NASA SP-7037 (80) AERONAUTICAL ENGINEERING CASE FILE COPY A SPECIAL BIBLIOGRAPHY WITH INDEXES Supplement 80 F E B R U A R Y 1977 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION https://ntrs.nasa.gov/search.jsp?R=19770012047 2020-03-22T11:43:21+00:00Z ACCESSION NUMBER RANGES Accession numbers cited in this Supplement fall within the following ranges: STAR(N-10000 Series) N77-10001—N77-11966 IAA (A-10000 Series) A77-10001 -A77-12945 This bibliography was prepared by the NASA Scientific and Technical Information Facility operated for the National Aeronautics and Space Administration by Informatics Information Systems Company. NASA S P - 7 0 3 7 ( 8 0 ) AERONAUTICAL ENGINEERING A Special Bibliography Supp lement 80 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 January 1 977 in • Scientific and Technical Aerospace Reports (STAR) • International Aerospace Abstracts (IAA) Scientific and Technical Information Office FEBRUARY 1977 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION Washington, D.C. This Supplement is available from the National Technical Information Service (NTIS). Springfield, Virginia 22161, at the price code E02 ($475 domestic. $9 50 foreign) INTRODUCTION Under the terms of an interagency agreement with the Federal Aviation Administration this publication has been prepared by the National Aeronautics and Space Administration 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 t ime, m o n t h l y supplements have been issued This supplement to Aeronautical Engineering -- A Special Bibliography (NASA SP-7037) lists 277 reports, journal articles, and other documents originally announced in January 1977 m Scientific and Technical Aerospace Reports (STAR) or in International Aerospace Abstracts (IA 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 aeronautical 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, in that order. The citations, and abstracts when available, are reproduced exactly as they appeared originally in IA A and 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 AVAILABILITY OF CITED PUBLICATIONS IAA ENTRIES (A77-10000 Series) 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 50 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 pojtage to foreign countries is $1 00 Please refer to the accession number eg (A77-10026) when requesting publications STAR ENTRIES (N77-10000 Series) One or more sources from which a document announced in STAR is available to the public is ordinarily given on the last line of the citation The most commonly indicated sources and their acronyms or abbreviations are listed below If the publication is available from a source other than those listed the publisher and his address will be displayed on the availability line or in combination with the corporate source line Avail NTIS Sold by the National Technical Information Service Prices for hard copy (HC) and microfiche (MF) are indicated by a price code followed by the letters HC or MF in the STAR citation Price codes are given in the tables on page vn of the current issue of STAR Microfiche'" is available regardless of age for those accessions followed by a # symbol Initially distributed microfiche under the NTIS SRIM (Selected Research in Microfiche) is available at greatly reduced unit prices For this service and for information concerning subscription to NASA printed reports, consult the NTIS Subscription Unit NOTE ON ORDERING DOCUMENTS When ordering NASA publications (those followed by the * symbol) use the N accession number NASA patenB applications (only the specifications are offered) should be ordered by the U S-Patent-Appl-SN number Non-NASA publications (no astenck) should be ordered by the AD, PB, or other report number shown on the last line of the citation, not by the N accession number It is also advisable to cite the title and other bibliographic identification Avail SOD (or GPO) Sold by the Superintendent of Documents U S Government Printing Office, in hard copy The current price and order number are given following the availability line (NTIS will fill microfiche requests, at the standard $300 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 SW, Washington, DC 20546, or public document rooms located at each of the NASA research centers, the NASA Space Technology Laboratories, and the NASA Pasadena Off ice at the Jet Propulsion Laboratory ID A microfiche is a transparent sheet of film 105 by 148 mm in size containing as many as 60 to 98 pages of information reduced to micro images Inot to exceed 26 1 reduction) Avail ERDA Depository Libraries Organizations in U S cities and abroad that maintain collections of Energy Research and Development Administration reports, usually in microfiche form, are listed in Nuclear Science Abstracts Services available from the ERDA and its depositories are described in a booklet. Science Information Available from the Energy Research and Development Administration (TID-4550). which may be obtained without charge from the ERDA 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) and microfilm All requests should cite the author and the Order Number as they appear m the citation Avail USGS Originals of many reports from the U S Geological Survey, which may contain color illustrations, or otherwise may not have the quality of illustrations preserved in the microfiche or facsimile reproduction, may be examined by the public at the libraries of the USGS field offices whose addresses are listed in this introduction The libraries may be queried concerning the availability of specific documents and the possible utilization of local copying services, such as color reproduction 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 and mailing charge) is given, or a conversion table may be obtained from PHI Avail BLL (formerly NIL) British Library Lending Division, Boston Spa. Wetherby. Yorkshire, England Photocopies available from this organization at the price shown (If none is given, inquiry should be addressed to the BLL) Avail ZLDI Sold by the Zentralstelle fur Luftfahrtdokumentation und -Information, Munich, Federal Republic of Germany, at the price shown in deutschmarks (DM) Avail Isbuing 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 cents 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 bibliography 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 is $45 00 domestic. $75 00 foreign All questions relating to the subscriptions should be referred to NTtS. Ann Subscrip- tions, 5285 Port Royal Road, Springfield Virginia 22161 VI ADDRESSES OF ORGANIZATIONS American Institute of Aeronautics and Astronautics Technical Information Service 750 Third Ave New York. NY 10017 British Library Lending Division. Boston Spa. Wetherby. Yorkshire. England Commissioner of Patents U S Patent Office Washington. D C 20231 Pendragon House. Inc 899 Broadway Avenue Redwood City. California 94063 Superintendent of Documents U S Government Printing Office Washington. D C 20402 University Microfilms A Xerox Company 300 North Zeeb Road Ann Arbor. Michigan 48106 Energy Research and Development Administration Technical Information Center P 0 Box 62 Oak Ridge. Tennessee 37830 ESA-Space Documentation Service ESRIN Via Galileo Galilei 00044 Frascati (Rome) Italy Her Majesty's Stationery Office P 0 Box 569. S E 1 London. England University Microfilms, Ltd Tylers Green London, England U S. Geological Survey 1033 General Services Administration Building Washington, D C 20242 U S Geological Survey 601 E Cedar Avenue Flagstaff. Arizona 86002 NASA Scientific and Technical Information Facility P 0 Box 8757 B W I Airport. Maryland 21240 National Aeronautics and Space Administration Scientific and Technical Information Office (KSI) Washington, D C 20546 National Technical Information Service 5285 Port Royal Road Springfield. Virginia 22161 U S Geological Survey 345 Middlefield Road Menlo Park, California 94025 U S Geological Survey Bldg 25. Denver Federal Center Denver, Colorado 80225 Zentralstelle fur Luftfahrtdoku- mentation und -Information 8 Munchen 86 Postfach 880 Federal Republic of Germany TABLE OF CONTENTS IAA Entries 1 STAR Entries 17 Subject Index A-1 Personal Author Index B-1 Contract Number Index C-1 TYPICAL CITATION AND ABSTRACT FROM STAR NASA SPONSORED DOCUMENT NASA ACCESSION NUMBER TITLE. AUTHORS. CONTRACT OR GRANT. REPORT NUMBERS. tt N77-10O48*# Lockheed Missiles and Space Co. Sunnyvale. •«- Calif Research and Development Div CIVIL USES OF REMOTELY PILOTED AIRCRAFT Summary Report Jon R Aderhold. G Gordon, and George W Scon Jul 1976 •*• 28 p refF -». (Contract NAS2-893S) ^.(NASA-CR-137895. LMSC-D057322) HC A03/MF A01 CSCL 01C -«- Avail NTIS- The economic, technical, and environmental implications of remotely piloted vehicles (RVP) are examined The time frame is 1980-85 Representative uses are selected, detailed functional and performance requirements are derived for RPV systems, and conceptual system designs are devised Total system cost comparisons are made with non-RPV alternatives The potential market demand for RPV systems is estimated Environmental and safety requirements are examined, and legal and regulatory concerns are identified A potential demand for 2,000-11.000 RVP systems is estimated Typical cost savings of 25 to 35% compared to non-RPV alternatives are determined There appear to be no environmental problems, and the safety issue appears manageable Author .AVAILABLE ON MICROFICHE —CORPORATE SOURCE .PUBLICATION DATE .AVAILABILITY SOURCE . COSATI CODE TYPICAL CITATION AND ABSTRACT FROM IAA NASA SPONSORED. AIAA ACCESSION I NUMBER ' TITLE. PUBLICATION PATE f t A77-10214 * # Resizing procedure for structures under com- f-*- bined mechanical and thermal loading. H M AdelmarTTNASA, Langley Research Center, Hampton, Va.) and R Narayanaswami (Old Dominion University, Norfolk, Va ). AIAA Journal, vol 14. ,*.()« 1976, p 1484-1486 6 refs E " The fully-stressed design (FSO) appears to be the most widely used approach for sizing of flight structures under strength and minimum-gage constraints Almost all of the experience with FSD has been with structures primarily under mechanical loading as opposed to thermal loading In this method the structural sizes are iterated with the step size, depending on the ratio of the total stress to the allowable stress In this paper, the thermal fully-stressed design (TFSD) procedure developed for problems involving substantial thermal stress is extended to biaxial stress members using a Von Mises failure criterion The TFSD resizing procedure for uniaxial stress is restated and the new procedure for biaxial stress members is developed Results are presented for an application of the two procedures to size a simplified wing structure S D • AVAILABLE ON MICROFICHE -AUTHORS AUTHOR'S AFFILIATION AERONAUTICAL ENGINEERING A Special Bibliography (Suppl. 80) FEBRUARY 1977 IAA ENTRIES A77-10026 Centrifugal compressor and pump stability, stall and surge. Proceedings of the Conference, New Orleans, La , March 22-25, 1976 Conference sponsored by the American Society of Mechanical Engineers Edited by P C Tramm (General Motors Corp , Indianapolis, Ind ) and R C Dean. Jr (Creare, Inc , Hanover, N H ) New York, American Society of Mechanical Engineers, 1976 211 p $20 Papers are presented on the control of surge in dynamic centrifugal compressors using close coupled resistances, controls for high energy centrifugal pumps to prevent pulsation and cavitation erosion, the time domain of centrifugal compressor and pump stability and surge, and the effect of rotor blade wakes on centrifugal compressor diffuser performance Also considered are asymmetric flow in vaneless diffusers of centrifugal blowers, the effect of inlet flow conditions and geometries of centrifugal vaneless diffusers on critical flow angle for reverse flow, and a cascade analogy of vaned diffuser influence on centrifugal compressor stability Individual items are announced in this issue B J A77-1003^ The effect of rotor blade wakes on centrifugal compressor diffuser performance - A comparative experiment S Baghdadi (General Motors Corp, Detroit Diesel Allison Div , Indianapolis, Ind ) In Centrifugal compressor and pump stability, stall and surge. Proceedings of the Conference, New Orleans, La , March 2225, 1976 New York, American So- ciety of Mechanical Engineers, 1976, p 121-138 5 refs A vortex nozzle facility for testing radial vaned diffusers independently of any rotor has been developed (Baghdadi and McDonald, 1975 and Baghdadi, 1973) This paper describes a comparative experiment designed to evaluate the applicability of results obtained on this facility to actual rotating compressors Geometrically scaled diffusers were tested in the vortex nozzle facility and in an actual rotating compressor rig, and the results are compared and shown to be very similar in terms of both performance and stability limits The implications of these results are that rotor blade wake mixing and unsteadiness do not significantly affect diffuser performance (Author) A77-10036 Experimental investigation of the near-surge flow in a high performance centrifugal compressor R Sovrano and P Avram (ONERA, Chatillon-sous-Bagneux, Hauts-de-Seme, France) In Centrifugal compressor and pump stability, stall and surge, Proceedings of the Conference, New Orleans, La , March 22-25, 1976 New York, American Society of Mechani- cal Engineers, 1976, p 179202 16 refs By using several measuring means (Schlieren visualization technique, fluctuating pressure transducers and wall pressure taps), the experimental study of near surge flow in a high pressure ratio centrifugal compressor is conducted in order to emphasize the fundamental influence of the diffuser on this phenomenon The diffuser being choked, the shock wave system in the throat region 'seems mainly responsible for the surge onset, while in the opposite case (diffuser unchoked) the inlet flow incidence effect determines critically the compressor surge For studying this very important {parameter two rotation speeds were used (8,000 and 9,500 rpm in a freon set-up), corresponding to inlet relative Mach numbers at the inducer tip equal to 1 08 and 1 27 respectively (Author) A77-10197 The influence of vortex shedding' on the generation of sound by convected turbulence M S Howe (Cam- bridge University, Cambridge, England) Journal of Fluid Mechanics, vol 76, Aug 25, 1976, p 711-740 44 refs Res'earch supported by Rolls-Royce (1971), Ltd This paper discusses the theory of the generation of sound which occurs when a frozen turbulent eddy is convected in a mean flow past an airfoil or a semnnfmite plate, with and without the application of a Kutta condition and with and without the presence of a mean vortex sheet in the wake A sequence of two-dimensional mathematical problems involving a prototype eddy in the form of a line vortex is examined To the order of approximation to which the sound from convected turbulence near a scattering body is usually estimated, the imposition of a Kutta condition at the trailing edge leads to a complete cancellation of the sound generated when frozen turbufence convects past a semnnfmite plate, and to the cancellation of the diffraction field produced by the trailing edge in the case of an airfoil of compact chord (Author) A77-10200 h Concorde navigation B J CalvertandT C R Guest {International Association of Institutes of Navigation, Inter- national Congress, Boston, Mass., Aug 2-6, 1976) Journal of Navigation, vol 29, Oct 1976, p 358-363 Problems peculiar to Concorde navigation practice are em- phasized These include special constraints dictated by considerations of fuel conservation and optimum fuel utilization (and shifting of center of gravity fore and aft by fuel transfer in flight), avoiding overflight of highly populated areas and particularly fccusmg of supersonic booms near such areas, and penalties in range and payload Exact definition of waypomts selected for acceleration and deceleration, automated navigation functions required to alleviate the crew workload for concentration on other tasks, in flight systems updating, and great-circle calculations at supersonic cruise altitudes are also mentioned R D V A77-10207 K Application of optimahty criteria to auto- mated structural design M W Dobbs and R B Nelson (California, University, Los Angeles, Calif) AIAA Journal, vol 14, Oct 1976, p 1436-1443 15 refs Grant No AF AFOSR-74-2460A This paper presents a recursive design method for the minimum weight design of linear elastic redundant structures subject to A77-10208 multiple independent static loading conditions and with behavioral constraints on allowable element stresses and nodal displacements and constraints on design variables This recursive method is based on the Kuhn-Tucker necessary conditions for a local optimum and gives, upon completion, a local optimum design An iterative procedure is used to resize the structure until a design satisfying the Kuhn Tucker necessary conditions is obtained For resizing, it is necessary to identify the current near-active (critical) constraints and to use this data to construct the Kuhn-Tucker test If the current design is not converged, then the information from the test is used to resize the design variables and improve the design Each iteration or redesign requires only the solution of a set of linear algebraic equations equal in number to the number of currently active constraints The method is used to design several well known truss-type structures, and the results are shown to compare favorably with p-evious results obtained using mathematical programing algorithms and other optimality criteria methods (Author) A77-10208 ff Experimental investigation of the boundary layer on a rotating cylinder J B Morton, I D Jacobson, and S Saunders (Virginia, University, Charlottesville, Va ) AIAA Journal. vol 14, Oct 1976, p 1458-1463 10refs Grant No DAAD05-72-C- 0131 • This paper documents the experimental analyses done in determining the stability, transition, and growth of boundary layers on a spinning cylinder at angle of attack It has been shown that spin alters the boundary-layer growth as well as skewing and moving forward the transition line These effects can have a significant influence on the thickness distribution of the boundary layer (Author) A77-10251 Approximate transonic profile flow with shock R Mitra (Lady Brabourne College, Calcutta, India) Acta Mechanics, vol 25, no 1-2, 1976, p 1-12 ISrefs The present work gives a procedure for computing approximate- ly steady mviscid transonic profile flow with shock Using an analysis similar to that adopted by Hosokawa (1960), it extends the shock-free transonic solution of Niyogi and Mitra (1973) to the case of flow with shock Supercritical flow past parabolic arc profiles and a NACA profile are computed and compared with theoretical results of Oswatitsch and Zierep and finite difference solution of Murman and Cole (1971) and with experimental results The agreements are satisfactory (Author) A77-10336 * Optimal ride control for the Twin Otter, STOL aircraft W E Holley (Oregon State University, Corvallis, Ore ) In Annual Asilomar Conference on Circuits, Systems, and Computers, 9th, Pacific Grove, Calif, November 3-5, 1975, Con- ference Record North Hollywood, Calif, Western Periodicals Co , 1976, p 585-590 5 refs Research sup- ported by the Oregon State University, Grant No NCA-OY586 501 An aircraft with low wing loading, such as the deHavilland, Twin Otter, exhibits a relatively large acceleration sensitivity to wind gusts These undesirable aircraft motions can be reduced using an auto- matic ride control system In this paper, the techniques of quadratic optimal control theory are utilized to investigate the capabilities of such a ride control system The effects of the wind gusts on the aircraft can be modeled by a vector stochastic process containing seven states The impact of this disturbance model on the optimal control system structure is assessed and comparison is made to a system without gust feedback (Author) A77-10214 * ff Resizing procedure for structures under com- bined mechanical and thermal loading H M Adelman (NASA, Langley Research Center, Hampton, Va ) and R Narayanaswami (Old Dominion University, Norfolk, Va ) AIAA Journal, vol 14, Oct 1976, p 1484-1486 6 refs The fully-stressed design (FSD) appears to be the most widely used approach for sizing of flight structures under strength and minimum-gage constraints Almost all of the experience with FSD has been with structures primarily under mechanical loading as opposed to thermal loading In this method the structural sizes are iterated with the step size, depending on the ratio of the total stress to the allowable stress In this paper, the thermal fully-stressed design (TFSD) procedure developed for problems involving substantial thermal stress is extended to biaxial stress members using a Von Mises failure criterion The TFSD resizing procedure for uniaxial stress is restated and the new procedure for biaxial stress members is developed Results are presented for an application of the two procedures to size a simplified wing structure S D A77 10218 § Amsotropic radiatively coupled wedge flow J B Elgin and J R Baron (MIT, Cambridge, Mass) AIAA Journal, vol 14, Oct 1976, p 1492-1494 7 refs Contract No F44620-75-C-0040 Geometrically thin shock layers are advantageous in reducing the radiation heat transfer to a high-speed body Since elongated shock layers imply anisotropic radiation fields, the differential Milne-Eddington approximation used by Gibelmg and Baron (1973) for minimum radiative transfer geometries is somewhat questionable for anisotropic shock layers The utility of ellipsoidal modeling for both anisotropic and coupled fields is assessed Attention is focused on an application of the'concept to a radiatively coupled wedge flow A realistic basis is provided for examining the adequacy of the differential approximation for shock layers It is shown that even in instances of overall insignificant reabsorption, ellipsoidal modeling is of some importance to the distributed absorption influence S D A77-10338 Eigenvalue/eigenvector control via spectral characterization - An application to helicopter hover dynamics S Srmathkumar and R P Rhoten (Oklahoma State University, Stillwater, Okla) In Annual Asilomar Conference on Circuits, Systems, and Computers, 9th, Pacific Grove, Calif, November 3-5, 1975, Conference Record North Hollywood, Calif , Western Periodicals Co , 1976, p 605-609 A linear state feedback gam selection procedure which allows arbitrary choice of eigenvalues and certain eigenvector entries and thus provides direct control of closed loop responses is described The technique is illustrated by synthesizing a hover controller for a ninth order model of the SH-3D helicopter, with emphasis on stabilization and mode decoupling B J A77-10347 A note on the acoustic effect of non- uniformly distributed stator rows P E Duncan (Central London, Polytechnic, London, England) Journal of Sound and Vibration, vol 48, Oct 8, 1976, p 441 444 Science Research Council Grant No B/RG/85125 A technique for reducing tonal radiation from axial flow fans is described which treats the complete downstream stator row as three vane sets (each evenly distributed) and then arranges the circumfer- ential and axial positions of the sets relative to each other so as to achieve self-cancellation of the principal interaction pattern Com- puted results are presented for a hypothetical fan with a blade tip Mach number of 0 58 and a hub-tip ratio of 0 83 Results show that the overall noise reduction of 6-9 dB originally anticipated is not approached,and that the technique is of little value for faster fans (for effective Mach numbers not less than 0 4 and not greater than 06) BJ A77-10349 ,7 Program system for computer calculations of let engine characteristics (Sistema programm dlia rascheta kharak- A77-10648 tenstik VRD na ETsVM) V I lankm Moscow, Izdatel'stvo Mashinostroenie, 1976 168 p 13refs In Russian The book describes a specialized system of procedures for calculations of gasdynamic processes and high velocity and throttle characteristics of jet engines, with special attention given to methods which are common to all types of jet engines These procedures are then codified in ALGOL-60, forming a program system The system is drawn up in two variants, one for computers with small operational memory and compilers with limited number of formal procedural parameters, and one for computers with large memory and many formal parameters P T H A77-10383 Strength of compressor wheels of low-ductility alloys I A Kozlov, L R Shlik, V N Gorodet#kn, L I Nemchenko, and V L Akhremenko (Akademiia Nauk Ukramskoi SSR, Institut Problem Prochnosti, Kiev, Ukrainian SSR) (Problemy Prochnosti, Jan 1976, p 92 97 ) Strength of Materials, vol 8, no 1.0ct 1976, p 91 95 Translation A77-10416 Flow of a radiating gas over a blunt body with intense vaporization V P Stulov and V N Mirskn (Moskovskn Gosudarstvennyi Universitet, Moscow, USSR) ITeplofizika Vyso- kikh Temperatur, vo\ 14, Jan-Feb 1976, p 112-119) High Temperature, vol 14, no 1, July 1976, p 98-104 15 refs Translation A77-10438 A systems approach to all weather landings L S Gephart, W P Fuchs (Dayton, University, Dayton, Ohio), G L Fileccia, T Joham (USAF, Flight Dynamics Laboratory, Wright- Patterson AFB, Ohio), and H G Tinsley (FAA, Terminal Navigation Branch, Washington, DC) In Annual Reliability and Maintain- ability Symposium, Las Vegas, Nev , January 20-22, 1976, Proceed- ings New York, Institute of Electrical and Electronics Engineers, Inc , 1976, p 25-30 This paper describes the modeling techniques adopted for a reliability/safety analysis of a unique FAA-AFFDL flight test program The program utilizes a large turbojet aircraft to gain approach and landing experience in Category III weather The total system includes the ground transmitting system with monitoring, the airborne flight control system (modified and augmented) as used in the automatic landing model with safety pilot and crew 'in the loop', and procedures, both standard and special The modeling techniques partition the vertical and lateral axes/functions and sub-divide the longitudinal or time axis into contiguous non-overlapping sub- intervals Analysis techniques, progress and present status are discussed (Author) A77-10442 Reliability of automated flight service stations N B Fuqua (NT Research Institute, Griffiss AFB, N Y ) In Annual Reliability and Maintainability Symposium, Las Vegas, Nev , January 20-22, 1976, Proceedings New-Yuik. InMUum- of Electrical and Electronics Engineers, Inc, 1976, p 113-119 10 refs Contract No F30602-73-C-0065 The flight service station (FSS) is an FAA air traffic control operational facility which provides services to pilots operating general aviation, civil air carrier, and military aircraft There are currently more than 300 Flight Service Stations within the con- tiguous U S The upgrading and automatization of the FSS system is considered An investigation is conducted to compare the reliability, maintainability, and availability (RMA) impact of three possible system'configurations under study The study demonstrates the effectiveness of the 'Single-Thread Functional Availability Modeling* techniques as a tool in examining and defining the RMA charac- teristics of a complex automated system which is required to randomly perform a number of unique functions G R A77-10483 Interface between maintainability and com- mercial aircraft spares support. J E Losee (Douglas Aircraft Co , Long Beach, Calif) In Annual Reliability and Maintainability Symposium, Las Vegas, Nev , January 20-22, 1976, Proceedings New York, Institute of Electrical and Electronics Engineers, Inc , 1976, p 500-503 A review of all aspects of the DC-10 program revealed that a new approach to spares support is imperative if an aircraft and a support system that would be financially attractive in the market place were to be produced The general methodology currently used by Douglas Aircraft to develop the spare support program for the D-10 is described VP A77-10500 Investigation and analysis of the human fac- tors in aircraft accidents (Investigation y analists de factores humanos en los accidentes de aviacion) A Perez Griffo (Centre de Investigacion de Medicina Aeronautica, Spam) Revista de Aero- nautica y Astronautics, vol 36, Sept 1976, p 711-720 16 refs In Spanish Aerospace medicine is concerned with the study of the physiopathological conditions existing during the flight and the determination of the psychophysical conditions which are desired for the members of the flight crew Attention must be given to human reactions in response to extraordinary situations which can occur It has been found that the reaction of the pilot is an important contributing factor in many aircraft accidents A description is given of the various aspects which have to be investigated in the study of the human factors The approaches which have to be employed in the investigation of aircraft accidents are discussed, taking into account studies at the location of the accident, laboratory studies, and organizational aspects G R A77-10524 Israel's pride of Lions Air International, vol II.Nov 1976, p 220-225,248,249 The delivery embargo imposed by the French government in 1967 on 50 Mirage 5J fighter-bombers for the Israel Defense Force together with a subsequent extension of the embargo led to the decision to manufacture the Mirage in Israel A licence was acquired for the General Electric J79-GE-17 engine and the basic Mirage 5J airframe was redesigned around this power plant Attention is given to the properties of the aircraft as a dogfighter, details of aircraft design, aspects of aircraft production, and plans for export sales G R A77-10525 YC-14 - All blow and no puff Air ~lriter-~ national, vol II.Nov 1976, p 227-232 The AMST program, which grew out of a Tactical Air Command requirement drawn up in 1970, is to provide a successor for the C-130 Hercules In connection with the introduction of new army weapons and equipment of greater size and weight, the Hercules can today carry only 55% of all combat brigade vehicles whereas the AMST is dimensioned to carry 90% The AMST can operate into and out of many airfields that would be unacceptable for the C-130 The YC-14 design for the AMST is discussed, taking into account details of aircraft structure, the power plant, aircraft performance, and the ability of the aircraft to meet mission requirements G R A77-10648 Simulating the last 100 ft J Belsoh Flight International, vol 110, Oct 23, 1976, p 1264-1266 Compu-Scene, a computer-generated-image visual display system fitted to the flight simulators of an American aerospace company. A77 10664 has been awarded Federal Aviation Administration approval for training purposes The optics of the system provide an infinity view through the windscreens and side windows on the flight deck Each unit is supplied with a full-color video signal representing an accurate perspective view of the outside world as it would appear from the flight deck for any position and attitude of the aircraft Compu- Scene offers a full daylight scene suitable for touch-down training G R A77-10664 Pressure distributions over frontal /nose/ sur- faces of bodies of revolution in transonic flow at angles of attack of' 0 to 10 deg P G Leutm ITsAGI, Uchenye Zapiski, vol 5, no 2, 1974, P 130-135) Fluid Mechanics - Soviet Rrtearch, vol 4, Nov-Dec 1975, p 18-24 5 refs Translation A77-10665 The hyperbolicity of integral equations of momentum in a three-dimensional incompressible laminar boundary layer V A Bannov (TsAGI, Uchenye Zapiski, vol 5, no 2,1974, p 55-60 ) Fluid Mechanics - Soviet Research, vol 4, Nov -Dec 1975, p 25-31 14refs Translation A77-10697 Bird hazards to aircraft Problems and preven- tion of bird/aircraft collisions H Blokpoel (Environment Canada, Canadian Wildlife Service, Ottawa, Canada) Research sponsored by the National Research Council of Canada, Ministry of Transport and Department of National Defence Toronto, Clarke, Irwm and Co, Ltd, 1976 250 p 445 ref s $950 Information on birds and on bird migration is presented and data of bird strike statistics are examined, taking into account aspects of bird classification and identification, bird numbers, bird sizes and weights, the annual cycle of bird migration, methods of studying migration, heights of migration, the behavior of birds with respect to approaching aircraft, and the types of damage resulting from bird strikes Work related to the bird-proofing of aircraft and engines is considered and a description is given of a search for on-board equipment to disperse birds Approaches for the prevention of bird strikes are discussed, giving attention to bird observation methods, bird dispersal methods, habitat manipulation, and pro cedures to minimize strike risks during periods of high bird densities G R A77-10771 H Unsteady pressure distributions on oscillating airfoils in a supersonic cascade M Kurosaka (GE Research and Development Center, Schenectady, N Y) ASMS, Transactions, Series A - Journal of Engineering for Power, vol 98, Oct 1976, p 553, 554 In Kurosaka's exact first-order theory for the unsteady super- sonic cascade with a subsonic leading edge, the expression for the pressure distribution - written in general form and applicable to any cascade geometry - is disturbingly lengthy in appearance In the present note, it is shown that for cascade geometries of practical interest, the expression for the unsteady pressure distribution can be reduced to a much simpler form V P A77-10772 ff Pressure loss coefficient of impingement cooled leading edge system of a turbine blade D K Mukherjee (Browa Bj>ven et Cie AG, Baden, Switzerland) ASME, Transac- tions, Series A - Journal of Engineering for Power, vol 98, Oct 1976, p 554-556 18 refs The pressure loss coefficient of an impingement cooled system similar to that often used to cool the leading edge of a turbine blade has been determined from model test The influence of Reynolds number in the range tested is negligible However, the influence of relative distance of the jet holes from the surface to be cooled is very significant (Author) A77-10773 ff Film cooling with injection through slots D K Mukherjee (Brown, Boveri et Cie AG, Baden, Switzerland) ASME, Transactions, Series A - Journal of Engineering for Power, vol 98, Oct 1976, p 556-559 23 ref s This work deals with film cooling of a surface with injection through slots From the vast number of literatures surveyed, the cooling effectiveness for an ideal geometry • a flat plate with no pressure gradient having tangential blowing from a slot with no lip thickness - could be found by using a suitable blowing parameter for three different regions The influence of blowing angle and lip geometry has been investigated and defined, each separately (Author) A77-10854 ~ Forces on unstaggered airfoil cascades in un- steady m-phase motion N H Kemp (Avco Everett Research Laboratory, Inc , Everett, Mass ) and H Ohashi (Tokyo, University, Tokyo, Japan) (American Society of Mechanical Engineers, Paper 76-FE-S, 1976) ASME, Transactions, Series I Journal of Fluids Engineering, vol 98, Sept 1976, p 521-530 18refs Incompressible flow through an unstaggered cascade in general, unsteady, m-phase motion is considered By methods of thin airfoil theory, using the assumptions of wakes trailing back at the through-flow velocity, and the Kutta condition, exact analytical expressions are derived for loading, lift and moment As application. A77-10855 " Flow interaction near the tail of a body of revolution I - Flow exterior to boundary layer and wake A Nakayama, V C Patel, and L Landweber (Iowa, University, Iowa City, Iowa) (American Society of Mechanical Engineers, Paper 76-FE-M, 1976 ) ASME, Transactions, Series I - Journal of Fluids Engineering, vol 98, Sept 1976, p 531-537 18 refs Research supported by the University of Iowa, Contract No N00014-68- A-0196-0002 An iterative procedure for the calculation of the thick attached turbulent boundary layer near the tail of a body of revolution is presented The procedure consists of the potential-flow calculation by a method of integral equation of the first kind and the calculation of the development of the boundary layer and the wake using an integral method with the condition that the velocity remains continuous across the edge of the boundary layer and the wake The additional terms that appear in the momentum integral equation for the thick boundary layer and the near wake are taken into account and the pressure difference between the body surface and the edge of the boundary layer and the wake can be determined The results obtained by the present method are in good agreement with the experimental data (Authoi) A77-10856 ,7 Flow interaction near the tail of a body of revolution II - Iterative solution for flow within and exterior to boundary layer and wake A Nakayama, V C Patel, and L Landweber (Iowa, University, Iowa City, Iowa) (American Society of Mechanical Engineers, Paper 76-FE-N, 1976) ASME, Trans- actions, Series I - Journal of Fluids Engineering, vol 98, Sept 1976, p 538-546, Discussion, p 546-548, Author's Closure, p 548, 549 33 refs Research supported by the University of Iowa, Contract No N00014-68 A-0196-0002 ' This part deals with the calculation of the flow within the A77-11276 attached boundary layer and the wake of a body of revolution and its interaction with the external potential flow which was treated in Part 1 The iterative technique described in Part 1 is used to obtain a complete solution to the flow in the neighborhood of the tail of the body The results of the calculations are compared with two sets of experimental data and reasonable agreement is demonstrated (Author) A77-10882 K Dual-spin spacecraft dynamics under con- ditions of a rotating unbalanced platform and rotor asymmetry G J Adams (Hughes Aircraft Co , Space and Communications Group, Los Angeles, Calif) International Astronautical Federation, Inter- national Astronautical Congress, 27th, Anaheim, Calif, Oct 10-16, 1976, Paper 76-019 9p 14refs Design of the attitude stabilization system of a dual-spin spacecraft is based primarily on proper management of internal energy dissipation with the platform despun If the platform is rotating, however, the dynamic response is determined by platform dynamic imbalance and rotor transverse inertia symmetry in addition to energy dissipation effects The rotating platform case is important as a temporary condition from which it is desired to recover The paper gives a heuristic description of the vehicle dynamics for roll/pitch ratios above and below unity, a summary of m-orbit experience with the TACSAT and DSCS-2 satellites, and a descrip- tion of some of the design features and operational procedures utilized on current dual-spin spacecraft to ensure recovery from various failure mode conditions (Author) A77-10911 /f The fuel approach to control emissions from aircraft R W Hurn (ERDA Bartlesville Energy Research Center, Bartlesville, Okla ) International Astronautical Federation, Interna- tional Astronautical Congress, 27th, Anaheim, Calif, Oct 10-16, 1976. Paper 76-111 7p Control of fuel composition may provide a means to control or affect the emission of metals, sulfur, smoke, and nitrogen oxides Metals emissions can be related to the occurrence of metals as trace elements in crude oils and to an erosion of metal engine parts Sulfur in fuel constitutes the only significant source of that element or its derivatives in turbine exhausts Suitable approaches for reducing the amount of sulfur and sulfur oxide emissions are considered G R A77-10912*# Effects of atmospheric conditions on the operating characteristics of supersonic cruise aircraft W G Schweik- hard, G B Gilyard (NASA, Flight Research Center, Edwards, Calif), J E Talbot, and T W Brown (British Aircraft Co, Bristol, England) International Astronautical Federation, International Astronautical Congress, 27th, Anaheim, Calif, Oct 10-16, 1976, Paper 76-112 21 p 20 refs Since for maximum range a supersonic transport must cruise near its maximum Mach number, accurate flight control is needed, especially when severe atmospheric transients are encountered This paper describes atmospheric transients that have been encountered by the XB-70, YF-12, and Concorde aircraft during supersonic flights and the ensuing responses of the aircraft propulsion and flight control systems It was found that atmospheric conditions affected these supersonic cruise vehicles in much the same way, with minor differences according to the type of propulsion and flight control system Onboard sensors are sufficiently accurate to provide data on the atmosphere, including turbulence over the route, that are accurate enough for entry in the climatic record and for use as inputs to the control systems Nominal atmospheric transients can be satisfactorily controlled, but some problems remain for extreme cases (Author) A7710939 if Strength of glass-fibre-remforced plastics at one-sided heating G S Pisarenko and G N Tret'iachenko (Akade- miia Nauk Ukramskoi SSR, Institut Problem Prochnosti, Kiev, Ukrainian SSR) International Astronautical Federation, Interna- tional Astronautical Congress, 27th, Anaheim, Calif, Oct 10-16, 1976, Paper 76-200 8 p 11 refs The surfaces of modern high-speed aircraft are protected from aerodynamic heating by coatings prepared of ablating materials, such as fiberglass laminates, asbestos textolites, carbon-base materials, and composites, each of whose elements serves a specific (load-carrying, insulating, etc ) purpose The facilities described in the present paper are designed for testing such protective coatings in bending, tension, or compression under unilateral heating Some techniques used to simulate the actual heating conditions are discussed V P A77 10972 # Beyond supersonic transport S B Rosenfield (New England School of Law, Boston, Mass ) International Astro- nautical Federation, International Astronautical Congress, 27th, Anaheim, Calif, Oct 10-16, 1976, Paper ISL-76-66 14 p 7 refs The legal aspects of a future civil transport system consisting of travel both in the atmosphere and in outer space - the civil air-space ransport system • are considered The discussion is based on the separate examination of space law and air law B J A77 11195 * Development of aircraft brake materials T -L Ho and M B Peterson (Rensselaer Polytechnic Institute, Troy, N Y ) American Society of Lubrication Engineers and American- Society of Mechanical Engineers, Lubrication Conference, Boston, Mass., Oct 5-7, 1976, ASLE Preprint 76-LC-1B-3 6p 5 refs Grant No NGR-33-018-152 A program has been carried out to study and develop high temperature aircraft brake materials A survey of the requirements of brake materials was made to select materials to meet these requirements Based upon their physical and thermal properties, a number of materials were selected and evaluated in sliding tests which simulated aircraft braking The mating material is 17-22 AS steel Additives were incorporated into these materials to optimize their wear or strength behavior with particular emphasis on nickel and molybdenum base materials Optimum materials were developed which had improved wear behavior over conventional brake materials in the simulated test The best materials were a nickel, aluminum oxide, lead tungstate composition containing graphite and a molyb- denum base material containing LPA 100 (an intermetallic com- pound of cobalt, molybdenum and silicon) (Author) A77-11261 Competition for airspace - Bird strikes and aircraft operations R W Doughty (Texas, University, Austin, Tex ) Traffic Quarterly, vol 30, July 1976, p 449-467 16 refs Research supported by the University of Texas The hazards of bird collisions with aircraft are examined and the growing encroachments of airports on wildlife habitats, particularly for certain species of birds, are noted Tables are presented containing information on significant bird-aircraft strikes from 1960 to 1974 and annual variations in damaging bird strikes, US Air Force 1956-1972 The relation of inflight collison risks and bird migration is investigated as are bird hazards on airport environments Methods for reducing bird hazards including distress calls, noise makers, chemical repellents, pyrotechnics and falconry are discussed B J A77-11276 European Rotorcraft and Powered Lift Air- craft Forum, 1st, University of Southampton, Southampton, England, September 22-24, 1975, Proceedings Vertica, vol 1, no 1, 1976. 