Aeronautical Engineering Case File Copy

NASA SP-7037 (80)

AERONAUTICAL ENGINEERING CASE FILE COPY

A SPECIAL BIBLIOGRAPHY WITH INDEXES Supplement 80

FEBRUARY 1977

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION 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 SP-7037(80)

AERONAUTICAL ENGINEERING

A Special Bibliography

Supplement 80

A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical 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 time, monthly 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 Office 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 Pendragon House. Inc and Astronautics 899 Broadway Avenue Technical Information Service Redwood City. California 94063 750 Third Ave New York. NY 10017 Superintendent of Documents U S Government Printing Office British Library Lending Division. Washington. D C 20402 Boston Spa. Wetherby. Yorkshire. England University Microfilms Commissioner of Patents A Xerox Company U S Patent Office 300 North Zeeb Road Washington. D C 20231 Ann Arbor. Michigan 48106

Energy Research and Development University Microfilms, Ltd Administration Tylers Green Technical Information Center London, England P 0 Box 62 Oak Ridge. Tennessee 37830 U S. Geological Survey ESA-Space Documentation Service 1033 General Services Administration ESRIN Building Via Galileo Galilei Washington, D C 20242 00044 Frascati (Rome) Italy

U S Geological Survey Her Majesty's Stationery Office 601 E Cedar Avenue P 0 Box 569. S E 1 Flagstaff. Arizona 86002 London. England

NASA Scientific and Technical Information U S Geological Survey Facility 345 Middlefield Road P 0 Box 8757 Menlo Park, California 94025 B W I Airport. Maryland 21240

U S Geological Survey National Aeronautics and Space Bldg 25. Denver Federal Center Administration Denver, Colorado 80225 Scientific and Technical Information Office (KSI) Washington, D C 20546 Zentralstelle fur Luftfahrtdoku- mentation und -Information National Technical Information Service 8 Munchen 86 5285 Port Royal Road Postfach 880 Springfield. Virginia 22161 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 .AVAILABLE ON tt MICROFICHE N77-10O48*# Lockheed Missiles and Space Co. Sunnyvale. •«- Calif Research and Development Div NASA ACCESSION CIVIL USES OF REMOTELY PILOTED AIRCRAFT Summary —CORPORATE NUMBER Report SOURCE Jon R Aderhold. G Gordon, and George W Scon Jul 1976 •*• 28 p ref TITLE. -». (Contract NAS2-893S) F .PUBLICATION ^.(NASA-CR-137895. LMSC-D057322) Avail NTIS- HC A03/MF A01 CSCL 01C -«- DATE AUTHORS. 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 .AVAILABILITY and performance requirements are derived for RPV systems, and CONTRACT SOURCE OR GRANT. 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 REPORT and safety requirements are examined, and legal and regulatory . COSATI NUMBERS. concerns are identified A potential demand for 2,000-11.000 CODE 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

TYPICAL CITATION AND ABSTRACT FROM IAA

NASA SPONSORED. • AVAILABLE ON ft MICROFICHE AIAA ACCESSION I A77-10214 * # Resizing procedure for structures under com- NUMBER 'f-*- bined mechanical and thermal loading. H M AdelmarTTNASA, Langley Research Center, Hampton, Va.) and R Narayanaswami -AUTHORS (Old Dominion University, Norfolk, Va ). AIAA Journal, vol 14. TITLE. ,*.()« 1976, p 1484-1486 6 refs E " The fully-stressed design (FSO) appears to be the most widely AUTHOR'S PUBLICATION used approach for sizing of flight structures under strength and AFFILIATION PATE 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 AERONAUTICAL ENGINEERING A Special Bibliography (Suppl. 80)

FEBRUARY 1977

fundamental influence of the diffuser on this phenomenon The diffuser being choked, the shock wave system in the throat region IAA ENTRIES '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) A77-10026 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, A77-10197 The influence of vortex shedding' on the N H ) New York, American Society of Mechanical Engineers, 1976 generation of sound by convected turbulence M S Howe (Cam- 211 p $20 bridge University, Cambridge, England) Journal of Fluid Mechanics, Papers are presented on the control of surge in dynamic vol 76, Aug 25, 1976, p 711-740 44 refs Res'earch supported by centrifugal compressors using close coupled resistances, controls for Rolls-Royce (1971), Ltd high energy centrifugal pumps to prevent pulsation and cavitation This paper discusses the theory of the generation of sound erosion, the time domain of centrifugal compressor and pump which occurs when a frozen turbulent eddy is convected in a mean stability and surge, and the effect of rotor blade wakes on centrifugal flow past an airfoil or a semnnfmite plate, with and without the compressor diffuser performance Also considered are asymmetric application of a Kutta condition and with and without the presence flow in vaneless diffusers of centrifugal blowers, the effect of inlet of a mean vortex sheet in the wake A sequence of two-dimensional flow conditions and geometries of centrifugal vaneless diffusers on mathematical problems involving a prototype eddy in the form of a critical flow angle for reverse flow, and a cascade analogy of vaned line vortex is examined To the order of approximation to which the diffuser influence on centrifugal compressor stability sound from convected turbulence near a scattering body is usually Individual items are announced in this issue B J 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 A77-1003^ The effect of rotor blade wakes on centrifugal of the diffraction field produced by the trailing edge in the case of an compressor diffuser performance - A comparative experiment S airfoil of compact chord (Author) 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 A77-10200 h Concorde navigation B J CalvertandT C R independently of any rotor has been developed (Baghdadi and Guest {International Association of Institutes of Navigation, Inter- McDonald, 1975 and Baghdadi, 1973) This paper describes a national Congress, Boston, Mass., Aug 2-6, 1976) Journal of comparative experiment designed to evaluate the applicability of Navigation, vol 29, Oct 1976, p 358-363 results obtained on this facility to actual rotating compressors Problems peculiar to Concorde navigation practice are em- Geometrically scaled diffusers were tested in the vortex nozzle phasized These include special constraints dictated by considerations facility and in an actual rotating compressor rig, and the results are of fuel conservation and optimum fuel utilization (and shifting of compared and shown to be very similar in terms of both performance center of gravity fore and aft by fuel transfer in flight), avoiding and stability limits The implications of these results are that rotor overflight of highly populated areas and particularly fccusmg of blade wake mixing and unsteadiness do not significantly affect supersonic booms near such areas, and penalties in range and diffuser performance (Author) 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 A77-10036 Experimental investigation of the near-surge are also mentioned R D V 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- A77-10207 K Application of optimahty criteria to auto- cal Engineers, 1976, p 179202 16 refs mated structural design M W Dobbs and R B Nelson (California, By using several measuring means (Schlieren visualization University, Los Angeles, Calif) AIAA Journal, vol 14, Oct 1976, p technique, fluctuating pressure transducers and wall pressure taps), 1436-1443 15 refs Grant No AF AFOSR-74-2460A the experimental study of near surge flow in a high pressure ratio This paper presents a recursive design method for the minimum centrifugal compressor is conducted in order to emphasize the weight design of linear elastic redundant structures subject to A77-10208

multiple independent static loading conditions and with behavioral A77-10251 Approximate transonic profile flow with constraints on allowable element stresses and nodal displacements shock R Mitra (Lady Brabourne College, Calcutta, India) Acta and constraints on design variables This recursive method is based on Mechanics, vol 25, no 1-2, 1976, p 1-12 ISrefs the Kuhn-Tucker necessary conditions for a local optimum and gives, The present work gives a procedure for computing approximate- upon completion, a local optimum design An iterative procedure is ly steady mviscid transonic profile flow with shock Using an analysis used to resize the structure until a design satisfying the Kuhn Tucker similar to that adopted by Hosokawa (1960), it extends the necessary conditions is obtained For resizing, it is necessary to shock-free transonic solution of Niyogi and Mitra (1973) to the case identify the current near-active (critical) constraints and to use this of flow with shock Supercritical flow past parabolic arc profiles and data to construct the Kuhn-Tucker test If the current design is not a NACA profile are computed and compared with theoretical results converged, then the information from the test is used to resize the of Oswatitsch and Zierep and finite difference solution of Murman design variables and improve the design Each iteration or redesign and Cole (1971) and with experimental results The agreements are requires only the solution of a set of linear algebraic equations equal satisfactory (Author) 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 A77-10336 * Optimal ride control for the Twin Otter, optimality criteria methods (Author) 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, A77-10208 ff Experimental investigation of the boundary Western Periodicals Co , 1976, p 585-590 5 refs Research sup- layer on a rotating cylinder J B Morton, I D Jacobson, and S ported by the Oregon State University, Grant No NCA-OY586 501 Saunders (Virginia, University, Charlottesville, Va ) AIAA Journal. An aircraft with low wing loading, such as the deHavilland, Twin vol 14, Oct 1976, p 1458-1463 10refs Grant No DAAD05-72-C- Otter, exhibits a relatively large acceleration sensitivity to wind gusts 0131 • These undesirable aircraft motions can be reduced using an auto- This paper documents the experimental analyses done in matic ride control system In this paper, the techniques of quadratic determining the stability, transition, and growth of boundary layers optimal control theory are utilized to investigate the capabilities of on a spinning cylinder at angle of attack It has been shown that spin such a ride control system The effects of the wind gusts on the alters the boundary-layer growth as well as skewing and moving aircraft can be modeled by a vector stochastic process containing forward the transition line These effects can have a significant seven states The impact of this disturbance model on the optimal influence on the thickness distribution of the boundary layer (Author) control system structure is assessed and comparison is made to a system without gust feedback (Author)

A77-10214 * ff Resizing procedure for structures under combined mechanical and thermal loading H M Adelman (NASA, A77-10338 Eigenvalue/eigenvector control via spectral Langley Research Center, Hampton, Va ) and R Narayanaswami characterization - An application to helicopter hover dynamics S (Old Dominion University, Norfolk, Va ) AIAA Journal, vol 14, Srmathkumar and R P Rhoten (Oklahoma State University, Oct 1976, p 1484-1486 6 refs Stillwater, Okla) In Annual Asilomar Conference on Circuits, The fully-stressed design (FSD) appears to be the most widely Systems, and Computers, 9th, Pacific Grove, Calif, November 3-5, used approach for sizing of flight structures under strength and 1975, Conference Record North Hollywood, minimum-gage constraints Almost all of the experience with FSD Calif , Western Periodicals Co , 1976, p 605-609 has been with structures primarily under mechanical loading as A linear state feedback gam selection procedure which allows opposed to thermal loading In this method the structural sizes are arbitrary choice of eigenvalues and certain eigenvector entries and iterated with the step size, depending on the ratio of the total stress thus provides direct control of closed loop responses is described to the allowable stress In this paper, the thermal fully-stressed design The technique is illustrated by synthesizing a hover controller for a (TFSD) procedure developed for problems involving substantial ninth order model of the SH-3D helicopter, with emphasis on thermal stress is extended to biaxial stress members using a Von stabilization and mode decoupling B J 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 A77-10347 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 A77 10218 § Amsotropic radiatively coupled wedge flow J B/RG/85125 B Elgin and J R Baron (MIT, Cambridge, Mass) AIAA Journal, A technique for reducing tonal radiation from axial flow fans is vol 14, Oct 1976, p 1492-1494 7 refs Contract No described which treats the complete downstream stator row as three F44620-75-C-0040 vane sets (each evenly distributed) and then arranges the circumfer- Geometrically thin shock layers are advantageous in reducing ential and axial positions of the sets relative to each other so as to the radiation heat transfer to a high-speed body Since elongated achieve self-cancellation of the principal interaction pattern Com- shock layers imply anisotropic radiation fields, the differential puted results are presented for a hypothetical fan with a blade tip Milne-Eddington approximation used by Gibelmg and Baron (1973) Mach number of 0 58 and a hub-tip ratio of 0 83 Results show that for minimum radiative transfer geometries is somewhat questionable the overall noise reduction of 6-9 dB originally anticipated is not for anisotropic shock layers The utility of ellipsoidal modeling for approached,and that the technique is of little value for faster fans both anisotropic and coupled fields is assessed Attention is focused (for effective Mach numbers not less than 0 4 and not greater than on an application of the'concept to a radiatively coupled wedge flow 06) BJ 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 A77-10349 ,7 Program system for computer calculations of of some importance to the distributed absorption influence S D let engine characteristics (Sistema programm dlia rascheta kharak- A77-10648

tenstik VRD na ETsVM) V I lankm Moscow, Izdatel'stvo techniques as a tool in examining and defining the RMA charac- Mashinostroenie, 1976 168 p 13refs In Russian teristics of a complex automated system which is required to The book describes a specialized system of procedures for randomly perform a number of unique functions G R 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 A77-10483 Interface between maintainability and com- is drawn up in two variants, one for computers with small mercial aircraft spares support. J E Losee (Douglas Aircraft Co , operational memory and compilers with limited number of formal Long Beach, Calif) In Annual Reliability and Maintainability procedural parameters, and one for computers with large memory Symposium, Las Vegas, Nev , January 20-22, 1976, Proceedings and many formal parameters P T H 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 A77-10383 Strength of compressor wheels of low-ductility support system that would be financially attractive in the market alloys I A Kozlov, L R Shlik, V N Gorodet#kn, L I Nemchenko, place were to be produced The general methodology currently used and V L Akhremenko (Akademiia Nauk Ukramskoi SSR, Institut by Douglas Aircraft to develop the spare support program for the Problem Prochnosti, Kiev, Ukrainian SSR) (Problemy Prochnosti, D-10 is described VP Jan 1976, p 92 97 ) Strength of Materials, vol 8, no 1.0ct 1976, p 91 95 Translation

A77-10500 Investigation and analysis of the human factors in aircraft accidents (Investigation y analists de factores humanos en los accidentes de aviacion) A Perez Griffo (Centre de A77-10416 Flow of a radiating gas over a blunt body with Investigacion de Medicina Aeronautica, Spam) Revista de Aero- intense vaporization V P Stulov and V N Mirskn (Moskovskn nautica y Astronautics, vol 36, Sept 1976, p 711-720 16 refs In Gosudarstvennyi Universitet, Moscow, USSR) ITeplofizika Vyso- Spanish kikh Temperatur, vo\ 14, Jan-Feb 1976, p 112-119) High Aerospace medicine is concerned with the study of the Temperature, vol 14, no 1, July 1976, p 98-104 15 refs physiopathological conditions existing during the flight and the Translation 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 A77-10438 A systems approach to all weather landings L contributing factor in many aircraft accidents A description is given S Gephart, W P Fuchs (Dayton, University, Dayton, Ohio), G L of the various aspects which have to be investigated in the study of Fileccia, T Joham (USAF, Flight Dynamics Laboratory, Wright- the human factors The approaches which have to be employed in Patterson AFB, Ohio), and H G Tinsley (FAA, Terminal Navigation the investigation of aircraft accidents are discussed, taking into Branch, Washington, DC) In Annual Reliability and Maintain- account studies at the location of the accident, laboratory studies, ability Symposium, Las Vegas, Nev , January 20-22, 1976, Proceed- and organizational aspects G R 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 A77-10524 Israel's pride of Lions Air International, vol program The program utilizes a large turbojet aircraft to gain II.Nov 1976, p 220-225,248,249 approach and landing experience in Category III weather The total The delivery embargo imposed by the French government in system includes the ground transmitting system with monitoring, the 1967 on 50 Mirage 5J fighter-bombers for the Israel Defense Force airborne flight control system (modified and augmented) as used in together with a subsequent extension of the embargo led to the the automatic landing model with safety pilot and crew 'in the loop', decision to manufacture the Mirage in Israel A licence was acquired and procedures, both standard and special The modeling techniques for the General Electric J79-GE-17 engine and the basic Mirage 5J partition the vertical and lateral axes/functions and sub-divide the airframe was redesigned around this power plant Attention is given longitudinal or time axis into contiguous non-overlapping sub- to the properties of the aircraft as a dogfighter, details of aircraft intervals Analysis techniques, progress and present status are design, aspects of aircraft production, and plans for export sales G R discussed (Author)

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 A77-10442 Reliability of automated flight service stations requirement drawn up in 1970, is to provide a successor for the N B Fuqua (NT Research Institute, Griffiss AFB, N Y ) In Annual C-130 Hercules In connection with the introduction of new army Reliability and Maintainability Symposium, Las Vegas, Nev , January weapons and equipment of greater size and weight, the Hercules can 20-22, 1976, Proceedings New-Yuik. InMUum- today carry only 55% of all combat brigade vehicles whereas the of Electrical and Electronics Engineers, Inc, 1976, p 113-119 10 AMST is dimensioned to carry 90% The AMST can operate into and refs Contract No F30602-73-C-0065 out of many airfields that would be unacceptable for the C-130 The The flight service station (FSS) is an FAA air traffic control YC-14 design for the AMST is discussed, taking into account details operational facility which provides services to pilots operating of aircraft structure, the power plant, aircraft performance, and the general aviation, civil air carrier, and military aircraft There are ability of the aircraft to meet mission requirements G R currently more than 300 Flight Service Stations within the contiguous U S The upgrading and automatization of the FSS system is considered An investigation is conducted to compare the reliability, A77-10648 Simulating the last 100 ft J Belsoh Flight maintainability, and availability (RMA) impact of three possible International, vol 110, Oct 23, 1976, p 1264-1266 system'configurations under study The study demonstrates the Compu-Scene, a computer-generated-image visual display system effectiveness of the 'Single-Thread Functional Availability Modeling* fitted to the flight simulators of an American aerospace company. A77 10664

has been awarded Federal Aviation Administration approval for similar to that often used to cool the leading edge of a turbine blade training purposes The optics of the system provide an infinity view has been determined from model test The influence of Reynolds through the windscreens and side windows on the flight deck Each number in the range tested is negligible However, the influence of unit is supplied with a full-color video signal representing an accurate relative distance of the jet holes from the surface to be cooled is very perspective view of the outside world as it would appear from the significant (Author) flight deck for any position and attitude of the aircraft Compu- Scene offers a full daylight scene suitable for touch-down training G R A77-10773 ff Film cooling with injection through slots D K Mukherjee (Brown, Boveri et Cie AG, Baden, Switzerland) A77-10664 Pressure distributions over frontal /nose/ sur- ASME, Transactions, Series A - Journal of Engineering for Power, faces of bodies of revolution in transonic flow at angles of attack of' vol 98, Oct 1976, p 556-559 23 ref s 0 to 10 deg P G Leutm ITsAGI, Uchenye Zapiski, vol 5, no 2, This work deals with film cooling of a surface with injection 1974, P 130-135) Fluid Mechanics - Soviet Rrtearch, vol 4, through slots From the vast number of literatures surveyed, the Nov-Dec 1975, p 18-24 5 refs Translation 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 A77-10665 The hyperbolicity of integral equations of (Author) 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 A77-10854 ~ Forces on unstaggered airfoil cascades in unsteady 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 A77-10697 Bird hazards to aircraft Problems and preven- Incompressible flow through an unstaggered cascade in general, tion of bird/aircraft collisions H Blokpoel (Environment Canada, unsteady, m-phase motion is considered By methods of thin airfoil Canadian Wildlife Service, Ottawa, Canada) Research sponsored by theory, using the assumptions of wakes trailing back at the the National Research Council of Canada, Ministry of Transport and through-flow velocity, and the Kutta condition, exact analytical Department of National Defence Toronto, Clarke, Irwm and Co, expressions are derived for loading, lift and moment As application. 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 A77-10855 " Flow interaction near the tail of a body of sizes and weights, the annual cycle of bird migration, methods of revolution I - Flow exterior to boundary layer and wake A studying migration, heights of migration, the behavior of birds with Nakayama, V C Patel, and L Landweber (Iowa, University, Iowa respect to approaching aircraft, and the types of damage resulting City, Iowa) (American Society of Mechanical Engineers, Paper from bird strikes Work related to the bird-proofing of aircraft and 76-FE-M, 1976 ) ASME, Transactions, Series I - Journal of Fluids engines is considered and a description is given of a search for Engineering, vol 98, Sept 1976, p 531-537 18 refs Research on-board equipment to disperse birds Approaches for the prevention supported by the University of Iowa, Contract No N00014-68- of bird strikes are discussed, giving attention to bird observation A-0196-0002 methods, bird dispersal methods, habitat manipulation, and pro An iterative procedure for the calculation of the thick attached cedures to minimize strike risks during periods of high bird densities turbulent boundary layer near the tail of a body of revolution is G R 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 A77-10771 H Unsteady pressure distributions on oscillating continuous across the edge of the boundary layer and the wake The airfoils in a supersonic cascade M Kurosaka (GE Research and additional terms that appear in the momentum integral equation for Development Center, Schenectady, N Y) ASMS, Transactions, the thick boundary layer and the near wake are taken into account Series A - Journal of Engineering for Power, vol 98, Oct 1976, p and the pressure difference between the body surface and the edge of 553, 554 the boundary layer and the wake can be determined The results In Kurosaka's exact first-order theory for the unsteady super- obtained by the present method are in good agreement with the sonic cascade with a subsonic leading edge, the expression for the experimental data (Authoi) 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 A77-10856 ,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 A77-10772 ff Pressure loss coefficient of impingement of Mechanical Engineers, Paper 76-FE-N, 1976) ASME, Trans- cooled leading edge system of a turbine blade D K Mukherjee actions, Series I - Journal of Fluids Engineering, vol 98, Sept 1976, (Browa Bj>ven et Cie AG, Baden, Switzerland) ASME, Transac- p 538-546, Discussion, p 546-548, Author's Closure, p 548, 549 tions, Series A - Journal of Engineering for Power, vol 98, Oct 33 refs Research supported by the University of Iowa, Contract No 1976, p 554-556 18 refs N00014-68 A-0196-0002 ' The pressure loss coefficient of an impingement cooled system 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 A7710939 if Strength of glass-fibre-remforced plastics at its interaction with the external potential flow which was treated in one-sided heating G S Pisarenko and G N Tret'iachenko (Akade- Part 1 The iterative technique described in Part 1 is used to obtain a miia Nauk Ukramskoi SSR, Institut Problem Prochnosti, Kiev, complete solution to the flow in the neighborhood of the tail of the Ukrainian SSR) International Astronautical Federation, Interna- body The results of the calculations are compared with two sets of tional Astronautical Congress, 27th, Anaheim, Calif, Oct 10-16, experimental data and reasonable agreement is demonstrated 1976, Paper 76-200 8 p 11 refs (Author) 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, A77-10882 K Dual-spin spacecraft dynamics under con- insulating, etc ) purpose The facilities described in the present paper ditions of a rotating unbalanced platform and rotor asymmetry G J are designed for testing such protective coatings in bending, tension, Adams (Hughes Aircraft Co , Space and Communications Group, Los or compression under unilateral heating Some techniques used to Angeles, Calif) International Astronautical Federation, Inter- simulate the actual heating conditions are discussed V P 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 A77 10972 # Beyond supersonic transport S B Rosenfield energy dissipation with the platform despun If the platform is (New England School of Law, Boston, Mass ) International Astro- rotating, however, the dynamic response is determined by platform nautical Federation, International Astronautical Congress, 27th, dynamic imbalance and rotor transverse inertia symmetry in addition Anaheim, Calif, Oct 10-16, 1976, Paper ISL-76-66 14 p 7 refs to energy dissipation effects The rotating platform case is important The legal aspects of a future civil transport system consisting of as a temporary condition from which it is desired to recover The travel both in the atmosphere and in outer space - the civil air-space paper gives a heuristic description of the vehicle dynamics for ransport system • are considered The discussion is based on the roll/pitch ratios above and below unity, a summary of m-orbit separate examination of space law and air law B J experience with the TACSAT and DSCS-2 satellites, and a description 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 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 A77-10911 /f The fuel approach to control emissions from No NGR-33-018-152 aircraft R W Hurn (ERDA Bartlesville Energy Research Center, Bartlesville, Okla ) International Astronautical Federation, Interna- A program has been carried out to study and develop high tional Astronautical Congress, 27th, Anaheim, Calif, Oct 10-16, temperature aircraft brake materials A survey of the requirements of 1976. Paper 76-111 7p brake materials was made to select materials to meet these Control of fuel composition may provide a means to control or requirements Based upon their physical and thermal properties, a affect the emission of metals, sulfur, smoke, and nitrogen oxides number of materials were selected and evaluated in sliding tests Metals emissions can be related to the occurrence of metals as trace which simulated aircraft braking The mating material is 17-22 AS elements in crude oils and to an erosion of metal engine parts Sulfur steel Additives were incorporated into these materials to optimize in fuel constitutes the only significant source of that element or its their wear or strength behavior with particular emphasis on nickel derivatives in turbine exhausts Suitable approaches for reducing the and molybdenum base materials Optimum materials were developed amount of sulfur and sulfur oxide emissions are considered G R 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 molybdenum base material containing LPA 100 (an intermetallic com- pound of cobalt, molybdenum and silicon) (Author) 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, A77-11261 Competition for airspace - Bird strikes and England) International Astronautical Federation, International aircraft operations R W Doughty (Texas, University, Austin, Tex ) Astronautical Congress, 27th, Anaheim, Calif, Oct 10-16, 1976, Traffic Quarterly, vol 30, July 1976, p 449-467 16 refs Research Paper 76-112 21 p 20 refs supported by the University of Texas Since for maximum range a supersonic transport must cruise The hazards of bird collisions with aircraft are examined and the near its maximum Mach number, accurate flight control is needed, growing encroachments of airports on wildlife habitats, particularly especially when severe atmospheric transients are encountered This for certain species of birds, are noted Tables are presented paper describes atmospheric transients that have been encountered containing information on significant bird-aircraft strikes from 1960 by the XB-70, YF-12, and Concorde aircraft during supersonic flights to 1974 and annual variations in damaging bird strikes, US Air Force and the ensuing responses of the aircraft propulsion and flight 1956-1972 The relation of inflight collison risks and bird migration control systems It was found that atmospheric conditions affected is investigated as are bird hazards on airport environments Methods these supersonic cruise vehicles in much the same way, with minor for reducing bird hazards including distress calls, noise makers, differences according to the type of propulsion and flight control chemical repellents, pyrotechnics and falconry are discussed B J 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 A77-11276 European Rotorcraft and Powered Lift Air- to the control systems Nominal atmospheric transients can be craft Forum, 1st, University of Southampton, Southampton, satisfactorily controlled, but some problems remain for extreme England, September 22-24, 1975, Proceedings Vertica, vol 1, no 1, cases (Author) 1976. 93 p A77-11277

The first issue of a new periodical devoted to rotorcraft and A77-11280 Hmgeless rotor dynamics in high speed flight. powered lift aircraft covers numerous topics in rotorcraft engineering H Huber and H Strehlow (Messerschmitt Bolkow-Blohm GmbH, and applications Topics represented include circulation control Ottobrunn, West Germany) (European Rotorcraft and Powered Lift rotors and stowed rotors, winged rotorcraft, rotor and flap control Aircraft Forum, 1st, Southampton, England, Sept 22-24, 1975) systems, vibration analysis and control, hinge less rotors, comparative Vertica, vol 1,no 1,1976, p 39-53 11 refs studies of passenger-service VTOL, STOL, and CTOL capabilities and A high speed flight research program has been carried out on shortcomings, and rotor-emitted noise analysis and abatement MBB BO 105 Hmgeless Rotor behavior within an expanded flight Individual items are announced in this issue R D V 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 A77-11277 Application of circulation control rotor tech- emphasis is placed upon rotor structural loads, control and stability nology to a stopped rotor aircraft design R M Williams (U S Naval behavior, and aeroelastic stability characteristics A continuous Material Command, Ship Research and Development Center, picture of hingeless rotor characteristics over a wide speed and Bethesda, Md ) (European Rotorcraft and Powered Lift Aircraft maneuver range is presented (Author) 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- A77-11281 Rotor impedance measurements at model tion of circulation control rotor (CCR) technology to the concept is scale D R Gaukroger and R Cansdale (Royal Aircraft Establish- discussed Handling of transition lift by blowing out of rotor slots ment, Structures Dept, Farnborough, Hants, England) (European separately or in unison and resulting advantages are dealt with Rotor Rotorcraft and Powered Lift Aircraft Forum, 1st, Southampton, design, blade and disk loading, and blade weight analysis are covered England, Sept 22-24, 1975) Vertica, vol 1, no 1, 1976, p 55-66 in addition to fixed-wing and rotary-wing performance modes A test rig has been built at the Royal Aircraft Establishment to (including stopped-wing mode, stowed-wing mode, and blown 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 fixed-wing mode) Aeroelastic bending divergence in the stopped- say, 1/5 or 1/4 scale models of an 'average' rotor The method of test wmg mode, resonant amplification of blade vibratory bending is to oscillate the rotor shaft in a particular direction over a range of stresses during rotor slowing and stopping, and potential high- frequencies and to measure the force or moment required to produce frequency coupled instabilities of isolated blades, multi-blades, and the oscillation, and the forces and moments required to prevent rotor/body combination are critical R D V 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 A77-11278 Advanced control systems for helicopters I matrices of rotor shaft impedances can be used either to check A Simons (Westland Helicopters, Ltd , Yeovil, Somerset, England) theory or to assess the stability of the rotor when it is joined to a (European Rotorcraft and Powered Lift Aircraft Forum, 1st, fuselage In the latter case, the impedance matrix of the fuselage Southampton, England, Sept 22-24, 1975) Vertica, vol 1, no 1, must also be determined (Author) 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 A77-11282 A wing on the SA 341 Gazelle helicopter and control systems is introduced as a possible solution to these problems its effects M Torres (Societe Nationale Industnelle Aerospatiale, and as a means to releasing some of the present rotor design Division Helicopteres, Mangnane, Bouches-du-Rhone, France) constraints - particularly in rotor stiffness In order to illustrate the (European Rotorcraft and Powered Lift Aircraft Forum, 1st, potential freedom in helicopter design resulting from the adoption of Southampton, England, Sept 22-24, 1975) Vertica, vol 1, no 1, very stiff rotors, their use in a coaxial system is briefly discussed 1976,p 67-73 (Author) 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 A77-11279 Reducing vibration by structural modification a flying- prototype Results of wind-tunnel tests, simulator tests, GTS Done and A D Hughes (Edinburgh, University, Edinburgh, reference flight tests, and basic flight tests are stated Airbrakes were Scotland) (European Rotorcraft and Powered Lift Aircraft Forum, fitted onto upper and lower wing surfaces as the wing adversely 1st, Southampton, England, Sept 22-24, 1975) Vertica, vol 1, no affects autorotation, producing high wing lift, unloading the rotor, 1,1976,p 31-38 and decreasing rotor rpm Interactions between wing and stabilizer, Selection of criteria for singling out those elements of a adjustments of wing area, dihedral and incidence angles, use of helicopter fuselage structure to be treated as variables in a model removable wing tips and adjustable struts, and stabilizer settings are designed to aid minimization of vibration response by modifying the described, along with quick-stop maneuvers using airbrakes, wing fuselage structural design are discussed Pinpointing sensitive and stall, and behavior in dive, banking, and hover R D V 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, A77-11283 Intercity VTOL aircraft - A Hawker Siddeley sensitivity criteria, and application to a simplified 60 DOF helicopter review M J Brennan (Hawker Siddeley Aviation, Ltd , Kingston-on- fuselage structure are discussed The gearbox and tail cone sub- Thames, Surrey, England) (European Rotorcraft and Powered Lift structures are found crucial areas for fuselage modification to achieve Aircraft Forum, 1st, Southampton, England, Sept 22-24, 1975) vibration abatement in the passenger and crew area R D V Vertica, vol 1,no 1,1976, p 75-88 11 refs A77-11595

