display instrument for providing aircraft vertical guidance during landing approach to comply with noise abatement procedures [NASA-TH-I-621871 N73-18021 FLIGHT SAFETY The role of the test pilot in evaluating auto landing systems. II. A73-22183 Human threats to air safety; Proceedings of the Twenty-fifth Annual International Air Safety Seminar, lashington, B.C., October 16-18, 1972. A73-24707 Airlines flight safety management, discussing . visual systems simulator /VSS/ for Tristar systems environmental and cycling endurance ground tests A73-24710 Airfield requirements for flight safety enhancement, considering approach and takeoff path obstructions, runway conditioning, glide slope information and radio aids 173-24713 Proceedings of symposium on flight operations and air traffic control to show problems affecting airports, general aviation, air traffic controllers, and governmental agencies [DlR-HITT-72-241 1173-19623 Analysis of general aviation activities in Germany and recommendations for flight control procedures to reduce aircraft accident hazards H73-19626 Analysis of general aviation activities in Germany and recommendations for flight control procedures to reduce aircraft accident hazards H73-19626 Analysis of problems in air traffic control caused by expansion of commercial and civil aviation in Germany and proposed actions for improved safety, and efficiency N73-19627 Regnirements for air traffic control in German air operations and recommendations for improved air traffic control procedures N73-19628 Development of computer prograns for design of air route networks for improved flight safety - Part 1 CFAA-RD-72-118-1-PT-1] H73-196U3 Development of systematic methodology and computer programs for optimal design of national grid of high altitude 7HF omnirange navigation systems - Part 2 CFAA-BD-72-118-2-PT-2] N73-19644 Development of gradient clearance monitor concept to ascertain glide slope clearance signal fFAA-HD-72-147] H73-19645 Analysis of effects of automation on productivity and efficiency of air traffic control and flight services tMTH-6110] H73-19646 FLIGHT SIHDLATIOH Comparison of validity of results obtained by flight simulation with results obtained from actual flight test of short takeoff aircraft N73-19007 FLIGHT SIHULATOBS Developments in aerodynamic test facilities to show past experience, present status, free flight techniques, and future plans fAGARD-R-603] H73-18250 Proceedings of conference on flight test technology to analyze results of flight test and comparison with data obtained using flight simulators for short takeoff aircraft fDLR-HITT-72-18] N73-19005 Procedure for developing aerodynamic parameters for use in flight simulator research projects with emphasis on wind tunnel measurements N73-19008 Analysis of selected problems in formation of simulation models of V/STOL aircraft H73-19009 Performance of typical V/STOL aircraft and comparison of data obtained vith flight simulator against data obtained by actual flight tests N73-19011 A-19 FLIGHT TEST IHSTBDHEHTS SUBJECT INDEI FLIGHT TEST liSTHUHEHTS Prefabricated strain qaqe bridge instrumentation for flight testing under time and environment installation restrictions, including tail vibration, wing load and tail boom tests 473-22506 FLIGHT TESTS 1972 report to the aerospace profession; Proceedings of the Sixteenth Symposium, Beverly . Hills, Calif., September 28-30, 1972. A73-22176 F-15 air superiority fighter aircraft flight testing, describing air inlet, flight control, landing gear, flaps, speed brake and cockpit layout 473-22178 F-8 digital fly by wire control system development and flight testing, using Apollo lunar guidance computer and inertial measurement unit for angular rates and accelerations A73-22180 Test pilots role in aircraft.flying gualities evaluation, discussing spin and longitudinal stability testing 473-22181 The role of the test pilot in evaluating auto landing systems. I. 473-22182 The role of the test pilot in evaluating auto landing systems. II. 473-22183 Flight research to develop airworthiness standards for civil aircraft. 473-22184 4rava STOL turboprop passenger aircraft flutter flight test program, describing measurement instrumentation and data recording system 473-22185 4 method of measuring the thrust, the polar, and the performance of an aircraft on the basis of flight tests 473-24494 Beasurement of surface pressure fluctuations at two locations on XB-70 aircraft at local Bach number range from 0.35 to 2.45 [HASA-IN-D-7226] N73-18013 Proceedings of conference on flight test technology to analyze results of flight test and comparison with data obtained using flight simulators for short takeoff aircraft CDLB-MITT-72-18] N73-19005 Comparison of validity of results obtained by flight simulation with results obtained from actual flight test of short takeoff aircraft N73-19007 Performance of typical T/STOL aircraft and comparison of data obtained Kith flight simulator against data obtained by actual flight tests ' N73-19011 Ground and flight test program of Stokes flow parachute [NASA-CE-1122511 N73-19016 FLIGHT VEHICLES Aircrew escape autogyro ejector seat/flight vehicle 873-18890 FLOH CBABACIEBISTICS Computer calculation of the characteristics of multistage gas turbines 473-22567 Rind tunnel tests to determine flow characteristics of stalled t»o dimensional airfoil [NASA-CB-130919] N73-18020 Jet deflection characteristics of jet-flapped airfoil vith Coanda deflection surfaces based on velocity distribution and flow angle measurements for static operation fAD-753618J N73-18074 Calculation of flow through airfoils in cascade to show pressure distribution under conditions of two dimensional incompressible flow with boundary layer separation at trailing edge [DLE-FB-72-62] H73-18276 Numerical analysis of inviscid, fully developed structure of lift-generated vortices behind aircraft wings and extension to arbitrary span-loaded distributions [NASA-TB-X-62224J H73-18289 Development of method for analyzing performance of magnetohydrodynamic generator based on thermodynamic properties and.flow characteristics N73-19051 Bethods for determining inviscid three dimensional flow about smooth shapes at supersonic speeds TAD-753695] • N73-19311 FLOH DISTOBTIOH Effects of vane-induced flow rotation on diffuser flow distortion in axisymnetric , . mixed-compression inlet rN4S4-TB-I-2752J N73-18012 Analysis of scaling parameters for flow in core region of vortex generated by rectangular wing - tip and vortex generated by ogee wing tip .• ( [H4S&-CH-2180] N.73-18995 FLOB DISTBIBDTIOH Calculation of forces on stores in the vicinity "of aircraft. 473-22433 Flowfield calculations for some' supersonic sections with ducted heat addition. 473-23089 Hydrodynamic visualization technique application to unsteady flow patterns around models and analysis of boundary layers, separation and wakes 473-24842 Computer program for analyzing flow field generated near aircraft engine operating in reverse thrust rN4SA-CR-121147] ' 1173-18264 Calculation of outer inviscid flow about. rectangular wing moving at supersonic speeds [HASA-CB-130985] H73-18269 Existence and uniqueness of solutions obtained . from streamline curvature method of calculating flow through tnrbomachines for several operating points of Hoiis-Soyce compressor fABC-CP-1234] N73-18293 Hethod of characteristics solution of flow field on lee side of flat plate delta wing with - supersonic leading edges fAD-753389] . , N73-18319 Analysis of flow field around two dimensional airfoil of arbitrary shape [AD-753387] K73-18320 Becirculation flow pattern in inlet of VTOL lift engine exhausting normally to ground • fDLE-FB-72-50] . N73-18798 Effects of boundary layer flow patterns on upright cascade blade performance . . N73-19803 FLOB EQDATIOHS . Calculation of the transonic flow around an . . airfoil, taking account of the'exact law of compressibility . 473-22210 FLO! HE4SOHEBBHT Experimental method for analyzing the unsteady flow in a transonic aircraft compressor . . 473-22715 Procedure for developing aerodynamic parameters for use in flight simulator research projects with emphasis on wind tunnel measurements 1173-19008 FLOS SI1BILITY Prediction of aeroelastic instabilities in turbines . . . 473-22204 Flow instabilities of supersonic variable ramp inlets at Hach 2 discussing Concorde aircraft intake [ARC-H/B-3711] H73-18999 FLOW THEORY Transonic airfoils - Recent developments in theory, experiment, and design. . 473-23856 Calculation of outer inviscid flow about . rectangular wing moving at supersonic speeds r.NASA-CH-130985] , 873-18269 FLO» VELOCITY ' . Graphoanalytic method of calculating plane potential flows A73-23106 Boundary layer efficiency as working fluid, in ramjets for high aircraft speeds, obtaining external efficiency as function of boundary layer parameters and flow rate A73-23360 A-20 SUBJECT IHDEX GAS TOBBIHES FLOS VIS01LIZ1TIOH , Book - Annual review of fluid mechanics. Volume 5. 173-23851 Hydrodynamic visualization technique application to unsteady flov patterns aroand models and analysis of boundary layers, separation and wakes 173-2*802 FLUID DIH1HICS Evaluation of fluid dynamics of aircraft stalling to determine effects of three dimensional flow, wing sweep back, and high lift devices tlGAHD-AB-49] H73-18023 FLUID FLO! Static charge generation in hydrocarbon fuels during flow through pipes [AD-753386] H73-18706 FLUID BBCH1BICS Association Technique Maritime et Aeronautique, Session, 72nd, Ecole Rationale Superieure de Techniques Avancees, Paris, France, Hay 15-19, 1972, Proceedings. A73-22201 Book - Annual review of fluid mechanics. Volume 5. 173-23851 FLUTIBS AB11ISIS Arava STOL turboprop passenger aircraft flutter flight test program, describing measurement instrumentation and data recording system 173-22185 Helicopter nain-rotor blade flutter in steady inclined flight 173-23662 Dynamic structural design of aeroelastic wind tunnel models using combinatorial flutter analyses 1173-19291 FLI BI IIBE CORTBOL Fighter aircraft survivable flight control system design and flight test philosophy, present status and trends, considering fly-by-wire and power-by-nire systems 173-22177 F-8 digital fly by wire control system development and flight testing, using Apollo lunar guidance computer and inertial measurement unit for angular rates and accelerations 173-22180 FOG Helicopter downwash for dispersing fogs of 500 to 600 feet in depth fAD-753357] H73-18661 POLDIHG STBOCTUBBS Dynamic and aeroelastic problems of stop-rotors of V/ST01 aircraft occurring during retracting and stowing of rotary wings rDLB-FB-72-65-PI-1] N73-18027 FOBCB DISTBIBDTIOB Bodifications to helicopter active transmission isolation system to provide method for measuring forces on rotary wing of CH-53 helicopter [HlSl-CB-1122 ,r»ASA-TH-D-7198] . H73-1.8082 JET AIBCBAFT Combustion efficiency of annular turbojet' ' combnstor using heated natural qas as fuel rHASA-TM-X-27H2] H73-18960 A-24 SUBJECT IHDBI LIFT FiHS JET ilECBAPT BOISE ; . Aircraft turboengine noise, discussing noise . level/power output' relations A73-23861 Jet aircraft engine noise reduction. . . ' 173-24555 Evaluation of head-up display instrument for providing aircraft vertical guidance during landing, approach to comply with noise abatement procedures . • [8ASA-TB-X-62187] , H73-18021 Far and near sound fields of Do-31 aircraft, and noise reduction for future VSTOL aircraft tBBVG-FBST-72-23] , ,H73-18015 Beasnreuent of noise levels produced by F-105 aircraft and analysis of effects on environment . and land use CAD-753113] ' . H73-18056 Development of techniques for reduction of aircraft noise generated by short takeoff aircraft [H1SA-TH-I-68195] H73-19021 Model of jet aircraft shock cell noise generation and reduction [NBC-12923] !H73-19666 Jet aircraft exhaust nozzle for noise reduction [HASA-CASE-LAH-10951-1] , H73-19819 JET EHGIIE FOELS Effect of prevaporization of jet fuels on exhaust emission levels produced in turbojet combustor segment -' . [HASA-TB-X-68194] ' K73-19949 JET EIGIRES , . ' Aviation and atmospheric pollution - The real . dimension of the.problem and its solutions ; ' ; : A73-22216 Hot die forging /gatorizing/ technique for Ti and heat resistant alloys jet engine parts, .emphasizing material and cost savings A73-J-23295 Compressibility effects on unsteady -forces generated by jet.engine blade rows aerodynamic interference, considering potential flow and viscous wake interactions A73-23443 Recircnlation flpv pattern, in inlet of'VTOL lift engine exhausting normally to ground ' CDLB-FB-72-50] ' ' N73-18798 Application of integrated circuit technology and digital computer techniques.to electric control of jet engines' ; [HAL-TR-281] ' N73-18799 JET EXHAUST , Effect of prevaporization of jet fuels on exhaust emission levels produced in turbojet combustor segment ' ' " [HASA-TB-X-68194] ' - ' N73-/19949 JET FLAPS j I • i Numerical analysis of aerodynamic.characteristics of unsteady, two-dimensional, jet-flapped wing [AD-752928] H73-18051 Jet deflection characteristics of jet-flapped airfoil with Coanda, deflection surfaces based on velocity, distribution and flow angle measurements for static operation [AD-753618] U73-1807H JET LIFT ; Results of aerodynamic jet interference tests for Do-31 aircraft'and application to future VSTOL development for lift-loss calculation . [BBVG-FBWT-72-22] H73-18044 LABIHATES Adhesive metal/glass laminate bonding, discussing materials, tests and interlaminar strength effects A73-24092 LAHDISG AIDS Airfield requirements for flight safety enhancement, considering approach and takeoff path obstructions, runway conditioning, glide slope information and radio aids ' A73-24713 Characteristics and functions of various types of aircraft.landing fields in Germany,and * development of airfields for improved'air safety . ' ' * . s 873-19624 LABDIBG GEAR ' Air cushion landing gears for transport aircraft, discussing peripheral jet stream performance prediction and system installation on Buffalo STOL A73-23659 A mechanized eddy current scanning system for aircraft struts. A73-24631 Development of criteria for predicting landing impact loads for V/STOL aircraft based on data obtained by flight tests of X-22 aircraft [AD-753852] H73-18075 LABDIHG IBSTBOHBHTS Flight control improvement of F-8 aircraft ' ' relative to carrier takeoff and landing .