93 p A77-11277 The first issue of a new periodical devoted to rotorcraft and powered lift aircraft covers numerous topics in rotorcraft engineering and applications Topics represented include circulation control rotors and stowed rotors, winged rotorcraft, rotor and flap control systems, vibration analysis and control, hinge less rotors, comparative studies of passenger-service VTOL, STOL, and CTOL capabilities and shortcomings, and rotor-emitted noise analysis and abatement Individual items are announced in this issue R D V A77-11277 Application of circulation control rotor tech- nology to a stopped rotor aircraft design R M Williams (U S Naval Material Command, Ship Research and Development Center, Bethesda, Md ) (European Rotorcraft and Powered Lift Aircraft Forum, 1st, Southampton, England, Sept 22-24, 19751 Vertica, vol 1,no 1,1976, P 3-15 6 refs Design and performance of a hybrid X-wmg stopped-rotor V/STOL aircraft optionally powered by outboard fan engines and top-mounted slot-blowable rotary wing lift are described Applica- tion of circulation control rotor (CCR) technology to the concept is discussed Handling of transition lift by blowing out of rotor slots separately or in unison and resulting advantages are dealt with Rotor design, blade and disk loading, and blade weight analysis are covered in addition to fixed-wing and rotary-wing performance modes (including stopped-wing mode, stowed-wing mode, and blown fixed-wing mode) Aeroelastic bending divergence in the stopped- wmg mode, resonant amplification of blade vibratory bending stresses during rotor slowing and stopping, and potential high- frequency coupled instabilities of isolated blades, multi-blades, and rotor/body combination are critical R D V \ ' A77-11278 Advanced control systems for helicopters I A Simons (Westland Helicopters, Ltd , Yeovil, Somerset, England) (European Rotorcraft and Powered Lift Aircraft Forum, 1st, Southampton, England, Sept 22-24, 1975) Vertica, vol 1, no 1, 1976,p 17-29 Some of the basic control and stability problems that are typical of the present day helicopter are discussed and their part in defining rotor characteristics is indicated The idea of demand types of control systems is introduced as a possible solution to these problems and as a means to releasing some of the present rotor design constraints - particularly in rotor stiffness In order to illustrate the potential freedom in helicopter design resulting from the adoption of very stiff rotors, their use in a coaxial system is briefly discussed (Author) A77-11279 Reducing vibration by structural modification GTS Done and A D Hughes (Edinburgh, University, Edinburgh, Scotland) (European Rotorcraft and Powered Lift Aircraft Forum, 1st, Southampton, England, Sept 22-24, 1975) Vertica, vol 1, no 1,1976,p 31-38 Selection of criteria for singling out those elements of a helicopter fuselage structure to be treated as variables in a model designed to aid minimization of vibration response by modifying the fuselage structural design are discussed Pinpointing sensitive and crucial structural elements or parts with respect to vibration performance of a newly assembled helicopter to minimize vibration response in the passenger and crew area is also dealt with Structural response theory, relevant analysis and mathematical properties, sensitivity criteria, and application to a simplified 60 DOF helicopter fuselage structure are discussed The gearbox and tail cone sub- structures are found crucial areas for fuselage modification to achieve vibration abatement in the passenger and crew area R D V A77-11280 Hmgeless rotor dynamics in high speed flight. H Huber and H Strehlow (Messerschmitt Bolkow-Blohm GmbH, Ottobrunn, West Germany) (European Rotorcraft and Powered Lift Aircraft Forum, 1st, Southampton, England, Sept 22-24, 1975) Vertica, vol 1,no 1,1976, p 39-53 11 refs A high speed flight research program has been carried out on MBB BO 105 Hmgeless Rotor behavior within an expanded flight envelope True airspeeds of 200 kt (pure helicopter version) and of 218 kt (winged helicopter version) were achieved in dive conditions, corresponding to advance ratios up to 0 53 and advancing blade tip Mach numbers up to 0 97 Rotor blade versions with constant thickness airfoil, and with thin tip modifications were evaluated Essential test results are compared to theoretical investigations Main emphasis is placed upon rotor structural loads, control and stability behavior, and aeroelastic stability characteristics A continuous picture of hingeless rotor characteristics over a wide speed and maneuver range is presented (Author) A77-11281 Rotor impedance measurements at model scale D R Gaukroger and R Cansdale (Royal Aircraft Establish- ment, Structures Dept, Farnborough, Hants, England) (European Rotorcraft and Powered Lift Aircraft Forum, 1st, Southampton, England, Sept 22-24, 1975) Vertica, vol 1, no 1, 1976, p 55-66 A test rig has been built at the Royal Aircraft Establishment to measure the shaft impedances of model rotors in hover conditions Model rotors up to about 3 m in diameter can be tested - that is to say, 1/5 or 1/4 scale models of an 'average' rotor The method of test is to oscillate the rotor shaft in a particular direction over a range of frequencies and to measure the force or moment required to produce the oscillation, and the forces and moments required to prevent oscillation in any other direction Provision is made for shaft motion either in a pitching direction about a rotor diameter or in a translatory direction in the rotor plane An automatic excitation and on-line analysis system enables all the forces and moments per unit motion (rotor impedances) to be calculated and displayed Complete matrices of rotor shaft impedances can be used either to check theory or to assess the stability of the rotor when it is joined to a fuselage In the latter case, the impedance matrix of the fuselage must also be determined (Author) A77-11282 A wing on the SA 341 Gazelle helicopter and its effects M Torres (Societe Nationale Industnelle Aerospatiale, Division Helicopteres, Mangnane, Bouches-du-Rhone, France) (European Rotorcraft and Powered Lift Aircraft Forum, 1st, Southampton, England, Sept 22-24, 1975) Vertica, vol 1, no 1, 1976,p 67-73 Control surfaces, handling, flight testing, and adjustments of the SA 349 or SA 341 helicopters are discussed A low-mounted wing (area 54 sq ft), wing-mounted airbrakes functioning as lift spoilers, and an in-flight trimmable stabilizer and their effects were tested on a flying- prototype Results of wind-tunnel tests, simulator tests, reference flight tests, and basic flight tests are stated Airbrakes were fitted onto upper and lower wing surfaces as the wing adversely affects autorotation, producing high wing lift, unloading the rotor, and decreasing rotor rpm Interactions between wing and stabilizer, adjustments of wing area, dihedral and incidence angles, use of removable wing tips and adjustable struts, and stabilizer settings are described, along with quick-stop maneuvers using airbrakes, wing stall, and behavior in dive, banking, and hover R D V A77-11283 Intercity VTOL aircraft - A Hawker Siddeley review M J Brennan (Hawker Siddeley Aviation, Ltd , Kingston-on- Thames, Surrey, England) (European Rotorcraft and Powered Lift Aircraft Forum, 1st, Southampton, England, Sept 22-24, 1975) Vertica, vol 1,no 1,1976, p 75-88 11 refs A77-11595 Comparisons between CTOL, STOL, and VTOL flight in passenger service are made for a wide range of criteria Comparative data are tabulated and diagrammed for passenger seat-km and loads, take-off and landing regimes, approach speed and angle, runway length, required airport area, noise footprints, airport costs, air traffic segregation, first costs and operating costs, total journey costs and total journey time, fuel consumption and flight time, time response to weather data, and instrumentation demands Service to low-density communities, intercity shuttle traffic, and detrimental social and political aspects of CTOL service are stressed STOL disadvantages in terminal-phase gust conditions are cited Time required to develop a V/STOL transport system from scratch is considered R D V A77-11284 Rotational noise measurement in a wind tun- nel by total sampling synchronization C Armand (ONERA, Chatillon-sous-Bagneux, Hauts-de-Seme, France) (European Rotor- craft and Powered Lift Aircraft Forum, 1st, Southampton, England, Sept 22-24, 1975.) Vertica, vol 1, no 1, 1976, p 89-92 A new method, total sampling synchronization (TSS), for extracting the rotational noise of an advancing rotor blade from wind tunnel noise is described The TSS method provides the best adaptation of numerical Fourier analysis to rotational noise or other periodic phenomena Rotorcraft rotational noise is singled out as the most troublesome and discomforting noise contribution emitted in flight, but deficiencies of in flight measurements (relative positions of microphones and rotorcraft, limitation of speeds of existing rotorcraft and rotors, and poor representation from onboard microphone signals) dictate the use of high-speed wind tunnels for noise testing Noise spectral analysis with correlations, with partial synchronization of sampling, with total sampling synchronization, and uncorrelated, is examined and compared R D V A77-11311 Co-operation in the European aircraft manu- facturing industry and among the scheduled airlines /Brancker Memorial Lecture/ K Hagrup (Scandinavian Airlines System, Bromma, Sweden, International Chamber of Commerce, Paris, France) Chartered Institute of Transport Journal, vol 37, May 1976, p 93-104 Cooperation (rather than competition) as the aviation industry has achieved it in AECMA (European Association of Aerospace Manufacturers), in AEA (Association of European Airlines), in ECAC (European Civil Aviation Conference), in KSSU (KLM, SAS, SWR, UTA) and in ATLAS (Air France, Alitalia, Iberia, Lufthansa, Sabena) and other cooperating groups in Europe is discussed Particular emphasis is on the EEC commission's proposal regarding extended cooperation and centralization of the aerospace manufacturers and airlines of the EEC Modifications of the EEC commission's proposal are suggested B J A77-11312 Transport progress in practice Air transport in Africa - East African Airways Corporation Experience A B S Kilewo (East African Airways Corp, Nairobi, Kenya) (Chartered Institute of Transport, Congress, Nairobi, Kenya, May 1976) Chartered Institute of Transport Journal, vol 37, July 1976, p 128-132 Some major problems facing the development of air transport industry in Africa are outlined, and the part played by the air transport industry in the economic development of the East African countries is examined The formation of an African multinational freight airline is proposed as a means of stimulating air cargo transportation among African countries The formation of such an airline could start with regional integration and the formation of stronger airlines in the African subregions The need for a co- ordinated transport policy and mutual assistance is emphasized V P A77-11325 High-nickel alloys for gas turbines J H DeBord (Huntmgton Alloys, Inc ) Gas Turbine International, vol 17, Sept-Oct 1976, p 28-30 Mechanically alloyed and conventionally alloyed high-nickel refractory alloys for gas-turbine design applications are discussed along with their advantages and applications The article deals with mconel grades MA 754, MA 757E, 617, 625, 718, and 706, and with mcoloy grades MA 956E, 903, and MA 757E Aerospace applications are given emphasis, including use of mcoloy alloy 903 in the Space Shuttle Mam Engine Use of mconel 625 in aircraft ducting systems, engine exhaust systems, thrust reverse systems, honeycomb struc- tures, heat exchanger tubing, mconel 718 in compressor and turbine discs, blades, and shafts, mconel 718 in rocket engines and in Space Shuttle, and mconel MA 754 in vanes and shrouds are among the applications mentioned R 0 V A77-11477 Estimating fatigue-crack lives for aircraft - Techniques. J P Gallagher (USAF, Flight Dynamics Laboratory, Wright-Patterson AFB, Ohio) (Society for experimental Stress Analysis, Spring Meeting, Chicago, III., May 11-16, 1975) Experi- mentalMechanics, vol 16, Nov 1976, p 425-433 24 refs Some complex aircraft stress histories, steady-state spectra, are noted to induce fatigue-crack growth-rate behavior similar to that observed under constant-amplitude loading The paper identifies, the behavior induced by steady-state spectra, and attributes the behavior to spectrum-stress-event periodicity Spectrum periodicity is sub- sequently defined by isolating the group of statistically repetitive stress events The noted crack-growth-rate behavior that exists for steady-state spectra provides the analyst with new techniques for estimating crack lives Several crack-life estimating techniques are compared, for the two steady-state spectra considered herein, one technique called the simple-crack incrementatiorvmmiblock ap- proach provides life estimates with the same accuracy as that given by the cycle-by-cycle life-prediction method studied but does so five times more efficiently The reasons for associated accuracy and efficiency are discussed (Author) A77-11594 Investigation into the optimum use of advanced displays in future transport aircraft R E Hillman (British Aircraft Corp, Weybndge, Surrey, England) and J W Wilson (Hawker Siddeley Aviation, Ltd , Hatfield, Herts , England) (Royal Aeronautical Society, Spring Convention on Seeds for Success in Civil Aircraft Design in the Next Two Decades, London, England, May 19, 20, 1976) Aeronautical Journal, vol 80, Sept 1976, p 377-384 New and future systems and formats for presentation of flight information to pilots are examined from the standpoint of pilot acceptance, pilot work load, and operating costs Demonstration of positjve engineering and pilot performance advantages is demanded, and weighed against potential improvements in the human-display system Flight deck instrumentation is broadly divided into three categories with different characteristics dictated by safety, precision, cost, and work load needs flight, engine, and system displays A comparison is set up between a two-crew flight deck outfitted with 7 CRT displays and a contemporary 3-engme 3-crew wide-bodied r aircraft Development of flexible electronic attitude director indi- cators and horizontal situation indicators with all required navigation and flight information efficiently displayed, untimely and super- fluous data suppressed, and relevant data integrated onto a smaller display area, is encouraged R D V A77-11595 Future trends in aero gas turbine design II - Unconventional engines R M Denning, S C Miller, and G H Wright (Rolls Royce /1971/, Ltd, Aero Div, Bristol, England) A77 11603 (Royal Aeronautical Society, Spring Convent/on on Seeds for Success in Civil Aircraft Design in the Next Two Decades, London, England, May 19, 20, 1976) Aeronautical Journal, vol 80, Sept 1976, p 385-393 9 refs Unconventional types of aircraft gas turbine (GT) engines reviewed are so treated in the sense of unconventional uses (other than propulsionl for the GT engine, modification of the thermo- dynarmc cycle under some flight conditions, or use of extremes of the constant-pressure GT cycle Variant thermodynamic/aero- dynamic cycles under consideration include a heat-exchanger engine, propulsion systems with mgestion or re-energizing of wake or boundary layer to reduce drag, and systems resorting to laminar flow control Jar boundary layer suction Engines featuring in flight variation of the thermodynamic cycle include those using variable turbine stators, SST variable-cycle engines with compressor switching valve system, and variable-pitch fan engines Engines developing vertical lift in addition to propulsive thrust include blow-fan engines, externally blown flap engines, and rotatable remote lift/ propulsion fan engines R D V A77-11603 Signal-treatment methods during aircraft- engine inspection based on vibroacoustic noises V V Izokh and V I Mikulovich (Belorusskn Gosudarstvennyi Umversitet, Minsk, Belo- russian SSR) (Defektoskopua, Jan -Feb 1976, p 39-47 ) Soviet Journal of Nondestructive Testing, vol 12, no 1, Nov 1976, p 29-34 15 refs Translation Several methods of signal analysis for vibroacoustic flaw detection applied to the rotating parts of aircraft engines are described The methods considered are spectral analysis and correla- tion analysis, and it is found that it is desirable to use synchronous detection and spectral analysis with high resolution for inspecting engines and their individual rotating parts under service conditions and in the experimental design stage B J A simple acoustic sounder is shown to produce reliable velocity profiles of aircraft wakes at altitudes below 50 m Data collection during normal airport landing operations was feasible because the sensor does not intrude into the airspace being measured A spatial scan through the wake is obtained when the ambient wind transports the wake through the sounder beam The characteristics of the scattered signals and their spectral densities are presented as intensity modulated CRT displays termed 'Acoustograms' The data are processed to yield the radial dependence of the velocity and circulation in the wake vortices The circulation data are fitted to a simple mode1 with two parameters strength and core radius The spatial and velocity -esolution of the sounder is adequate to measure vortex strength but not to probe details of the core structure Reliable measurements using this technique are possible only when the vortex transport velocity is well-defined (Author) A77-11844 A test facility for aircraft jet noise reduction II B L McGehee (Boeing Commercial Airplane Co , Seattle, Wash ) Journal of Environmental Sciences, vol 19, Sept-Oct 1976, p 2028 24 refs An overview is given of the design and performance of the Boeing large test chamber (LTC) and subsystems for studying abatement of aircraft jet noise Support systems for the LTC facility, the anechoic room, acoustic calibration problems, data handling, support systems and test rigs are described at length Acquisition of reliable aircraft noise performance test data and isolation of LTC noise and surrounding community noise are singled out as the key problems Measures to keep outside community noise from intruding into the test arena, and preventing LTC noise from causing a nuisance in the surrounding community area are detailed Test area sizing, flow visualization, the development model chamber, a model propane burner, exhaust stack, pumps, room ventilation, air supplies, cooling water, safety measures, and future LTC facility needs are dealt with R D V A77-11606 Magnetic particle inspection of aviation engine vanes A G Aleksandrov and S G Shehkhov (Defektoskopua, Jan-Feb 1976, p 81-85 ) Soviet Journal of Nondestructive Testing, vol 12, no 1,IMov 1976, P 6265 Translation Consideration is given to the reason for the decrease in revealing fine fatigue cracks in aviation engine vanes in inspection in an electromagnet Recommendations for inspection methods are given Compositions of magnetic suspensions and methods of interpretation are shown (Author) A77-11625 'C22', the new French target drone CC 22' nouvel engm cible francais) P Langereux Air et Cosmos, vol 14, Oct 23, 1976, p 24,25 In French The C22 is a subsonic, remotely controlled, target drone, of variable speed It is to replace the target drones of the type CT20 It is expected that the mass production of the C22 will begin in 1981 The target drone is to be propelled by the turbojet engine TRI 60 which is also to be used in remotely piloted vehicles The C22 will be employed with a towed target for gunnery-training exercises of antiaircraft artillery and for tests conducted with surface to air missiles The C22 will be able to attain a speed of 0 95 Mach G R A77-11712 ft Measurement of, wake vortex strength by means of acoustic back scattering D C Burnham, T E Sullivan (U S Department of Transportation, Transportation Systems Center, Cambridge, Mass), and L S Wilk (MIT, Cambridge, Mass)'Journal of Aircraft vol 13, Nov 1976, p 889-894 9 refs A77-11887 Laser air-jet engine A I Barchukov, F V Bunkm, V I Konov, and A M Prokhorov (Akademna Nauk SSSR, Fizicheskn Institut, Moscow, USSR) (ZHETF Pis'ma v Redakts/iu, vol 23, Mar 5, 1976, p 237-240 ) JETP Letters, vol 23, Mar 5, 1976, p 213215 6 refs Translation A scheme is outlined for a laser air jet engine (LAJE), in which jet thrust is obtained by optical discharges in the engine caused by a pulsed radiation beam generated on earth Pulsed optical breakdowns create pulsed shock waves, which are reflected off a surface, impelling the vehicle Some basic parameter calculations have been performed for different pressure chamber configurations, to gam an idea of required laser performance for a given thrust level P T H A77-12000 VTOL RPVs - A technology assessment B Lmdenbaum American Helicopter Society, Journal, vol 21, Oct 1976, p 29-39 Military uses and advantages of VTOL remotely piloted vehicles (RPV) and VTOL RPV development problems are discussed, along with the state of the art, means of RPV recovery and launch, and numerous VTOL concepts The higher unit cost of VTOL systems is measured against the total system costs for non-VTOL craft (including landing field or aircraft carrier construction costs and operating costs, ground transportation costs, accident rates), and VTOL advantages where no design accommodation for onboard crew is needed are emphasized (including feasibility of tail-sitter designs, size, availability of all known VTOL approaches) VTOL concepts considered and compared for RPV application include jet lift, augmented thrust (with lift fan and ejector type flow augmenters), shrouded propeller/fans, open propeller/rotor, and VATOL (vertical attitude TO L tail-sitter configuration) RDV A77 12182 A77-12069 Maintaining transport aircraft R Krahenbuhl (Swissair AG, Kloten, Switzerland) Esso Air World, vol 28, no 4, 1976, p 90-93 The article surveys Swissair maintenance practice at Zurich airport, covering the integration of existing computer maintenance programs, programs of periodic checks, and a rundown of main tenance theory for wide-body craft Hard time maintenance, on condition maintenance, and condition monitoring are defined and contrasted, fail safe and safe life options are defined and their ranges of validity are stated, and the maintenance decision diagram adopted in 1970 is outlined The computerized automatic test equipment, built in test equipment, and aircraft integrated data system are sketched Periodic checks, from service check after each flight through checks scheduled for 270 and 1500 flight hours to the heavy maintenance visit (after 12,000 flight hours), are indicated Physical inspection methods, time allocations in maintenance tasks, and cooperation in maintenance pooling between various carriers are mentioned R D V A77-12175 H Dynamic-stress-data management for aero- mechanical testing of turbomachmery W J Rakowski (ARO, Inc , Arnold Air Force Station, Tenn ) Society for Experimental Stress Analysis, Spring Meeting, Silver Spring, Md. May 9-14, 1976. Paper 26 p The aeromechanical test programs described were initiated to provide experimental data concerning specific turbine engine struc- tural problems and general characterization of turbine engines Test techniques and data acquisition/processing analysis techniques were developed during these test programs to meet the program require- ments The present paper deals with the data management philos- ophy and techniques developed for the dynamic strain-gauge data acquired during the programs The transition from single channel analog analysis equipment to the incorporation of digital computers for aidina on-line data monitoring, bulk processing of test data, and rapid analysis of test results is discussed The present on-line monitoring and post test processing/analysis systems are described, and refinements for improving the on line data monitoring and post test data processing capabilities are noted V P A77-12114 Concorde Endurance flights results (Con corde - Resultats des vols d'endurance) P Lebouc (La Concorde, Toulouse, France) L'Aeronautique et L'Astronautique, no 60, 1976, p 10-15 In French Data are presented and tabulated on Air France Concordes run through endurance tests to date Data on each aircraft tested, on the flights executed, the routes traveled, amount of fuel consumed, amount of fuel taken on board, flight profiles, prescheduled detours, and test facilities placed on board for the endurance tests are included Time out of service during this period is compared to figures for subsonic large aircraft It is concluded that Concorde has proved itself as an operationally viable passenger aircraft R D V A77-12115 Concorde maintenance as seen by the designer - The maintenance program (La maintenance de Concorde vue du cote constructeur - Le programme d'entretien) P Gavin (La Concorde, Pans, France) L'Aeronautique et L'Astronautique, no 60, 1976, p 1733 In French Preventive maintenance measures for Concorde are presented and it is pointed out that no special problems occur Emphasis is laid on routine preventive maintenance procedures Some modes of maintenance are distinguished, parties directly interested in orgamza tion of maintenance (airline, aviation officials, and designers) are indicated, and examples of maintenance documentation are pre sented Structural analysis, analysis by zones, and analysis based on aircraft, equipment, and motor systems are contrasted Organization of the maintenance data bank is sketched Emergency repair procedures and inspection frequency are discussed briefly R D V A77-12176 # System considerations for reliable strain data from gas turbine engines D L Willis (General Motors Corp , Detroit Diesel Allison Div , Indianapolis, Ind ) Society for Experimental Stress Analysis, Spring Meeting, Silver Spring, Md, May 9 14, 1976, Paper 17 p This discussion will consider the problems of dynamic stiam gage installations on the high pressure turbine rotor of a typical twin-spool gas turbine engine The hostile environment of high temperatures, centrifugal loads and very limited physical space are defined and the total system elements to meet these re-requirements are described Some of the elements considered in the system are choices available for the strain gage, means of attachment to the test part, and the lead wire system between the strain gage and the signal transfer device Special attention is given to the unique wire routing problems associated with the gas turbine engine The available choices for signal transfer devices are also discussed with a summary of advantages and limitations for various systems (Author) A77-12181 H Estimating procedures associated with aircraft modifications J A Knagg (E-Systems, Inc , Dallas, Tex ) Society of Allied Weight Engineers, Annual Conference, 35th, Philadelphia, Pa, May 24-26, 1976, Paper 1101 lip Modification of existing or obsolescent aircraft is discussed from the viewpoint of the weight engineer Several examples of modified aircraft are described, and a general modification methodology is outlined Consideration is given to the use of micromodules in aircraft electronic systems, antenna miniaturization, and effects of modification programs on fuel requirements and management F G M A77-12116 Reliability applied to landing gear and hydrau lies (La fiabihte apphquee aux atternsseurs et a I'hydrauhque) M Woerner (Messier-Hispano SA, Service Fiabihte, Montrouge, Hauls de-Seme, France) L'Aeronautique et L'Astronautique, no 60,1976, p 63-70 In French Malfunction analysis and assessment, reporting and documenta tion, and acquisition and treatment of fault data are discussed for civil aviation landing gears and hydraulics systems, on the basis of Messier Hispano practice Various levels of readily diagnosed and hidden faults are considered, and tables and branching trees of fault diagnostic tests (for mistimed landing gear actuation) are displayed Leakage of hydraulic fluid and seizing of equipment parts are also treated An outline of fault data reporting procedure and fault coding procedure is presented, along with a sample fault report sheet R D V A77-12182 # Fuselage analytical weight estimation method A D G Bayly (Lockheed California Co , Burbank, Calif ) Society of Allied Weight Engineers, Annual Conference, 35th, Philadelphia, Pa , May 24-26, 1976, Paper 1102 20 p Much time and energy has been spent into the investigation of fuselage weight prediction methods Most of these methods have been established by the use of statistical data derived from past and existing aircraft A more accurate and convenient method is required for use during the contract definition phase of a program where more detailed information is readily available to the weight engineer This paper presents an analytical method of weight prediction for the A77-12183 basic shell of any fuselage It assumes that the shear loads are absorbed by the skin and stringers and the bending loads are taken out by frames and longeron Basic loads are required to be known in order to determine the shear and bending material of the shell structure The method also takes into account cutouts, pressunzation and shape penalties The resulting basic shell weight can then be used along with statistical data for specific design features to arrive at a total fuselage weight (Author) A77-12183 ff Weight and balance considerations in the design of the A-10A close air support aircraft G C Leavy (Fairchild Republic Co , Farmmgdale, N Y ) Society of Allied Weight En- gineers, Annual Conference, 35th, Philadelphia, Pa, May 24-26, 1976, Paper 1104 30 p This paper describes the design features included in the A-10A Close Air Support Aircraft which had a significant effect on the aircraft weight and balance Particular attention is given to the survivability features and to the 30 MM gun installation, which are peculiar to the A-10 and had the greatest effect on the weight and balance Included are quantitative assessments of the first order weight increments due to the design features as well as discussions of the effects of these design features on the configuration and size of the aircraft (Author) A77-12184 ff Advanced design composite aircraft, the next step for composites P Schwartz (Grumman Aerospace Corp, Bethpage, N Y) Society of Allied Weight Engineers, Annual Conference, 35th, Philadelphia, Pa, May 24-26, 1976, Paper 1105 13 p Contract No F33615-75 C-3124 The Advanced Design Composite Aircraft (ADCA) program was initiated to define the benefits and effects of unrestrained applica- tion of composite materials to a completely new aircraft The present paper deals with the first phase of the ADCA program whose aim was to define criteria and requirements affecting ADCA design This phase included parametric tradeoff studies conducted to identify the preferred aircraft configuration and also the weight savings compared with an equivalent metal counterpart The Supersonic Penetration Interdiction Fighter mission was chosen because it provides the most demanding set of requirements and yields the maximum potential payoff from the unrestrained use of composite materials Configura- tions capable of performing the desired mission were evaluated using Grumman's RAVES sizing programs The resulting smaller and lighter aircraft was found capable of performing the same mission as its metal counterpart V P A77-12191 # A method for estimating the weight of aircraft transmissions A H Schmidt (Boeing Vertol Co, Philadelphia, Pa) Society of Allied Weight Engineers, Annual Conference, 35th, Philadelphia, Pa, May 24-26, 1976, Paper 1120 24 p In the design phase of vertical take-off aircraft, it is necessary to estimate the weight of the transmissions in the drive system as accurately as possible since it comprises a significant portion of the total aircraft weight A method of determining transmission weight is presented based upon the size of the gears in the transmission The gear size is not used directly to derive the weight, instead, the more easily obtained values of surface compressive stress index, design horsepower, and gearbox input speed are used along with various factors for special features, etc Also included, are the weight effects of bearing supports, output shaft, combining stages of gearing and special features such as clutches The use of graphs enables the rapid selection of the factors needed for the application of this weight determination method A technique for deriving the weight of accessory gearboxes is also presented, along with several examples of the application of the weight estimating method for typical gearboxes A plot of the statistical accuracy of this method is also presented (Author) A77-12194 * ff Application of advanced technology to future long-range aircraft 0 E Schrader (NASA, Langley Research Center, Hampton, Va ) Society of Allied Weight Engineers, Annual Con- ference, 35th, Philadelphia, Pa , May 24-26, 1976, Paper 1126 45 p 9 refs The objective of this paper is to provide an overview assessment of three separate programs at Langley Research Center that have incorporated advanced technology into the design of long-range passenger and cargo aircraft The first technology centers around the use of an span-loaded cargo aircraft with the payload distributed along the wing This concept has the potential for reduced structural weights The second technology is the application of laminar flow control (LFC) to the aircraft to reduce the aerodynamic drag The use of LFC can reduce the fuel requirements during long-range cruise The last program evaluates the production of alternate aircraft fuels from coal and the use-of liquid hydrogen as an aircraft fuel Coal-derived hydrogen as an aircraft fuel offers both the prospect for reduced dependence on petroleum fuels and improved performance for long-range aircraft (Author) A77-12195 •/' The next-generation subsonic transport D P Marsh (Douglas Aircraft Co , Long Beach, Calif ) Society of Allied Weight Engineers, Annual Conference, 35th, Philadelphia, Pa, May 24-26, 1976, Paper 1127 8 p The design approach used at McDonnell Douglas to satisfy the market requirements and operating economics for a next-generation commercial subsonic transport is discussed The principal near-term design objectives are reduced fuel consumption and the development of a configuration, to satisfy this goal, on the basis of wing geometry studies, advanced technology applications, and fuselage and engine configuration studies The results of the configuration development studies, marketing reports, and airline inputs indicate that the next-generation transport will incorporate the following features all-new wing design with higher aspect ratios for reduced drag, advanced high-lift systems for reduced noise and wing area, in- corporation of such advanced technologies as supercritical wing, composite materials, and relaxed static stability to reduce fuel consumption and weight, reduced passenger capacity over current wide-body transports to meet market requirements, reduced cruise speed for minimum operating costs, and commonality with existing transport aircraft to reduce development costs V P A77-12201 # Aircraft loadabihty parameters - Some results of an airline survey N J Carraway (Lockheed-California Co, Burbank, Calif ( Society of Allied Weight Engineers, Annual Conference, 35th, Philadelphia, Pa, May 24-26, 1976, Paper 1146 12 p A survey was conducted to obtain current information from commercial airlines regarding those items which affect load flexibili- ty A summary is presented of the data obtained to date These data are being used to aid the development of a method for optimizing the initial construction of a design center-of-gravity envelope for commercial aircraft F G M A77-12202 ff Operational mass properties data for military aircraft - Data formulation, presentation and usage T Dills (General Dynamics Corp, Fort Worth, Tex ) Society of Allied Weight Engineers, Annual Conference, 35th, Philadelphia, Pa, May 24 26, 1976, Paper 1147 56 p A77-12206 Structural tests of aerodynamic surfaces - A systems approach to analysis and design K Goldenberg (Albany Medical College, Albany, N Y ) Journal of Testing and Evaluation, vol 4, IMov 1976, p 418-424 7 refs 10 A77-12460 One of the primary tasks in structural ground testing of aerodynamic surfaces is to resolve complex, curvilinear pressure fields into applied test loads A systems approach is presented which optimally performs this analysis and integrates it with major subsequent phases of the engineering operation specifically, correla- tion of actual/theoretical shear and moment curves, selection of loading pad geometry, test fixture analysis, and graphical display of the results Computer programs are available to calculate these results rapidly using curve fitting and statistical methods modified for test data evaluation (Author) A77-12218 Lifting-surface theory of straight cascades of swept blades A F Falcao (Institute Superior Tecmco, Lisbon, Portugal) International Journal of Mechanical Sciences, vol 18, no 6, 1976, p 313-320 17 refs Research supported by the Institute de Alta Culture Lifting-line and lifting-surface expressions are derived for the steady irrotational incompressible flow through a straight cascade of swept blades of finite length and constant loading along the span, the mam object being to study the three-dimensional perturbations arising from the presence of the end walls and to determine the warped shape of the blade camber surface The blade axis is taken perpendicular to the blade-to-blade direction, as an approximation to conical flow with radially set blades The solution, in terms of the velocity potential, is based on the author's analytical expressions for cascades of unswept blades of varying circulation along the span Numerical results are presented for a wide range of cascade geometries, and the effects of several cascade parameters upon the wall-induced three-dimensional perturbations are discussed In partic- ular, it has been found, for most geometries used in practice, that a good approximation is obtained by superposing the disturbances due to the two walls separately (Author) A77-12428 « The stochastic .control of the F 8C aircraft using the multiple model adaptive control /MMAC/ method M Athans, K -P Dunn, C S Greene, W H Lee, N R Sandell, Jr, I Segall, and A S Willsky (MIT, Cambridge, Mass ) In Conference on Decision and Control, 6th, and Symposium on Adaptive Processes, 14th, Houston, Tex, December 10-12, 1975, Proceedings New York, Institute of Electrical and Electronics Engineers, Inc, 1975, p 217-228 15 refs Grants No NGL-22-009-124, No NsG 1018, No AF AFOSR-72-2273 The purpose of this paper is to summarize results obtained for the adaptive control of the F-8C aircraft using the so-called MMAC method The discussion includes the selection of the performance criteria for both the lateral and the longitudinal dynamics, the design of the Kalman filters for different flight conditions, the 'identifica tion' aspects of the design using hypothesis testing ideas, and the performance of the closed loop adaptive system (Author) A77-12444 Optimal control for the rolling pullout maneuver of a modern fighter aircraft G Satyanarayana, U R Prasad, and I G Sarma (Indian Institute of Science, Bangalore, India) In Conference on Decision and Control, 6th, and Symposium on Adaptive Processes, 14th, Houston, Tex , December 10 12, 1975, Proceedings New York, Institute of Electrical and Electronics Engineers, Inc , 1975, p 443, 444 Optimal control laws for the elevator and ailerons of a mode-n fighter aircraft in a rolling pullout maneuver are obtained to determine the limiting performance In the analysis, a five-degree-of freedom model is employed which incorporates many physical phenomena peculiar to the maneuver and also takes account of various disturbance products Necessary conditions for optimality are derived, and the problem is solved by the conjugate-gradient method for three sets of flight cond.tions The results show that the roll rate should be about 250 deg/sec, the maximum normal acceleration should not exceed 5 g's, the minimum time required for the maneuver is less than 1 sec, the ailerons must be reversed at some stage so that the roll rate becomes zero when the aircraft has rolled through the desired angle, and the elevator deflection should be maximum at the end of the maneuver since the normal acceleration must be maximum only at the end F G M A77-12448 On the identification of state-denvative- coupled systems J M Mendel (Southern California, University, Los Angeles, Calif) In Conference on Decision and Control, 6th, and Symposium on Adaptive Processes, 14th, Houston, Tex , December 10-12, 1975, Proceedings New York, Institute of Electrical and Electronics Engineers, Inc, 1975, p 529-533 8 refs NSF Grant No GK-41482 A description is given of a sequence of tests for establishing the identifiability of structural parameters which are associated with a given structural state equation, from reduced form parameters, which are associated with a reduced form state equation A test involving the determination of the rank of a matrix is developed to make a use of either structural parameters or reduced form parameters possible The application of the identifiability tests is illustrated with the aid of an example G R A77-12452 The pursuit-evasion problem of two aircraft in a horizontal plane N Rajan and U R Prasad (Indian Institute of Science, Bangalore, India) In Conference on Decision and Control, 6th, and •Symposium on Adaptive Processes, 14th, Houston, Tex , December 10-12, 1975, Proceedings New York, Institute of Electrical and Electronics Engineers, Inc, 1975, p 635, 636 5 refs The pursuit-evasion problem of two aircraft in a horizontal plane is modeled as a zerosum differential game with capture time as payoff The aircraft are modeled as point masses with thrust and bank angle controls The games of kind and degree for this differential game are solved (Author) A77-12455 R & D project cost and schedule realism - A risk analysis approach D C Borgman (U S Army, Air Mobility Research and Development Laboratory, St Louis, Mo ) and J D Hwang (U S Army, Air Mobility Research and Development Laboratory, Moffett Field, Calif ) In Conference on Decision and Control, 6th, and Symposium on Adaptive Processes, 14th, Houston, Tex, December 10-12, 1975, Proceedings New York, Institute of Electrical