Comparisons between CTOL, STOL, and VTOL flight in A77-11325 High-nickel alloys for gas turbines J H passenger service are made for a wide range of criteria Comparative DeBord (Huntmgton Alloys, Inc ) Gas Turbine International, vol data are tabulated and diagrammed for passenger seat-km and loads, 17, Sept-Oct 1976, p 28-30 take-off and landing regimes, approach speed and angle, runway Mechanically alloyed and conventionally alloyed high-nickel length, required airport area, noise footprints, airport costs, air refractory alloys for gas-turbine design applications are discussed traffic segregation, first costs and operating costs, total journey costs along with their advantages and applications The article deals with and total journey time, fuel consumption and flight time, time mconel grades MA 754, MA 757E, 617, 625, 718, and 706, and with response to weather data, and instrumentation demands Service to mcoloy grades MA 956E, 903, and MA 757E Aerospace applications low-density communities, intercity shuttle traffic, and detrimental are given emphasis, including use of mcoloy alloy 903 in the Space social and political aspects of CTOL service are stressed STOL Shuttle Mam Engine Use of mconel 625 in aircraft ducting systems, disadvantages in terminal-phase gust conditions are cited Time engine exhaust systems, thrust reverse systems, honeycomb struc- required to develop a V/STOL transport system from scratch is tures, heat exchanger tubing, mconel 718 in compressor and turbine considered R D V 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

A77-11284 Rotational noise measurement in a wind tunnel by total sampling synchronization C Armand (ONERA, Chatillon-sous-Bagneux, Hauts-de-Seme, France) (European Rotor- A77-11477 Estimating fatigue-crack lives for aircraft - craft and Powered Lift Aircraft Forum, 1st, Southampton, England, Techniques. J P Gallagher (USAF, Flight Dynamics Laboratory, Sept 22-24, 1975.) Vertica, vol 1, no 1, 1976, p 89-92 Wright-Patterson AFB, Ohio) (Society for experimental Stress A new method, total sampling synchronization (TSS), for Analysis, Spring Meeting, Chicago, III., May 11-16, 1975) Experi- extracting the rotational noise of an advancing rotor blade from wind mentalMechanics, vol 16, Nov 1976, p 425-433 24 refs tunnel noise is described The TSS method provides the best Some complex aircraft stress histories, steady-state spectra, are adaptation of numerical Fourier analysis to rotational noise or other noted to induce fatigue-crack growth-rate behavior similar to that periodic phenomena Rotorcraft rotational noise is singled out as the observed under constant-amplitude loading The paper identifies, the most troublesome and discomforting noise contribution emitted in behavior induced by steady-state spectra, and attributes the behavior flight, but deficiencies of in flight measurements (relative positions to spectrum-stress-event periodicity Spectrum periodicity is sub- of microphones and rotorcraft, limitation of speeds of existing sequently defined by isolating the group of statistically repetitive rotorcraft and rotors, and poor representation from onboard stress events The noted crack-growth-rate behavior that exists for microphone signals) dictate the use of high-speed wind tunnels for steady-state spectra provides the analyst with new techniques for noise testing Noise spectral analysis with correlations, with partial estimating crack lives Several crack-life estimating techniques are synchronization of sampling, with total sampling synchronization, compared, for the two steady-state spectra considered herein, one and uncorrelated, is examined and compared R D V technique called the simple-crack incrementatiorvmmiblock approach provides life estimates with the same accuracy as that given by the cycle-by-cycle life-prediction method studied but does so five A77-11311 Co-operation in the European aircraft manu- times more efficiently The reasons for associated accuracy and facturing industry and among the scheduled airlines /Brancker efficiency are discussed (Author) 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 A77-11594 Investigation into the optimum use of has achieved it in AECMA (European Association of Aerospace advanced displays in future transport aircraft R E Hillman (British Manufacturers), in AEA (Association of European Airlines), in ECAC Aircraft Corp, Weybndge, Surrey, England) and J W Wilson (European Civil Aviation Conference), in KSSU (KLM, SAS, SWR, (Hawker Siddeley Aviation, Ltd , Hatfield, Herts , England) (Royal UTA) and in ATLAS (Air France, Alitalia, Iberia, Lufthansa, Sabena) Aeronautical Society, Spring Convention on Seeds for Success in and other cooperating groups in Europe is discussed Particular Civil Aircraft Design in the Next Two Decades, London, England, emphasis is on the EEC commission's proposal regarding extended May 19, 20, 1976) Aeronautical Journal, vol 80, Sept 1976, p cooperation and centralization of the aerospace manufacturers and 377-384 airlines of the EEC Modifications of the EEC commission's proposal New and future systems and formats for presentation of flight are suggested B J 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 A77-11312 Transport progress in practice Air transport in categories with different characteristics dictated by safety, precision, Africa - East African Airways Corporation Experience A B S cost, and work load needs flight, engine, and system displays A Kilewo (East African Airways Corp, Nairobi, Kenya) (Chartered comparison is set up between a two-crew flight deck outfitted with 7 Institute of Transport, Congress, Nairobi, Kenya, May 1976) CRT displays and a contemporary 3-engme 3-crew wide-bodied r Chartered Institute of Transport Journal, vol 37, July 1976, p aircraft Development of flexible electronic attitude director indi- 128-132 cators and horizontal situation indicators with all required navigation Some major problems facing the development of air transport and flight information efficiently displayed, untimely and super- industry in Africa are outlined, and the part played by the air fluous data suppressed, and relevant data integrated onto a smaller transport industry in the economic development of the East African display area, is encouraged R D V 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 A77-11595 Future trends in aero gas turbine design II - stronger airlines in the African subregions The need for a co- Unconventional engines R M Denning, S C Miller, and G H ordinated transport policy and mutual assistance is emphasized V P Wright (Rolls Royce /1971/, Ltd, Aero Div, Bristol, England) A77 11603

(Royal Aeronautical Society, Spring Convent/on on Seeds for A simple acoustic sounder is shown to produce reliable velocity Success in Civil Aircraft Design in the Next Two Decades, London, profiles of aircraft wakes at altitudes below 50 m Data collection England, May 19, 20, 1976) Aeronautical Journal, vol 80, Sept during normal airport landing operations was feasible because the 1976, p 385-393 9 refs sensor does not intrude into the airspace being measured A spatial Unconventional types of aircraft gas turbine (GT) engines scan through the wake is obtained when the ambient wind transports reviewed are so treated in the sense of unconventional uses (other the wake through the sounder beam The characteristics of the than propulsionl for the GT engine, modification of the thermo- scattered signals and their spectral densities are presented as intensity dynarmc cycle under some flight conditions, or use of extremes of modulated CRT displays termed 'Acoustograms' The data are the constant-pressure GT cycle Variant thermodynamic/aero- processed to yield the radial dependence of the velocity and dynamic cycles under consideration include a heat-exchanger circulation in the wake vortices The circulation data are fitted to a engine, propulsion systems with mgestion or re-energizing of wake or simple mode1 with two parameters strength and core radius The boundary layer to reduce drag, and systems resorting to laminar flow spatial and velocity -esolution of the sounder is adequate to measure control Jar boundary layer suction Engines featuring in flight vortex strength but not to probe details of the core structure variation of the thermodynamic cycle include those using variable Reliable measurements using this technique are possible only when turbine stators, SST variable-cycle engines with compressor switching the vortex transport velocity is well-defined (Author) 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/ A77-11844 A test facility for aircraft jet noise reduction propulsion fan engines R D V 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 A77-11603 Signal-treatment methods during aircraft- Boeing large test chamber (LTC) and subsystems for studying engine inspection based on vibroacoustic noises V V Izokh and V abatement of aircraft jet noise Support systems for the LTC facility, I Mikulovich (Belorusskn Gosudarstvennyi Umversitet, Minsk, Belo- the anechoic room, acoustic calibration problems, data handling, russian SSR) (Defektoskopua, Jan -Feb 1976, p 39-47 ) Soviet Journal of Nondestructive Testing, vol 12, no 1, Nov 1976, p support systems and test rigs are described at length Acquisition of 29-34 15 refs Translation reliable aircraft noise performance test data and isolation of LTC noise and surrounding community noise are singled out as the key Several methods of signal analysis for vibroacoustic flaw problems Measures to keep outside community noise from intruding detection applied to the rotating parts of aircraft engines are described The methods considered are spectral analysis and correla- into the test arena, and preventing LTC noise from causing a tion analysis, and it is found that it is desirable to use synchronous nuisance in the surrounding community area are detailed Test area detection and spectral analysis with high resolution for inspecting sizing, flow visualization, the development model chamber, a model propane burner, exhaust stack, pumps, room ventilation, air supplies, engines and their individual rotating parts under service conditions and in the experimental design stage B J cooling water, safety measures, and future LTC facility needs are dealt with R D V

A77-11606 Magnetic particle inspection of aviation engine A77-11887 Laser air-jet engine A I Barchukov, F V vanes A G Aleksandrov and S G Shehkhov (Defektoskopua, Bunkm, V I Konov, and A M Prokhorov (Akademna Nauk SSSR, Jan-Feb 1976, p 81-85 ) Soviet Journal of Nondestructive Testing, Fizicheskn Institut, Moscow, USSR) (ZHETF Pis'ma v Redakts/iu, vol 12, no 1,IMov 1976, P 6265 Translation vol 23, Mar 5, 1976, p 237-240 ) JETP Letters, vol 23, Mar 5, Consideration is given to the reason for the decrease in revealing 1976, p 213215 6 refs Translation fine fatigue cracks in aviation engine vanes in inspection in an A scheme is outlined for a laser air jet engine (LAJE), in which electromagnet Recommendations for inspection methods are given jet thrust is obtained by optical discharges in the engine caused by a Compositions of magnetic suspensions and methods of interpretation pulsed radiation beam generated on earth Pulsed optical breakdowns are shown (Author) 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 A77-11625 '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 A77-12000 VTOL RPVs - A technology assessment B variable speed It is to replace the target drones of the type CT20 It Lmdenbaum American Helicopter Society, Journal, vol 21, Oct is expected that the mass production of the C22 will begin in 1981 1976, p 29-39 The target drone is to be propelled by the turbojet engine TRI 60 Military uses and advantages of VTOL remotely piloted vehicles which is also to be used in remotely piloted vehicles The C22 will be (RPV) and VTOL RPV development problems are discussed, along employed with a towed target for gunnery-training exercises of with the state of the art, means of RPV recovery and launch, and antiaircraft artillery and for tests conducted with surface to air numerous VTOL concepts The higher unit cost of VTOL systems is missiles The C22 will be able to attain a speed of 0 95 Mach G R 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, A77-11712 ft Measurement of, wake vortex strength by size, availability of all known VTOL approaches) VTOL concepts means of acoustic back scattering D C Burnham, T E Sullivan considered and compared for RPV application include jet lift, (U S Department of Transportation, Transportation Systems Center, augmented thrust (with lift fan and ejector type flow augmenters), Cambridge, Mass), and L S Wilk (MIT, Cambridge, Mass)'Journal shrouded propeller/fans, open propeller/rotor, and VATOL (vertical of Aircraft vol 13, Nov 1976, p 889-894 9 refs attitude TO L tail-sitter configuration) RDV A77 12182

A77-12069 Maintaining transport aircraft R Krahenbuhl A77-12175 H Dynamic-stress-data management for aero- (Swissair AG, Kloten, Switzerland) Esso Air World, vol 28, no 4, mechanical testing of turbomachmery W J Rakowski (ARO, Inc , 1976, p 90-93 Arnold Air Force Station, Tenn ) Society for Experimental Stress The article surveys Swissair maintenance practice at Zurich Analysis, Spring Meeting, Silver Spring, Md. May 9-14, 1976. Paper airport, covering the integration of existing computer maintenance 26 p programs, programs of periodic checks, and a rundown of main The aeromechanical test programs described were initiated to tenance theory for wide-body craft Hard time maintenance, on provide experimental data concerning specific turbine engine struc- condition maintenance, and condition monitoring are defined and tural problems and general characterization of turbine engines Test contrasted, fail safe and safe life options are defined and their ranges techniques and data acquisition/processing analysis techniques were of validity are stated, and the maintenance decision diagram adopted developed during these test programs to meet the program require- in 1970 is outlined The computerized automatic test equipment, ments The present paper deals with the data management philos- built in test equipment, and aircraft integrated data system are ophy and techniques developed for the dynamic strain-gauge data sketched Periodic checks, from service check after each flight acquired during the programs The transition from single channel through checks scheduled for 270 and 1500 flight hours to the heavy analog analysis equipment to the incorporation of digital computers maintenance visit (after 12,000 flight hours), are indicated Physical for aidina on-line data monitoring, bulk processing of test data, and inspection methods, time allocations in maintenance tasks, and rapid analysis of test results is discussed The present on-line cooperation in maintenance pooling between various carriers are monitoring and post test processing/analysis systems are described, mentioned R D V 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, A77-12176 # System considerations for reliable strain data Toulouse, France) L'Aeronautique et L'Astronautique, no 60, from gas turbine engines D L Willis (General Motors Corp , Detroit 1976, p 10-15 In French Diesel Allison Div , Indianapolis, Ind ) Society for Experimental Data are presented and tabulated on Air France Concordes run Stress Analysis, Spring Meeting, Silver Spring, Md, May 9 14, 1976, through endurance tests to date Data on each aircraft tested, on the Paper 17 p flights executed, the routes traveled, amount of fuel consumed, This discussion will consider the problems of dynamic stiam amount of fuel taken on board, flight profiles, prescheduled detours, gage installations on the high pressure turbine rotor of a typical and test facilities placed on board for the endurance tests are twin-spool gas turbine engine The hostile environment of high included Time out of service during this period is compared to temperatures, centrifugal loads and very limited physical space are figures for subsonic large aircraft It is concluded that Concorde has defined and the total system elements to meet these re-requirements proved itself as an operationally viable passenger aircraft R D V 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 A77-12115 Concorde maintenance as seen by the designer choices for signal transfer devices are also discussed with a summary - The maintenance program (La maintenance de Concorde vue du of advantages and limitations for various systems (Author) 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 A77-12181 H Estimating procedures associated with aircraft on routine preventive maintenance procedures Some modes of modifications J A Knagg (E-Systems, Inc , Dallas, Tex ) Society of maintenance are distinguished, parties directly interested in orgamza Allied Weight Engineers, Annual Conference, 35th, Philadelphia, Pa, tion of maintenance (airline, aviation officials, and designers) are May 24-26, 1976, Paper 1101 lip indicated, and examples of maintenance documentation are pre Modification of existing or obsolescent aircraft is discussed from sented Structural analysis, analysis by zones, and analysis based on the viewpoint of the weight engineer Several examples of modified aircraft, equipment, and motor systems are contrasted Organization aircraft are described, and a general modification methodology is of the maintenance data bank is sketched Emergency repair outlined Consideration is given to the use of micromodules in procedures and inspection frequency are discussed briefly R D V 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 A77-12182 # Fuselage analytical weight estimation method Malfunction analysis and assessment, reporting and documenta A D G Bayly (Lockheed California Co , Burbank, Calif ) Society tion, and acquisition and treatment of fault data are discussed for of Allied Weight Engineers, Annual Conference, 35th, Philadelphia, civil aviation landing gears and hydraulics systems, on the basis of Pa , May 24-26, 1976, Paper 1102 20 p Messier Hispano practice Various levels of readily diagnosed and Much time and energy has been spent into the investigation of hidden faults are considered, and tables and branching trees of fault fuselage weight prediction methods Most of these methods have diagnostic tests (for mistimed landing gear actuation) are displayed been established by the use of statistical data derived from past and Leakage of hydraulic fluid and seizing of equipment parts are also existing aircraft A more accurate and convenient method is required treated An outline of fault data reporting procedure and fault for use during the contract definition phase of a program where more coding procedure is presented, along with a sample fault report sheet detailed information is readily available to the weight engineer This R D V paper presents an analytical method of weight prediction for the A77-12183

basic shell of any fuselage It assumes that the shear loads are A77-12194 * ff Application of advanced technology to future absorbed by the skin and stringers and the bending loads are taken long-range aircraft 0 E Schrader (NASA, Langley Research Center, out by frames and longeron Basic loads are required to be known in Hampton, Va ) Society of Allied Weight Engineers, Annual Con- order to determine the shear and bending material of the shell ference, 35th, Philadelphia, Pa , May 24-26, 1976, Paper 1126 45 p structure The method also takes into account cutouts, pressunzation 9 refs and shape penalties The resulting basic shell weight can then be used The objective of this paper is to provide an overview assessment along with statistical data for specific design features to arrive at a of three separate programs at Langley Research Center that have total fuselage weight (Author) 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 A77-12183 ff Weight and balance considerations in the weights The second technology is the application of laminar flow design of the A-10A close air support aircraft G C Leavy (Fairchild control (LFC) to the aircraft to reduce the aerodynamic drag The Republic Co , Farmmgdale, N Y ) Society of Allied Weight En- use of LFC can reduce the fuel requirements during long-range gineers, Annual Conference, 35th, Philadelphia, Pa, May 24-26, cruise The last program evaluates the production of alternate aircraft 1976, Paper 1104 30 p fuels from coal and the use-of liquid hydrogen as an aircraft fuel This paper describes the design features included in the A-10A Coal-derived hydrogen as an aircraft fuel offers both the prospect for Close Air Support Aircraft which had a significant effect on the reduced dependence on petroleum fuels and improved performance aircraft weight and balance Particular attention is given to the for long-range aircraft (Author) 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 A77-12195 •/' The next-generation subsonic transport D P the effects of these design features on the configuration and size of Marsh (Douglas Aircraft Co , Long Beach, Calif ) Society of Allied the aircraft (Author) 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 A77-12184 ff Advanced design composite aircraft, the next commercial subsonic transport is discussed The principal near-term step for composites P Schwartz (Grumman Aerospace Corp, design objectives are reduced fuel consumption and the development Bethpage, N Y) Society of Allied Weight Engineers, Annual of a configuration, to satisfy this goal, on the basis of wing geometry Conference, 35th, Philadelphia, Pa, May 24-26, 1976, Paper 1105 studies, advanced technology applications, and fuselage and engine 13 p Contract No F33615-75 C-3124 configuration studies The results of the configuration development The Advanced Design Composite Aircraft (ADCA) program was studies, marketing reports, and airline inputs indicate that the initiated to define the benefits and effects of unrestrained applica- next-generation transport will incorporate the following features tion of composite materials to a completely new aircraft The present all-new wing design with higher aspect ratios for reduced drag, paper deals with the first phase of the ADCA program whose aim was advanced high-lift systems for reduced noise and wing area, in- to define criteria and requirements affecting ADCA design This corporation of such advanced technologies as supercritical wing, phase included parametric tradeoff studies conducted to identify the composite materials, and relaxed static stability to reduce fuel preferred aircraft configuration and also the weight savings compared consumption and weight, reduced passenger capacity over current with an equivalent metal counterpart The Supersonic Penetration wide-body transports to meet market requirements, reduced cruise Interdiction Fighter mission was chosen because it provides the most speed for minimum operating costs, and commonality with existing demanding set of requirements and yields the maximum potential transport aircraft to reduce development costs V P 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 A77-12201 # Aircraft loadabihty parameters - Some results its metal counterpart V P 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 A77-12191 # A method for estimating the weight of aircraft A survey was conducted to obtain current information from transmissions A H Schmidt (Boeing Vertol Co, Philadelphia, Pa) commercial airlines regarding those items which affect load flexibili- Society of Allied Weight Engineers, Annual Conference, 35th, ty A summary is presented of the data obtained to date These data Philadelphia, Pa, May 24-26, 1976, Paper 1120 24 p are being used to aid the development of a method for optimizing In the design phase of vertical take-off aircraft, it is necessary to the initial construction of a design center-of-gravity envelope for estimate the weight of the transmissions in the drive system as commercial aircraft F G M 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 A77-12202 ff Operational mass properties data for military easily obtained values of surface compressive stress index, design aircraft - Data formulation, presentation and usage T Dills (General horsepower, and gearbox input speed are used along with various Dynamics Corp, Fort Worth, Tex ) Society of Allied Weight factors for special features, etc Also included, are the weight effects Engineers, Annual Conference, 35th, Philadelphia, Pa, May 24 26, of bearing supports, output shaft, combining stages of gearing and 1976, Paper 1147 56 p 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 A77-12206 Structural tests of aerodynamic surfaces - A the application of the weight estimating method for typical systems approach to analysis and design K Goldenberg (Albany gearboxes A plot of the statistical accuracy of this method is also Medical College, Albany, N Y ) Journal of Testing and Evaluation, presented (Author) vol 4, IMov 1976, p 418-424 7 refs

10 A77-12460

One of the primary tasks in structural ground testing of the maneuver is less than 1 sec, the ailerons must be reversed at some aerodynamic surfaces is to resolve complex, curvilinear pressure stage so that the roll rate becomes zero when the aircraft has rolled fields into applied test loads A systems approach is presented which through the desired angle, and the elevator deflection should be optimally performs this analysis and integrates it with major maximum at the end of the maneuver since the normal acceleration subsequent phases of the engineering operation specifically, correla- must be maximum only at the end F G M 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 A77-12448 On the identification of state-denvative- rapidly using curve fitting and statistical methods modified for test coupled systems J M Mendel (Southern California, University, Los data evaluation (Author) 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 A77-12218 Lifting-surface theory of straight cascades of of Electrical and Electronics Engineers, Inc, 1975, p 529-533 8 swept blades A F Falcao (Institute Superior Tecmco, Lisbon, refs NSF Grant No GK-41482 Portugal) International Journal of Mechanical Sciences, vol 18, no A description is given of a sequence of tests for establishing the 6, 1976, p 313-320 17 refs Research supported by the Institute de identifiability of structural parameters which are associated with a Alta Culture given structural state equation, from reduced form parameters, which Lifting-line and lifting-surface expressions are derived for the are associated with a reduced form state equation A test involving steady irrotational incompressible flow through a straight cascade of the determination of the rank of a matrix is developed to make a use swept blades of finite length and constant loading along the span, the of either structural parameters or reduced form parameters possible mam object being to study the three-dimensional perturbations The application of the identifiability tests is illustrated with the aid arising from the presence of the end walls and to determine the of an example G R 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 A77-12452 The pursuit-evasion problem of two aircraft in velocity potential, is based on the author's analytical expressions for a horizontal plane N Rajan and U R Prasad (Indian Institute of cascades of unswept blades of varying circulation along the span Science, Bangalore, India) In Conference on Decision and Control, Numerical results are presented for a wide range of cascade 6th, and •Symposium on Adaptive Processes, 14th, Houston, Tex , geometries, and the effects of several cascade parameters upon the December 10-12, 1975, Proceedings New York, wall-induced three-dimensional perturbations are discussed In partic- Institute of Electrical and Electronics Engineers, Inc, 1975, p 635, ular, it has been found, for most geometries used in practice, that a 636 5 refs good approximation is obtained by superposing the disturbances due The pursuit-evasion problem of two aircraft in a horizontal to the two walls separately (Author) 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 A77-12428 « The stochastic .control of the F 8C aircraft differential game are solved (Author) 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 A77-12455 R & D project cost and schedule realism - A New York, Institute of Electrical and Electronics risk analysis approach D C Borgman (U S Army, Air Mobility Engineers, Inc, 1975, p 217-228 15 refs Grants No Research and Development Laboratory, St Louis, Mo ) and J D NGL-22-009-124, No NsG 1018, No AF AFOSR-72-2273 Hwang (U S Army, Air Mobility Research and Development The purpose of this paper is to summarize results obtained for Laboratory, Moffett Field, Calif ) In Conference on Decision and the adaptive control of the F-8C aircraft using the so-called MMAC Control, 6th, and Symposium on Adaptive Processes, 14th, Houston, method The discussion includes the selection of the performance Tex, December 10-12, 1975, Proceedings New criteria for both the lateral and the longitudinal dynamics, the design York, Institute of Electrical and Electronics Engineers, Inc , 1975, p of the Kalman filters for different flight conditions, the 'identifica 731 733 5 refs tion' aspects of the design using hypothesis testing ideas, and the All project managers strive for cost and schedule realism The performance of the closed loop adaptive system (Author) 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- A77-12444 Optimal control for the rolling pullout modates program uncertainties/risks inherent to specific work maneuver of a modern fighter aircraft G Satyanarayana, U R elements, and the high-risk work elements are budgeted accordingly Prasad, and I G Sarma (Indian Institute of Science, Bangalore, The purpose of this paper is to propose such a procedure which India) In Conference on Decision and Control, 6th, and Symposium subscribes to a risk analysis approach and satisfies the essential on Adaptive Processes, 14th, Houston, Tex , December 10 12, 1975, elements of the TRACE concept The procedure consists of two Proceedings New York, Institute of Electrical models a cost impact model and a schedule variance model and Electronics Engineers, Inc , 1975, p 443, 444 Applications of the procedure to the NASA/Army Tilt Rotor Optimal control laws for the elevator and ailerons of a mode-n Research Aircraft Project are also presented for illustration fighter aircraft in a rolling pullout maneuver are obtained to (Author) 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 A77-12460 Application of Liapunov model - Tracking roll rate should be about 250 deg/sec, the maximum normal parameter identification for the CH-47 helicopter R L Carroll acceleration should not exceed 5 g's, the minimum time required for (South Carolina, University, Columbia, SC) In Conference on