[AD-753010] N73-18052 LAHDIBG LOADS Landing loads of Do-31 aircraft in vertical landing, noting undercarriage reactions and sinking speed ' [BBVG-FBHT-72-24] N73-18046 Development of criteria for predicting landing impact loads for V/STOL aircraft based on data obtained by flight tests of X-22 aircraft [AD-753852] ' ' N73-18075 LABDIHG SITES Design, construction, and maintenance of landing fields and runways ,[AD-75140p] H73-18263 Ground erosion on grassland and concrete by vertical' takeoff of Do-31 aircraft [BBVG-FBfT-72-26] , H73-19023 LAP JOISTS Circular cylindrical tube lap joints .elastic strain relations based on plane contact problem reduction to Frandtl type equation in finit'e-span wing theory ' A73-24363 LASER BABGBB/CBACKEB Airborne visible laser optical communication experiment between.high altitude aircraft and' ground'station, discussing tracker-transmitter - eguipment and atmospheric effects on performance A73-23395 LAUBCH VEHICLES . Linear programming for design of large flexible launch vehicle'autopilots [HASA-CB-124124] H73-19621 Users manual for COEBRA program for'design of launch vehicle autopilots [NASA-CR-12U125] H73-19622 LAR (JOBISPBDDEBCE) Civil aircraft commander and crew duties and rights in air piracy cases, discussing international agreements and national legal provisions 1 ' A73-23683 LEADIHG EDGES' Vortex sheet and increased lift caused by blowing from leading edges of slender delta wing tABC-R/B-3692] H73-18016 LIFT Fluctuating lift and moment' coefficients for cascaded airfoils in a nonuniform compressible flow. ' ' A73-22432 Correlation of wing-body combination lift data. • ' A73-22435 Flow through moving cascades of lifting lines with . fluctuating lift. A73-23697 A probabilistic evaluation of helicopter lift capability. A73-23775 Drag reduction of rectangular wing with blunt. trailing edge [DLB-FB-71-85] H73-18004 LIFT ADGHEBTATIOH Becirculation flow pattern in inlet of VTOL lift engine exhausting normally to ground [DLB-FB-72-50) . 'H73-18798 LIFT FAHS ' ' . Preliminary aerodynamic and mechanical design of selected gas generators and lift unit for V/STOL aircraft fNASA-CH-120972] N73-19020 A-25 LIFTING BODIES SDBJECI IHDEI LIFIIBG BODIES, Aerodynamic forces and moments estimation for slender bodies of circular and noncircnlar cross section without and with lifting surfaces at 0-90 degree angles of attack A73-23U68 LIFTING EOTOES Improving reliability and eliminating naintenance with elastomeric dampers for rotor systems. A73-23950 LIGHT AIBCBAFT Analysis of response of constant-attitude aircraft to atnospheric turbulence CNASA-CE-2201] . N73-18025 Analysis of factors affecting crashworthiness of light aircraft to show nature of damage to aircraft and hazards to flight crews [FAA-TB-FS-70-592-120A] \ N73-18032 Design of simple to fly, constant attitude light general purpose aircraft [NASA-CB-2208} H73-18037 Analysis of structural response of light aircraft to crash loadings based on dynamic buckling of discretely stiffened shells . N73-19910 LIGHT TRANSMISSION Airborne visible laser optical communication experiment between high altitude aircraft and ground station, discussing tracker-transmitter eguipment and atmospheric effects on performance A73-23395 LIGHTING BODIPHEHT Illuminance measurement of two types of airborne flares [DBEV-B-673/72J H73-19942 LIGHTHIBG breakdown criteria for streamer formation, electrostatic field analysis and laboratory high voltage experiments on aircraft initiation of lightning strikes A73-2U558 LINBAS PBOGBAHHIBG Linear programming for design of large flexible launch vehicle autopilots [NASA-CB-12IH24] H73-19621 Dsers manual for COEBEA program for design of launch vehicle autopilots [NASA-CR-124125] N73-19622 LIQUID HYDROGEN Potentials and problems of hydrogen fueled supersonic and hypersonic aircraft. A73-22830 LOB ASPECT BAIIO Performance tests on loir hub-tip ratio supersonic axial flow compressor rAD-752585] H73-18805 LOU ASPECT BATIO SIHGS Force and pressure distribution measurements on wing-body combination with wing of low aspect ratio in compressible flow tDLB-FB-72-081 N73-18008 LOB SPEED BIND TOBBELS Kind tunnel tests of bloving on circular cylinders applied to aircraft control and braking at low speeds [ABC-CP-1232] N73-19000 LOBES ATMOSPHERE Node of thickening of a lov morning convective layer in clear sky A73-23036 LUBRICATING OILS Emission spectrographic analysis of used aero engine oil - A tool of maintenance. A73-23212 Investigation of iron content of lubricating oil using a .ferroqraph and an emission spectrometer. A7 3-2416 5 M MAGNETIC TAPES Bussian book on multichannel magnetic tape recorders in civil aviation ATC for speech communication monitoring and preservation covering design and operation principles . A73-232U5 HAGNETOHIDBODIHAHIC GEHBBATOBS Characteristics of large, lightweight, saddle-coil, superconducting dipole magnet for airborne magnetohydrodynamic .generators 873-19038 Development of method for analyzing performance of magnetohydrodynamic generator based on thermodynamic properties and flow characteristics N73-19051 MAINTAINABILITY Bussian book - Transport aircraft maintainability. A73-22375 •AH MACBIHE SISTEBS Test pilots role in aircraft flying gualities evaluation, discussing spin and longitudinal ••' < stability testing A73-22181 The role of the test pilot in evaluating auto landing systems. I. A73-22182 HAHAGEHEBT METHODS DSAF experience in lightweight fighter aircraft acguisition as illustration of reguests for industrial proposals simplification and source selection process streamlining : A73-21947 Charter air fleet maintenance economic management, discussing budget, manpower, time and materials control A73-23243 Accomplishments during evaluation of automatic inspection, diagnostic, and prognostic maintenance system using OH-1 helicopter as test bed - Vol. 2 [AD-7528911 .N73-18059 • Development of automatic inspection diagnostic and prognostic systems for maintenance of military helicopters - Vol. 1 [AD-752893] N73-18060 Development of automatic inspection diagnostic and prognostic systems for maintenance of military helicopters - Vol. 2 > [AD-75289U] N73-18061 Formulation of automatic inspection, diagnostic, and prognostic system for maintenance of army aircraft - Vol. 1 [AD-752882] N73-18062 Design and tradeoff studies applied to automatic inspection, diagnostic, and prognostic maintenance system for military aircraft - Vol. 2 [AD-752883] . H73-18063 Technical proposal and development plan for automatic inspection, diagnostic, and prognostic maintenance system for military aircraft - Vol. 3 . rAD-752884] • • ' • • - N73-180611 General specification for automatic inspection, diagnostic, and prognostic maintenance system for military aircraft - Vol. » [AD-752885] H73-18065 Computer output data for automatic inspection, diagnostic, and' prognostic system'for maintenance of military aircraft - Appendix D [AD-752887) , N73-18067 Haintenance data tabulations for automatic inspection, diagnostic, and prognostic systems for military aircraft maintenance - Appendix S [AD-752888] , N73-18068 Cost effectiveness of automatic inspection, diagnostic, and prognostic maintenance system for military aircraft - Appendix F [AD-752889] N73-18069 Air Force research and development programs in aircraft electrical power systems to show planning process for developing specific classes of•technology 1 H73-19052 BAHBED SPACECRAFT - - - - 1972 report to the aerospace profession; Proceedings of the Sixteenth Symposium, Beverly Hills, Calif., September 28-30, 1972. A73-22176 HAIOAL COBTBOL Banned vehicle systems analysis technignes application to manual approach-to-landing phase of aircraft flight, developing analytical control model A73-2 boundary layer separation at trailing edge [DLR-FB-72-62] H73-18276 numerical analysis of inviscid, fully developed structure of lift-generated vortices behind aircraft wings and extension to arbitrary span-loaded distributions CH4SA-TM-X-62224] N73-18289 Turbulent pressure fluctuation measurements for cross section of supersonic diffnser inlet flow model N73-19288 PEESSDBE GRADIENTS Calculation of flow through airfoils in cascade to show pressure distribution under conditions of two dimensional incompressible flow with boundary layer.separation at trailing edge [DLB-FB-72-62] 873^ 18276 PBESSDBE HEASUBBHEIITS Analytical determination of pressure distributions on harmonically oscillating slender cruciform wing and cylindrical body combinations in compressible flow .CDLB-FB-71-87] N73-18006 Measurement of unsteady pressures developed on harmonically oscillating wing planform in three dimensional compressible flow tDLB-FB-72-55] N73-18007 Measurement of.surface pressure fluctuations at two locations on XB-70 aircraft at local Bach number range from 0.35 to 2.45 CHASA-TN-D-7226] H73-18013 Analysis of three methods for evaluation of pressure error in aircraft pitot-static systems tCBANFIELD-AEEO-11] H73-18029 Turbulent pressure fluctuation measurements for cross section of supersonic diffuser inlet flow model B73-19288 Error sources in pressure measurements on turbulent supersonic flows by nonstationary microphone H73-19629 PBESSDBE OSCILLATIONS Turbulent pressure fluctuation measurements for cross section of supersonic diffuser inlet flow model H73-19288. PBBSSOBE SEHSOBS Digital pressure transducer based on vibrating cylinder freguency response to pressure changes, discussing operational principles and applications A73-22502 PBIMEES (COATIHGS) Aircraft surface primers and finishes composition, pretreatment and application, discussing epoxy, acrylic and polyurethane primers mechanical and chemical properties A73-23522 PBOBABILITI DISTBIBUTIOH FUNCTIONS A probabilistic evaluation of helicopter lift capability. . • • . A73-23775 PEOBLBH SOLVING Development of algorithm for multiple hypothesis testing with application to amplitude comparison monopnlse radar, system in air traffic control operations fTN-1973-7] B73-18173 PBOCOHEHEHT MABAGEHENT OSAF experience in lightweight fighter aircraft acquisition as illustration of reguests for- industrial proposals simplification and.source selection process streamlining . A73-21947 PEODDCT DZVELOPBEBT Boeing 72,7 design and development in response to airline market reguirements, emphasizing, profitability A73-24875 PBODOCIIVITI Productivity estimates of the strategic airlift system by the use of simulation. • A73-23774 PEOPELLEE BLADES Extended natural mode method for calculating flapwise bending, edgewise bending, and torsional vibration modes and freguencies of helicopter rotor blades [DLB-FB-71-1081 . . . .. . K,73-18026 PEOPELLER FANS Effect of various physical and operating • parameters on noise produced by low pressure ratio propulsive fans operating at subsonic speeds CNASA-CB-2188] , S73-18011 PBOPELLEE SLIPSTREAMS - L Theoretical determination of the characteristics of helicopter rotors A73-22205 A-30 SUBJECT IHDEX REIBFORCIBG FIBERS PROPULSION SISTEH COBFIGDR&TIOHS Flowfield calculations for some supersonic ' sections with ducted heat addition. A73-23089 Desiqn parameters and characteristics of intermittent pulse jet engine for use as auxiliary power source ' • ' B73-19047 Propulsion system requirements for aircraft engines installed in high speed commercial transport aircraft - Vol. 3 fNASA-CR-121134] R73-19822 PBOPOLSIOH SYSTEM PERFORMANCE Potentials and problems of hydrogen fueled supersonic and hypersonic aircraft. A73-22830 Analysis of qas turbine engine requirements and performance when main propulsion system furnishes auxiliary power source < ' • N73-19050 PSYCHOLOGICAL FACIOBS Community response to aircraft noise. A73-24562 POLSEJET EHGIIES Desiqn parameters and characteristics of intermittent pulse jet engine for use as auxiliary power source N73-19047 PtJHP IHPELLEBS Improvement of the calculation of the quide vanes of centrifugal pumps A73-22569 QUIET EBGIHE PBOGBAB Jet aircraft engine noise reduction. A73-21555 BAD4B EQOIPHBHT Independent radar systems using information processing, data correlation, and telecommunication N73-18179 BADAR NAVIGATION Badio navigation review, discussing Decca, Loran, Omega, VOB/DBE,, satellite, inertial, integrated, area, approach and landinq, collision avoidance and space navigation systems A73-23636 BADAB TEACHING Development of algorithm for multiple hypothesis testing with application to amplitude comparison monopulse radar system in air traffic control operations riN-1973-7] ' N73-18173 Evaluation of associative processor in performance of tracking and conflict detection function in real time ATC terminal environment fPX-61106-REV-A] N73-19642 RADIATION EFFECTS EASCON '72; Electronics and Aerospace Systems Convention, Washington, D.C., October 16-18, 1972, Record. : A73-24551 BADIO HATIGATIOH Badio navigation review, discussing Decca, Loran, Omega, YOH/DME, satellite, inertial, integrated, area, approach and landing, collision avoidance and space navigation systems A73-23636 Performance tests of various Tacan ground station modifications designed to minimize false distance measuring equipment indications [FAA-NA-72-651 ' N73-18664 Design, construction, and demonstration of airborne, low frequency, phase stable receiver for aircraft navigation tAD-7511027] N73-19651 BADIO BECEIVBBS ' Desiqn, construction, and demonstration of airborne, low frequency, phase stable receiver for aircraft navigation CAD-75«027] B73-19651 BADOHES Nuclear thermal vulnerability of honey comb sandwich radome panels tAD-753666) N73-18605 BAILS Snow accumulations on air cushion vehicle track sections CHRC-129391 H73-18247 BilB IMPACT DAHAGE Experimental determination of high velocity liquid impact damage for application to rain erosion protection of supersonic aircraft [AD-753381] N73-1830S RAHJET EHGIRES Boundary layer efficiency as working fluid in ramjets for high aircraft speeds, obtaininq external efficiency as function of boundary layer parameters and flow rate ' •- . 