and Electronics Engineers, Inc , 1975, p 731 733 5 refs All project managers strive for cost and schedule realism The Department of the Army has established a novel concept called the Total Risk Assessing Cost Estimate (TRACE)' to develop a new program cost-estimation procedure for research, development, test and evaluation cost realism Such a procedure properly accom- modates program uncertainties/risks inherent to specific work elements, and the high-risk work elements are budgeted accordingly The purpose of this paper is to propose such a procedure which subscribes to a risk analysis approach and satisfies the essential elements of the TRACE concept The procedure consists of two models a cost impact model and a schedule variance model Applications of the procedure to the NASA/Army Tilt Rotor Research Aircraft Project are also presented for illustration (Author) A77-12460 Application of Liapunov model - Tracking parameter identification for the CH-47 helicopter R L Carroll (South Carolina, University, Columbia, SC) In Conference on 1 1 A77-12470 Decis'on and Control, 6th, and Symposium on Adaptive Processes, 14th, Houston, Tex, December 10-12, 1975, Proceedings New York, Institute of Electrical and Electronics Engineers, Inc. 1975, p 858-863 7 refs This paper reports results obtained in an evaluation study of model-tracking parameter identification for the optimally controlled CH-47 helicopter while in flight The model is made to track some of the helicopter parameters by means of Liapunov-designed adaptive algorithm The topics investigated include the accuracy of identifica- tion of the time-varying vehicle and the effect of controller feedback upon the performance of the identifier (Author) A77-12470 New orientations of intergovernmental organi- zations of civil aviation (Nouvelles orientations des organismes intergouvernementaux d'aviation civile) M G Folliot (Paris II, Universite, Paris, France) Revue Franpaise de Droit Aerien, vol 30, July-Sept 1976, p 313-321 13 refs In French Political, economic, and legal changes in international civil aviation relations are discussed with particular reference to the International Civil Aviation Organization The politicization of aviation organizations whose function was formerly to deal with technical problems is considered The problem of regionalism is examined in its two aspects of cooperation and competition The attitudes of individual states to such questions as legal organization, and fares are discussed B J A77-12472 Responsibilities and assurances with regard to cargo transport - Air transport law (Responsabilites et assurances en matiere de transports de marchandises - Droit applicable speciale- rnent en matiere de transport aerien) R R Nys (Bruxelles, Universite Libre, Sabena S A , Brussels, Belgium) Revue Franfaise de Droit Aerien, vol 30, July-Sept 1976, p 329-344 In French The paper examines the competition of internal state laws and international conventions in the field of air transport of cargo Attention is given to the Warsaw Convention of 1929, the Conven- tion of Brussels of 1924, the protocol signed at the Hague in 1955, and the protocol of Guatemala of 1971 B J A77-12502 Equation solution accuracy in calculating jet engine characteristics A M Akhmedzianov, S Kh Aksel'rod, and Kh S Gumerov (Aviatsionnaia Tekhnika, vol 19, no 1, 1976, p 5-10) Soviet Aeronautics, vol 19, no 1, 1976, p 1 5 5 refs Translation The calculation of engine characteristics is conventionally reduced to ensuring an accurate selection of the position of the operating point on the characteristic curve of the compressor In the present paper, a method is proposed for determining the accuracy to which the selection conditions are satisfied for solving a system of equations in the computation of the characteristics of a turbojet engine It is shown that to achieve convergence of the solution to this system of equations by computer-aided selection (at a prescribed accuracy of such output parameters as thrust and fuel consumption), a specific relation must be used to determine the error in the selection conditions This relation must be precisely satisfied in the computer-aided determination of the turbojet engine characteristics V P A77-12503 Air-cooled turbine cascade effectiveness crite- rion E N Bogomolov (Aviatsionnaia Tekhnika, vol 19, no 1, 1976, p 11-20 ) Sower Aeronautics, vol 19, no 1,1976, p 6-12 10 refs Translation It is proposed to use a parameter that indicates the possible relative increase in kinetic energy behind the blading caused by a blade-temperature drop as the efficiency criterion for an air-cooled turbine cascade The criterion takes into account the influence of cooling on the gasdynamic characteristics of the cascade Cascades with internal cooling and with film cooling of the blade trailing edge are compared, and methods of evaluating analytically the efficiency of such cascades are examined Relations are derived for calculating the efficiency of trailmg-edge cooling with allowance for heat input from the butt end of the trailing edge V P A77-12504 Off-design regimes of asymmetric nozzles with supersonic inlet velocity L M Vetlutskaia, V N Zudov, and V V Zatoloka (Aviatsionnaia Tekhnika, vol 19, no 1, 1976, p 21-27) Soviet Aeronautics, vol 19, no 1, 1976, p 13-17 5 refs Translation The flow in plane asymmetric nozzles of different geometry is analyzed for the case of a variable supersonic velocity at the nozzle inlet The thrust characteristics of nozzles of fixed geometry and of optimal nozzles of identical length are compared for a specific inlet Mach number The influence of external pressure on the force characteristics of a nozzle is demonstrated V P A77-12509 Thermal analysis of flight vehicle compart- ment structure N M Krutova, G B Petrazhitskn, and A M Pylaev (Aviatsionnaia Tekhnika, vol 19, no 1, 1976, p 55-60) Sower Aeronautics, vol 19, no 1,1976, p 40-44 Translation A method is proposed for solving systems of heat conduction problems that are interrelated solely by linear inclusion of a set of functional parameters The solution is reduced to obtaining in- dependent particular solutions to each problem of the system and to subsequent treatment of algebraic equations or linear systems As an example, the method is applied to the analysis of a steady periodic mode, and also of a general regular mode of the first kind, for the case where N subsystems with strong thermal couplings interact with each other V P A77-12511 Experimental study of combustion time in two-stage combustion process A V Mosm, O V Strogonov, V A Shchukm, and A V Talantov (Aviatsionnaia Tekhnika, vol 19, no 1, 1976, p 67-70) Soviet Aeronautics, vol 19, no 1, 1976, p 50-52 7 refs Translation The burning process in afterburners of gas turbine engines takes place in mixtures diluted by combustion products The combustion period in turbulent flows in such mixtures is studied experimentally, showing that the combustion products affect appreciably the combustion period The empirical relationships obtained are inter- preted in terms of the postulates of a 'surface' model of turbulent combustion V P A77-12513 Selection of compressor pressure ratio of small GTE installed in bypass turbojet engine fan duct B D Fishbein (Aviatsionnaia Tekhnika, vol 19, no 1, 1976, p 78-85) Soviet Aeronautics, vol 19, no 1,1976, p 58-62 9 refs Translation The problem of determining the pressure ratio that is optimal with respect to thrust for the compressor for a small-scale gas-turbine engine in the bypass dust is analyzed The compressor pressure ratio is plotted against the pressure ratio of the fan, against the gas temperature in front of the turbine of the small-scale engine, and against the parameters of the engine inlet It is shown that a pressure ratio between 4 and 5 provides optimal thrust characteristics V P A77-12515 Penetration and mixing of liquid injected into supersonic transverse gas stream Z G Shaikhutdinov and V M Klevansku (Aviatsionnaia Tekhnika, vol 19, no 1, 1976, p 99-108 ) 12 A77-12554 Sower Aeronautics, vol 19, no 1, 1976, p 74-80 7 refs Translation Photographic methods do not yield correct quantitative relation- ships in studies of secondary flows propagating in a cross-wind The 'thermometric' method proposed makes it possible to study the spatial dispersion boundaries of the injected fluid and the mixing characteristics of the injected stream The penetration depth, the shape of the cross section, and the mixing characteristics are plotted for water jet< injected at pressures of 4 to 80 bars into gas flow of Mach number 2 Sand a temperature of 500 K V P A77-12517 Heat transfer in tube entrance segment with initial flow swirl and transverse injection V K Shchukin, A A Khalatov, and A V Kozhevmkov (Aviatsionnaia Tekhmka, vol 19, no 1,l976,p 115-121 I Soviet Aeronautics, vol 19, no 1,1976,p 86-90 8 refs Translation A77-12520 Study of flow swirl influence on axiradial diffuser effectiveness I G Gogolev, A M Drokonov, and V M Sivaev (Aviatsionnaia Tekhmka, vol 19, no 1, 1976, p 132 135 ) Soviet Aeronautics, vol 19, no 1,1976, p 102105 Translation The economic efficiency gas turbine units can be improved by using an exit cone that will operate efficiently over a range of turbine modes If, however, the mode of operation of the preceeding stage is changed, the flow conditions at the diffusor inlet, in particular, the flow direction, will also change The wind-tunnel study described was aimed at studying the influence of swirl on the economic efficiency of mixed-flow diffusor with an expansion ratio of 1 8 The diagrammed results of the study are discussed V P recuperative (fixed) heat exchanger which uses heat pipes to offset the intrinsic drawbacks of recuperative heat exchangers, such as a low recovery factor and high hydraulic pressure losses along the hot gas duct V P A77-12551 Computational methods and problems in aero- nautical fluid dynamics Edited by B L Hewitt (British Aircraft Corp, Ltd, Weybridge, Surrey, England), C R Illmgworth (Manchester, Victoria University, Manchester, England), R C Lock (Royal Aircraft Establishment, Farnborough, Hants , England), K W Mangier (Southampton, University, Southampton, England), J H McDonnell (British Aircraft Corp, Ltd, Weybridge, Surrey, England), C Richards (Institute of Mathematics and its Applications, Southend-on-Sea, Essex, England), and F Walkden (Salford, Uni- versity, Salford, Lanes , England) London and New York, Academic Press, 1976 536 p $2975 The papers collected provide a review of recent developments in numerical solution techniques for aeronautical flows Some papers review basic techniques as well, while others present new concepts *or specific problems Topics covered include methods for elliptic problems in external aerodynamics, compressible subcritical flow through axially symmetric sharp-lipped orifices and nozzles, finite element and difference methods for cascades, problems of unsteady flow past aircraft, an extended integral equation method for the unsteady transonic flow past a two dimensional airfoil, relaxation near a sonic line, steady supersonic flowfields with embedded subsonic regions, and numerical solution of turbulent swirling flows P T H A77-12521 Determination of magnitudes of the pa- rameters characterizing ducted airscoop operation downstream B L Zel'dovich, L M Kotliar, and E D Nesterov (Aviatsionnaia Tekhmka, vol 19, no 1,1976, p 136-140 ) Soviet Aeronautics, vol 19, no 1,1976, p 106-110 8 refs Translation The impingement of a nozzle jet against the endplate of an external target type thrust reverser is analyzed with the framework of the theory of ideal fluid jets Specifically, the two-dimensional problems of the impingement of an ideal imponderable jet expelled from a semi-infinite nozzle with straight parallel walls onto two plates arranged symmetrically with respect to the channel axis is solved by the method of singular points A relationship between the geometrical and physical parameters of the problem is established V P A77-12522 Analytic and experimental study of turbine rotor blade temperature K M Iskakov, A A Panteleev, V A Trushin, and V N Fedorov (Aviatsionnaia Tekhmka, vol 19, no 1, 1976, p 141 146) Soviet Aeronautics, vol 19, no 1, 1976, p 111-115 7 refs Translation A numerical finite-difference scheme is proposed for calculating the thermal state of turbine blades with a transverse cooling-air flow The technique can be used to determine the temperature distribu- tions over the blade contour and over the wall thickness of the blade, and the behavior of the cooling-air temperature along the path from the leading edge to the exit slot at the trailing edge The theoretical results are found to correlate with thermocouple and pyrometer measurements V P A77-12528 Heat-pipe regenerator for gas turbine engine V K Shchukin, I I Mosm. N V Lokai, and I I Fedorov (Aviatsionnaia Tekhmka, vol 19, no 1, 1976, p 172-175 ) Sower Aeronautics, vol 19, no 1,1976, p 140-143 Translation The principles of operation of gas-turbine-engine regenerator of a fundamentally new design are discussed The device is essentially a A77-12552 Practical requirements in industry H Hitch- IB'itish Aircraft Corp, Ltd, Weybridge, Surrey, England) In Computational methods and problems in aeronautical fluid dynam ics London and New York, Academic Press 1976, p 1-14 6 refs The present procedure of potential flow solutions and general boundary layer calculations for aircraft aerodynamic calculations is a makeshift procedure that contains no real statement about separa tion, drag, buffet, or sensitivity of the design to these phenomena, and moreover, the boundary layer calculations are only two dimensional For modern aircraft, especially those featuring super critical wings, computational methods are required that produce reliable drag estimates for three-dimensional, compressible, viscous flows over real geometries, in which separation and shock conditions are produced in the process Wind tunnels for the Reynolds number range 20 to 40 million will be required, along with computers of greater performance than present ones PTH A77-12554 Methods for elliptic problems in external aerodynamics R C Lock (Royal Aircraft Establishment, Farn- borough, Hants, England) In Computational methods and prob lems in aeronautical fluid dynamics London and New York, Academic Press, 1976, p 53-99 24 refs The paper reviews some of the more important methods for calculating the inviscid, incompressible, subsonic flow past aero dynamic bodies The most efficient methods of solution are obtained by representing the flow by a distribution of singularities - sources, doublets, or vortices placed either on or inside the body and also, for lifting systems, on the vortex wake behind it Considerable attention is given to the panel method for incompressible flows For two-dimensional compressible flow, a conformal mapping technique with finite-difference approximation is described PTH 13 A77-12555 A77-12555 Compressible subcritical flow through axial I y symmetric sharp-lipped orifices and nozzles G M Alder (Edinburgh, University, Edinburgh, Scotland) In Computational methods and problems in aeronautical fluid dynamics London and New York, Academic Press, 1976, p 100-116 16 refs The paper describes a finite difference method for the solution of irrotational axially symmetric subcritical flows of an ideal gas through conical nozzles Transformation to hodograph coordinates maps the whole flowfield into a rectangle and allows a rectangular finite difference mesh to be used The error in the solution may be estimated by considering different mesh node densities Typical results for both axially symmetric and two-dimensional flows are given P T H A77-12559 Free vortex sheets. K W Mangier (South- ampton, University, Southampton, England) In Computational methods and problems in aeronautical fluid dynamics 12551 02-02) London and New York, Academic Press, 1976, p 198-213 18 refs The paper is concerned with the analysis of the shape and strength of the vortex sheet which is shed from the trailing edge of a slender delta wing or from a lifting wing at incidence For the delta wing, the pressure condition on the vortex sheet is nonlinear, and the problem is essentially two-dimensional. An iterative procedure for the core of the vortex sheet is described For a vortex sheet behind a lifting wing, a doublet source distribution is used, and the panel method is used to perform numerical calculations of velocities P.TH A77-12556 -Subsonic flows in turbomachmes H Marsh (Durham, University, Durham, England) In Computational methods and problems m aeronautical fluid dynamics London and New York, Academic Press, 1976, p 117 139 22 refs The paper discusses the basic mathematical model for the flow in turbomachmes as developed by Wu for a single cascade The discussion concentrates on the two main methods for solving the governing equations, the method of streamline curvature and the through-flow analysis involving finite differences, for calculating the flow on a mean blade-like surface between two blades The relationship between the two methods is discussed together with their limitation on Mach number Some areas where the techniques need further refinement are indicated, such as transonic flows, unsteady flows, the use of a consistent loss model, wall boundary layers, and secondary flows P T H A77-12557 Finite element and difference methods for cascades M J O'Carroll and L A Morgan (Lanchester Polytechnic, Coventry, England) In Computational methods and problems in aeronautical fluid dynamics London and New York, Academic Press, 1976, p 140-157 14 refs The paper is concerned with finding rapid iterative techniques for linearized flow problems on skew nets as arise in the numerical solution of the three dimensional steady, mviscid, incompressible blade-to-blade cascade flow Comparisons are made between finite element and finite difference techniques, with a test cascade of known exact solution being used to demonstrate the discretization accuracy of the methods The two methods are compared for block successive overrelaxation performance on a skewed net The element equations take about three times longer to assemble that the comparable difference equations, and convergence of iterations is of similar speed Optimal convergence is guaranteed for the element equations, but not for the difference ones The two methods give results of similar discretization accuracy, but the element method lends itself more easily to local net refinement P T H A77-12560 Some problems of unsteady flow about air- craft G J Hancock (Queen Mary College, London, England) In Computational methods and problems in aeronautical fluid dynam- ics London and New York, Academic Press, 1976, p 214241 15 refs The paper discusses some methods used to study the problem of aircraft wings in unsteady motion In particular, some of the extensions of the Smith approach to unsteady problems are described Some problems associated with the use of vortex lattice methods for calculating steady and unsteady load characteristics on finite wings are also investigated P T H A77-12561 Transonic flows M G Hall (Royal Aircraft Establishment, Farnborough, Hants, England) In Computational methods and problems in aeronautical fluid dynamics London and New York, Academic Press, 1976, p 242269 26 refs The paper outlines some of the recent approaches to the problem of mixed flow calculations, giving attention to integral equation methods, the method of integral relaxations, and finite difference methods Closer attention is then given to the relaxation type of finite difference method, which is illustrated by an outline of the solution of the transonic small perturbation equation for the flow past a two dimensional airfoil Developments and extensions of the basic relaxation method are then considered, and shortcomings and remaining problems to be worked on are pointed out P T H A77-12562 An extended integral equation method for the steady transonic flow past a two-dimensional aerofoil D Nixon (Queen Mary College, London, England) In Computational methods and problems in aeronautical fluid dynamics London and New York, Academic Press, 1976, p 270-289 12 refs A77-12558 The finite element method applied to fluid mechanics J H. Argyris and P C. Dunne (Stuttgart, Universitat, Stuttgart, West Germany) In Computational methods and problems in aeronautical fluid dynamics London and New York, Academic Press, 1976, p. 158-197 21 refs. The paper reviews the basic properties of the main types of elements used in finite element computations, and then presents some examples of the use of the finite element technique in basic fluid dynamics problems The simplest type of problem is one with positive definite quadratic forms, illustrated by plane incompressible flow in a duct A simple membrane analogy and a more complex plate analogy from solid mechanics are developed for an incom- pressible potential flow problem and the problem of Stokes flow. P T H A77-12563 Relaxation near a sonic line A Roberts (British Aircraft Corp, Ltd, Weybndge, Surrey, England) In Computational methods and problems m aeronautical fluid dynam ics London and New York, Academic Press, 1976, p 290-326 The paper is concerned with achieving rapid relaxation over the interfaces between the supersonic and subsonic regions describing the complete transonic flow past a subsonic lifting aircraft The physical plane is regarded as the near field inside a rectangular working section together with the far field The steady isentropic field equation is to be satisfied over the whole physical plane, and the 14 A77-12872 limiting form of the field equation is the Prandtl-Glauert equation The nonlinear isentropic field equation is solved indirectly with the aid of elliptic solvers within iterative loops This gives rapid local convergence where the velocity is near the freestream value A wall relaxation sequence based on Laplacian field concepts gives rapid convergence when the compressibility effects are small P T H A77-12564 A transonic hodograph theory for aerofoil design J W Boerstoel (Nationaal Luchtvaartlaboratormm, Amsterdam, Netherlands) In Computational methods and problems in aeronautical fluid dynamics London and New York, Academic Press, 1976, p 327 353 9 refs Research supported by the Netherlands Agency for Aerospace Programs Theory, implementation, and typical results are described for a hodograph method for transonic airfoil design The method is based on the approximate solution of Tricomi boundary value problems for the mixed elliptic-hyperbolic hodograph equations, where appioxi- mation is achieved by a linear combination of solutions of the hodograph equations Some examples of computed airfoils and their design pressure distributions are shown P T H. A77-12565 Supersonic flows F Walkden (Salford, Univer- sity, Salford, Lanes, England) In Computational methods and problems in aeronautical fluid dynamics London and New York, Academic Press, 1976, p 354382 13 refs Research supported by the Science Research Council This review paper is concerned with methods and problems associated with the computation of steady flowfields produced when a body is placed in a uniform supersonic stream Attention is restricted to body shapes such that the effects of viscosity are confined to narrow layers lying close to body surfaces In these cases good predictions of both surface pressures and flow outside the boundary layers can be obtained by solving equations of motion in which the effects of fluid viscosity are neglected Distinctive features of numerical methods which have been used successfully to calculate a variety of steady inviscid supersonic flowfields are then examined Some numerical results are presented (Author) A77-12566 Applications of linearised supersonic wing theory to the calculation of some aircraft interference flows M Purshouse and R K Nangia (British Aircraft Corp , Ltd , Weybndge, Surrey, England) In Computational methods and problems in aeronautical fluid dynamics London and New York, Academic Press, 1976, p 383-423 25 refs Research sup- ported by the British Aircraft Corp The Mach box method is used to provide a numerical formula- tion of linearized supersonic wing theory for calculating some typical aircraft interference flows In this method, the disturbance regions in a wing plane are overlaid by a grid of rectangular constant source strength Mach boxes, which become square when a coordinate transformation to the equivalent problem at Mach 1 414 is in- troduced Flow perturbations produced at a point in the downstream zone from a source are calculated by appropriate aerodynamic influence coefficient relations In the calculation of an underwing flowfield at a typical intake location, the effect of leading edge droop on the intake flowfield is studied Other applications are the calculation of the interference field at a fin location arising from asymmetric elevon deflection, and the mutual interference field produced by two 65-deg-sweep delta wings P T H analogn k raschetu deformatsii polzuchesti stekloplastikov v nesta- tsionarnom pole temperatur) lu S Pervushm, V P Pavlov, and V V Zamullm (Ufimskn Aviatsionnyi Institut, Ufa, USSR). Problemy Prochnosti, July 1976, p 27-29 In Russian A77-12583 # Effect of structural state on the high- temperature long-term strength of molybdenum (Vliiame struktumogo sostoianna na vysokotemperaturnuiu dlitel'nuiu proch- nost' mohbdena) N P Drozd, R K. Ivashchenko, G G Maksi- movich, lu V Mil'man, N M Sinchenko, and V J Trefilov (Akaderniia'Nauk Ukramskoi SSR, IPM, Kiev, Akademna Nauk Ukramskoi SSR, Fiziko-Mekhanicheskii Institut, Lvov, Ukrainian SSR) Problemy Prochnosti, July 1976, p. 39-43 26 refs In Russian A77-12630 If Nonlinear analysis of flows generated by the impulsive motion of a wedge (Nelmemyi analiz techenna, mitsiirue- mogo vnezapnym dvizhemem klma) V V Titarenko PMTF • Zhurnal Pnkladnoi Mekhaniki i Tekhmcheskoi Fiziki, May-June 1976, p 37-47 15 refs In Russian The method of matched asymptotfc expansions is applied to the analysis of some self-simulating problems concerning the impulsive motion of a wedge The nature of the wave boundary of a perturbed region is identified Solutions are obtained which, in the second approximation, describe flows behind weak shock fronts propagating in a gas at rest and behind the fronts of weak discontinuity lines, propagating in certain homogeneous flows A boundary value problem is formulated, whose solution describes, in the first approximation, flows near points of interaction of fronts The existence of similarity laws for such flows is demonstrated V P A77-12680 * Two-phase turbine engines D G Elliott (Cali- fornia Institute of Technology, Jet Propulsion Laboratory, Pasadena, Biphase Engines, Inc , Santa Monica, Call' ) and L G Hays (Biphase Engines, Inc, Santa Monica, Calif ) In Intersociety Energy Conver- sion Engineering Conference, 11th, State Line, Nev, September 12-17, 1976, Proceedings Volume 1 New York, American Institute of Chemical Engineers, 1976, p 222-228 11 refs Contracts No E(04-3)-1228, No E(04-3)-1207, No E(04-3)-1255 A description is given of a two-phase turbine which utilizes a uniform mixture of gas and liquid accelerated in nozzles of the types reported by Elliott and Wemberg (1968) The mixture acts directly on an axial flow or tangential impulse turbine or is separated into gas and liquid streams which operate separately on a gas turbine and a hydraulic turbine The basic two-phase cycles are examined, taking into account working fluids, aspects of nozzle expansion, details of turbine cycle operation, and the effect of mixture ratio variation Attention is also given to two-phase nozzle efficiency, two-phase turbine operating characteristics and efficiencies, separator turbines, and impulse turbine experiments GR A77-12778 Survey of hydrogen energy application pro- jects. R E Billings (Billings Energy Corp, Provo, Utah) In Intersociety Energy Conversion Engineering Conference, 11th, State Line, Nev, September 12-17, 1976, Proceedings Volume 1 New York, American Institute of Chemical Engineers, 1976, p 972-977 17 refs Contemporary U S hydrogen application research projects are reviewed Specific emphasis is placed on aircraft, industrial and domestic applications, electrical generation and storage, vehicles, and farms Although the study does not attempt to evaluate the technical feasibility or status of individual projects, some prognostications are made as to future hydrogen energy applications (Author) A77-12579 # Application of the time-temperature analogy to the calculation of the total creep of fiberglass plastics in an unsteady temperature field (O pnmenenn temperaturno-vremennoi A77-12872 Design consideration for the Dameus rotor. R W Thresher and R W Wilson (Ohio State University, Corvallis, 15 A77-12927 Ohio) In IntetsuCiety Energy Conversion Engineering Conference, 11th, State Line, Nev , September 12-17, 1976, Proceedings Volume 2 New York, American Institute of Chemical Engineers, 1976, p 1787-1794 20 refs Research supported by the Oregon People's Utility Districts Directors' Association, Contract No AT(04-3)-1075 The objective of this study was to determine the performance, operating and load characteristics of Darneus wind turbines The performance of Darneus Rotors was examined using the flow model of Wilson and Lissaman The blades of the rotors were assumed to be of a parabolic shape with the vertical height equal to twice the maximum radius Performance curves and operating envelopes for a family of Darneus Rotors with diameters ranging from 7 62 to 30 49 meters were determined Aerodynamic loads are also presented for various blade positions and operating conditions The rotors have been selected to reach maximum rated shaft power at a wind speed of 8 94 m/s (20 mph) and have a cut-off wind speed of 20 12 m/s (45 mph) A structural analysis of the Darneus vertical axis wind turbine is also presented The emphasis was placed on obtaining an estimate for the lead-lag bendmg-torsion stresses and deformations To accomplish this task, a rather elementary model was developed where several simplifying assumptions were used, both a maximum stress based design and a maximum deformation based design were developed (Author) A77-12927 The technical basis for a national civil aviation research, technology, and development /RT & D/ policy, Proceedings of the Workshop Conference, Crystal City, Va , March 10-12,1976 Conference sponsored by the American Institute of Aeronautics and Astronautics and National Science Foundation, NSF Grant No C-76-12038 Edited by J Grey (American Institute of Aeronautics and Astronautics, New York, N Y ) New York, American Institute of Aeronautics and Astronautics, Inc , 1976 83 p $8 50 Technology requirements for civil air transportation systems projected for operational status circa 2000 AD are emphasized, with attention also given to developments probably requiring longer lead times Major subject areas are aerodynamics and configurations, structures and materials, propulsion, air operations and ground support technology and organization, airport design and access to terminals, testing and evaluation facilities The entire spectrum of speeds and aircraft flying modes, from subsonic to hypersonic, and including CTOL, STOL, VTOL and QVTOL, new rotorcraft con- cepts, and hypersonic cruise aircraft, is encompassed in the survey Advances in wind tunnels, materials technology, nondestructive evaluation techniques, crashworthmess, and development of alterna- tive fuels and fuel consumption reduction are also dealt with R D V 16 N77-10007 STAR ENTRIES N77-10001* National Aeronautics and Space Administration Langley Research Center Langley Station Va WINGTIP VORTEX DISSIPATOR FOR AIRCRAFT Patent James C Patterson Jr. inventor (to NASA) Issued 5 Oct 1976 6 p Filed 28 May 1974 Supersedes N74-26456 (12 - 16 p 1855) (NASA-Case-LAR-11645-1 US-Patent-3 984 070 US-Patem-Appl-SN-473973 US-Patent-Class-244-130 US-Patent-Class-244-113) Avail US Patent Office CSCL 01A A means for attenuating the vortex created at aircraft wmgtips which consists of a retractable planar surface transverse to the airstream and attached downstream of the wmgtip which creates a positive pressure gradient |ust downstream from the wing is presented The positive pressure forces a break up of the rotational air flow of the vortex Official Gazette of the U S Patent Office tests not used in the state and parameter identification The identified analytical perturbation model is also compared with a simple theory The method that is applicable both to small scale and full scale dynamic rotor testing is being extended to perturbations from forward flight trim conditions Author N77-10005*# Washington Univ St Louis Mo Dept of Mechanical Engineering METHODS STUDIES ON SYSTEM IDENTIFICATION FROM TRANSIENT ROTOR TESTS Annual Report. Part 1 K H Hohenemser D Banenee and S K Yin Jun 1975 125 p refs (Contract NAS2-7613) (NASA-CR-137965 AR-2-PM) Avail NTIS HC A06/MF A01 CSCL 01A Some of the moie important methods are discussed that have been used or proposed for aircraft parameter identification The methods are classified into two groups Equation error or regression estimates and Bayesian estimates and their derivatives that are based on probabilistic concepts In both of these two groups the cost function can be optimized either globally over the entire time span of the transient or sequentially leading to the formulation of optimum filters Identifiabihty problems and the validation of the estimates are briefly outlined and applications to lifting rotors are discussed Author N77-10003*# Washington Univ St Louis Mo Dept of Mechanical Engineering ROTOR DYNAMIC STATE AND PARAMETER IDENTIFICA- TION. FROM SIMULATED FORWARD FLIGHT TRAN- SIENTS. PART 1 K H Hohenemser D Banerjee and S K Yin Jun 1976 61 p refs (Contract IMAS2-7613) (NASA-CR-137963 Rept-3) Avail NTIS HC A04/MF A01 CSCL 01A State and parameter identifications from simulated forward flight blade flapping measurements are presented The transients were excited by progressing cyclic pitch stirring or by hub stirring with constant stirring acceleration Rotor dynamic inflow models of varying degree of sophistication were used from a one parameter inflow model (equivalent Lock number) to an eight parameter inflow model The maximum likelihood method with assumed fixed measurement error covariance matrix was applied The rotor system equations for both fixed hub and tilting hub are given The identified models were verified by comparing true responses with predicted responses An optimum utilization of the simulated measurement data can be defined From the numerical results it can be anticipated that brief-periods of either accelerated cyclic pitch stirring or of hut) stirring are sufficient to extract with adequate accuracy up to 8 rotor dynamic inflow parameters plus the blade Lock number from the transients Author N77-100O4*# Washington Univ St Louis Mo Dept of Mechanical Engmeenng ROTOR DYNAMIC STATE AND PARAMETER IDENTIFICA- TION FROM SIMULATED FORWARD FLIGHT TRANSIENTS. PART 2 K H Hohenemser and S T Crews Jun 1976 44 p refs (Contract NAS2-7613) (NASA-CR-137964 Rept-3) Avail NTIS HC A03/MF A01 CSCL 01A State and parameter identifications based on a form of the maximum likelihood method are applied to the problem of extracting linear perturbation models including rotor dynamic inflow effects from transient blade f.appmg measurements The estimation method is first studied in computer simulations and then applied to cyclic pitch stirring transients generated with a four-bladed rotor model operating in hovering trim conditions The analytical perturbation models extracted from the transient test results are compared with transient and frequency response N77-10006*# Washington Univ St Louis. Mo Dept of Mechanical Engineering ADDITIONAL EXPERIMENTS WITH A FOUR-BLADED CYCLIC PITCH STIRRING MODEL ROTOR. PART 2 OF SECOND YEARLY REPORT K H Hohenemsei and S T Crews Jun 1975 70 p (Contract NAS2-7613) (NASA-CR-137966) Avail NTIS HC A04/MF A01 CSCL 01A The four bladed pitch stirring rotor model was used in a rotor dynamic wake survey at zero advance ratio covering 2 deg 5 deg and 8 deg collective pitch settings Dynamic wake data were taken in planes 12 and 20 radii below the rotor disk and are to be compared with analytical wake data with parameters to be identified from pitch stirring transients The model was modified to perform such transients The instrumentation developed for this purpose is described together with the method of data acquisition and with the test procedures The hardware and software for several data handling systems are discussed These systems extract from pitch stirring transients the parameters of analytical dynamic rotor wake models Author N77-10O07*# Princeton Univ NJ Dept of Aerospace and Mechanical Sciences SENSITIVITY OF HINGELESS ROTOR BLADE FLAP-LAG STABILITY IN HOVER TO ANALYTICAL MODELLING ASSUMPTIONS H C Curtiss Jr Jan 1975 99 p refs Sponsored in part by Army (Contract NAS2-7615) (NASA-CR-137967 AMS-1236) Avail NTIS HC A05/MF A01 CSCL 01A Prediction of flap-lag stability using a single bending mode for each degree-of-freedom is examined in the case in which the bending modes are assumed to be the same in the flap and lag directions and are independent of pitch angle and stiffness distribution It is shown that this model gives results analogous to those obtained by Ormiston employing a rigid blade model with the blade and hub stiffness represented by springs in the limiting cases of the elastic coupling parameter R = 0 and 1 For intermediate values of R the results are shown to be quite different The mode shape assumptions are shown to result in what is referred to as the parallel spring model in contrast to Ormiston s model which is referred to as a series spring model The similarities and differences between these two models are developed in some details The differences between these two 17 N77-10008 models are examined for various typical rotor blade characteristics Other aspects of the sensitivity of this problem are also considered Author N77-10O08*# Princeton Univ NJ Dept of Aerospace and Mechanical Sciences AN EXPERIMENTAL STUDY OF THE NONLINEAR STIFF- NESS OF A ROTOR BLADE UNDERGOING FLAP. LAG AND TWIST DEFORMATIONS Final Technical Report E H DowellandJ J Traybar Jan 1975 58 p refs Sponsored in part by Army (Contract NAS2-7615) (NASA-CR-'137968 AMS-1194) Avail NTIS HC A04/MF A01 CSCL 01A The large deformation of a cantilevered beam under a gravity tip load was studied The beam root is rotated so that the tip load is oriented at various angles with respect to the beam principal axes Static twist and bending deflections of the tip and bending natural frequencies were measured as a function of tip load magnitude and orientation The experimental data are compared with the results of a recently developed nonlinear structural theory and agreement is good for deflections that are small compared to the beam span with systematic deviations for larger deflections These results support the validity and utility of the nonlinear structural theory for rotor blade applications Author N77-10009*# Princeton Univ. NJ Dept of Aerospace and Mechanical Sciences AN EXPERIMENTAL STUDY OF THE NONLINEAR STIFF- NESS OF A ROTOR BLADE UNDERGOING FLAP. LAG AND TWIST DEFORMATIONS E H DowellandJ J Traybar Dec 1975 79 p refs Sponsored in part by Army (Contract NAS2-7615) (NASA-CR-137969 AMS-1257) Avail NTIS HC A05/MF A01 CSCL 01A This is an addendum to an experimental study of the large deformation of a cantilevered beam under a gravity tip load It adds higher quality and new data on the static twist and bending deflections of the beam The experimental data are compared with a recently developed nonlinear structural theory Agreement is good for deflections that are small compared to the beam span and has systematic deviations for larger deflections Author N77-10010*# Chrysler Corp New Orleans, La Space Div HIGH SUPERSONIC AERODYNAMIC CHARACTERISTICS OF FIVE IRREGULAR PLAWFORM WINGS WITH SYSTEM- ATICALLY VARYING WING FILLET GEOMETRY TESTED IN THE NASA/LARC 4-FOOT UPWT (LEG 2) (LA4SA/B) Oct 1976 478 p ref (Contract NAS9-13247) (NASA-CR-147628 DMS-DR-2297) Avail NTIS HC A21/MF A01 CSCL 01A An experimental and analytical aerodynamic program to develop predesign giJides for irregular planform wings is reported The benefits are linearization of subsonic lift curve slope to high angles of attack and avoidance of subsonic pitch instabilities at high lift by proper tailoring of the planform fillet wing combination while providing the desired hypersonic trim angle and stability The two prime areas of concern are to optimize shuttle orbiter landing and entry characteristics Basic longitudinal aerodynamic characteristics at high supersonic speeds are developed Author N77-10012*# Transemantics Inc Washington D C MECHANISM OF STABILIZATION OF THE 'SEPARATION POINT' OF A VORTEX DURING FLOW OF A STREAM AT LOW SUBSONIC VELOCITY OVER A DELTA WING E A" Truneva NASA Nov 1976 11 p refs Transl into ENGLISH from Izv Vyssh Ucheb Zaved . Aviats Tekh (USSR). no 2. Feb, 1976 p 106-110 (Contract NASw-2792) (NASA-TT-F-17283) Avail NTIS HC A02/MF A01 CSCL 01A The mechanism of vortex separation and displacement of the separation point beginning with the development of the separation phenomenon is presented The results of this research may be valuable for determination of stresses on the wind and investigation of non-stationary aerodynamic characteristics of aircraft with delta wings, in the low velocity region corresponding to takeoff and landing Author N77-10013*# Lockheed-Georgia Co , Marietta NEW DEVELOPMENTS IN BLOWN FLAP NOISE TECHNOL- OGY John S Gibson 1976 12 p refs Presented at the 10th Congr of ICAS Ottawa 3-8 Oct 1976 (Contract NAS1-13870) (NASA-CR-145086) Avail NTIS HC A02/MF A01 CSCL 01A The noise technology relating to blown-flap systems is reviewed There are three general sources of noise tur- bomachmery airframe and the interaction noise of the jet blowing on the flaps The latter noise-source area is the most critical and the mam subject dicussed Characteristics of lower surface blown and upper surface blown systems are described, including noise spectra directivity jet velocity characteristics aircraft geometric variation effects and aircraft forward speed effects Noise reduction concepts are described including slowing down the jet flow field by devices and engine cycle modifications, structural geometry and shielding modifications, local flow field modifications of the passive and active type, and the absorption of noise It is concluded that while there has been considerable progress in the past several years low noise characteristics in blown flap aircraft must be largely built in by better application of low noise principles during the design Author N77-10014*# Lockheed-Georgia Co Marietta NUMERICAL STUDIES OF THREE-DIMENSIONAL BREAK- DOWN IN TRAILING VORTEX WAKES P F Evans and J E Hackett Jun 1976 100 p refs (Contract NAS2-8651) (NASA-CR-137888) Avail NTIS HC A05/MF A01 CSCL 20D Finite element three dimensional relaxation methods are used to calculate the development of vortex wakes behind aircraft for a considerable downstream distance The inclusion of a self- induction term in the solution dependent upon local curvature and vortex core radius permits calculation of finite lifetimes for systems for which infinite life would be predicted two di- mensionally The associated computer program is described together with single-pair twin-pair and multiple-pair studies carried out using it It is found in single-pair studies, that there is a lower limit to the wavelengths at which the Crow-type of instability can occur Below this limit, self-induction effects cause the plane of the disturbance waves to rotate counter to the vortex direction Self induction in two dimensionally generated twin spiral waves causes an increase in axial length which becomes more marked with decreasing initial wavelength The time taken for vortex convergence toward the center plane is correspondingly increased The limited parametric twin-pair study performed suggests that time-to-converge increases with increasing flap span Limited studies of Boeing 747 configurations show correct qualitative response to removal of the outer flap and to gear deployment as compared with wind tunnel and flight test experience Author 18 N77-10027 N77-10017# Office National d Etudes et de Recherches Aerospatiales Pans (France) STUDY OF THE SUBSONIC FLOW AROUND A SHARP LEADING EDGE Gerard Laruelle and Paul Levart Assoc Aecon et Astronautique de France 1976 23 p refs In FRENCH. ENGLISH summary Presented at the 12th Ecole Natl Super de Mecan et d'Aerotech / CEAT Colloq Appl Poitiers France. 