1 1 A77-12470

Decis'on and Control, 6th, and Symposium on Adaptive Processes, blade-temperature drop as the efficiency criterion for an air-cooled 14th, Houston, Tex, December 10-12, 1975, Proceedings turbine cascade The criterion takes into account the influence of New York, Institute of Electrical and Electronics cooling on the gasdynamic characteristics of the cascade Cascades Engineers, Inc. 1975, p 858-863 7 refs with internal cooling and with film cooling of the blade trailing edge This paper reports results obtained in an evaluation study of are compared, and methods of evaluating analytically the efficiency model-tracking parameter identification for the optimally controlled of such cascades are examined Relations are derived for calculating CH-47 helicopter while in flight The model is made to track some of the efficiency of trailmg-edge cooling with allowance for heat input the helicopter parameters by means of Liapunov-designed adaptive from the butt end of the trailing edge V P algorithm The topics investigated include the accuracy of identification of the time-varying vehicle and the effect of controller feedback A77-12504 Off-design regimes of asymmetric nozzles with upon the performance of the identifier (Author) 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 A77-12470 New orientations of intergovernmental organi- The flow in plane asymmetric nozzles of different geometry is zations of civil aviation (Nouvelles orientations des organismes analyzed for the case of a variable supersonic velocity at the nozzle intergouvernementaux d'aviation civile) M G Folliot (Paris II, inlet The thrust characteristics of nozzles of fixed geometry and of Universite, Paris, France) Revue Franpaise de Droit Aerien, vol 30, optimal nozzles of identical length are compared for a specific inlet July-Sept 1976, p 313-321 13 refs In French Mach number The influence of external pressure on the force Political, economic, and legal changes in international civil characteristics of a nozzle is demonstrated V P 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 A77-12509 Thermal analysis of flight vehicle compart- examined in its two aspects of cooperation and competition The ment structure N M Krutova, G B Petrazhitskn, and A M Pylaev attitudes of individual states to such questions as legal organization, (Aviatsionnaia Tekhnika, vol 19, no 1, 1976, p 55-60) Sower and fares are discussed B J 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- A77-12472 Responsibilities and assurances with regard to dependent particular solutions to each problem of the system and to cargo transport - Air transport law (Responsabilites et assurances en subsequent treatment of algebraic equations or linear systems As an matiere de transports de marchandises - Droit applicable speciale- example, the method is applied to the analysis of a steady periodic rnent en matiere de transport aerien) R R Nys (Bruxelles, mode, and also of a general regular mode of the first kind, for the Universite Libre, Sabena S A , Brussels, Belgium) Revue Franfaise de case where N subsystems with strong thermal couplings interact with Droit Aerien, vol 30, July-Sept 1976, p 329-344 In French each other V P 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, A77-12511 Experimental study of combustion time in and the protocol of Guatemala of 1971 B J 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 A77-12502 Equation solution accuracy in calculating jet The burning process in afterburners of gas turbine engines takes engine characteristics A M Akhmedzianov, S Kh Aksel'rod, and place in mixtures diluted by combustion products The combustion Kh S Gumerov (Aviatsionnaia Tekhnika, vol 19, no 1, 1976, p period in turbulent flows in such mixtures is studied experimentally, 5-10) Soviet Aeronautics, vol 19, no 1, 1976, p 1 5 5 refs showing that the combustion products affect appreciably the Translation combustion period The empirical relationships obtained are inter- The calculation of engine characteristics is conventionally preted in terms of the postulates of a 'surface' model of turbulent reduced to ensuring an accurate selection of the position of the combustion V P 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 A77-12513 Selection of compressor pressure ratio of small engine It is shown that to achieve convergence of the solution to this GTE installed in bypass turbojet engine fan duct B D Fishbein system of equations by computer-aided selection (at a prescribed (Aviatsionnaia Tekhnika, vol 19, no 1, 1976, p 78-85) Soviet accuracy of such output parameters as thrust and fuel consumption), Aeronautics, vol 19, no 1,1976, p 58-62 9 refs Translation a specific relation must be used to determine the error in the The problem of determining the pressure ratio that is optimal selection conditions This relation must be precisely satisfied in the with respect to thrust for the compressor for a small-scale gas-turbine computer-aided determination of the turbojet engine characteristics engine in the bypass dust is analyzed The compressor pressure ratio VP 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 A77-12503 Air-cooled turbine cascade effectiveness criterion 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 A77-12515 Penetration and mixing of liquid injected into It is proposed to use a parameter that indicates the possible supersonic transverse gas stream Z G Shaikhutdinov and V M relative increase in kinetic energy behind the blading caused by a 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 recuperative (fixed) heat exchanger which uses heat pipes to offset Translation the intrinsic drawbacks of recuperative heat exchangers, such as a Photographic methods do not yield correct quantitative relation- low recovery factor and high hydraulic pressure losses along the hot ships in studies of secondary flows propagating in a cross-wind The gas duct V P '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 A77-12551 Computational methods and problems in aero- for water jet< injected at pressures of 4 to 80 bars into gas flow of nautical fluid dynamics Edited by B L Hewitt (British Aircraft Mach number 2 Sand a temperature of 500 K V P Corp, Ltd, Weybridge, Surrey, England), C R Illmgworth (Manchester, Victoria University, Manchester, England), R C Lock A77-12517 Heat transfer in tube entrance segment with (Royal Aircraft Establishment, Farnborough, Hants , England), K W initial flow swirl and transverse injection V K Shchukin, A A Mangier (Southampton, University, Southampton, England), J H Khalatov, and A V Kozhevmkov (Aviatsionnaia Tekhmka, vol 19, McDonnell (British Aircraft Corp, Ltd, Weybridge, Surrey, no 1,l976,p 115-121 I Soviet Aeronautics, vol 19, no 1,1976,p England), C Richards (Institute of Mathematics and its Applications, 86-90 8 refs Translation Southend-on-Sea, Essex, England), and F Walkden (Salford, Uni- versity, Salford, Lanes , England) London and New York, Academic Press, 1976 536 p $2975 A77-12520 Study of flow swirl influence on axiradial The papers collected provide a review of recent developments in diffuser effectiveness I G Gogolev, A M Drokonov, and V M numerical solution techniques for aeronautical flows Some papers Sivaev (Aviatsionnaia Tekhmka, vol 19, no 1, 1976, p 132 135 ) review basic techniques as well, while others present new concepts Soviet Aeronautics, vol 19, no 1,1976, p 102105 Translation *or specific problems Topics covered include methods for elliptic The economic efficiency gas turbine units can be improved by problems in external aerodynamics, compressible subcritical flow using an exit cone that will operate efficiently over a range of turbine through axially symmetric sharp-lipped orifices and nozzles, finite modes If, however, the mode of operation of the preceeding stage is element and difference methods for cascades, problems of unsteady changed, the flow conditions at the diffusor inlet, in particular, the flow past aircraft, an extended integral equation method for the flow direction, will also change The wind-tunnel study described was unsteady transonic flow past a two dimensional airfoil, relaxation aimed at studying the influence of swirl on the economic efficiency near a sonic line, steady supersonic flowfields with embedded of mixed-flow diffusor with an expansion ratio of 1 8 The subsonic regions, and numerical solution of turbulent swirling flows diagrammed results of the study are discussed V P PTH

A77-12521 Determination of magnitudes of the parameters characterizing ducted airscoop operation downstream B L Zel'dovich, L M Kotliar, and E D Nesterov (Aviatsionnaia A77-12552 Practical requirements in industry H Hitch- Tekhmka, vol 19, no 1,1976, p 136-140 ) Soviet Aeronautics, vol IB'itish Aircraft Corp, Ltd, Weybridge, Surrey, England) In 19, no 1,1976, p 106-110 8 refs Translation Computational methods and problems in aeronautical fluid dynam The impingement of a nozzle jet against the endplate of an ics London and New York, Academic Press 1976, p 1-14 6 refs external target type thrust reverser is analyzed with the framework of the theory of ideal fluid jets Specifically, the two-dimensional The present procedure of potential flow solutions and general problems of the impingement of an ideal imponderable jet expelled boundary layer calculations for aircraft aerodynamic calculations is a from a semi-infinite nozzle with straight parallel walls onto two makeshift procedure that contains no real statement about separa plates arranged symmetrically with respect to the channel axis is tion, drag, buffet, or sensitivity of the design to these phenomena, solved by the method of singular points A relationship between the and moreover, the boundary layer calculations are only two geometrical and physical parameters of the problem is established dimensional For modern aircraft, especially those featuring super V P 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 A77-12522 Analytic and experimental study of turbine are produced in the process Wind tunnels for the Reynolds number rotor blade temperature K M Iskakov, A A Panteleev, V A range 20 to 40 million will be required, along with computers of Trushin, and V N Fedorov (Aviatsionnaia Tekhmka, vol 19, no 1, greater performance than present ones PTH 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- A77-12554 Methods for elliptic problems in external tions over the blade contour and over the wall thickness of the blade, aerodynamics R C Lock (Royal Aircraft Establishment, Farn- and the behavior of the cooling-air temperature along the path from borough, Hants, England) In Computational methods and prob the leading edge to the exit slot at the trailing edge The theoretical lems in aeronautical fluid dynamics London and results are found to correlate with thermocouple and pyrometer New York, Academic Press, 1976, p 53-99 24 refs measurements V P 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 A77-12528 Heat-pipe regenerator for gas turbine engine by representing the flow by a distribution of singularities - sources, V K Shchukin, I I Mosm. N V Lokai, and I I Fedorov doublets, or vortices placed either on or inside the body and also, (Aviatsionnaia Tekhmka, vol 19, no 1, 1976, p 172-175 ) Sower for lifting systems, on the vortex wake behind it Considerable Aeronautics, vol 19, no 1,1976, p 140-143 Translation attention is given to the panel method for incompressible flows For The principles of operation of gas-turbine-engine regenerator of two-dimensional compressible flow, a conformal mapping technique a fundamentally new design are discussed The device is essentially a with finite-difference approximation is described PTH

13 A77-12555

A77-12555 Compressible subcritical flow through axial I y A77-12559 Free vortex sheets. K W Mangier (South- symmetric sharp-lipped orifices and nozzles G M Alder (Edinburgh, ampton, University, Southampton, England) In Computational University, Edinburgh, Scotland) In Computational methods and methods and problems in aeronautical fluid dynamics problems in aeronautical fluid dynamics London 12551 02-02) London and New York, Academic Press, 1976, p and New York, Academic Press, 1976, p 100-116 16 refs 198-213 18 refs The paper describes a finite difference method for the solution The paper is concerned with the analysis of the shape and of irrotational axially symmetric subcritical flows of an ideal gas strength of the vortex sheet which is shed from the trailing edge of a through conical nozzles Transformation to hodograph coordinates slender delta wing or from a lifting wing at incidence For the delta maps the whole flowfield into a rectangle and allows a rectangular wing, the pressure condition on the vortex sheet is nonlinear, and the finite difference mesh to be used The error in the solution may be problem is essentially two-dimensional. An iterative procedure for estimated by considering different mesh node densities Typical the core of the vortex sheet is described For a vortex sheet behind a results for both axially symmetric and two-dimensional flows are lifting wing, a doublet source distribution is used, and the panel given P T H 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 A77-12560 Some problems of unsteady flow about air- and problems m aeronautical fluid dynamics craft G J Hancock (Queen Mary College, London, England) In London and New York, Academic Press, 1976, p 117 139 22 refs Computational methods and problems in aeronautical fluid dynam- The paper discusses the basic mathematical model for the flow ics London and New York, Academic Press, in turbomachmes as developed by Wu for a single cascade The 1976, p 214241 15 refs discussion concentrates on the two main methods for solving the The paper discusses some methods used to study the problem of governing equations, the method of streamline curvature and the aircraft wings in unsteady motion In particular, some of the through-flow analysis involving finite differences, for calculating the extensions of the Smith approach to unsteady problems are flow on a mean blade-like surface between two blades The described Some problems associated with the use of vortex lattice relationship between the two methods is discussed together with methods for calculating steady and unsteady load characteristics on their limitation on Mach number Some areas where the techniques finite wings are also investigated P T H 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

A77-12561 Transonic flows M G Hall (Royal Aircraft Establishment, Farnborough, Hants, England) In Computational A77-12557 Finite element and difference methods for methods and problems in aeronautical fluid dynamics cascades M J O'Carroll and L A Morgan (Lanchester Polytechnic, London and New York, Academic Press, 1976, p Coventry, England) In Computational methods and problems in 242269 26 refs aeronautical fluid dynamics London and New The paper outlines some of the recent approaches to the York, Academic Press, 1976, p 140-157 14 refs problem of mixed flow calculations, giving attention to integral The paper is concerned with finding rapid iterative techniques equation methods, the method of integral relaxations, and finite for linearized flow problems on skew nets as arise in the numerical difference methods Closer attention is then given to the relaxation solution of the three dimensional steady, mviscid, incompressible type of finite difference method, which is illustrated by an outline of blade-to-blade cascade flow Comparisons are made between finite the solution of the transonic small perturbation equation for the element and finite difference techniques, with a test cascade of flow past a two dimensional airfoil Developments and extensions of known exact solution being used to demonstrate the discretization the basic relaxation method are then considered, and shortcomings accuracy of the methods The two methods are compared for block and remaining problems to be worked on are pointed out P T H 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 A77-12562 An extended integral equation method for the results of similar discretization accuracy, but the element method steady transonic flow past a two-dimensional aerofoil D Nixon lends itself more easily to local net refinement P T H (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 A77-12563 Relaxation near a sonic line A Roberts York, Academic Press, 1976, p. 158-197 21 refs. (British Aircraft Corp, Ltd, Weybndge, Surrey, England) In The paper reviews the basic properties of the main types of Computational methods and problems m aeronautical fluid dynam elements used in finite element computations, and then presents ics London and New York, Academic Press, some examples of the use of the finite element technique in basic 1976, p 290-326 fluid dynamics problems The simplest type of problem is one with The paper is concerned with achieving rapid relaxation over the positive definite quadratic forms, illustrated by plane incompressible interfaces between the supersonic and subsonic regions describing the flow in a duct A simple membrane analogy and a more complex complete transonic flow past a subsonic lifting aircraft The physical plate analogy from solid mechanics are developed for an incom- plane is regarded as the near field inside a rectangular working pressible potential flow problem and the problem of Stokes flow. section together with the far field The steady isentropic field PTH 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 analogn k raschetu deformatsii polzuchesti stekloplastikov v nesta- The nonlinear isentropic field equation is solved indirectly with the tsionarnom pole temperatur) lu S Pervushm, V P Pavlov, and V aid of elliptic solvers within iterative loops This gives rapid local V Zamullm (Ufimskn Aviatsionnyi Institut, Ufa, USSR). Problemy convergence where the velocity is near the freestream value A wall Prochnosti, July 1976, p 27-29 In Russian relaxation sequence based on Laplacian field concepts gives rapid convergence when the compressibility effects are small P T H A77-12583 # Effect of structural state on the high- temperature long-term strength of molybdenum (Vliiame struktumogo sostoianna na vysokotemperaturnuiu dlitel'nuiu proch- A77-12564 A transonic hodograph theory for aerofoil nost' mohbdena) N P Drozd, R K. Ivashchenko, G G Maksi- design J W Boerstoel (Nationaal Luchtvaartlaboratormm, movich, lu V Mil'man, N M Sinchenko, and V J Trefilov Amsterdam, Netherlands) In Computational methods and problems (Akaderniia'Nauk Ukramskoi SSR, IPM, Kiev, Akademna Nauk in aeronautical fluid dynamics London and New Ukramskoi SSR, Fiziko-Mekhanicheskii Institut, Lvov, Ukrainian York, Academic Press, 1976, p 327 353 9 refs Research supported SSR) Problemy Prochnosti, July 1976, p. 39-43 26 refs In Russian 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 A77-12630 If Nonlinear analysis of flows generated by the on the approximate solution of Tricomi boundary value problems for impulsive motion of a wedge (Nelmemyi analiz techenna, mitsiirue- the mixed elliptic-hyperbolic hodograph equations, where appioxi- mogo vnezapnym dvizhemem klma) V V Titarenko PMTF • mation is achieved by a linear combination of solutions of the Zhurnal Pnkladnoi Mekhaniki i Tekhmcheskoi Fiziki, May-June hodograph equations Some examples of computed airfoils and their 1976, p 37-47 15 refs In Russian design pressure distributions are shown P T H. 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 A77-12565 Supersonic flows F Walkden (Salford, Univer- in a gas at rest and behind the fronts of weak discontinuity lines, sity, Salford, Lanes, England) In Computational methods and propagating in certain homogeneous flows A boundary value problems in aeronautical fluid dynamics London problem is formulated, whose solution describes, in the first and New York, Academic Press, 1976, p 354382 13 refs Research approximation, flows near points of interaction of fronts The supported by the Science Research Council existence of similarity laws for such flows is demonstrated V P 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 A77-12680 * Two-phase turbine engines D G Elliott (Cali- restricted to body shapes such that the effects of viscosity are fornia Institute of Technology, Jet Propulsion Laboratory, Pasadena, confined to narrow layers lying close to body surfaces In these cases Biphase Engines, Inc , Santa Monica, Call' ) and L G Hays (Biphase good predictions of both surface pressures and flow outside the Engines, Inc, Santa Monica, Calif ) In Intersociety Energy Conver- boundary layers can be obtained by solving equations of motion in sion Engineering Conference, 11th, State Line, Nev, September which the effects of fluid viscosity are neglected Distinctive features 12-17, 1976, Proceedings Volume 1 New York, of numerical methods which have been used successfully to calculate American Institute of Chemical Engineers, 1976, p 222-228 11 refs a variety of steady inviscid supersonic flowfields are then examined Contracts No E(04-3)-1228, No E(04-3)-1207, No E(04-3)-1255 Some numerical results are presented (Author) 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 A77-12566 Applications of linearised supersonic wing and liquid streams which operate separately on a gas turbine and a theory to the calculation of some aircraft interference flows M hydraulic turbine The basic two-phase cycles are examined, taking Purshouse and R K Nangia (British Aircraft Corp , Ltd , Weybndge, into account working fluids, aspects of nozzle expansion, details of Surrey, England) In Computational methods and problems in turbine cycle operation, and the effect of mixture ratio variation aeronautical fluid dynamics London and New Attention is also given to two-phase nozzle efficiency, two-phase York, Academic Press, 1976, p 383-423 25 refs Research sup- turbine operating characteristics and efficiencies, separator turbines, ported by the British Aircraft Corp and impulse turbine experiments GR The Mach box method is used to provide a numerical formulation of linearized supersonic wing theory for calculating some typical aircraft interference flows In this method, the disturbance regions in A77-12778 Survey of hydrogen energy application pro- a wing plane are overlaid by a grid of rectangular constant source jects. R E Billings (Billings Energy Corp, Provo, Utah) In strength Mach boxes, which become square when a coordinate Intersociety Energy Conversion Engineering Conference, 11th, State transformation to the equivalent problem at Mach 1 414 is in- Line, Nev, September 12-17, 1976, Proceedings Volume 1 troduced Flow perturbations produced at a point in the downstream New York, American Institute of Chemical Engineers, zone from a source are calculated by appropriate aerodynamic 1976, p 972-977 17 refs influence coefficient relations In the calculation of an underwing Contemporary U S hydrogen application research projects are flowfield at a typical intake location, the effect of leading edge reviewed Specific emphasis is placed on aircraft, industrial and droop on the intake flowfield is studied Other applications are the domestic applications, electrical generation and storage, vehicles, and calculation of the interference field at a fin location arising from farms Although the study does not attempt to evaluate the technical asymmetric elevon deflection, and the mutual interference field feasibility or status of individual projects, some prognostications are produced by two 65-deg-sweep delta wings P T H 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 A77-12872 Design consideration for the Dameus rotor. R unsteady temperature field (O pnmenenn temperaturno-vremennoi 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 concepts, and hypersonic cruise aircraft, is encompassed in the survey Advances in wind tunnels, materials technology, nondestructive evaluation techniques, crashworthmess, and development of alternative fuels and fuel consumption reduction are also dealt with R D V

16 N77-10007

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 STAR ENTRIES Mechanical Engineering METHODS STUDIES ON SYSTEM IDENTIFICATION FROM TRANSIENT ROTOR TESTS Annual Report. Part 1 N77-10001* National Aeronautics and Space Administration K H Hohenemser D Banenee and S K Yin Jun 1975 Langley Research Center Langley Station Va 125 p refs WINGTIP VORTEX DISSIPATOR FOR AIRCRAFT Patent (Contract NAS2-7613) James C Patterson Jr. inventor (to NASA) Issued 5 Oct 1976 (NASA-CR-137965 AR-2-PM) Avail NTIS 6 p Filed 28 May 1974 Supersedes N74-26456 (12 - 16 HC A06/MF A01 CSCL 01A p 1855) Some of the moie important methods are discussed that (NASA-Case-LAR-11645-1 US-Patent-3 984 070 have been used or proposed for aircraft parameter identification US-Patem-Appl-SN-473973 US-Patent-Class-244-130 The methods are classified into two groups Equation error or US-Patent-Class-244-113) Avail US Patent Office CSCL regression estimates and Bayesian estimates and their derivatives 01A that are based on probabilistic concepts In both of these two A means for attenuating the vortex created at aircraft wmgtips groups the cost function can be optimized either globally over which consists of a retractable planar surface transverse to the the entire time span of the transient or sequentially leading to airstream and attached downstream of the wmgtip which creates the formulation of optimum filters Identifiabihty problems and a positive pressure gradient |ust downstream from the wing is the validation of the estimates are briefly outlined and applications presented The positive pressure forces a break up of the rotational to lifting rotors are discussed Author air flow of the vortex Official Gazette of the U S Patent Office

N77-10006*# Washington Univ St Louis. Mo Dept of N77-10003*# Washington Univ St Louis Mo Dept of Mechanical Engineering Mechanical Engineering ADDITIONAL EXPERIMENTS WITH A FOUR-BLADED ROTOR DYNAMIC STATE AND PARAMETER IDENTIFICA- CYCLIC PITCH STIRRING MODEL ROTOR. PART 2 OF TION. FROM SIMULATED FORWARD FLIGHT TRAN- SECOND YEARLY REPORT SIENTS. PART 1 K H Hohenemsei and S T Crews Jun 1975 70 p K H Hohenemser D Banerjee and S K Yin Jun 1976 (Contract NAS2-7613) 61 p refs (NASA-CR-137966) Avail NTIS HC A04/MF A01 CSCL (Contract IMAS2-7613) 01A (NASA-CR-137963 Rept-3) Avail NTIS HC A04/MF A01 The four bladed pitch stirring rotor model was used in a CSCL 01A rotor dynamic wake survey at zero advance ratio covering 2 deg State and parameter identifications from simulated forward 5 deg and 8 deg collective pitch settings Dynamic wake data flight blade flapping measurements are presented The transients were taken in planes 12 and 20 radii below the rotor disk and were excited by progressing cyclic pitch stirring or by hub stirring are to be compared with analytical wake data with parameters with constant stirring acceleration Rotor dynamic inflow models to be identified from pitch stirring transients The model was of varying degree of sophistication were used from a one parameter modified to perform such transients The instrumentation inflow model (equivalent Lock number) to an eight parameter developed for this purpose is described together with the method inflow model The maximum likelihood method with assumed of data acquisition and with the test procedures The hardware fixed measurement error covariance matrix was applied The rotor and software for several data handling systems are discussed system equations for both fixed hub and tilting hub are given These systems extract from pitch stirring transients the parameters The identified models were verified by comparing true responses of analytical dynamic rotor wake models Author 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 N77-10O07*# Princeton Univ NJ Dept of Aerospace and plus the blade Lock number from the transients Author 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 N77-100O4*# Washington Univ St Louis Mo Dept of Army Mechanical Engmeenng (Contract NAS2-7615) ROTOR DYNAMIC STATE AND PARAMETER IDENTIFICA- (NASA-CR-137967 AMS-1236) Avail NTIS TION FROM SIMULATED FORWARD FLIGHT TRANSIENTS. HC A05/MF A01 CSCL 01A PART 2 Prediction of flap-lag stability using a single bending mode K H Hohenemser and S T Crews Jun 1976 44 p refs for each degree-of-freedom is examined in the case in which (Contract NAS2-7613) the bending modes are assumed to be the same in the flap (NASA-CR-137964 Rept-3) Avail NTIS HC A03/MF A01 and lag directions and are independent of pitch angle and stiffness CSCL 01A distribution It is shown that this model gives results analogous State and parameter identifications based on a form of the to those obtained by Ormiston employing a rigid blade model maximum likelihood method are applied to the problem of with the blade and hub stiffness represented by springs in the extracting linear perturbation models including rotor dynamic limiting cases of the elastic coupling parameter R = 0 and 1 inflow effects from transient blade f.appmg measurements The For intermediate values of R the results are shown to be quite estimation method is first studied in computer simulations and different The mode shape assumptions are shown to result in then applied to cyclic pitch stirring transients generated with a what is referred to as the parallel spring model in contrast to four-bladed rotor model operating in hovering trim conditions Ormiston s model which is referred to as a series spring model The analytical perturbation models extracted from the transient The similarities and differences between these two models are test results are compared with transient and frequency response developed in some details The differences between these two

17 N77-10008

models are examined for various typical rotor blade characteristics E A" Truneva NASA Nov 1976 11 p refs Transl into Other aspects of the sensitivity of this problem are also ENGLISH from Izv Vyssh Ucheb Zaved . Aviats Tekh (USSR). considered Author no 2. Feb, 1976 p 106-110 (Contract NASw-2792) (NASA-TT-F-17283) Avail NTIS HC A02/MF A01 CSCL N77-10O08*# Princeton Univ NJ Dept of Aerospace and 01A Mechanical Sciences The mechanism of vortex separation and displacement of AN EXPERIMENTAL STUDY OF THE NONLINEAR STIFF- the separation point beginning with the development of the NESS OF A ROTOR BLADE UNDERGOING FLAP. LAG AND separation phenomenon is presented The results of this research TWIST DEFORMATIONS Final Technical Report may be valuable for determination of stresses on the wind and E H DowellandJ J Traybar Jan 1975 58 p refs Sponsored investigation of non-stationary aerodynamic characteristics of in part by Army aircraft with delta wings, in the low velocity region corresponding (Contract NAS2-7615) to takeoff and landing Author (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 N77-10013*# Lockheed-Georgia Co , Marietta and bending natural frequencies were measured as a function NEW DEVELOPMENTS IN BLOWN FLAP NOISE TECHNOL- of tip load magnitude and orientation The experimental data OGY are compared with the results of a recently developed nonlinear John S Gibson 1976 12 p refs Presented at the 10th structural theory and agreement is good for deflections that are Congr of ICAS Ottawa 3-8 Oct 1976 small compared to the beam span with systematic deviations (Contract NAS1-13870) for larger deflections These results support the validity and utility (NASA-CR-145086) Avail NTIS HC A02/MF A01 CSCL of the nonlinear structural theory for rotor blade applications 01A Author The noise technology relating to blown-flap systems is reviewed There are three general sources of noise turbomachmery airframe and the interaction noise of the jet blowing on the flaps The latter noise-source area is the most critical N77-10009*# Princeton Univ. NJ Dept of Aerospace and and the mam subject dicussed Characteristics of lower surface Mechanical Sciences blown and upper surface blown systems are described, including AN EXPERIMENTAL STUDY OF THE NONLINEAR STIFF- noise spectra directivity jet velocity characteristics aircraft NESS OF A ROTOR BLADE UNDERGOING FLAP. LAG AND geometric variation effects and aircraft forward speed effects TWIST DEFORMATIONS Noise reduction concepts are described including slowing down E H DowellandJ J Traybar Dec 1975 79 p refs Sponsored the jet flow field by devices and engine cycle modifications, in part by Army structural geometry and shielding modifications, local flow field (Contract NAS2-7615) modifications of the passive and active type, and the absorption (NASA-CR-137969 AMS-1257) Avail NTIS of noise It is concluded that while there has been considerable HC A05/MF A01 CSCL 01A progress in the past several years low noise characteristics in This is an addendum to an experimental study of the large blown flap aircraft must be largely built in by better application deformation of a cantilevered beam under a gravity tip load It of low noise principles during the design Author 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 N77-10014*# 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 N77-10010*# Chrysler Corp New Orleans, La Space Div (Contract NAS2-8651) HIGH SUPERSONIC AERODYNAMIC CHARACTERISTICS (NASA-CR-137888) Avail NTIS HC A05/MF A01 CSCL OF FIVE IRREGULAR PLAWFORM WINGS WITH SYSTEM- 20D ATICALLY VARYING WING FILLET GEOMETRY TESTED IN Finite element three dimensional relaxation methods are used THE NASA/LARC 4-FOOT UPWT (LEG 2) (LA4SA/B) to calculate the development of vortex wakes behind aircraft for Oct 1976 478 p ref a considerable downstream distance The inclusion of a self- (Contract NAS9-13247) induction term in the solution dependent upon local curvature (NASA-CR-147628 DMS-DR-2297) Avail NTIS and vortex core radius permits calculation of finite lifetimes for HC A21/MF A01 CSCL 01A systems for which infinite life would be predicted two di- An experimental and analytical aerodynamic program to mensionally The associated computer program is described develop predesign giJides for irregular planform wings is reported together with single-pair twin-pair and multiple-pair studies The benefits are linearization of subsonic lift curve slope to high carried out using it It is found in single-pair studies, that there angles of attack and avoidance of subsonic pitch instabilities at is a lower limit to the wavelengths at which the Crow-type of high lift by proper tailoring of the planform fillet wing combination instability can occur Below this limit, self-induction effects cause while providing the desired hypersonic trim angle and stability the plane of the disturbance waves to rotate counter to the The two prime areas of concern are to optimize shuttle orbiter vortex direction Self induction in two dimensionally generated landing and entry characteristics Basic longitudinal aerodynamic twin spiral waves causes an increase in axial length which becomes characteristics at high supersonic speeds are developed Author 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 N77-10012*# Transemantics Inc Washington D C span Limited studies of Boeing 747 configurations show correct MECHANISM OF STABILIZATION OF THE 'SEPARATION qualitative response to removal of the outer flap and to gear POINT' OF A VORTEX DURING FLOW OF A STREAM AT deployment as compared with wind tunnel and flight test LOW SUBSONIC VELOCITY OVER A DELTA WING experience Author

18 N77-10027

N77-10017# Office National d Etudes et de Recherches N77-10O24# Air Force Inst of Tech. Wright-Patterson AFB Aerospatiales Pans (France) Ohio School of Engineering STUDY OF THE SUBSONIC FLOW AROUND A SHARP AN INVESTIGATION OF THE EFFECT ON AERODYNAMIC LEADING EDGE FORCES CAUSED BY THE ADDITION OF END PLATES Gerard Laruelle and Paul Levart Assoc Aecon et Astronautique TO HELICOPTER ROTOR BLADES M S Thesis de France 1976 23 p refs In FRENCH. ENGLISH summary Roger J Korenberg Jun 1975 76 p refs Presented at the 12th Ecole Natl Super de Mecan et d'Aerotech / (AD-A023541 GAM/AE/74D-11) Avail NTIS CEAT Colloq Appl Poitiers France. 5-7 Nov 1975 HC A05/MF A01 CSCL 01/1 (AAAF-NT-76-14, ISBN-2-7170-0396-7) Avail NTIS The purpose of this investigation was to determine the effects HC A02/MF A01 CEDOCAR. Paris FF 15 (France and EEC) on lift, drag and thrust produced by a helicopter rotor after FF 19 (others) installing end plates on the blades Fixed wing end plate theory The subsonic flow around a sharp leading edge, resulting was applied in a modified form to rotor blade calculations to from the air intake drag of supersonic aircraft flying at subsonic investigate correlation The results indicate that end plate factors speeds was studied The calculation method used is presented are not satisfactory analytic tools for rotor blade calculations and the simulation of leading edge separation is detailed The End plates do increase the effective rotor radius and increase experimental setup is presented (S5 wind tunnel at Chalais- the lift at a given angle of attack and RPM. however, there are Meudon France) The calculated and measured values were heavy penalties in power required GRA compared and found to be satisfactory An adaptation of the computer program for potential flow by finite differences was attempted ESA N77 10026$ Naval Surface Weapons Center White Oak Md NORMAL IMPINGEMENT OF A SUPERSONIC JET ON A N77-10O19# Aix-Marseilles Umv (France) Inst de Mecamque PLANE A BASIC STUDY OF SHOCK-INTERFERENCE des Fluides HEATING EXPERIMENTAL STUDY OF THE AERODYNAMICS OF A Kuei-Yuan Chien 20 Dec 1975 60 p refs HELICOPTER ROTOR IN TRANSLATIONAL FLIGHT TWO (AD-A024511 NSWC/WOL/TR-75-195) Avail NTIS DIMENSIONAL SIMULATION OF THE EFFECTS DUE TO HC A04/MF A01 CSCL 20/4 CYCLIC VARIATIONS OF THE VELOCITY VECTOR [ETUDE The problem of a balanced, planar or axisymmetnc. supersonic EXPERIMENTALE RELATIVE A L'AERODYNAMIQUE D'UN jet impinging normally on a flat surface has been considered ROTOR D'HELICOPTERE EN VOL DE TRANSLATION based on an mviscid theory The object of the study was to SIMULATION EN ECOULEMENT PLAN DES EFFETS DUS provide a rational model for calculating shock-interference heating AUX VARIATIONS CYCLIQUES DU VECTEUR VITESSE] as produced by a type IV shock-interaction pattern The unwanted J Rebont, C Maresca, A Guillermmet, and D Favier Pans singularity at a low supersonic Mach number peculiar to scheme Assoc Aeron et Astronautique de France 1976 37 p refs I of the one-strip formulation of the method of integral relations In FRENCH Presented at the 12th Ecole Natl Super de Mecan as observed by South and by Gummer and Hunt, was successfully et d'Aerotech/CEAT Colloq dAerodyn Appl Poitiers. France removed by the application of the scheme III of the one-strip 5-7 Nov 1975 formulation of the method of integral relations The resulting (AAAF-NT-76-20 ISBN-2-7170-0398-3) Avail NTIS simultaneous nonlinear algebraic equations were easily solved HC A03/MF A01 CEDOCAR Pans FF 25 (France and EEC) iteratively by the Newton-Raphson method Sensitivity of the FF 29 (others) solution on various approximating functions employed was Aerodynamic characteristics of a helicopter wing harmonic extensively investigated Unlike the findings reported by Gummer oscillations of which the vector is parallel to the mam flow and Hunt solutions that satisfy all well-posed boundary conditions were studied in a subsonic wind tunnel NACA profile 0012 can be obtained by the one-strip formulation Results indicate (1 = 0495 m c = 03 m) was used angle of attack between -20 that, for the planar case a rational engineering solution for the and 20 deg and Reynolds number between 60 000 and 400.000 stagnation-point velocity gradient (and hence the peak heat- It is shown that the instability effects remain small with small transfer rate) has been obtained For the axisymmetnc case, angle of attack and with oscillation frequencies below 0 26 ESA however solutions appear to be not quite converging A two-strip formulation based on the method of integral relations is also included Author (GRA)