473-23360 Design and characteristics of auxiliary power source to operate electric, hydraulic, and pneumatic subsystems in ramjet powered aerospace vehicles N73-19048 BAHPS (STRUCTURES) Flow instabilities of supersonic variable ramp inlets at Bach 2 discussing Concorde aircraft intake tABC-H/B-3711] 1173-18999 BAPID TBABSIT STSTEHS Short haul air travel with Internodal Automated Transfer system for integrating ground transportation to allow passenger to stay in seat from origin to destination A73-23653 BATE OF CLIBB INDICATORS Electronic systems for time constant and altitude error compensation of rate of climb indicator used'in high performance glider flight A73-2U916 RATLEIGH-BITZ SETBOD Bayleiqh-Bitz solution of boundary value problem ' for plane compressible subsonic flow past aerofoil noting convergence A73-22951 BEAL TIBE OPEBATIOB Evaluation of associative processor in performance of tracking and conflict detection function in real time ATC terminal environment CPX-6406-REV-A] B73-19612 RECIBCULATI7E FLUID FLOi Hot gas recirculation in Do-31 aircraft from scale model to aircraft and trends for future developments of V/STOL aircraft [BHVG-FBIT-72-291 873-1902U BECTABGLES Noise intensities of rectangular and circular supersonic nozzle geometries [BASA-CR-130961] N73-1870H BECTANGULAB WINGS • Drag reduction of rectangular wing with blunt trailing edge (DLB-FB-71-85] N73-1800U Calculation of outer inviscid flow about rectangular wing moving at supersonic speeds tNASA-CR-130985] N73-18269 BEEBTBI VEHICLES Bethods for determining inviscid three dimensional flow about smooth shapes at supersonic speeds [AD-753695] B73-19311 REINFORCED FUSTICS High modulus organic fibre composites in aircraft applications. ' A73-22519 Ballistic-tolerant helicopter flight control components from plastic composite materials. A73-2396I) Feasibility evaluation of graphite/epoxy composite materials to helicopter transmission housing. A73-23969 Terminal ballistic performance of fiber glass epoxy composite material for aerodynamic control surfaces [AD-752918] 873-1858* REINFORCING FIBERS High modulus organic fibre composites in aircraft' applications. A73-22519 A-31 BELI4BILITT AH4LTSIS SDBJECT INDEX BELIABILITT AHALISIS Development of maintenance policies in the operation of aircraft 473-23655 Preliminary design assessment of turbofan engines for installation on high speed commercial transport aircraft - Vol. 2 CNASA-CH-121133) H73-19821 EESCOE OPERATIONS Human threats to air safety; Proceedings of the Twenty-fifth Annual International Air Safety Seminar, Washington, B.C., October 16-18, 1972. A73-24707 Significant elements of an effective search, rescue, and survival system. A73-24712 Avionics requirements for HH-53C. helicopter engaged in search and rescue operations CAD-752625] , N73-18047 BESEABCH AHD DEVELOPMENT The DOI/SASA Civil Aviation Research and Development Policy Study. A73-24552 BESEABCH PROJECTS Air Force research and development programs in aircraft electrical power systems to show planning process for developing specific classes of technology , H73-19052 Organization and research projects for 1971 N73-19988 BESOHAHT VIBBATIOB Digital pressure transducer based on vibrating cylinder frequency response to pressure changes, discussing operational principles and applications A73-22502 BEHOLDS BOBBBB Dependence of turbulent line vortices decay on Reynolds number fAD-753131] N73-18297 BIGID ROTORS AH-56A rigid rotor compound helicopter configuration and handling gualities under autorotation conditions, discussing flight 'test program, piloting descent performance A73-22179 Analytic methods for calculating blade loads and shaft-transmitted vibratory forces in stiff bladed hingeless rotors operating at various advance ratios - Vol. 1 [HASA-CB-11*562] N73-18034 Descriptions, geometry, and technical data for three rotary wing systems used in determining vibration and loads in hingeless rotary wings. - Vol. 2 [UASA-CB-114568] N73-18035 BIVETIHG Methods for designing and developing aircraft structural components by riveting, velding, and gluing aluminum alloys parts . fAD-753513] S73-18491 ROCKET VEHICLES Stiletto air-launched supersonic aerial target design, development and capabilities, describing configuration, propulsion and control systems and operational envelope 473-23121 BOTABI STABILITT Improving reliability and eliminating maintenance with eiastomeric dampers for rotor systems. A73-23950 BOTABI IIHG AIBCBAFT Aircraft control system for rotary ding aircraft CHASA-C4SE-EBC-10139] N73-19004 BOTABI BIHGS - • - Theoretical determination of the characteristics of helicopter rotors 473-22205 Helicopter main-rotor blade flutter in steady inclined flight A73-23662 Modifications to helicopter active transmission isolation system to provide method for measuring forces on rotary wing of CH-53 helicopter rSASA-CB-112245] H73-18024 Dynamic and aeroelastic problems of stop-rotors of V/STOL aircraft occurring during retracting and stowing of rotary vings [DLB-FB-72-65-PT-1 ] N73-18027 Analytic methods for calculating blade loads and shaft-transmitted vibratory forces in stiff bladed hingeless rotors operating at various advance ratios -.Vol. 1 [NASA-CB-114562] N73-18034 Descriptions, geometry, and technical data, for three rotary King systems used in determining vibration and loads in hingeless rotary vings - Vol. 2 •CNASA-CB-11*568] N73-18035 Analysis of aerodynamic stall characteristics of airfoils at various angles of attack vith application to control forces of H-53 helicopter CAD-752917] N73-18053 Analysis of effects of rotary wing configuration on aerodynamic noise generation during hovering flight [AD-753397] N73-18070 Analysis of aerodynamic noise generated by tips of helicopter rotary vings during acceleration to near sonic speed [AD-752301] N73-18072 Analysis of airload and blade response of rotary vings to determine sources of rotor vibratory loads in level and maneuvering flight of HH-3A and CH-53A helicopters [HASA-CB-2225] H73-18996 Predicting loads and stresses on helicopter rotor blades CNAS4-TT-F-14845] N73-19014 ROT1TIHG FLUIDS Plow twisting in front of rotor for centrifugal blover operation control, predicting efficiency criteria 473-24671 ECTOS 3LABES Helicopter main-rotor blade flutter in steady inclined flight 473-23662 Extended natural mode method for calculating flapvise bending, edgewise bending, and torsional vibration modes and frequencies of helicopter rotor blades [DLH-FB-71-1081 H73-18026 BOIRAI COHDITIOHS Airfield requirements for flight safety enhancement, considering approach and takeoff path obstructions, runway conditioning, glide slope information and radio aids 473-24713 BDHBAtS Evaluation of aluminum runway surface concepts as possible aid to aircraft braking [HASA-TH-D-7186] H73-18040 Design, construction, and maintenance of landing fields and runways [AD-751400] H73-18263 SAFETT HANAGBHBHT Human threats to air safety; Proceedings of the Twenty-fifth Annual International Air Safety Seminar, dashington, D.C., October 16-18, 1972. A73-24707 Airlines flight safety management, discussing visual systems simulator /VSS/ for Tristar systems environmental and cycling endurance ground tests 473-24710 Airport design and management for safe aircraft ' ground handling, discussing ?A4 rules on pavement and safety areas, marking and lighting, fire fighting, etc • 473-24714 Aircraft and ground equipment damage during ground handling operations, discussing repair costs and out-of-service time 473-24715 SAIDilCH STRUCTURES Huclear thermal vulnerability of honey comb sandwich radome panels C4D-753666] . H73-18605 SATELLITE BAVIGATIOB SISTERS •>' Hadio navigation review, discussing Decca, Loran, Omega, VOB/DHE, satellite, inertial, integrated, area, approach and landing, collision avoidance and space navigation systems A73-23636 4-32 SUBJECT IBDEX SHROUDED PBOPELLEBS SCALIBG Perceived level calculation methods for aircraft flyover noise scaling, rating jets, torboprops, piston aircraft and helicopters with freguency weighting functions, duration and tone corrections • • ... 173-24391 SCAIIBG LABS Hot gas recirculation in Do-31 aircraft from scale model to aircraft and trends for future developments of V/STOL aircraft [BHVG-FBWT-72-29] N73-19021 SCABBEBS- Hicrovave landing system /HLS/ with Doppler ••' scanning technique for aircraft guidance precision improvement over standard VHF/OHP US, detailing five-year development plan A73-23652 A mechanized eddy current scanning system for aircraft struts. ' ' - A73-24631 SEABCHIBG : Significant elements of an effective search, rescue, and survival system. " A73-24712 SECOHDABI FLOI - - . - • - . Secondary flows - 'Theory, experiment, and application in tnrbomachinery aerodynamics. A73-23860 Experiments'1 with cascade secondary flows N73-19811 SEHIBHPIBICAl EQDATIOHS Toward simpler prediction of transonic airfoil- lift, drag, and moment. A73-22434 SEBISPAB HODELS Hind tunnel tests to determine acoustic properties of semispan wing with externally blown jet flap to include effects of flap size, vertical' location and forward speed CNASA-IB-X-27491 1173-18041 SEBSOBS ' " ' High temperature fatigue sensor based on conductive' composite device irreversible resistance increase resulting from cumulative • strain damage • ' A73-22504 SEHSOBT PEECEPTIOH Perceived level calculation methods for aircraft flyover noise scaling, rating jets, tnrboprops, piston aircraft and helicopters with freguency weighting functions, duration and tone corrections A73-24391 SEBVICE LIFE Gas turbine engine turbine blades service life increase by Cr and Al vacuum diffusion metallization, presenting full scale endurance test results A73-24965 Optimum service life determination technigne for Naval aircraft rAD-752747] N73-18057 Structural design guidance and construction standards for upgrading and extending service life of airport pavements fFAA-ED-08-2] - • H73-19266 SHELLS (STBOCTUBAL FOBHS) Analysis of structural response of light aircraft to crash loadings based on dynamic buckling- of discretely stiffened shells • '• N73-19910 SHOCK FBONTS One dimensional supersonic shock front location by sonic circle involute point by point plotting, using geometric considerations A73-23467 SHOCK HEATIBG Flowfield calculations for some supersonic - sections with ducted heat addition. ' • . A73-23089 SHOCK TESTS node! of jet aircraft shock cell noise generation and reduction ' . CHRC-12923] U73-19666 SHOCK iAVE IBTEBACTIOB Shock wave boundary layer interaction in : compressors cascades - • • • N73-19816 SHOCK RIVES Technigne for predicting shock envelopes and pressure distributions for two dimensional airfoil at angles of attack producing shock detachment and subsonic flow [HASA-TH-D-7197] ' H73-18001 Flight test measurements and analysis of sonic booms to determine caustics produced by variations in fligbt speed and to develop method for predicting shock wave-ground intersections [NASA-CB-2167] S73-18022 Development of model for analyzing propagation of weak normal shock wave through turbulent atmosphere and application to sonic boom characteristics [HBC-12981] ' N73-18028 SHOBT BADI AIBCBJFT Short haul air travel with Intermodal Automated Transfer system for integrating ground . transportation to allow passenger to stay in seat from origin to destination A73-23653 Conceptual designs of V/STOL lift fan commercial short haul transport aircraft to determine technical and economic feasibility [NASA-CB-2183] H73-18038 Analysis of system concepts, design criteria, operating procedures, and terminal facilities for short haul transportation aircraft and supporting systems [HASA-TH-1-62235] ' H73-19013 Economic analysis of high density short haul air market to show aircraft requirements,' engine development, and funding sources fBASA-CB-2227] N73-19017 SHOBT TAKEOFF AIBCBAFT Arava STOL turboprop passenger aircraft flutter flight test program, describing measurement instrumentation and data recording system A73-22185 STOL Seminar, St. Louis, Ho., March 24, 1972, Record. ' ' A73-22524 Automative approach systems certification and short distance takeoff and landing trajectography "by cinetheodolites, digital optical, airborne and inertial/radiosonde equipment A73-23656 Comparison of conventional flight control systems with a modern integrated flight control system A73-23762 Analysis of internal flow conditions of inlet with centerbody retracted for short takeoff and landing aircraft takeoff and approach operations [NASA-TK-D-7185] B73-18010 ' Detail design features of short takeoff and landing commercial aircraft and impact on design caused by STOL requirement - Part 2 [AEHO-13-PT-2] H73-18033 Proceedings of conference on flight test technology to analyze results of flight test and comparison with data obtained using flight simulators for short takeoff aircraft [DLR-HITT-72-18] ' K73-19005 Comparison of simulation and flight test results for automatic short takeoff aircraft landing system N73-19006' Comparison of validity of results obtained by flight simulation with results obtained from 'actual flight test of short takeoff aircraft H73-19007 Analysis of system concepts, design criteria, operating procedures, and terminal facilities for short haul transportation aircraft and supporting systems rBASA-TH-X-62235] N73-19013 Development of techniques for reduction of aircraft noise generated by short takeoff aircraft [NASA-TH-X-68195] H73-19021 SHBODDED PBOPELLEBS Vortice distribution field for calculating inlet ' flow of ducted propeller [AD-75411II] B73-19318 A-33 SIHGOLABISY (BATHEBATICS) SUBJECT IHDEI SIBGDLAEITT (BiTHEHATICS) Calculation of. the transonic flow around an airfoil, taking account of the exact lav of compressibility A73-22210 SLEBDEB BODIES Calculation of forces on stores in the vicinity of aircraft. A73-22433 Aerodynamic forces and moments estimation for slender bodies of circular and noncircular cross section without and Kith liftinq surfaces at 0-90 degree angles of attack A73-23168 Analytical determination of pressure distributions on harmonically oscillatinq slender cruciform •ing and cylindrical body combinations in compressible flow fDLB-PB-71-87] H73-18006 SLBBDBB SIBGS Slender delta-wings for future subsonic passenger planes A73-21992 Vortex sheet and increased lift caused by blowing from leading edges of slender delta wing [AHC-B/H-3692] H73-18016 SHOi Snow accamulations on air cushion vehicle track sections [NBC-12939] H73-182U7 SOLID STATE DEVICES Feasibility of solid state electric switch gear for aircraft and spacecraft CHASA-CB-121140] H73118223 Application of solid state switching, Dultiplexing, and electrically programmable logic to aircraft electrical systems N73-19053 Development of electrical generation and distribution systems for supersonic aircraft using solid state switching and remote control of protective devices N73-1905U SOLID STATE PHYSICS Proceedings of conference on application of superconductivity techniques to auxiliary power systems for aircraft and missiles [AGABD-CP-104] N73-19030 SOLID SOSPEBSIONS Investigation of iron content of lubricating oil usinq a ferroqraph and an emission spectrometer. A73-2U165 SOLID-SOLID IHTEBFACBS Circular cylindrical tube lap -joints elastic strain relations based on plane contact problem reduction to Prandtl type equation in finite-span ving theory A73-2H363 SOLIDIFICAflOH Advances in directional solidification spur usaqe in turbine airfoil shapes. A73-23293 SOHIC BOOHS One dimensional supersonic shock front location by sonic circle involute point by point plotting, usinq geometric considerations A73-23H67 Performance characteristics of solid state converter system for measurinq aircraft noise and sonic boom rNASA-CB-112260] N73-18019 Fliqht test measurements and analysis of sonic booms to determine caustics produced by variations in flight speed and to develop method for predicting shock wave-ground intersections fNASA-CB-2167] N73-18022 Development of model for analyzing propagation of weak normal shock wave through turbulent atmosphere and application to sonic boom characteristics [HBC-129811 N73-18028 Low sonic boom overpressure profiles for supersonic transport aircraft configurations CNASA-TH-I-27U6] N73-18039 SOUND FIELDS Far and near sound fields of Do-31 aircraft, and noise redaction for future VSTOL aircraft fBBVG-FBlT-72-23] B73-180U5 SOUBD GEHEBATOBS Analysis of aerodynamic noise generated by tips of helicopter rotary wings during acceleration to near sonic speed [AD-752301] B73-18072 SOOBD PBESSOBE Heasurement of indoor and outdoor sound pressure levels at airport control towers during aircraft takeoff and landing CAD-752535] S73-18262 SODBD PBOP46ATIOB Analysis of effects of rotary wing configuration on aerodynamic noise generation during hovering flight [4D-753397] H73-18070 Model of jet aircraft shock cell noise generation and reduction [NEC-12923] H73-19666 SOOBD HAVES Flight test measurements and analysis of sonic booms to determine caustics produced by variations in flight speed and to develop method for predicting shock wave-ground intersections [NASA-CB-2167] N73-18022 SPBCTBOBETBBS Emission spectrographic analysis of used aero engine oil - A tool of maintenance. 173-23242 SPEED IBDICATOBS Influence of the nonidentity of the antennas 'of a Doppler speed meter on the accuracy of its operation A73-24386 Analysis of three methods for evaluation of pressure error in aircraft pitot-static systems tCBABFIELD-AEBO-11] 873-18029 Flight test of instrument for determining low airspeeds to evaluate suitability for helicopter airspeed indicator [AD-7533H3] H73-18071 SPIH Correlation between lateral-directional static stability characteristics and spin susceptibility [AD-753905] H73-19029 STAGHATIOH PBESSOBE Flow through moving cascades of lifting lines with fluctuating lift. A73-23697 STAIB1ESS STEELS Study and realization of special parts for aerospace constrnction by brazing in a flaorided reducing atmosphere A73-22202 STALLIHG Time variant distortion in supersonic inlet related to stall in compressor tBASA-TH-1-68189] H73-19825 SZABDABDS Flight research to develop airworthiness standards for civil aircraft. A73-2218U Bemarks on the ISO international standards relating to 'Terms and Symbols for Flight Dynamics' A73-23657 STATIC ELECTBICITI Static charge generation in hydrocarbon fuels during flow through pipes IAD-753386] N73-18706 STATIC PBESSOBE Analysis of three methods for evaluation of pressure error in aircraft pitot-static systems CCBABFIELD-AERO-11] N73-18029 STATIC STABILITY Correlation between lateral-directional static stability characteristics and spin susceptibility [AD-753905] B73-19029 STATISTICAL AIALYSIS Statistical analysis of engine failure/malfunction accidents for OS fixedwing aircraft of general aviation category during 1965 to 1969 [BTSB-AAS-72-10] H73-19015 STOKES FLOW Ground and flight test program of Stokes flow parachute r»ASA-CB-112251] 1173-19016 A-3» SUBJECT IBDEI SOPEBSOHIC SPEEDS STBAIH GAGES Prefabricated strain qage bridge instrumentation for flight testing under time and environment installation restrictions, including tail vibration, wing load and tail boon tests A73-22506 Evaluation of airfrane fatigue life gage under constant and variable amplitude loading tAD-753800] H73-18U6U STBATOSPHEBE Measurements of some hydrogen-oxygen-nitrogen coapoands in the stratosphere from Concorde 002. A73-22917 STBESS COBCBHTBATIOB Stress concentration and groove design as factors in crack failure of low power single stage gas turbine rotor disk, using optical polarization technique A73-22166 STBESSED-SKIH STBDCTD1ES Optimization and design of the rear fuselage of the A 300 B aircraft structure. A73-23799 STBOCTOBAL DESIGN Structural design guidance and construction standards for upgrading and extending service life of airport pavements [FAA-ED-08-2] U73-19266 SIBOCIDBAL ENGIHEEBING Computer techniques and test facilities for structural engineering at German university institute [ISD-119] N73-18935 SttDCTOBAL FAILOBE Stress concentration and groove design as factors in crack failure of Ion power single stage gas turbine rotor disk, using optical polarization technique A73-22166 STBOTS A mechanized eddy current scanning system for aircraft struts. A73-2U631 SOBCOHIBACTS Aircraft structural components in-house or subcontracted fabrication, discussing technical performance, economic and manpower aspects A73-23521 SOBSOHIC AIBCBAFT Slender delta-wings for future subsonic passenger planes A73-21992 SOBSOHIC not Prediction of aeroelastic instabilities in turbines A73-2220<1 Bayleigh-Bitz solution of boundary value problem for plane compressible subsonic flow past aerofoil noting convergence A73-22954 SOBSOHIC SPEED Effect of various physical and operating parameters on noise produced by low pressure ratio propulsive fans operating at subsonic speeds CHiSA-CB-2188] H73-18011 SUPEBCH4BGBBS Piston engine tnrbocharging system based on split low and high pressure exhaust gas discharge porting, discussing different turbine staging arrangements 173-24925 SDPEBCOSDOCTIHG HAGHBTS Characteristics of large, lightweight, saddle-coil, superconducting dipole magnet for airborne magnetohydrodynamic generators N73-19038 Characteristics of superconducting electric generators to show effect of electromechanical, electromagnetic, and cryogenic parameters on design N73-19039 Features and characteristics of superconducting electrical nachines and design of synchronous electric generator for airborne use N73-19010 SOPBBCOHDOCTIVITI Proceedings of conference on application of superconductivity techniques to auxiliary power systems for aircraft and missiles fAGABD-CP-1011] H73-19030 SOPEBCOHDOCTOBS characteristics of conventional alternators and aircraft electrical power systems and comparison with electric systems using superconductors 873-19036 SUPERSONIC AIBCEAFT Experimental method for analyzing the unsteady flow in a transonic aircraft compressor A73-22715 stiletto air-launched supersonic aerial target design, development and capabilities, describing confiquration, propulsion and control systems and operational envelope ; A73-23121 Low sonic boom overpressure profiles for supersonic transport aircraft configurations IKASA-TH-X-27U6] H73-18039 Experimental determination of high velocity liguid impact damage for application to rain erosion protection of supersonic aircraft [AD-753381] H73-18305 Development of electrical generation and distribution systems for supersonic aircraft using solid state switching and remote control of protective devices N73-19054 SOPEBSOBIC AIBFOILS Flowfield calculations for some supersonic sections with ducted heat addition. A73-23089 SOPEBSOHIC COBBOSTIOH Rixinq controlled supersonic combustion for air breathing engine equipped hypersonic aircraft, discussing chemical and fluid dynamic interaction effects A73-23862 SOPEBSOHIC COBBOSTIOH HAHJET EHGIHES Potentials and problems of hydrogen fueled supersonic and hypersonic aircraft. A73-22830 SOPEBSOBIC COBPBBSSOBS Performance tests on low hub-tip ratio supersonic axial flow compressor [AD-752585] ' H73-18805 SOPEBSOHIC OIFFOSBBS Turbulent pressure fluctuation measurements for cross section of supersonic diffuser inlet flow model N73-19288 SOPEBSOHIC FLOW One dimensional supersonic shock front location by sonic circle involute point by point plotting, using geometric considerations A73-23467 Supersonic aerodynamic influence coefficients for isolated and parallel interfering coplanar and noncoplanar wings tHASi-CR-2168] H73-18003 Application of optimal control theory to design of control system for supersonic inlet of turbojet engine CHASA-TH-D-7188] N73-18803 Error sources in pressure measurements on turbulent supersonic flows by nonstationary microphone H73-19629 SOPBBSOBIC IHIBTS Application of optimal control theory to design of control system for supersonic inlet of turbojet engine [KASA-TH-D-7188] H73-18803 Flow instabilities of supersonic variable ramp inlets at Bach 2 discussing Concorde aircraft intake [AHC-B/g-3711] N73-18999 Time variant distortion in supersonic inlet related to stall in compressor f»ASA-Ta-I-68189] H73-19825 SOPEBSOHIC HOZZIES Noise intensities of rectangular and circular supersonic nozzle geometries fNASA-CR-130964] N73-18704 SOPEBSOHIC SPEEDS Aeroelastic divergence of transport aircraft flying at supersonic speeds and design techniques to eliminate adverse effects CHASA-C8-112262] H73-18036 A-35 SOPPOBIS • SUBJECT XHDEX I Calculation 'of outer inviscid flow about rectangular vinq moving at supersonic speeds [N4SA-CB-130985] H73-18269 SOPPOEIS Kelson Tyler helicopter camera mount for aerial reconnaissance photography providing camera balance and notion stability under combat flight > conditions SUBVEILLAHCE BADAB Systems planning for improved airport surveillance radar equipment using dual airborne antenna switching for air traffic control CFAA-BD-72-136] N73-18176 SURVIVAL I Ballistic-tolerant helicopter flight control components from plastic composite materials. : 473-23964 SDEVIViL BQOIPBENT Human threats to air safety; Proceedings of the Twenty-fifth Annual International Air Safety Seminar, Washington, D.C., October 16-18, 1972. ( . 473-21707 Significant elements of an effective search, rescue, and survival system. 