5-7 Nov 1975 (AAAF-NT-76-14, ISBN-2-7170-0396-7) Avail NTIS HC A02/MF A01 CEDOCAR. Paris FF 15 (France and EEC) FF 19 (others) The subsonic flow around a sharp leading edge, resulting from the air intake drag of supersonic aircraft flying at subsonic speeds was studied The calculation method used is presented and the simulation of leading edge separation is detailed The experimental setup is presented (S5 wind tunnel at Chalais- Meudon France) The calculated and measured values were compared and found to be satisfactory An adaptation of the computer program for potential flow by finite differences was attempted ESA N77-10O19# Aix-Marseilles Umv (France) Inst de Mecamque des Fluides EXPERIMENTAL STUDY OF THE AERODYNAMICS OF A HELICOPTER ROTOR IN TRANSLATIONAL FLIGHT TWO DIMENSIONAL SIMULATION OF THE EFFECTS DUE TO CYCLIC VARIATIONS OF THE VELOCITY VECTOR [ETUDE EXPERIMENTALE RELATIVE A L'AERODYNAMIQUE D'UN ROTOR D'HELICOPTERE EN VOL DE TRANSLATION SIMULATION EN ECOULEMENT PLAN DES EFFETS DUS AUX VARIATIONS CYCLIQUES DU VECTEUR VITESSE] J Rebont, C Maresca, A Guillermmet, and D Favier Pans Assoc Aeron et Astronautique de France 1976 37 p refs In FRENCH Presented at the 12th Ecole Natl Super de Mecan et d'Aerotech/CEAT Colloq dAerodyn Appl Poitiers. France 5-7 Nov 1975 (AAAF-NT-76-20 ISBN-2-7170-0398-3) Avail NTIS HC A03/MF A01 CEDOCAR Pans FF 25 (France and EEC) FF 29 (others) Aerodynamic characteristics of a helicopter wing harmonic oscillations of which the vector is parallel to the mam flow were studied in a subsonic wind tunnel NACA profile 0012 (1 = 0495 m c = 03 m) was used angle of attack between -20 and 20 deg and Reynolds number between 60 000 and 400.000 It is shown that the instability effects remain small with small angle of attack and with oscillation frequencies below 0 26 ESA N77-10023# ARO Inc . Arnold Air Force Station, Tenn AN INTEGRAL EQUATION METHOD FOR BOUNDARY INTERFERENCE IN A PERFORATED-WALL WIND TUNNEL AT TRANSONIC SPEEDS Final Report. Jan 1974 - Oct 1975 E M Kraft AEDC Apr 1976 84 p refs (AD-A023493 ARO-PWT-TR-75-162 AEDC-TR-76-43) Avail NTIS HC A05/MF A01 CSCL 20/4 The wind tunnel boundary interference at transonic speeds on a thin airfoil in a two-dimensional perforated-wall wind tunnel was determined The interference was found by applying an integral equation method to the nonlinear transonic small disturbance equation including embedded supersonic regions with shock waves The kernels of the ensuing integral equation were replaced by senes approximations and the integrals were evaluated in closed form The iterative technique used to calculate the interference from the integral equation method is shown to converge rapidly and the computing time for the integral equation method is typically an order of magnitude less than present numerical methods As a special case the integral equation method for a thin airfoil in free air was also examined It was found that the introduction of a novel influence function yields, for the first time, a self-contained integral equation for a lifting airfoil In addition a systematic study of the classical assumption used to simplify the integral equation shows that the integral method can provide solutions m good agreement with results from the numerical methods GRA N77-10O24# Air Force Inst of Tech. Wright-Patterson AFB Ohio School of Engineering AN INVESTIGATION OF THE EFFECT ON AERODYNAMIC FORCES CAUSED BY THE ADDITION OF END PLATES TO HELICOPTER ROTOR BLADES M S Thesis Roger J Korenberg Jun 1975 76 p refs (AD-A023541 GAM/AE/74D-11) Avail NTIS HC A05/MF A01 CSCL 01/1 The purpose of this investigation was to determine the effects on lift, drag and thrust produced by a helicopter rotor after installing end plates on the blades Fixed wing end plate theory was applied in a modified form to rotor blade calculations to investigate correlation The results indicate that end plate factors are not satisfactory analytic tools for rotor blade calculations End plates do increase the effective rotor radius and increase the lift at a given angle of attack and RPM. however, there are heavy penalties in power required GRA N77 10026$ Naval Surface Weapons Center White Oak Md NORMAL IMPINGEMENT OF A SUPERSONIC JET ON A PLANE A BASIC STUDY OF SHOCK-INTERFERENCE HEATING Kuei-Yuan Chien 20 Dec 1975 60 p refs (AD-A024511 NSWC/WOL/TR-75-195) Avail NTIS HC A04/MF A01 CSCL 20/4 The problem of a balanced, planar or axisymmetnc. supersonic jet impinging normally on a flat surface has been considered based on an mviscid theory The object of the study was to provide a rational model for calculating shock-interference heating as produced by a type IV shock-interaction pattern The unwanted singularity at a low supersonic Mach number peculiar to scheme I of the one-strip formulation of the method of integral relations as observed by South and by Gummer and Hunt, was successfully removed by the application of the scheme III of the one-strip formulation of the method of integral relations The resulting simultaneous nonlinear algebraic equations were easily solved iteratively by the Newton-Raphson method Sensitivity of the solution on various approximating functions employed was extensively investigated Unlike the findings reported by Gummer and Hunt solutions that satisfy all well-posed boundary conditions can be obtained by the one-strip formulation Results indicate that, for the planar case a rational engineering solution for the stagnation-point velocity gradient (and hence the peak heat- transfer rate) has been obtained For the axisymmetnc case, however solutions appear to be not quite converging A two-strip formulation based on the method of integral relations is also included Author (GRA) N77-10027# McDonnell Aircraft Co St Louis Mo PERFORMANCE OF STEADY AND INTERMITTENT BLOW- ING JET FLAPS AND SPANWISE UPPER SURFACE SLOTS Final Report. Apr 1973 - Nov 1975 W L Ely and F C Berner Nov 1975 514 p refs (Contract F33615-73-C-3056 AF Proj 1476) (AD-A024364 AFFDL-TR-75-128) Avail NTIS HC A22/MF A01 CSCL 20/4 A wind tunnel test was conducted in the NASA Ames 14 foot wind tunnel to determine the performance of steady and pulsed blown jet flaps and constant percent chord spanwise upper surface slots, and to provide wing load and tail power data for a proposed Air Force COMMA (Composite Maneuver Augmentation) RPV flight test program The tests were performed on a 72 1% scale semi-span model of the proposed vehicle with a wing leading edge sweep of 45 deg over a Mach number range of 0 4 to 1 1 The Reynolds number was approximately 4 million per foot and the angle of attack range was -5 deg to -25 deg Full and partial span jet flaps jet flap angles of 30 deg 60 deg and 80 deg 40% and 70% constant chord slots and horizontal tail deflections of 4-2 deg 0 deg -2 deg -4 deg and -6 deg were tested over a blowing momentum coefficient range of 0 to 0 018 Balance forces wing upper and lower surface static pressures wing root bending moment wing tip accelerometer and flow 19 N77-10028 visualization data were obtained The results in general indicated that slot blowing was ineffective, jet flaps provided lift augmenta- tion at all angles of attack tested and drag reduction at high lift conditions and pulsed blowing provided minor benefits over steady blowing Trimmed jet flap data indicates a Mach dependence on jet flap performance and that jet flaps provide a perform- ance advantage only at high lifts Author (GRA) support and maintenance for the LH2 fueled aircraft were analyzed An estimate was made of capital and operating costs which might be expected for the facility Recommendations were made for design modifications to the reference aircraft, reflecting results of the analysis of airport fuel handling requirements, and for a program of additional technology development for air terminal related items Author N77-10028# Texas Umv Austin Dept of Aerospace Engineering and Engineering Mechanics THE DEVELOPMENT OF A COMPUTER AIDED AIRFOIL DESIGN PROCEDURE INCLUDING PRELIMINARY WIND TUNNEL EXPERIMENTS ON A LOW REYNOLDS NUMBER HIGH LIFT SECTION. VOLUME 1 Final Report. 1 Dec 1970 - 30 Nov 1975 Jimmy Charles Narramore, Ralph Dean Orlander and Ronald Oran Stearman Jan 1976 153 p refs (Grant AF-AFOSR-1998-71 AF Proj 9782) (AD-A024361 AFOSR-76-0536TR) Avail NTIS HC A08/MF A01 CSCL 20/4 An investigation on the state of the art of subsonic airfoil section design including a review of the historical development of airfoil design methodology was carried out A computer aided airfoil design procedure employing current technology was developed and utilized to design a low-Reynolds number high-lift airfoil section Preliminary wind tunnel studies were carried out on this high-lift section and the influence of flow disturbances on its performances evaluated This study represents the first phase m determming how changes in airfoil design parameters influence the dynamical properties of the airfoil Author (GRA) N77-10029# Advanced Technology Center Inc Dallas, Tex TEST VERIFICATION OF A TRANSONIC AIRFOIL DESIGN EMPLOYING ACTIVE DIFFUSION CONTROL Final Report. 13 Jun 1974 - 14 Jun 1975 C H Haight and J G Spangler 1975 90 p refs (Contract N62269-74-C-0517) (AD-A024297 ATC-B-94300/5CR-34) Avail NTIS HC A05/MF A01 CSCL 20/4 Experimental results are presented that show active diffusion control, with its integrated contouring/blowing charactenstics to be a viable concept for relaxing transonic airfoil design constraints The antiseparation tailored contour (ATC) is the basic device for active diffusion control A modified 12% thick C-141 section with a trailing edge upper surface ATC designated as the TEATC12 airfoil was selected as the proof-of-concept configuration It incorporates the mam features of active diffusion control while providing a reliable baseline for comparison The transonic BLC/diffusion process was modeled in an axisymmetric diffuser facility Blowing predictions for the ATC geometry were substantiated and interactions between the jet and the mainstream were examined Experimental verification was completed by testing a TEATC12 airfoil model in the Vought Systems Division High Speed Wind Tunnel A C-141 model was also tested to provide a direct reference for the TEATC12 results Author N77-10032*# Lockheed-California Co, Burbank LH2 AIRPORT REQUIREMENTS STUDY Final Report, Sep 1975 - Feb 1976 G D Brewer ed Oct 1976 202 p refs (Contract NAS1-14137) (NASA-CR-2700 LR-27581) Avail NTIS HC A10/MF A01 CSCL 21 D A preliminary assessment of the facilities and equipment which will be required at a representative airport is provided so liquid hydrogen LH2 can be used as fuel in long range trans- port aircraft m 1995-2000 A complete facility was conceptually designed sized to meet the projected air traffic requirement The facility includes the liquefaction plant, LH2 storage capability, and LH2 fuel handling system The requirements for ground N77-10033*# Boeing Commercial Airplane Co Seattle Wash Dept of Preliminary Design ,, AN EXPLORATORY STUDY TO DETERMINE THE INTE- GRATED TECHNOLOGICAL AIR TRANSPORTATION SYSTEM GROUND REQUIREMENTS OF LIQUID- HYDROGEN-FUELED SUBSONIC. LONG-HAUL CIVIL AIR TRANSPORTS Final Report Washington NASA Sep 1976 176 p refs Prepared in cooperation with United Airlines and Air Products and Chemicals Inc (Contract NAS1-14159) (NASA-CR-2699 D6-75775) Avail NTIS HC A09/MF A01 CSCL 01 C A baseline air terminal concept was developed which permitted airlines and the airport to operate JP- or LH2-fueled aircraft at common terminal gates The concept included installation of a hydrogen liquefaction and storage facility on airport property as well as the fuel distribution system The capital investment and hydrogen-related operating costs to the airlines were estimated Author N77-10O34# Simat, Helliesen and Eichner Inc Washing^ DC AN ANALYSIS OF THE INTRASTATE AIR CARRIER REGULATORY FORUM VOLUME 1 SUMMARY REPORT Jan 1976 49 p (Contract DOT-OST-60078) (AD-A023761) Avail NTIS HC A03/MF A01 CSCL 05/3 Although the regulatory environments in Texas and California differ substantially, each has resulted in the establishment of carriers which are specialized in their desire and ability to serve medium- and high-density short-haul markets Further each has allowed these carriers to pursue a marketing and operational philosophy which has enabled them to achieve improved productivity and as a result charge lower fares CAB regulation on the other hand has produced both tight control of entry and tight rate regulation, and has required equal fares for markets of the same distance Consequently, there has been no develop- ment of specialized interstate carriers serving short-haul routes of density comparable to those served by the mtrastate carriers Application of a two-tier' pricing system, along with improved frequency, would be expected to double the traffic volume in these markets generating more than 18 million additional air passengers each year GRA N77-10035# Simat Helliesen and Eichner Inc Washington. DC AN ANALYSIS OF THE INTRASTATE AIR CARRIER REGULATORY FORUM VOLUME 2 TECHNICAL REPORT Final Report L J Eichner N S Simat K T Carlson, and R A Sunshine Jan 1976 420 p refs (Contract DOT-OS-60078) (AD-A023762) Avail NTIS HC A18/MF A01 CSCL 05/3 Intrastate air carriers in California and Texas have succeeded in earning profits and providing a high level of service while keeping fares well below those charged by interstate air carriers The three carriers analyzed in this report are not subject to regulation by the Civil Aeronautics Board (CAB) which controls both rates and routes of the trunk and local interstate air carriers The different regulatory environments impact on the performance of the aviation system Sixty interstate markets are identified 20 N77-10048 with potential for profitable operation at high levels of service at lower air fares and regulatory requirements to allow such service to develop can be identified Author (GRA) N77-10036# California Univ Los Angeles Graduate School of Management THE HELICOPTER AIR SERVICE PASSENGER PROGRAM A RETROSPECT Research Report. 1974 • 1975 Tim Yeomans and Frank G Mittelbach Sep 1975 60 p refs (PB-254830/3. CAL-URT-7(7)T-35 UMTA-CA-11-0009-75-4 Occasional-Paper-10) Avail NTIS HC A04/MF A01 CSCL 01B The initial expectations for helicopter development, and the reasons behind the helicopters ability or inability to fulfill its predicted role in moving large numbers of people in cities and between cities and outlying areas are discussed Attention is directed to basic helicopter characteristics and capabilities the rationale behind the helicopter experiment the effects of a federal subsidy granted to the industry and an analysis of four certified helicopter carrier operations GRA N77-10044*# United Technologies Research Center East Hartford Conn INVESTIGATION OF A BEARINGLESS HELICOPTER ROTOR CONCEPT HAVING A COMPOSITE PRIMARY STRUCTURE Final Report Richard L Bielawa Marvin C Cheney. Jr and Richard C Novak Oct 1976 253 p refs (Contract NAS1-10960, DA Proj 1 F1-61102-AH-45) (NASA-CR-2637. R76-911209-47) Avail NTIS HC A12/MF A01 CSCL QIC Experimental and analytical investigations were conducted to evaluate a beanngless helicopter rotor concept (CBR) made possible through the use of the specialized nonisotropic properties of composite materials The investigation was focused on four principal areas which were expected to answer .mportant questions regarding the feasibility of this concept First an examination of material properties was made to establish moduli ultimate strength, and fatigue characteristics of unidirectional graphite/ epoxy. the composite material selected for this application The results confirmed the high bending modulus and strengths and low shear modulus expected of this material and demonstrated fatigue properties in torsion which make this material ideally suited for the CBR application Second a dynamically scaled model was fabricated and tested in the low speed wind tunnel to explore the aeroelastic characteristics of the CBR and to explore various concepts relative to the method of blade pitch control Two basic control configurations were tested one in which pitch flap coupling could occur and another which eliminated all coupling It was found that both systems could be operated successfully at simulated speeds of 180 knots however the configuration with coupling present revealed a potential for undesirable aeroelastic response The uncoupled configuration behaved generally as a conventional hingeless rotor and was stable for all conditions tested Author N77-10045*# Lockheed-Georgia Co Marietta AN ANALYTICAL STUDY FOR SUBSONIC OBLIQUE WING TRANSPORT CONCEPT Edward S Bradley J Honrath K H Tomlm G Swift P Shumpert. and W Warnock Jul 1976 219 p refs (Contract NAS2-8686) (NASA-CR-137896 LG76ER0156) Avail NTIS HC A10/MF A01 CSCL 01C The oblique wing concept has been investigated for subsonic transport application for a cruise Mach number of 095 Three different mission applications were considered and the concept analyzed against the selected mission requirements Configuration studies determined the best area of applicability to be a commercial passenger transport mission The critical parameter for the oblique wing concept was found to be aspect ratio which was limited to a value of 6 0 due to aeroelastic divergence Comparison of the concept final configuration was made with fixed winged configurations designed to cruise at Mach 0 85 and 0 95 The crossover Mach number for the oblique wing concept was found to be Mach 091 for takeoff gross weight and direct operating cost Benefits include reduced takeoff distance installed thrust and mission block fuel and improved community noise characteristics The variable geometry feature enables the final configuration to increase range by 10% at Mach 0712 and to increase endurance by as much as 44% Author N77-10046*# Lockheed-Georgia Co Marietta AN ANALYTICAL STUDY FOR SUBSONIC OBLIQUE WING TRANSPORT CONCEPT Edward S Bradley Jul 1976 37 p refs (Contract NAS2-8686) (NASA-CR-137897 LG76ER0156) Avail NTIS HC A03/MF A01 CSCL01C For abstract see N77-10045 N77-10047*# Lockheed Missiles and Space Co, Sunnyvale Calif Research and Development Div CIVIL USES OF REMOTELY PILOTED AIRCRAFT Final Report Jon R Aderhold G Gordon and George W Scott Jul 1976 326 p refs (Contract NAS2-8935) (NASA-CR-137894. LMSC-D057323) Avail NTIS HC A15/MF A01 CSCL 01C The technology effort is identified and assessed that is required to bring the civil uses of RPVs to fruition and to determine whether or not the potential market is real and economically practical, the technologies are within reach, the operational problems are manageable, and the benefits are worth the cost To do so the economic, technical and environmental implications are examined The time frame is 1980-85 Representative uses are selected detailed functional and performance requirements are derived for RPV systems and conceptual system designs are devised Total system cost comparisons are made with non-RPV alternatives The potential market demand for RPV systems is estimated Environmental and safety requirements are examined and legal and regulatory concerns are identified A potential demand for 2000-11 000 RPV systems is estimated Typical cost savings of 25-35% compared to non-RPV alternatives are determined There appear to be no environmental problems and the safety issue appears manageable Author N77-10048*# Lockheed Missiles and Space Co Sunnyvale. Calif Research and Development Div CIVIL USES OF REMOTELY PILOTED AIRCRAFT Summary Report Jon R Aderhold G Gordon, and George W Scott Jul 1976 28 p ref (Contract NAS2-8935) (NASA-CR-137895. LMSC-D057322) Avail NTIS HC A03/MF A01 CSCL01C The economic technical and environmental implications of remotely piloted vehicles (RVP) are examined The time frame is 1980-85 Representative uses are selected, detailed functional and performance requirements are derived for RPV systems and conceptual system designs are devised Total system cost comparisons are made with non-RPV alternatives The potential market demand for RPV systems is estimated Environmental and safety requirements are examined and legal and regulatory concerns are identified A potential demand for 2000-11,000 21 N77-10049 RVP systems is estimated Typical cost savings of 25 to 35% compared to non-RPV alternatives are determined There appear to be no environmental problems, and the safety issue appears manageable Author N77-10049*# Kanner (Leo) Associates Redwood City Calif CRITICAL ANALYSIS OF COMPARISONS BETWEEN FLIGHT TEST RESULTS AND WIND TUNNEL TEST PREDICTIONS IN SUBSONIC AND SUPERSONIC TRANS- PORT AIRCRAFT C Pelagatti, J C Pilon and J Bardaud Washington NASA Aug 1976 56 p refs Transl into ENGLISH of French report AGARD-CP-187. Apr 1976 Presented at the 46th Meeting of the Flight Mech Panel Valloire. France. 9-13 Jun 1975 (Contract NASw-2790) (NASA-TT-F-17185 AGARD-CP-187) Avail NTIS HC A04/MF A01 CSCL01C In relating test results obtained from wind tunnels to results from actual flight tests corrections must be made to allow for aeroelastic effects and the effect of Reynolds' number differences Using data from Concorde and airbus tests, an attempt is made to define what degree of accuracy may be expected from aerodynamic coefficients derived from wind tunnel measure- ments Author N77-10050# Poitiers Univ (France) BUFFETING PROBLEMS [PROBLEMES DE BUFFETING] J Tensi and P Perner (Avions Marcel Dassault-Breguet Aviation) Pans Assoc Aeron et Astronautique de France 1976 48 p refs In FRENCH Presented at the 12th Ecole Natl Super de Mecan et d Aerotech / CEAT Colloq d'Aerodyn Appl Poitiers . France. 5-7 Nov 1975 (AAAF-NT-76-7. ISBN-2-7170-0385-1) Avail NTIS HC A03/MF A01. CEDOCAR. Paris FF 25 (France and EEC) FF 29 (others) Wind tunnel studies of buffeting of two types of profiles in incompressible flow are presented leading edge separation NACA 65 (sub 1)012 and trailing edge separation NACA 65 (sub 3) 618 The tests were made in the wind tunnel T sub 5 P sub 0 of the return (Prandtl) and guide vane type at 40 m/s Results of the two tests are detailed and compared It is shown that with the equipment used it is possible to determine the angle of attack and Reynolds number at which flow separation occurs Also the separation progress with increasing angle of attack can be followed ESA N77-10052# European Space Agency Pans (France) THREE-COMPONENT MEASUREMENTS ON A MODEL OF A LIGHT STOL AIRCRAFT WITH CHORDWISE BLOWING Horst Koerner et al May 1976 22 p refs Transl into ENGLISH of 'Dreikomponentenmessungen am Modell eines leichten STOL-Flugzeugs mit Ausblasen in Fluegeltiefenrichtung . DFVLR Brunswick Report DLR-FB-75-74 7 Nov 1975 Original German report available from DFVLR. Cologne DM 1020 (ESA-TT-299 DLR-FB-75-74) Avail NTIS HC A02/MF A01 Investigations on a STOL aircraft with internally blown flaps are described To avoid separation on the wing slots were located behind the nose flap and in front of the trailing edge flap The investigations were designed to examine maximum lift and lift/drag ratio In addition the effectiveness of the aileron and the horizontal tail were investigated Author (ESA) N77-10053# United Technologies Corp Windsor Locks, Conn V/STOL ROTARY 'PROPULSION SYSTEMS NOISE PREDICTION AND REDUCTION VOLUME 1 IDENTIFICA- TION OF SOURCES, NOISE GENERATING MECHANISMS, NOISE REDUCTION MECHANISMS, AND PREDICTION METHODOLOGY Final Report B Maghozzi May 1976 143 p refs (Contract DOT-FA74WA-3477) (AD-A027389/6 FAA-RD-76-49-Vol-1) Avail NTIS HC A07/MF A01 CSCL 01/3 The propulsion systems of current and future V/STOL vehicles can be defined as combinations of free air propellers shrouded propellers variable pitch fans fixed pitch fans tilt rotors helicopter rotors lift fans gearboxes and drive engines Noise sources for each of these prop'ulsors gearboxes and drive engines are identified and rank ordered The noise generating mechanisms for each of the propulsor noise sources identified are defined and systematically catalogued Three approaches to reduction of propulsor noise are discussed changes m physical geometry, changes in design operating conditions and the use of acoustic treatments Computerized and graphical procedures based on methodology from the open literature are presented for predicting aerodynamic performance of and noise from the V/STOL propulsors The developed methodo'ogy allows the user to estimate the achieved noise reduction as well as the incurred performance penalties of noise reduction design features and noise attenuation devices such as partly sonic inlets and acoustic treatment Much of the, noise generating mechanism substantiation data and prediction methodology are based on static operation Forward flight effects have recently been recognized as having a significant effect on the noise sources Forward flight effect corrections are included in the methodology Author N77-10051# Conservatoire National des Arts et Metiers, Pans (France) NEW BUFFETING ACQUISITION METHODS [NOUVELLES METHODES D'ACOUISITION DE BUFFETING] E Gaignebet and G Heckmann (Avions Marcel Dassault-Breguet Aviation) Assoc Aeron et Astronautique de France 1976 44 p refs In FRENCH Presented at the 12th Ecole Natl Super de Mecan et d'Aerotech / CEAT Colloq d Aerodyn Appl Poitiers, France. 5-7 Nov 1975 (AAAF-NT-76-8 ISBN-2-7170-0386-X) Avail NTIS HC A03/MF A01, CEDOCAR. Pans FF 25 (France and EEC) FF 29 (others) A new method for military aircraft buffeting data acquisi- tion using wind tunnel tests is presented The data analysis principle is discussed and inertia measurements are detailed The characteristics of the aircraft model are given and the data acquisition and data processing aspects are dealt with in detail It is concluded that with the hypothesis of small displacement the use of six accelerometers is justified any two of the three accelerometers related to one direction produce comparable results ESA N77-10054# United Technologies Corp Windsor Locks Conn V/STOL ROTARY PROPULSION SYSTEMS NOISE PREDICTION AND REDUCTION VOLUME 2 GRAPHICAL PREDICTION METHODS Final Report B Maghozzi May 1976 304 p refs 3 Vol (Contract DOT-FA74WA-3477) (AD-A027390/4 FAA-RD-76-49-Vol-2) Avail NTIS HC A13/MF A01 CSCL 01/3 Graphical procedures for estimating noise and performance of free air propellers variable pitch fans with inlet guide vanes variable pitch fans with outlet guide vanes, fixed pitch fans, helicopter rotors, tilt rotors and lift fans are presented Noise prediction methods for drive engines gearboxes jets with and without bypass flow as well as noise reduction and performance losses for partly sonic inlets and duct linings are also presented The procedures are extensive and applicable to a wide variety of V/STOL propulsor systems including present and future V/STOL vehicles The methods have been validated with available data wherever possible However high quality data for isolated propulsors which are free from contamination by other sources and ground reflections are somewhat limited particularly for forward flight conditions Author 22 N77-10062 N77-10055# United Technologies Corp Windsor Locks. Conn V/STOL ROTARY PROPULSION SYSTEMS NOISE PREDICTION AND REDUCTION VOLUME 3 COMPUTER PROGRAM USERS MANUAL Final Report B Magliozzi May 1976 302 p refs (Contract DOT-FA74WA-3477) (AD-A027363/1. FAA-RD-76-49-Vol-3) Avail NTIS HC A14/MF A01 CSCL 01/3 A computer program is presented which allows a user to make performance and far field acoustic noise predictions for free air propellers, variable pitch fans with inlet guide vanes variable pitch fans with outlet guide vanes, fixed pitch fans, helicopter rotors, tilt rotors fixed pitch lift vanes with remote integral, and tip turbine drives, and variable pitch lift fans with remote and integral drives Noise prediction methodology for drive engines, single stream and coaxial jets and gearboxes is also included as well as noise reduction and performance losses of partly sonic inlets and duct acoustic treatment A description of the program, detailed instructions for its use, required inputs, and sample cases are presented Author N77-10056*# Ellco Engineering, Inc . Compton Calif TRANSONIC PERFORMANCE OF MACH 265 AUXILIARY FLOW AXISYMMETRIC INLET Final Report Don M Santman Oct 1976 63 p refs (Contract NAS2-8679) (NASA-CR-2747) Avail NTIS HC A04/MF A01 CSCL 21E Transonic experimental performance for a large scale Mach 2 65 axisymmetnc inlet model with auxiliary airflow systems are presented The inlet model incorporated both centerbody and cowl auxiliary airflow systems When the centerbody system was fully open the performance at the simulated compressor face was such that at 0 10 total pressure distortion the total capture mass flow ratio increased 0055 and 0 051 and the total pressure recovery increased 0015 and 0012 at Mach 09 and 13 respectively Flow separation on the centerbody resulted in supercritical centerbody auxiliary throat flow prior to attainment of choked main duct throat flow Cowl auxiliary airflow had a detrimental effect on compressor-face performance To overcome the detrimental effect alternate cowl auxiliary airflow systems are described for efficient merging of auxiliary and mam duct airflows and for providing similar auxiliary and mam duct throat choking characteristics Author N77-10059*# National Aeronautics and Space Administration Lewis Research Center, Cleveland, Ohio SUPERSONIC VARIABLE-CYCLE ENGINES E A Willis and A. 0 Welliver (Boeing Aerospace Co, Seattle. Wash) 1976 11 p refs Presented at the 12th Propulsion Conf Palo Alto. Calif. 26-29 Jul 1976. cosponsored by AIAA and SAE / (NASA-TM-X-73524) Avail NTFS HC A02/MF A01 CSCl 21E The evolution and current status of selected recent variable cycle engine (VCE) studies are reviewed, and how the results were influenced by airplane requirements is described Promising VCE concepts are described, their designs are simplified and the potential benefits in terms of aircraft performance are identified This includes range noise, emissions and the time and effort it may require to ensure technical readiness of sufficient depth to satisfy reasonable economic performance and environmental constraints A brief overview of closely related, ongoing technology programs in acoustics and exhaust emissions is also presented Realistic technology advancements in critical areas combined with well matched aircraft and selected VCE concepts can lead to significantly improved economic and environmental performance relative to first generation SST predictions Author N77-10060*# Notre Dame Umv. Ind Dept of Electrical Engineering COMPUTATIONAL ALTERNATIVES TO OBTAIN TIME OPTIMAL JET ENGINE CONTROL M S Thesis R J Basso and R J Leake Oct 1976 73 p refs (Grant NsG-3048) (NASA-CR-149106, EE-7611) Avail NTIS HC A04/MF A01 CSCL 21E Two computational methods to determine an open loop time optimal control sequence for a simple single spool turbojet engine are described by a set of nonlinear differential equations Both methods are modifications of widely accepted algorithms which can solve fixed time unconstrained optimal control problems with a free right end Constrained problems to be considered have fixed right ends and free time Dynamic programming is defined on a standard problem and it yields a successive approximation solution to the time optimal problem of interest A feedback control law is obtained and it is then used to determine the corresponding open loop control sequence The Fletcher-Reeves conjugate gradient method has been selected for adaptation to solve a nonlinear optimal control problem with state variable and control constraints Author N77-10058*# National Aeronautics and Space Administration Lewis Research Center, Cleveland, Ohio EMISSIONS OF AN AVCO LYCOMING 0-320 DI AD AIR COOLED LIGHT AIRCRAFT ENGINE AS A FUNCTION OF FUEL-AIR RATIO. TIMING. AND AIR TEMPERATURE AND HUMIDITY Phillip R Meng Michael Skorobatckyi, Donald V Cosgrove and Erwm E Kempke Aug 1976 206 p refs (NASA-TM-X-73500) Avail NTIS HC A10/MF A01 CSCL 21G A carbureted aircraft engine was operated over a range of test conditions to establish the exhaust levels over the EPA seven-mode emissions cycle Baseline (full rich production limit) exhaust emissions at an induction air temperature of 59 F and near zero relative humidity were 90 percent of the EPA standard for HC, 35 percent for NOx. and 161 percent for CO Changes in ignition timing around the standard 25 deg BTDC from 30 deg BTDC to 20 deg BTDC had little effect on the exhaust emissions Retarding the timing to 15 deg BTDC increased both the HC and CO emissions and decreased NOx emissions HC and CO emissions decreased as the carburetor was leaned out while NOx emissions increased The EPA emission standards were marginally achieved at two leanout conditions Variations in the quantity of cooling air flow over the engine had no effect on exhaust emissions Temperature-humidity effects at the higher values of air temperature and relative humidity tested indicated that the HC and CO emissions increased significantly, while the NOx emissions decreased Author N77-10061*# Notre Dame Umv Ind Dept of Electrical Engineering SIMPLIFIED SIMULATION MODELS FOR CONTROL STUDIES OF TURBOJET ENGINES Thomas C Brennan and R Jeffrey Leake Nov 1975 93 p refs (Grant NsG-3048) (NASA-CR-149107 EE-757) Avail NTIS HC A05/MF A01 CSCL 21E The essential dynamical characteristics of a simple single spool turbojet engine were determined through simulation of low order system models on an analog computer An accurate model was studied and system complexity was reduced through various linearizations and approximations A derivation of a seventh order simplified simulation model is presented with a derivation of an even simpler third order model, and simulation results from each The control problem studied is one of getting from zero fuel flow equilibrium to a high thrust equilibrium while taking into account surge margin and turbine inlet temperature constraints Author N77-10062*| National Aeronautics and Space Administration Lewis Research Center Cleveland Ohio 23 N77-10063 ADVANCED COMBUSTION TECHNIQUES FOR CONTROL- LING NO SUB x EMISSIONS OF HIGH ALTITUDE CRUISE AIRCRAFT R A Rudey and G M Reck 1976 21 p refs Presented at 27th Intern Astronaut Congr. Anaheim, Calif 10-16 Oct 1976. sponsored by AIAA (NASA-TM-X-73473 E-8858) Avail NTIS HC A02/MF A01 CSCL 21E An array of experiments designed to explore the potential of advanced combustion techniques for controlling the emissions of aircraft into the upper atmosphere was discussed Of particular concern are the oxides of nitrogen (NOx) emissions into the stratosphere The experiments utilize a wide variety of approaches varying from advanced combustor concepts to fundamental flame tube experiments Results are presented which indicate that substantial reductions in cruise NOx emissions should be achievable in future aircraft engines A maior NASA oroaram is described which focuses the many fundamental experiments into a planned evolution and demonstration of the prevaponzed- premixed combustion technique in a full-scale engine Author N77-10063*# National Aeronautics and Space Administration Lewis Research Center Cleveland Ohio THE IMPACT OF EMISSIONS STANDARDS ON THE DESIGN OF AIRCRAFT GAS TURBINE ENGINE COMBUS- TORS Richard A Rudey 1976 19 p refs Presented at the Aerospace Conf San Diego Calif. 29 Nov - 2 Dec 1976 sponsored by SAE (NASA-TM-X-73490) Avail NTIS HC A02/MF A01 CSCL 21E Effective emission control techniques have been identified and a wide spectrum of potential applications for these techniques to existing and advanced engines are being considered Results from advanced combustor concept evaluations and from fundamental experiments are presented and discussed and comparisons are made with existing EPA emission standards and recommended levels for high altitude cruise The impact that the advanced low emission concepts may impose on future aircraft engine combustor designs and related engine components is discussed Author N77-10064*# Pratt and Whitney Aircraft East Hartford Conn EXPERIMENTAL CLEAN COMBUSTOR PROGRAM NOISE STUDY T G Sofrm and N Riloff Jr Sep 1976 191 p refs (Contract NAS3-18544) (NASA-CR-135106 PWA-5458) Avail NTIS HC A09/MF A01 CSCL 21E Under a Noise Addendum to the NASA Experimental Clean Combustor Program (ECCP) internal pressure fluctuations were measured during tests of JT9D combustor designs conducted in a burner test rig Measurements were correlated with burner operating parameters using an expression relating farfield noise to these parameters For a given combustor variation of internal noise with operating parameters was reasonably well predicted by this expression but the levels were higher than farfield predictions and differed significantly among several combustors For two burners discharge stream temperature fluctuations were obtained with fast-response thermocouples to allow calculation of indirect combustion noise which would be generated by passage of the temperature mhomogeneities through the high pressure turbine stages of a JT9D turbofan engine Using a previously developed analysis the computed indirect combustion noise was significantly lower than total low frequency core noise observed on this and several other engines Author N77-10065*# National Aeronautics and Space Administration Langley Research Center Langley Station Va ASSESSMENT OF VARIABLE-CYCLE ENGINES FOR MACH 2 7 SUPERSONIC TRANSPORTS Status Report S J Morns W E Foss. Jr and J W Russell (Vought Corp Hampton. Va) 1 Nov 1976 59 p refs (NASA-TM-X-73977) Avail NTIS HC A04/MF A01 CSCL 21E Three proposed SCAR propulsion systems in terms of aircraft range for a fixed payload and take-off gross weight with a design cruise Mach number 2 7 are evaluated The effects of various noise and operational restraints are determined and sensitivities to some of the more important performance variables are presented for the most probable design noise and operational restraint case Critical areas requiring new or improved technology for each cycle are delineated Author N77-10066*# National Aeronautics and Space Administration Lewis Research Center, Ceveland Ohio EFFECT OF AIR TEMPERATURE AND RELATIVE HUMIDITY AT VARIOUS FUEL-AIR RATIOS ON EXHAUST EMISSIONS ON A PER-MODE BASIS OF AN AVCO LYCOMING 0-320 DIAD LIGHT AIRCRAFT ENGINE VOLUME 2 INDIVIDUAL DATA POINTS Michael Skorobatckyi Donald V Cosgrove Phillip R Meng and Edward R Kempke Sep 1976 850 p (NASA-TM-X-73507 E-8916-Vol-2) Avail NTIS HC A99/MF A01 CSCL 21 E A carbureted four cylinder air cooled 0-320 DIAD Lycoming aircraft engine was tested to establish the effects of air temperature and humidity at various fuel-air ratios on the exhaust emissions on a per-mode basis The test conditions included carburetor lean-out at air temperatures of 50 59 80 and 100 F at relative humidities of 0 30 60 and 80 percent Temperature-humidity effects at the higher values of air temperature and relative humidity tested indicated that the HC and CO emissions increased significantly while the NOx emissions decreased Even at a fixed fuel-air ratio the HC emissions increase and the NOx emissions decrease at the higher values of air temperature and humidity Volume II contains the data taken at each of the individual test points Author N77-1O067# Techmsche Hochschule Aachen (West Germany) Inst fuer Luft- und Raumfahrt NOISE GENERATING BY INTERACTION BETWEEN SUB- SONIC JETS AND BLOWN FLAPS Erich Evertz Valentin Kloeppel Guenther Neuwerth and August Wilhelm Quick Cologne DFVLR 15 Mar 1976 23 p refs Presented at AIAA Meeting, Tenn Sponsored by Mm fuer Wiss u Forsch des Landes Nordrhem-Westfalen (DLR-FB-76-20) Avail NTIS HC A02/MF A01. DFVLR, Cologne DM 1080 On the basis of experimental results the strong noise generation originating from the interference between air jets of high subsonic speed and externally blown flaps (EBF) is discussed It is shown that in an undisturbed free jet as well as in a jet deflected by EBF there are ordered turbulence structures An acoustical feedback mechanism which develops at small distances between nozzle and stagnation point on the flaps and which reinforces the turbulence structures is explained It is subsequently shown that even without acoustic feedback both the undisturbed free jet and the jet deflected by EBF have their maximum noise levels at the Strouhal number of the natural ordered structures Author (ESA) N77-1OO68# Naval Air Systems Command. Washington, D C PREDICTION METHODS FOR JET V/STOL PROPULSION AERODYNAMICS. VOLUME 1 M F Platzer Jul 1975 541 p refs Workshop held at Arlington Va 28-31 Jul 1975 (AD-A024022) Avail NTIS HC A23/MF A01 CSCL01/1 High speed V/STOL aircraft operating iroin widely dispersed platforms have become of increasing interest to the U S Navy The dispersed force concept requires a well developed technology base, involving phenomena and problems which do not occur on conventional aircraft or low speed V/STOL craft Proper design must account for the interdependence of aerodynamic and 24 N77-10195 N77-10069# Naval Air Systems Command Washington D C PREDICTION METHODS FOR JET V/STOL PROPULSION AERODYNAMICS. VOLUME 2 M F Platzer Jul 1975 545 p refs Workshop held at Arlington Va, 28-31 Jul 1975 (AD-A024023) Avail NTIS HC A23/MF A01 CSCL01/1 For abstract seeN77-10068 N77-10070# Air Force Inst of Tech . Wright-Patterson AFB Ohio School of Engineering COMBUSTOR DESIGN FOR LOW COST EXPENDABLE TURBOJETS M S Thesis Raymond L Greene Mar 1976 57 p refs (AD-A024541 GAE/AE/76M-1) Avail NTIS HC A04/MF A01 CSCL 21/5 The development of two experimental burners was completed as part of a project to evaluate the suitability of the use of converted reciprocating engine turbochargers as expendable jet engines for remotely piloted vehicles As a result of analytic studies Burner A was constructed as a reverse flow burner and was designed to accept a mass flow up to 0 75 Ibm/sec Burner 'B was also reverse and designed for a mass flow up to 1 5 Ibm/sec Both burners operated successfully on their respective turbochargers GRA N77-10083# Office National d Etudes et de Recherche: Aerospatiales Pans (France) INFLUENCE OF WIND TUNNEL WALL BOUNDARY LAYERS ON TWO DIMENSIONAL TRANSONIC TESTS Rene Bernard-Guelle Assoc Aeron et Astronautique de France 1976 24 p refs In FRENCH ENGLISH summary Presented at the 12th Ecole Natl Super de Mecan et d Aerotech/CEAT Colloq Appl Poitiers France 5-7 Nov 1975 (AAAF-NT-76-13 ISBN-2-7T70-0391-6) Avail NTIS HC A02/MF A01, CEDOCAR, Pans FF 15 (France and EEC) FF 19 (others) Wind tunnel tests on the aspiration of the boundary layer upstream of the reference profiles NACA 0012 and LC 100D are discussed The two-dimensional test section of the ONERA RICh wind tunnel contains a porous wall permitting partial aspiration of the boundary layer upstream of the model The aspiration rate is adjustable and generates a variation of the displacement thickness from 5 to 1% of the model half-span permitting in some cases the extrapolation of the results to the extreme case of no boundary layer The effect of wall boundary, layers appears as a variation of the profile performance and a displacement of the shock waves To compare the results obtained in various wind tunnels this parameter should be taken into consideration It appears very difficult to establish a method for correcting these wall boundary layer effects therefore it seems mandatory to reduce them as far as possible Author (ESA) N77-10090# Texas Univ Austin Dept of Aerospace Engineering and Engineering Mechanics THE DESIGN. ANALYSIS AND TESTING OF A LOW BUDGET WIND TUNNEL FLUTTER MODEL WITH ACTIVE AERODY- NAMIC CONTROLS. VOLUME 2 Final Report. 