N77-10023# 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 N77-10027# McDonnell Aircraft Co St Louis Mo 1975 PERFORMANCE OF STEADY AND INTERMITTENT BLOW- E M Kraft AEDC Apr 1976 84 p refs ING JET FLAPS AND SPANWISE UPPER SURFACE SLOTS (AD-A023493 ARO-PWT-TR-75-162 AEDC-TR-76-43) Avail Final Report. Apr 1973 - Nov 1975 NTIS HC A05/MF A01 CSCL 20/4 W L Ely and F C Berner Nov 1975 514 p refs The wind tunnel boundary interference at transonic speeds (Contract F33615-73-C-3056 AF Proj 1476) on a thin airfoil in a two-dimensional perforated-wall wind tunnel (AD-A024364 AFFDL-TR-75-128) Avail NTIS was determined The interference was found by applying an HC A22/MF A01 CSCL 20/4 integral equation method to the nonlinear transonic small A wind tunnel test was conducted in the NASA Ames 14 foot disturbance equation including embedded supersonic regions wind tunnel to determine the performance of steady and pulsed with shock waves The kernels of the ensuing integral equation blown jet flaps and constant percent chord spanwise upper surface were replaced by senes approximations and the integrals were slots, and to provide wing load and tail power data for a proposed evaluated in closed form The iterative technique used to calculate Air Force COMMA (Composite Maneuver Augmentation) RPV the interference from the integral equation method is shown to flight test program The tests were performed on a 72 1% scale converge rapidly and the computing time for the integral equation semi-span model of the proposed vehicle with a wing leading method is typically an order of magnitude less than present edge sweep of 45 deg over a Mach number range of 0 4 to numerical methods As a special case the integral equation method 1 1 The Reynolds number was approximately 4 million per foot for a thin airfoil in free air was also examined It was found and the angle of attack range was -5 deg to -25 deg Full and that the introduction of a novel influence function yields, for the partial span jet flaps jet flap angles of 30 deg 60 deg and first time, a self-contained integral equation for a lifting airfoil 80 deg 40% and 70% constant chord slots and horizontal tail In addition a systematic study of the classical assumption used deflections of 4-2 deg 0 deg -2 deg -4 deg and -6 deg were to simplify the integral equation shows that the integral method tested over a blowing momentum coefficient range of 0 to 0 018 can provide solutions m good agreement with results from the Balance forces wing upper and lower surface static pressures numerical methods GRA wing root bending moment wing tip accelerometer and flow

19 N77-10028

visualization data were obtained The results in general indicated support and maintenance for the LH2 fueled aircraft were analyzed that slot blowing was ineffective, jet flaps provided lift augmenta- An estimate was made of capital and operating costs which tion at all angles of attack tested and drag reduction at high lift might be expected for the facility Recommendations were made conditions and pulsed blowing provided minor benefits over steady for design modifications to the reference aircraft, reflecting results blowing Trimmed jet flap data indicates a Mach dependence of the analysis of airport fuel handling requirements, and for a on jet flap performance and that jet flaps provide a perform- program of additional technology development for air terminal ance advantage only at high lifts Author (GRA) related items Author

N77-10028# Texas Umv Austin Dept of Aerospace N77-10033*# Boeing Commercial Airplane Co Seattle Wash Engineering and Engineering Mechanics Dept of Preliminary Design ,, THE DEVELOPMENT OF A COMPUTER AIDED AIRFOIL AN EXPLORATORY STUDY TO DETERMINE THE INTE- DESIGN PROCEDURE INCLUDING PRELIMINARY WIND GRATED TECHNOLOGICAL AIR TRANSPORTATION TUNNEL EXPERIMENTS ON A LOW REYNOLDS NUMBER SYSTEM GROUND REQUIREMENTS OF LIQUID- HIGH LIFT SECTION. VOLUME 1 Final Report. 1 Dec HYDROGEN-FUELED SUBSONIC. LONG-HAUL CIVIL AIR 1970 - 30 Nov 1975 TRANSPORTS Final Report Jimmy Charles Narramore, Ralph Dean Orlander and Ronald Washington NASA Sep 1976 176 p refs Prepared in Oran Stearman Jan 1976 153 p refs cooperation with United Airlines and Air Products and Chemicals (Grant AF-AFOSR-1998-71 AF Proj 9782) Inc (AD-A024361 AFOSR-76-0536TR) Avail NTIS (Contract NAS1-14159) HC A08/MF A01 CSCL 20/4 (NASA-CR-2699 D6-75775) Avail NTIS HC A09/MF A01 An investigation on the state of the art of subsonic airfoil CSCL 01 C section design including a review of the historical development A baseline air terminal concept was developed which of airfoil design methodology was carried out A computer permitted airlines and the airport to operate JP- or LH2-fueled aided airfoil design procedure employing current technology was aircraft at common terminal gates The concept included developed and utilized to design a low-Reynolds number high-lift installation of a hydrogen liquefaction and storage facility on airfoil section Preliminary wind tunnel studies were carried out airport property as well as the fuel distribution system The on this high-lift section and the influence of flow disturbances capital investment and hydrogen-related operating costs to the on its performances evaluated This study represents the first airlines were estimated Author phase m determming how changes in airfoil design parameters influence the dynamical properties of the airfoil Author (GRA)

N77-10O34# Simat, Helliesen and Eichner Inc Washing^ DC AN ANALYSIS OF THE INTRASTATE AIR CARRIER N77-10029# Advanced Technology Center Inc Dallas, Tex REGULATORY FORUM VOLUME 1 SUMMARY REPORT TEST VERIFICATION OF A TRANSONIC AIRFOIL DESIGN Jan 1976 49 p EMPLOYING ACTIVE DIFFUSION CONTROL Final Report. (Contract DOT-OST-60078) 13 Jun 1974 - 14 Jun 1975 (AD-A023761) Avail NTIS HC A03/MF A01 CSCL 05/3 C H Haight and J G Spangler 1975 90 p refs Although the regulatory environments in Texas and California (Contract N62269-74-C-0517) differ substantially, each has resulted in the establishment of (AD-A024297 ATC-B-94300/5CR-34) Avail NTIS carriers which are specialized in their desire and ability to serve HC A05/MF A01 CSCL 20/4 medium- and high-density short-haul markets Further each has Experimental results are presented that show active diffusion allowed these carriers to pursue a marketing and operational control, with its integrated contouring/blowing charactenstics philosophy which has enabled them to achieve improved to be a viable concept for relaxing transonic airfoil design productivity and as a result charge lower fares CAB regulation constraints The antiseparation tailored contour (ATC) is the basic on the other hand has produced both tight control of entry and device for active diffusion control A modified 12% thick C-141 tight rate regulation, and has required equal fares for markets section with a trailing edge upper surface ATC designated as of the same distance Consequently, there has been no develop- the TEATC12 airfoil was selected as the proof-of-concept ment of specialized interstate carriers serving short-haul routes configuration It incorporates the mam features of active diffusion of density comparable to those served by the mtrastate carriers control while providing a reliable baseline for comparison The Application of a two-tier' pricing system, along with improved transonic BLC/diffusion process was modeled in an axisymmetric frequency, would be expected to double the traffic volume in diffuser facility Blowing predictions for the ATC geometry were these markets generating more than 18 million additional air substantiated and interactions between the jet and the mainstream passengers each year GRA 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

N77-10035# Simat Helliesen and Eichner Inc Washington. DC AN ANALYSIS OF THE INTRASTATE AIR CARRIER N77-10032*# Lockheed-California Co, Burbank REGULATORY FORUM VOLUME 2 TECHNICAL REPORT LH2 AIRPORT REQUIREMENTS STUDY Final Report, Sep Final Report 1975 - Feb 1976 L J Eichner N S Simat K T Carlson, and R A Sunshine G D Brewer ed Oct 1976 202 p refs Jan 1976 420 p refs (Contract NAS1-14137) (Contract DOT-OS-60078) (NASA-CR-2700 LR-27581) Avail NTIS HC A10/MF A01 (AD-A023762) Avail NTIS HC A18/MF A01 CSCL 05/3 CSCL 21 D Intrastate air carriers in California and Texas have succeeded A preliminary assessment of the facilities and equipment in earning profits and providing a high level of service while which will be required at a representative airport is provided so keeping fares well below those charged by interstate air carriers liquid hydrogen LH2 can be used as fuel in long range trans- The three carriers analyzed in this report are not subject to port aircraft m 1995-2000 A complete facility was conceptually regulation by the Civil Aeronautics Board (CAB) which controls designed sized to meet the projected air traffic requirement both rates and routes of the trunk and local interstate air carriers The facility includes the liquefaction plant, LH2 storage capability, The different regulatory environments impact on the performance and LH2 fuel handling system The requirements for ground of the aviation system Sixty interstate markets are identified

20 N77-10048

with potential for profitable operation at high levels of service studies determined the best area of applicability to be a at lower air fares and regulatory requirements to allow such commercial passenger transport mission The critical parameter service to develop can be identified Author (GRA) 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 N77-10036# California Univ Los Angeles Graduate School and 0 95 The crossover Mach number for the oblique wing of Management concept was found to be Mach 091 for takeoff gross weight THE HELICOPTER AIR SERVICE PASSENGER PROGRAM and direct operating cost Benefits include reduced takeoff A RETROSPECT Research Report. 1974 • 1975 distance installed thrust and mission block fuel and improved Tim Yeomans and Frank G Mittelbach Sep 1975 60 p refs community noise characteristics The variable geometry feature (PB-254830/3. CAL-URT-7(7)T-35 UMTA-CA-11-0009-75-4 enables the final configuration to increase range by 10% at Occasional-Paper-10) Avail NTIS HC A04/MF A01 CSCL Mach 0712 and to increase endurance by as much as 44% 01B Author 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 N77-10046*# Lockheed-Georgia Co Marietta directed to basic helicopter characteristics and capabilities the AN ANALYTICAL STUDY FOR SUBSONIC OBLIQUE WING rationale behind the helicopter experiment the effects of a federal TRANSPORT CONCEPT subsidy granted to the industry and an analysis of four certified Edward S Bradley Jul 1976 37 p refs helicopter carrier operations GRA (Contract NAS2-8686) (NASA-CR-137897 LG76ER0156) Avail NTIS HC A03/MF A01 CSCL01C For abstract see N77-10045 N77-10044*# United Technologies Research Center East Hartford Conn INVESTIGATION OF A BEARINGLESS HELICOPTER ROTOR CONCEPT HAVING A COMPOSITE PRIMARY STRUCTURE Final Report N77-10047*# Lockheed Missiles and Space Co, Sunnyvale Richard L Bielawa Marvin C Cheney. Jr and Richard C Novak Calif Research and Development Div Oct 1976 253 p refs CIVIL USES OF REMOTELY PILOTED AIRCRAFT Final (Contract NAS1-10960, DA Proj 1 F1-61102-AH-45) Report (NASA-CR-2637. R76-911209-47) Avail NTIS Jon R Aderhold G Gordon and George W Scott Jul 1976 HC A12/MF A01 CSCL QIC 326 p refs Experimental and analytical investigations were conducted (Contract NAS2-8935) to evaluate a beanngless helicopter rotor concept (CBR) made (NASA-CR-137894. LMSC-D057323) Avail NTIS possible through the use of the specialized nonisotropic properties HC A15/MF A01 CSCL 01C of composite materials The investigation was focused on four The technology effort is identified and assessed that is principal areas which were expected to answer .mportant questions required to bring the civil uses of RPVs to fruition and to determine regarding the feasibility of this concept First an examination of whether or not the potential market is real and economically material properties was made to establish moduli ultimate practical, the technologies are within reach, the operational strength, and fatigue characteristics of unidirectional graphite/ problems are manageable, and the benefits are worth the cost epoxy. the composite material selected for this application The To do so the economic, technical and environmental implications results confirmed the high bending modulus and strengths and are examined The time frame is 1980-85 Representative uses low shear modulus expected of this material and demonstrated are selected detailed functional and performance requirements fatigue properties in torsion which make this material ideally are derived for RPV systems and conceptual system designs suited for the CBR application Second a dynamically scaled are devised Total system cost comparisons are made with model was fabricated and tested in the low speed wind tunnel non-RPV alternatives The potential market demand for RPV to explore the aeroelastic characteristics of the CBR and to systems is estimated Environmental and safety requirements are explore various concepts relative to the method of blade pitch examined and legal and regulatory concerns are identified A control Two basic control configurations were tested one in potential demand for 2000-11 000 RPV systems is estimated which pitch flap coupling could occur and another which eliminated Typical cost savings of 25-35% compared to non-RPV alternatives all coupling It was found that both systems could be operated are determined There appear to be no environmental problems successfully at simulated speeds of 180 knots however the and the safety issue appears manageable Author 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 N77-10048*# 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 N77-10045*# Lockheed-Georgia Co Marietta (Contract NAS2-8935) AN ANALYTICAL STUDY FOR SUBSONIC OBLIQUE WING (NASA-CR-137895. LMSC-D057322) Avail NTIS TRANSPORT CONCEPT HC A03/MF A01 CSCL01C Edward S Bradley J Honrath K H Tomlm G Swift P Shumpert. The economic technical and environmental implications of and W Warnock Jul 1976 219 p refs remotely piloted vehicles (RVP) are examined The time frame (Contract NAS2-8686) is 1980-85 Representative uses are selected, detailed functional (NASA-CR-137896 LG76ER0156) Avail NTIS and performance requirements are derived for RPV systems and HC A10/MF A01 CSCL 01C conceptual system designs are devised Total system cost The oblique wing concept has been investigated for subsonic comparisons are made with non-RPV alternatives The potential transport application for a cruise Mach number of 095 Three market demand for RPV systems is estimated Environmental different mission applications were considered and the concept and safety requirements are examined and legal and regulatory analyzed against the selected mission requirements Configuration concerns are identified A potential demand for 2000-11,000

21 N77-10049

RVP systems is estimated Typical cost savings of 25 to 35% N77-10052# European Space Agency Pans (France) compared to non-RPV alternatives are determined There appear THREE-COMPONENT MEASUREMENTS ON A MODEL OF to be no environmental problems, and the safety issue appears A LIGHT STOL AIRCRAFT WITH CHORDWISE BLOWING manageable Author 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 N77-10049*# Kanner (Leo) Associates Redwood City Calif (ESA-TT-299 DLR-FB-75-74) Avail NTIS HC A02/MF A01 CRITICAL ANALYSIS OF COMPARISONS BETWEEN Investigations on a STOL aircraft with internally blown flaps FLIGHT TEST RESULTS AND WIND TUNNEL TEST are described To avoid separation on the wing slots were PREDICTIONS IN SUBSONIC AND SUPERSONIC TRANS- located behind the nose flap and in front of the trailing edge PORT AIRCRAFT flap The investigations were designed to examine maximum lift C Pelagatti, J C Pilon and J Bardaud Washington NASA and lift/drag ratio In addition the effectiveness of the aileron Aug 1976 56 p refs Transl into ENGLISH of French report and the horizontal tail were investigated Author (ESA) 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 N77-10053# United Technologies Corp Windsor Locks, Conn HC A04/MF A01 CSCL01C V/STOL ROTARY 'PROPULSION SYSTEMS NOISE In relating test results obtained from wind tunnels to results PREDICTION AND REDUCTION VOLUME 1 IDENTIFICA- from actual flight tests corrections must be made to allow for TION OF SOURCES, NOISE GENERATING MECHANISMS, aeroelastic effects and the effect of Reynolds' number differences NOISE REDUCTION MECHANISMS, AND PREDICTION Using data from Concorde and airbus tests, an attempt is made METHODOLOGY Final Report to define what degree of accuracy may be expected from B Maghozzi May 1976 143 p refs aerodynamic coefficients derived from wind tunnel measure- (Contract DOT-FA74WA-3477) ments Author (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 N77-10050# Poitiers Univ (France) rotors lift fans gearboxes and drive engines Noise sources for BUFFETING PROBLEMS [PROBLEMES DE BUFFETING] each of these prop'ulsors gearboxes and drive engines are J Tensi and P Perner (Avions Marcel Dassault-Breguet Aviation) identified and rank ordered The noise generating mechanisms Pans Assoc Aeron et Astronautique de France 1976 48 p for each of the propulsor noise sources identified are defined refs In FRENCH Presented at the 12th Ecole Natl Super de and systematically catalogued Three approaches to reduction of Mecan et d Aerotech / CEAT Colloq d'Aerodyn Appl Poitiers propulsor noise are discussed changes m physical geometry, . France. 5-7 Nov 1975 changes in design operating conditions and the use of acoustic (AAAF-NT-76-7. ISBN-2-7170-0385-1) Avail NTIS treatments Computerized and graphical procedures based on HC A03/MF A01. CEDOCAR. Paris FF 25 (France and EEC) methodology from the open literature are presented for predicting FF 29 (others) aerodynamic performance of and noise from the V/STOL Wind tunnel studies of buffeting of two types of profiles in propulsors The developed methodo'ogy allows the user to estimate incompressible flow are presented leading edge separation NACA the achieved noise reduction as well as the incurred performance 65 (sub 1)012 and trailing edge separation NACA 65 (sub 3) penalties of noise reduction design features and noise attenuation 618 The tests were made in the wind tunnel T sub 5 P sub 0 devices such as partly sonic inlets and acoustic treatment of the return (Prandtl) and guide vane type at 40 m/s Results Much of the, noise generating mechanism substantiation data of the two tests are detailed and compared It is shown that and prediction methodology are based on static operation Forward with the equipment used it is possible to determine the angle flight effects have recently been recognized as having a significant of attack and Reynolds number at which flow separation occurs effect on the noise sources Forward flight effect corrections are Also the separation progress with increasing angle of attack included in the methodology Author can be followed ESA

N77-10054# United Technologies Corp Windsor Locks Conn N77-10051# Conservatoire National des Arts et Metiers, Pans V/STOL ROTARY PROPULSION SYSTEMS NOISE (France) PREDICTION AND REDUCTION VOLUME 2 GRAPHICAL NEW BUFFETING ACQUISITION METHODS [NOUVELLES PREDICTION METHODS Final Report METHODES D'ACOUISITION DE BUFFETING] B Maghozzi May 1976 304 p refs 3 Vol E Gaignebet and G Heckmann (Avions Marcel Dassault-Breguet (Contract DOT-FA74WA-3477) Aviation) Assoc Aeron et Astronautique de France 1976 (AD-A027390/4 FAA-RD-76-49-Vol-2) Avail NTIS 44 p refs In FRENCH Presented at the 12th Ecole Natl HC A13/MF A01 CSCL 01/3 Super de Mecan et d'Aerotech / CEAT Colloq d Aerodyn Appl Graphical procedures for estimating noise and performance Poitiers, France. 5-7 Nov 1975 of free air propellers variable pitch fans with inlet guide vanes (AAAF-NT-76-8 ISBN-2-7170-0386-X) Avail NTIS variable pitch fans with outlet guide vanes, fixed pitch fans, HC A03/MF A01, CEDOCAR. Pans FF 25 (France and EEC) helicopter rotors, tilt rotors and lift fans are presented Noise FF 29 (others) prediction methods for drive engines gearboxes jets with and A new method for military aircraft buffeting data acquisi- without bypass flow as well as noise reduction and performance tion using wind tunnel tests is presented The data analysis losses for partly sonic inlets and duct linings are also presented principle is discussed and inertia measurements are detailed The procedures are extensive and applicable to a wide variety The characteristics of the aircraft model are given and the data of V/STOL propulsor systems including present and future acquisition and data processing aspects are dealt with in detail V/STOL vehicles The methods have been validated with available It is concluded that with the hypothesis of small displacement data wherever possible However high quality data for isolated the use of six accelerometers is justified any two of the three propulsors which are free from contamination by other sources accelerometers related to one direction produce comparable and ground reflections are somewhat limited particularly for results ESA forward flight conditions Author

22 N77-10062

N77-10055# United Technologies Corp Windsor Locks. Conn N77-10059*# National Aeronautics and Space Administration V/STOL ROTARY PROPULSION SYSTEMS NOISE Lewis Research Center, Cleveland, Ohio PREDICTION AND REDUCTION VOLUME 3 COMPUTER SUPERSONIC VARIABLE-CYCLE ENGINES PROGRAM USERS MANUAL Final Report E A Willis and A. 0 Welliver (Boeing Aerospace Co, Seattle. B Magliozzi May 1976 302 p refs Wash) 1976 11 p refs Presented at the 12th Propulsion (Contract DOT-FA74WA-3477) Conf Palo Alto. Calif. 26-29 Jul 1976. cosponsored by AIAA (AD-A027363/1. FAA-RD-76-49-Vol-3) Avail NTIS and SAE / HC A14/MF A01 CSCL 01/3 (NASA-TM-X-73524) Avail NTFS HC A02/MF A01 CSCl A computer program is presented which allows a user to 21E make performance and far field acoustic noise predictions for The evolution and current status of selected recent variable free air propellers, variable pitch fans with inlet guide vanes cycle engine (VCE) studies are reviewed, and how the results variable pitch fans with outlet guide vanes, fixed pitch fans, were influenced by airplane requirements is described Promising helicopter rotors, tilt rotors fixed pitch lift vanes with remote VCE concepts are described, their designs are simplified and integral, and tip turbine drives, and variable pitch lift fans with the potential benefits in terms of aircraft performance are identified remote and integral drives Noise prediction methodology for This includes range noise, emissions and the time and effort it drive engines, single stream and coaxial jets and gearboxes is may require to ensure technical readiness of sufficient depth to also included as well as noise reduction and performance losses satisfy reasonable economic performance and environmental of partly sonic inlets and duct acoustic treatment A description constraints A brief overview of closely related, ongoing technology of the program, detailed instructions for its use, required inputs, programs in acoustics and exhaust emissions is also presented and sample cases are presented Author 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 N77-10056*# Ellco Engineering, Inc . Compton Calif TRANSONIC PERFORMANCE OF MACH 265 AUXILIARY FLOW AXISYMMETRIC INLET Final Report N77-10060*# Notre Dame Umv. Ind Dept of Electrical Don M Santman Oct 1976 63 p refs Engineering (Contract NAS2-8679) COMPUTATIONAL ALTERNATIVES TO OBTAIN TIME (NASA-CR-2747) Avail NTIS HC A04/MF A01 CSCL 21E OPTIMAL JET ENGINE CONTROL M S Thesis Transonic experimental performance for a large scale R J Basso and R J Leake Oct 1976 73 p refs Mach 2 65 axisymmetnc inlet model with auxiliary airflow systems (Grant NsG-3048) are presented The inlet model incorporated both centerbody and (NASA-CR-149106, EE-7611) Avail NTIS HC A04/MF A01 cowl auxiliary airflow systems When the centerbody system was CSCL 21E fully open the performance at the simulated compressor face Two computational methods to determine an open loop time optimal control sequence for a simple single spool turbojet engine was such that at 0 10 total pressure distortion the total capture are described by a set of nonlinear differential equations Both mass flow ratio increased 0055 and 0 051 and the total pressure methods are modifications of widely accepted algorithms which recovery increased 0015 and 0012 at Mach 09 and 13 can solve fixed time unconstrained optimal control problems with respectively Flow separation on the centerbody resulted in a free right end Constrained problems to be considered have supercritical centerbody auxiliary throat flow prior to attainment fixed right ends and free time Dynamic programming is defined of choked main duct throat flow Cowl auxiliary airflow had a on a standard problem and it yields a successive approximation detrimental effect on compressor-face performance To overcome solution to the time optimal problem of interest A feedback the detrimental effect alternate cowl auxiliary airflow systems control law is obtained and it is then used to determine the are described for efficient merging of auxiliary and mam duct corresponding open loop control sequence The Fletcher-Reeves airflows and for providing similar auxiliary and mam duct throat conjugate gradient method has been selected for adaptation to choking characteristics Author 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 N77-10061*# Notre Dame Umv Ind Dept of Electrical EMISSIONS OF AN AVCO LYCOMING 0-320 DI AD AIR Engineering COOLED LIGHT AIRCRAFT ENGINE AS A FUNCTION OF SIMPLIFIED SIMULATION MODELS FOR CONTROL FUEL-AIR RATIO. TIMING. AND AIR TEMPERATURE AND STUDIES OF TURBOJET ENGINES HUMIDITY Thomas C Brennan and R Jeffrey Leake Nov 1975 93 p Phillip R Meng Michael Skorobatckyi, Donald V Cosgrove and refs Erwm E Kempke Aug 1976 206 p refs (Grant NsG-3048) (NASA-TM-X-73500) Avail NTIS HC A10/MF A01 CSCL (NASA-CR-149107 EE-757) Avail NTIS HC A05/MF A01 21G CSCL 21E A carbureted aircraft engine was operated over a range of The essential dynamical characteristics of a simple single test conditions to establish the exhaust levels over the EPA spool turbojet engine were determined through simulation of seven-mode emissions cycle Baseline (full rich production limit) low order system models on an analog computer An accurate exhaust emissions at an induction air temperature of 59 F and model was studied and system complexity was reduced through near zero relative humidity were 90 percent of the EPA standard various linearizations and approximations A derivation of a seventh for HC, 35 percent for NOx. and 161 percent for CO Changes order simplified simulation model is presented with a derivation in ignition timing around the standard 25 deg BTDC from 30 deg of an even simpler third order model, and simulation results BTDC to 20 deg BTDC had little effect on the exhaust emissions from each The control problem studied is one of getting from Retarding the timing to 15 deg BTDC increased both the HC zero fuel flow equilibrium to a high thrust equilibrium while and CO emissions and decreased NOx emissions HC and CO taking into account surge margin and turbine inlet temperature emissions decreased as the carburetor was leaned out while constraints Author 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 N77-10062*| National Aeronautics and Space Administration NOx emissions decreased Author Lewis Research Center Cleveland Ohio