473-24712 STSTEB EFFECTIVENESS The role of the test pilot in evaluating auto landing systems. II. A73-22183 Significant elements of an effective search, rescue, and survival system. - : , A73-2U712 STSTEHS AHALS-SIS Manned vehicle systems analysis techniques application to manual approach-to-landiag phase of aircraft flight, developing analytical' control • model . , ; • . '• A73-24011 DH-1 helicopter test bed program for evaluation of automatic inspection, diagnosis, and prognostic • maintenance functions on selected subsystems - Vol. 1 tAD-752890] N73-18058 STSTEHS BNGIHBEBIIIS Fighter aircraft survivable flight control system design and fliqht test philosophy, present status and. trends, considering fly-by-wire and power-by-wire systems A73-22177 Microwave landing system /BIS/ with Doppler scanning technique for aircraft guidance precision improveoent over standard VHF/OHF ILS, detailing five-year development plan 473-23652 Short haul air travel with Intermodal Automated Transfer system 'for integrating ground transportation to allow passenger to stay in seat from origin to destination A73-23653 International Federation of 'Automatic Control, iorld Congress, 5th, Paris, France, June 12-17, 1972, Proceedings. Part 2 - Transportation, aeronautics and space, ship automation, and control components. Part 3 - Ecology and systems engineering: Large scale, sensitivity, • optimization and .adaptation theory. Part 4 - Education, feedback, regulators, linear and nonlinear systems: Identification, differential games, discrete and stochastic systems. - • A73-24001 Design principles of auxiliary power units of secondary power system for operation of aircraft equipment H73--19046 ' Desiqn and characteristics of auxiliary power source to operate electric, hydraulic, and pneumatic ''subsystems in ramjet powered aerospace vehicles ! I 1173-19048 T4CAB ! Doppler TACAN navigation system for helicopters obtaining data through computer display method A73-24475 Performance tests of various Tacan ground station modifications designed to minimize false distance measuring equipment indications' rFAA-NA-72-65] . - .1 H73-18664 TAKEOFF Analysis of internal flow conditions of inlet with centerbody retracted for short takeoff and landinq aircraft takeoff and approach operations f H4SA-TM-D-7185} • B73-18010 TAPE BECOBDBBS Russian book on multichannel maqnetic tape recorders in civil aviation 4TC for speech communication monitoring and preservation coverinq desiqn and operation principles A73-23245 TARGET ACQOISITIOB Air-to-ground tarqet acquisition with- flare ; . • .. illumination N73-19968 Application of night vision technology helicopter night scouts H73-19970 4erial targets for weapon .systems performance testing, discussing converted aircraft, pilotless drones and towed targets 473-23120 Stiletto air-launched supersonic aerial -target desiqn, development and capabilities, describing configuration, propulsion and control systems and operational envelope A73-23121 Tnrana drone system desiqn and development for . Australian .naval quns and guided weapons . exercises, describinq construction and operational details 473-23122 TECHNOLOGICAL FOBECASTIHG . . • Civil transport aircraft future desiqn trends, discussing subsonic, supersonic, hypersonic and V/STOL aircraft, engine design, fuels and -noise reduction A73-23682 Commercial air transportation projections, discussing mass transportation, international fare structure and exchange of riqhts, security and technoloqy A73-2I1646 TECHNOLOGY ASSESSBBHT Fighter aircraft survivable fliqht control system design and flight test philosophy, present status and trends, considering fly-by-wire and power-by-wire systems 473-22177 Radio navigation review, discussing Decca, Loran, Omega, VOE/DHE, satellite, inertial, integrated, area, approach and landing, collision avoidance and space navigation systems 473-23636 Aircraft noise reduction technology and certification standards, reviewing federal laws and regulations 473-24553 TELECOHSUHICATIOS - ' Independent radar systems using information processing, data correlation, and telecommunication N73-18179 TBHPEBATOBB HKASOBEHBNT Methods for measuring temperature in wind tunnels with electric contact thermometers rDLR-BITT-72-27] N73-18246 TEHPEB4TDRE SEHSOBS • 4irborne atmospheric temperature measurements correction for sensor response lag, deriving ' numerical scheme based on sensing systems wind tunnel calibration 473-23991 TENSILE TESTS Artificial slow crack growth under constant stress - The E-curv'e concept in plane stress. A73-23255 TEBBIHAL BALLISTICS Terminal ballistic performance of fiber glass epoxy composite material for aerodynamic control surfaces fAD-752918] N73-18584 4-36 SUBJECT IHDEI TBABSITIOB TBBBIHAL yiCILITIES Cost effectiveness of planned aviation system improvements, considering ATC automation vs terminal aids, noise control, ground facilities, capacity and enroute situation 473-28767 Analysis of airport operations to sho« importance to community, effect on environment, and application of new technologies for airport development 873-19625 Analysis of airport operations to show importance to community, effect on environment, and application of nev technologies for airport developaent N73-19625 TBBBIHAl GOIDiHCE ill-weather aircraft landing automation, discussing efficient optimal feedback control law selection based on trajectory termination or terminal control requirements 473-21(010 TEBBIHOL06Y Bemarks on the ISO international standards relating to 'Terms and Symbols for Flight Dynamics' A73-23657 TEST EQUIPBBBT Arava STOL turboprop passenger aircraft flutter flight test program, describing measurement instrumentation and data recording system A73-22185 Developments in aerodynamic test facilities to show past experience, present status, free flight techniques, and future plans [A6ABD-E-603] 873-18250 TESI FACILITIES Developments in aerodynamic test facilities to show past experience, present status, free flight techniques, and future plans CAGABD-B-603] K73-18250 Computer techniques and test facilities for structural engineering at German university institute [ISD-119] N73-18935 Analysis of selected problems in formation of simulation models of V/STOL aircraft S73-19009 TEST PILOTS 1972 report to the aerospace profession; Proceedings of the Sixteenth Symposium, Beverly Hills, Calif., September 28-30, 1972. A73-22176 Test pilots role in aircraft flying gualities evaluation, discussing spin and longitudinal stability testing 473-22181 The role of the test pilot in evaluating auto landing systems. I. 473-22182 The role of the test pilot in evaluating auto landing systems. II. 473-22183 XBTBEBIBG Theoretical and practical aspects of an automatic hover control system for an unmanned tethered rotorplatform. 173-21009 THBBBAL COBDOCTIVITI Thermal conductivity of mixed-composition plasma-sprayed coatings. 473-231(611 TBEBHAL COHTB01 C04TIBGS Thermal conductivity of mixed-composition plasma-sprayed coatings. 473-231(64 TBEBBAL BADIATIOB Unclear thermal vulnerability of honey comb sandwich radome panels [AD-753666] H73-18605 TBEHBAL STBBSSBS Thermal stresses in cooled gas turbine blade foils and roots with allowance for thermoelastic effects A73-22568 THBBHODTBARIC PBOPEBTIES Bode of thickening of a low morning convective layer in clear sky 473-23036 Development of neetod for analyzing performance of magnetohydrodynamic generator based on thermodynamic properties and flow characteristics H73-19051 THBBBOELASTICITT , Thermal stresses in cooled gas turbine blade foils and roots with allowance for thermoelastic effects / 473-22568 THEBBOBETEBS Bethods for measuring temperature in wind tunnels with electric contact thermometers [DLB-HITT-72-27] 873-1821(6 TBBEE DIBENSIOS4L FLOB Beasnrement of unsteady pressures developed on harmonically oscillating wing planform in three dimensional compressible flow CDLH-FB-72-55] 873-18007 Bethods for determining inviscid three dimensional flow about smooth shapes at supersonic speeds [AD-753695] • 873-19311 TBBUST Computer program for analyzing flow field generated near aircraft engine operating in reverse thrust [B4S4-CB-121147] . H73-1826II TBBDST HEASDBEBBBI A method of measuring the thrust, the polar; and • the performance of an aircraft on the basis of flight tests 473-2449l( THEOST BETEBSAL • - ' Development of empirical method for determining optimum reversing coefficient of thrust reversal of jet engines on passenger aircraft . [AD-752811(] . S73-18048 TIITIBG BOTOBS Rind tnnnel tests to determine effects of blade twist and aeroelasticity of rotary wings on tilt rotor performance from hover to Hach 0.7 speed [H4S4-TB-X-68948] • 873-19012 TIBE BESPOBSE Airborne atmospheric temperature measurements correction for sensor response lag, deriving numerical scheme based on sensing systems wind tunnel calibration A73-23991 TITABIDB ALLOTS Rot die forging /gatorizing/ technique .for Ti and heat resistant alloys jet engine parts, emphasizing material and cost savings 473-23295 TOBBD BODIES. Aerial targets for weapon systems performance testing, discussing converted aircraft, pilotless drones and towed targets A73-23120 Computerized simulation of aerodynamic characteristics for trailing wire system towed by orbiting aircraft [AD-753909] H73-19255 Computerized simulation of spiral curve of wire being towed behind orbiting aircraft tAD-753908] H73-19256 TBAIBIHG DEVICES Turana drone system design and development for Australian naval guns and guided weapons exercises, describing construction and operational details 473-23122 TBAJECTOBI BBASUBBHEBT Automative approach systems certification and short distance takeoff and landing> trajectography by cinetheodolites,.digital optical, airborne and inertial/radiosonde equipment 473-23656 TB4JECTOBY OPTIBIZATIOB flaximum range flight path daring climb with specified fuel supply and variable lift coefficient, solving differential eguations system by conjugate gradient procedure 473-2451(2 TBABSITIOB Bathematical model of transition flight and application to Do-31 aircraft • ; [BBTG-FBHT-72-30] - 873-19025 A-37 TBiHSBISSIOH LIBES SUBJECT IHDEZ TBIHSBISSIOH LINES Computerized simulation of longitudinal cable shapes during deployment from missile away from flying aircraft [AD-753907] N73-1925:. TBAHSOHIC COSPRBSSOBS Experimental method for analyzing the unsteady flow in a transonic aircraft compressor 473-22715 TSAHSONIC FLIGHT Aeromechanical measurements in free flight on piloted aircraft A73-224U7 IBAHSOHIC FLO! Calculation of the transonic flow around an airfoil, taking account of the exact Ian of compressibility A73-22210 Transonic airfoils - Becent developments in theory, experiment, and design. 173-23856 Analysis of aerodynamic noise generated by tips of helicopter rotary vings during acceleration to near sonic speed rAD-752301] H73-18072 Numerical solution to transonic airfoil problems fAD-7533903 N73-1830U IBANSOBIC SPEED Toward simpler prediction of transonic airfoil lift, drag, and aoment. A73-22U3* Transonic wind tunnel tests of tiro dimensional airfoil fitted with square and convex semicircular blunt bases to determine aerodynamic drag coefficients tAB1/A-MOTE-3361 H73-1899U TBAHSPOBT AIBCBAFT Slender delta-Kings for future subsonic passenger planes A73-21992 Russian book - Transport aircraft maintainability. A73-22375 Air cushion landing gears for transport aircraft, discussing peripheral jet stream performance prediction and system installation on Buffalo STOL A73-23659 Civil transport aircraft future design trends, discussing subsonic, supersonic, hypersonic and V/STOL aircraft, engine design, fuels and noise reduction ' A73-23682 Development of takeoff airworthiness standards for new aircraft designs using motion simulators to compare performance and handling characteristics rNASA-TN-D-7106] N73-18031 Aeroelastic divergence of transport aircraft flying at supersonic speeds and design techniques to eliminate adverse effects [HASA-CB-112262] H73-18036 Conceptual designs of V/STOL lift fan commercial short haul transport aircraft to determine technical and economic feasibility CHASA-CB-2183] H73-18038 Low sonic boom overpressure profiles for supersonic transport aircraft configurations rMASA-TH-X-2746] N73-18039 TBAHSPOBTATIOH Prediction models for surface and air transportation dynamic environments, considering broadband and single frequency continuous and recurrent and intermittent discrete excitation modes • A73-22718 TBEHDS Hot gas recirculation in Do-31 aircraft from scale model to aircraft and trends for future developments of V/STOL aircraft [BBVG-FBHT-72-29] N73-1902U TOBBIHE BLADES Prediction of aeroelastic instabilities in turbines A73-2220U Thermal stresses in cooled gas turbine blade foils and roots with allowance for therooelastic effects A73-22568 Gas turbine engine turbine blades service life increase by Cr and Al vacuum diffusion metallization, presenting full scale endurance test results : A73-21965 TOBBIHE BHGIHES Suppression of turbine engine inlet noise [AD-753000] H73-18806 Development of techniques for reducing exhaust emissions from turbine engines CNASA-TH-I-68192] ' N73-19821 TDBBIHE iHEELS ' Stress concentration and groove design as- factors in crack failure of low pover single stage gas turbine rotor disk, using optical polarization technique A73-22166 TDBBOCOBPBESSOBS Influence of regulated nnegual guide-vane spacing on the alternating stress level in the working blades of a compressor A73-22165 Graphoanalytic method of calculating plane potential flows A73-23106 Piston engine turbocharging system based on split low and high pressure exhaust gas discharge porting, discussing different turbine staging arrangements A73-21925 Existence and unigueness of solutions obtained from streamline curvature method of calculating flow through turbomachines for several operating points of Bolls-Boyce compressor CAEC-CP-123K] H73-18293 Development of supersonic cascade and wheel structure for axial flow compressor [AD-7525831 N73-1880* Development of algorithm for testing gas dynamic design of axial flow compressors with multiple stages (AD-753519J K73-18803 Influence of axial velocity density ratio on compressor cascade performance in compressible flow H73-19805 Bathematical model for prediction of axial compressor performance including effect of annulus wall boundary layers H73-19812 Shock wave boundary layer interaction in compressor cascades N73-19816 TOBBOFAH EHGIHES Analysis of requirements for turbofan engines for high speed commercial transport aircraft - Vol. 1 [HASA-CB-121132] N73-19820 Preliminary design assessment of turbofan engines for installation on high speed commercial transport aircraft - Vol. 2 [NASA-CB-121133] S73-19821 Propulsion system reguirements for aircraft engines installed in high speed commercial transport aircraft - Vol. 3 [NASA-CB-12113U] H73-19822 TCBBOGEHEBATORS Bam air turbines for aircraft emergency power supply, discussing design, performance and control A73-23525 TDBBOJET EHGIHES Engine cycle, configuration, and design requirements rNASA-CB-120970-VOL-2] H73-19019 Tine variant distortion in supersonic inlet related to stall in compressor CHASA-TB-X-68189] H73-19825 Development of sampling and analytical procedures for gas turbine engine exhaust using aircraft auxiliary power unit as emission source rBB-BI-7735] H73-19907 Effect of prevaporization of jet fuels on exhaust emission levels produced in turbojet combustor segment CHASA-TB-X-681911 H73-199H9 TOBBOBACBIHE BLADES Compressibility effects on unsteady forces generated by jet engine blade rows aerodynamic interference, considering potential flow and viscous wake interactions A73-23143 Flow through moving cascades of lifting lines with fluctuating lift. A73-23697 A-38 SUBJECT IHDEX ViBIiBlK GEOHBTHY STHDCTOEES TUBBOBACBIHEBY Secondary flows - Theory, experiment, and application in turbomachinery aerodynamics. ,.. . 