1 Dec 1970 - 30 Nov 1975 Randall M Bolding and Ronald 0 Stearman Jan 1976 34 p refs Presented at the NASA Symp on Flutter Testing, Edwards, Calif 9-10 Oct 1975 (Grant AF-AFOSR-1998-71, AF Proj 9782) (AD-A024480 AFOSR-76-0537TR-Vol-2) Avail NTIS HC A03/MF A01 CSCL 20/4 This report describes a low budget flutter model incorporating active aerodynamic controls for flutter suppression studies, concentrating on the interfering lifting surface flutter phenomenon in the form of a swept wing-tail configuration A flutter suppression mechanism was first demonstrated on a simple semi-rigid three degree of freedom flutter model of this configuration employing an active stabilator control These preliminary studies were extended to the analysis of a larger degree of freedom AFFDL wing-tail flutter model The analytical and experimental design of a flutter suppression system for the AFFDL model is presented along with the results of a pre- liminary passive flutter test Author (GRA) N77-10162# European Space Agency, Pans (France) THEORETICAL AND EXPERIMENTAL INVESTIGATIONS ON LANDING GEAR SPRING BLADES OUT OF FIBER REIN- FORCED PLASTIC FOR SMALL AIRCRAFT Ramer Schuetze Sep 1976 35 p refs Trans) into ENGLISH of Theoretische u exptl Untersuch an Fahrwerksfederblaettern aus faserverstaerkten Kunststoffen fuer Klemflugzeuge DFVLR. Brunswick Report DLR-FB-76-06. 12 Jan 1976 Original German report available from DFVLR, Cologne DM 1620 (ESA-TT-312 DLR-FB-76-06) Avail NTIS HC A03/MF A01 The development of several landing gear spring blades for a small aircraft is described A special sandwich structure not only minimized the weight of the spring blade but also enabled it to resist both high longitudinal stresses in the facing layers and high shear stresses in the core The considerable length of these spring blades made it essential for them to have a high flexural rigidity Carbon and Kevlar 49 fibers both of which have a greater modulus of elasticity than glass fibers were therefore used as alternative reinforcements in the facing layers on the tension side of the blades All the blades were subjected to dynamic and static testing with the help of a gravitational-fall test bed The use of Kevlar 49 fibers in the tension flange of the sandwich permitted the weight to be reduced even as compared with the GRP sandwich and an improved damping behavior was also obtained Author (ESA) N77-10183*# National Aeronautics and Space Administration Lewis Research Center, Cleveland Ohio HOT CORROSION STUDIES OF FOUR NICKEL-BASE SUPERALLOYS B 1900, NASA-TRW VIA. 713C AND IN738 George C Fryburg Fred J Kohl, and Carl A Stearns 1976 11 p refs Presented at Symp on Properties of High Temp Alloys Las Vegas Nev 17-22 Oct 1976 sponsored by the Electrochem Soc and the Met Soc of the Am Inst of Mining Met and Petrol Engrs (NASA-TM-X-73479) Avail NTIS HC A02/MF A01 CSCL 11F The susceptibility to hot corrosion of four nickel base superalloys has been studied at 900 deg and 1000 deg C in one atmosphere of slowly flowing oxygen Hot corrosion was induced by coating the samples with known doses of NaS04 and oxidizing the coated samples isothermally on a sensitive microbalance In general the order of susceptibility found was B-1900 is greater than 713C is greater than NASA-TRW VIA and is greater than IN738 This order corresponds to the order of decreasing molybdenum content of the alloys Chemical .evidence for B-1900 indicates that hot corrosion is instigated by acid fluxing of the protective AI203 coating by Mo03 Author N77-10195$ Aluminum Co of America Alcoa Centei. Pa Alcoa Labs DESIGN MECHANICAL PROPERTIES. FRACTURE TOUGH- NESS. FATIGUE PROPERTIES. EXFOLIATION AND STRESS-CORROSION RESISTANCE OF 7060 SHEET. PLATE. HAND FORCINGS. DIE FORCINGS AND EXTRU- SIONS Final Report. 12 May 1972 - 12 Nov 1974 R E Davies G E Nordmack and J D Walsh Jul 1975 301 p refs (Contract N00019-72-C-0512) (AD-A024609) Avail NTIS HC A14/MF A01 CSCL 11/6 The mechanical properties including fracture toughness and fatigue fatigue-crack growth rates and corrosion characteristics 25 N77-10210 have been determined for a total of 51 lots of 7050-T76 sheet. 7050-T73651 plate 7050-T73652 hand forgmgs, 7050-T736 die forgmgs and 7050-T76511 extruded shapes Tables of computed design mechanical properties, modulus of elasticity values and individual stress-strain curves are presented The critical stress-intensity factor. (K sub c), was determined for samples of each lot of sheet and the plane-strain stress-intensity factor, (K sub Ic) was determined for plate hand and die forgmgs and extruded shapes The combination of strength and toughness of all products are generally comparable to or higher than those of conventional 7XXX alloys Axial-stress fatigue strengths were determined in ambient-air and salt-fog environments Modified Goodman diagrams were, developed from tests made in ambient air GRA N77-10210# Lockheed Aircraft Corp , Marietta Ga FULL TEMPERATURE RANGE PROTECTIVE SYSTEM FOR FASTENER AREAS OF CARRIER-BASED NAVAL AIRCRAFT Summary Report, 1 Jan 1974 - 31 Dec 1975 R N Wilier G G Seeliger. and W A Boggs Feb 1976 107 p refs (Contract N00019-74-C-0267) (AD-A024523, LG76ER0029) Avail NTIS HC A06/MF A01 CSCL 11/3 Results are presented for a program to develop a full temperature range (-65 to 325 F) protective systems for carrier-based aircraft Selected primers intermediate coatings and topcoats were subjected to screening tests The best coating systems were applied to aluminum and titanium specimens representative of aircraft joints After five cycles of a simulated flight spectrum the specimens were checked for coating defects, corrosion, and coating adhesion The most effective coating combinations were three-layer systems composed of a MIL-P- 23377 epoxy-polyamide primer, an aliphatic linear polyurethane topcoat and intermediate coats of elastomenc polyurethane or inhibited polysulfide These plus an additional system with an inhibited polysulfide primer and polyurethane topcoat were applied to A-7 carrier-based Navy aircraft during 1975 Plans were made for the periodic inspection of the test aircraft over a span of 3 years Navy C-130 Aircraft BUNO 1497S7 with experimental coating systems on the upper center wing was given a two-year inspection in August 1975 Except for minor scratches, all systems were in excellent condition Author (GRA) N77-10230*# National Aeronautics and Space Administration Langley Research Center Langley Station Va ADVANCES IN ENGINEERING SCIENCE, VOLUME 1 1976 360 p refs Presented at the 13th Ann Meeting of The Soc of Eng Sci 1-3 Nov 1976, Hampton. Va . sponsored by JIAFS and George Washington Univ 1 Vol (NASA-CP-2001-Vol-1) Avail NTIS HC Al'6/MF A01 CSCL 13M Proceedings from a conference on engineering advances are presented including materials science fracture mechanics, and impact and vibration testing The tensile strength and moisture transport of laminates are also discussed N77-10311*$ National Aeronautics and Space Administration Lewis Research Center Cleveland, Ohio INLET NOISE SUPPRESSOR DESIGN METHOD BASED UPON THE DISTRIBUTION OF ACOUSTIC POWER WITH MODE CUTOFF RATIO Edward J Rice In its Advan in Eng Sci Vol 3 1976 p 883-894 refs Avail NTIS HC A20/MF A01 CSCL 20A A liner design for noise suppressors with outer wall treatment such as in an engine inlet is presented which potentially circumvents the problems of resolution in modal measurement The method is based on the fact that the modal optimum impedance and the maximum possible sound power attenuation at this optimum can be expressed as functions of cutoff ratio alone Modes with similar cutoff ratios propagate similarly in the duct and in addition propagate similarly to the far field Thus there is no need to determine the acoustic power carried by these modes individually and they can be grouped together 95 one entity With the optimum impedance and maximum attenuation specified as functions of cutoff ratio, the off-optimum liner performance can be estimated using an approximate attenuation equation Author N77-10344*# National Aeronautics and Space Administration Langley Research Center. Langley Station, Va HYDROGEN-FUELED SUBSONIC AIRCRAFT A PERSPEC- TIVE Robert D Witcofski In its Advan in Eng Sci. Vol 3 1976 p 1265-12^8 refs Avail NTIS HCA20/MFA01 CSCL21D The performance characteristics of hydrogen-fueled subsonic transport aircraft are compared to those using conventional aviation kerosene Additional aspects discussed include potential improvements in the exhaust emissions characteristics of aircraft jet engines problems associated with onboard fuel containment, results of recent studies of the impact of hydrogen-fueled aircraft on the airport and associated ground support equipment, and estimates of the cost and thermal efficiency of producing synthetic aviation fuels from coal Author N77-10345*# National Aeronautics and Space Administration Langley Research Center, Langley Station Va ADVANCES IN ENGINEERING SCIENCE. VOLUME 4 1976 521 p refs Presented at 13th Ann Meeting of Soc of Eng Sci. Hampton, Va 1-3 Nov 1976 sponsored by JIAFS and George Washington Univ 4 Vol (NASA-CP-2001-Vol-4) Avail NTIS HC A22/MF A01 CSCL 13M The following areas of flight science are discussed in detail, (1) mviscid flow (2) viscous flow (3) aircraft aerodynamics, (4) fluid mechanics (5) propulsion and combustion and (6) flight dynamics and control N77-10347*# North Carolina State Univ Raleigh Dept of Mechanical and Aerospace Engineering LIFTING SURFACE THEORY FOR RECTANGULAR WINGS Fred R DeJarnette In NASA Langley Res Center Advan in Eng Sci Vol 4 1976 p 1301-1309 refs (Grant DAAG29-76-G-0045) Avail NTIS HC A22/MF A01 A new incompressible lifting-surface theory is developed for thin rectangular wings The solution requires the downwash equation to be in the form of Cauchy-type integrals Lan's method is employed for the chordwise integrals since it properly accounts for the leading-edge singularity. Cauchy singularity and Kutta condition The Cauchy singularity in the spanwise integral is also accounted for by using the midpoint trapezoidal rule and theory of Chebychev polynomials The resulting matrix equation formed by satisfying the boundary condition at control points, is simpler and quicker to compute than other lifting surface theories Solutions were found to converge with only a small number of control points and to compare favorably with results from other methods Author N77-10348*# National Aeronautics and Space Administration Ames Research Center Moffett Field, Calif consumption by reducing drag Computer codes have served well in meeting the consequent demand for new wing sections The possibility of replacing wind tunnel tests by computational fluid dynamics is discussed Another approach to the supercritical wing is through shockless airfoils A novel boundary value problem in 26 N77-10366 the hodograph plane is studied that enables one to design a shockless airfoil so that its pressure distribution very nearly takes on data that are prescribed Author N77-10349*# Virginia Polytechnic Inst and State Univ Blacksburg APPUCATION OF THE NONLINEAR VORTEX-LATTICE CONCEPT TO AIRCRAFT-INTERFERENCE PROBLEMS Osama A Kandil Dean T Mook and All H Nayfeh In NASA Langley Res Center Advan in Eng Sci. Vol 4 1976 p 1321-1330 refs Avail NTIS HC A22/MF A01 A discrete-vortex model was developed to account for the hazardous effects of the vortex trail issued from the edges of separation of a large leading wing on a small trailing wing The model is divided into three main parts the leading wing and its near wake the near and far wakes of the leading wing, and the trailing wing and the portion of the far wake in its vicinity The normal force pitching moment and rolling moment coefficients for the trailing wing are calculated The circulation distribution in the vortex trail is calculated in the first part of the model where the leading wing is far upstream and hence is considered isolated A numerical example is solved to demonstrate the feasibility of using this method to study interference between aircraft The numerical results show the correct trends The following wing experiences a loss in lift between the wing-tip vortex systems of the leading wing a gam outside this region and strong rolling moments which can change sign as the lateral relative position changes All the results are strongly dependent on the vertical relative position Author N77-10350*# National Aeronautics and Space Administration Langley Research Center Langley Station Va AN APPLICATION OF THE SUCTION ANALOG FOR THE ANALYSIS OF ASYMMETRIC FLOW SITUATIONS James M Luckring In its Advan in Eng Sci Vol 4 1976 p 1331-1347 refs Avail NTIS HC A22/MF A01 CSCL01A A recent extension of the suction analogy for estimation of vortex loads on asymmetric configurations is reviewed This extension includes asymmetric augmented vortex lift and the forward sweep effect on side edge suction Application of this extension to a series of skewed wings has resulted in an improved estimating capability for a wide range of asymmetric flow situations Hence the suction analogy concept now has more general applicability for subsonic lifting surface analysis Author N77-10351*# New York Univ. NY Courant Inst of Mathematical Sciences TRANSONIC FLOW THEORY OF AIRFOILS AND WINGS P R Garabedian In NASA Langley Res Center Eng Sci Vol 4 1976 p 1349-1358 refs Advan in (Grants NGR-33-016-167 NGR-33-016-201 Contract AT(11-11-3077) Avail NTIS HC A22/MF A01 There are plans to use the supercritical wing on the next generation of commercial aircraft so as to economize on fuel consumption by reducing drag Computer codes have served well in meeting the consequent demand for new wing sections The possibility of replacing wind tunnel tests by computational fluid dynamics is discussed Another approach to the supercritical wing is through shockless airfoils A novel boundary value problem in the hodograph plane is studied that enables one to design a shockless airfoil so that its pressure distribution very nearly takes on data that are prescribed Author N77-10354*# Texas A&M Univ. College Station INVERSE TRANSONIC AIRFOIL DESIGN INCLUDING VISCOUS INTERACTION Leland A Carlson In NASA Langley Res Center Advan in Eng Sci Vol 4 1976 p 1387-1395 refs (Grant NsG-1174) Avail NTIS HC A22/MF A01 A numerical technique was developed for the analysis of specified transonic airfoils or for the design of airfoils having a prescribed pressure distribution, including the effect of weak viscous interaction The method uses the full potential equation a stretched Cartesian coordinate system and the Nash-MacDonald turbulent boundary layer method Comparisons with experimental data for typical transonic airfoils show excellent agreement An example shows the application of the method to design a thick aft-cambered airfoil and the effects of viscous interaction on its performance are discussed Author N77-10355*# Mississippi State Univ Mississippi State NUMERICAL SOLUTIONS FOR LAMINAR AND TURBULENT VISCOUS FLOW OVER SINGLE AND MULTI-ELEMENT AIRFOILS USING BODY-FITTED COORDINATE SYSTEMS Joe F Thompson Z U A Warsi. and B B Amlicke In NASA Langley Res Center Advan in Eng Sci Vol 4 1976 p 1397-1407 refs (Grants NGR-25-001-005 AF-AFOSR-2922-76) Avail NTIS HC A22/MF A01 The technique of body-fitted coordinate systems is applied in numerical solutions of the complete time-dependent compressible and incompressible Navier-Stokes equations for laminar flow and to the time-dependent mean turbulent equations closed by modified Kolmogorov hypotheses for turbulent flow Coordinate lines are automatically concentrated near to the bodies at higher Reynolds number so that accurate resolution of the large gradients near the solid boundaries is achieved Two-dimensional bodies of arbitrary shapes are treated the body contour(s) being simply input to the program The complication of the bod- shape is thus removed from the problem Author N77-10365*# National Aeronautics and Space Administration Langley Research Center, Langley Station Va ADVANCED TRANSONIC AERODYNAMIC TECHNOLOGY Richard T Whitcomb In its Advan m Eng Sci Vol 4 1976 p 1521-1537 refs Avail NTIS HC A22/MF A01 CSCL 01A Supercritical airfoils and their applications to wings for various types of aircraft are studied The various wings discussed were designed for a subsonic jet transport with increased speed a variable sweep fighter with greater transonic maneuverability a high subsonic speed STOL jet transport with improved low speed characteristics, and a subsonic jet transport with substan- tially improved aerodynamic efficiency Results of wind tunnel and flight demonstration investigations are described Also discussed are refinements of the transonic area rule concept and methods for reducing the aerodynamic interference between engine nacelles and wings at high subsonic speeds Author N77-10366*# Lockheed-Georgia Co Marietta DESIGN CONSIDERATIONS FOR LAMINAR FLOW CON- TROL AIRCRAFT R F Sturgeon and J A Bennett In NASA Langley Res Center Advan in Eng Sci Vol 4 1976 p 1539-1548 refs (Contract NAS1-13694) Avail NTIS HC A22/MF A01 A study was conducted to investigate major design considera- tions involved in the application of laminar flow control to the 27 N77-10367 wings and empennage of long range subsonic transport aircraft compatible with initial operation in 1985 For commercial transports with a design mission range of 10.186 km (5500 n mil) and a payload of 200 passengers, parametric configuration analyses were conducted to evaluate the effect of aircraft performance, operational and geometric parameters on fuel efficiency Study results indicate that major design goals for aircraft optimization include maximization of aspect ratio and wing loading and minimization of wing sweep consistent with wing volume and airport performance requirements Author N77-10367*# Pennsylvania State Univ , University Park Dept of Aerospace Engineering ON THE STATUS OF V/STOL FLIGHT Barnes W McCormick In NASA Langley Res Center Advan in Enq Sci Vol 4 1976 p 1549-1562 refs Avail NTIS HC A22/MF A01 Basic principles relating to the accomplishment of V/STOL flight are reviewed as they pertain to current prototype develop- ments Particular consideration is given to the jet flap flow augmentation and circulation control separately and in combina- tion Configurations as the augmentor wing upper-surface blown flaps externally blown flaps and the circulation-controlled rotor are also examined Author N77-10368*# National Aeronautics and Space Administration Langley Research Center Langley Station Va THE CRYOGENIC WIND TUNNEL Robert A Kilgore In its Advan in Eng Sci Vol 4 1976 p 1565-1581 refs Avail NTIS HC A22/MF A01 CSCL 14B Based on theoretical studies and experience with a low speed cryogenic tunnel and with a 1/3-meter transonic cryogenic tunnel the cryogenic wind tunnel concept was shown to offer many advantages with respect to the attainment of full scale Reynolds number at reasonable levels of dynamic pressure in a ground based facility The unique modes of operation available in a pressurized cryogenic tunnel make possible for the first time the separation of Mach number Reynolds number and aeroelastic effects By reducing the drive-power requirements to a level where a conventional fan drive system may be used the cryogenic concept makes possible a tunnel with high productivity and run times sufficiently long to allow for all types of tests at reduced capital costs and, for equal amounts of testing reduced total energy consumption in comparison with other tunnel concepts Author N77-10377*# National Aeronautics and Space Administration Langley Research Center, Langley Station. Va DESIGN OF ACTIVE CONTROLS FOR THE NASA F-8 DIGITAL FLY-BY-WIRE AIRPLANE Joseph Gera In its Advan in Eng Sci. Vol 4 1976 p 1687-1701 refs Avail NTIS HC A22/MF AOI^CSCL 01C The design of a set of control laws for the NASA F-8 digital fly by wire research airplane is described These control laws implement several active controls functions maneuver load control, ride smoothing and departure boundary limiting The criteria and methods which were used in the design of the control laws are also included Results of linear analyses and nonlinear simulation are summarized Author N77-10378*# Aerospace Systems. Inc. Burlington. Mass PERFORMANCE ANALYSIS OF FLEXIBLE AIRCRAFT WITH ACTIVE CONTROL Richard B Noll and Luigi Monno (Boston Univ) In NASA Langley Res Center Advan in Eng Sci, Vol 4 1976 p 1703-1711 refs (Contract NAS1-13371) Avail NTIS HC A22/MF A01 Small perturbation equations of motion of a flexible aircraft with an active control technology (ACT) system were developed to evaluate the stability and performance of the controlled aircraft The total aircraft system was formulated in state vector format and the system of equations was completed with fully unsteady and low frequency aerodynamics for arbitrary, complex configura- tions based on a potential aerodynamic method The ACT system equations were incorporated in the digital computer program FCAP (Flight Control Analysis Program) which tan be used for the analysis of complete aircraft configurations, including control system with either low frequency or fully unsteady aerodynamics The applicatioi. of classical performance analyses including frequency response, poles and zeros mean square response, and time response in FCAP in state vector format was discussed Author N77-10379*# North Carolina State Univ Raleigh Dept of Mechanical and Aerospace Engineering BEST-RANGE FLIGHT CONDITIONS FOR CRUISE-CLIMB FLIGHT OF A JET AIRCRAFT Francis J Hale In NASA Langley Res Center Advan in Eng Sci. Vol 4 1976 p 1713-1719 refs Avail NTIS HC A22/MF A01 The Breguet range equation was developed for cruise climb flight of a jet aircraft to include the climb angle and is then maximized with respect to the no wind true airspeed The expression for the best range airspeed is a function of the specific fuel consumption and minimum drag airspeed and indicates that an operational airspeed equal to the fourth root of three times the minimum-drag airspeed introduces range penalties of the order of one percent Author N77-10381*# National Aeronautics and Space Administration Langley Research Center Langley Station Va RESULTS OF RECENT NASA STUDIES ON AUTOMATIC SPIN PREVENTION FOR FIGHTER AIRCRAFT Joseph R Chambers and Luat T Nguyen In its Advan in Eng Sci. Vol 4 1976 p 1733-1751 refs Avail NTIS HCA22/MFA01 CSCL01C A broad based research program was developed to eliminate or minimize inadvertent spins for advanced military aircraft Recent piloted simulator studies and airplane flight tests have demonstra- ted that the automatic control systems in use on current fighters can be tailored to provide a high degree of spin resistance for some configurations without restrictions to maneuverability Such systems result in greatly increased tactical effectiveness safety, and pilot confidence Author N77-10383*# Youngstown State Univ. Ohio TERMINAL AREA GUIDANCE ALONG CURVED PATHS. A STOCHASTIC CONTROL APPROACH J E Quaranta and R H Foulkes. Jr In NASA Langley Res Center Advan in Eng Sci. Vol 4 1976 p 1767-1777 refs (Grant NsG-1199) Avail NTIS HC A22/MF A01 Stochastic control theory is applied to the problem of designing a digital flight compensator for terminal guidance along a helical flight path as a prelude to landing The development of aircraft, wind, and measurement models is discussed along with a control scheme consisting of feedback gams multiplying estimate of the aircraft and wind states obtained from a Kalman one step predictor Preliminary results are presented which indicate that the compensator performs satisfactorily in the presence of both steady winds and gusts Author 28 N77-10998 N77-10432*# Massachusetts Inst of Tech Cambridge Electronic Systems Lab UNEAR REGULATOR DESIGN FOR STOCHASTIC SYSTEMS BY A MULTIPLE TIME SCALES METHOD Demosthenis Teneketzis and Nils R Sandell Jr |1976] 19 p refs (Grants NGL-22-009-124. E(49-18)-2087) (NASA-CR-149099) Avail NTIS HC A02/MF A01 CSCL 09A A hierarchically-structured suboptimal controller for a linear stochastic system composed of fast and slow subsystems is considered The controller is optimal in the limit as the separation of time scales of the subsystems becomes infinite The methodol- ogy is illustrated by design of a controller to suppress the phugoid and short period modes of the longitudinal dynamics of the F-8 aircraft Author N77-10512# Aeronautical Systems Div Wright-Patterson AFB Ohio PRAM Program Office LCC ANALYSIS OF FLIGHT RECORDER FOR F-4 WILD WEASEL AIRCRAFT Final Report Thomas D Mcitzler 7 Apr 1976 7 p refs (AD-A023830 ASD, RAXA-76-6) Avail NTIS HC A02/MF A01 CSCL 14/3 ^ This report briefly summarizes a basic life cycle cost effort on two flight recorders It discusses the background approach results and conclusions of the study GRA N77-10b56*# United Technologies Research Center. East Hartford Conn AEROELASTIC ANALYSIS FOR HELICOPTER ROTOR BLADES WITH TIME-VARIABLE. NON-LINEAR STRUC- TURAL TWIST AND MULTIPLE STRUCTURAL RE- DUNDANCY MATHEMATICAL DERIVATION AND PROGRAM USER'S MANUAL Final Report Richard L Bielawa Oct 1976 155 p refs (Contract NAS1-10960 DA Pro) 1 F1-61102-AH-45) (NASA-CR-2638) Avail NTIS HC A08/MF A01 CSCL01C The differential equations of motion for the lateral and torsional deformations of a nonlmearly twisted rotor blade in steady flight conditions together with those additional aeroelastic features germane to composite bearmgless rotors are derived The differential equations are formulated in terms of uncoupled (zero pitch and twist) vibratory modes with exact coupling effects due to finite time variable blade pitch and to second order twist Also presented are derivations of the fully coupled inertia and aerodynamic load distributions automatic pitch change coupling effects structural redundancy characteristics of the composite bearmgless rotor flexbeam - torque tube system in bending and torsion, and a descr jtion of the linearized equations appropriate for eigensolution analyses Three appendixes are included presenting material appropriate to the digital computer program implementation of the analysis, program G400 Author N77-10640*# National Aeronautics and Space Administration Lewis Research Center Cleveland Ohio EARLY OPERATION EXPERIENCE ON THE ERDA/NASA 100 kW WIND TURBINE John C Glasgow and Bradford S Linscott Sep 1976 25 p refs (NASA-TM-X-71601 E-8076) Avail NTIS HC A02/MF A01 CSCL 10A As part of the Energy Research and Development Administra- tion (ERDA) wind energy program. NASA Lewis Research Center is testing an experimental 100-kW wind turbine Rotor blade and drive shaft loads and tower deflection were measured during operation of the wind turbine at rated rpm The blade loads measured are higher than anticipated Preliminary results indicate that air flow blockage by the towei structure probably caused the high rotor blade bending moments Author N77-10690# Urban Systems Research and Engineering Inc Cambridge Mass BASELINE ENERGY FORECASTS AND ANALYSIS OF ALTERNATIVE STRATEGIES FOR AIRLINE FUEL CONSER- VATION Jul 1976 199 p (Contract FEA-C-04-50088-00) (PB-255351/9 FEA/D-76/026 FEA/D-CP-48) Avail NTIS HC A09/MF A01 CSCL 10A Baseline forecasts of airline activity and energy consumption to 1990 were developed to evaluate the impact of fuel conservation strategies Alternative policy options to reduce fuel consumption were identified and analyzed for three baseline levels of aviation activity within the framework of an aviation activity/ energy consumption model By combining the identified policy options a strategy was developed to provide incentives for airline fuel conservation Strategies and policy options were evaluated in teims of their impact on airline fuel conservation and the functioning of the airline industry as well as the associated social environmental and economic costs GRA N77-10873# European Space Agency. Paris (France) EXPERIMENTS ON THE FEASIBILITY OF AERO-ACOUSTIC MEASUREMENTS IN THE 3-m LOW SPEED WIND TUNNEL OF THE DFVLR-AVA Friednch-Remhard Grosche et al Sep 1976 36 p refs Transl into ENGLISH of 'Expt zur Moeghchkeit von aeroakustischen Messungen im 3-m-Niedergeschwindigkeitswmdkanal der DFVLR- AVA DFVLR Goettmgen West Ger Report DLR-FB-75-52 26 Nov 1975 Original German report available from DFVLR. Cologne DM 19,90 (ESA-TT-311 DLR-FB-75-52) Avail NTIS HC A03/MF A01 The experiments include measurements of the tunnel noise and measurements of the noise of a high subsonic jet emana- ting from a nozzle of 5 cm diameter located in a test section of the wind tunnel The noise level of the jet was 10 to 20 db higher at frequencies about 2 kHz than the noise level of the tunnel although a large airplane model producing additional flow noise was installed in the test section Author (ESA) N77-10997*# Transemantics Inc Washington D C VISCOUS INTERACTION WITH SEPARATION IN TRAN- SONIC FLOW J Delery J J Chattot and J C LeBalleur NASA Aug 1976 27 p refs Transl into ENGLISH of ONERA conf paper Presented at Flow Separation, AGARD Fluid Dyn Symp Goettmgen West Germany 27-30 May 1975 (Contract NASw-2792) (NASA-TT-F-17187) Avail NTIS HC A03/MF A01 CSCL 01A _ Strong viscous interactions which are present m transonic flows past airfoils give rise to an important thickening of the boundary layer with the frequent formation of a separated region Under such conditions, the calculation of the flow must call upon rapid interaction theories whose application for the case of a turbulent boundary layer is examined in conjunction with experimental analysis The experiments were conducted in a continuous wind tunnel equipped with a two dimensional nozzle having a 120 sq cm section The experimental installation is made of a half profile mounted on the lower wall of the transonic channel A detailed analysis of the flow field was made by using interferometry a measuring technique which avoids any disturb- ance of the flow At the same time an effort was made to develop a method of calculation similar to Klmeborg's approach Author N77-10998*# National Aeronautics and Space Administration Langley Research Center Langley Station Va EFFECTS OF JETS. WAKES. AND VORTICES ON LIFTING SURFACES Richard J Margason Nov 1976 15 p refs Presented at the AGARD Flight Dyn Panel Round Table Discussion Meeting 29 N77-10999 Moffett Field. Calif. 30 Sep - 1 Oct 1976 (NASA-TM-X-73974) Avail NTIS HC A02/MF A01 CSCL 01A The interaction of jets, wakes, and vortices on lifting bodies represents a broad spectrum of aerodynamic flow phenomena A literature survey is presented of 79 research activities in related aerodynamic situations Author N77-10999# National Aeronautical Establishment, Ottawa (Ontario) CONTROLLED AND UNCONTROLLED FLOW SEPARATION IN THREE DIMENSIONS D J Peake Jul 1976 70 p refs Presented at Symp on Viscous Flows Marietta Ga . 22-23 Jun 1976 (LR-591. NRC-15471 ISSN-0077-5541) Avail NTIS HC A04/MF A01 The advantages of swept, sharp edges that generate controlled (or fixed) three dimensional flow separations on a vehicle - because of the qualitatively unchanging flowfield developed throughout the range of flight conditions are promoted in preference to allowing uncontrolled (or unfixed) separations The three dimen- sional viscous flowfields and vortical interactions about typical components such as delta wings and bodies at incidence are discussed in apposition to their use on selected examples of current flight vehicles Author N77-11001*# National Aeronautics and Space Administration Langley Research Center Langley Station Va A FLIGHT INVESTIGATION OF PILOTING TECHNIQUES AND CROSSWIND LIMITATIONS DURING VISUAL STOL-TYPE LANDING OPERATIONS Bruce D Fisher, Robert A Champme Perry L Deal James M Patton Jr and Albert W Hall Washington Oct 1976 57 p refs (NASA-TN-D-8284 L-10923) Avail NTIS HC A04/MF A01 CSCL 05H A flight research program was undertaken to investigate problems concerned with landing a STOL airplane in crosswind conditions The program included a study of piloting techniques and crosswind limitations during visual STOL type landing operations The results indicated that the crosswind was more limiting during the ground roll out than during the airborne phases The pilots estimated that the crosswind limit for commercial STOL type operations with the test aircraft would be approximately 15 to 20 knots The pilots thought that the crosswind limits for ground operation might be extended by incorporating wing-lift spoilers improved nose gear steering, and improved engine response The pilots agreed that a crosswind landing gear would also be beneficial Author N77-11002# Lockheed Missiles and Space Co Huntsville Ala DEVELOPMENT OF PREDICTIVE WAKE VORTEX TRANS- PORT MODEL FOR TERMINAL AREA WAKE VORTEX AVOIDANCE Final Report. Feb - Oct 1975 M R Brashears A 0 Zalay L C Chou and K R Shrider May 1976 232 p refs (Contract DOT-TSC-988) (AD-A029049/4 LMSC-HREC-TR-D496597 FAA-RD-76-94 DOT-TSC-FAA-76-15) Avail NTIS H C A 1 1 / M F A 0 1 CSCL 01/2 The wake vortex transport program wa" expanded to include viscous effects and the influence of initial roll-up atmospheric turbulence and wind shear on the persistence and motion of wake vortices in terminal areas Analysis of wake characteristics show that changes in the spanwise loading due to flaps increase the initial sink rate decrease the separation and initiates the circulation decay process earlier Buoyancy due to jet exhaust entramment and ambient stratification retards vortex spreading and increases descent Atmospheric turbulence and shear promote a more rapid decay reducing the late-time descent and spread N77-11005*# Boeing Commercial Airplane Co Seattle. Wash A COMPUTATIONAL SYSTEM FOR AERODYNAMIC DESIGN AND ANALYSIS OF SUPERSONIC AIRCRAFT PART 2 USER'S MANUAL Final Report. Jan 1976 - Mar 1976 W D Middleton J L Lundry and R G Coleman Washington NASA Aug 1976 267 p refs (Contract NAS1-13732) (NASA-CR-2716 D6-43798-2) Avail NTIS HC A12/MF A01 CSCL 01A An integrated system of computer programs was developed for the design and analysis of supersonic configurations The system uses linearized theory methods for the calculation of surface pressures and supersonic area rule concepts in combination with linearized theory for calculation of aerodynamic force coefficients Interactive graphics-are optional at the user's request This user s manual contains a description of the system, an explanation of its usage, the input definition and example output Author N77-110O6*# Nielsen Engineering and" Research. Inc. Mountain View Calif CALCULATION OF THE LONGITUDINAL AERODYNAMIC CHARACTERISTICS OF WING-FLAP CONFIGURATIONS WITH EXTERNALLY BLOWN FLAPS Final Report Michael R Mendenhall. Selden B Spangler, Jack N Nielsen, and Frederick K Goodwin Washington NASA Sep 1976 143 p refs (Contract NAS1-13158) (NASA-CR-2705) Avail NTIS HC A07/MF A01 CSCL 01A A theoretical investigation was carried out to extend and improve an existing method for predicting the longitudinal characteristics of wing flap configurations with externally blown flaps (EBF) Two potential flow models were incorporated into the prediction method a wing and flap lifting-surface model and a turbofan engine wake model The wing-flap model uses a vortex-lattice approach to represent the wing and flaps The jet wake model consists of a series of closely spaced vortex rings normal to a centerline which may have vertical and lateral curvature to conform to the local flow field beneath the wing and flaps Comparisons of measured and predicted pressure distributions, span load distributions on each lifting surface and total lift and pitching moment coefficients on swept and unswept EBF configurations are included A wide range of thrust coefficients and flap deflection angles is considered at angles of attack up to the onset of stall Results indicate that overall lift and pitchmg-moment coefficients are predicted reasonably well over the entire range The predicted detailed load distributions are qualitatively correct and show the peaked loads at the jet impingement points, but the widths and heights of the load peaks are not consistently predicted Author N77-11007*# National Aeronautics and Space Administration Lewis Research Center Cleveland. Ohio TWO-DIMENSIONAL COLD-AIR CASCADE STUDY OF A FILM COOLED TURBINE STATOR BLADE 3 EFFECT OF HOLE SIZE ON SINGLE-ROW AND MULTIROW EJECTION Herman W Prust Jr and Thomas P Moffitt Washington Oct 1976 33 p refs (NASA-TM-X-3442 E-8720) Avail NTIS HC A03/MF A01 CSCL 20D The effect of coolant discharge on the aerodynamic perform- ance of s film cooled turbine stator blade was determined The blade had the same number, location and injection angle of coolant holes but the coolant hole diameters were one half that of a previously investigated blade Otherwise the blades were the same Tests with discharge from individual coolant rows and multiple coolant rows including full film discharge are studied The results of the blade with smaller holes are reported and compared with the blades with larger holes Author 30 N77-11019 N77-11008*# National Aeronautics and Space Administration Lewis Research Center Cleveland Ohio PERFORMANCE OF 1 15-PRESSURE-RATIO FAN STAGE AT SEVERAL ROTOR BLADE SETTING ANGLES WITH REVERSE FLOW George Kovich and Royce D Moore Washington Nov 1976 91 p refs (NASA-TM-X-3451 E-85711 Avail NTIS HC A05/MF A01 CSCL 21E A 51 cm diameter low pressure ratio fan stage was tested in reverse flow Survey flow data were taken over the range of rotative speed from 50 percent to 100 percent design speed at several rotor blade setting angles through both flat and feather pitch Normal flow design values of pressure ratio and weight How were 1 15 and 299 kg/sec with a rotor tip speed of 2438 m/sec The maximum thrust in reverse flow was 52 5 percent of design thrust in normal flow Author N77-11011|j! National Aerospace Lab Amsterdam (Netherlands) Ruid Dynamics Div CALCULATION OF THE FLOW AROUND A SWEPT WING. TAKING INTO ACCOUNT THE EFFECT OF THE THREE- DIMENSIONAL BOUNDARY LAYER PART 1 WING WITH TURBULENT BOUNDARY LAYER W J Piers G J Schipholt and B VandenBerg 27 May 1975 44 p refs (Contract NIVR-1737) (NLR-TR-75076-U) Avail NTIS HC A03/MF A01 The attached flow around swept wing was calculated with allowance for the effects of boundary layer and wake The outer potential flow was computed with an adapted version of the NLR panel method The displacement effect of the boundary layer and the wake was taken into account by the outflow concept For the calculation of the three-dimensional turbulent boundary layer the method of Wesselmg and Lmdhout was used The boundary layer calculations were based on measured pressure distributions while for the wake a crude estimation was made It is concluded that the calculated potential flow, with allowance for viscous effects compares well with experimental results in terms of pressure ana lift distribution With regard to the computing time the potential flow program was about eight times faster than the boundary layer program Author (ESA) N77-11013# Hydronautics Inc Laurel Md HIGH SPEED COMPUTER STUDIES OF VORTEX MOTIONS IN RELATION TO AIRCRAFT WAKE TURBULENCE Final Report Clinton E Brown and Poter VanDyke Jan 1976 42 p refs (Contract F446?0 71-C-0030 AF Pro "7811 (AD-A024290 TR 7115-4 AFOSR . .48'TR) Avail NTIS HC A03/MF A01 • SCL 01, 1 Computatons are presented and cor pared with experimental data from ottie' aource^ fo« basic a"d advanced problems in aircraft - wake vortex interactions Results are presented for coalescence of corotation and counterrotating vortex groups and finally a complete high speed computer method is developed for simulating the roll reaction of an aircraft to the wake produced by a large aircraft with flaps deployed Suggestions for improved experimental approaches are also appended Author (GRA) N77-11115*# IIT Research Inst Chicago III WAVE PROPAGATION IN FIBER COMPOSITE LAMINATES. PART 2 Final Report. 1 Jtil 1974 - 29 Feb 1976 I M Daniel and T Liber Jun 1976 135 p refs (Contract NAS3-16766) (NASA-CR-135086, IITRI-D6073-3-Pt-2) Avail NTIS HC A07/MF A01 CSCL 11D An experimental investigation was conducted to determine the wave propagation characteristics transient strains and residual properties in unidirectional and angle-ply boron/epoxy and graphite/epoxy laminates impacted witn silicone rubber projectiles at velocities up to 250 MS-1 The predominant wave is flexural propagating at different velocities in different directions In general measured wave velocities were higher than theoretically predicted values The amplitude of the in-plane wave is less than ten percent of that of the flexural wave Peak strains and strain rates in the transverse to the (outer) fiber direction are much higher than those in the direction of the fibers The dynamics of impact were also studied with high speed photography Author N77-11116*# IIT Research Inst. Chicago III STRAIN RATE EFFECTS ON MECHANICAL PROPERTIES OF FIBER COMPOSITES. PART 3 Final Report. 