23 N77-10063

ADVANCED COMBUSTION TECHNIQUES FOR CONTROL- S J Morns W E Foss. Jr and J W Russell (Vought Corp LING NO SUB x EMISSIONS OF HIGH ALTITUDE CRUISE Hampton. Va) 1 Nov 1976 59 p refs AIRCRAFT (NASA-TM-X-73977) Avail NTIS HC A04/MF A01 CSCL R A Rudey and G M Reck 1976 21 p refs Presented at 21E 27th Intern Astronaut Congr. Anaheim, Calif 10-16 Oct 1976. Three proposed SCAR propulsion systems in terms of aircraft sponsored by AIAA range for a fixed payload and take-off gross weight with a design (NASA-TM-X-73473 E-8858) Avail NTIS HC A02/MF A01 cruise Mach number 2 7 are evaluated The effects of various CSCL 21E noise and operational restraints are determined and sensitivities An array of experiments designed to explore the potential to some of the more important performance variables are presented of advanced combustion techniques for controlling the emissions for the most probable design noise and operational restraint of aircraft into the upper atmosphere was discussed Of particular case Critical areas requiring new or improved technology for concern are the oxides of nitrogen (NOx) emissions into the each cycle are delineated Author 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 N77-10066*# National Aeronautics and Space Administration Lewis Research Center, Ceveland Ohio achievable in future aircraft engines A maior NASA oroaram is described which focuses the many fundamental experiments into EFFECT OF AIR TEMPERATURE AND RELATIVE HUMIDITY a planned evolution and demonstration of the prevaponzed- AT VARIOUS FUEL-AIR RATIOS ON EXHAUST EMISSIONS premixed combustion technique in a full-scale engine Author ON A PER-MODE BASIS OF AN AVCO LYCOMING 0-320 DIAD LIGHT AIRCRAFT ENGINE VOLUME 2 INDIVIDUAL DATA POINTS N77-10063*# National Aeronautics and Space Administration Michael Skorobatckyi Donald V Cosgrove Phillip R Meng and Lewis Research Center Cleveland Ohio Edward R Kempke Sep 1976 850 p THE IMPACT OF EMISSIONS STANDARDS ON THE (NASA-TM-X-73507 E-8916-Vol-2) Avail NTIS DESIGN OF AIRCRAFT GAS TURBINE ENGINE COMBUS- HC A99/MF A01 CSCL 21 E TORS A carbureted four cylinder air cooled 0-320 DIAD Lycoming Richard A Rudey 1976 19 p refs Presented at the Aerospace aircraft engine was tested to establish the effects of air temperature Conf San Diego Calif. 29 Nov - 2 Dec 1976 sponsored by and humidity at various fuel-air ratios on the exhaust emissions SAE on a per-mode basis The test conditions included carburetor (NASA-TM-X-73490) Avail NTIS HC A02/MF A01 CSCL lean-out at air temperatures of 50 59 80 and 100 F at relative 21E humidities of 0 30 60 and 80 percent Temperature-humidity Effective emission control techniques have been identified effects at the higher values of air temperature and relative humidity and a wide spectrum of potential applications for these techniques tested indicated that the HC and CO emissions increased to existing and advanced engines are being considered Results significantly while the NOx emissions decreased Even at a fixed from advanced combustor concept evaluations and from fuel-air ratio the HC emissions increase and the NOx emissions fundamental experiments are presented and discussed and decrease at the higher values of air temperature and humidity comparisons are made with existing EPA emission standards Volume II contains the data taken at each of the individual test and recommended levels for high altitude cruise The impact points Author that the advanced low emission concepts may impose on future aircraft engine combustor designs and related engine components is discussed Author N77-1O067# Techmsche Hochschule Aachen (West Germany) Inst fuer Luft- und Raumfahrt NOISE GENERATING BY INTERACTION BETWEEN SUB- SONIC JETS AND BLOWN FLAPS N77-10064*# Pratt and Whitney Aircraft East Hartford Conn Erich Evertz Valentin Kloeppel Guenther Neuwerth and August EXPERIMENTAL CLEAN COMBUSTOR PROGRAM NOISE Wilhelm Quick Cologne DFVLR 15 Mar 1976 23 p refs STUDY Presented at AIAA Meeting, Tenn Sponsored by Mm fuer T G Sofrm and N Riloff Jr Sep 1976 191 p refs Wiss u Forsch des Landes Nordrhem-Westfalen (Contract NAS3-18544) (DLR-FB-76-20) Avail NTIS HC A02/MF A01. DFVLR, Cologne (NASA-CR-135106 PWA-5458) Avail NTIS DM 1080 HC A09/MF A01 CSCL 21E On the basis of experimental results the strong noise Under a Noise Addendum to the NASA Experimental Clean generation originating from the interference between air jets of Combustor Program (ECCP) internal pressure fluctuations were high subsonic speed and externally blown flaps (EBF) is discussed measured during tests of JT9D combustor designs conducted in It is shown that in an undisturbed free jet as well as in a jet a burner test rig Measurements were correlated with burner deflected by EBF there are ordered turbulence structures An operating parameters using an expression relating farfield noise acoustical feedback mechanism which develops at small distances to these parameters For a given combustor variation of internal between nozzle and stagnation point on the flaps and which noise with operating parameters was reasonably well predicted reinforces the turbulence structures is explained It is subsequently by this expression but the levels were higher than farfield shown that even without acoustic feedback both the undisturbed predictions and differed significantly among several combustors free jet and the jet deflected by EBF have their maximum noise For two burners discharge stream temperature fluctuations were levels at the Strouhal number of the natural ordered structures obtained with fast-response thermocouples to allow calculation Author (ESA) 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 N77-1OO68# Naval Air Systems Command. Washington, D C developed analysis the computed indirect combustion noise PREDICTION METHODS FOR JET V/STOL PROPULSION was significantly lower than total low frequency core noise AERODYNAMICS. VOLUME 1 observed on this and several other engines Author 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 N77-10065*# National Aeronautics and Space Administration The dispersed force concept requires a well developed technology Langley Research Center Langley Station Va base, involving phenomena and problems which do not occur ASSESSMENT OF VARIABLE-CYCLE ENGINES FOR on conventional aircraft or low speed V/STOL craft Proper design MACH 2 7 SUPERSONIC TRANSPORTS Status Report must account for the interdependence of aerodynamic and

24 N77-10195

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 N77-10069# Naval Air Systems Command Washington D C degree of freedom AFFDL wing-tail flutter model The analytical PREDICTION METHODS FOR JET V/STOL PROPULSION and experimental design of a flutter suppression system for the AERODYNAMICS. VOLUME 2 AFFDL model is presented along with the results of a pre- M F Platzer Jul 1975 545 p refs Workshop held at liminary passive flutter test Author (GRA) Arlington Va, 28-31 Jul 1975 (AD-A024023) Avail NTIS HC A23/MF A01 CSCL01/1 N77-10162# European Space Agency, Pans (France) For abstract seeN77-10068 THEORETICAL AND EXPERIMENTAL INVESTIGATIONS ON LANDING GEAR SPRING BLADES OUT OF FIBER REIN- FORCED PLASTIC FOR SMALL AIRCRAFT N77-10070# Air Force Inst of Tech . Wright-Patterson AFB Ramer Schuetze Sep 1976 35 p refs Trans) into ENGLISH Ohio School of Engineering of Theoretische u exptl Untersuch an Fahrwerksfederblaettern COMBUSTOR DESIGN FOR LOW COST EXPENDABLE aus faserverstaerkten Kunststoffen fuer Klemflugzeuge DFVLR. TURBOJETS M S Thesis Brunswick Report DLR-FB-76-06. 12 Jan 1976 Original German Raymond L Greene Mar 1976 57 p refs report available from DFVLR, Cologne DM 1620 (AD-A024541 GAE/AE/76M-1) Avail NTIS (ESA-TT-312 DLR-FB-76-06) Avail NTIS HC A03/MF A01 HC A04/MF A01 CSCL 21/5 The development of several landing gear spring blades for a The development of two experimental burners was completed small aircraft is described A special sandwich structure not only as part of a project to evaluate the suitability of the use of minimized the weight of the spring blade but also enabled it to converted reciprocating engine turbochargers as expendable jet resist both high longitudinal stresses in the facing layers and engines for remotely piloted vehicles As a result of analytic high shear stresses in the core The considerable length of these studies Burner A was constructed as a reverse flow burner spring blades made it essential for them to have a high flexural and was designed to accept a mass flow up to 0 75 Ibm/sec rigidity Carbon and Kevlar 49 fibers both of which have a Burner 'B was also reverse and designed for a mass flow up greater modulus of elasticity than glass fibers were therefore to 1 5 Ibm/sec Both burners operated successfully on their used as alternative reinforcements in the facing layers on the respective turbochargers GRA 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 N77-10083# Office National d Etudes et de Recherche: compared with the GRP sandwich and an improved damping Aerospatiales Pans (France) behavior was also obtained Author (ESA) 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 N77-10183*# National Aeronautics and Space Administration at the 12th Ecole Natl Super de Mecan et d Aerotech/CEAT Lewis Research Center, Cleveland Ohio Colloq Appl Poitiers France 5-7 Nov 1975 HOT CORROSION STUDIES OF FOUR NICKEL-BASE (AAAF-NT-76-13 ISBN-2-7T70-0391-6) Avail NTIS SUPERALLOYS B 1900, NASA-TRW VIA. 713C AND HC A02/MF A01, CEDOCAR, Pans FF 15 (France and EEC) IN738 FF 19 (others) George C Fryburg Fred J Kohl, and Carl A Stearns 1976 Wind tunnel tests on the aspiration of the boundary layer 11 p refs Presented at Symp on Properties of High Temp upstream of the reference profiles NACA 0012 and LC 100D Alloys Las Vegas Nev 17-22 Oct 1976 sponsored by the are discussed The two-dimensional test section of the ONERA Electrochem Soc and the Met Soc of the Am Inst of Mining RICh wind tunnel contains a porous wall permitting partial Met and Petrol Engrs aspiration of the boundary layer upstream of the model The (NASA-TM-X-73479) Avail NTIS HC A02/MF A01 CSCL aspiration rate is adjustable and generates a variation of the 11F displacement thickness from 5 to 1% of the model half-span The susceptibility to hot corrosion of four nickel base permitting in some cases the extrapolation of the results to the superalloys has been studied at 900 deg and 1000 deg C in extreme case of no boundary layer The effect of wall boundary, one atmosphere of slowly flowing oxygen Hot corrosion was layers appears as a variation of the profile performance and a induced by coating the samples with known doses of NaS04 displacement of the shock waves To compare the results obtained and oxidizing the coated samples isothermally on a sensitive in various wind tunnels this parameter should be taken into microbalance In general the order of susceptibility found was consideration It appears very difficult to establish a method for B-1900 is greater than 713C is greater than NASA-TRW VIA correcting these wall boundary layer effects therefore it seems and is greater than IN738 This order corresponds to the order mandatory to reduce them as far as possible Author (ESA) 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 N77-10090# Texas Univ Austin Dept of Aerospace Author Engineering and Engineering Mechanics THE DESIGN. ANALYSIS AND TESTING OF A LOW BUDGET N77-10195$ Aluminum Co of America Alcoa Centei. Pa Alcoa WIND TUNNEL FLUTTER MODEL WITH ACTIVE AERODY- Labs NAMIC CONTROLS. VOLUME 2 Final Report. 1 Dec DESIGN MECHANICAL PROPERTIES. FRACTURE TOUGH- 1970 - 30 Nov 1975 NESS. FATIGUE PROPERTIES. EXFOLIATION AND Randall M Bolding and Ronald 0 Stearman Jan 1976 34 p STRESS-CORROSION RESISTANCE OF 7060 SHEET. refs Presented at the NASA Symp on Flutter Testing, Edwards, PLATE. HAND FORCINGS. DIE FORCINGS AND EXTRU- Calif 9-10 Oct 1975 SIONS Final Report. 12 May 1972 - 12 Nov 1974 (Grant AF-AFOSR-1998-71, AF Proj 9782) R E Davies G E Nordmack and J D Walsh Jul 1975 (AD-A024480 AFOSR-76-0537TR-Vol-2) Avail NTIS 301 p refs HC A03/MF A01 CSCL 20/4 (Contract N00019-72-C-0512) This report describes a low budget flutter model incorporating (AD-A024609) Avail NTIS HC A14/MF A01 CSCL 11/6 active aerodynamic controls for flutter suppression studies, The mechanical properties including fracture toughness and concentrating on the interfering lifting surface flutter phenomenon fatigue fatigue-crack growth rates and corrosion characteristics

25 N77-10210

have been determined for a total of 51 lots of 7050-T76 sheet. the duct and in addition propagate similarly to the far field 7050-T73651 plate 7050-T73652 hand forgmgs, 7050-T736 Thus there is no need to determine the acoustic power carried die forgmgs and 7050-T76511 extruded shapes Tables of by these modes individually and they can be grouped together computed design mechanical properties, modulus of elasticity 95 one entity With the optimum impedance and maximum values and individual stress-strain curves are presented The critical attenuation specified as functions of cutoff ratio, the off-optimum stress-intensity factor. (K sub c), was determined for samples of liner performance can be estimated using an approximate each lot of sheet and the plane-strain stress-intensity factor, attenuation equation Author (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 N77-10344*# National Aeronautics and Space Administration of conventional 7XXX alloys Axial-stress fatigue strengths were Langley Research Center. Langley Station, Va determined in ambient-air and salt-fog environments Modified HYDROGEN-FUELED SUBSONIC AIRCRAFT A PERSPEC- Goodman diagrams were, developed from tests made in ambient TIVE air GRA Robert D Witcofski In its Advan in Eng Sci. Vol 3 1976 p 1265-12^8 refs N77-10210# Lockheed Aircraft Corp , Marietta Ga Avail NTIS HCA20/MFA01 CSCL21D FULL TEMPERATURE RANGE PROTECTIVE SYSTEM FOR The performance characteristics of hydrogen-fueled subsonic FASTENER AREAS OF CARRIER-BASED NAVAL AIRCRAFT transport aircraft are compared to those using conventional Summary Report, 1 Jan 1974 - 31 Dec 1975 aviation kerosene Additional aspects discussed include potential R N Wilier G G Seeliger. and W A Boggs Feb 1976 improvements in the exhaust emissions characteristics of aircraft 107 p refs jet engines problems associated with onboard fuel containment, (Contract N00019-74-C-0267) results of recent studies of the impact of hydrogen-fueled aircraft (AD-A024523, LG76ER0029) Avail NTIS HC A06/MF A01 on the airport and associated ground support equipment, and CSCL 11/3 estimates of the cost and thermal efficiency of producing synthetic Results are presented for a program to develop a full aviation fuels from coal Author 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 N77-10345*# National Aeronautics and Space Administration representative of aircraft joints After five cycles of a simulated Langley Research Center, Langley Station Va flight spectrum the specimens were checked for coating defects, ADVANCES IN ENGINEERING SCIENCE. VOLUME 4 corrosion, and coating adhesion The most effective coating 1976 521 p refs Presented at 13th Ann Meeting of Soc of combinations were three-layer systems composed of a MIL-P- Eng Sci. Hampton, Va 1-3 Nov 1976 sponsored by JIAFS and George Washington Univ 4 Vol 23377 epoxy-polyamide primer, an aliphatic linear polyurethane (NASA-CP-2001-Vol-4) Avail NTIS HC A22/MF A01 CSCL topcoat and intermediate coats of elastomenc polyurethane or 13M inhibited polysulfide These plus an additional system with an The following areas of flight science are discussed in detail, inhibited polysulfide primer and polyurethane topcoat were applied (1) mviscid flow (2) viscous flow (3) aircraft aerodynamics, to A-7 carrier-based Navy aircraft during 1975 Plans were made (4) fluid mechanics (5) propulsion and combustion and (6) flight for the periodic inspection of the test aircraft over a span of dynamics and control 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) N77-10347*# North Carolina State Univ Raleigh Dept of Mechanical and Aerospace Engineering LIFTING SURFACE THEORY FOR RECTANGULAR WINGS N77-10230*# National Aeronautics and Space Administration Langley Research Center Langley Station Va Fred R DeJarnette In NASA Langley Res Center Advan in ADVANCES IN ENGINEERING SCIENCE, VOLUME 1 Eng Sci Vol 4 1976 p 1301-1309 refs 1976 360 p refs Presented at the 13th Ann Meeting of The Soc of Eng Sci 1-3 Nov 1976, Hampton. Va . sponsored (Grant DAAG29-76-G-0045) by JIAFS and George Washington Univ 1 Vol Avail NTIS HC A22/MF A01 (NASA-CP-2001-Vol-1) Avail NTIS HC Al'6/MF A01 CSCL A new incompressible lifting-surface theory is developed for 13M thin rectangular wings The solution requires the downwash Proceedings from a conference on engineering advances are equation to be in the form of Cauchy-type integrals Lan's method presented including materials science fracture mechanics, and is employed for the chordwise integrals since it properly accounts impact and vibration testing The tensile strength and moisture for the leading-edge singularity. Cauchy singularity and Kutta transport of laminates are also discussed 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 N77-10311*$ National Aeronautics and Space Administration Solutions were found to converge with only a small number of Lewis Research Center Cleveland, Ohio control points and to compare favorably with results from other INLET NOISE SUPPRESSOR DESIGN METHOD BASED methods Author 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 N77-10348*# National Aeronautics and Space Administration such as in an engine inlet is presented which potentially Ames Research Center Moffett Field, Calif circumvents the problems of resolution in modal measurement consumption by reducing drag Computer codes have served well The method is based on the fact that the modal optimum in meeting the consequent demand for new wing sections The impedance and the maximum possible sound power attenuation possibility of replacing wind tunnel tests by computational fluid at this optimum can be expressed as functions of cutoff ratio dynamics is discussed Another approach to the supercritical wing alone Modes with similar cutoff ratios propagate similarly in is through shockless airfoils A novel boundary value problem in

26 N77-10366

the hodograph plane is studied that enables one to design a N77-10354*# Texas A&M Univ. College Station shockless airfoil so that its pressure distribution very nearly takes INVERSE TRANSONIC AIRFOIL DESIGN INCLUDING on data that are prescribed Author VISCOUS INTERACTION Leland A Carlson In NASA Langley Res Center Advan in Eng Sci Vol 4 1976 p 1387-1395 refs N77-10349*# Virginia Polytechnic Inst and State Univ Blacksburg (Grant NsG-1174) APPUCATION OF THE NONLINEAR VORTEX-LATTICE Avail NTIS HC A22/MF A01 CONCEPT TO AIRCRAFT-INTERFERENCE PROBLEMS A numerical technique was developed for the analysis of specified transonic airfoils or for the design of airfoils having a Osama A Kandil Dean T Mook and All H Nayfeh In NASA prescribed pressure distribution, including the effect of weak Langley Res Center Advan in Eng Sci. Vol 4 1976 viscous interaction The method uses the full potential equation p 1321-1330 refs a stretched Cartesian coordinate system and the Nash-MacDonald Avail NTIS HC A22/MF A01 turbulent boundary layer method Comparisons with experimental A discrete-vortex model was developed to account for the data for typical transonic airfoils show excellent agreement An hazardous effects of the vortex trail issued from the edges of example shows the application of the method to design a thick separation of a large leading wing on a small trailing wing The aft-cambered airfoil and the effects of viscous interaction on its model is divided into three main parts the leading wing and its performance are discussed Author 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 N77-10355*# Mississippi State Univ Mississippi State in the vortex trail is calculated in the first part of the model NUMERICAL SOLUTIONS FOR LAMINAR AND TURBULENT where the leading wing is far upstream and hence is considered VISCOUS FLOW OVER SINGLE AND MULTI-ELEMENT isolated A numerical example is solved to demonstrate the AIRFOILS USING BODY-FITTED COORDINATE SYSTEMS feasibility of using this method to study interference between aircraft The numerical results show the correct trends The Joe F Thompson Z U A Warsi. and B B Amlicke In NASA following wing experiences a loss in lift between the wing-tip Langley Res Center Advan in Eng Sci Vol 4 1976 vortex systems of the leading wing a gam outside this region p 1397-1407 refs and strong rolling moments which can change sign as the lateral (Grants NGR-25-001-005 AF-AFOSR-2922-76) relative position changes All the results are strongly dependent Avail NTIS HC A22/MF A01 on the vertical relative position Author 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 N77-10350*# National Aeronautics and Space Administration lines are automatically concentrated near to the bodies at higher Langley Research Center Langley Station Va Reynolds number so that accurate resolution of the large gradients AN APPLICATION OF THE SUCTION ANALOG FOR THE near the solid boundaries is achieved Two-dimensional bodies ANALYSIS OF ASYMMETRIC FLOW SITUATIONS of arbitrary shapes are treated the body contour(s) being simply James M Luckring In its Advan in Eng Sci Vol 4 1976 input to the program The complication of the bod- shape is thus removed from the problem Author 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 N77-10365*# National Aeronautics and Space Administration extension includes asymmetric augmented vortex lift and the Langley Research Center, Langley Station Va forward sweep effect on side edge suction Application of this ADVANCED TRANSONIC AERODYNAMIC TECHNOLOGY extension to a series of skewed wings has resulted in an improved estimating capability for a wide range of asymmetric flow Richard T Whitcomb In its Advan m Eng Sci Vol 4 1976 situations Hence the suction analogy concept now has more p 1521-1537 refs general applicability for subsonic lifting surface analysis Author 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 N77-10351*# New York Univ. NY Courant Inst of speed characteristics, and a subsonic jet transport with substan- Mathematical Sciences tially improved aerodynamic efficiency Results of wind tunnel TRANSONIC FLOW THEORY OF AIRFOILS AND WINGS and flight demonstration investigations are described Also discussed are refinements of the transonic area rule concept P R Garabedian In NASA Langley Res Center Advan in Eng Sci Vol 4 1976 p 1349-1358 refs and methods for reducing the aerodynamic interference between engine nacelles and wings at high subsonic speeds Author (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 N77-10366*# Lockheed-Georgia Co Marietta generation of commercial aircraft so as to economize on fuel DESIGN CONSIDERATIONS FOR LAMINAR FLOW CON- consumption by reducing drag Computer codes have served well TROL AIRCRAFT in meeting the consequent demand for new wing sections The R F Sturgeon and J A Bennett In NASA Langley Res possibility of replacing wind tunnel tests by computational fluid Center Advan in Eng Sci Vol 4 1976 p 1539-1548 refs dynamics is discussed Another approach to the supercritical wing is through shockless airfoils A novel boundary value problem in (Contract NAS1-13694) the hodograph plane is studied that enables one to design a Avail NTIS HC A22/MF A01 shockless airfoil so that its pressure distribution very nearly takes A study was conducted to investigate major design considera- on data that are prescribed Author tions involved in the application of laminar flow control to the

27 N77-10367

wings and empennage of long range subsonic transport aircraft p 1703-1711 refs compatible with initial operation in 1985 For commercial (Contract NAS1-13371) transports with a design mission range of 10.186 km (5500 n Avail NTIS HC A22/MF A01 mil) and a payload of 200 passengers, parametric configuration Small perturbation equations of motion of a flexible aircraft analyses were conducted to evaluate the effect of aircraft with an active control technology (ACT) system were developed performance, operational and geometric parameters on fuel to evaluate the stability and performance of the controlled aircraft efficiency Study results indicate that major design goals for aircraft The total aircraft system was formulated in state vector format optimization include maximization of aspect ratio and wing loading and the system of equations was completed with fully unsteady and minimization of wing sweep consistent with wing volume and low frequency aerodynamics for arbitrary, complex configura- and airport performance requirements Author 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 N77-10367*# Pennsylvania State Univ , University Park Dept system with either low frequency or fully unsteady aerodynamics of Aerospace Engineering The applicatioi. of classical performance analyses including ON THE STATUS OF V/STOL FLIGHT frequency response, poles and zeros mean square response, and Barnes W McCormick In NASA Langley Res Center Advan time response in FCAP in state vector format was discussed in Enq Sci Vol 4 1976 p 1549-1562 refs Author

Avail NTIS HC A22/MF A01 Basic principles relating to the accomplishment of V/STOL flight are reviewed as they pertain to current prototype developments Particular consideration is given to the jet flap flow N77-10379*# North Carolina State Univ Raleigh Dept of augmentation and circulation control separately and in combina- Mechanical and Aerospace Engineering tion Configurations as the augmentor wing upper-surface blown BEST-RANGE FLIGHT CONDITIONS FOR CRUISE-CLIMB flaps externally blown flaps and the circulation-controlled rotor FLIGHT OF A JET AIRCRAFT are also examined Author 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 N77-10368*# National Aeronautics and Space Administration The Breguet range equation was developed for cruise climb Langley Research Center Langley Station Va flight of a jet aircraft to include the climb angle and is then THE CRYOGENIC WIND TUNNEL maximized with respect to the no wind true airspeed The Robert A Kilgore In its Advan in Eng Sci Vol 4 1976 expression for the best range airspeed is a function of the specific p 1565-1581 refs fuel consumption and minimum drag airspeed and indicates that Avail NTIS HC A22/MF A01 CSCL 14B an operational airspeed equal to the fourth root of three times Based on theoretical studies and experience with a low speed the minimum-drag airspeed introduces range penalties of the cryogenic tunnel and with a 1/3-meter transonic cryogenic tunnel order of one percent Author 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 N77-10381*# National Aeronautics and Space Administration pressurized cryogenic tunnel make possible for the first time the Langley Research Center Langley Station Va separation of Mach number Reynolds number and aeroelastic RESULTS OF RECENT NASA STUDIES ON AUTOMATIC effects By reducing the drive-power requirements to a level SPIN PREVENTION FOR FIGHTER AIRCRAFT where a conventional fan drive system may be used the cryogenic Joseph R Chambers and Luat T Nguyen In its Advan in Eng concept makes possible a tunnel with high productivity and run Sci. Vol 4 1976 p 1733-1751 refs times sufficiently long to allow for all types of tests at reduced capital costs and, for equal amounts of testing reduced total Avail NTIS HCA22/MFA01 CSCL01C energy consumption in comparison with other tunnel concepts A broad based research program was developed to eliminate Author or minimize inadvertent spins for advanced military aircraft Recent piloted simulator studies and airplane flight tests have demonstrated that the automatic control systems in use on current fighters can be tailored to provide a high degree of spin resistance for N77-10377*# National Aeronautics and Space Administration some configurations without restrictions to maneuverability Such Langley Research Center, Langley Station. Va systems result in greatly increased tactical effectiveness safety, DESIGN OF ACTIVE CONTROLS FOR THE NASA F-8 and pilot confidence Author DIGITAL FLY-BY-WIRE AIRPLANE Joseph Gera In its Advan in Eng Sci. Vol 4 1976 p 1687-1701 refs N77-10383*# Youngstown State Univ. Ohio Avail NTIS HC A22/MF AOI^CSCL 01C TERMINAL AREA GUIDANCE ALONG CURVED PATHS. A The design of a set of control laws for the NASA F-8 digital STOCHASTIC CONTROL APPROACH fly by wire research airplane is described These control laws J E Quaranta and R H Foulkes. Jr In NASA Langley Res implement several active controls functions maneuver load Center Advan in Eng Sci. Vol 4 1976 p 1767-1777 refs control, ride smoothing and departure boundary limiting The criteria and methods which were used in the design of the (Grant NsG-1199) control laws are also included Results of linear analyses and Avail NTIS HC A22/MF A01 nonlinear simulation are summarized Author 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 N77-10378*# Aerospace Systems. Inc. Burlington. Mass scheme consisting of feedback gams multiplying estimate of the PERFORMANCE ANALYSIS OF FLEXIBLE AIRCRAFT WITH aircraft and wind states obtained from a Kalman one step predictor ACTIVE CONTROL Preliminary results are presented which indicate that the Richard B Noll and Luigi Monno (Boston Univ) In NASA compensator performs satisfactorily in the presence of both Langley Res Center Advan in Eng Sci, Vol 4 1976 steady winds and gusts Author

28 N77-10998

N77-10432*# Massachusetts Inst of Tech Cambridge N77-10690# Urban Systems Research and Engineering Inc Electronic Systems Lab Cambridge Mass UNEAR REGULATOR DESIGN FOR STOCHASTIC SYSTEMS BASELINE ENERGY FORECASTS AND ANALYSIS OF BY A MULTIPLE TIME SCALES METHOD ALTERNATIVE STRATEGIES FOR AIRLINE FUEL CONSER- Demosthenis Teneketzis and Nils R Sandell Jr |1976] 19 p VATION refs Jul 1976 199 p (Grants NGL-22-009-124. E(49-18)-2087) (Contract FEA-C-04-50088-00) (NASA-CR-149099) Avail NTIS HC A02/MF A01 CSCL (PB-255351/9 FEA/D-76/026 FEA/D-CP-48) Avail NTIS 09A HC A09/MF A01 CSCL 10A A hierarchically-structured suboptimal controller for a linear Baseline forecasts of airline activity and energy consumption stochastic system composed of fast and slow subsystems is to 1990 were developed to evaluate the impact of fuel considered The controller is optimal in the limit as the separation conservation strategies Alternative policy options to reduce fuel of time scales of the subsystems becomes infinite The methodol- consumption were identified and analyzed for three baseline levels ogy is illustrated by design of a controller to suppress the phugoid of aviation activity within the framework of an aviation activity/ energy consumption model By combining the identified policy and short period modes of the longitudinal dynamics of the F-8 options a strategy was developed to provide incentives for airline aircraft Author 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 N77-10512# Aeronautical Systems Div Wright-Patterson AFB environmental and economic costs GRA Ohio PRAM Program Office LCC ANALYSIS OF FLIGHT RECORDER FOR F-4 WILD WEASEL AIRCRAFT Final Report N77-10873# European Space Agency. Paris (France) Thomas D Mcitzler 7 Apr 1976 7 p refs EXPERIMENTS ON THE FEASIBILITY OF AERO-ACOUSTIC (AD-A023830 ASD, RAXA-76-6) Avail NTIS MEASUREMENTS IN THE 3-m LOW SPEED WIND TUNNEL HC A02/MF A01 CSCL 14/3 ^ OF THE DFVLR-AVA This report briefly summarizes a basic life cycle cost effort Friednch-Remhard Grosche et al Sep 1976 36 p refs Transl on two flight recorders It discusses the background approach into ENGLISH of 'Expt zur Moeghchkeit von aeroakustischen results and conclusions of the study GRA 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 N77-10b56*# United Technologies Research Center. East (ESA-TT-311 DLR-FB-75-52) Avail NTIS HC A03/MF A01 Hartford Conn The experiments include measurements of the tunnel noise AEROELASTIC ANALYSIS FOR HELICOPTER ROTOR and measurements of the noise of a high subsonic jet emana- BLADES WITH TIME-VARIABLE. NON-LINEAR STRUC- ting from a nozzle of 5 cm diameter located in a test section of TURAL TWIST AND MULTIPLE STRUCTURAL RE- the wind tunnel The noise level of the jet was 10 to 20 db DUNDANCY MATHEMATICAL DERIVATION AND higher at frequencies about 2 kHz than the noise level of the PROGRAM USER'S MANUAL Final Report tunnel although a large airplane model producing additional flow Richard L Bielawa Oct 1976 155 p refs noise was installed in the test section Author (ESA) (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 N77-10997*# Transemantics Inc Washington D C conditions together with those additional aeroelastic features VISCOUS INTERACTION WITH SEPARATION IN TRAN- germane to composite bearmgless rotors are derived The SONIC FLOW differential equations are formulated in terms of uncoupled (zero J Delery J J Chattot and J C LeBalleur NASA Aug 1976 pitch and twist) vibratory modes with exact coupling effects 27 p refs Transl into ENGLISH of ONERA conf paper Presented due to finite time variable blade pitch and to second order at Flow Separation, AGARD Fluid Dyn Symp Goettmgen West twist Also presented are derivations of the fully coupled inertia Germany 27-30 May 1975 and aerodynamic load distributions automatic pitch change (Contract NASw-2792) coupling effects structural redundancy characteristics of the (NASA-TT-F-17187) Avail NTIS HC A03/MF A01 CSCL composite bearmgless rotor flexbeam - torque tube system in 01A _ bending and torsion, and a descr jtion of the linearized equations Strong viscous interactions which are present m transonic appropriate for eigensolution analyses Three appendixes are flows past airfoils give rise to an important thickening of the included presenting material appropriate to the digital computer boundary layer with the frequent formation of a separated program implementation of the analysis, program G400 Author 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 N77-10640*# National Aeronautics and Space Administration a continuous wind tunnel equipped with a two dimensional nozzle Lewis Research Center Cleveland Ohio having a 120 sq cm section The experimental installation is EARLY OPERATION EXPERIENCE ON THE ERDA/NASA made of a half profile mounted on the lower wall of the transonic 100 kW WIND TURBINE channel A detailed analysis of the flow field was made by using John C Glasgow and Bradford S Linscott Sep 1976 25 p interferometry a measuring technique which avoids any disturb- refs ance of the flow At the same time an effort was made to (NASA-TM-X-71601 E-8076) Avail NTIS HC A02/MF A01 develop a method of calculation similar to Klmeborg's approach CSCL 10A Author 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 N77-10998*# National Aeronautics and Space Administration and drive shaft loads and tower deflection were measured during Langley Research Center Langley Station Va operation of the wind turbine at rated rpm The blade loads EFFECTS OF JETS. WAKES. AND VORTICES ON LIFTING measured are higher than anticipated Preliminary results indicate SURFACES that air flow blockage by the towei structure probably caused Richard J Margason Nov 1976 15 p refs Presented at the the high rotor blade bending moments Author AGARD Flight Dyn Panel Round Table Discussion Meeting