173-23860 Boundary layer effects in turbomachines . tAGARD-lG-16«] 1173-19794 TDEBOPEOP AIECHiFT lrava-,STOL, turboprop passenger, aircraft flutter flight test program, describing measurement instrumentation and data recording "system 473-22185 TOBBOSHAPIS Influence of a change in the throughput of the pover turbine on^the parameters of a dual-shaft gas turbine engine A73-23599 TDBBDLEiCE EFFECTS Influence of degree of turbulence on aerodynamic coefficients of cascades H73-19798 TDEBOLEHT BODHDABY LAYEB Method for prediction of turbulent boundary layer flov in vaneless radial diffnser and experimental validation 373-19809 TOBBOLBHT FLOS Book - Annual review of fluid mechanics. Volume 5. A73-23851 Analysis of scaling parameters for flov in core region of vortex generated by rectangular ling tip and vortex generated by ogee ving tip fHASi-CB-21801 N73-18995 Error sources in pressure measurements on turbulent supersonic flows by nonstationary microphone K73-19629 TDBBULEHT MIXING Book - Annual review of fluid mechanics. Volume 5. A73-23851 10BBOLEBT RAKES Numerical analysis of inviscid, fully developed structure of lift-generated vortices behind aircraft wings and extension to arbitrary span-loaded distributions riiASi-TB-z-6222<>l B73-18289 Dependence of turbulent line vortices decay on Reynolds number [AO-753131] H73-18297 180 DIBESSIOHAL BODIES Technique for predicting shock envelopes and pressure distributions for two dimensional airfoil at angles of attack producing shock detachment and subsonic flov [SAS4-TN-D-7197] . H73-18001 Analysis of flow field around two dimensional airfoil of arbitrary shape CAD-753387] . H73-18320 TiO DIBEHSIOH4L FLOi Unsteady nonlinear flow around an airfoil or a blade cascade with emission of turbulent vortices A73-22212 Bayleigh-Ritz solution of boundary value problem for plane compressible subsonic flow past aerofoil noting convergence 473-22951* Graphoanalytic method of calculating plane potential flows : 473-23106 Flow through moving cascades of lifting lines with fluctuating lift. 473-23697 Transonic airfoils - Becent developments in theory, experiment, and design. 473-23856 Measurement of lift, drag, and pitching moments in wing section for range of flap deflections under two-dimensional flow conditions fAHC-CP-1233] U73-18018- Calculation of flow through airfoils in cascade to show pressure distribution under conditions of two dimensional incompressible flow with boundary layer separation at trailing edge CDLE-PB-72-62] '. H73-18276 Effect of two dimensional suction flows into double intakes on upper surface of Joukovski , ' airfoil for application to vertical takeoff and landing aircraft fAD-754208) H73-19003 u DH-1 HELICOPTEB Investigation of correlation between pilot disorientation and OH-1 helicopter accidents CAD-753208) . H73-18049 DH-1 helicopter test bed program for evaluation -of automatic inspection, diagnosis, and prognostic maintenance functions on selected subsystems - Vol. 1 [AD-752890] 1173-18058 Accomplishments during evaluation of automatic inspection, diagnostic, and prognostic maintenance system using TJH-1 helicopter as test bed - Vol. 2 [AD-7528911 . H73-18059 OSSTEJ.DY FLOS Unsteady nonlinear flow around an airfoil or a blade cascade with emission of turbulent vortices A73-22212 Experimental method for analyzing the unsteady flow in a transonic aircraft compressor A73-22715 Bydrodynamic visualization technique application to unsteady flov patterns around models and analysis of boundary layers, separation and wakes A73-2H8U2 ?/STOL AIBCBAFT Russian book on aviation fundamentals covering aerodynamics and flight theory, designs, components, engines and instrumentation of aircraft, including helicopters, VIOL and STOL A73-23224 . Dynamic and aeroelastic problems of stop-rotors of V/STOL aircraft occurring during retracting and stoving of rotary wings rDLB-FB-72-65-PT-1] H73-18027 Conceptual designs of V/STOI lift fan commercial short haul transport aircraft to determine technical and economic feasibility ISAS4-CB-2183] 1173-18038 Analysis of V/STOL aircraft design and operation to determine effects of noise problems and constraints with emphasis on helicopter performance [AD-752447] N73-18073 Analysis of aircraft instruments and display devices for approach control and landing of V/STOL aircraft [AGABD-AB-51] N73-18439 Analysis of selected problems in formation of simulation models of V/STOL aircraft H73r19009 Performance of typical V/STOL aircraft and comparison of data obtained with flight simulator against data obtained by actual flight tests -B73-19011 Concepts for achieving low noise levels for V/STOL aircraft tHASA-CB-120970-VOL-11 S73-19018 Engine cycle, configuration, and design reguirements [HASA-CB-120970-VOL-2J N73-19019 Preliminary aerodynamic and mechanical design of selected gas generators and lift unit for V/STOL aircraft TNASA-CB-120972] H73-19020 VACOUB DEPOSITIOH Gas turbine engine turbine blades service life increase by Cr and Al vacuum diffusion metallization, presenting foil scale endurance - test results 473-24965 VAHELESS DIFFUSEBS Method for prediction of turbulent boundary layer flow in vaneless radial diffnser and experimental validation H73-19809 VABIABLE GEOBETBt STBDCTUBES Dynamics of variable sveep wing aircraft in the course of changing geometry* 473-24012 4-39 VABIABLB SHEEP fIHGS SUBJECT IHDEX VARIABLE SWEEP iIHGS Dynamics of variable sweep wing aircraft in the course of changing geometry. -. 473-24012 VABIATIOBAL PBIBCIPLES Convergent iterative smoothing algorithm for aircraft stability parameter identification from measurement, using variational optimization procedure 473-22233 VELOCITY DISTBIBOTIOH Calculation of forces on stores in the vicinity of aircraft. A73-22433 Symmetrical airfoils optimized for small flap deflection. A73-24915 Jet deflection characteristics of jet-flapped airfoil vith Coanda deflection surfaces based on velocity distribution and flow angle , measurements for static operation [40-753618] N73-18074 VELOCITY BBASUBEHBBT Book - Annual review, of fluid mechanics. Volume 5. A73-2"3851 Flight test of instrument for determining low airspeeds to evaluate suitability for helicopter airspeed indicator CAD-7533U3] , N73-18071 Calculation of wind tunnel wall interference velocities affecting pitching moments of high lift wings , [NAS4-CB-2191 J . ,: N73-19269 Measurement of low airspeeds with ion beam produced in positive corona discharge based,^ on beas deflection properties • , iH73-19423 VERBAL COBBOBICATIOH Russian book on multichannel magnetic tape recorders in civil aviation 4TC for speech communication monitoring and preservation covering design and operation principles 473-23245 VEBTICAL AIB CDBBEHTS Node of thickening of a low morning convective layer in clear sky 473-23036 VEETICAL DISTBIBOIIOH A probabilistic evaluation of helicopter lift capability. 173-23775 VEBTICAL LAHDIBG Landing loads of Do-31 aircraft in vertical landing, noting undercarriage reactions and sinking speed [BBVG-FBBT-72-24] H73-18046 7EBIICAL TAKEOFF Ground erosion on grassland and concrete by vertical takeoff of Do-31 aircraft CBMVG-FBiT-72-26] B73-19023 VEBTICAL TAKEOFF AIBCB4FT Numerical analysis of aerodynamic characteristics of unsteady, two-dimensional, jet-flapped wing CAD-752928] N73-18051 Becirculation flow pattern in inlet of VTOL lift engine exhausting normally to ground CDLB-FB-72-50] H73-18798 Effect of two dimensional suction flows into double intakes on upper surface of Joukowski airfoil for application to vertical takeoff and landing aircraft tAD-754208] H73-19003 Mission analysis of VTOL passenger transport aircraft to determine optimum engine cycle for minimum direct operating cost tSASA-TB-I-681863 H73-19826 VHP OHHIBABGB BAVIGATIOH Development of systematic methodology and computer programs for optimal design of national grid of high altitude VBF omnirange navigation systems - Part 2 tFAA-BD-72-118-2-PT-2] B73-19644 VIBBATIOH DAHEIBG Prediction of aeroelastic instabilities in turbines 473-22204 Improving reliability and eliminating maintenance with elastomeric dampers for rotor systems. A73-23950 VIBBATIOH EFFECTS . . . .-. Analytic methods for calculating blade loads and shaft-transmitted.vibratory forces in stiff, bladed hinge,less rotors operating at various advance ratios - Vol. 1 [N4S4-CR-114562] , . , H73-18034 Descriptions, geometry, and technical data Jfof three rotary wing systems used in determining vibration and loads in hingeless rotary wings - Vol. 2 tNASA-CB-114568] N73-18035 VIBE4TIOS BEASBBE8BBT Descriptions, geometry, and technical .data for . ; three rotary wing systems used in determining vibration and loads in hingeless rotary wings - Vol. 2 f NiSA-CR-114568] ', N73-18035 Analysis "of airload and blade response of rotary wings to determine sources of rotor .vibratory „* f loads in level and maneuvering flight .of HH-3A and CH-53A helicopters fNAS4-CB-2225] ,. N73-18996 VIBBATIOH BODE Dynamic analysis of helicopter structures ,A73-22206 Extended natural mode method for calculating flapwise bending, edgewise bending, and,, torsional vibration modes and freguencies of helicopter rotor blades [DLB-FB-71-108] i . N73-18026 VIBBATIOSAL SPECTBA , , Extended natural mode method for calculating flapwise bending,, edgewise bending, .and torsional vibration modes and freguencies of helicopter rotor blades rni.H-FB-71-108] . N73-18026 VIBBATIOHAL STBSSS Influence of regulated unegual guide-vane spacing on the alternating stress level 'in the working blades of a compressor . - A73r22165 VISCOUS D4BPIHG , Improving reliability and eliminating maintenance with elastomeric dampers for rotor systems. 473-23950 VISCOUS FLOW Effect of axial velocity ratio on aerodynamic coefficients of compressor cascade in viscous flow N73-19804 VISUAL iCOITr Air-to-ground target acgnisition with flare illumination , - N73-19968 VISUAL AIDS , . • Visual systems for indicating approach slope ,during aircraft landing 473-22975 VISUAL FIELDS Improved visual capability for police helicopters ' N73-19984 VOBTEI BIHGS Vortice distribution field for calculating, inlet flow of ducted propeller CAD-75411UJ . H73-19318 VOBTEX SHEETS . , i- . . . ' Trailing vortex sheet roll-up behind finite aspect ratio wings for different loading conditions, discussing drag penalties for tip vortices strength improvements '473-23125 Numerical analysis of inviscid, fully developed structure of lift-generated vortices behind • • aircraft wings and extension to arbitrary span-loaded distributions rSAS4-TB-X-6222«l '. N73-18289 VOBTEX STBEETS , Dependence of turbulent line vortices decay on Beynolds number - [AD-753131] , K73-18297 VORTICES" Unsteady nonlinear flow around.an airfoil or a blade cascade with emission of turbulent vortices . , ... 473-22212 Secondary flows - Theory, experiment, and ' application in tnrbomachinery aerodynamics. 