1 Jul 1974 - 29 Feb 1976 I M Daniel and T Liber Jun 1976 49 p refs (Contract NAS3-16766) (NASA-CR-135087 IITRI-D6073-4) Avail NTIS HC A03/MF A01 CSCL 11D An experimental investigation was conducted to determine the strain rate effects in fiber composites Unidirectional composite specimens of boron/epoxy, graphite/epoxy, S-glass/epoxy and Kevlar/epoxy were tested to determine longitudinal transverse and intralammar (in-plane) shear properties In the Longitudinal direction the Kevlar/epoxy shows a definite increase in both modulus and strength with strain rate In the transverse direction, a general trend toward higher strength with strain rate is noticed The mtralaminar shear moduli and strengths of boron/epoxy and graphite/epoxy show a definite rise with strain rate Author N77-11117*# Scientific Translation Service Santa Barbara Calif CONTRIBUTIONS TO THE STUDY OF THE PHYSICAL PROPERTIES OF CARBON F Carmona Washington NASA Nov 1976 193 p refs Transl into ENGLISH of 'Contributions a I Etude des Propnetes Physiques des Carbons" Doctoral Dissertation Bordeaux Umv 1976 p 1-178 (Contract NASw-2791) (NASA-TT-F-17246) Avail NTIS HC A09/MF A01 CSCL 11D A theoretical justification is given for old results of electron paramagnetic resonance The evolution of the physical properties of carbon during carbonization is examined in light of recent theoretical and experimental studies on non-crystalline solids Author N77-11118*# National Aeronautics and Space Administration Lewis Research Center Cleveland Ohio EFFECT OF FIBER DIAMETER AND MATRIX ALLOYS ON IMPACT-RESISTANT BORON/ALUMINUM COMPOSITES David L McDanels and Robert A Signorelli Washington Nov 1976 38 p refs (NASA-TN-D-8204. E-8648) Avail NTIS HC A03/MF A01 CSCL 11 D Efforts to improve the impact resistance of B/A are reviewed and analyzed Nonstandard thin-sheet charpy and Izod impact tests and standard full-size Charpy impact tests were conducted on composites containing unidirectional 010mm 014mm and 020mm diameter boron fibers m 1100 2024 5052 and 6061 Al matrices Impact failure modes of B/AI are proposed in an attempt to describe the mechanisms involved and to provide insight for maximizing impact resistance The impact strength of B/AI was significantly increased by proper selection of materi- als and processing The use of a ductile matrix and large diameter boron fibers gave the h'ghest impact strengths This combination resulted in improved energy absorption through matrix shear deformation and multiple fiber breakage Author N77-11019*# Transemantics Inc Washington DC TOWARD NEW HEIGHTS B P Bugayev NASA Oct 1976 82 p refs Transl into ENGLISH of the mono K Novym Vystam (Novoye v Zhizni Nauke. Tekhnike Senya Transport no 3) Moscow Znaniye 31 N77-11020 Press 1976 p 1-64 (Contract NASw-2792) (NASA-TT-F-17248) Avail NTIS HC A05/MF A01 CSCL 01B Aeroflot is not only the daily transport of hundreds of thousands of passengers but also the delivery of equipment, machinery parts and other cargoes to construction sites of the energy and industrial giants, flights with geologists in search of petroleum gas and other natural resources ice reconnaissance aid to fishermen on the open sea emergency flights to patients with a physician aboard the protection of forests against fires and much else The results are presented of accomplishing the tasks of the Ninth Five-year Plan and how Civil Aviation will develop in the future Author N77-11020# National Aerospace Lab Amsterdam (Netherlands) Flight Div THE ESTABLISHMENT OF SAFE SEPARATIONS BETWEEN AIRCRAFT IN FLIGHT A Pool 1 Dec 1975 12 p Presented at the 28th Intern Air Safety Seminar Amsterdam 3-5 Nov 1975 (NLR-MP-75041-U) Avail NTIS HC A02/MF A01 The history of the use of models and statistical data for the assessment of separation standards is reviewed This work was mainly done by the ICAO Vertical Separation Panel the North Atlantic Systems Planning Group and the ICAO Panel for the Review of the General Concept of Separation After a brief description of the model and of the target level of safety plans for future work are indicated Author (ESA) N77-11022# Naval Surface Weapons Center White Oak Md AIRCRAFT GROUND FIRE SUPPRESSION AND RESCUE SYSTEMS CHARACTERISTICS OF KINEMATIC JET FUEL FIRES CASCADING AND ROD FUEL GEOMETRIES Final Report. Dec 1974 - Dec 1975 R S Alger F I Laughndge L L Wiltshire R G McKee (Stanford Res Inst Menlo Park Calif) W H Johnson (Stanford Res Inst. Menlo Park Calif) and N S Alvares (Stanford Res Inst, Menlo Park Calif) Wright-Patterson AFB Ohio DON Aircraft Ground Fire Suppression and Rescue Office Mar 1976 83 p refs Sponsored by DOD Aircraft Ground Fire Suppression and Rescue Office Prepared |Ointly by Stanford Res Inst Menlo Park Calif (AD-A024447 DOD-AGFSRS-76-3) Avail NTIS HC A05/MF A01 CSCL 01/2 Based on a survey of kinematic fuel fires in aircraft accidents, two types i e, cascade and rod fuel flows, were selected to theoretical and experimental examination The twofold objectives was (1) relate fire characteristics such as burning rate, radiation field and flame size to the fuel parameters the flowing conditions, and the environment and (2) determine the parameters and their degree of control required to achieve reproducible fires suitable for testing extinguishing agents equipment, and techniques Theoretical models based on steady, laminar, one-dimensional flow were developed flying hour and attrition data supplied by the Air Force Inspection and Safety Center The earlier study resulted in sufficient understanding of the attrition process to develop estimating methodologies that were adopted by the Air Force in official publications and that are still in use The conceptual bases for the findings of the first study are discussed, and in conjunction with statistical parameters and an examination of some typical projections the utility of the method is evaluated Author (GRA) N77-11024$ Westmghouse Defense and Electronic Systems Center. Baltimore Md Aerospace and Electronic Systems Div FINAL APPROACH PERFORMANCE MONITOR Final Report I T Basil Jul 1976 189 p (Contract DOT-FA72WA-2837) (AD-A028513/0 FAA-RD-76-117 Rept-75-0280A) Avail NTIS HC A09/MF A01 CSCL 17/7 The objectives the system design goals, the hardware developed, and the laboratory test results of an instrument landing system (ILSI performance monitor are stipulated This new measuring system makes angular measurements of the angular deviation from the glidepath of an aircraft on a final approach Measurements are made once every airport surveillance radar (ASR) scan The signal used for this measurement is the aircraft's transponder reply to the ASR interrogation A fixed monopulse monitoring antenna measures the angular position of the aircraft relative to the antenna boresight Since the antenna is boresighted along the glidepath computations can determine the deviation of the aircraft from the glideslope The technique is very precise in measuring angular deviation from antenna boresight its range measuring accuracy is limited by the inherent jitter in the transponder reply Author N77-11029*# Transemantics. Inc. Washington. DC CALCULATION OF MULTI-CONTOUR THIN-WALLED STRUCTURES BY THE METHOD OF SECTIONS V G Shatayev NASA Nov 1976 15 p refs Transl into ENGLISH from Izv Vysshikh Uchebn Zavedenn Aviats Tekhn (Kazan) no 2. Feb 1976 p 117-123 (Contract NASw-2792) (NASA-TT-F-17284) Avail NTIS HC A02/MF A01 CSCL 01C In calculating thin-walled airframe structures of the type used in the wings and tails of aircraft, the hypothesis of the invariability of the shape of the contour of the cross sections during deformation is widespread Many theoretical and experimental studies have shown that it applies in the study of the majority of problems of strength of wing and tail assemblies The method of final sums is used in this article to obtain the numerical solution for a cantilevered thin-walled beam Matrix formulation of basic relationships, equations for numerical solution of a cantilevered stringer and methods of sections are discussed Author N77-11023# RAND Corp Santa Monica Calif A SECOND LOOK AT RELATIONSHIPS FOR ESTIMATING PEACETIME AIRCRAFT ATTRITION Interim Report William i Mooz Feb 1976 65 p refs (Contract F44620-73-C-0011) (AD-A023681 R-1840-PR) Avail NTIS HC A04/MF A01 CSCL 01/3 The attrition experience of individual aircraft systems is found to change over the flying life of the system in such a way as to continually lower the attrition rate This process can be represented mathematically, and the resulting model used to project future losses for the system A study was made to evaluate the results of an earlier Rand study of peacetime aircraft attrition (RM-4840-PR August 1966) in light of 12 years of additional N77-11030*# Aerospace Systems. Inc Burlington. Mass DISPLAY/CONTROL REQUIREMENTS FOR VTOL AIR- CRAFT Interim Technical Report William C Hoffman Renwick E Curry (MIT Cambridge) David L Klemman (Connecticut Univ Storrs) Walter M Hollister (MIT Cambridge) and Laurence R Young (MIT. Cambridge) Aug 1975 273 p refs (Contract NAS1-13653) (NASA-CR-145026 ASI-TR-75-26) Ava.l NTIS HC A12/MF A01 CSCL 01C Quantative metrics were determined for system control performance workload for control, monitoring performance, and workload for monitoring Pilot tasks were allocated for navigation and guidance of automated commercial V/STOL aircraft in all weather conditions using an optimal control model of the human operator to determine display elements and design A H 32 N77-11037 N77-11031*# National Aeronautics and Space Administration Langley Research Center Langley Station Va PRELIMINARY SIZING AND PERFORMANCE EVALUATION OF SUPERSONIC CRUISE AIRCRAFT D f. Fetterman Jr Sep 1976 80 p refs (NASA-TM-X-73936) Avail NTIS HC A05/MF A01 CSCL 01C The basic processes of a method that performs sizing operations on a baseline aircraft and determines their subsequent effects on aerodynamics propulsion weights and mission performance are described The input requirements of the associated computer program are defined and its output listings explained Results obtained by applying the method to an advanced supersonic technology concept are discussed These results include the effects of wing loading thrust to weight ratio and technology improvements on range performance and possible gains in both range and payload capability that become available through growth versions of the baseline aircraft The results from an in depth contractual study that confirm the range gam predicted for a particular wing loading thrust-to-weight ratio combination are also included Author N77-11035/? Rockwell Interns; unal Coip Columbus Ohio Missile Systems Div CONCEPTUAL DESIGNS FOR A MODULAR REMOTELY PILOTED VEHICLE Final Report, 2 Dec 1974 - 26 Now 1975 Francis L Goebel Krsey 0 Smith and Frederick W Hessman Jan 1976 279 p refs (Contract F336\5-75-C-3036 AF Pro) 1989) (AD-A023844 C75-1443/034C AFI-OL-TR-75-162) Avail NTIS H C A 1 3 / M F A 0 1 CSCL 01/3 The application of the modular design approach to remotely piloted vehicles 'S described It is shewn that by modular exchange of structura and equipment components a basic vehicle can be configured to perform low level recce and strike medium altitude EW nigh altitude recce and tactical air-to-air missions Two basic vehicle configuration design concepts which differ primarily in engine installation arrangement (nacelle versus internal) are presented The design approach using the nacelle-mounted engine is shown to be superior and to provide the best basis for a technology evaluator 01 demonstrator GRA N77-11032*f/ Loi kheed-Georgia Co Manotia P R O G R A M FOR ESTABLISHING LONGTIME FLIGHT SERVICE PERFORMANCE OF COMPOSITE MATERIALS IN THE CENTER WING STRUCTURE OF C-130 AIRCRAFT PHASE 4 GROUND/FLIGHT ACCEPTANCE TESTS W E Harvill and J A Kizer Sep 1976 153 p refs (Contract NAS1-1 1 100) (NASA-CR-145043 LG76ER0095) Avail NTIS HC A08/MF A01 CSCL 01C. "t The advantageous structural uses of advanced filamentary composites are demonstrated by design fabrication and test of three boron epoxy reinforced C-130 center wing boxes The advanced development work necessary to support detailed design of a composite reinforced C-130 center wing box was conduc- ted Activities included the development of d basis for structural design selection and verification ot materials and processes manufacturing and tool ng development and fabrication and test of full-scale portions of the center wing box Detailed design drawings and necessary analytical structural substantiation including static strength fatigue endurance flutter and weight analyses are considered Some additional component testing was conducted to verify the design for panel buckling and to evaluate specific local design areas Development of the cool tool restraint concept was completed and bonding capabilities were evaluated using full-length skin panel and stringer specimens Author N77-11036# Douglas Aircraft Co Inc Long Beach Calif DEVELOPMENT OF A GRAPHITE HORIZONTAL STABIL- IZER Final Report, 3 Nov 1969 - 31 Aug 1975 George M Lehman M Ashizawa M J Gailippi A V Hawley and C A VanPappelendam Mar 1976 85 p (Contract N001 56-70 C-1 321 WF41422206) (AD-A023767 MDC-J6902 NADC-76078-30) Avail NTIS HC A05/MF A01 CSCL 01/3 A summary of the design syn'hesis structural development testing tooling manufacturing and ground testing of an advanced composite horizontal stabilizer tor the A-4 Skyhawk is presented The stabilizer utilized Narmco 5206 graphite-epoxy as the primary load-bearing structural material (58 5 percent by weight) The most significant problem encountered was the development of structurally efficient joints In ground tests the graphite stabilizer successfully sustained design ultimate loads and subsequently sustained two lifetimes of fatigue spectrum loads A positive margin of-safety of 12 peicent was indicated in a final ultimate- strength test after completion of the fatigue test A flutter analysis based on the natural modes and frequencies of the graphite stabilizel indicated an improvement in empennage flutter speed A weight reduction of 26 2 percent was achieved in comparison to the existing metal stabilizer GRA N77-11033*# National Aeronautics and Space Administration Langley Research Center Langley Station Va LANDING PRACTICES OF GENERAL AVIATION PILOTS IN SINGLE-ENGINE LIGHT AIRPLANES Maxwell W Goode Thomas C OBryan Kenneth R Yenni Robert L Cannaday and Marna H Mayo Washington Oct 1976 50 p refs Technical film supplement L-1208 is available on loan from Langley Research Center Attn Photographic Branch mail stop 425 Hampton Va 23665 (NASA-TN-D-8283 L-10878) Avail NTIS HC A03/MF A01 CSCL 05H The methods and techniques used by a group of general aviation pilots during the landing phase of light airplane operations are documented The results of 616 landings made by 22 pilots in 2 modern four-place single-engine flight airplanes (one having a low wing and the other a high wing) are presented The landings were made on both a long runway (1524 m (5000 ft)) and a short runway (762 m (2500 ft)) both runways were considered typical of those used in general aviation The results generally show that most of the approaches were fast with considerable floating during the flares and with touchdowns that were relatively flat or nose low Author N77-11037# ARO Inc Arnold Air Force Station Tenn A WIND TUNNEL CAPTIVE AIRCRAFT TESTING TECH- NIQUE Final Report, 1 Jul 1974 - 30 Jun 1975 R W Butler AEDC Apr 1976 37 p refs (ARO Pro) P32A-33A ARO Pro| P41T-78A) (AD-A023690 ARO-PWT-TR-75-80 AEDC-TR-76-22) Avail NTIS HC A03/MF A01 CSCL 01/3 A captive aircraft testing technique has been developed for use in the 16 ft wind tunnels at the Arnold Engineering Development Center (AEDC) With the captive system an aircraft motion study may be conducted in the wind tunnel with the tunnel acting as an analog forcing function The large static aerodynamic data matrix normally required for a motion study has been alleviated The system validity is established by a comparison of F 15 aircraft motion generated in the wind tunnel with flight motion of a NASA 3/8-scale F-15 Remotely Piloted Vehicle (RPV) Good agreement between the longitudinal and lateral/directional motions of the model was achieved in the absence of RPV unsteady aerodynamics (wing buffet) The captive technique ability to efficiently define changes in aircraft flight characteristics resulting 'rom different external store configura- tions is demonstrated Author (GRA) 33 N77 11038 N77-11038# Naval Air Development Center Warminster Pa Air Vehicle Technology Dept CATAPULT LAUNCH FATIGUE INVESTIGATION OF THE MODEL S-2 E AIRPLANE Final Report H D Lystad 31 Dec 1975 58 p refs (AD-A024071 NADC-75368-30) Avail NTIS HC A04/MF A01 CSCL 01/3 A laboratory fatigue investigation was performed on an S-2 E fuselage with reinforced catapult keel beam and holdback carry through structure to determine if it could sustain the loads associated with 3 000 catapult launches The bulkhead at fuselage station 206 failed after 5 690 test cycles of the catapult start of run condition Using a test scatter factor of 2 this is equivalent to 2 845 service catapult launches The test article experienced 419 service catapult launches prior to reinforcement which when added to the test results provides for a service catapult launch life in excess of 3 000 launches The holdback release condition test was discontinued after 10000 test cycles with no failures Again using a test scatter factor of 2 this is equivalent to 5.000 service catapult launches Author (GRA) N77-11039# Army Aviation Engineering Flight Activity Edwards AFB Cahf ARMY PRELIMINARY EVALUATION YOH-58A HELICOPTER WITH A FLAT-PLATE CANOPY Final Report James R Arnold and Gary L Skinner Dec 1975 45 p refs (AD-A024501 USAAEFA-75-20) Avail NTIS HC A03/MF A01 CSCL 01/3 A limited evaluation of the performance and handling qualities of the OH-58A helicopter was conducted to determine the effects of a four-plane flat-plate canopy installation Testing was conducted at the Bell Helicopter Company flight test facility at Arlington Texas from 25 October through 4 November 1975 Personnel from the United States Army Aviation Engineering Flight Activity conducted 11 test flights for a total of 6 5 productive test flight hours The evaluation revealed a loss in airspeed of 2 and 6 knots at the airspeed for maximum continuous power and a loss in range of 8 and 23 nautical miles at the cruise airspeed (forward and aft center-of-g ravity configurations respectively) The noticeable changes in the handling qualities were a slight increase in the nose-down pitching rate following a sudden loss of power (more pronounced for the forward center-of-gravity configuration) and a slight increase in the dihedral effect of the helicopter The flat-plate canopy installation resulted in a slight reduction in the field of view but visibility was improved due to the optical clarity of the flat-plate The installation of glare shields between the chin bubble and canopy significantly reduced the canopy reflections during both day and night tests One shortcoming was noted during this evaluation but cannot be attributed to the flat-plate canopy installation Author (GRA) N77-11040# Naval Air Development Center Warminster Pa Vehicle Technology Dept FATIGUE INVESTIGATION OF THE E-2B/C NOSE LANDING GEAR Final Report H D Lystad 31 Dec 1975 65 p refs (AD-A024072 NADC-75369-30) Avail NTIS HC A04/MF A01 CSCL 01/3 A laboratory fatigue investigation was performed on an E-2B and an E-2C nose landing gear to determine whether the authorized limit of 650 catapult launches could be extended The starboard holdback lug of the E-2B nose landing gear with modified drag brace attachment lugs failed after the application of 3 336 test cycles Using a test scatter factor of two this is equivalent to 1 668 service catapult launches The outer cylinder of the E-2C shock strut assembly cracked under the packing nut after completion of 7 430 test cycles Again using a test scatter factor of two. this is equivalent to 3715 service catapult launches Author (GRA) N77-11041# Bell Helicopter Co, Fort Worth. Tex HELICOPTER RELIABILITY GROWTH EVALUATION Final Report G S Conway Apr 1976 170 p refs (Contract DAAJ02-73-C-0097. DA Pro) 1F1-63204-DB-38) (AD-A025265 USAAMRDL-TR-75-53) Avail NTIS HC A08/MF A01 CSCL 01/3 This report presents the results and data resulting from a research evaluation made of the reliability growth characteristics of the development and early production of UH-1D and AH-1G helicopters The major subjects covered by the technique and backed by research are off-board MTBF reliability (MTBF) growth versus test time and reliability growth versus calendar time A tentative technique for predicting helicopter reliability growth applicable to reliability program planning and management is also presented based on the results of the research An example of the technique procedures applied to a hypothetical helicopter is also presented " Author (GRA) N77-11042# Massachusetts Inst of Tech Can,bridge Aeroelas- tic and Structures Research Lab ANALOG COMPUTATION ASSESSMENT OF THE RISK OF STRUCTURAL FAILURE DUE TO CRACK GROWTH UNDER RANDOM LOADING Final Report. Feb 1974 - May 1975 Oscar Ornnger Richard F Harris and John F McCarthy. Jr Oct 1975 98 p refs (Contract F33615-74-C-3046 AF Pro) 1929) (AD-A025266 ASRL-TR-179-1 AFFDL-TR-75-123) Avail NTIS HC A05/MF A01 CSCL 01/3 Risks of fiacture were computed from a Monte Carlo simulation of the Paris equation for crack growth rate The simulation covered a total number of load events approximately equivalent to the estimated useful service life for a typical fighter airplane The simulation was implemented by development of a computation technique based on the analog computer Ap- proximately 200 simulations were run for each of 11 assumed initial crack sizes with the loading represented by a random noise signal filtered through a track-hold circuit to match a stress range exceedance distribution derived from an acceleration peak exceedance curve for the typical aircraft fleet The resulting data were sampled at four fractions of simulated service life and then reduced to four final crack size histograms for each initial crack size The raw data histograms were used to estimate parameter values for three-parameter Weibull distributions for final crack size in each case and a regression analysis was performed to correlate the distributions for risk analysis Mathematical risks of structural failure were computed and compared for several combinations of assumptions about the loading and the initial crack size distributions Author (GRA) N77-11043jjf Aerospace Medical Research Labs Wright- Patterson AFB Ohio INFLUENCE OF AIRCRAFT ANGLE OF ATTACK ON HIGH G COCKPIT DESIGN Philip V Kulwicki Mar 1976 31 p refs (AF Pro( 7184) (AD-A025083 AMRL-TR-75-124) Avail NTIS HC A03/MF A01 CSCL 01/3 The effects of aircraft angle of attack and flight path acceleration during high G fighter maneuvering on the position of the resultant G relative to the pilot are examined by means of a computer simulated dogfight engagement It is demonstrated that a transient shifting in position of the resultant G relative to an aircraft vertical reference is correlated with variations in flight path acceleration which occur due to pilot actuation of controls with attendant changes in flight path characteristics Although time intervals during high G turns are noted wherein high values for aircraft angle of attack coincide with high values for the position of resultant G forward of aircraft vertical these cases generally occur at subsonic (M equal to or less than 0 7) airspeeds and for the best case for which the maximum power throttle setting is elected For high G turns at transonic and supersonic speeds the associated angle of attack is substantially reduced as is the maximum inclination of resultant G forward of vertical for the best case of maximum power setting Application of 34 N77-11050 speed brakes or selection of an intermediate power setting has the effect of shifting the G-vector aft It is concluded that the arbitrary addition of a large angle equal to the aircraft angle of attack to the ejection seat back angle to provide added pilot protection against high G forces is not warranted Author (GRA) N77-11044*# National Aeronautics and Space Administration Ames Research Center. M off en Field. Calif RATIONALE AND DESCRIPTION OF A COORDINATED COCKPIT DISPLAY FOR AIRCRAFT FLIGHT MANAGE- MENT Daniel L Baty Washington Nov 1976 18 p refs (NASA-TM-X-3457. A-6663) Avail NTIS HC A02/MF A01 CSCL 01C The design for aircraft cockpit display systems is discussed in detail The system consists of a set of three beam penetration color cathode ray tubes (CRT) One of three orthogonal projects of the aircraft s state appears on each CRT which displays different views of the same information The color feature is included to obtain visual separation of information elements The colors of red. green and yellow are used to differentiate control performance and navigation information Displays are coordinated in information and color B B N77-11045# Lockheed-Georgia Co Marietta V/STOL AIRCRAFT NOISE PREDICTION (JET PROPUL SORS) Final Report. Jun 1974 - Jun 1975 N N Reddy D F Blakney J G Tibbets and J S Gibson Jun 1975 309 p refs Supersedes FAA-RD-73-145 (Contract DOT-FA72WA-3099) (AD-A028765/6. LG75ER0054 FAA-RD-75-125 FAA-RD-73-145) Avail NTIS HC A14/MF A01 CSCL 01/3 A computer program is presented for predicting the noise levels of V/STOL aircraft with jet-propulsive-lift systems Using the equations developed in this report the noise levels may also be estimated with hand calculations Vectored thrust externally blown flap upper surface blown flap internally blown flap and augmentor wing are the propulsive-lift concepts considered Semi-empirical equations are derived using the test results and theories for the following aircraft noise sources Internal engine let excess (core engine) high-lift system, airframe and auxiliary power unit The computer program predicts the perceived noise levels and tone corrected perceived noise levels for V/STOL aircraft at any specified sideline distance for known geometrical and operational parameters Author N77-11046*# AiResearch Mfg Co Phoenix Ariz COMPRESSOR BLADE SETTING ANGLE ACCURACY STUDY, VOLUME 1 Final Report F F HolmanandJ R Kidwell Jun 1976 107 p refs Sponsored by Army Air Mobility Res and Develop Lab Moffett Field Calif 2 Vol (Contract NAS3-18024) (NASA-CR-135068-Vol-1 AiResearch-73-311305-Vol-1) Avail NTIS HC A06/MF A01 CSCL21E The aerodynamic test of a small single stage highly loaded axial flow transonic compressor is covered The stage was modified by fabricating a 24 blade rotor with mis-set blades in a repeating pattern - two degrees closed from nominal, two degrees open from nominal and nominal The unit was instrumented to determine overall performance and average blade element data High- response dynamic pressure probes were installed to record pressure patterns at selected points in the flowpath Testing was conducted at speeds from 70 to 94% of design equivalent speed with a conventional casing and also with circumferential grooves over the rotor tip Testing indicated severe performance penalties were incurred as a result of the mis-set bladmg Lower flow pressure ratio, and efficiency were observed for the stage with or without casing treatment Periodic pressure variations were detected at every location where high response pressure sensors were located and were directly related to bladmg geometry Author N77-11047*# AiResearch Mfg Co Phoenix. Ariz COMPRESSOR BLADE SETTING ANGLE ACCURACY STUDY VOLUME 2 DATA COMPILATION Final Report •F F Holman and J R Kidwell Jun 1976 133 p Sponsored by Army Air Mobility Res and Develop Lab Moffett Field Calif 2 Vol (Contract NAS3-18024) (NASA-CR-135068-Vol-2 AiResearch-73-311305-Vol-2) Avail NTIS HC A07/MF A01 CSCL21E For abstract see N77-11046 N77-11O48*# AiResearch Mfg Co Phoenix Ariz SMALL AXIAL COMPRESSOR TECHNOLOGY. VOLUME 1 F F Holman, J R Kidwell and T C Ware Jun 1976 185 p refs Sponsored in part by Army (Contract NAS3-17846) (NASA-CR-134827-Vol-1 AiResearch-74-310862-Vol-1) Avail NTIS HC A05/MF A01 CSCL21E A scaled single-stage, highly-loaded axial-flow transonic compressor was tested at speeds from 70 to 110% design equivalent speed to evaluate the effects of scaling compromises and the individual and combined effects of rotor tip running clearance and rotor shroud casing treatment on the overall and blade element performance At design speed and 1% tip clearance the stage demonstrated an efficiency of 83 2% at 96 4% design flow and a pressure ratio of 1 865 Casing treatment increased design speed surge margin 20 points to 128% Overall performance was essentially unchanged An increase in rotor running clearance to 2 2% with smooth casing reduced design speed peak efficiency 5 7 points flow by 7 4% pressure ratio to 1 740 and surge margin to 5 4% Reinstalling casing treatment regained 3 5 points in design speed peak efficiency 4 7% flow increased pressure ratio to 1 800 and surge margin to 8 7% Author N77-11049*# AiResearch Mfg Co Phoenix Ariz SMALL AXIAL COMPRESSOR TECHNOLOGY. VOLUME 2 Final Report F F Holman J R Kidwell and T C Ware Jun 1976 329 p Sponsored in part by Army (Contract NAS3-17846) (NASA-CR-134827-Vol-2 AiResearch-74-310862-Vol-2) Avail NTIS H C A 1 5 / M F A 0 1 CSCL21E Complete computer printout data are presented and suppor- ting tests discussed in Volume I Author N77-11050*# National Aeronautics and Space Administration Lewis Research Center Cleveland Ohio SIMULATION OF FLIGHT-TYPE ENGINE FAN NOISE IN THE NASA-LEWIS 9X15 ANECHOIC WIND TUNNEL M F Heidmann and D A Dietrich Nov 1976 24 p refs Presented at the 92d Meeting of the Acoust Soc of Am San Diego. Calif 16-19 Nov 1976 (NASA-TM-X-73540 E-8972) Avail NTIS HC A02/MF A01 CSCL 20A Flight type noise as contrasted to the usual ground static test noise exhibits substantial reductions in the time unsteadiness of tone noise and in the mean level of tones calculated to be nonpropagatmg or cut-off A model fan designed with cuttoff of the fundamental tone was acoustically tested in the anechoic wind tunnel under both static and tunnel flow conditions The properties that characterize flight type noise were progressively simulated with increasing tunnel flow The distinctly lobed directivity pattern of propagating rotor/stator interaction modes was also observed Excess noise attributed to the ingestion of the flow disturoances that prevail near most static test facilities is substantially reduced with tunnel flow Author 35 N77-11051 N77-11051*# National Aeronautics and Space Administration Lewis Research Center Cleveland. Ohio EFFECTS OF FORWARD VELOCITY ON NOISE FOR A J85 TURBOJET ENGINE WITH MULTITUBE SUPPRESSOR FROM WIND TUNNEL AND FLIGHT TESTS James R Stone Jeffrey H Miles and Noel B Sargent Nov 1976 30 p refs Presented at the 92d Meeting of the Acoustical Soc of Am San Diego Calif 16-19 Nov 1976 (NASA-TM-X-73542 E-8974) Avail NTIS HC A03/MF A01 CSCL 20A Flight and wind tunnel noise tests were conducted using a J85 turbojet engine as a part of comprehensive programs to obtain an understanding of forward velocity effects on jet exhaust noise Nozzle configurations of primary interest were a 104-tube suppressor with and without an acoustically-treated shroud The installed configuration of the engine was as similac as possible in the flight and wind tunnel tests Exact simultaneous matcrvng of engine speed exhaust velocity and exhaust temperature was not possible and the wind tunnel maximum Mach number was approximately 0 27 while the flight Mach number was ap- proximately 0 37 The nominal jet velocity range was 450 to 640 m/sec For both experiments background noise limited the jet velocity range for which significant data could be obtained In the present tests the observed directivity dnd forward velocity effects for the suppressor are more similar lo predicted trends for internally-generated noise than unsuppressed jet noise Author N77-11052*)!' National Aeronautic"; and Space Administration Lewis Research Center Cleveland Ohio MACROSCOPIC STUDY OF TIME UNSTEADY NOISE OF AN AIRCRAFT ENGINE DURING STATIC TESTS B J Clark M F Heidmann and W J Kreim Nov 1976 14 p refs Presented at the 92d Meeting of the Acoustical Soc of Am San Diego Calif 16-19 Nov 1976 (NASA-TM-X-73556 E-8995) Avail NTIS HCA02/MFA01 CSCL 20A Static tests of aircraft engines can exhibit greater than 10 db random unsteadiness of tone noise levels because flow disturb- ances that prevail near test site facilities are ingested Presumably such changes are related to installation and test site features Some properties of unsteady noise observed during tests of a Lycommg YF-102 turbofan engine are presented Time and spatial variations in tone noise obta'ned from closely spaced far field and inlet duct microphones are displayed Long to extremely short intermittent tone bursts are observed Unsteadiness of the tone its harmonics and the broadband noise show little similarity In the far field identity of tone bursts is retained over a directivity angle of less than 10 deg In the inlet duct tone bursts appear to propagate axially but exhibit little circumferential similarity They show only slight relationship to tone bursts observed in the far field The results imply an intermittent generation of random mixtures of propagating duct modes Author N77-11053*# National Aeronautics and Space Administration Lewis Research Center, Cleveland Ohio CORE NOISE SOURCE DIAGNOSTICS ON A TURBOFAN ENGINE USING CORRELATION AND COHERENCE TECHNIQUES Allen Karchmer and Meyer Reshotko 1976 27 p refs Presented at the ninety-second Meeting of the Acoust Soc of Am San Diego Cahf 16-19 Nov 1976 (NASA-TM-X-73535 E-8961) Avail NTIS HC A03/MF A01 CSCL 21 E Fluctuating pressure measurements at several locations within the core of a turbofan engine were made simultaneously with far field acoustic measurements Correlation and coherence techniques were used to determine the relative amplitude and phase relationships between core pressures at these various locations and between the core pressures and far field acoustic pressure The combustor is a low frequency source region for acoustic propagation through the core nozzle and out to the far field The relation between source pressure and the resulting sound pressure involves a 180 degree phase shift and an amplitude transfer function which varies approximately as frequency squared This is consistent with a simplified model using fluctuating entropy as a source term Author N77-11054*# AiResea'ch Mfg Co Phoenix Ariz STUDY OF SMALL TURBOFAN ENGINES APPLICABLE TO SINGLE-ENGINE LIGHT AIRPLANES Final Report G L Merrill Sep 1976 118 p refs (Contract NAS2-8582) ( N A S A - C R - 1 3 7 9 4 4 AiResearch-76-211893) Avail NTIS HC A06/MF A01 CSCL 21E The design efficiency and cost factors are investigated for application of turbofan propulsion engines to single engine general aviation light airplanes A companion study of a hypothetical engine family of a thrust range suitable to such aircraft and having a high degree of commonality of design features and parts is presented Future turbofan powered light airplanes can have a lower fuel consumption lower weight reduced airframe maintenance requnements and improved engine overhaul periods as compared to current piston engined powered airplanes Achievement of compliance with noise and chemical emission regulations is expected without impairing performance operating cost or safety Author N77-11055*$ National Aeronautics and Space Administration Washington D C AIRCRAFT FUEL CONSERVATION TECHNOLOGY TASK FORCE REPORT. SEPTEMBER 10,1975 10 Sep 1975 141 p (NASA-TM-X-742951 Avail NTIS HC A07/MF A01 CSCL 21E An advanced technology program is described for reduced fuel consumption in air transport Cost benefits and estimates are given for improved engine design and components turboprop propulsion systems active control systems laminar flow control and composite primary structures A H N77-11057*jj( National Aeronautics and Space Administration Lewis Research Center Cleveland Ohio METHOD OF DISCRETE MODELING AND ITS APPLICA- TION TO ESTIMATION OF TF30 ENGINE VARIABLES Dale J Arpasi and William M Bruton Oct 1976 40 p refs (NASA-TM-X-3443 E-8560) Avail NTIS HC A03/MF A01 CSCL 21 E A method of discrete modeling is presented that effectively isolates steady state model accuracy from dynamic model accuracy The steady state model may be generated from the engine design equations with any desired degree of accuracy The dynamic model is generated by applying a step disturbance of a manipulated variable to an open loop engine simulation The sampled response of the variable is combined with the steady state model s response to form a set of weighting factors These weighting factors are then used to weight past values of the manipulated variable thus forming the dynamic model The method is used to estimate various TF30-P-3 engine variables A dynamic trim function is developed to compensate for the dynamic nonlmearities of the variables as well as for inaccuracies in dynamic definition The trim function is shown to be realted to the square root of the sum of the squares of the weighting factors obtained at various engine operating conditions Finally, the estimation of variables without dynamic modeling n fuer Verteidigung (LBF-FB-109/76) Avail NTIS HC A04/MF A01 i_ab fuet B- .'Mebsfesl'okei' ^a.m^adt W»T be' OM 38 Reliable 'ife 11 ,ves- were HSTab ishcd for a ioad sequence and a cumulative frequency LJis[nbu~'on v^nch ate t/pical at the wing structure of transport aircraft The life estimation for details subjected to load spectra varying from that applied to the specimens were demonstrated using the Relative Miner s rule It was found that for large differences between the test load and the design load spectra the Relative Miner's rule is not advantageous As the difference between the estimated life based on the Relative Miners rule and the corresponding tests results could to a laige extent be explained by the action of residual stresses a suitable correction was introduced The correction was applied to the specimens of this investigation using empirically derived data The results pioved an effective refinement of the Relative Miners rule leading to very accurate life predictions Author (ESA) N77-11447# Ldboratorium fuer Betriebsfestigkeit Darmstadt (West Germany) COMPILATION OF M E A S U R E S TO INCREASE THE FATIGUE STRENGTH OF AIRCRAFT STRUCTURES D Schuetz and J J Gerharz 5 Nov 1975 96 p refs In GERMAN ENGLISH summary (LBF-TB-126/75) Avan NTIS HC A05/MF A01 Lab fuer Betnebsfestigkeit Darmstadt West Ger DM 42 The compilation is the result of a literature survey and was made to comprehensive!/ imorm the designer and to facilitate the selection of suitable measures for a fatigue critical struc- tural detail Together with the description of the measures, improvement factors are presented which should be used only as lead values A total of 40 compilations of structures such as eye rods open holes and riveted screw joints are presented Author (ESA) N77-11449# Royal Netherlands Aircraf t Factories Fokker Schiphol Oost FRACTURE TOUGHNESS OF 8mm 2024-T3 NON CLAD PLATE WITH LONG CENTRAL CRACKS A H LaCrois 2 Jun 1975 9 p (FOK-R-1879) Avail NTIS HC A02/MF A01 Fracture toughness tests were carried out with center notched specimens of 8 mm 2024-T3 non clad plate to predict the fail safe properties of laminated airbus links A K-value (fracture toughness) of 142 kgf x mm to the 3/2th power was established using the Feddersen method The Feddersen method for presenting fracture toughness test results is briefly described ESA N77-11450/jf National Aerospace Lab , Amsterdam 'Netherlands) Structures and Materials Div CALCULATION OF VIBRATION MODES AND RESONANCE FREQUENCIES OF THE NORTHROP NF-5 H H Ottens 15 Apr 1975 71 p refs Supersedes NLR-TR- 74012-U Sponsored by Directorate of Mater Air RNLAF (NLR-TR-75050-U NLR-TR-74012-U) Avail NTIS HC A04/MF A01 A calculation of global values of resonance frequencies vibration modes and generalized masses was made for the Northrop NF-5 in order to investigate the potentialities of both the finite element method and the component mode method in obtaining these characteristics The configurations considered involve full tiptanks 70 Ibs stores at the outboard pylons full or empty 275 USG tanks at the inboard pylons and a 150 USG tank at the center line pylon For these configur-tions a comparison was made with ground vibration test results ESA N77-11478# Air Force Flight Dynamics Lab. Wright-Patterson AFB. Ohio CURRENT PRACTICE ON ESTIMATING CRACK GROWTH DAMAGE ACCUMULATION WITH SPECIFIC APPLICATION TO STRUCTURAL SAFETY DURABILITY AND RELIABILITY Final Report. 