29 N77-10999

Moffett Field. Calif. 30 Sep - 1 Oct 1976 N77-11005*# Boeing Commercial Airplane Co Seattle. Wash (NASA-TM-X-73974) Avail NTIS HC A02/MF A01 CSCL A COMPUTATIONAL SYSTEM FOR AERODYNAMIC 01A DESIGN AND ANALYSIS OF SUPERSONIC AIRCRAFT The interaction of jets, wakes, and vortices on lifting bodies PART 2 USER'S MANUAL Final Report. Jan 1976 - represents a broad spectrum of aerodynamic flow phenomena Mar 1976 A literature survey is presented of 79 research activities in related W D Middleton J L Lundry and R G Coleman Washington aerodynamic situations Author NASA Aug 1976 267 p refs (Contract NAS1-13732) (NASA-CR-2716 D6-43798-2) Avail NTIS HC A12/MF A01 CSCL 01A N77-10999# National Aeronautical Establishment, Ottawa An integrated system of computer programs was developed (Ontario) for the design and analysis of supersonic configurations The CONTROLLED AND UNCONTROLLED FLOW SEPARATION system uses linearized theory methods for the calculation of IN THREE DIMENSIONS surface pressures and supersonic area rule concepts in combination D J Peake Jul 1976 70 p refs Presented at Symp on with linearized theory for calculation of aerodynamic force Viscous Flows Marietta Ga . 22-23 Jun 1976 coefficients Interactive graphics-are optional at the user's request (LR-591. NRC-15471 ISSN-0077-5541) Avail NTIS This user s manual contains a description of the system, an HC A04/MF A01 explanation of its usage, the input definition and example The advantages of swept, sharp edges that generate controlled output Author (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 dimensional viscous flowfields and vortical interactions about typical components such as delta wings and bodies at incidence are N77-110O6*# Nielsen Engineering and" Research. Inc. Mountain discussed in apposition to their use on selected examples of View Calif current flight vehicles Author 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, N77-11001*# National Aeronautics and Space Administration and Frederick K Goodwin Washington NASA Sep 1976 Langley Research Center Langley Station Va 143 p refs A FLIGHT INVESTIGATION OF PILOTING TECHNIQUES (Contract NAS1-13158) AND CROSSWIND LIMITATIONS DURING VISUAL (NASA-CR-2705) Avail NTIS HC A07/MF A01 CSCL 01A STOL-TYPE LANDING OPERATIONS Bruce D Fisher, Robert A Champme Perry L Deal James M A theoretical investigation was carried out to extend and Patton Jr and Albert W Hall Washington Oct 1976 57 p improve an existing method for predicting the longitudinal refs characteristics of wing flap configurations with externally blown (NASA-TN-D-8284 L-10923) Avail NTIS HC A04/MF A01 flaps (EBF) Two potential flow models were incorporated into CSCL 05H the prediction method a wing and flap lifting-surface model A flight research program was undertaken to investigate and a turbofan engine wake model The wing-flap model uses a problems concerned with landing a STOL airplane in crosswind vortex-lattice approach to represent the wing and flaps The jet conditions The program included a study of piloting techniques wake model consists of a series of closely spaced vortex rings and crosswind limitations during visual STOL type landing normal to a centerline which may have vertical and lateral operations The results indicated that the crosswind was more curvature to conform to the local flow field beneath the wing limiting during the ground roll out than during the airborne phases and flaps Comparisons of measured and predicted pressure The pilots estimated that the crosswind limit for commercial distributions, span load distributions on each lifting surface and STOL type operations with the test aircraft would be approximately total lift and pitching moment coefficients on swept and unswept 15 to 20 knots The pilots thought that the crosswind limits for EBF configurations are included A wide range of thrust coefficients ground operation might be extended by incorporating wing-lift and flap deflection angles is considered at angles of attack up spoilers improved nose gear steering, and improved engine to the onset of stall Results indicate that overall lift and response The pilots agreed that a crosswind landing gear would pitchmg-moment coefficients are predicted reasonably well over also be beneficial Author 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

N77-11002# Lockheed Missiles and Space Co Huntsville Ala DEVELOPMENT OF PREDICTIVE WAKE VORTEX TRANS- PORT MODEL FOR TERMINAL AREA WAKE VORTEX N77-11007*# National Aeronautics and Space Administration AVOIDANCE Final Report. Feb - Oct 1975 Lewis Research Center Cleveland. Ohio M R Brashears A 0 Zalay L C Chou and K R Shrider TWO-DIMENSIONAL COLD-AIR CASCADE STUDY OF A May 1976 232 p refs FILM COOLED TURBINE STATOR BLADE 3 EFFECT OF (Contract DOT-TSC-988) HOLE SIZE ON SINGLE-ROW AND MULTIROW EJECTION (AD-A029049/4 LMSC-HREC-TR-D496597 FAA-RD-76-94 Herman W Prust Jr and Thomas P Moffitt Washington Oct DOT-TSC-FAA-76-15) Avail NTIS HCA11/MFA01 CSCL 1976 33 p refs 01/2 (NASA-TM-X-3442 E-8720) Avail NTIS HC A03/MF A01 The wake vortex transport program wa" expanded to include CSCL 20D viscous effects and the influence of initial roll-up atmospheric The effect of coolant discharge on the aerodynamic perform- turbulence and wind shear on the persistence and motion of ance of s film cooled turbine stator blade was determined The wake vortices in terminal areas Analysis of wake characteristics blade had the same number, location and injection angle of show that changes in the spanwise loading due to flaps increase coolant holes but the coolant hole diameters were one half the initial sink rate decrease the separation and initiates the that of a previously investigated blade Otherwise the blades circulation decay process earlier Buoyancy due to jet exhaust were the same Tests with discharge from individual coolant entramment and ambient stratification retards vortex spreading rows and multiple coolant rows including full film discharge are and increases descent Atmospheric turbulence and shear promote studied The results of the blade with smaller holes are reported a more rapid decay reducing the late-time descent and spread and compared with the blades with larger holes Author

30 N77-11019

N77-11008*# National Aeronautics and Space Administration propagating at different velocities in different directions In general Lewis Research Center Cleveland Ohio measured wave velocities were higher than theoretically predicted PERFORMANCE OF 1 15-PRESSURE-RATIO FAN STAGE values The amplitude of the in-plane wave is less than ten AT SEVERAL ROTOR BLADE SETTING ANGLES WITH percent of that of the flexural wave Peak strains and strain REVERSE FLOW rates in the transverse to the (outer) fiber direction are much George Kovich and Royce D Moore Washington Nov 1976 higher than those in the direction of the fibers The dynamics of 91 p refs impact were also studied with high speed photography Author (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 N77-11116*# IIT Research Inst. Chicago III STRAIN RATE EFFECTS ON MECHANICAL PROPERTIES in reverse flow Survey flow data were taken over the range of rotative speed from 50 percent to 100 percent design speed at OF FIBER COMPOSITES. PART 3 Final Report. 1 Jul 1974 - 29 Feb 1976 several rotor blade setting angles through both flat and feather I M Daniel and T Liber Jun 1976 49 p refs pitch Normal flow design values of pressure ratio and weight (Contract NAS3-16766) How were 1 15 and 299 kg/sec with a rotor tip speed of (NASA-CR-135087 IITRI-D6073-4) Avail NTIS 2438 m/sec The maximum thrust in reverse flow was HC A03/MF A01 CSCL 11D 52 5 percent of design thrust in normal flow Author An experimental investigation was conducted to determine the strain rate effects in fiber composites Unidirectional composite N77-11011|j! National Aerospace Lab Amsterdam (Netherlands) specimens of boron/epoxy, graphite/epoxy, S-glass/epoxy and Kevlar/epoxy were tested to determine longitudinal transverse Ruid Dynamics Div CALCULATION OF THE FLOW AROUND A SWEPT WING. and intralammar (in-plane) shear properties In the Longitudinal TAKING INTO ACCOUNT THE EFFECT OF THE THREE- direction the Kevlar/epoxy shows a definite increase in both DIMENSIONAL BOUNDARY LAYER PART 1 WING WITH modulus and strength with strain rate In the transverse direction, TURBULENT BOUNDARY LAYER a general trend toward higher strength with strain rate is noticed W J Piers G J Schipholt and B VandenBerg 27 May 1975 The mtralaminar shear moduli and strengths of boron/epoxy and 44 p refs graphite/epoxy show a definite rise with strain rate Author (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 N77-11117*# Scientific Translation Service Santa Barbara Calif potential flow was computed with an adapted version of the CONTRIBUTIONS TO THE STUDY OF THE PHYSICAL NLR panel method The displacement effect of the boundary PROPERTIES OF CARBON F Carmona Washington NASA Nov 1976 193 p refs layer and the wake was taken into account by the outflow concept For the calculation of the three-dimensional turbulent boundary Transl into ENGLISH of 'Contributions a I Etude des Propnetes Physiques des Carbons" Doctoral Dissertation Bordeaux Umv layer the method of Wesselmg and Lmdhout was used The 1976 p 1-178 boundary layer calculations were based on measured pressure (Contract NASw-2791) distributions while for the wake a crude estimation was made (NASA-TT-F-17246) Avail NTIS HC A09/MF A01 CSCL It is concluded that the calculated potential flow, with allowance 11D for viscous effects compares well with experimental results in A theoretical justification is given for old results of electron terms of pressure ana lift distribution With regard to the computing paramagnetic resonance The evolution of the physical properties time the potential flow program was about eight times faster of carbon during carbonization is examined in light of recent than the boundary layer program Author (ESA) theoretical and experimental studies on non-crystalline solids Author

N77-11013# Hydronautics Inc Laurel Md HIGH SPEED COMPUTER STUDIES OF VORTEX MOTIONS N77-11118*# National Aeronautics and Space Administration IN RELATION TO AIRCRAFT WAKE TURBULENCE Final Lewis Research Center Cleveland Ohio Report Clinton E Brown and Poter VanDyke Jan 1976 42 p refs EFFECT OF FIBER DIAMETER AND MATRIX ALLOYS ON IMPACT-RESISTANT BORON/ALUMINUM COMPOSITES (Contract F446?0 71-C-0030 AF Pro "7811 (AD-A024290 TR 7115-4 AFOSR . .48'TR) Avail NTIS David L McDanels and Robert A Signorelli Washington Nov HC A03/MF A01 • SCL 01, 1 1976 38 p refs Computatons are presented and cor pared with experimental (NASA-TN-D-8204. E-8648) Avail NTIS HC A03/MF A01 data from ottie' aource^ fo« basic a"d advanced problems in CSCL 11 D aircraft - wake vortex interactions Results are presented for Efforts to improve the impact resistance of B/A are reviewed coalescence of corotation and counterrotating vortex groups and and analyzed Nonstandard thin-sheet charpy and Izod impact finally a complete high speed computer method is developed tests and standard full-size Charpy impact tests were conducted for simulating the roll reaction of an aircraft to the wake produced on composites containing unidirectional 010mm 014mm and by a large aircraft with flaps deployed Suggestions for improved 020mm diameter boron fibers m 1100 2024 5052 and experimental approaches are also appended Author (GRA) 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- N77-11115*# IIT Research Inst Chicago III als and processing The use of a ductile matrix and large diameter WAVE PROPAGATION IN FIBER COMPOSITE LAMINATES. boron fibers gave the h'ghest impact strengths This combination PART 2 Final Report. 1 Jtil 1974 - 29 Feb 1976 resulted in improved energy absorption through matrix shear I M Daniel and T Liber Jun 1976 135 p refs deformation and multiple fiber breakage Author (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 N77-11019*# Transemantics Inc Washington DC the wave propagation characteristics transient strains and residual TOWARD NEW HEIGHTS properties in unidirectional and angle-ply boron/epoxy and B P Bugayev NASA Oct 1976 82 p refs Transl into graphite/epoxy laminates impacted witn silicone rubber projectiles ENGLISH of the mono K Novym Vystam (Novoye v Zhizni at velocities up to 250 MS-1 The predominant wave is flexural Nauke. Tekhnike Senya Transport no 3) Moscow Znaniye

31 N77-11020

Press 1976 p 1-64 flying hour and attrition data supplied by the Air Force Inspection (Contract NASw-2792) and Safety Center The earlier study resulted in sufficient (NASA-TT-F-17248) Avail NTIS HC A05/MF A01 CSCL understanding of the attrition process to develop estimating 01B methodologies that were adopted by the Air Force in official Aeroflot is not only the daily transport of hundreds of publications and that are still in use The conceptual bases for thousands of passengers but also the delivery of equipment, the findings of the first study are discussed, and in conjunction machinery parts and other cargoes to construction sites of the with statistical parameters and an examination of some typical energy and industrial giants, flights with geologists in search of projections the utility of the method is evaluated Author (GRA) 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 N77-11024$ Westmghouse Defense and Electronic Systems and much else The results are presented of accomplishing the Center. Baltimore Md Aerospace and Electronic Systems Div tasks of the Ninth Five-year Plan and how Civil Aviation will FINAL APPROACH PERFORMANCE MONITOR Final develop in the future Author Report I T Basil Jul 1976 189 p (Contract DOT-FA72WA-2837) N77-11020# National Aerospace Lab Amsterdam (Netherlands) (AD-A028513/0 FAA-RD-76-117 Rept-75-0280A) Avail Flight Div NTIS HC A09/MF A01 CSCL 17/7 THE ESTABLISHMENT OF SAFE SEPARATIONS BETWEEN The objectives the system design goals, the hardware AIRCRAFT IN FLIGHT developed, and the laboratory test results of an instrument landing A Pool 1 Dec 1975 12 p Presented at the 28th Intern Air system (ILSI performance monitor are stipulated This new Safety Seminar Amsterdam 3-5 Nov 1975 measuring system makes angular measurements of the angular (NLR-MP-75041-U) Avail NTIS HC A02/MF A01 deviation from the glidepath of an aircraft on a final approach The history of the use of models and statistical data for the Measurements are made once every airport surveillance radar assessment of separation standards is reviewed This work was (ASR) scan The signal used for this measurement is the aircraft's mainly done by the ICAO Vertical Separation Panel the North transponder reply to the ASR interrogation A fixed monopulse Atlantic Systems Planning Group and the ICAO Panel for the monitoring antenna measures the angular position of the aircraft Review of the General Concept of Separation After a brief relative to the antenna boresight Since the antenna is boresighted description of the model and of the target level of safety plans along the glidepath computations can determine the deviation for future work are indicated Author (ESA) 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 N77-11022# 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 N77-11029*# Transemantics. Inc. Washington. DC Report. Dec 1974 - Dec 1975 CALCULATION OF MULTI-CONTOUR THIN-WALLED R S Alger F I Laughndge L L Wiltshire R G McKee (Stanford STRUCTURES BY THE METHOD OF SECTIONS Res Inst Menlo Park Calif) W H Johnson (Stanford Res V G Shatayev NASA Nov 1976 15 p refs Transl into Inst. Menlo Park Calif) and N S Alvares (Stanford Res Inst, ENGLISH from Izv Vysshikh Uchebn Zavedenn Aviats Tekhn Menlo Park Calif) Wright-Patterson AFB Ohio DON Aircraft (Kazan) no 2. Feb 1976 p 117-123 Ground Fire Suppression and Rescue Office Mar 1976 83 p (Contract NASw-2792) refs Sponsored by DOD Aircraft Ground Fire Suppression and (NASA-TT-F-17284) Avail NTIS HC A02/MF A01 CSCL Rescue Office Prepared |Ointly by Stanford Res Inst Menlo 01C Park Calif In calculating thin-walled airframe structures of the type used (AD-A024447 DOD-AGFSRS-76-3) Avail NTIS in the wings and tails of aircraft, the hypothesis of the invariability HC A05/MF A01 CSCL 01/2 of the shape of the contour of the cross sections during Based on a survey of kinematic fuel fires in aircraft accidents, deformation is widespread Many theoretical and experimental two types i e, cascade and rod fuel flows, were selected to studies have shown that it applies in the study of the majority theoretical and experimental examination The twofold objectives of problems of strength of wing and tail assemblies The method was (1) relate fire characteristics such as burning rate, radiation of final sums is used in this article to obtain the numerical field and flame size to the fuel parameters the flowing conditions, solution for a cantilevered thin-walled beam Matrix formulation and the environment and (2) determine the parameters and of basic relationships, equations for numerical solution of a their degree of control required to achieve reproducible fires cantilevered stringer and methods of sections are discussed suitable for testing extinguishing agents equipment, and Author techniques Theoretical models based on steady, laminar, one-dimensional flow were developed

N77-11030*# Aerospace Systems. Inc Burlington. Mass DISPLAY/CONTROL REQUIREMENTS FOR VTOL AIR- N77-11023# RAND Corp Santa Monica Calif CRAFT Interim Technical Report A SECOND LOOK AT RELATIONSHIPS FOR ESTIMATING William C Hoffman Renwick E Curry (MIT Cambridge) David PEACETIME AIRCRAFT ATTRITION Interim Report L Klemman (Connecticut Univ Storrs) Walter M Hollister (MIT William i Mooz Feb 1976 65 p refs Cambridge) and Laurence R Young (MIT. Cambridge) Aug (Contract F44620-73-C-0011) 1975 273 p refs (AD-A023681 R-1840-PR) Avail NTIS HC A04/MF A01 (Contract NAS1-13653) CSCL 01/3 (NASA-CR-145026 ASI-TR-75-26) Ava.l NTIS The attrition experience of individual aircraft systems is found HC A12/MF A01 CSCL 01C to change over the flying life of the system in such a way as Quantative metrics were determined for system control to continually lower the attrition rate This process can be performance workload for control, monitoring performance, and represented mathematically, and the resulting model used to workload for monitoring Pilot tasks were allocated for navigation project future losses for the system A study was made to evaluate and guidance of automated commercial V/STOL aircraft in all the results of an earlier Rand study of peacetime aircraft attrition weather conditions using an optimal control model of the human (RM-4840-PR August 1966) in light of 12 years of additional operator to determine display elements and design A H

32 N77-11037

N77-11031*# National Aeronautics and Space Administration N77-11035/? Rockwell Interns; unal Coip Columbus Ohio Langley Research Center Langley Station Va Missile Systems Div PRELIMINARY SIZING AND PERFORMANCE EVALUATION CONCEPTUAL DESIGNS FOR A MODULAR REMOTELY OF SUPERSONIC CRUISE AIRCRAFT PILOTED VEHICLE Final Report, 2 Dec 1974 - 26 Now D f. Fetterman Jr Sep 1976 80 p refs 1975 (NASA-TM-X-73936) Avail NTIS HC A05/MF A01 CSCL Francis L Goebel Krsey 0 Smith and Frederick W Hessman 01C Jan 1976 279 p refs The basic processes of a method that performs sizing (Contract F336\5-75-C-3036 AF Pro) 1989) operations on a baseline aircraft and determines their subsequent (AD-A023844 C75-1443/034C AFI-OL-TR-75-162) Avail effects on aerodynamics propulsion weights and mission NTIS HCA13/MFA01 CSCL 01/3 performance are described The input requirements of the The application of the modular design approach to remotely associated computer program are defined and its output listings piloted vehicles 'S described It is shewn that by modular explained Results obtained by applying the method to an advanced exchange of structura and equipment components a basic vehicle supersonic technology concept are discussed These results include can be configured to perform low level recce and strike medium the effects of wing loading thrust to weight ratio and technology altitude EW nigh altitude recce and tactical air-to-air missions improvements on range performance and possible gains in both Two basic vehicle configuration design concepts which differ range and payload capability that become available through growth primarily in engine installation arrangement (nacelle versus versions of the baseline aircraft The results from an in depth internal) are presented The design approach using the contractual study that confirm the range gam predicted for a nacelle-mounted engine is shown to be superior and to provide particular wing loading thrust-to-weight ratio combination are the best basis for a technology evaluator 01 demonstrator GRA also included Author

N77-11032*f/ Loi kheed-Georgia Co Manotia PROGRAM FOR ESTABLISHING LONGTIME FLIGHT N77-11036# Douglas Aircraft Co Inc Long Beach Calif SERVICE PERFORMANCE OF COMPOSITE MATERIALS IN DEVELOPMENT OF A GRAPHITE HORIZONTAL STABIL- THE CENTER WING STRUCTURE OF C-130 AIRCRAFT IZER Final Report, 3 Nov 1969 - 31 Aug 1975 PHASE 4 GROUND/FLIGHT ACCEPTANCE TESTS George M Lehman M Ashizawa M J Gailippi A V Hawley W E Harvill and J A Kizer Sep 1976 153 p refs and C A VanPappelendam Mar 1976 85 p (Contract NAS1-1 1 100) (Contract N001 56-70 C-1 321 WF41422206) (NASA-CR-145043 LG76ER0095) Avail NTIS (AD-A023767 MDC-J6902 NADC-76078-30) Avail NTIS HC A08/MF A01 CSCL 01C. "t HC A05/MF A01 CSCL 01/3 The advantageous structural uses of advanced filamentary A summary of the design syn'hesis structural development composites are demonstrated by design fabrication and test of testing tooling manufacturing and ground testing of an advanced three boron epoxy reinforced C-130 center wing boxes The composite horizontal stabilizer tor the A-4 Skyhawk is presented advanced development work necessary to support detailed design The stabilizer utilized Narmco 5206 graphite-epoxy as the of a composite reinforced C-130 center wing box was conduc- primary load-bearing structural material (58 5 percent by weight) ted Activities included the development of d basis for structural The most significant problem encountered was the development design selection and verification ot materials and processes of structurally efficient joints In ground tests the graphite stabilizer manufacturing and tool ng development and fabrication and test successfully sustained design ultimate loads and subsequently of full-scale portions of the center wing box Detailed design sustained two lifetimes of fatigue spectrum loads A positive drawings and necessary analytical structural substantiation margin of-safety of 12 peicent was indicated in a final ultimate- including static strength fatigue endurance flutter and weight strength test after completion of the fatigue test A flutter analyses are considered Some additional component testing was analysis based on the natural modes and frequencies of the conducted to verify the design for panel buckling and to evaluate graphite stabilizel indicated an improvement in empennage flutter specific local design areas Development of the cool tool restraint speed A weight reduction of 26 2 percent was achieved in concept was completed and bonding capabilities were evaluated comparison to the existing metal stabilizer GRA using full-length skin panel and stringer specimens Author

N77-11033*# National Aeronautics and Space Administration N77-11037# ARO Inc Arnold Air Force Station Tenn Langley Research Center Langley Station Va A WIND TUNNEL CAPTIVE AIRCRAFT TESTING TECH- LANDING PRACTICES OF GENERAL AVIATION PILOTS IN NIQUE Final Report, 1 Jul 1974 - 30 Jun 1975 SINGLE-ENGINE LIGHT AIRPLANES R W Butler AEDC Apr 1976 37 p refs Maxwell W Goode Thomas C OBryan Kenneth R Yenni Robert (ARO Pro) P32A-33A ARO Pro| P41T-78A) L Cannaday and Marna H Mayo Washington Oct 1976 (AD-A023690 ARO-PWT-TR-75-80 AEDC-TR-76-22) Avail 50 p refs Technical film supplement L-1208 is available on NTIS HC A03/MF A01 CSCL 01/3 loan from Langley Research Center Attn Photographic Branch A captive aircraft testing technique has been developed for mail stop 425 Hampton Va 23665 use in the 16 ft wind tunnels at the Arnold Engineering (NASA-TN-D-8283 L-10878) Avail NTIS HC A03/MF A01 Development Center (AEDC) With the captive system an aircraft CSCL 05H motion study may be conducted in the wind tunnel with the The methods and techniques used by a group of general tunnel acting as an analog forcing function The large static aviation pilots during the landing phase of light airplane operations aerodynamic data matrix normally required for a motion study are documented The results of 616 landings made by 22 pilots has been alleviated The system validity is established by a in 2 modern four-place single-engine flight airplanes (one having comparison of F 15 aircraft motion generated in the wind tunnel a low wing and the other a high wing) are presented The with flight motion of a NASA 3/8-scale F-15 Remotely Piloted landings were made on both a long runway (1524 m (5000 ft)) Vehicle (RPV) Good agreement between the longitudinal and and a short runway (762 m (2500 ft)) both runways were lateral/directional motions of the model was achieved in the considered typical of those used in general aviation The results absence of RPV unsteady aerodynamics (wing buffet) The captive generally show that most of the approaches were fast with technique ability to efficiently define changes in aircraft flight considerable floating during the flares and with touchdowns that characteristics resulting 'rom different external store configura- were relatively flat or nose low Author tions is demonstrated Author (GRA)

33 N77 11038

N77-11038# Naval Air Development Center Warminster Pa N77-11041# Bell Helicopter Co, Fort Worth. Tex Air Vehicle Technology Dept HELICOPTER RELIABILITY GROWTH EVALUATION Final CATAPULT LAUNCH FATIGUE INVESTIGATION OF THE Report MODEL S-2 E AIRPLANE Final Report G S Conway Apr 1976 170 p refs H D Lystad 31 Dec 1975 58 p refs (Contract DAAJ02-73-C-0097. DA Pro) 1F1-63204-DB-38) (AD-A024071 NADC-75368-30) Avail NTIS (AD-A025265 USAAMRDL-TR-75-53) Avail NTIS HC A04/MF A01 CSCL 01/3 HC A08/MF A01 CSCL 01/3 A laboratory fatigue investigation was performed on an This report presents the results and data resulting from a S-2 E fuselage with reinforced catapult keel beam and holdback research evaluation made of the reliability growth characteristics carry through structure to determine if it could sustain the loads of the development and early production of UH-1D and AH-1G associated with 3 000 catapult launches The bulkhead at fuselage helicopters The major subjects covered by the technique and station 206 failed after 5 690 test cycles of the catapult start backed by research are off-board MTBF reliability (MTBF) growth of run condition Using a test scatter factor of 2 this is equivalent versus test time and reliability growth versus calendar time A to 2 845 service catapult launches The test article experienced tentative technique for predicting helicopter reliability growth 419 service catapult launches prior to reinforcement which when applicable to reliability program planning and management is added to the test results provides for a service catapult launch also presented based on the results of the research An example of the technique procedures applied to a hypothetical helicopter life in excess of 3 000 launches The holdback release condition test was discontinued after 10000 test cycles with no failures is also presented " Author (GRA) Again using a test scatter factor of 2 this is equivalent to 5.000 service catapult launches 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 N77-11039# Army Aviation Engineering Flight Activity Edwards Oscar Ornnger Richard F Harris and John F McCarthy. Jr AFB Cahf Oct 1975 98 p refs ARMY PRELIMINARY EVALUATION YOH-58A HELICOPTER (Contract F33615-74-C-3046 AF Pro) 1929) WITH A FLAT-PLATE CANOPY Final Report (AD-A025266 ASRL-TR-179-1 AFFDL-TR-75-123) Avail James R Arnold and Gary L Skinner Dec 1975 45 p refs NTIS HC A05/MF A01 CSCL 01/3 (AD-A024501 USAAEFA-75-20) Avail NTIS Risks of fiacture were computed from a Monte Carlo HC A03/MF A01 CSCL 01/3 simulation of the Paris equation for crack growth rate The A limited evaluation of the performance and handling qualities simulation covered a total number of load events approximately of the OH-58A helicopter was conducted to determine the effects equivalent to the estimated useful service life for a typical fighter of a four-plane flat-plate canopy installation Testing was airplane The simulation was implemented by development of a conducted at the Bell Helicopter Company flight test facility at computation technique based on the analog computer Ap- Arlington Texas from 25 October through 4 November 1975 proximately 200 simulations were run for each of 11 assumed Personnel from the United States Army Aviation Engineering initial crack sizes with the loading represented by a random Flight Activity conducted 11 test flights for a total of 6 5 productive noise signal filtered through a track-hold circuit to match a stress test flight hours The evaluation revealed a loss in airspeed of 2 range exceedance distribution derived from an acceleration peak and 6 knots at the airspeed for maximum continuous power exceedance curve for the typical aircraft fleet The resulting and a loss in range of 8 and 23 nautical miles at the cruise r data were sampled at four fractions of simulated service life airspeed (forward and aft center-of-g avity configurations and then reduced to four final crack size histograms for each respectively) The noticeable changes in the handling qualities initial crack size The raw data histograms were used to estimate were a slight increase in the nose-down pitching rate following parameter values for three-parameter Weibull distributions for a sudden loss of power (more pronounced for the forward final crack size in each case and a regression analysis was center-of-gravity configuration) and a slight increase in the dihedral performed to correlate the distributions for risk analysis effect of the helicopter The flat-plate canopy installation resulted Mathematical risks of structural failure were computed and in a slight reduction in the field of view but visibility was improved compared for several combinations of assumptions about the due to the optical clarity of the flat-plate The installation of loading and the initial crack size distributions Author (GRA) 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 N77-11043jjf Aerospace Medical Research Labs Wright- be attributed to the flat-plate canopy installation Author (GRA) 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 N77-11040# Naval Air Development Center Warminster Pa HC A03/MF A01 CSCL 01/3 Vehicle Technology Dept The effects of aircraft angle of attack and flight path FATIGUE INVESTIGATION OF THE E-2B/C NOSE LANDING acceleration during high G fighter maneuvering on the position GEAR Final Report of the resultant G relative to the pilot are examined by means H D Lystad 31 Dec 1975 65 p refs of a computer simulated dogfight engagement It is demonstrated (AD-A024072 NADC-75369-30) Avail NTIS that a transient shifting in position of the resultant G relative to HC A04/MF A01 CSCL 01/3 an aircraft vertical reference is correlated with variations in flight A laboratory fatigue investigation was performed on an E-2B path acceleration which occur due to pilot actuation of controls and an E-2C nose landing gear to determine whether the with attendant changes in flight path characteristics Although authorized limit of 650 catapult launches could be extended time intervals during high G turns are noted wherein high values The starboard holdback lug of the E-2B nose landing gear with for aircraft angle of attack coincide with high values for the modified drag brace attachment lugs failed after the application position of resultant G forward of aircraft vertical these cases of 3 336 test cycles Using a test scatter factor of two this is generally occur at subsonic (M equal to or less than 0 7) airspeeds equivalent to 1 668 service catapult launches The outer cylinder and for the best case for which the maximum power throttle of the E-2C shock strut assembly cracked under the packing setting is elected For high G turns at transonic and supersonic nut after completion of 7 430 test cycles Again using a test speeds the associated angle of attack is substantially reduced scatter factor of two. this is equivalent to 3715 service catapult as is the maximum inclination of resultant G forward of vertical launches Author (GRA) for the best case of maximum power setting Application of