473-23860 4-1(0 SUBJECT IBDBI 1-22 AIBCRAFT Aircraft wake vortex avoidance systems vith current locus detection and/or prediction capability, discussing design based on hazard assessment and computer simulation for performance A73-2U557 Analysis of scaling parameters for flow in core . region of vortex generated b'y rectangular wing tip and vortex generated by ogee wing tip [NASA-CB-2180]" H73-18995 w iAEIIHG SISTERS Aircraft wake vortex avoidance systems with current locus detection and/or prediction capability, discussing design based on hazard assessment and computer simulation for performance ; ' A73-2U557 117E PBOP1G4TIOB Development' of model for analyzing propagation of weak normal shock.wave through turbulent atmosphere and application to sonic boom characteristics (me-12981] ' B73-18028 •BAB TESTS Emission'spectrographic analysis of used aero engine oil - A tool of maintenance. A73-232U2 BIBD TOH1BL BODE1S . ' . Rind tunnel tests to determine flow . characteristics of stalled two dimensional airfoil [HASA-CB-130919] N73-18020 Bind tunnel tests to determine acoustic properties of semispan wing with externally blown jet flap to include effects of flap size, vertical location and forward speed [HASA-TM-1-27091 H73-18041 Dynamic structural design of aeroelastic wind tunnel models using combinatorial flutter analyses N73-19291 BIHD TOHBE1 STABILITY TESTS Jet deflection characteristics of jet-flapped ' airfoil with Coanda deflection surfaces based on velocity distribution and.flow angle measurements for static operation ~~ fAD-753618] B73-18071I BIHD TOHHBI WALLS '* Calculation' of wind tunnel wall interference velocities affecting pitching moments of high lift wings [tlASA-CB-2191] '• N73-19269 BIBD TOBBELS Methods for measuring temperature in wind tunnels with electric contact thermometers [plB-HITT-72-27] ' • '- N73-18216 Cats acgnisition system for S-1 wind tunnel with continuous subsonic/supersonic flow (H8B-TB-78«(HB/D) 1 H73-182U8 Developments in aerodynamic test facilities to sliow past experience, present status, free flight technignes, and future plans [JGABD-B-603] . . . N73-18250 Procedure for developing aerodynamic parameters for use in flight simulator, research projects with emphasis on wind tunnel measurements '• N73-19008 BIBS FLAPS Measurement of lift, drag, and pitching moments in wing section for range of flap deflections under two-dimensional flow conditions t»BC-CP-1233] N73-18018 ilHG L0ADIBG Trailing vortex sheet roll-up behind finite aspect ratio wings for different "loading conditions, discussing drag penalties for tip vortices strength improvements A73-23125 RIRG PLABrOBBS Measurement of unsteady.pressures developed on harmonically oscillating wing planforn in three dimensional compressible flow fDLB-FB-72-55] ' N73-18007 Hind tunnel tests to determine flow • characteristics of stalled two dimensional airfoil (H4SA-CB-130919] ' N73-18020 Analysis of scaling parameters for flow in core region of vortex generated by rectangular wing tip and vortex generated by ogee wing tip rsASA-CB-2180] B73-18995 BUG PBOFILBS '• • Measurement of lift, drag, and pitching moments' in wing section for range of'flap deflections under two—dimensional flow conditions [ABC-CP-1233] ' H73-18018 Aerodynamic characteristics of flow around wing profiles tAD-752686] B73-18054 •IBG TIPS ' ; Analysis of scaling parameters for flow in core region of vortex generated by rectangular wing tip and vortex generated- by ogee wing tip • . [BASi-CB-21801 H73-18995 BIBGS Trailing vortex sheet roll-up behind finite aspect ratio wings for different loading conditions, discussing drag penalties for tip vortices strength improvements ' • ' A73-23125 Supersonic aerodynamic influence coefficients for isolated and parallel interfering coplanar' and noncoplanar wings f [NASA-CB-2168] . N73-18003 'Calculation of wind tunnel wall interference velocities affecting pitching moments of high lift wings ' [NASA-CB-2191] 1173-19269 BIBB ' Computerized simulation of aerodynamic ' characteristics for trailing wire system t'owed by orbiting aircraft [AD-753909] N73-19255 BOBKIBG FLUIDS ' ' Boundary'layer efficiency as working fluid in - ramjets for high aircraft speeds, obtaining i external efficiency as function of boundary ' layer parameters and flow rate A73-233"60 1-22 AIBCBAFT ' : > Development of criteria for predicting landing impact loads for T/STOL aircraft based on data obtained by flight tests of X-22 aircraft- ' [AD-753852] ' H73-18075 4-11 PERSONAL AUTHOR INDEX AERONAUTICAL ENGINEERING / A Special Bibliography (Suppl. 32) JUNE 1973 Typical Personal Author Index Listing BLAHA, B. jf] 1~[ PERSONAL AUTHOR ["plight and vlod tunnel investigation of the I effects of Beyaolds number on installed boattall j_ drag at subsonic speeds ,BASA-TH-X-66162, 11173-110071 TITLE I I REPORT NUMBER Listings in this index are arranged alphabetically by personal author. The title of the document provide? 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 first. AICBBB, ». Construction, scope and use of the test facilities at the ISO tISD-119] H73-18935 1LBEES, J. A. Theoretical and experimental internal flow characteristics of a 13.97-centimeter-diameter inlet at STOL takeoff and approach conditions fSASA-TH-D-7185] H73-18010 AHDEBSOB, J. L. Air-cushion tankers for Alaskan North slope oil [ HASA-TH-X-2683 ] H73-18981 APfi, K. Development and applications of supersonic unsteady consistent aerodynamics for interfering parallel vings [SASA-CB-21681 1173-18003 ABBUCKLE, B. S. Emission spectroqraphic analysis of used aero engine oil - A tool of maintenance. A73-23242 ABGIBIS. J. B. Construction, scope and use of the test facilities at the ISO riSD-119] N73-18935 ATA1LAH, S. Evaluation of auxiliary agents and systems for aircraft ground fire suppression, phase 1 tAD-7530691 H73-18256 ATHEBTOB, D. L. Lightweight superconduction magnet for airborne (IHD generators N73-19038 B BABOHIH, ». I. Influence of the.nonidentity of the antennas of a Doppler speed mpter on the accuracy of its operation A73-21386 BACH, B. B., JB. Aircraft parameter identification - A variational procedure. A73-22233 BAETB, J. Temperature measurements in wind tunnels [DLB-HITT-72-27J N73-18246 BAEV. B. S. Flow around wing profile with the presence of the surface of a system of sources and sinks fAD-752686] N73-1805H BAIHBBIDGE. A. Electrical generation and distribution systems for future supersonic aircraft U73-19054 BAIED, B. F. Becent developments in flight flatter testing in the United states. Supplement to the Manual on Aeroelasticity, volume 4, chapter 10 rAGABD-B-596] H73-18030 BAISLET, B. I. Helicopter visual aid system H73-1998I) BAKABOV, E. A. fundamentals of aviation A73-2322U BALSA, T. F. The prediction of axial compressor performance with emphasis on the effect of annnlns wall boundary layers S73-19812 BAHHETT, B. J. Optimal control of the F-8C in a fully automatic carrier approach [AD-7530101 H73-18052 BABLOR, 8. B. OH-6A phase 2 quiet helicopter program rAD-7536• . i • . ' A73-23659 BBYAH, F. T. . • A case for more qualitative flight testing. . A73-2218V BUCHABAB. E. :- Study of feasibility of solid-state electric- switch gear for aircraft and spacecraft [HASA-CB-1211101 . • N73-18223 BOLERO?, T. F. . Dynamics of variable sweep wiag aircraft in the course of changing geometry. ' . ' A73-2U012 BOEGHABT, J. B. • Application of four methods for approximating optimal feedback gains. •' • . . . A73-22234 BOBKE, B. F. •'• Air speed measurement with the ion beam of the positive corona discharge • • . , . , . . , N73-19U23 BDBBOiS, A. A. Optimization of maintenance manuals to minimize error. A73-24716 BOBBOBS, I. L. F-15 air superiority fighter briefing. : . A73-22178 Beport on the F-15 programme. I A73-22198 BOTCHES, B. B. OH-1 test bed program, volume 1 [AD-7528901 • N73-18058 OH-1 test bed program. Volume 2 [AD-752891] N73-18059 CALIE8DI, S. C. The designer's view of aircraft maintenance. , • A73-23759 CALOGEBAS. J. B.. Instantaneous distortion investigation [NASA-TH-X-68189] H73-19825 CABOB. B. F. Development of a high temperature fatigue sensor. A73-2250U CAHTBELL,'B. Experimental study of flow about a stalled two-dimensional airfoil [NASA-CH-1309191 N73-18020 CAPELL, B. A. Noise environments of control towers rAD-752535] ( N73-18262 CAEDEH, B. K. . - An analytical study of the response of a constant-attitude aircraft to atmospheric • turbulence t i fNASA-CH-22011 ' ; N73-18025 CABLSOH, B. G. ' ' Investigation of airfoil dynamic stall and its influence on helicopter control loads fAD-7529171 . i , H73-18053 CABBICBAEL, D. i An investigation of noise generation on a hovering rotor, part 2 [AD-753397] H73-18070 CABTA, F. O. . Investigation of airfoil dynamic stall and its influence on helicopter control loads [AD-752917] N73-18053 CASCI, C. . A method for preliminary analysis of HHD generator performance , . j • N73-19051 CASSBTTI, B. , . . : A method of measuring the thrust, the polar', and the performance of an aircraft on the basis of flight testsi • I • A73r2U491 CH4S, I. I. A simple model of shock cell noise generation and its reduction [SBC-12923] ' . H73-19666 I B-2 PERS08&L 10THOE IHDEX DODS, J. B., JE. CBAO, K. I. Calculation of the unsteady, pressure distributions 'on harmonically oscillating slender cruciform wing and cylindrical body combinations [DLB-FB-71-87;| 1173-18006 CHiSE, 1. A. Ballistic-tolerant helicopter flight control components from plastic composite materials. ' ' A73-23964 Feasibility evaluation of graphite/epoxy composite naterials to helicopter transmission housing. 173-23969 CHRISTEHSBH, J. V. Terminal-area STOL operating systems experiments program tNASA-TB-X-62235J ' ' N73-19013 CHBISIOPHE1, B. 6. . Flow field on the lee side of a delta wing CAD-753389] B73-18319 CBD, C. The calculation of three dimensional supersonic flows around spherically-capped smooth bodies and wings. Volume 1: Theory and application fAD-753695] N73-19311 CIEPLDCB, C. C. "' Jet aircraft engine noise reduction. A73-2155S CIVIHSKAS, K. C. ' < Preliminary study of an integral fan lift/cruise engine for a 100 passenger VIOL transport ' fKASA-TH-I-68186] N73-19826 CLABK, K. G. ' ' Preliminary design and cost study of recirculating chromate rinse system for aircraft corrosion control rAD-753214] 1173-18050 CLABK, S. K. A study of the dynamic tire properties over a range of tire constructions ftIASA-CH-2219] 1173-1801*2 CLABK, 8. B. • Recent developments in flight flutter testing in the United States. Supplement to the Banual' on ieroelasticity, volume 4, chapter 10 tAGARD-R-596] U73-18030 CLEBEBTS, B. B. The rolling up of a trailing vortex sheet. A73-23125 COGBE, A. A method for preliminary analysis of HHD generator performance S73-19051 COLES, D. Experimental study of flow about a stalled two'-dimensional airfoil CNASA-CH-1309191 H73-18020 COHHEBFOBD, G. L. - Investigation of airfoil dynamic stall and its influence on helicopter control loads fAD^7529171 H73-18053 COHLEY, B. f. ,' : - Development of ballistic-daoage-tolerant flight control components'molded of a short-fiber reinforced composite material. Phase 1 summary report: Composite material formation, . evaluation, and characterization fAD-752918] : N73-18584 COBBAD, B. i. I ' - Jet aircraft engine noise reduction. A73-21555 COOK, G. i •. • • Solving flight-path optimization problems'oh a. minicomputer. ... . ' .. A73-24542 COOK, I. L. 'A summary of wind tunnel research on tilt rotors from hover to cruise flight . : • • • tNASA-TB-X-68948] : . • • . • • < 1173-19012 COOPER, G . . ' • • ! • . . . . Initial flight and simulator evaluation of .a head up display for standard and noise abatement visual approaches •> i;iNASA-TB-lT62187] • N73-18021 COBHIGLIOH, J. Unsteady nonlinear flow around an airfoil or a blade cascade with emission of turbulent vortices A73-22212 COBSOB, B. S., JR. ' Cascade plug nozzle tNASA-CiSE-LAH-10951-1] H73-19819 COOLHY, G. Calculation of the transonic flow around an ' airfoil, taking account of the exact lav of compressibility • ' • ' ' A73-22210 CODBTEB, J. Application of solid state switching and multiplexing to aircraft electrical systems 1)73-19053 CBISI, S. A. ' ROCK-CABLE, a computer program to simulate • aircraft to 'missile cable dynamics CAD-753907] H73-19254 Dynamics of cables towed from aircraft ' • ' ' • • • CAD-753909] H73-19255 Steady state shape of orbiting trailing wire system fAD-753908] H73-19256 CBOHACK, D. E. • Calculation of inlet flows by means of a closed vorticity distribution applied to ducted ' propellers rAD-754114] N73-19318 CBOSSFIELD, A. S. Considerations for future approach operations. 1 A73-24768 CBDHP, G. B. Emission spectrographic analysis of used aero } engine oil - A tool of maintenance. • A73-23242 COLLT, D. C. ' Development of ballistic-damage-tolerant flight control components molded of a short-fiber • reinforced composite material. Phase 1 summary report: Composite material formation, evaluation, and characterization CAD-752918] ' N73-18584 COHDALL, B. B. Selling high cost capital equipment. A73-24650 DADATEV, S. S. . ; Condition of drift invariance of two-stage gyroscope with arbitrary gas-lubricated main ' • bearings to active accelerations 1 H73-19635 DANESBTAB, B. The off-design analysis of flow in axial compressors ' rAEC-CP-123U] N73-18293 DAHESHIAB, B. ' ' Prediction of annnlus wall boundary layers in 'axial flow turbomachines • N73-19813 DEFELICE, J. J. Active transmission isolation/rotor loads - measurement system [HASA-CH-1122lt5] 'H73-18024 DEHBIHGEB, 7. L. A method to compare the potential of a flowing liquid hydrocarbon to generate static electricity CAD-753386] ' ' • 1173-18706 DICK, P. . ; Ho't gas recircnlation in the VSTOL let transport aircraft Do 31 and its significance for future VSTOL developments [BHVG-FBBT-72-29] N73-19024 DICKSOH, D. H. Helicopter downwash applied to foq clearing: A status summary ' TAD-753357] • • H73-18661 DIETZLER, B. G. Knoxville associative processor evaluation ' fPX-6406-REV-A] N73-19642 DODGE, B. H. A study of the dynamic tire properties over a ' range of tire constructions fNASA-CR-22191 ' ' S73-18042 DODS, J. B., JB. Measurements of surface-pressure fluctuations on the XB-70 airplane at local Mack numbers up to 2.H5 CHASA-TH-D-72261 N73-18013 B-3 DBIHKIATEB, F. J., III PEBSOHAL iDTHOB IHDEI DBIHKgATEB, F. J., III Takeoff certification considerations for large subsonic and supersonic transport airplanes using the Ames flight simulator for advanced aircraft [NASA-TH-D-7106) N73-18031 DOGAB, J. F., JB. Preliminary study of supersonic-transport configurations with low values of sonic boom fHASA-TB-I-27461 N73-18039 DOHL, D. H. 