15 Jan - 15 Mar 1975 Howard A Wood Joseph Gallagher Robert M Engle and John M Potter Jan 1976 67 p refs (AF Proj 1367) (AD-A025499. AFFDL-TR-75-32) Avail NTIS HC A04/MF A01 CSCL 11/6 40 This report provides a brief summary of current practice on predicting crack growth damage accumulation with specific applications to current USAF policies on Safety and Durability Analytical procedures are required to determine safe crack growth-life intervals and to estimate economic limits of crack growth Reliability and risk analyses are discussed to illustrate their impact on structural decisions The life prediction methodology will be examined to illustrate the major effects of the structural parameters (geometry) the material parameters (basic crack growth rate) and loading (usage patterns) Examples are cited to give indication of confidence in making life predictions A summary of procedures for estimating service loads and chemical-thermal environments is included as they relate to simulating usage effects in the laboratory GRA 41 SUBJECT INDEX AERONAUTICAL ENGINEERING/ A Special Bibliography (Suppl 80) Typical Subject Index Listing FEBRUARY 1977 rH SUBJECTHEADING BODHABIC LOADS 1 Early operation experience on the vind turbine rotor blade loa [HASA-TH-I-71601] TITLE REPORT NUMBER L TITLEEXTENSION EBDA/HASA 100 ~l " M77-10640 ACCESSION NUMBER The title is used to provide a description of the subject matter When the title is insufficiently descriptive of the document content a title extension is added separated from the title by three hyphens The NASA or AIAA accession number is included m each entry to assist the user in locating the abstract in the abstract section of this supplement If applicable a report number is also included as an aid in identifying the document A-7 AIBCBAFT Full temperature range protective system for fastener areas of carrier-based naval aircraft [AD-A024523] N77-10210 A-10 AIBCBAFT Height and balance considerations in the design of the A-10A close air support aircraft [SAKE PAPER 1104] A77-12183 ABLATIVE BA1EBIALS Strength of glass-fibre-reinforced plastics at one-sided heating aircraft ablative thermal protection coatings [IAF PAPIB 76-200] A77-10939 ACODSTIC ATTEHUATIOH Inlet noise suppressor design metnod based upon the distribution of acoustic power with mode cutoff ratio N77-10311 ACOUSTIC BEASDBEBESIS Signal-treatment methods during aircraft-engine inspection based on vibroacoustic noises A77-11603 Additional experiments with a four-bladed cyclic pitch stirring model rotor, part 2 of second yearly report tNASA-CB-137966J S77-10006 Acoustical evaluation of the NASA Langley V/STOL wind tunnel [NASA-CR-1450d7] S77-11068 ACOUSTIC FBOPEBIIES Acoustical evaluation of the NASA Langley V/STOL wind tunnel [NASA-CR-145087] N77-11068 ACOUSTIC SCATTERING Measurement of wake vortex strength by Deans of acoustic back scattering A77-11712 ACTDATOBS Design and fabrication of an 8000 PSI control-by-wire actuator for flignt testing in a T-2 C airplane [AD-A02UU87] N77-11065 ADAPTIVE CONTB01 The stochastic control of the F-8C aircraft using the multiple model adaptive control /HMAC/ method A77-12428 Application or Liapunov model - Tracking parameter identification for tne Cri-47 helicopter A77-12460 ADHESIVE BOBDIHG Besearch on adhesive bonding and surface characteristics of metals at Fokker-VPH [FOK-B-1816] H77-11U05 AEBODTHAHIC BALABCE ieight and balance considerations in the design of the A-10A close air support aircraft [SAHE PAPEB 1104] ' 477-12183 AEBODIHAHIC CHABACTEBISTICS Practical requirements in industry --- in computerized aerodynamic calculations for aircraft A77-12552 Methods studies on system identification from transient rotor tests [HASA-CB-1 37965] B77-10005 High supersonic aerodynamic characteristics of five irregular planform wings vith systematically varying mng fillet geometry tested in the NASA/LaBC 4-foot OPHT (LEG 2) (LA45A/B) [NASA-CB-1 47628] B77-10010 Experimental study of the aerodynamics of a helicopter rotor in translational flight. Two dimensional simulation of the effects due to cyclic variations of the velocity vector [AAAF-NT-76-20] 1177-10019 Prediction Methods for Jet V/STOL Propulsion Aerodynamics, volume 1 [AD-A024022] 1177-10068 Prediction Methods for Jet V/STOL Propulsion Aerodynamics, volume 2 [AD-A024023] B77-10069 Lifting surface theory for rectangular wings B77-10347 Application of the nonlinear vortex-lattice concept to aircraft-interference problems N77-10349 An application of the suction analog for the analysis of asymmetric flow situations N77-10350 Inverse transonic airfoil design including viscous interaction 1177-10354 Advanced transonic aerodynamic technology B77-10365 Calculation of the longitudinal aerodynamic characteristics of wing-flap configurations with externally blown flaps [NASA-CB-2705] Small axial compressor technology, volume [NASA-CB-13I4827-VOL-1 ] Small axial compressor technology tables [NASA-CR-134827-VOL-2] AEBODYBABIC COEFFICIENTS Performance of steady and intermittent blowing jet flaps and spanwise upper surface slots [AD-A024364 ] AEBODYBABIC COSPIGOBATIONS Anisotropic radiatively coupled wedge flow A77-10218 Structural tests of aerodynamic surfaces - A systems approacn to analysis and design A77-12206 Methods for elliptic pronlams in external aerodynamics A77-12554 The impact of emissions standards on the design of aircraft gas turbine engine combustors [NASA-TH-X-73490] N77-10063 A computational system for aerodynamic design and analysis of supersonic aircraft. Part 2: User's manual [NASA-C8-2716] 1177-11005 N77-11006 N77-11048 volume 2 --- 1177-11049 N77-10027 AEBODINABIC fOBCBS SUBJECT INDEX AEBOD'NUBIC FOBCES Forces on unstaggered airfoil cascades in unsteady in-phase motion [ASBE P4PEB 76-FE-S] 477-10851 An investigation of the effect on aerodynamic forces caused by the addition of end plates to helicopter rotor blades [AD-A0235I11] H77-10024 AEBODIHAHIC HEATIBG Strength of glass-fibre-reinforced plastics at one-sided heating aircraft ablative thermal protection coatings [IAF PAPIB 76-200] A77-10939 ABHODYSiBIC IHTEBFEBEHCB Applications of linearised supersonic wing theory to the calculation of some aircraft interference flows A77-12566 AEBODYHAHIC LOADS . Early operation experience on the ERDA/NASA 100 kw wind turbine rotor blade loads [NASA-TB-X-71601] N77-10640 AEBODYNABIC BOISE A test facility for aircraft jet noise reduction. II A77-118i(t Experiments on the feasibility of aero-acoustic measurements in the 3-ffl low speed wind tunnel of the DFVIB-AVA [ESA-TT-311] N77-10873 ABBODYNAHIC STABILITY Mechanism of stabilization of the 'separation point1 of a vortex during flow of a stream at low subsonic velocity over a delta wing [NAS4-TT-F-17283 ] N77-10012 The design, analysis and testing of a low budget wind tunnel flutter model with active aerodynamic controls, volume 2 [AD-A024480] N77-10090 AERODYNAMICS Project SCUID: 4 cooperative program of fundamental research related to jet propulsion [AD-A02«001] N77-11059 ABBOELASTICITY On the identification of state-derivative-coupled systems A77-12448 Aeroelastic analysis for helicopter rotor blades with time-variable, non-linear structural twist and multiple structural redundancy: Hathematical derivation and program user's manual [NASA-C8-2638] N77-10556 AERONAUTICAL ENGINEERING Aircraft fuel conservation technology. Task force report, September 10, 1975 [NAS4-TH-X-74295] 877-11055 AEROSPACE ENGINEERING Application of optimality criteria to automated structural design A77-10207 AEROSPACE MEDICINE Investigation and analysis of the huaan factors in aircraft accidents 477-10500 AEBOTHEBHODYHAHICS Air-cooled turbine cascade effectiveness criterion 477-12503 AFBICA Transport progress in practice: Air transport in Africa - East African Airways Corporation experience 477-11312 AFTERBURNING Experimental study ot combusticn time in two-stage combustion process A77-12511 AILERONS Optimal control for tne rolling pullout maneuver of a modern fighter aircraft 477-12444 AIB CABGO nesponsiDillties and assurances with regard to cargo transport - Air transport law A77-12472 AIB COOLIBG Pressure loss coefficient of impingement cooled leading edge system of a turbipe blade A77-10772 Film cooling with injection through slots A77-10773 Air-cooled turbine cascade effectiveness criterion A77-12503 Analytic and experimental study of turbine rotor blade temperature A77-12522 Emissions of an AVCO Lycoming 0-320-DIAD air cooled light aircraft engine as a function of fuel-air ratio, timing, and air temperature and humidity [BASA-TH-X-73500] N77-10058 AIB FLOB Computational methods and problems in aeronautical fluid dynamics Book A77-12551 Some problems of unsteady flow about aircraft A77-12560 AIB INTAKES Transonic performance of Hach 2.65 auxiliary flow axisynmetric inlet [N4SA-CB-2747] N77-10056 AIB JETS Laser air-jet engine earth-based pulse radiation created thrust A77-11887 AIB NAVIGATION Concorde navigation A77-10200 AIB POLLUTION The fuel approach to control emissions from aircraft [IAF PAPEB 76-111] A77-10911 Experimental clean combustor program: Noise study [NASA-CB-135106] N77-1Q064 AIB TBAFFIC CONTBOL Reliability of automated flight service stations A77-10442 LH2 airport requirements study £NASA-CB-2700] N77-10032 The establishment of safe separations between aircraft in flight [NLB-BP-75041-0] N77-11020 AIB TBANSPOBTATION Beyond supersonic transport [IAF PAPEB ISL-76-66] A77-10972 Transport progress in practice: Air transport in Africa - East African Airways Corporation Experience A77-11312 Responsibilities and assurances with regard to cargo transport - Air transport law A77-12472 An analysis of tne intrastate air carrier regulatory forum. Volume 2: Technical report [AD-A023762] N77-10035 Baseline energy forecasts and analysis of alternative strategies for airline fuel conservation [PB-255351/9] S77-10690 Toward new heights air transportation in the Soviet Union [NASA-TT-F-17248 ] N77-11019 AIBCBAFT ACCIDENT INVESTIGATION Investigation and analysis of the human factors in aircraft accidents A77-10500 AIBCBAFT ACCIDENTS Competition for airspace - Bird strikes and aircraft operations A77-11261 AIBCBAFT BRAKES Development of aircraft brake materials [ASLE PREPRINT 76-LC-1B-3] A77-11195 AIBCBAFT COHPABTBBHTS Tnermal analysis of flight vehicle compartment structure A77-12509 AIBCBAFT CONFIGURATION Height and balance considerations in the design of the A-10A close air support aircraft [SArfE PAPER 1104] A77-12183 Advanced design composite aircraft, the next step for composites [SAKE PAPEB 1105] A77-12184 The next-generation subsonic transport [SAKE PAPEB 1127] A77-12195 AIBCBAFT CONTBOL Optimal ride control for the Twin Otter, STOL aircraft 477-10336 A-2 SUBJECT INDEX AIBCBAFI HODELS Effects of atmospheric conditions on the operating characteristics of supersonic cruise aircraft [IAF PaPEB 76-112] 477-10912 The stochastic control of the P-8C aircraft using the multiple model adaptive control /MBAC/ method 477-121428 Design considerations for laminar flow control aircraft N77-10366 Design of active controls for the N A S A F-8 digital xly-by-wire airplane 077-10377 Performance analysis of flexible aircraf t with active control N77-10378 AIBCBAFT DESIG8 Israel's pride of Lions K f i v f igh te r aircraft program 477-10521 YC-14 - All blow and no p u f f general design details 477-10525 Application of circulation control rotor technology to a stopped rotor aircraft design X-wing V/STCL A77-11277 'C.221, the new French target drone 477-11625 Estimating procedures associated with aircraft modifications [ S A N E P A P E E 1101] 477-12131 Fuselage analytical weight estimation method [ S A H E P A P E E 1102] 477-12182 Weight and balance considerations in the design of the &-10A close air support aircraft [ S A h E P A P E E 1101] A77-12183 Advanced design composite aircraft , the next step for composites [ S A K E PAPEE 1105] A77-12184 Application of advanced technology to fu tu re long-range aircraft [ S A H E PAPEB 1126] A77-12194 The next-generation subsonic transport [ S A W E P A P E B 1127] 477-12195 Thermal analysis of flight vehicle compar tment structure 477-12509 Practical requirements in industry in computerized aerodynamic calculations for aircraft 477-12552 Transonic flows calculation by integral equation, relaxation and finite difference metnods 477-12561 4 transonic hodograph theory for aerofoil design 477-12561 The technical basis for a national civil aviation research, technology, and development /BT & D/ policy; Proceedings of the Workshop Conference, Crystal City, Va., (larch 10-12, 1976 1 477-12927 4n analytical study for subsonic oblique wing transport concept [NAS4-CB-137896] - N77-10045 An analytical study for subsonic oblique wing transport concept [NAS4-CB-137897] N77-10046 Inverse transonic airfoil design including viscous interaction 1177-10354 Preliminary sizing and performance evaluation of supersonic cruise aircraft [N4S4-TM-X-73936] N77-11031 4IBC64FT ENGINES Future trends in aero gas turbine design. II - Unconventional engines 477-11595 Signal-treatment methods during aircraft-engine inspection based on vibroacoustic noises 477-11603 Magnetic particle inspection of aviation engine vanes A77-11606 Dynamic-stress-data management for aeromechanical testing of turbomachinery 477-12175 Equation solution accuracy in calculating jet engine characteristics 477-12502 Emissions of an AVCO Lycoming 0-320-DIAD air cooled light aircraft engine as a function of fuel-air ratio, timing, and air tenperature and humidity [SASA-TM-X-73500] N77-10058 Advanced combustion techniques for controlling NO sub x emissions of high altitude cruise aircraft [NASA-TM-X-73473] N77-10062 Effect of air temperature and relative humidity at various fuel-air ratios on exhaust emissions on a per-mode basis of an Avco Lycoming 0-320 DI4D 'light aircraft engine. Volume 2: Individual data points [N4S4-TB-X-73507] N77-10066 Performance of 1.15-pressure-ratio fan stage at several rotor olade setting angles with reverse flow [NASA-TB-X-3451] N77-11008 AIBCBAFT FOE1 SYSTEMS The fuel approach to control emissions from aircraft [IAF PAPEE 76-111] 477-10911 Aircraft fuel conservation technology. Task force report, September 10, 1975 [NASA-TM-X-74295] N77-11055 Seduction of gaseous pollutant emissions from gas turbine coDbustors using hydrogen-enriched jet fuel [N4S4-CH-1191U6] N77-11198 4IECB4FI FUELS Survey of hydrogen energy application projects 477-12778 Hydrogen-fueled subsonic aircraft: A perspective N77-10344 AIBCBAFT H4Z4BDS Bird hazards to aircraft: Problems and prevention of bird/aircraft collisions Book 477-10697 AIBCBAFT HIDB40LIC SYSTEHS Reliability applied to landing gear and hydraulics A77-12116 AIBCBAFI INOUSIBI Co-operation in the European aircraft manufacturing industry and among the scheduled airlines /Brancker Memorial Lecture/ 477-11311 Practical requirements in industry in computerized aerodynamic calculations for aircraft 477-12552 AIBCBAFT INSTBOHBBTS Investigation into tae optimum use of advanced displays in future transport aircraft A77-11594 AIBCBAFT LANDING Simulating the last 100 ft computer-generated images for landing training A77-10648 Application of the nonlinear vortex-lattice concept to aircraft-interference problems H77-10349 A flight investigation of piloting techniques and crosswind limitations during visual STOL-type landing operations [NASA-TN-D-8284] N77-11001 Landing practices of general aviation pilots in single-engine light airplanes [NASA-TN-D-8283] N77-11033 AIBCBAFI MAINTENANCE Interface between maintainability and commercial aircraft spares support 477-101483 Maintaining transport aircraft A77-12069 Concorde maintenance as seen by the designer - The maintenance program 477-12115 Bearing restoration by grinding [N4SA-CB-149188] N77-11404 AIBCBAFT BAHBUVEBS Optimal control for the rolling pullout maneuver of a modern fighter aircraft 477-12444 The pursuit-evasion problem of two aircraft in a horizontal plane 477-12452 AIBCBAFT MODELS On the identification of state-derivative-coupled systems A77-12448 A-3 AIRCRAFT BOISE SUBJECT INDEX New buffeting acquisition methods data acquisition, military aircraft [AAAF-NT-76-8] " N77-10051 A wind tunnel captive aircraft testinq technique PAD-A023690] .177-11037 AIRCRAFT NOISE Rotational noise measurement in a wind tunnel by total sampling synchronization A77-11281 New developments in Dloun flap noise technoloqy [NASA-CH-115086] N77-10013 V/STOL aircraft noise prediction (jet prcpulsors) computer program UD-A028765/6] N77-11015 AIRCRAFT PEHFOBHANCE YC-11 - All blow and no puff general design details A77-10525 Concorde - Endurance fl ights results A77-12111 Final approach per formance monitor [AD-A028513/0] N77-11021 AIRCRAFT PILOTS Rationale and description of a coordinated cockpit display for aircraft f l ight managemen t [NASA-TH-X-3157] N77-11011 AIRCRAFT BELIABI1ITI Helicopter reliability growth evaluation [AD-A025265] N77-11011 AIRCRAFT SAFETY Aircraf t g round f i re suppression and rescue systems. Characteristics of k inemat ic jet fuel fires cascading and rod fuel geometries [AD-A024117] N77-11022 Rationale and description of a coordinated cockpit display for aircraft f l ight management [NASA-TH-X-3457] N77-1KW4 Conference on the Development of Fire-Resistant Aircraf t Passenger Seats [NASA-TM-X-73111 ] N77-11111 AIRCRAFT STABILITY Advanced control systems for helicopters A77-11273 A rfing on the SA.341 Gazelle helicopter and its efrects A77-11282 AIRCRAFT STRDCTDBES Resizing procedure for structures under combined mechanical and thermal loading A77-10211 Strength of glass-fibre-reinforced plastics at one-sided heating aircraft ablative thermal protection coatings [IAF PAPER 76-200] A77-10939 Estimating fatigue-crack lives for aircraft - Techniques A77-11177 On the identification of state-derivative-coupled systems A77-12118 Hingtip vortex dissipator for aircraft [NASA-CASE-LAR-11615-1] N77-10001 Compilation of measures to increase the fatigue strength of aircraft structures [LSI-IB-126/75] N77-11117 Current practice on estimating crack growth damage accumulation with specific application to structural safety durability and reliaoility [AD-A025199] N77-11178 AIRCRAFT BAKES Measurement of wake vortex strength by means of acoustic back scattering A77-11712 Effects of jets, wakes, and vortices on lifting surfaces [NASA-TM-X-73971] H77-10998 Development of predictive wake vortex transport model for terminal area wake vortex avoidance [AD-A029019/1] 1177-11002 Holographic flow visualization of aircraft wakes [NASA-CR-119182] N77-11365 AIRFOIL PROFILES Approximate transonic profile flow with shock A77-10251 Some problems of unsteady flow about aircraft A77-12560 An extended integral equation method for the steady transonic flow past a two-dimensional aerofoil A77-12562 A transonic nodograph theory for aerofoil design A77-12561 AIRFOILS The development of a computer aided airfoil design procedure including preliminary wind tunnel experiments on a low Reynolds number hign lift section, volume 1 [AD-A021361 ] N77-10028 Test verification of a transonic airfoil design employing active diffusion control [AD-A021297] N77-10029 Inverse transonic airfoil design including viscous interaction N77-10351 Viscous interaction with separation in transonic flow [NASA-TT-F-17187] N77-10997 AIHFRAHE MATERIALS Mechanism of material fatigue during the crack initiation staye [ICAF-DOC-895] N77-11141 AIHFRAHES Design mecnanical properties, fracture toughness, fatigue properties, exfoliation and stress-corrosion resistance of 7050 sheet, plate, hand forgings, die forgings and extrusions [AD-A024609] N77-10195 Calculation of multi-contour thin-walled structures by the method of sections [NAS»-TT-F-17281] N77-11029 AIRLINE OPERATIONS Concorde navigation A77-10200 Interface between maintainability and commercial aircraft spares support A77-10183 Competition for airspace - Bird strikes and aircraft operations A77-11261 Co-operation in the European aircraft manufacturing industry and among the scheduled airlines /Brancker Memorial Lecture/ A77-11311 Transport progress in practice: Air transport in Africa - East African Airways Corporation Experience A77-11312 Aircraft loadaoility parameters - Some results of an airline survey [SAKE PAPER 1116] A77-12201 An exploratory study to determine the integrated technological air transportation system ground requirements of liguid-hydrogen-fueled subsonic, long-haul civil air transports [NASA-CH-2699] N77-10033 AIRPORT PLANNING LH2 airport requirements study [NASA-CB-2700] N77-10032 AIRPORTS Competition for airspace - Bird strikes and aircraft operations A77-11261 AIRSPACE The establishment of safe separations between aircraft in flight [NLR-HP-75011-U] N77-11020 AIRSPEED Army preliminary evaluation YOH-58A helicopter with a flat-plate canopy [AD-A021501] N77-11039 Effects of forward velocity on noise for a J85 turbojet engine with multitube suppressor from wind tunnel and flight tests [NASA-TH-X-73512] H77-11051 ALGOL Program system for computer calculations of jet engine characteristics Russian book A77-10349 ALL-BEATHEH LANDING SYSTEBS A systems approach to all weather landings A77-10138 ALDHINOH ALLOTS Strength of compressor wheels of low-ductility alloys A77-10383 A-4 SUBJECT IBDBI BOEOB-BPOII COBCOOIDS Design mechanical properties, fracture toughness, fatigue properties, exfoliation and stress-corrosion resistance of 7050 sheet, plate, hand forgings, die forgings and extrusions [AD-A021609] 877-10195 ABALOG COHPOTBBS Analog coaputation assessoent of the risk of structural failure due to crack growth under random loading [AD-A025266] 877-11012 ABBCHOIC CHAHBEBS A test facility for aircraft jet noise reduction. II A77-11844 SmBlation of flight-type engine fan noise in the NASA-Lewis 9115 anechoic wind tunnel [BASA-TH-X-73540] H77-11050 AHGLE OF AltiCK Experimental investigation of the boundary layer on a rotating cylinder A77-10208 Pressure distributions over frontal /nose/ surfaces of bodies of revolution in transonic flow at angles of attack of 0 to 10 deg A77-10664 Influence of aircraft angle of attack on high G cockpit design [AD-A025083] 877-11043 ABGULAB BESOLOTIOB Compressor blade setting angle accuracy study, volume 1 [BASA-CB-135068-VOL-1] B77-11046 A8ISOTBOPIC PLOIDS Anisotropic radiatively coupled wedge flow A77-10218 AHISOIBOPI Investigation of a bearingless helicopter rotor concept having a composite primary structure [NASA-CB-2637] N77-10044 A8IISaBHABI§B RABFABE AIBCB&F1 Catapult launch fatigue investigation of the model S-2 E airplane [AD-A024071] H77-11038 ATHOSPBEBIC HODELS Development of predictive wake vortex transport model for terminal area wake vortex avoidance [AD-A029049/4] 877-11002 ATHOSPBEBIC 1EBFBBAIOBE Emissions of an AVCO Lycoming 0-320-DIAD air cooled light aircraft engine as a function of fuel-air ratio, timing, and air temperature and humidity [NASA-TH-X-73500] 877-10058 ATBOSPBEBIC TDBBOIEHCE Effects of atmospheric conditions on the operating characteristics of supersonic cruise aircraft [IAF PAPEB 76-112] A77-10912 ATTITDDB COBTE01 The stochastic control of the F-8C aircraft using the multiple model adaptive control /HHAC/ method A77-12428 ATTITDDE STABILITY Dual-spin spacecraft dynamics under conditions of a rotating unbalanced platform and rotor asymmetry [IAF PAPEB 76-019] A77-10882 AUTOMATIC COBTBOL Reliability of automated flight service stations A77-10442 Display/control reguirements for vrOL aircraft [BASA-CB-145026] 877-11030 AOTOHATIC PILOTS Effects of atmospheric conditions on the operating characteristics of supersonic cruise aircraft [IAF PAPEB 76-112] A77-10912 AVAILABILITY Reliability of automated flight service stations A77-1014I42 AVIOHICS Estimating procedures associated with aircraft modifications [SAME PAPEE 1101] A77-12181 AXIAL PLOR A note on the acoustic effect of non-uniformly distributed stator rows A77-10347 Compressor blade setting angle accuracy study, volume 1 [NASA-CE-135068-VOL-1] 877-11046 Compressor blade setting angle accuracy study. Volute 2: Data compilation [HASA-CB-135068-VOL-2] ^ H77-11047 AIIAL STBESS Resizing procedure for structures under combined mechanical and thermal loading A77-102"ia AIISVBHBTBIC FLO! Compressible snbcritical flow through axially syaaetric sharp-lipped orifices and nozzles A77-12555 transonic perfomance of Hach 2.65 auxiliary flow axisyaoetnc inlet [HASi-C8-2747] H77-10056 B BACKSCATTBBIBG Measurement of wake vortex strength by Beans of acoustic back scattering A77-11712 BALL BEABIHGS Bearing restoration by grinding [HASA-CB-149188] 877-11101 BASE BEATIBG Normal impingement of a supersonic jet on a plane: A basic study of shock-interference heating [AD-A021511] 877-10026 BEBDIBG DIAGBAHS An experimental study of the nonlinear stiffness of a rotor blade undergoing flap, lag and twist deformations [BASA-CB-137969] 877-10009 BIBLIOGBAPHIES Compilation of measures to increase the fatigue strength of aircraft structures [LBF-TB-126/75J M77-11147 BIBD-AIBCBAFI COLLISIOBS Bird hazards to aircraft: Problems and prevention of bird/aircraft collisions Book A77-10697 Competition for airspace - Bird strikes and aircraft operations A77-11261 BLADE TIFS An experimental study of the nonlinear stiffness of a rotor blade undergoing flap, lag and twist deformations [BASA-CB-137968] 877-10008 BLOBING Three-component measurements on a model of a light STOL aircraft with chordwise blowing [ESA-TT-299] 877-10052 BLOB! BODIES Flow of a radiating gas over a blunt body with intense vaporization A77-10416 BO-105 BELICOPTBB Uingeless rotor dynamics in high speed flight A77-11280 BOATTAILS An improved projectile boattail, part 2 [AD-A024073] 877-11016 BODIES OF BBVOLOTIOB Pressure distributions over frontal /nose/ surfaces of bodies of revolution in transonic flow at angles of attack of 0 to 10 deg A77-10664 Flow interaction near the tail of a body of revolution. I - Plow exterior to boundary layer and wake [ASHE PAPEB 76-PE-B] A77-10855 Flow interaction near the tail of a body of revolution. II - Iterative solution for flow within and exterior to boundary layer and wake [ASaE PAPEB 76-FE-N] A77-10856 BOEIBG AIBCBAFT TC-14 - All blow and no puff general design details A77-10525 BOBDIBG Advances in engineering science, volume 1 [NASA-CP-2001-VOL-1] N77-10230 BOBOB-BPOXI COHFODBDS Program for establishing long-time flight service performance of composite materials in the center wing structure of C-130 aircraft. Phase 4: Ground/flight acceptance tests CSASA-CB-145043] 877-11032 A-5 BOOHOABI IAT8B COHTBOI SUBJECT INDEX BOUNDARY LAY8B COBTEOL An integral equation method for boundary interference in a perforated-nail wind tunnel at transonic speeds [AD-A023U93] N77-10023 Test verification of a transonic airfoil design employing active diffusion control [AD-A02U297] N77-10029 BOUNDABY LAYBB EQUATIONS The hypertoolicity of integral equations of momentum in a three-dimensional incompressible laminar boundary layer A77-10665 BOUNDARY IAYBB FLOI Flow interaction near the tail of a body of revolution. I - Flow exterior to boundary layer and wake [ASMS PAPEB 76-FE-fl] A77-10855 Some problems of unsteady flow about aircraft A77-12560 Supersonic flows numerical computation for steady inviscid flowfield A77-12565 BOONDABY 1AYBB SEEABATION Controlled and uncontrolled flow separation in three dimensions [LB-591] N77-10999 BOUNDARY LATEB STABILITY Experimental investigation of the boundary layer on a rotating cylinder A77-10208 BODNDAHY LAYEB TRANSITION Experimental investigation of the boundary layer on a rotating cylinder A77-10208 BODNDABY LAYEBS Influence of wind tunnel wall boundary layers on two dimensional transonic tests [AAAF-NT-76-13] 877-10083 BOUNDARY VALUE PBOBLEHS Thermal analysis of flight vehicle compartment structure A77-12509 A transonic hodograph theory for aerofoil design A77-12564 BUFFETING Buffeting problems leading and trailing edge flow separation [AAAF-NT-76-7] N77-10050 New buffeting acquisition methods data acquisition, military aircraft [AAAF-NT-76-8] N77-10051 BDBNING TIME Experimental study of combustion time in two-stage combustion process A77-12511 BYPASSES Selection cf compressor pressure ratio of small GTE installed in bypass turbojet engine fan duct A77-12513 C-130 AIBCBAFT Full temperature r fastener areas o [AD-A024523) Program for establ performance of c wing structure o Ground/flight ac [NASA-CS-1150i)3] C-1U1 AIBCBAFT Test verification employing active [AD-A021297] CALIFOBHIA An analysis of the regulatory forum [AD-A023761 ] CAMBBBED KINGS Applications of li to the calculati flows CANOPIES A r a y prel iminary e with a flat-plat [ A D - A 0 2 4 5 0 1 ] ange protective system for f carrier-based naval aircraft N77-10210 ishing long-time flight service omposite materials in the center f C-130 aircraft. Phase 1: ceptance tests N77-11032 of a transonic airfoil design diffusion control N77-10029 Intrastate air carrier Volume 1: summary report N77-10034 nearised supersonic wing theory on of some aircraft interference A77-12566 valuation YOH-58A helicopter e canopy N77-11039 CANTILEVER BBABS An experimental study of the nonlinear stiffness of a rotor blade undergoing flap, lag and twist deformations [NASA-CB-137969] H77-10009 CANTILE7EB BBHBBBS Application of optimality criteria to automated structural design A77-10207 CABBON FIBEB BEINFOBCED PLASTICS Theoretical and experimental investigations on landing gear spring blades out of fiber reinforced plastic for small aircraft [ESA-TT-312] S77-10162 CARBURETORS Effect of air temperature and relative humidity at various fuel-air ratios on exhaust emissions OB a per-mode basis of an Avco Lycoming 0-320 DIAD light aircraft engine. Volume 2: Individual data points [NASA-TB-X-73507] N77-10066 CABGO AIBCBAFT Application of advanced technology to future long-range aircraft [SA8E PAPEE 1126] A77-12191 CABBIEBS An analysis of the Intrastate air carrier regulatory forum. Volume 1: Summary report [AD-A023761] N77-10031 CASCADE FLOH Unsteady pressure distributions on oscillating airfoils in a supersonic cascade A77-10771 Forces on unstaggered airfoil cascades in unsteady in-phase motion [ASME PAPEB 76-FE-S] A77-10854 Lifting-surface theory of straight cascades of swept blades A77-12218 Finite element and difference methods for cascades A77-12557 CASCADE RIND TUNNELS Two-dimensional cold-air cascade study of a film-cooled turbine stator blade. 3: Effect of hole size on single-row and multlrow ejection [NAS4-TM-X-3H12] • N77-11007 CATAPULTS Fatigue investigation of the E-2B/C nose landing gear [AD-A02I4072] N77-11010 CATHODE BAI TUBES Rationale and description of a coordinated cockpit display for aircraft flight management [NASA-TM-X-3457] N77-110t4 CAOCBY INTEGRAL FORHULA Lifting surface theory for rectangular wings N77-10347 CENTBIFOGAL COBPBESSOBS Centrifugal compressor and pump stability, stall and surge; Proceedings of the Conference, New Orleans, La., March 22-25, 1976 A77-10026 The effect of rotor blade wakes on centrifugal compressor diffuser performance - A comparative experiment A77-10032 Experimental investigation of the near-surge flow in a high performance centrifugal compressor A77-10036 Strength of compressor wheels of low-ductility alloys A77-10383 CH-17 HELICOPTEB Application of Liapunov model - Tracking parameter identification for the CH-47 helicopter A77-12160 A77-11195 CUEHICAL COMPOSITION Development of aircraft brake materials [ASLE PREPRINT 76-LC-1B-3] CIVIL AVIATION Concorde navigation A77-10200 A77-1Q972 Beyond supersonic transport [IAF PAPER ISL-76-66] Co-operation in the European aircraft manufacturing industry and among the scheduled airlines /Brancker Memorial Lecture/ A77-11311 A-6 SUBJECT INDEX COHPDTEBIZED DESIGN Transport progress an practice: Air transport in Africa - East African Airways Corporation Experience A77-11312 Reliability applied to landing gear and hydraulics A77-12116 Aircraft loadability parameters - Some results of an airline survey [SAVE PAPEB 1116] A77-12201 New orientations of intergovernoental organizations of civil aviation A77-12«70 The technical basis for a national civil aviation research, technology, and development /BT 6 D/ policy; Proceedings of the Workshop Conference, Crystal city, Va., March 10-12, 1976 A77-12927 An analysis of the Intrastate air carrier regulatory forum. Volume 1: Summary report [AD-A023761] N77-10031 An analysis of the intrastate air carrier regulatory forum. Volume 2: Technical report [AD-A023762] N77-10035 Civil uses of remotely piloted aircraft [NASA-CB-13789U] N77-100K7 Civil uses of remotely piloted aircraft [NASi-CR-137895] N77-10018 Toward new heights air transportation in the Soviet Union [NASA-TT-F-172148 ] N77-11019 CLIMBING FLIGHT Best-range flight conditions for cruise-climb flight of a jet aircraft N77-10379 COCKPITS Investigation into the optimum use of advanced displays in future transport aircraft A77-1159 N77-10354 CABBAiAY, N. J. Aircraft loadability parameters - Some results of an airline survey [SAHE PAPER 1146] A77-12201 CARROLL, R. L. Application of Liapunov model - Tracking parameter identification for the CH-47 helicopter A77-12460 CABTA, F. O. Transients in turbocompressors [AD-A024275] N77-11412 B-2 PBBSOHAL AOTHOB IHDEI 0011, Ei-P. CHABBBBS, J. B. Eesults of recent NASA studies on automatic spin prevention for fighter aircraft H77-10381 CHAHPIBE, B. A. A flight investigation of piloting techniques and crosswind limitations daring visual STOL-type landing operations [BASA-TS-D-8284] H77-11001 CBAPPBLL. B. S. The rotating stator concept. Experimental performance characteristics compared with the conventional compressor [AD-A021465] H77-11411 CHAB1AT, A. F. Holographic flow visualization [NASA-CB-1U9182] N77-11365 CHATTOT, J. J. Viscous interaction with separation in transonic flow [MASA-T1-F-17187] N77-10997 CHEH, S. H. Bearing restoration by grinding [HASA-CB-149188] N77-11404 CHENEY, H. C., JB. Investigation of a bearingless helicopter rotor concept having a composite primary structure [NASA-CB-2637] N77-100U4 CHIEN, ft. T. Normal impingement of a supersonic jet on a plane: A basic study of shock-interference heating [AD-A024511] N77-10026 CHOO, L. C. Development of predictive wake vortex transport model for terminal area wake vortex avoidance [ AD-A0290U9/U] N77-11002 CLARK, B. J. Macroscopic study of time unsteady noise of an aircraft engine during static tests £ NASA-TH-X-73556] JJ77-11052 CLABK, 1. E. Helicopter yaw axis augmentation investigation [AD-A024512] N77-11066 CLAYTON, B. B. Beduction of gaseous pollutant emissions from gas turbine combustors using hydrogen-enriched jet fuel [NASA-CB-1491«6] N77-11198 COLEHJN, B. G. A computational system for aerodynamic design and analysis of supersonic aircraft. Part 2: User's manual [NASA-CR-2716] N77-11005 CONIAI, G. 5. Helicopter reliaoility growth evaluation [AD-A025265] N77-11041 C03GBOVE, O. V. Emissions of an ATCO Lycoming 0-320-DIAD air cooled light aircraft engine as a function of fuel-air ratio, timing, and air temperature and humidity [NASA-TM-X-73500] N77-10058 Effect of air temperature and relative humidity at various fuel-air ratios on exhaust emissions on a per-mode basis of an Avco Lycoming Q-320 DIAD light aircraft engine. Volume 2: Individual data points CNASA-TH-X-73507] N77-10066 CBBSS, S. T. Botor dynamic state and parameter identification from simulated forward flight transients, part 2 [NASA-CR-137964 ] N77-1000U Additional experiments with a four-bladed cyclic pitch stirring model rotor, part 2 of second yearly report [NASA-CR-137966] N77-10006 CURRY, B. E. Display/control requirements for VIOL aircraft [NASA-CB-1U5026] N77-11030 CORTISS, H. C., JB. Sensitivity of hingeless rotor blade flap-lag stanility in hover to analytical modelling assumptions [NASA-CR-137967] N77-10007 DABBBRG, J. B. Sone supersonic wind tunnel nozzle boundary layer characteristics [AD-A024980J B77-11018 DAVIBS. B. E. Design mechanical properties, fracture toughness, fatigue properties, exfoliation and stress-corrosion resistance of 7050 sheet, plate, hand forgings, die forgings and extrusions [AD-A024609] 877-10195 DEAL, P. L. A flight investigation of piloting technigues and crosswind limitations during visual STOL-type landing operations [HASA-TH-D-8284] H77-11001 DEAH, B. C., JB. Centrifugal compressor and pump stability, stall and surge; Proceedings of the Conference, New Orleans, La., March 22-25, 1976 A77-10026 DEBOBD, J. B. High-nickel alloys for gas turbines A77-11325 DEJABHBTTE, F. B. Lifting surface theory for rectangular wings N77-1031I7 DELEBY, J. Viscous interaction with separation in transonic flow [NASA-TT-F-17187] N77-10997 OEBABCHI, J. N. Design and fabrication of an 8000 PSI control-by-wire actuator for flight testing in a T-2 C airplane [AD-A02U487] N77-11065 DENNING, B. H. Future trends in aero gas turbine design. II - Unconventional engines A77-11595 DIETRICH, D. A. Simulation of flight-type engine fan noise in the NASA-Lewis 9X15 anechoic wind tunnel [NASA-TM-X-735140] N77-11050 DILLS, T. Operational mass properties data for military aircraft - Data formulation, presentation and usage [SAKE PAPER 11t7] A77-12202 DIXOB, C. J. Vortex/jet/wing viscous interaction theory and , analysis [AD-A025290] N77-11017 DOBBS, S. I. Application of optimality criteria to automated structural design A77-10207 DONE, G. T. S. Reducing vibration by structural modification A77-11279 DODGHTY, B. I. Competition for airspace - Bird strikes and aircraft operations A77-11261 D01E1L, E. H. An experimental study of the nonlinear stiffness of a rotor blade undergoing flap, lag and twist deformations [NASA-CH-137968] , 1177-10008 An experimental study of the nonlinear stiffness of a rotor blade undergoing flap, lag and twist deformations [NASA-CB-13796:)] N77-10009 DBOKONOV, A. S. Study of flow swirl influence on axiradial dlffuser effectiveness A77-12520 DDNCAN, P. S. A note on the acoustic effect of non-uniformly distributed stator rows , A77-10347 DONN, K.-P. The stocnastic control of the F-8C aircraft using the multiple model adaptive control /MHAC/ method A77-12128 B-3 DOIHB. P. C. PBBSOHAL ADTHOB IHDBI DUNNE, P. C. The finite element method applied to fluid mechanics A77-12558 E01ABDS, B. The productioo and refining of crude oil into nilitary fuels [AD-A021652] N77-11207 BICHHBB, L. J. An analysis of the intrastate air carrier regulatory forum. Volume 2: Technical report [AD-A023762] N77-10035 ELGIN, J. B. Anisotropic radiatively coupled wedge flow A77-10218 ELLIOTT, 0. G. Two-phase turbine engines A77-12680 ELI, I. L. Performance of steady and intermittent bloving ]et flaps and spanwise upper surface slots [AD-A021361] H77-10027 EHGLE, B. B. Current practice on estimating crack growth damage accumulation with specific application to structural safety durability and reliability [AD-A025199] H77-11478 ESKEB, D. I. Ground test of the D shaped vented thrust vectoring nozzle [NASA-CB-137959] N77-11107 EVANS, P. F. Numerical studies of three-dimensional breakdown in trailing vortex wakes [NASA-CR-137888] N77-10011 BVEBTZ, E. Noise generating by interaction between subsonic ]ets and blown flaps CDLR-FB-76-20] N77-10067 FALCAO, A. F. DE O. Lifting-surface theory of straight cascades of swept blades 477-12218 FAVIEB, D. Experimental study of the aerodynamics of a helicopter rotor in translational flight. Two dimensional simulation of the effects due to • cyclic variations of the velocity vector [AAAF-NT-76-20] N77-10019 FBDOBOV, I. I. Heat-pipe regenerator for gas turbine engine 477-12528 FEDOBOV, V. M. Analytic and experimental study of turbine rotor blade temperature 477-12522 FEBBI, A. Investigation of slot cooling for high-speed aircraft [AD-A021316] N77-11061 FETTEBHAM, O. E., JB. Preliminary sizing and performance evaluation of supersonic cruise aircraft [NASA-TH-X-73936J N77-11031 FEUELL, L. L. Conference on the Development of Fire-Resistant Aircraft Passenger Seats [NASA-TM-X-73111] N77-11111 FILECCIA, G. L. A systems approach to all weather landings A77-10138 FISBBEIH, B. 0. Selection of compressor pressure ratio of small GTE installed in bypass turbojet engine fan duct A77-12513 FISHEB, B. D. 4 flight investigation of piloting technigues and crosswind limitations during visual STOL-type landing operations . [NASA-TN-D-B281] N77-11001 FOLLIOT, B. G. New orientations of intergovernmental organizations of civil aviation 477-12170 FOSS, I. Ei. JR. Assessment of variable-cycle engines for Bach 2.7 supersonic transports [NASA-TB-X-73977] 877-10065 FOOLKES, B. B., OB. Terminal area guidance along curved paths: A stochastic control approach . H77-10383 FOOBHEI, B. B. Holographic flow visualization [NASA-CB-119182] B77-11365 FBICK, J. Improved computational treatment of transonic flow about swept wings H77-10318 FBTBOBG, G. C. Hot corrosion studies of four nickel-base superalloys: B-1900, HASA-TBW VIA, 713C and IH738 [NASA-TB-X-73179] B77-10183 FOCHS, i. P. A systems approach to all weather landings 477-10138 FOQOA, B. B. Beliability of automated flight service stations A77-10112 GAIGNEBET, E. New buffeting acquisition methods [AAAF-NT-76-8] B77-10051 GALLAGBEB, J. Current practice on estimating crack growth damage accumulation with specific application to structural safety durability and reliability [AD-A025199] B77-11178 GALLAGHEB, J. P. Estimating fatigue-crack lives for aircraft - Technigues A77-11177 GALLIPPI, B. J. Development of a graphite horizontal staoilizer [AD-A023767] N77-11036 GABABEDIAN, P. B. Transonic flow theory of airfoils and wings B77-10351 GAOKBOGEB, D. B. Rotor impedance measurements at model scale 477-11281 GAVIH, P. Concorde maintenance as seen by the designer - The maintenance program 477-12115 GEPBABT, L. S. A systems approach to all weather landings 477-10138 GEBA, J. Design of active controls for the NASA F-8 digital fly-by-wire airplane N77-10377 GEBHABZ, J. J. Compilation of measures to increase the fatigue strength of aircraft structures [LBF-Tfl-126/75] N77-11117 GIBSON, J. S. New developments in blown flap noise technology [NASA-CH-115086] N77-10013 V/STOL aircraft noise prediction (}et propulsors) [ AD-A028765/6] 1177-11015 GILIABD, G. B. Effects of atmospheric conditions on the operating cnaracteristics of supersonic cruise aircraft [IAF PAPER 76-112] 477-10912 GLASGOH, J. C. Eariy operation experience on the EBDA/N4SA 100 kH wind turbine [NAS4-TH-X-71601 ] N77-10610 GODFBIEO, L. B. Certification of the replacement of glass fabric per mat. spec. 5.670/1, with glass fabric per mat. spec. 5.670 in the F27 plastic sandwich wing-and-stabilizer-leading edges [FOK-R-1876] N77-11122 GOEBEL, F. L. Conceptual designs for a modular remotely piloted vehicle [4D-A023811] N77-11035 PEBSOBAL AOTBOH INDEX BOLLEY, II. E. GOGOLBV, I. G. Study of flow swirl influence on axiradial diffuser effectiveness A77-12520 GOLDEHBEBG, K. Structural tests of aerodynamic surfaces - A systems approach to analysis and design A77-12206 GOODE, H. B. Landing practices of general aviation pilots in single-engine light airplanes [NASA-TN-D-8283] N77-11033 GOODWIN, F. K. Calculation of the longitudinal aerodynamic characteristics of wing-flap configurations with externally blown flaps [NASA-CR-2705] N77-11006 GORDON, G. Civil uses of remotely piloted aircraft [NASA-CH-137894] N77-10047 Civil uses of remotely piloted aircraft [NASA-CR-137895] N77-10048 GOHODETSKII, V. B. Strength of compressor wheels of low-ductility alloys A77-10383 GOTLIEB. P. Preliminary design-lift/cruise fan research and technology airplane flight control system [NASA-CR-137971] N77-11064 GBEEBE, C. S. The stochastic control of the F-8C aircraft using the multiple model adaptive control /MMAC/ method A77-12428 GBEEBE, B. L. Comoustor design for low cost expendable turbo^ets [ AD-A024541 ] N77-10070 GREY. J. The technical basis for a national civil aviation research, technology, and development /BT £ D/ policy; Proceedings of the Workshop Conference, Crystal City, Va., Harch 10-12, 1976 A77-12927 GBIFFITH, I. C. Transients in turbocompressors [AD-A024275] N77-11412 GBOSCHE. F. B. Experiments on the feasibility of aero-acoustic measurements in the 3-m low speed wind tunnel of the DFV1E-AVA [ESA-TT-311] N77-10873 GDEST. I. C. B. Concorde navigation A77-10200 GUILLERBIHET, 1. Experimental study of the aerodynamics of a helicopter rotor in translational flight. Two dimensional simulation of the effects due to cyclic variations of the velocity vector [AAAF-NT-76-20] N77-10019 GOHEBOV, KB. S. Eguation solution accuracy in calculating ]et engine characteristics 477-12502 H HACKEIT, J. E. Numerical studies of three-dimensional breakdown in trailing vortex wakes [NASA-CB-137888] N77-10014 BAGBOP, E. Co-operation in the European aircraft manufacturing industry and among the scheduled airlines /Brancker Memorial Lecture/ A77-11311 BAIGHT, C. B. Test verification of a transonic airfoil design employing active diffusion control [AD-A024297] N77-10029 BALE, I. J. Best-range flight conditions for cruise-climb flight of a ]et aircraft N77-10379 BILL, A. i. A flight investigation of piloting techniques and crosswind limitations during visual STOL-type landing operations [HASA-TH-D-828U] 877-11001 BALL, G. F. The inviscid pressure field on the tip of a semi-infmite wing and its application to the formation of a tip vortex [HASA-CB-2718] H77-11345 BALL, H. G. Transonic flows A77-12561 BASAO, B. Bearing restoration by grinding [ NASA-CR-149183] N77-11404 ifANCOCK. G. J. Some problems of unsteady flow about aircraft A77-12560 HAUIHG, B. K. Design and fabrication of an 8000 PSI control-by-wire actuator for flight testing in a T-2 C airplane [AD-A024487 ] M77-11065 BABDIB, L. V. Transients in turbocompressors [AD-A024275] H77-11U12 HARRIS, B. F. Analog computation assessment of the risk of structural failure due to crack growth under random loading [AD-A025266] H77-11012 HABTILL, B. E. Program for establishing long-time flight service performance of composite materials in the center wing structure of C-130 aircraft. Phase 4: Ground/flight acceptance tests [NASA-Ci-145043] N77-11032 BARLEY, A. V. Development of a graphite horizontal stabilizer [AD-A023767] N77-11036 HAYS, L. G. Two-phase turbine engines 477-12680 HECKHANN, G. New buffeting acguisition methods [AAAF-NT-76-8] N77-10051 UEIDHANH, 0. F. Simulation of flight-type engine fan noise in the NASA-Lewis 9X15 anechoic wind tunnel [NASA-TH-X-73540] N77-11050 Macroscopic study of time unsteady noise of an aircraft engine during static tests [N4SA-TH-X-73556 ] N77-11052 BESSBAM, F. H. Conceptual designs for a modular remotely piloted vehicle [AD-A023844] N77-11035 HBBITT, B. L. Computational methods and problems in aeronautical fluid dynamics A77-12551 BILLHAH, B. E. Investigation into the optimum use of advanced displays in future transport aircraft 477-11594 BITCH, B. Practical requirements in industry A77-12552 HO, T.