34 N77-11050

speed brakes or selection of an intermediate power setting has N77-11047*# AiResearch Mfg Co Phoenix. Ariz the effect of shifting the G-vector aft It is concluded that the COMPRESSOR BLADE SETTING ANGLE ACCURACY arbitrary addition of a large angle equal to the aircraft angle of STUDY VOLUME 2 DATA COMPILATION Final Report attack to the ejection seat back angle to provide added pilot •F F Holman and J R Kidwell Jun 1976 133 p Sponsored protection against high G forces is not warranted Author (GRA) by Army Air Mobility Res and Develop Lab Moffett Field Calif 2 Vol (Contract NAS3-18024) N77-11044*# National Aeronautics and Space Administration (NASA-CR-135068-Vol-2 AiResearch-73-311305-Vol-2) Avail Ames Research Center. M off en Field. Calif NTIS HC A07/MF A01 CSCL21E RATIONALE AND DESCRIPTION OF A COORDINATED For abstract see N77-11046 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 N77-11O48*# AiResearch Mfg Co Phoenix Ariz The design for aircraft cockpit display systems is discussed in SMALL AXIAL COMPRESSOR TECHNOLOGY. VOLUME 1 detail The system consists of a set of three beam penetration F F Holman, J R Kidwell and T C Ware Jun 1976 185 p color cathode ray tubes (CRT) One of three orthogonal projects refs Sponsored in part by Army of the aircraft s state appears on each CRT which displays different (Contract NAS3-17846) views of the same information The color feature is included to (NASA-CR-134827-Vol-1 AiResearch-74-310862-Vol-1) Avail obtain visual separation of information elements The colors of NTIS HC A05/MF A01 CSCL21E red. green and yellow are used to differentiate control performance A scaled single-stage, highly-loaded axial-flow transonic and navigation information Displays are coordinated in information compressor was tested at speeds from 70 to 110% design and color B B 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 N77-11045# Lockheed-Georgia Co Marietta blade element performance At design speed and 1% tip clearance V/STOL AIRCRAFT NOISE PREDICTION (JET PROPUL the stage demonstrated an efficiency of 83 2% at 96 4% design SORS) Final Report. Jun 1974 - Jun 1975 flow and a pressure ratio of 1 865 Casing treatment increased N N Reddy D F Blakney J G Tibbets and J S Gibson design speed surge margin 20 points to 128% Overall Jun 1975 309 p refs Supersedes FAA-RD-73-145 performance was essentially unchanged An increase in rotor (Contract DOT-FA72WA-3099) running clearance to 2 2% with smooth casing reduced design (AD-A028765/6. LG75ER0054 FAA-RD-75-125 speed peak efficiency 5 7 points flow by 7 4% pressure ratio FAA-RD-73-145) Avail NTIS HC A14/MF A01 CSCL 01/3 to 1 740 and surge margin to 5 4% Reinstalling casing treatment A computer program is presented for predicting the noise regained 3 5 points in design speed peak efficiency 4 7% flow levels of V/STOL aircraft with jet-propulsive-lift systems Using increased pressure ratio to 1 800 and surge margin to 8 7% the equations developed in this report the noise levels may also Author 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 N77-11049*# AiResearch Mfg Co Phoenix Ariz let excess (core engine) high-lift system, airframe and auxiliary SMALL AXIAL COMPRESSOR TECHNOLOGY. VOLUME 2 power unit The computer program predicts the perceived noise Final Report levels and tone corrected perceived noise levels for V/STOL F F Holman J R Kidwell and T C Ware Jun 1976 329 p aircraft at any specified sideline distance for known geometrical Sponsored in part by Army and operational parameters Author (Contract NAS3-17846) (NASA-CR-134827-Vol-2 AiResearch-74-310862-Vol-2) Avail NTIS HCA15/MFA01 CSCL21E N77-11046*# AiResearch Mfg Co Phoenix Ariz Complete computer printout data are presented and suppor- COMPRESSOR BLADE SETTING ANGLE ACCURACY ting tests discussed in Volume I Author 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 N77-11050*# National Aeronautics and Space Administration (Contract NAS3-18024) Lewis Research Center Cleveland Ohio (NASA-CR-135068-Vol-1 AiResearch-73-311305-Vol-1) Avail SIMULATION OF FLIGHT-TYPE ENGINE FAN NOISE IN NTIS HC A06/MF A01 CSCL21E THE NASA-LEWIS 9X15 ANECHOIC WIND TUNNEL The aerodynamic test of a small single stage highly loaded M F Heidmann and D A Dietrich Nov 1976 24 p refs axial flow transonic compressor is covered The stage was modified Presented at the 92d Meeting of the Acoust Soc of Am San by fabricating a 24 blade rotor with mis-set blades in a repeating Diego. Calif 16-19 Nov 1976 pattern - two degrees closed from nominal, two degrees open (NASA-TM-X-73540 E-8972) Avail NTIS HC A02/MF A01 from nominal and nominal The unit was instrumented to determine CSCL 20A overall performance and average blade element data High- Flight type noise as contrasted to the usual ground static response dynamic pressure probes were installed to record test noise exhibits substantial reductions in the time unsteadiness pressure patterns at selected points in the flowpath Testing of tone noise and in the mean level of tones calculated to be was conducted at speeds from 70 to 94% of design equivalent nonpropagatmg or cut-off A model fan designed with cuttoff of speed with a conventional casing and also with circumferential the fundamental tone was acoustically tested in the anechoic grooves over the rotor tip Testing indicated severe performance wind tunnel under both static and tunnel flow conditions The penalties were incurred as a result of the mis-set bladmg Lower properties that characterize flight type noise were progressively flow pressure ratio, and efficiency were observed for the stage simulated with increasing tunnel flow The distinctly lobed with or without casing treatment Periodic pressure variations directivity pattern of propagating rotor/stator interaction modes were detected at every location where high response pressure was also observed Excess noise attributed to the ingestion of sensors were located and were directly related to bladmg the flow disturoances that prevail near most static test facilities geometry Author is substantially reduced with tunnel flow Author

35 N77-11051

N77-11051*# National Aeronautics and Space Administration sound pressure involves a 180 degree phase shift and an amplitude Lewis Research Center Cleveland. Ohio transfer function which varies approximately as frequency squared EFFECTS OF FORWARD VELOCITY ON NOISE FOR A J85 This is consistent with a simplified model using fluctuating entropy TURBOJET ENGINE WITH MULTITUBE SUPPRESSOR as a source term Author 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 N77-11054*# AiResea'ch Mfg Co Phoenix Ariz Soc of Am San Diego Calif 16-19 Nov 1976 STUDY OF SMALL TURBOFAN ENGINES APPLICABLE TO (NASA-TM-X-73542 E-8974) Avail NTIS HC A03/MF A01 SINGLE-ENGINE LIGHT AIRPLANES Final Report CSCL 20A G L Merrill Sep 1976 118 p refs Flight and wind tunnel noise tests were conducted using a (Contract NAS2-8582) J85 turbojet engine as a part of comprehensive programs to (NASA-CR-137944 AiResearch-76-211893) Avail NTIS obtain an understanding of forward velocity effects on jet exhaust HC A06/MF A01 CSCL 21E noise Nozzle configurations of primary interest were a 104-tube The design efficiency and cost factors are investigated for suppressor with and without an acoustically-treated shroud The application of turbofan propulsion engines to single engine general installed configuration of the engine was as similac as possible aviation light airplanes A companion study of a hypothetical in the flight and wind tunnel tests Exact simultaneous matcrvng engine family of a thrust range suitable to such aircraft and of engine speed exhaust velocity and exhaust temperature was having a high degree of commonality of design features and not possible and the wind tunnel maximum Mach number was parts is presented Future turbofan powered light airplanes can approximately 0 27 while the flight Mach number was ap- have a lower fuel consumption lower weight reduced airframe proximately 0 37 The nominal jet velocity range was 450 to maintenance requnements and improved engine overhaul periods 640 m/sec For both experiments background noise limited the as compared to current piston engined powered airplanes jet velocity range for which significant data could be obtained Achievement of compliance with noise and chemical emission In the present tests the observed directivity dnd forward velocity regulations is expected without impairing performance operating effects for the suppressor are more similar lo predicted trends cost or safety Author for internally-generated noise than unsuppressed jet noise Author N77-11055*$ National Aeronautics and Space Administration Washington D C N77-11052*)!' National Aeronautic"; and Space Administration AIRCRAFT FUEL CONSERVATION TECHNOLOGY TASK Lewis Research Center Cleveland Ohio FORCE REPORT. SEPTEMBER 10,1975 MACROSCOPIC STUDY OF TIME UNSTEADY NOISE OF 10 Sep 1975 141 p AN AIRCRAFT ENGINE DURING STATIC TESTS (NASA-TM-X-742951 Avail NTIS HC A07/MF A01 CSCL B J Clark M F Heidmann and W J Kreim Nov 1976 21E 14 p refs Presented at the 92d Meeting of the Acoustical An advanced technology program is described for reduced Soc of Am San Diego Calif 16-19 Nov 1976 fuel consumption in air transport Cost benefits and estimates (NASA-TM-X-73556 E-8995) Avail NTIS HCA02/MFA01 are given for improved engine design and components turboprop CSCL 20A propulsion systems active control systems laminar flow control Static tests of aircraft engines can exhibit greater than 10 db and composite primary structures A H random unsteadiness of tone noise levels because flow disturbances that prevail near test site facilities are ingested Presumably such changes are related to installation and test site features N77-11057*jj( National Aeronautics and Space Administration Some properties of unsteady noise observed during tests of a Lewis Research Center Cleveland Ohio Lycommg YF-102 turbofan engine are presented Time and spatial METHOD OF DISCRETE MODELING AND ITS APPLICA- variations in tone noise obta'ned from closely spaced far field TION TO ESTIMATION OF TF30 ENGINE VARIABLES and inlet duct microphones are displayed Long to extremely Dale J Arpasi and William M Bruton Oct 1976 40 p refs short intermittent tone bursts are observed Unsteadiness of the (NASA-TM-X-3443 E-8560) Avail NTIS HC A03/MF A01 tone its harmonics and the broadband noise show little similarity CSCL 21 E In the far field identity of tone bursts is retained over a directivity A method of discrete modeling is presented that effectively angle of less than 10 deg In the inlet duct tone bursts appear isolates steady state model accuracy from dynamic model to propagate axially but exhibit little circumferential similarity accuracy The steady state model may be generated from the They show only slight relationship to tone bursts observed in engine design equations with any desired degree of accuracy the far field The results imply an intermittent generation of The dynamic model is generated by applying a step disturbance random mixtures of propagating duct modes Author 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 N77-11053*# National Aeronautics and Space Administration is used to estimate various TF30-P-3 engine variables A dynamic Lewis Research Center, Cleveland Ohio trim function is developed to compensate for the dynamic CORE NOISE SOURCE DIAGNOSTICS ON A TURBOFAN nonlmearities of the variables as well as for inaccuracies in ENGINE USING CORRELATION AND COHERENCE dynamic definition The trim function is shown to be realted to TECHNIQUES the square root of the sum of the squares of the weighting Allen Karchmer and Meyer Reshotko 1976 27 p refs Presented factors obtained at various engine operating conditions Finally, at the ninety-second Meeting of the Acoust Soc of Am San the estimation of variables without dynamic modeling

~~36 N77-11066~~

Reports of progress during the past six months on the 21 N77-11064*# Boeing Aerospace Co Seattle Wash research programs comprising Project SQUID are presented The PRELIMINARY DESIGN-LIFT/CRUISE FAN RESEARCH research programs fall into the areas of Aerodynamics and AND TECHNOLOGY AIRPLANE FLIGHT CONTROL SYSTEM Turbomachmery Combustion and Chemical Kinetics Measure- Final Report ments and Turbulence Protect SQUID is a cooperative program Philip Gotheb. George E Lewis, and Leo J Little Nov 1976 of basic research related to jet propulsion It is administered by 106 p refs Purdue University and sponsored by the Office of Naval (Contract NAS2-9177) Research Author (GRA) (NASA-CR-137971 D180-20216-1) Avail NTIS HC A06/MF A01 CSCL 01C This report presents the preliminary design of a stability N77-11061/J New York Univ Westbury Aerospace and augmentation system for a NASA V/STOL research and Energetics Lab technology airplane This stability augmentation system is INVESTIGATION OF SLOT COOLING FOR HIGH-SPEED postulated as the simplest system that meets handling qualities AIRCRAFT Final Report. 1 Aug 1971 - 30 Sep 1975 levels for research and technology missions flown by NASA test Antonio Fern Dec 1975 23 p refs pilots The airplane studied in this report is a T-39 fitted with (Grant AF-AFOSR-2167-72. AF Pro) 6813 AF Pro) 9781) tilting lift/cruise fan nacelles and a nose fan The propulsion (AD-A024316 AFOSR-76-0505TR) Avail NTIS system features a shaft interconnecting the three variable pitch HC A02/MF A01 CSCL 21/5 fans and three power plants The mathematical modeling is based Active film cooling for gas turbine blades has been investiga- on pre-wmd tunnel test estimated data The selected stability ted Upstream injection at the leading edge and tangential injection augmentation system uses variable gams scheduled with airspeed downstream has been used to protect the blade GRA Failure analysis of the system illustrates the benign effect of engine failure Airplane rate sensor failure must be solved with redundancy Author N77-11062# Engelhard Minerals and Chemicals Corp Edison NJ Research and Development Dept HIGH TEMPERATURE THERMOCOUPLE SYSTEM FOR ADVANCED AIRCRAFT TURBINE ENGINES Final Technical N77-11065# Rockwell International Corp Columbus Ohio Report. 1 Aug 1974 - 31 Dec 1975 Aircraft Div D A Toenshoff and E D Zysk Wright-Patterson AFB Ohio DESIGN AND FABRICATION OF AN 8000 PSI CONTROL AFAPL 31 Dec 1975 109 p refs BY-WIRE ACTUATOR FOR FLIGHT TESTING IN A T-2 C (Contract F33615-74-C-2069 AF Proj 3066) AIRPLANE Final Report. 28 Mar 1975 - 5 Jan 1976 (AD-A025500 AFAPL-TR-75-108) Avail NTIS Joseph N Demarchi and Robert K Haning Jan 1976 45 p HC A06/MF A01 CSCL 21/5 refs This is a final report covering the development of a (Contract N62269-75-C-0311) temperature measuring system for the very high temperature (AD-A024487 NR76H-1. NADC-76049-30) Avail NTIS gas streams found in advanced jet engines The measurement HC A03/MF A01 CSCL 01/3 system is a thermocouple probe assembly suitable for interfacing This report describes the design and fabrication of an to the Detroit Diesel-Allison GMA 200 Joint Technology 8000 psi control-by-wire hydraulic rudder actuator for future flight Demonstration Engine Average temperatures of the order of testing in a T-2C airplane Actuator output is commanded by a 2600-2700F (1425-1480C) will have to be measured and it is single stage spool/sleeve valve driven directly by a permanent anticipated that hot spots to 3000F (1650C) will be encountered magnet force motor Actuator design criteria were based on This study covered the selection of an optimum thermocouple T-2C aerodynamic considerations and envelope constraints A (Pt-40% Rh vs Pt-0 6% Th02). compatible compensating system analysis was conducted to determine heat dissipation extension lead wire (base metal) usable to around 750C in air and hydraulic line sizes and routing Modifications required on (Nichrome vs EA 9R-682), high temperature resisting sheath the T-2C airplane to accommodate the test system installation and shield tube material (Pt-0 6% Th02) crushable MgO were outlined Author (GRA) insulation design of a temperature probe using the optimum materials and vibration testing at 1450C of one of the finished probes The selected probe passed the high temperature vibration test successfully GRA N77-11066# Instrument Flight Center Randolph AFB Tex HELICOPTER YAW AXIS AUGMENTATION INVESTIGA- N77-11063*# National Aeronautics and Space Administration TION Ames Research Center Moffett Field Calif William E Clark and Gabriel P Intano Mar 1976 147 p SIMULATION OF AN AUTOMATICALLY-CONTROLLED (AD-A024512 IFC-TR-76-3) Avail NTIS HC A07/MF A01 STOL AIRCRAFT IN A MICROWAVE LANDING SYSTEM CSCL 01/3 MULTIPATH ENVIRONMENT This investigation was conducted to document changes in Mitsuhiko Toda. Stuart C Brown and Clifford N Burrous Jul pilot performance and activity resulting from augmentation of 1976 42 p refs the helicopter yaw axis Subject pilot opinions regarding workload (NASA-TM-X-73154, A-6693) Avail NTIS HC A03/MF A01 and pilot acceptance of the concept of yaw augmentation were CSCL 17G also evaluated Eight highly qualif'ed instructor pilots were used The simulated response is described of a STOL aircraft to as data collection pilots These pilots flew profiles representing Microwave Landing System (MLS) multipath errors during final typical helicopter instrument maneuvers Each maneuver, except approach and touchdown The MLS azimuth elevation and DME for the instrument takeoff flown augmented only was flown multipath errors were computed for a relatively severe multipath first with the yaw-augmentation system engaged and then environment at Cnssy Field California utilizing an MLS multipath repeated without yaw-augmentation Objective and subjective simulation at MIT Lincoln Laboratory A NASA/Ames six-degree- data was obtained through the use of video audio, oscillograph of-freedom simulation of an automatically-controlled deHavil- recording equipment and m-flight and postflight questionnaires land C-8A STOL aircraft was used to determine the response and debnefmgs Due to the lack of large scale computer facilities to these errors The results show that the aircraft response to for objective data analysis, an interim report is being published all of the Cnssy Field MLS multipath errors was small The A final report utilizing correlation and regression analysis small MLS azimuth and elevation multipath errors did not result documenting cause and effect relationships will be published in any discernible aircraft motion and the aircraft response to when computer facilities are available The present interim report the relatively large (200-ft (61-m) peak) DME multipath was provides limited objective data analysis and project personnel noticeable but small Author interpretation of the subjective data Author (GRA)

~~37 N77-11068~~

N77-11068*# Bolt, Beranek, and Newman. Inc Cambridge. The mechanical properties of sandwich constructions for Mass F27 leading edges provided with faces of different glass fabric ACOUSTICAL EVALUATION OF THE NASA LANGLEY combinations were investigated Three-point bending tests were V/STOL WIND TUNNEL carried out on sandwiches built up with glass fabric No significant Istvan L Ver [1976] 45 p refs difference was found in mechanical strength and stiffness between (Contract NAS1-9559) the sandwiches tested Author (ESA) (NASA-CR-145087. Rept-2288) Avail NTIS HC A05/MF A01 CSCL 20A The results are presented of the acoustical measurements made to supply NASA Langley operating personnel with the N77-11186# Service Technique de I Aeronautique Paris (France) acoustical characteristics of the tunnel test section needed for Section Armements Missiles the planning of acoustical measurements and to identify the MILITARY ROCKET AIRCRAFT INHERENT CONSTRAINTS major noise sources The results of the preliminary measurements AND THEIR USES [LES ROQUETTES D'AVIATION of the spatial distribution of the sound field in the closed tunnel CONTRAINTES INHERENTES A LEUR UTILISATION] configuration indicate that the total sound power output of an Claude Sengeissen In AGARD Small Solid Propellant Rockets unknown sound source placed in the test section could most for Field Use Sep 1976 7p In FRENCH (For primary document probably be evaluated by measuring the sound pressure in two see N77-11185 02-28) properly chosen locations in the duct - one upstream and one Avail NTIS HC A06/MF A01 downstream of the test section However, it is recommended The capabilities and'disadvantages of aircraft launched that the practicability of this method of sound power output self-propelled rockets are discussed Transl by A H measurements be further investigated, preferably in a small scale model of the V/STOL Tunnel Author N77-11198*# Jet Propulsion Lab, Calif Inst of Tech Pasadena N77-11107*# McDonnell Aircraft Co St Louis Mo REDUCTION OF GASEOUS POLLUTANT EMISSIONS FROM GROUND TEST OF THE D SHAPED VENTED THRUST GAS TURBINE COMBUSTORS USING HYDROGEN- VECTORING NOZZLE ENRICHED JET FUEL Progress Report D W Esker 15 Oct 1976 83 p refs Richard M Clayton 15 Oct 1976 58 p refs (Contract NAS2-8663) (Contract NAS7-100) (NASA-CR-137959 MDC-A4434) Avail NTIS (NASA-CR-149146 JPL-TM-33-790) Avail NTIS HC A05/MF A01 CSCL 21 H HC A04/MF A01 CSCL 21 D Static ground tests of a large scale lift/cruise thrust vectoring Recent progress in an evaluation of the applicability of the nozzle were conducted to establish (1) vectoring performance hydrogen enrichment concept to achieve ultralow gaseous 'in and out of ground effect (2) thrust spoilage capability (3) pollutant emission from gas turbine combustion systems is compatibility of the nozzle with a turbotip fan, and (4) the nozzle described The target emission indexes for the program are 1 0 structural temperature distribution Vectoring performance of a for oxides of nitrogen and carbon monoxide, and 0 5 for unbumed short coupled vented nozzle design on a large scale (60%) hydrocarbons The basic concept utilizes premixed molecular basis was compared with small scale (4 5%) test nozzle results hydrogen, conventional jet fuel and air to depress the lean The test nozzle was a boilerplate' model of the MCAIR D flammability limit of the mixed fuel This is shown to permit vented nozzle configured for operation with the LF336/J85 very lean combustion with its low*NOx production while turbotip lift fan system Calibration of the LF336/J85 test fan simultaneously providing an increased flame stability margin with a simple convergent nozzle was performed with four different with which to maintain low CO and HC emission Experimental nozzle exit areas to establish reference thrust nozzle pressure emission characteristics and selected analytical results are ratio and nozzle corrected flow characteristics for comparison presented for a cylindrical research combustor designed for with the thrust vectoring nozzle data Thrust vectoring tests with operation with inlet-air state conditions typical for a 30 1 compression ratio high bypass ratio turbofan commercial the D vented nozzle were conducted over the range of vector Author angles between 0 and 117 deg for several different nozzle exit engine areas Author

N77-11111*# National Aeronautics and Space Administration N77-11207# Applied Systems Corp Vienna Va Ames Research Center. Moffett Field. Calif THE PRODUCTION AND REFINING OF CRUDE OIL INTO CONFERENCE ON THE DEVELOPMENT OF FIRE- MILITARY FUELS Final Report RESISTANT AIRCRAFT PASSENGER SEATS Herbert Bartick Kumar Kunchal Duane Switzer Robert Bowen Larry L Fewell Demetrius A Kourtides, Robert W Rosser, and and Rita Edwards Aug 1975 215 p refs John A Parker Aug 1976 130 p refs Conf held at Moffett (Contract N00014-75-C-0055) Field Calif. 19 Mar 1976 (AD-A024652) Avail NTIS HC A10/MF A01 CSCL 21/4 (NASA-TM-X-73144 A-6633) Avail NTIS HC A07/MF A01 The technical objectives of the program were to demonstrate CSCL 06K that a wide spectrum of military operational fuels derived from Papers are presented dealing with the development of aircraft shale oil crude could be obtained in a commercial industrial seats with the minimum fire risk Criteria examined include flame facility with minimum or minor modification, and to mcentivize spread, heat release, and smoke and/or toxic fumes Materials industry in oil shale development and technology Shale oil crude and performance specifications of all seat material options are was processed into gasoline heavy fuel oil and JP-4 in small provided Author laboratory quantities in the United States by the Bureau of Mines (ERDA) and private industry however no large scale commercial I refining of the shale oil crude into a wide variety of products had been attempted up until this program The various fuels produced met a majority of the military federal and commercial N77-11122# Royal Netherlands Aircraft Factories Fokker specifications requirements However these fuels tended to Schiphol-Oost | exhibit storage and thermal instabilities In addition the fuels CERTIFICATION OF THE REPLACEMENT OF GLASS contained a high wax content high paniculate matter and high FABRIC PER MAT SPEC 5670/1, WITH GLASS FABRIC gum content It is concluded that it is feasible to-obtain military PER MAT SPEC 5670 IN THE F27 PLASTIC SANDWICH and civilian operational fuels from shale oil crude using a WING-AND STABILIZER LEADING EDGES commercial refinery However additional effort has to be extended L M Godfned 12 May 1975 11 p / to overcome some refinery and operational problems to obtain (FOK-R-1876) Avail NTIS HC A02/MF A01 maximum yields and improved properties GRA

~~38 N77-11411~~

N77-11346*£f United Technologies Research Center, East N77-114O4*# Army Aviation Systems Command St Louis, Mo Hartford. Conn THE INVISCID PRESSURE FIELD ON THE TIP OF A BEARING RESTORATION BY GRINDING SEMI-INFINITE WING AND ITS APPLICATION TO THE 'Heinz Hanau R J Parker, E V Zaretsky S M Chen and FORMATION OF A TIP VORTEX Final Report Hubert L Bull 21 May 1976 94 p refs Presented at joint G F Hall S J Shamroth H McDonald, and W R Briley Army-NASA Seminar. St Louis 20-21 May 1976 Sponsored by NASA Washington NASA Oct 1976 84 p refs (Contract NAS1-12794) (NASA-CR-149188 AD-A025420 USAAVSCOM-TR-76-27) (NASA-CR-2748. Rept-36 300) Avail NTIS HC A05/MF A01 Avail NTIS HC A05/MF A01 CSCL 01/3 A joint program was undertaken by the NASA Lewis Research CSCL 01A A method was developed for determining the aerodynamic Center and the Army Aviation Systems Command to restore by loads on the tip of an infinitely thin, swept, cambered semi-infinite grinding those rolling-element bearings which are currently being wing at an angle of attack which is operating subsomcally in an discarded at aircraft engine and transmission overhaul Three inviscid medium and is subjected to a sinusoidal gust Under bearing types were selected from the UH-1 helicopter engine the assumption of linearized aerodynamics the loads on the tip (T-53) and transmission for the pilot program No bearing are obtained by superposition of the steady aerodynamic results failures occurred related to the restoration by grinding process for angle of attack and camber, and the unsteady results for The risk and cost of a bearing restoration by grinding programs the response to the sinusoidal gust The near field disturbance was analyzed A microecohomic impact analysis was performed pressures in the fluid surrounding the tip are obtained by assuming GRA a dipole representation for the loading on the tip and calculating the pressures accordingly The near field pressures are used to dnve a reduced form of the Navier-Stokes equations which yield the tip vortex formation The combined viscid-mviscid analysis is N77-11405# Royal Netherlands Aircraft Factories Fokker, applied to determining the pressures and examining the vortex Schiphol-Oost rollup in the vicinity of on unswept, uncambered wing moving RESEARCH ON ADHESIVE BONDING AND SURFACE steadily at a Mach number of 0 2 at an angle of attack of CHARACTERISTICS OF METALS AT FOKKER-VFW 0 1 rad The viscous tip flow calculation shows features expected R J Schliekelmann 16 Sep 1974 18 p refs in the tip flow such as the qualitatively proper development of (FOK-R-1816) Avail NTIS HC A02/MF A01 boundary layers on both the upper and lower airfoil surfaces In Background information is given about the research work addition, application of the viscous solution leads to the that has been carried out on various aspects of the strength generation of a circular type flow pattern above the airfoil suction and durability of adhesive bonded joints for aerospace applications surface Author That work includes studies on the relation between surface characteristics of metals and the durability of adhesion and corrosion resistance of bonded joints, the research and development on innovative nondestructive adhesion and cohesion testing methods, and adhesion characteristics of esteroil resistant paints N77-11356# Naval Ship Research and Development Center The capabilities in this field of the Fokker-VFW Technological Bethesda Md Aviation and Surface Effects Dept Center at Schiphol the Netherlands are given Author (ESA) ANALYSIS AND DESIGN OF EJECTOR DIFFUSER FOR OPTIMUM THRUST Tsze C Tai Mar 1976 29 p refs Presented at Navy Symp on Aeroballistics (1Oth) Fredencksbrurg Va, 15-17 Jul 1975 (AD-A025491. AERO-1214) Avail NTIS HC A03/MF A01 N77-11411# National Research Council of Canada. Ottawa CSCL 21/5 (Ontario) Oiv of Mechanical Engineering Recent advances in jet ejectors operating under static THE ROTATING STATOR CONCEPT EXPERIMENTAL conditions have produced high thrust augmentation that is feasible PERFORMANCE CHARACTERISTICS COMPARED WITH for application to V/STOL flight However because of (a) loss THE CONVENTIONAL COMPRESSOR in augmentation in duct flow (b) ramjet effect and (c) space M S Chappell D A J Millar and A A Swiderski Jul 1975 limitations high performance and compactness are required in 66 p refs the design of thrust-augmenting ejectors for V/STOL aircraft (AD-A024465. DME-ME-242 NRC-1915032) Avail NTIS An analytical inverse approach is presented in which the pressure HC A04/MF A01 CSCL 21/5 distribution along the diffuser wall of an ejector is defined for a The Small Compressor Research Program is a co-operative given entrance flow condition and the contour of the desired project between the National Research Council of Canada (NRC) diffuser wall is determined by using a finite difference technique and Rolls Royce (Canada) Limited (RR) Its objectives are to The prescribed pressure distribution is first optimized by a modified investigate both analytically and experimentally, the Fanstat Stratford criterion for incipient separation of turbulent boundary concept of compressor spooling This concept involves the layers this optimization makes it applicable to compressible co-rotation of both rotor and stator rows of a compressor in two-dimensional and axisymmetnc flows GRA the core engine with the fan being mounted on, and driven by the rotating stator case The primary function of the fan and stat is to provide an aerodynamic gearbox' that will permit the fan and the fan turbine to run close to their individual optimum speeds so overcoming the mismatch in blade speeds inherent in direct-coupled fan-turbine spools of high-bypass ratio turbofan engines Previous reports have described preliminary experimental N77-11365*# California Univ. Los Angeles Mechanics and calibrations of the conventional three-stage axial compressor Structures Dept from which the Fanstat compressor was derived and a HOLOGRAPHIC FLOW VISUALIZATION Final Report hybrid-computer model of the rotating stator compressor test A F Charwat and M E Fourney Nov 1976 47 p refs rig The current report describes a more-detailed calibration of (Grant NsG-268) this conventional compressor and presents the performance (NASA-CR-149182 UCLA-ENG-76105) Avail NTIS characteristics of the co-rotating compressor configuration The HC A03/MF A01 CSCL 14E test results confirmed aerodynamic feasibility of the Fanstat Holographic visualization techniques are presented of the arrangement of compressor spooling and major performance vortex wake of a lifting wing The motions of tracer particles in parameters were not significantly different from the compressor vortical flows are described along with the development of a in the useful operating region Flow range and surge behavior liquid-drop tracer generator An analysis is presented of the motion of the co-rotating compressor were examined and although of particles of arbitrary density and size in solid body and potential somewhat unusual at various speeds did not indicate any vortex flows M C F serious limitat.ons on the applicability of the concept GRA