'Advances in directional solidification spur usage in turbine airfoil shapes. A73-23293 DDLIBO, A. Calculation of the transonic flow around an airfoil, taking account of the exact law of compressibility A73-22210 BBEBLE, K. Construction, scope and use of the test facilities at the ISD [ISD-119] N73-18935 EDHISTOH, B. D. Evaluation of noise pollution level based upon community exposure and response data rNASA-CB-130920] N73-18978 EDBABDS, J. I. BLS - On the beam for '76. A73-23652 EICK. 8. K. Pulse let engine as a source of energy for auxiliary power units: Pulse gas turbine without compressor N73-190 Transportation safety-- Technology applications: A systems approach to anti-hilacking. 473-2*559 LEBEDEV, P. P.. . . Effectiveness of diffusion metallizing as a means of increasing the life of gas turbine blades. , A73-2*965 IECLERC, J. • • . • • I •' ' Prediction of aeroelastic instabilities in turbines . ;A73-22204 12111178, 1. A., 35. . ; Analysis of the flow field generated near an aircraft engine operating in reverse thrust CHASA-CB-1211K7] ^73-182611 LEE, B. H. 1C. A deterministic model of sonic boom propagation through a turbulent atmosphere [NBC-12981] , N73-18028 LEPIEVEE, C. Take-off and landing tra^ectoqraphy . ' '. A73-23656 1EHTIHEH, B. ; Analytical and experimental performance of optimal controller designs for a supersonic inlet fNASA-TlI-D-7188] . »;73-18803 LEBAHSKII. A. A. , Influence of the nonidentity of the antennas of a Doppler speed meter on the accuracy of its operation , , A73-2H386 LESSRABE, D. A. t . Manufactured-in-house or subcontracted - Finding the economic balance. A73-23521 LEVINS, D. C. . . . •. ,' STOL Arava - Flutter-free fliqht envelope. A73-22185 1EVT, E. ' '. \ • A probabilistic evaluation of helicopter lift ,. capability. . '. -473-23775 LEBIN, J. B. G. Besistant finishes. . j, , A73.-23522 LEWIS, T. L.. • i Heasurements of surface-pressure fluctuations on the IB-70 airplane at local Hach numbers up to 2.K5 [NASA-TS-D-7226] N73-18013 1ICHTE, H. ', ', Slender delta-wings for future subsonic passeicjer planes A73r21992 LIHAIE, D. B. • .- '• :.' A probabilistic evaluation of helicopter lift :, capability. • - ' • ! , A73T237.75 LIHDQDIST, O. H. .. . An investigation of airborne displays and controls for Search And Bescne (SAB). Volume 6: , kvionics req\iiieiiieTits for "the HH-53C' helicopter [AD-752625] . H73r18047 LIHHARES, A. B. . The DOT/NASA Civil Aviation Research and Development Policy Study. 473-2*552 LIVSHITS, S. P. Some control problems for centrifugal blowers t A73-2 . i- - A case of failure of gas-turbine-engine turbine disks A73-22166 SBEHSKI, D. t. i Advanced airborne auxiliary power system S73-19045 SBIK, B. Theoretical and practical.aspects of an autonatic hover .control system., for an unmanned .tethered rotorplatform. A73-2U009 SZOLLOSI, 6. D. . Automated design and optimization of flexible booster autopilots via linear programming. Volume 2: User's manual • [HASA-CB-121125] N73-19622 TAIHEB, H. • - L Influence of the trailing edge shape on the drag of a rectangular wing in the Bach number range-: from free stream Bach .5 to 2.2 i . - - rD!B-PB-71-85];r - H73-1800H TEBIAEy, E. D. Dynamics of variable sweep wing aircraft in the course of changing geometry. A73-21012 TBOMXSSOH, f.1, Solving flight-path optimization problems-on a minicomputer. . > . * t A73-2B5»2 THOBKi-GAZDIK, J. G. . : Co-existence,of scheduled and charter services in public air.transport. , A73-23123 THOHPSOS, I. J. Report of an experiment examining the air cushion concept in a logistical role in the arctic [AD-753527] S73-19027 TIDLEHEV, V. H. - Influence of regulated unequal guide-vane spacing on the alternating stress level in the working blades of a compressor A73-22165 TOLZTICH, I. Aircraft of the future A73-23682 TOILS, G. B. Analytical parametric investigation of low pressure ratio fan noise [NASA-CR-2188] H73-18011 TEIEBSTEIB, B. Unsteady pressure measurements on a harmonically oscillating wing model in three dimensional compressible flow fDIR-FB-72-55] . • H73-18C07 TBIBKAUS, I. Flight operations from the viewpoint of general aviation H73-19626 Flight operations from the viewpoint of general aviation H73-19626 TUCK, D. A.. Flight research to develop airworthiness standards for civil aircraft. A73-22181 TDCKEB, J. E. Aircraft parameter identification - A variational procedure. • A73-22233 TOSAKOV. i. P. Gas-dynamic verification calculation of axial flow multistage compressors on EDC [AD-753519] H73-18809 u OIDBRBOOD, B. B., JB. An analysis of the flow field around a 2-D body of arbitrary shape CAD-753387] H73-18320 OHTERHEIBER, K. B. Selected problems of sinnlation model function S73-19009 TAH iOKEH, B. L. Ballistic-tolerant helicopter flight control components from plastic composite materials. A73-2396H Feasibility evaluation of graphite/epoxy composite materials to helicopter transmission housing. A73-23969 TAB DYKE, H. Annual review of fluid mechanics. Volume 5. 473-23851 VIHCEHTI, ». G. Annual review of fluid mechanics. Volume 5. A73-23851 B-12 PEBSOHiL ADTHOE IHDEI ' ZBLLEB, J. B. VOGBL, J. B. Numerical calculation of flov fields about rectanqolar wings of finite thickness in sapersonic flow .. fHASA-CB-130985} '• • • H73-18269 VOOBDB, C. -B. 7. D. Heasured and calculated turbulent boundary layec flov in a vaneless radial diffuser : .N73-19809 w IADCOCK, i. Experimental study of flow about a stalled tHO-dinensional airfoil CNASA-CK-130919] R73-18020 IADDIBGXOH, D. Study of feasibility of solid-state electric svitcb gear for aircraft and spacecraft (BASA-CB-121140] H73-18223 BAGBEB. P. B. 'Design-and construction of a new cloud-particle replicator for use on a pressurized aircraft [AD-753091] ' - H73-18655 BiTKIIS, T. C. • '- OH-1 test bed program, volnme 1 rAD-752890] B73-18058 DH-1 test bed prograa. Volume 2 fAD-752891] H73-18059 BATSOB, D. Terminal-area STOL operating systems experiments proqram fBASA-TB-I-62235] - H73-19013 VATSOB, 1. 1. Fre-fab strain gage bridges. A73-22506 SATTS, G. A. Vibration and loads in hingeless rotors. Volnme 1: Theoretical analyses [HASA-CB-114562) N73-18034 Vibration and loads in hinqeless rotors. Volume 2: Experimental data [KAS4-CB-114568) H73-18035 BAYBB, J. E. , JB. Conceptual design studies of candidate V/STOL lift fan commercial short haul transport for 1980 - 1985 V/STOL lift fan study [NASA-CB-21831 H73-18038 BEBB, H. H. Study of V/STOL aircraft implementation. Volnme 1: Summary CNASA-CB-2227J H73-19017 BEETBAB, B. J. Calculation of inlet flows by means of a closed vorticity distribution applied to ducted propellers fAD-7541141 H73-19318 BEIHSTOCK, G. L. Aircraft initiation of lightning strikes. A73-24558 BEISSBAB, B. Criteria for predicting spin susceptibility of fighter-type aircraft fAD-753905] B73-19029 BELLS, T. 1. -.;. Development of a high temperature fatigue sensor. A73-22504 BELIE, D. Besults and knowledge gained in aerodynamic l^et interference from the VSTOL "let transport aircraft Do 31 and their application to future VSTOL developments tBBVG-FBWT-72-221 B73-18044 BEBLE, H. Hydrodynamic visualization of unsteady flows A73-24842 IKSTCOTT, V. C. Investigation of iron content of lubricating oil using a ferrograph and an emission spectrometer. A73-2«165 BESTEBBOEB, I. Electronic developments for high-performance glider flight. I A73-24916 BHITTEB, B. P. Community response to aircraft noise. A73-24562 BILHELB, W. E.. following theory with applications . N73-19259 WTLKIHSOB, I. E. . A design study for a simple-to-fly, constant attitude light aircraft • ' fBASA-CB-2208] - - B73-18037 BILLIAHS, H. 6. Deficient airfields - Still today's problem-child. • A73-21713 BILSOH, E. J. Development of a high temperature fatigue sensor. A73-22504 BIHGEBT, J. B. An investigation of airborne displays and controls for Search And Rescue (SAB). Voluae 6: Avionics requirements for the HH-53C helicopter [AD-752625J N73-18047 BIBS, A. L. Flight evaluation Elliott low-airspeed system [AD-753343] B73-18071 BITCOPSItl, B. 0. Potentials and problems of hydrogen fueled supersonic and hypersonic aircraft. A73-22830 BOLFFBAB, 0. Airports today: significance and problems of airports in todays air traffic N73-19625 Airports today: Significance and problems of airports in todays air traffic ' H73-19625 BOODSOB, B. H. Superconducting generators B73-19039 BOBTB1HH, F. X. Symmetrical airfoils optimized for small flap deflection. ^73-21915 BOTTOB, J. Pneumatics in supersonic energetics S73-19C56 BOEBBEHBEBG, H. VSTOL aircraft stability and control experienced froa methods and results of Do 31 flight tests tBHVG-FBBT-72-25} , H73-19022 BYBOSTEK, A. DU-1H AIDAPS test bed program, Volnme 1 CAD-752893] N73-18060 DH-1B AIDAPS test bed program. Volume 2 [AD-752891] N73-18061 YOSHIDA, A. Digital control of Jet engines. 1: Control system and preliminary experiments [SAL-TB-281] S73-18799 IODEHS, F. P. The Stiletto prelect. A73-23121 IODBG, J. HR-1B AIDAPS test bed proqram. Volume 1 [AD-752893] • N73-18060 DH-1H AIDAPS test bed proqram. Volume 2 [AD-7528941 H73-18C61 ZABIBSKT. J. H. Conceptual design studies of candidate V/STOL lift fan commercial short haul transport for 1980 - 1985 V/STOL lift fan study '• CBASA-CB-2183] N73-18038 ZAKHAB'EV, L. H. Influence of the nonidentity of the antennas of a Doppler speed meter on the accuracy of its- operation A73-24386 ZAVTALOV, G. A. Condition of drift invariance of two-stage gyroscope with arbitrary gas-lubricated main bearings to active accelerations B73-19635 ZELLEB, J. B. ' • • Analytical and experimental performance of optimal controller designs for a sapersonic inlet CBASA-TN-D-71881 ' N73-18803 B-13 ZEEEK, L. PSESOHAL ADTHOB IHDEX • ZEBEK, L. Helicopter main-rotor blade flatter in steady inclined flight A73-23662 ZHUKOVSKII, G. V. Computer calculation of the characteristics of multistage gas turbines A73-22567 ZBDBAYIEV. V. H. Flo* aroand viuq profile Kith the presence of the surface of a systei of sources and sinks fAD-752686] H73-1805II ZIHEHKO, Id. V. ' 4ir-traffic-control magnetic tape recorders in civil aviation &73-232U5 ZDCKEEdiE, A. J. ! A solid state converter for measurement of aircraft noise and sonic boom fSSSA-CB-112260] N73-18019 B-11 CONTRACT NUMBER INDEX AERONAUTICAL ENGINEERING / A Special Bibliography (Suppl. 32) Typical Contract Number Index Listing JUNE 1973 |BAS3-12430| i — 1 |H73-11799| 1 ^ - .1 -, • CONTRACT • NASA ACCESSION NUMBER . NUMBER Jstings in this index are -arranged alphanumerically by contract number. Under each contract number, the accession numbers denoting documents hat have been produced as a result of research done under that contract . are arranged in ascending order with the IAA accession numbers appearing irst. The accession number denotes the number by which the citation is demified in either the IAA or STAR section. i IF PHOJ. HBF-133 DOT-FA69WA-2066 N73-18262 \f PEOJ. 1366 B73-19311 IF PEOJ. 3048 N73-18975 IF PBOJ. 3066 N73-18975 IF PBOJ. 7061 1173-19003 it PEOJ. 7065 N73-18804 N73-18805 IF PBOJ. 9783 N73-18297 1F-AFOSB-2092-71 N73-18297 iF-AFOSB-2104-71 B73-18804 H73-18805 IBPA OBDEB 1321 N73-18077 IBPA OBDEB 1615 H73-19026 )A PBOJ. 1F1-62203-A-150 N73-18581 5A PBOJ. 1F1-62204-A-139 M73-18053 )A PBOJ. 1F1-64204-DC-32 H73-18058 H73-18060 1173-18061 )A PHOJ. 1TO-61102-B-53A H73-18661 >A-AHO(D)-31-124-G13 B73-18051 >AAB07-68-C-0084 S73-19651 )AAH01-72-C-0375 S73-18305 JAAJ01-70-C-0827 H73-18060 B73-18061 )AAJ01-70-C-0828 M73-18058 H73-18059 1AAJ01-71-C-0503 H73-18062 N73-18063 N73-18061I S73-18065 N73-18066 N73-18067 1173-18068 1173-18069 AAJ02-69-C-0078 1173-18077 AAJ02-70-C-0062 N73-1858K AAJ02-71-C-0003 1173-18053 ABC01-69-C-0086 S73-18073 ABC04-69-C-0087 N73-18070 N73-19645 DOT-FA70WA-2289 N73-196142 DOT-FA70HA-2188 H73-19616 DOT-FA71WA-25U7 N73-19613 S73-196it4 DOT-FA72NAI-2112 N73-18176 DOT-FA72BAI-261 N73-18173 DOT-TSC-1t2 N73-1870U FAA PBOJ. 031-211-012 B73-18173 FAA PBOJ. 011-306-051 S73-18664 FID PBOJ. T70-01-12 H73-18051 F19628-70-C-0230 H73-18176 F19628-70-C-0279 K73-18655 F19628-72-C-0108 H73-18055 V19628-73-C-0002 H73-18173 F33615-70-C-1120 A73-21617 F33615-71-C-1581 A73-21558 F33615-71-C-1591 N73-19010 F33615-72-C-1129 S73-19311 F33657-72-C-0122 M73-18256 BF5152U005 H73-18049 HASU-2301 »73- 18978 NAS»-2182 N73-19014 NAS1-2538 N73-19697 NAS1-9603 B73-18025 HAS1-10116 H73-18995 NAS1-10880 H73-18003 MAS1-10896 S73-18011 HAS1-10900 H73-18036 NAS1-10917 H73-19016 HAS1-10992 H73-18022 NAS1-11019 H73-18996 NAS1-11519 H73-18021 HAS2-5168 B73-180311 1173-18035 KAS2-5962 A73-24011 NAS2-6U73 H73-19017 HAS2-6563 N73- 18038 NAS3-11106 1173-19020 NAS3-11108 1173-19018 H73-19019 NAS3-15572 K73-19820 N73-19821 N73-19822 »AS3-1582t (173-18223 NAS1-1796 A73-22501 HAS8-28182 N73-19621 1173-19622 HGL-05-002-229 873-18020 HG1-22-009-383 H73-18701 HGL-23-005-010 H73-18012 SGL-39-009-007 . A73-23860 HGL-18-002-010 •; . .1173-19269 HGB-16-002-029 N73-18269 HGB-33-016-131 A73-23862 HGB-34-002-086 H73-18037 HGB-36-028-004 N73-18019 NGB-13-002-031 H73-18264 BB PBOJ. 200-016 B73-19318 BH PBOJ. 213-072 1173-18047 HSF 6A-28190X1 A73-23991 B00014-68-A-0116 S73-19318 B00011-69-C-C406 K73-18047 B00011-72-C-0278 473-21165 B00019-71-C-0041 N73T18075 B62474-72-C-0344 1173-19028 RFF-4019 H73-18935 SB PBOJ. 271-168 873-18057 SB-271 B73-18057 SHI PBOJ. 1096 1173-19643 N73-19614 TSACOB PBOJ. 076-166 N73-18978 ZFXI412 H73-18164 117-07-02-01-00-21 1173-18001 126-62-10-04-00-21 H73-18031 132-15 S73-18039 501-22-04-01 H73-18003 501-24 B73-18010 H73-18012 873-18082 B73-18803 S73-18960 S73-18981 501-24-12-00- 2t H73-18013 501-38 K73-18010 501-38-12-02 K73-18042 736-05-10-02 K73-18025 760-61-02-81-23 S7 3-19269 760-71-03-01 1173-18037 760-72-01-05-00-21 H73-18041 863-11-00-01 H73-19697

Aeronautical Engineering: A special bibliography with indexes, supplement 32, June 1973

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