-L. Development of aircraft brake materials [ASLE PBEPBINT 76-LC-1B-3] 477-11195 HOFFBAN, B. C. Display/control requirements for VTOL aircraft [NAS4-C8-145026] B77-11030 HOHBHBHSEB, K. B. Rotor dynamic state and parameter identification, . from simulated forward flight transients, part 1 [NASA-CH-137963] B77-10003 Rotor dynamic state and parameter identification from simulated forward flight transients, part 2 [NASA-CB-137964] N77-10004 Methods studies on system identification from transient rotor tests [NASA-CB-137965] S77-10005 Additional experiments with a four-bladed cyclic pitch stirring model rotor, part 2 of second yearly report [NASA-CB-137966] N77-10006 HOLLEY, B. B. Optimal ride control for the Twin Otter, STOL aircraft 477-10336 B-5 HOLLISTEB. H. H. PEBSOHAL ADTHOB INDEI HOLLISTEB, I. B. Display/control requirements for VTOL aircraft [>)ASA-CB-145026] N77-11030 BOLflAH, F. F. Compressor blade setting angle accuracy study, volume 1 [NASA-CB-135068-VOL-1 ] N77-11046 Compressor blade setting angle accuracy study. Volume 2: Data compilation [ NASA-CH-135068-VOL-2] N77-11047 Small axial compressor technology, volume 1 [NASA-CS-134827-VOL-1 ] N77-11048 Small axial compressor technology, volume 2 [NASA-CR-134827-VOL-2] N77-11049 HONBATH, J. An analytical study for subsonic oblique wing transport concept [NASA-CR-137896] S77-10045 BORE, H. S. The influence of vortex shedding on the generation of sound by convected turbulence A77-10197 HUBEB, H. Hingeless rotor dynamics in high speed flight A77-11280 HDGHES, A. D. Beducing vibration by structural modification A77-11279 UDBN, B. V. The fuel approach to control emissions from aircraft [IAF PAPER 76-111] A77-10911 HWANG, J. D. B. S D. project cost and schedule realism - A risk analysis approach A77-12455 IAHKIH, V. I. Program system for computer calculations of jet engine characteristics A77-10349 ILLINGWOBTH, C. B. Computational methods and problems in aeronautical fluid dynamics A77-12551 INTANO, G. F. Helicopter yaw axis augmentation investigation [AD-A024512] N77-11066 ISKAKOV, K. S. Analytic and experimental study of turbine rotor blade temperature A77-12522 IZOKH, V. V. Signal-treatment methods during aircraft-engine inspection based on vibroacoustic noises A77-11603 JACOBSON, I. 0. Experimental investigation of the boundary layer on a rotating cylinder A77-10208 JOHANI, T. A systems approach to all weather landings A77-10438 JOBHSOS, i. B. Aircraft ground fire suppression and rescue systems. Characteristics of kinematic ]et fuel fires cascading and rod fuel geometries [AD-A02i)4«7] H77-11022 K KABDIL, O. A. Application of the nonlinear vortex-lattice concept to aircraft-interference problems N77-10349 KAECHHEB, A. Core noise source diagnostics on a turbofan engine using correlation and coherence techniques [HASA-Tfl-X-73535] N77-11053 KEHP, H. H. Forces on unstaggered airfoil cascades in unsteady in-phase motion [ASHE PAPER 76-FE-S ] A77-10854 KEBPKE, E. B. Emissions of an AVCO Lycoming 0-320-DIAD air cooled light aircraft engine as a function of fuel-air ratio, timing, and air temperature and humidity [NASA-TH-X-73500] N77-10058 KEHPKB, E. B. Effect of air temperature and relative humidity at various fuel-air ratios on exhaust emissions on a per-mode basis of an Avco Lycoaing 0-320 DIAD light aircraft engine. Volume 2: Individual data points [NASA-TM-X-73507] N77-10066 KHALATOV, A. A. Heat transfer in tube entrance segment with initial flow swirl and transverse injection A77-12517 KIDWELL, J. B. Compressor blade setting angle accuracy study, volume 1 [NASA-Cfl-1350b3-VOL-1 ] N77-11046 Compressor blade setting angle accuracy study. Volume 2: Data compilation [NASA-CR-135063-VOL-2] N77-11047 Small axial compressor technology, volume 1 [NASA-CR-134827-VOL-1] H77-110U8 Small axial compressor technology, volume 2 [NASA-CB-134827-VOL-2] N77-11049 KILEBO, A. B. S. Transport progress in practice: Air transport in Africa - East African Airways Corporation Experience A77-11312 KILGOBE, R. A. The cryogenic wind tunnel N77-10368 KIZEB, J. A. Program for estaolishing long-time flight service performance of composite materials in the center uing structure of C-130 aircraft. Phase 1: Ground/flight acceptance tests [NASA-CR-145043] N77-11032 KLBINBAN, D. L. Display/control requirements for VTOL aircraft [NASA-CB-145026] N77-11030 KLEVANSKII, V. H. Penetration and mixing of liquid injected into supersonic transverse gas stream A77-12515 KLOEPPEL, V. Noise generating by interaction between subsonic jets and blown flaps [DLB-FB-76-20] N77-10067 KNAGG, J. A. Estimating procedures associated with aircraft modifications [SAKE PAPER 1101] A77-12181 KOEBNEB, B. Three-component measurements on a model of a light STOI aircraft with chordwise blowing [ESA-TT-299] N77-10052 KOHL, F. J. Hot corrosion studies of four nickel-base superalloys: B-1900, NASA-THW VIA, 713C and IN738 [NASA-Tfl-X-73479] N77-10183 KONOV, V. I. Laser air-jet engine A77-11887 KOBBSBEEG, B. J. An investigation of the effect on aerodynamic forces caused by the addition of end plates to helicopter rotor blades [AD-A023541] N77-1002U KOTLIAB, L. K. Determination of magnitudes of the parameters characterizing ducted airscoop operation downstream A77-12521 KODBTIDBS, D. A. Conference on the Development of Fire-Besistant Aircraft Passenger Seats [NASA-TM-X-7311<1] N77-11111 KOTICH. G. Performance of 1.15-pressure-ratio fan stage at several rotor blade setting angles with reverse flow [NASA-TH-X-3451] U77-11008 B-6 PEBSOBAL AOTBOB IHDEI BAHGIBB, K. 1. KOZHEVHIKOV, A. V. Heat transfer in tube entrance segment with initial flow swirl and transverse injection 177-12517 EOZLOV, I. A. Strength of compressor wheels of low-ductility alloys A77-10383 KBABBENBOEHL, B. Maintaining transport aircraft A77-12069 KBAFT, E. B. An integral equation method for boundary interference in a perforated-nail Kind tnnnel at transonic speeds [AD-A023493] 1177-10023 KEEIB, I. J. Macroscopic study of tine unsteady noise of an aircraft engine during static tests [NASA-TH-X-73556] H77-11052 KBUTOVA. H. B. Thermal analysis of flight vehicle compartment structure A77-12509 EOLIICKI, P. V. Influence of aircraft angle of attack on high G cockpit design [AD-A025083] H77-110..3 KDHCHAL, K. The production and refining of crude oil into military fuels [AD-A024652] N77-11207 KDBOSAKA, H. Unsteady pressure distributions on oscillating airfoils in a supersonic cascade A77-10771 KVITKA, A. L. Calculation of gas-turbine engine blades by the finite element method A77-12583 LACBOIS, A. H. Fracture toughness of 8mm 2024-T3 non clad plate with long central cracks [FOK-B-1879] N77-11U49 LANDiEBEB, L. Flow interaction near the tail of a body of revolution. I - Flow exterior to boundary layer and wake [ASHE PAPEB 76-FE-M] A77-10855 Flow interaction near the tail of a body of revolution. II - Iterative solution for flow within and exterior to boundary layer and wajce [ASHE PAPER 76-FE-N] A77-10856 LSHGEBEUX, P. 'C.221, the new French target drone A77-11625 LARUELLE, G. Study of the suosonic flow around a sharp leading edge CAAAF-NT-76-14 ] N77-10017 LAUGHBIDGE, F. I. Aircraft ground fire suppression and rescue systems. Characteristics of kinematic ]et ±uel fires cascading and rod fuel geometries [ 4D-A024447] N77-11022 LEAKE, B. J. Computational alternatives to obtain tine optimal ]et engine control [ilASA-CB-149106] H77-100oO Simplified simulation models for control studies of turbojet engines [NASA-CB-149107] N77-10061 1EAVY. G. C. Weight and balance considerations in the design of the A-10A close air support aircraft [SAKE PAPEB 1101] A77-12183 LEBALLEUE, J. C. Viscous interaction with separation in transonic flow [NASA-TT-F-17187 ] N77-10997 LEBODC, P. Concorde - Endurance flights results A77-12114 LBE, I. B. The stochastic control of the F-8C aircraft using the unltiple model ada£"iive control /BHAC/ nethod A77-12128 LEHBAH, G. B. Development of a graphite horizontal stabilizer [AD-A023767] S77-11036 LEDTIB, E. G. Pressure distributions over frontal /nose/ surfaces of bodies of revolution in transonic flow at angles of attack of 0 to 10 deg A77-10664 LBVABT, F. Study of the subsonic flow around a sharp leading edge [AAAF-HT-76-14] B77-10017 LBBIS. G. E. Preliminary design-lift/cruise fan research and technology airplane flight control system [NASA-CB-137971] H77-11064 LIHDBSBADB, B. VTOL BPVs - A technology assessment A77-12000 LIBSCOTT. B. S. Early operation experience on the EBDA/NA5A 100 kH wind turbine [MASA-TH-X-71601] H77-10640 LITTLE, L. J. Preliminary design-lift/cruise fan research and technology airplane flight control system [HASA-CB-137971] 1177-11064 LOCK, B. C. Computational methods and problems in aeronautical fluid dynamics A77-12551 Methods for elliptic problems in external aerodynamics A77-12554 LOKAI, H. V. Heat-pipe regenerator for gas turbine engine A77-12528 LOSBB, J. E. Interface between maintainability and commercial aircraft spares support A77-10483 LOHAK, B. Application of design data derived from fatigue tests with service-like load sequences for life prediction [LBF-FB-109/76] 1177-11445 LDCKBIHG, J. Bi An application of the suction analog for the analysis of asymmetric flow situations 1177-10350 LONDBI, J. L. A computational system for aerodynamic design and analysis of supersonic aircraft. Part 2: User*s manual [NASA-CB-2716] 1177-11005 LYSTAD, H. D. Catapult launch fatigue investigation of the model S-2 E airplane [ AD-A024071 ] ' 1177-11038 Fatigue investigation of the E-2B/C nose landing gear [AD-A024072] N77-11040 M MAGLIOZZI, B. V/STOL rotary propulsion systems: Noise prediction and reduction. Volume 1: Identification ot sources, noise generating mechanisms, noise reduction mechanisms, and prediction oethodology [AD-A027389/6] N77-10053 V/STOL rotary propulsion systems: Noise preaiction and reduction. Volume 2: Graphical prediction netflods [ AD-A027390/4] N77-1005U V/STOL rotary propulsion systems: Noise prediction and reduction. Volume 3: Computer program users oanual OD-A027363/1 ] N77-10055 HANGLBB, K. H* Computational met nods and prooletas in aeronautical fluid dynanics A77-12551 B-7 BABESCA, C. PEESOSiL 10THOB IBDEX Free vortei sheets A77-12559 HAEESC4, C. Experimental study of the aerodynamics of a helicopter rotor in translational flight. Two dimensional simulation of the effects due to cyclic variations of the velocity vector [AAAF-NT-76-20] N77-10019 HARGASOH, B. J. Effects of ]ets, wakes, and vortices on lifting surfaces [N&SA-TH-X-7397U] N77-10998 BABSH, O. P. The next-generation subsonic transport [SAKE PAPER 1127] A77-12195 BABSH, H. Subsonic flows in turbomachines A77-12556 HAIO, a. B. Landing practices of general aviation pilots in single-engine light airplanes [NASA-TN-D-8283] N77-11033 HCCABTHI, J. F., JB. Analog computation assessment of the risk of structural failure due to crack growth under random loading [AD-A025266] N77-11012 BCCOBBICK, B. B. On the status of V/S1OL flight N77-10367 BCDOHALD, B. The inviscid pressure field on the tip of a semi-infinite wing and its application to the formation of a tip vortex [NASA-CB-27U8] N77-11315 BCDONHELL, J. H. Computational methods and problems in aeronautical fluid dynamics A77-12551 BCGEHEE, B. L. A test facility for aircraft ]et noise reduction. II A77-118H4 BCKEE, B. G. Aircraft ground fire suppression and rescue systems. Characteristics of kinematic jet fuel fires cascading and rod fuel geometries [AD-A024447] N77-11022 BBITZLEB, T. D. ICC analysis of flight recorder for F-"4 Wild weasel aircraft [AD-A023830] N77-10512 BENDEL, J. H. On the identification of state-derivative-coupled systems A77-12UU8 BBNDEHHAL1, H. B. Calculation of the longitudinal aerodynamic characteristics of wing-flap configurations with externally blown flaps [NASA-CR-2705] S77-11006 BEHG, P. B. Emissions of an AVCO Lycoming 0-320-DIAD air cooled light aircraft engine as a function of fuel-air ratio, timing, and air temperature and humidity [NASA-TM-X-73500] N77-10058 Effect of air temperature and relative humidity at various fuel-air ratios on exhaust emissions on a per-mode basis of an Avco Lycoming 0-320 DIAD light aircraft engine. Volume 2: Individual data points [NASA-TH-X-73507 ] N77-10066 BBRBILL. G. L. §tudy ot small turbofan engines applicable to single-engine light airplanes [NASA-CR-1379t«] N77-11054 HIDDLETOH, H. D. A computational system for aerodynamic design and analysis of supersonic aircraft. Part 2: User's manual [NASA-CR-2716] N77-11005 BIKDLOVICH, V. I. Signal-treatment methods during aircraft-engine inspection based on vibroacoustic noises 477-11603 BILES, J. B. Effects of forward velocity on noise for a J85 turbojet engine with multitube suppressor from wind tunnel and flight tests [NASA-TB-X-73542] N77-11051 BILLAR, D. A. J. The rotating stator concept. Experimental performance characteristics compared with the conventional compressor [AD-A02UU65] H77-11411 BILLER, Bl B. Full temperature range protective system for fastener areas of carrier-based naval aircraft [AD-A024523] H77-10210 BILLEB, S. C. Future trends in aero gas turbine design. II - Unconventional engines A77-11595 BIRSKII, V. B. Flow of a radiating gas over a blunt body with intense vaporization A77-10t16 BITB4, B, Approximate transonic profile flow with shock 477-10251 HITTELBACH, F. G. The helicopter air service passenger program: A retrospect [PB-25t830/3] N77-10036 BOFFITT, T. P. Two-dimensional cold-air cascade study of a film-cooled turbine stator blade. 3: Effect of hole size on single-row and multirow ejection [NASA-TH-X-31U2] H77-11007 HOOK, D. T. Application of the nonlinear vortex-lattice concept to aircraft-interference problems B77-103t9 BOOBE, fi, 0. Performance of 1.15-pressure-ratio fan stage at several rotor Dlade setting angles with reverse flow [NASA-TH-X-3151] N77-11008 BOOZ, I. E. A second look at relationships for estimating peacetime aircraft attrition [4D-A023681] N77-11023 BORGAH, L. A. Finite element and difference methods for cascades 477-12557 BOBINO, L. Performance analysis of flexible aircraft with active control N77-10378 BOBBIS, S. J. Assessment of vanaule-cycle engines for Bach 2.7 supersonic transports [NASA-TS-X-73977 ] N77-10065 BOSTON, J. B. Experimental investigation of the boundary layer on a rotating cylinder A77-10208 BOSIH, A. V. Experimental study of combustion time in two-stage combustion process A77-12511 BOSIN, I. I. Heat-pipe regenerator for gas turbine engine 477-12528 BOKUEBJEE, D. K. Pressure loss coefficient of impingement cooled leading edge system of a turbine blade A77-10772 Film cooling with injection through slots 477-10773 N NAKAYAHA, A. Flow interaction near the tail of a body of revolution. I - Flow exterior to boundary layer and wake [ASME PAPER 76-FE-M] A77-10855 Flow interaction near the tail of a nody of revolution. II - Iterative solution for flow within and exterior to boundary layer and wake [ASME PAPEB 76-FE-N] A77-10856 PERSONAL 40IBOB INDEX PIEBS, II. J. NANGIA, B. K. Applications of linearised supersonic wing theory to the calculation of some aircraft interference flows A77-12566 NABAIAHASHAHI, B. Resizing procedure for structures under combined mechanical and thermal loading A77-1021U HABBAHOBE, J. C. The development of a computer aided airfoil design procedure including preliminary wind tunnel experiments on a Ion Reynolds number high lift section, volume 1 [AD-A024361 ] N77-10028 NAYFEH, A. B. Application of the nonlinear vortex-lattice concept to aircraft-interference problems N77-10349 BELSOH, B. B. Application of optimality criteria to automated structural design A77-10207 NEHCBENKO, L. I. Strength of compressor wheels of low-ductility alloys A77-10383 HESTEB07, E. D. Determination of magnitudes of the parameters characterizing ducted airscoop operation downstream A77-12521 NEUBEBTB, G. Noise generating by interaction between subsonic •jets and blown flaps [DLR-FB-76-20] N77-10067 NGUYEN, L. 1. Results of recent NASA studies on automatic spin prevention for fighter aircraft N77-10381 NIELSEN, G. I. T. An improved projectile boattail, part 2 [AD-A021073] N77-11016 NIELSEN, J. H. Calculation of the longitudinal aerodynamic characteristics of wing-flap configurations with externally blown flaps [NASA-CR-2705] N77-11006 NIXON, D. An extended integral equation method for the steady transonic flow past a two-dimensional aerofoil A77-12562 NOLL, B. B. Performance analysis of flexible aircraft with active control N77-10378 NOBDHACK, G. B. Design mechanical properties, fracture toughness, fatigue properties, exfoliation and stress-corrosion resistance of 7050 sheet, plate, hand forgings, die forgings and extrusions [AD-A02M609] N77-10195 NOVAK, B. C. Investigation of a bearingless helicopter rotor concept having a composite primary structure [NASA-CR-2637] N77-10011 NTS, B. B. Responsibilities and assurances with regard to cargo transport - Air transport law 477-12172 OBBIAN, I. C. Landing practices of general aviation pilots in single-engine light airplanes [NASA-TN-D-8283] 1177-11033 OCABROLL, H. J. Finite element and difference methods for cascades 477-12557 OBASBI. B. Forces on unstaggered airfoil cascades in unsteady in-phase motion [ASHE PAPEB 76-FE-S] 477-10851 OBL4HDEB, B. D. The development of a computer aided airfoil design procedure including preliminary wind tunnel experiments on a low Reynolds number high lift section, volume 1 [AD-A02M361 ] N77-10028 OBBINGEB, 0. Analog computation assessment of the risk of structural failure due to crack growth under random loading [ A D - A 0 2 5 2 6 6 ] 877-11012 OTTENS, H. B. Calculation of vibration modes and resonance frequencies of the Nor throp BF-5 [NLR-TB-75050-U ] N77-11«50 PAHTELBEV, A. A. Analytic and experimental study of turbine rotor blade temperature A77-12522 PARKER, J. A. Conference on the Development of Fire-Besistant Aircraft Passenger Seats [NASA-TH-X-7311"] N77-11111 PABKBR. B. J. Bearing restoration oy grinding [NASA-CH-1149188] H77-11101 PATBL, V. C. Flow interaction near the tail of a body of revolution. I - Flow exterior to boundary layer and wake [ASME PAPEB 76-FE-M] A77-10855 Flow interaction near the tail of a body of revolution. II - Iterative solution for flow within and exterior to boundary layer and wake [ASME PAPER 76-FE-N] A77-10856 PATTERSON, J. C.. JB. Hingtip vortex dissipator for aircraft [NASA-CASE-LAH-11645-1 ] N77-10001 PATTON, J. H., JB. A flignt investigation of piloting technigues and crosswind limitations during visual STOL-type landing operations [NASA-TN-D-828U] N77-11001 PEAKS, D. J. Controlled and uncontrolled flow separation in three dimensions [LR-591] N77-10999 PELAGATTI, C. Critical analysis of comparisons between flight test results and wind tunnel test predictions in subsonic and supersonic transport aircraft [NASA-TT-F-17185] N77-10049 PENBEI, T. B. The AFFDL-Nielsen flow-field study [AD-A023755] N77-11015 PEBEZ GBIFFO, A. Investigation and analysis of the human factors in aircraft accidents A77-10500 PEBKIHS, J. N. Transients in turbocompressors [AD-A024275] N77-11112 PEBBIEB, P. Buffeting problems [AAAF-NT-76-7] H77-10050 PETEBSON, H. B. Development of aircraft brake materials [ASLE PBEPBINT 76-LC-1B-3] A77-11195 PBfBAZBITSKII, G_ B. Thermal analysis of flight vehicle compartment structure A77-12509 PBTOKB07. 4. B. Dispersion of fatigue test data for cast gas-turbine blades in association with structural and technological factors A77-12579 PIEBS, H. J. Calculation of the flow around a swept wing, taking into account the effect of the three-dimensional boundary layer. Part 1: King with turbulent boundary layer [NLB-TB-75076-0] N77-11011 B-9 PILOH, J. C. PEESONAL AOTHOB INDEX PI10N, J. C. Critical analysis of comparisons between flight test results and wind tunnel test predictions in subsonic and supersonic transport aircraft f NASA-TT-F-17185 ] B77-100"49 PISABENKO, G. S. Strength of glass-fibre-reinforced plastics at one-sided beating [IAF PAPER 76-200] A77-10939 PLATOU. A. S. An improved projectile boattall, part 2 [AD-A021)073] N77-11015 PLATZEH, H. F. Prediction Methods for Jet V/S10L Propulsion Aerodynamics, volume 1 [AD-4024022] N77-10068 Prediction Methods for Jet V/STOL Propulsion Aerodynamics, volume 2 [AD-A02U023] N77-10069 POOL, A. The establishment of safe separations between aircraft in rlight [BLfl-aP-75041-U] , N77-11020 POEIEB, J. H. The AFFDL-Nielsen flow-field study [AD-A023755] 877-11015 POTTER, J. H. Current practice on estimating cracK growth damage accumulation with specific application to structural safety duraoility and reliability [ AD-A025499] 877-11178 PEASAD, 0. H. Optimal control for the rolling pullout maneuver of a modern fighter aircraft A77-12it44 The pursuit-evasion problem of two aircraft in a horizontal plane A77-12152 PEOKHOKOV, A. H. Laser air-jet engine A77-11887 PHUST, H. W. , JR. Two-dimensional cold-air cascade study of a film-cooled turbine stator blade. 3: Effect of hole size on single-row and multirow ejection [NASA-TH-X-3442] N77-11007 PUBSHOUSE, H. Applications of linearised supersonic wing theory to the calculation of some aircraft interference flows A77-12566 PILAEV, A. H. Thermal analysis of flight vehicle compartment structure A77-12509 Q QUABA8TA, J. E. Terminal area guidance along curved paths: A stochastic control approach N77-10383 QUICK, A. V. Noise generating by interaction between subsonic jets and blown flaps [DLE-FB-76-20] N77-10067 BAJAB, B. The pursuit-evasion problem of two aircraft in a horizontal plane A77-12152 BAKOISKI, I. J. Dynamic-stress-data management for aeromechanical testing of turbomachinery A77-12175 BEBOBT, J. Experimental study of the aerodynamics of a helicopter rotor in translational flight. Two dimensional simulation of the effects due to cyclic variations of the velocity vector [ AAAF-NI-76-20] N77-10019 BECK, G. B. Advanced combustion techniques for controlling NO sub x emissions of high altitude cruise aircraft [NASA-TH-X-73473] N77-10062 EBDDT, N. N. V/STOL aircraft noise prediction (jet propulsors) [AD-A028765/6] 877-1101)5 BBSHOTKO, H. Core noise source diagnostics on a turbofan engine using correlation and coherence techniques [NASA-Td-X-73535] 877-11053 BBOTEH, B. P. Eigenvalue/eigenvector control via spectral cnaracterization - An application to helicopter hover dynamics A77-10338 BICE, E. J. Inlet noise suppressor design method based upon tne distribution of acoustic power with mode cutoff ratio N77-10311 BICUABDS, C. Computational methods and proolems in aeronautical fluid dynamics A77-12551 BILOFF, N., JB. Experimental clean combustor program: Noise study [NASA-CB-13510b] N77-1C064 BOBESTS, A. Relaxation near a sonic line A77-12563 BOSENFIELD, S. B. Beyond supersonic transport [IAF PAPEB ISL-76-66] A77-10972 BOSSES, B. H. Conference on the Development of Fire-Besistant Aircraft Passenger Seats [NASA-TM-X-7314U] N77-11111 BDDEY, B. A. Advanced combustion techniques for controlling NO sub x emissions of high altitude cruise aircraft [8ASA-TM-X-73473] N77-10062 The impact of emissions standards on the design of aircraft gas turbine engine combustors [NASA-TM-X-73U90] 877-10063 BDSSELL, J. H. Assessment of variable-cycle engines for Mach 2.7 supersonic transports [BASA-TM-X-73977] 877-10065 SANDELL, H. B., JB. The stochastic control of the F-8C aircraft using the multiple model adaptive control /MMAC/ method A77-12428 Linear regulator design for stochastic systems by a multiple time scales method [NASA-CR-119099] 877-10432 SAHTBAH, D. H. Transonic performance of Mach 2.65 auxiliary flow axisymmetric inlet [8ASA-CB-27U7] 877-10056 SABGENT, N. B. Effects of forward velocity on noise for a J85 turbojet engine with multitube suppressor from wind tunnel and flight tests [BASA-TM-X-735U2] 877-11051 SABHA, I. G. Optimal control for the rolling pullout maneuver of a modern figater aircraft A77-1244II SATYABABAYABA, G. Optimal control for the rolling pullout maneuver of a modern fighter aircraft A77-124U4 SAONDEBS, S. Experimental investigation of the boundary layer on a rotating cylinder A77-10208 SCBIPHOLT, G. J. Calculation of the flow around a swept wing, taking into account the effect of the three-dimensional boundary layer. Part 1: Ming with turbulent boundary layer [NLH-TB-75076-0] 877-11011 SCBLIBKELHAHN, B. J. Research on adhesive bonding and surface characteristics of metals at Fokker-VFW [FOK-B-1816] 877-11105 B-10 PBBSOBAL AOTHOB IBDEI STUIOV. ?. P. SCHHIDT, A. B. A method for estimating the veigbt of aircraft transmissions [SAWE PAPEB 1120] A77-12191 SCBBADEB, O. E. Application of advanced technology to future long-range aircraft [SA»E PAPEB 1126] A77-1219U SCBOETZ, 0. Application of design data derived from fatigue tests with service-like load seguences for life prediction [LBF-FB-109/76] H77-111115 Compilation of measures to increase the fatigue strength of aircraft structures [LBF-TB-126/75] N77-11117 SCBUBfZB, B. Theoretical and experimental investigations on landing gear spring blades out of fiber reinforced plastic for small aircraft [ESA-TT-312] H77-10162 SCBfAHTZ, P. Advanced design composite aircraft, the next step for composites [SAWE PAPES 1105] A77-1218U SCBIEIKHABD, B. G. Effects of atmospheric conditions on the operating characteristics of supersonic cruise aircraft [IAF PAPEB 76-112] A77-10912 SCOTT, G. R. Civil uses of remotely piloted aircraft [BASA-CB-1378911] B77-100U7 Civil uses of remotely piloted aircraft [NASA-CB-137895] 1)77-1001(8 SCBOGGS, B. B. Vortex/jet/wing viscous interaction theory and analysis [AD-A025290] 1(77-11017 SEELIGEB, G. G. Full temperature range protective system for fastener areas of carrier-based naval aircraft [AD-A024523] N77-10210 SEGALL. I. The stochastic control of the F-8C aircraft using the multiple model adaptive control /BMAC/ method A77-12428 SBHGEISSEH, C. Military rocket aircraft: Inherent constraints and their uses N77-11186 SHAIKBOTDIBOV, Z. G. Penetration and mixing of liquid injected into supersonic transverse gas stream A77-12515 SH&MBOTH, S. J. The inviscid pressure field on the tip of a semi-infmite wing and its application to the formation of a tip vortex [NASA-CF-2748] H77-11315 SBATAYEV. V. G. Calculation of multi-contour thin-nailed structures by the method of sections [NASA-T1-F-17281] N77-11029 SBCHOKIH, V. A. Experimental study of combustion time in two-stage combustion process A77-12511 SaCHOKIB, V. K. Heat transfer in tube entrance segment with initial flow swirl and transverse injection A77-12517 Heat-pipe regenerator for gas turbine engine A77-12528 SHELIKHOV, S. G. Magnetic particle inspection of aviation engine vanes A77-11606 SULIK, L. B. Strength of compressor wheels of low-ductility alloys A77-10383 SHBIDEB, K. B. Development of predictive wake vortex transport model for terminal area wake vortex avoidance [AD-A029049/4] N77-11002 SBOHPBBT, P. An analytical study for subsonic obligue wing transport concept [NASA-CP-137896] N77-100U5 SIBAf, B. S. _• An analysis of the intrastate air carrier regulatory forua. Volume 2: Technical report [AD-A023762] H77-10035 SIBOHS, I. i. Advanced control systems for helicopters A77-11278 SIVAEV, V. B. Study of flow swirl influence on axiradial diffuser effectiveness A77-12520 SKIHHBB, 6. L. Army preliminary evaluation TOB-58A helicopter with a flat-plate canopy [AD-A021501] B77-11039 SKOBOBATCKII, B. Emissions of an AVCO Lycoming 0-320-DIAD air cooled light aircraft engine as a function of fuel-air ratio, timing, and air temperature and humidity CHASA-TH-X-73500] K77-10058 Effect of air temperature and relative humidity at various fuel-air ratios on exhaust emissions on a pec-mode basis of an Avco Lycoming 0-320 DIAD light aircraft engine. Volume 2: Individual data points [NASA-TH-X-73507] H77-10066 SHITH, K. O. Conceptual designs for a modular remotely piloted vehicle [AD-A02384II] M77-11035 SOFBIH, T. G. Experimental clean combustor program: Noise study [NASA-CB-135106] B77-10064 SOVBAHO, B. Experimental investigation of the near-surge flow in a high performance centrifugal compressor A77-10036 SPABGLEB, J. G. Test verification of a transonic airfoil design employing active diffusion control [AD-A024297] B77-10029 SPABGLEB, S. B. Calculation of the longitudinal aerodynamic characteristics of wing-flap configurations with externally blown flaps [NASA-CB-2705] B77-11006 SBIBATHKOHAB, S. Eigenvalue/eigenvector control via spectral characterization - An application to helicopter hover dynamics A77-10338 S1BABHAB, B. O. The development of a computer aided airfoil design procedure including preliminary wind tunnel experiments on a low Reynolds number high lift section, volume 1 [AD-A024361] N77-10028 The design, analysis and testing of a low budget wind tunnel flutter model with active aerodynamic controls, volume 2 IAD-A024480] N77-10090 SIBABBS, C. A. Hot corrosion studies of four nickel-base superalloys: B-1900, BASA-TBil VIA, 713C and IB738 CNASA-TM-X-73479] N77-10183 STEHiHEIL, E. Mechanism of material fatigue during the crack initiation stage [ICAF-DOC-895] B77-11441 STOBE, J. B. Effects of forward velocity on noise for a J85 turbojet engine with multitube suppressor from wind tunnel and flight tests [NASA-TM-X-73542] B77-11051 STBEHLOB. a. Hingeless rotor dynamics in nign speed flight A77-11280 STBIKB, I. T. The AFFDL-Bielsen flow-field study [AD-A023755] B77-1101S S1BOGOBOV, 0. V. Experimental study of combustion time in two-stage combustion process A77-12511 STOLOV, V. P. Flow of a radiating gas over a blunt body with intense vaporization A77-10U16 B-11 STOBGEOH, B. t. PBBSOHAL tDTBOB IHDBX STOBGEOH, B. F. Design considerations for laminar flow control aircraft N77-10366 SDLLIVAH, T. E. Measurement of wake vortex strength by means of acoustic back scattering A77-11712 SUNSHINE. B. A. An analysis of the intrastate air carrier regulatory forum. Volume 2: Technical report [AD-A023762] N77-10035 SflDEBSKI, A. A. The rotating stator concept. Experimental performance characteristics compared with the conventional compressor [AD-A024465] N77-11411 SHIFT, G. An analytical study for subsonic obligue wing transport concept [NASA-CB-137896] N77-10045 SHITZEB, 0. The production and refining of crude oil into military fuels [AD-A024652] N77-11207 TAI, T. C. Analysis and design of ejector diffuser for optimum thrust [AD-A025491 ] N77-11356 TALANIOV, A. V. Experimental study of combustion time in two-stage combustion process A77-12511 TALBOT, J. E. Effects of atmospheric conditions on the operating characteristics of supersonic cruise aircraft [IAF PAPEE 76-112] A77-10912 TENEKETZIS, D. Linear regulator design for stochastic systems by a multiple time scales method [NASA-CB-1U9099] N77-10432 TENSI, J. Buffeting problems [AAAF-NT-76-7] N77-10050 THOHPSOH, J. F. Numerical solutions for laminar and turbulent viscous flow over single and multi-element airfoils using body-fitted coordinate systems N77-10355 THBESHEB, B. B. Design consideration for the Darrieus rotor A77-12872 TIBBETS, J. G. V/STOL aircraft noise prediction (jet propulsors) [AD-A028765/6] N77-11045 TINSLEY, H. G. A systems approach to all weather landings A77-10438 TITABENKO, V. V. Nonlinear analysis of flows generated by the impulsive motion of a wedge A77-12630 TODA, B. Simulation of an automatically-controlled STOL aircraft in a microwave landing system multipath environment [NASA-TM-X-73154] N77-11063 TOENSHOFF, D. A. High temperature thermocouple system for advanced aircraft turbine engines [AD-A025500] N77-11062 TOBLIN. K. B. An analytical study for suosonic obligue wing transport concept [NASA-CE-137896] N77-10045 TOBBES, B. A wing on the SA.341 Gazelle helicopter and its effects A77-11282 TBABB, P. C. Centrifugal compressor and pump staoility, stall and surge; Proceedings of the Conference, New Orleans, La., March 22-25, 1976 A77-10026 TBAYBAB, J, J. An experimental study of the nonlinear stiffness of a rotor blade undergoing flap, lag and twist deformations [NASA-CB-137968] H77-10008 An experimental study of the nonlinear stiffness of a rotor blade undergoing flap, lag and twist deformations [NASA-CH-137969] S77-10009 TBBTIACHENKO, G. B. * Strength of glass-fibre-reinforced plastics at one-sided heating [IAF PAPEB 76-200] A77-10939 TBDHEVA, E. A. Hechanism of stabilization of the 'separation point1 of a vortex during flow of a stream at low subsonic velocity over a delta wing [SASA-TT-F-17283] H77-10012 TBDSHIN, T. A. Analytic and experimental study of turbine rotor blade temperature A77-12522 VANOENBEBG, B. Calculation of the flow around a swept wing, taking into account the effect of the three-dimensional boundary layer. Part 1: Sing with turbulent boundary layer [NLB-TB-75076-U] N77-11011 VANDYKE, P. High speed computer studies of vortex motions in relation to aircraft wake turbulence [AD-A024290] N77-11013 VANPAPPEIEBDAB, C. A. Development of a graphite horizontal stabilizer [AD-A023767] N77-11036 VEB, I. L. Acoustical evaluation of the NASA Langley V/STOL wind tunnel [NASA-CB-145087] N77-11068 VETIUTSKAIA, L. B. Off-design regimes of asymmetric nozzles with supersonic inlet velocity A77-12504 VOLODENKO, B. V. Dispersion of fatigue test data for cast gas-turbine blades in association with structural and technological factors A77-12579 VOEOSHKO, P. P. Calculation of gas-turbine engine blades by the finite element method A77-12583 w iALKDEM, F. Computational methods and problems in aeronautical fluid dynamics A77-12551 Supersonic flows A77-12565 IALSB, J. D. Design mechanical properties, fracture toughness, fatigue properties, exfoliation and stress-corrosion resistance of 7050 sheet, plate, hand forgings, die forgings and extrusions [AD-A024609] N77-10195 BABE, T. C. Small axial compressor technology, volume 1 [NASA-CB-134827-VOL-1] N77-11048 Small axial compressor technology, volume 2 [NASA-CB-134827-VOL-2] N77-11049 IABNOCK, 1. An analytical study for subsonic obligue wing transport concept [NASA-CB-137896] N77-10045 IABSI, Z. D. A. Numerical solutions for laminar and turbulent viscous flow over single and multi-element airfoils using body-fitted coordinate systems N77-10355 BE1LIVEB. A. D. Supersonic variable-cycle engines [BASA-TH-X-73524] N77-10059 B-12 PEBSOHAL ADIBOB IHDEI ZISK, B. D. WHITCOHB, B. T. Advanced transonic aerodynamic technology H77-10365 SILK, 1. S. BeasQreoent of wake vortex strength by means of acoustic back scattering A77-11712 1ILLIABS, B. B. Application of circulation control rotor technology to a stopped rotor aircraft design A77-11277 UILLIS, 0. L. System considerations for reliable strain data from gas turbine engines A77-12176 UILLIS, E. A. Supersonic variable-cycle engines [NASA-TH-X-73520 ] N77-10059 1ILLSKI, A. S. The stochastic control of the F-8C aircraft using the multiple model adaptive control /MH4C/ method A77-12428 RILSOH, J. 1. Investigation into the optimum use of advanced displays in future transport aircraft A77-1159" ilLSON, B. I. Design consideration for the Darrieus rotor A77-12872 IILISHIBE, L. L. Aircraft ground fire suppression and rescue systems. Characteristics of kinematic ]et fuel fires cascading and rod fuel geometries [AD-A02UUU7] N77-11022 BITCOFSKI, B. D. Hydrogen-fueled subsonic aircraft: A perspective N77-10341 iOEBHEB, B. Reliability applied to landing gear and hydraulics A77-12116 •ODD, H. A. Current practice on estimating crack growth damage accumulation with specific application to structural safety durability and reliability [AD-A025499] 1177-11478 BRIGHT, G. B. Future trends in aero gas turbine design. II - Unconventional engines A77-11595 ZBLDOVICB, B. L. Determination of aagnitudes of the parameters characterizing ducted airscoop operation downstream A77-12S21 ZODOV, V. H. Off-design regimes of asymmetric nozzles with supersonic inlet velocity A77-1250D ZTSK, E. 0. High temperature thermocouple system for advanced aircraft turbine engines [AD-4025500] N77-11062 YEHHI, K. B. Landing practices of general aviation pilots in single-engine light airplanes [NASA-TN-D-8283] N77-11033 IEOKAHS, T. The helicopter air service passenger program: A retrospect [PB-254830/3] N77-10036 YIN, S. K. Rotor dynamic state and parameter identification, from simulated forward flight transients, part 1 [NASA-CB-137963] N77-10003 Methods studies on system identification from transient rotor tests [NASA-CB-137965] H77-10005 YOOHG. L. B. Display/control reguirements for VIOL aircraft [NASA-CB-1U5026] N77-11030 ZALAY. A. 0. Development of predictive wake vortex transport model for terminal area wake vortex avoidance [AD-A0290U9/U] N77-11002 ZABEISKT, E. V. Bearing restoration by grinding [NASA-CB-149188] N77-11«0« ZASLOTSKAIi, 1. A. Calculation of gas-turbine engine blades by the finite element method A77-12583 ZATOLOKA, V. T. Off-design regimes of asymmetric nozzles with supersonic inlet velocity A77-1250IJ B-13 CONTRACT NUMBER INDEX AERONAUTICAL ENGINEERING / A Special Bibliography (Suppl 80) FEBRUARY 1977 Typical Contract Number Index Listing HAS2-9177 H77-11064 CONTRACT NUMBER Listings in this index are arranged alphanumencally by contract number Under each contract number the accession numbers denoting documents that have been produced as a result of research done under that contract are arranged in ascending order with the IAA accession numbers appearing first The accession number denotes the number by which the citation is identified m either the lAAoi STARsecvon AF PHOJ. 1367 N77-11478 &P PSOJ. 1476 N77-10027 AF PHOJ. 1929 N77-11042 AF PEOJ. 1989 N77-11035 AF PBOJ. 3066 N77-11062 AF PBOJ. 6813 N77-11061 AF PBOJ. 7181 N77-11043 AF PBOJ. 8219 N77-11015 AF PBOJ. 9781 N77-11013 N77-11061 H77-11412 iF PROJ. 9782 N77-10028 1177-10090 AF-AFOSB-72-2273 A77-12428 AF-AFOSB-74-2460A A77-10207 AP-AFOSB-1998-71 N77-10028 H77-10090 AF-AFOSH-2167-72 N77-11061 AP-AFOSB-2802-75 N77-11412 AF-AFOSK-2922-76 1177-10355 ABO PBOJ. P32A-33A 1177-11037 ABO PBOJ. P41T-78A (177-11037 ABO PBOJ. V 4 1 A - B 4 A H77-11015 AT(04-3) -1075 A77-12872 Al(11-1)-3077 N77-10351 DA PEOJ. 1F1-61102-AH-45 H77-10044 K77-10556 DA PBOJ. 1F1-63204-DB-38 N77-11041 DA PEOJ. 111-61102-A-33D N77-11016 DA PBOJ. 1T1-61102-A-33H H77-11018 DAAD05-72-C-0131 A77-10208 DAAG29-76-G-0045 N77-103D7 DAAJ02-73-C-0097 H77-11041 DOT-FA72BA-2837 H77-11024 DOT-FA72HA-3099 H77-11045 DOT-FA74WA-3477 N77-10053 N77-10051 H77-10055 DOT-OS-60078 H77-10035 DOT-OST-60078 N77-1003U DOT-TSC-988 N77-11002 E (01-3)-1207 A77-12680 E (01-3)-1228 A77-12680 E(01-3)-12S5 A77-12680 E(19-18)-2087 N77-10432 FEA-C-04-50088-00 N77-10690 F30602-73-C-0065 A77-10442 F33b15-73-C-3056 S77-10027 F33615-74-C-2069 N77-11062 F33615-74-C-3046 N77-11042 F33615-75-C-3036 N77-11035 P33615-75-C-3124 A77-12184 F44620-71-C-0080 N77-11013 P44620-73-C-0011 N77-11023 F44620-75-C-0040 A77-10218 NASB-2790 N77-10049 NASH-2792 N77-10012 N77-10997 [177-11019 N77-11029 NAS1-9559 N77-11068 N4S1-10960 N77-10044 N77-10556 NAS1-11100 H77-11032 NAS1-12794 N77-11345 NAS1-13158 N77-11006 NAS1-13371 N77-10378 NAS1-13653 H77-11030 HAS1-13694 N77-10366 SAS1-13732 N77-11005 NAS1-13870 N77-10013 NAS1-14137 H77-10032 NAS1-14159 N77-10033 NAS2-7613 N77-10003 H77-10004 H77-10005 N77-10006 NAS2-7615 N77-10007 H77-10008 H77-10009 NAS2-8582 N77-11054 H&S2-8651 S77-10014 HAS2-8663 M77-11107 NAS2-8679 N77-10056 NAS2-8686 H77-10015 N77-10046 HAS2-8935 N77-10047 H77-10048 BAS2-9177 S77-11064 HAS3-17846 N77-11048 N77-11049 NAS3-18024 N77-11046 N77-110K7 KAS3-18544 N77-10064 BAS7-100 N77-11198 NAS9-13^47 N77-10010 NCA-OY536-501 A77-10336 NG1-22-009-124 A77-12428 N77-10432 N6E-25-001-005 N77-10355 NGE-33-016-167 N77-10351 KGE-33-016-201 N77-10351 NGE-33-018-152 A77-11195 NIVB-1737 K77-11011 KB PBOJ. 078-038 H77-11059 NR PBOJ. 215-233 077-11017 NSF C-76-12038 A77-12927 NSF GK-41482 A77-12448 NSG-268 N77-11365 NSG-1018 A77-12428 NSG-1174 N77-10354 NSG-1199 N77-10383 NSG-3048 N77-10060 N77-10061 N00014-68-A-0196-0002 A77-10855 477-10856 N00014-74-C-0151 N77-11017 N00014-75-C-0055 N77-11207 N00011-75-C-1143 N77-11059 N00019-72-C-0512 N77-10195 H00019-74-C-0267 N77-10210 N00156-70-C-1321 N77-11036 N62269-74-C-0517 N77-10029 N62269-75-C-0311 N77-11065 PBOJ. SQUID N77-11059 SBC-B/EG/85125 A77-10347 MF41422206 N77-11036 50U-09-33 N77-11044 505-04 1177-11007 1177-11008 505-05 1177-11057 505-08-30-01 N77-11001 505-10-11-01 1177-11033 505-10-21-01 N77-11345 505-11-24-02 H77-10998 510-56-01 1177-11111 513-53-02 H77-11063 743-04-01-01 N77-11031 C-1 NASA-Lanqley, 1977 1 Report No NASA SP-7'">37 (30) 2 Government Accession No 3 Recipient's Catalog No 4 Title and Subtitle AERONAUTICAL ENGINEERING A Special Bibliography (Supplement 80) 5 Report Date February 1977 6 Performing Organization Code 7 Author(s) 8 Performing Organization Report No 10 Work Unit No 9 Performing Organization Name and Address National Aeronautics and Space Administration Washington, De C. 205^ 6 11 Contract or Grant No 13 Type of Report and Period Covered 12 Sponsoring Agency Name and Address 14 Sponsoring Agency Code 15 Supplementary Notes 16 Abstract This bibliography lists ?77 reports, articles, and other documents intro- duced into the NASA scientific and technical information system in January 1977. 17 Key Words (Suggested by Author(s)) Aerodynamics Aeronautical Engineering Aeronaut!cs 3 ibliograph ies 18 Distribution Statement Unclassified - Unlimited 19 Security Qassif (of this report) Unclassified 20 Security Classif (of this page) Unclass t f i ed 21 No of Pages 22 Price" $4.75 HC for sale by the National Technical Information Service, Springfield, Virginia 22161 PUBLIC COLLECTIONS OF NASA DOCUMENTS DOMESTIC NASA distributes its technical documents and bibliographic tools to ten special libraries located in the organizations listed below Each library is prepared to furnish the public such services as reference assistance, mterhbrary loans, photocopy service, and assistance in obtaining copies of NASA documents for retention MASSACHUSETTS Massachusetts Institute of Technology. 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Baltimore MASSACHUSETTS Boston Public Library MICHIGAN Detroit Public Library MINNESOTA Minneapolis Public Library MISSOURI Kansas City Public Library St Louis Public Library NEW JERSEY Trenton Public Library NEW YORK Brooklyn Public Library Buffalo and Erie County Public Library Rochester Public Library New York Public Library OHIO Akron Public Library Cincinnati Public Library Cleveland Public Library Dayton Public Library Toledo Public Library OKLAHOMA Oklahoma County Libraries. Oklahoma City TENNESSEE Memphis Public Library TEXAS Dallas Public Library Fort Worth Public Library WASHINGTON Seattle Public Library WISCONSIN Milwaukee Public Library An extensive collection of NASA and NASA-sponsored documents and aerospace publications avail- able to the public for reference purposes is maintained by the American Institute of Aeronautics and Astronautics. Technical Information Service. 750 Third Avenue. New York. New York. 10O17 EUROPEAN An extensive collection of NASA and NASA-sponsored publications is maintained by the British Library Lending Division, Boston Spa. Wetherby. Yorkshire. England By virtue of arrangements other than with NASA, the British Library Lending Division also has available many of the non-NASA publications cited in STAR. European requesters may purchase'facsimile copy or microfiche of NASA and NASA-sponsored documents, those identified by both the symbols "ft" and "*". from ESRO/ELDO Space Documentation Service. European Space Research Organization, 114, av Charles de Gaulle, 92-Neuilly-sur-Seine, France NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC 2O546 POSTAGE AND FEES PAID ~ NATIONAL AERONAUTICS AND OFFICIAL BUSINESS SPACE ADMINISTRATION ^LTV FO« PR ,VATE USE saoo SPECIAL FOURTH CLASS MAIL NASALS, Book If I'mlelivernble (Section 158 ro-,t.il M.inu.ll) Do Not Return NASA CONTINUING BIBLIOGRAPHY SERIES NUMBER TITLE FREQUENCY NASA SP-7011 AEROSPACE MEDICINE AND BIOLOGY Monthly Aviation medicine, space medicine, and space biology NASA SP -7037 AERONAUTICAL ENGINEERING Monthly Engineering, design, and operation of aircraft and aircraft components NASA SP -7039 NASA PATENT ABSTRACTS BIBLIOGRAPHY Semiannually NASA patents and applications for patent NASA SP-7041 EARTH RESOURCES Quarterly Remote sensing of earth resources by aircraft and spacecraft NASA SP-7043 ENERGY Quarterly Energy sources, solar energy, energy conversion, transport, and storage NASA SP-7500 MANAGEMENT Annually Program, contract, and personnel management, and management technfques Details on the availability of these publications may be obtained from: SCIENTIFIC AND TECHNICAL INFORMATION OFFICE NATIONAL A E R O N A U T I C S A N D S P A C E A D M I N I S T R A T I O N Washington, D.C. 20546

Aeronautical engineering: A special bibliography with indexes, supplement 80

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