~~39 N77-11412~~

on the Relative Miners rule and the corresponding tests results N77-11412# North Carolina State Univ, Raleigh Engineering could to a laige extent be explained by the action of residual Design Center stresses a suitable correction was introduced The correction TRANSIENTS IN TURBOCOMPRESSORS Final Report Jan was applied to the specimens of this investigation using empirically 1975 - Fob 1976 derived data The results pioved an effective refinement of the J N Perkins. L W Hardin F 0 Carta (United Technol Res Relative Miners rule leading to very accurate life predictions Center. East Hartford Conn) and W C Griffith Feb 1976 Author (ESA) 49 p refs (Grant AF-AFOSR-2802-75. AF Pro| 9781) (AD-A024275 EDC-76-1 AFOSR-76-0501TR) Avail NTIS HC A03/MF A01 CSCL 21/5 N77-11447# Ldboratorium fuer Betriebsfestigkeit Darmstadt This report describes the work done between the Spring of (West Germany) 1975 and February 1976 on a cooperative program between COMPILATION OF MEASURES TO INCREASE THE North Carolina State University and the United Technologies FATIGUE STRENGTH OF AIRCRAFT STRUCTURES Research Center The effect of unsteady flow on compressor D Schuetz and J J Gerharz 5 Nov 1975 96 p refs In performance is being investigated experimentally in the UTRC GERMAN ENGLISH summary Large Scale Rotating Rig and theoretically at NCSU with a (LBF-TB-126/75) Avan NTIS HC A05/MF A01 Lab fuer refined computer-based flow model The goal of the program is Betnebsfestigkeit Darmstadt West Ger DM 42 to provide improved predictive techniques for use in turbocompres- The compilation is the result of a literature survey and was sor design based upon an improved understanding of the basic made to comprehensive!/ imorm the designer and to facilitate coupling between distorted inlet flow the onset and disappearance the selection of suitable measures for a fatigue critical struc- of rotating stall, and compressor stage performance The tural detail Together with the description of the measures, diameter is 5 ft with the maximum rotational speed of improvement factors are presented which should be used only 600 rpm The blade chord of 6 in coupled with an inlet as lead values A total of 40 compilations of structures such as velocity of 100 ft/sec gives a blade RE approx 0000005 eye rods open holes and riveted screw joints are presented Upstream screens provide a 20% sinusoidal variation in axial Author (ESA) velocity once per revolution Rotating instrumentation will measure steady and unsteady surface pressures on the rotor blade the boundary layer behavior on the blade, and will allow a complete investigation of the 3-D properties of the near wake of the rotor Stationary frame measurements will include mean and N77-11449# Royal Netherlands Aircraft Factories Fokker transient inlet and downstream conditions A 45 channel slipnng Schiphol Oost assembly with on-board excitation and amplification electronics FRACTURE TOUGHNESS OF 8mm 2024-T3 NON CLAD developed under this program will give high quality signals on PLATE WITH LONG CENTRAL CRACKS 18 transient data channels A refined theoretical flow model A H LaCrois 2 Jun 1975 9 p has been developed at NCSU for use in data irterpretation (FOK-R-1879) Avail NTIS HC A02/MF A01 with runs planned for early spring The program is continuing Fracture toughness tests were carried out with center under a follow-on contract with the AFOSR Author (GRA) 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 N77-11441/JI Schweizeribcher Verband fuer die Matenalpruefung using the Feddersen method The Feddersen method for presenting der Technik (SVMT) Duebendorf (Switzerland) fracture toughness test results is briefly described ESA MECHANISM OF MATERIAL FATIGUE DURING THE CRACK INITIATION STAGE [ZUM MECHANISMUS DER MATERIALERMUEDUNG IM VORRISS STADIUM] J Branger and E Stemheil 1976 19 p refs In GERMAN (ICAF-DOC-895) Avail NTIS HC A02/MF A01 N77-11450/jf National Aerospace Lab , Amsterdam 'Netherlands) Full scale fatigue tests by fatigue-history loading were Structures and Materials Div performed with the aim to fly military A/C up to the limit of CALCULATION OF VIBRATION MODES AND RESONANCE their structural capacity and to extend the service life by statistical FREQUENCIES OF THE NORTHROP NF-5 fatigue tests of a critical safe-life element The first analyses of H H Ottens 15 Apr 1975 71 p refs Supersedes NLR-TR- fatigued light alloy specimens revealed in surface layers down 74012-U Sponsored by Directorate of Mater Air RNLAF to about 30 nm concentrations of metal hydroxides increasing (NLR-TR-75050-U NLR-TR-74012-U) Avail NTIS with increasing fatigue straining Similar concentrations were HC A04/MF A01 analyzed in steel specimens Author 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 N77-11445# Laboratorium fuer Betriebsfestigkeit Darmstadt involve full tiptanks 70 Ibs stores at the outboard pylons full (West Germany) or empty 275 USG tanks at the inboard pylons and a 150 USG APPLICATION OF DESIGN DATA DERIVED FROM FATIGUE tank at the center line pylon For these configur-tions a TESTS WITH SERVICE-LIKE LOAD SEQUENCES FOR LIFE comparison was made with ground vibration test results ESA PREDICTION D Schuetz and H Lowak 16 Feb 1976 61 p refs In GERMAN ENGLISH summary Sponsored by Bundesrr>n fuer Verteidigung N77-11478# Air Force Flight Dynamics Lab. Wright-Patterson (LBF-FB-109/76) Avail NTIS HC A04/MF A01 i_ab fuet AFB. Ohio B- .'Mebsfesl'okei' ^a.m^adt W»T be' OM 38 CURRENT PRACTICE ON ESTIMATING CRACK GROWTH Reliable 'ife 11 ,ves- were HSTab ishcd for a ioad sequence and a DAMAGE ACCUMULATION WITH SPECIFIC APPLICATION cumulative frequency LJis[nbu~'on v^nch ate t/pical at the wing TO STRUCTURAL SAFETY DURABILITY AND RELIABILITY structure of transport aircraft The life estimation for details Final Report. 15 Jan - 15 Mar 1975 subjected to load spectra varying from that applied to the Howard A Wood Joseph Gallagher Robert M Engle and John specimens were demonstrated using the Relative Miner s rule M Potter Jan 1976 67 p refs It was found that for large differences between the test load (AF Proj 1367) and the design load spectra the Relative Miner's rule is not (AD-A025499. AFFDL-TR-75-32) Avail NTIS advantageous As the difference between the estimated life based 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) FEBRUARY 1977~~

~~Typical Subject Index Listing~~

SUBJECT TITLE rH HEADING EXTENSION ~l BODHABIC LOADS 1 L Early operation experience on the EBDA/HASA 100 ADHESIVE BOBDIHG vind turbine rotor blade loa " Besearch on adhesive bonding and surface [HASA-TH-I-71601] M77-10640 characteristics of metals at Fokker-VPH [FOK-B-1816] H77-11U05 AEBODTHAHIC BALABCE ieight and balance considerations in the design of REPORT ACCESSION the A-10A close air support aircraft TITLE NUMBER NUMBER [SAHE PAPEB 1104] ' 477-12183 AEBODIHAHIC CHABACTEBISTICS Practical requirements in industry --- in computerized aerodynamic calculations for aircraft A77-12552 The title is used to provide a description of the subject matter When the title is Methods studies on system identification from insufficiently descriptive of the document content a title extension is added transient rotor tests separated from the title by three hyphens The NASA or AIAA accession number [HASA-CB-1 37965] B77-10005 is included m each entry to assist the user in locating the abstract in the abstract High supersonic aerodynamic characteristics of section of this supplement If applicable a report number is also included as an five irregular planform wings vith aid in identifying the document 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 A-7 AIBCBAFT cyclic variations of the velocity vector Full temperature range protective system for [AAAF-NT-76-20] 1177-10019 fastener areas of carrier-based naval aircraft Prediction Methods for Jet V/STOL Propulsion [AD-A024523] N77-10210 Aerodynamics, volume 1 A-10 AIBCBAFT [AD-A024022] 1177-10068 Height and balance considerations in the design of Prediction Methods for Jet V/STOL Propulsion the A-10A close air support aircraft Aerodynamics, volume 2 [SAKE PAPER 1104] A77-12183 [AD-A024023] B77-10069 ABLATIVE BA1EBIALS Lifting surface theory for rectangular wings Strength of glass-fibre-reinforced plastics at B77-10347 one-sided heating aircraft ablative thermal Application of the nonlinear vortex-lattice protection coatings concept to aircraft-interference problems [IAF PAPIB 76-200] A77-10939 N77-10349 ACODSTIC ATTEHUATIOH An application of the suction analog for the Inlet noise suppressor design metnod based upon analysis of asymmetric flow situations the distribution of acoustic power with mode N77-10350 cutoff ratio Inverse transonic airfoil design including viscous N77-10311 interaction ACOUSTIC BEASDBEBESIS 1177-10354 Signal-treatment methods during aircraft-engine Advanced transonic aerodynamic technology inspection based on vibroacoustic noises B77-10365 A77-11603 Calculation of the longitudinal aerodynamic Additional experiments with a four-bladed cyclic characteristics of wing-flap configurations with pitch stirring model rotor, part 2 of second externally blown flaps yearly report [NASA-CB-2705] N77-11006 tNASA-CB-137966J S77-10006 Small axial compressor technology, volume Acoustical evaluation of the NASA Langley V/STOL [NASA-CB-13I4827-VOL-1 ] N77-11048 wind tunnel Small axial compressor technology volume 2 --- [NASA-CR-1450d7] S77-11068 tables ACOUSTIC FBOPEBIIES [NASA-CR-134827-VOL-2] 1177-11049 Acoustical evaluation of the NASA Langley V/STOL AEBODYBABIC COEFFICIENTS wind tunnel Performance of steady and intermittent blowing jet [NASA-CR-145087] N77-11068 flaps and spanwise upper surface slots ACOUSTIC SCATTERING [AD-A024364 ] N77-10027 Measurement of wake vortex strength by Deans of AEBODYBABIC COSPIGOBATIONS acoustic back scattering Anisotropic radiatively coupled wedge flow A77-11712 A77-10218 ACTDATOBS Structural tests of aerodynamic surfaces - A Design and fabrication of an 8000 PSI systems approacn to analysis and design control-by-wire actuator for flignt testing in a A77-12206 T-2 C airplane Methods for elliptic pronlams in external [AD-A02UU87] N77-11065 aerodynamics ADAPTIVE CONTB01 A77-12554 The stochastic control of the F-8C aircraft using The impact of emissions standards on the design of the multiple model adaptive control /HMAC/ method aircraft gas turbine engine combustors A77-12428 [NASA-TH-X-73490] N77-10063 Application or Liapunov model - Tracking parameter A computational system for aerodynamic design and identification for tne Cri-47 helicopter analysis of supersonic aircraft. Part 2: A77-12460 User's manual [NASA-C8-2716] 1177-11005 AEBODINABIC fOBCBS SUBJECT INDEX

AEBOD'NUBIC FOBCES Air-cooled turbine cascade effectiveness criterion Forces on unstaggered airfoil cascades in unsteady A77-12503 in-phase motion Analytic and experimental study of turbine rotor [ASBE P4PEB 76-FE-S] 477-10851 blade temperature An investigation of the effect on aerodynamic A77-12522 forces caused by the addition of end plates to Emissions of an AVCO Lycoming 0-320-DIAD air helicopter rotor blades cooled light aircraft engine as a function of [AD-A0235I11] H77-10024 fuel-air ratio, timing, and air temperature and AEBODIHAHIC HEATIBG humidity Strength of glass-fibre-reinforced plastics at [BASA-TH-X-73500] N77-10058 one-sided heating aircraft ablative thermal AIB FLOB protection coatings Computational methods and problems in aeronautical [IAF PAPIB 76-200] A77-10939 fluid dynamics Book ABHODYSiBIC IHTEBFEBEHCB A77-12551 Applications of linearised supersonic wing theory Some problems of unsteady flow about aircraft to the calculation of some aircraft interference A77-12560 flows AIB INTAKES A77-12566 Transonic performance of Hach 2.65 auxiliary flow AEBODYHAHIC LOADS . axisynmetric inlet Early operation experience on the ERDA/NASA 100 kw [N4SA-CB-2747] N77-10056 wind turbine rotor blade loads AIB JETS [NASA-TB-X-71601] N77-10640 Laser air-jet engine earth-based pulse AEBODYNABIC BOISE radiation created thrust A test facility for aircraft jet noise reduction. II A77-11887 A77-118i(t AIB NAVIGATION Experiments on the feasibility of aero-acoustic Concorde navigation measurements in the 3-ffl low speed wind tunnel A77-10200 of the DFVIB-AVA AIB POLLUTION [ESA-TT-311] N77-10873 The fuel approach to control emissions from aircraft ABBODYNAHIC STABILITY [IAF PAPEB 76-111] A77-10911 Mechanism of stabilization of the 'separation Experimental clean combustor program: Noise study point1 of a vortex during flow of a stream at [NASA-CB-135106] N77-1Q064 low subsonic velocity over a delta wing AIB TBAFFIC CONTBOL [NAS4-TT-F-17283 ] N77-10012 Reliability of automated flight service stations The design, analysis and testing of a low budget A77-10442 wind tunnel flutter model with active LH2 airport requirements study aerodynamic controls, volume 2 £NASA-CB-2700] N77-10032 [AD-A024480] N77-10090 The establishment of safe separations between AERODYNAMICS aircraft in flight Project SCUID: 4 cooperative program of [NLB-BP-75041-0] N77-11020 fundamental research related to jet propulsion AIB TBANSPOBTATION [AD-A02«001] N77-11059 Beyond supersonic transport ABBOELASTICITY [IAF PAPEB ISL-76-66] A77-10972 On the identification of state-derivative-coupled Transport progress in practice: Air transport in systems Africa - East African Airways Corporation A77-12448 Experience Aeroelastic analysis for helicopter rotor blades A77-11312 with time-variable, non-linear structural twist Responsibilities and assurances with regard to and multiple structural redundancy: cargo transport - Air transport law Hathematical derivation and program user's manual A77-12472 [NASA-C8-2638] N77-10556 An analysis of tne intrastate air carrier AERONAUTICAL ENGINEERING regulatory forum. Volume 2: Technical report Aircraft fuel conservation technology. Task force [AD-A023762] N77-10035 report, September 10, 1975 Baseline energy forecasts and analysis of [NAS4-TH-X-74295] 877-11055 alternative strategies for airline fuel AEROSPACE ENGINEERING conservation Application of optimality criteria to automated [PB-255351/9] S77-10690 structural design Toward new heights air transportation in the A77-10207 Soviet Union AEROSPACE MEDICINE [NASA-TT-F-17248 ] N77-11019 Investigation and analysis of the huaan factors in AIBCBAFT ACCIDENT INVESTIGATION aircraft accidents Investigation and analysis of the human factors in 477-10500 aircraft accidents AEBOTHEBHODYHAHICS A77-10500 Air-cooled turbine cascade effectiveness criterion AIBCBAFT ACCIDENTS 477-12503 Competition for airspace - Bird strikes and AFBICA aircraft operations Transport progress in practice: Air transport in A77-11261 Africa - East African Airways Corporation AIBCBAFT BRAKES experience Development of aircraft brake materials 477-11312 [ASLE PREPRINT 76-LC-1B-3] A77-11195 AFTERBURNING AIBCBAFT COHPABTBBHTS Experimental study ot combusticn time in two-stage Tnermal analysis of flight vehicle compartment combustion process structure A77-12511 A77-12509 AILERONS AIBCBAFT CONFIGURATION Optimal control for tne rolling pullout maneuver Height and balance considerations in the design of of a modern fighter aircraft the A-10A close air support aircraft 477-12444 [SArfE PAPER 1104] A77-12183 AIB CABGO Advanced design composite aircraft, the next step nesponsiDillties and assurances with regard to for composites cargo transport - Air transport law [SAKE PAPEB 1105] A77-12184 A77-12472 The next-generation subsonic transport AIB COOLIBG [SAKE PAPEB 1127] A77-12195 Pressure loss coefficient of impingement cooled AIBCBAFT CONTBOL leading edge system of a turbipe blade Optimal ride control for the Twin Otter, STOL A77-10772 aircraft Film cooling with injection through slots 477-10336 A77-10773

~~A-2 SUBJECT INDEX AIBCBAFI HODELS~~

Effects of atmospheric conditions on the operating Emissions of an AVCO Lycoming 0-320-DIAD air characteristics of supersonic cruise aircraft cooled light aircraft engine as a function of [IAF PaPEB 76-112] 477-10912 fuel-air ratio, timing, and air tenperature and The stochastic control of the P-8C aircraft using humidity the multiple model adaptive control /MBAC/ method [SASA-TM-X-73500] N77-10058 477-121428 Advanced combustion techniques for controlling NO Design considerations for laminar flow control sub x emissions of high altitude cruise aircraft aircraft [NASA-TM-X-73473] N77-10062 N77-10366 Effect of air temperature and relative humidity at Design of active controls for the NASA F-8 digital various fuel-air ratios on exhaust emissions on xly-by-wire airplane a per-mode basis of an Avco Lycoming 0-320 DI4D 077-10377 'light aircraft engine. Volume 2: Individual Performance analysis of flexible aircraft with data points active control [N4S4-TB-X-73507] N77-10066 N77-10378 Performance of 1.15-pressure-ratio fan stage at AIBCBAFT DESIG8 several rotor olade setting angles with reverse Israel's pride of Lions Kfiv fighter aircraft flow program [NASA-TB-X-3451] N77-11008 477-10521 AIBCBAFT FOE1 SYSTEMS YC-14 - All blow and no puff general design The fuel approach to control emissions from aircraft details [IAF PAPEE 76-111] 477-10911 477-10525 Aircraft fuel conservation technology. Task force Application of circulation control rotor report, September 10, 1975 technology to a stopped rotor aircraft design [NASA-TM-X-74295] N77-11055 X-wing V/STCL Seduction of gaseous pollutant emissions from gas A77-11277 turbine coDbustors using hydrogen-enriched jet 'C.221, the new French target drone fuel 477-11625 [N4S4-CH-1191U6] N77-11198 Estimating procedures associated with aircraft 4IECB4FI FUELS modifications Survey of hydrogen energy application projects [SANE PAPEE 1101] 477-12131 477-12778 Fuselage analytical weight estimation method Hydrogen-fueled subsonic aircraft: A perspective [SAHE PAPEE 1102] 477-12182 N77-10344 Weight and balance considerations in the design of AIBCBAFT H4Z4BDS the &-10A close air support aircraft Bird hazards to aircraft: Problems and prevention [SAhE PAPEE 1101] A77-12183 of bird/aircraft collisions Book Advanced design composite aircraft, the next step 477-10697 for composites AIBCBAFT HIDB40LIC SYSTEHS [SAKE PAPEE 1105] A77-12184 Reliability applied to landing gear and hydraulics Application of advanced technology to future A77-12116 long-range aircraft AIBCBAFI INOUSIBI [SAHE PAPEB 1126] A77-12194 Co-operation in the European aircraft The next-generation subsonic transport manufacturing industry and among the scheduled [SAWE PAPEB 1127] 477-12195 airlines /Brancker Memorial Lecture/ Thermal analysis of flight vehicle compartment 477-11311 structure Practical requirements in industry in 477-12509 computerized aerodynamic calculations for aircraft Practical requirements in industry in 477-12552 computerized aerodynamic calculations for aircraft AIBCBAFT INSTBOHBBTS 477-12552 Investigation into tae optimum use of advanced Transonic flows calculation by integral displays in future transport aircraft equation, relaxation and finite difference metnods A77-11594 477-12561 AIBCBAFT LANDING 4 transonic hodograph theory for aerofoil design Simulating the last 100 ft computer-generated 477-12561 images for landing training The technical basis for a national civil aviation A77-10648 research, technology, and development /BT & D/ Application of the nonlinear vortex-lattice policy; Proceedings of the Workshop Conference, concept to aircraft-interference problems Crystal City, Va., (larch 10-12, 1976 H77-10349 1 477-12927 A flight investigation of piloting techniques and 4n analytical study for subsonic oblique wing crosswind limitations during visual STOL-type transport concept landing operations [NAS4-CB-137896] - N77-10045 [NASA-TN-D-8284] N77-11001 An analytical study for subsonic oblique wing Landing practices of general aviation pilots in transport concept single-engine light airplanes [NAS4-CB-137897] N77-10046 [NASA-TN-D-8283] N77-11033 Inverse transonic airfoil design including viscous AIBCBAFI MAINTENANCE interaction Interface between maintainability and commercial 1177-10354 aircraft spares support Preliminary sizing and performance evaluation of 477-101483 supersonic cruise aircraft Maintaining transport aircraft [N4S4-TM-X-73936] N77-11031 A77-12069 4IBC64FT ENGINES Concorde maintenance as seen by the designer - The Future trends in aero gas turbine design. II - maintenance program Unconventional engines 477-12115 477-11595 Bearing restoration by grinding Signal-treatment methods during aircraft-engine [N4SA-CB-149188] N77-11404 inspection based on vibroacoustic noises AIBCBAFT BAHBUVEBS 477-11603 Optimal control for the rolling pullout maneuver Magnetic particle inspection of aviation engine of a modern fighter aircraft vanes 477-12444 A77-11606 The pursuit-evasion problem of two aircraft in a Dynamic-stress-data management for aeromechanical horizontal plane testing of turbomachinery 477-12452 477-12175 AIBCBAFT MODELS Equation solution accuracy in calculating jet On the identification of state-derivative-coupled engine characteristics systems 477-12502 A77-12448

~~A-3 AIRCRAFT BOISE SUBJECT INDEX~~

New buffeting acquisition methods data An extended integral equation method for the acquisition, military aircraft steady transonic flow past a two-dimensional [AAAF-NT-76-8] " N77-10051 aerofoil A wind tunnel captive aircraft testinq technique A77-12562 PAD-A023690] .177-11037 A transonic nodograph theory for aerofoil design AIRCRAFT NOISE A77-12561 Rotational noise measurement in a wind tunnel by AIRFOILS total sampling synchronization The development of a computer aided airfoil design A77-11281 procedure including preliminary wind tunnel New developments in Dloun flap noise technoloqy experiments on a low Reynolds number hign lift [NASA-CH-115086] N77-10013 section, volume 1 V/STOL aircraft noise prediction (jet prcpulsors) [AD-A021361 ] N77-10028 computer program Test verification of a transonic airfoil design UD-A028765/6] N77-11015 employing active diffusion control AIRCRAFT PEHFOBHANCE [AD-A021297] N77-10029 YC-11 - All blow and no puff general design Inverse transonic airfoil design including viscous details interaction A77-10525 N77-10351 Concorde - Endurance flights results Viscous interaction with separation in transonic A77-12111 flow Final approach performance monitor [NASA-TT-F-17187] N77-10997 [AD-A028513/0] N77-11021 AIHFRAHE MATERIALS AIRCRAFT PILOTS Mechanism of material fatigue during the crack Rationale and description of a coordinated cockpit initiation staye display for aircraft flight management [ICAF-DOC-895] N77-11141 [NASA-TH-X-3157] N77-11011 AIHFRAHES AIRCRAFT BELIABI1ITI Design mecnanical properties, fracture toughness, Helicopter reliability growth evaluation fatigue properties, exfoliation and [AD-A025265] N77-11011 stress-corrosion resistance of 7050 sheet, AIRCRAFT SAFETY plate, hand forgings, die forgings and extrusions Aircraft ground fire suppression and rescue [AD-A024609] N77-10195 systems. Characteristics of kinematic jet fuel Calculation of multi-contour thin-walled fires cascading and rod fuel geometries structures by the method of sections [AD-A024117] N77-11022 [NAS»-TT-F-17281] N77-11029 Rationale and description of a coordinated cockpit AIRLINE OPERATIONS display for aircraft flight management Concorde navigation [NASA-TH-X-3457] N77-1KW4 A77-10200 Conference on the Development of Fire-Resistant Interface between maintainability and commercial Aircraft Passenger Seats aircraft spares support [NASA-TM-X-73111 ] N77-11111 A77-10183 AIRCRAFT STABILITY Competition for airspace - Bird strikes and Advanced control systems for helicopters aircraft operations A77-11273 A77-11261 A rfing on the SA.341 Gazelle helicopter and its Co-operation in the European aircraft efrects manufacturing industry and among the scheduled A77-11282 airlines /Brancker Memorial Lecture/ AIRCRAFT STRDCTDBES A77-11311 Resizing procedure for structures under combined Transport progress in practice: Air transport in mechanical and thermal loading Africa - East African Airways Corporation A77-10211 Experience Strength of glass-fibre-reinforced plastics at A77-11312 one-sided heating aircraft ablative thermal Aircraft loadaoility parameters - Some results of protection coatings an airline survey [IAF PAPER 76-200] A77-10939 [SAKE PAPER 1116] A77-12201 Estimating fatigue-crack lives for aircraft - An exploratory study to determine the integrated Techniques technological air transportation system ground A77-11177 requirements of liguid-hydrogen-fueled subsonic, On the identification of state-derivative-coupled long-haul civil air transports systems [NASA-CH-2699] N77-10033 A77-12118 AIRPORT PLANNING Hingtip vortex dissipator for aircraft LH2 airport requirements study [NASA-CASE-LAR-11615-1] N77-10001 [NASA-CB-2700] N77-10032 Compilation of measures to increase the fatigue AIRPORTS strength of aircraft structures Competition for airspace - Bird strikes and [LSI-IB-126/75] N77-11117 aircraft operations Current practice on estimating crack growth damage A77-11261 accumulation with specific application to AIRSPACE structural safety durability and reliaoility The establishment of safe separations between [AD-A025199] N77-11178 aircraft in flight AIRCRAFT BAKES [NLR-HP-75011-U] N77-11020 Measurement of wake vortex strength by means of AIRSPEED acoustic back scattering Army preliminary evaluation YOH-58A helicopter A77-11712 with a flat-plate canopy Effects of jets, wakes, and vortices on lifting [AD-A021501] N77-11039 surfaces Effects of forward velocity on noise for a J85 [NASA-TM-X-73971] H77-10998 turbojet engine with multitube suppressor from Development of predictive wake vortex transport wind tunnel and flight tests model for terminal area wake vortex avoidance [NASA-TH-X-73512] H77-11051 [AD-A029019/1] 1177-11002 ALGOL Holographic flow visualization of aircraft wakes Program system for computer calculations of jet [NASA-CR-119182] N77-11365 engine characteristics Russian book AIRFOIL PROFILES A77-10349 Approximate transonic profile flow with shock ALL-BEATHEH LANDING SYSTEBS A77-10251 A systems approach to all weather landings Some problems of unsteady flow about aircraft A77-10138 A77-12560 ALDHINOH ALLOTS Strength of compressor wheels of low-ductility alloys A77-10383

~~A-4 SUBJECT IBDBI BOEOB-BPOII COBCOOIDS~~

Design mechanical properties, fracture toughness, Compressor blade setting angle accuracy study. fatigue properties, exfoliation and Volute 2: Data compilation stress-corrosion resistance of 7050 sheet, [HASA-CB-135068-VOL-2] ^ H77-11047 plate, hand forgings, die forgings and extrusions AIIAL STBESS [AD-A021609] 877-10195 Resizing procedure for structures under combined ABALOG COHPOTBBS mechanical and thermal loading Analog coaputation assessoent of the risk of A77-102"ia structural failure due to crack growth under AIISVBHBTBIC FLO! random loading Compressible snbcritical flow through axially [AD-A025266] 877-11012 syaaetric sharp-lipped orifices and nozzles ABBCHOIC CHAHBEBS A77-12555 A test facility for aircraft jet noise reduction. II transonic perfomance of Hach 2.65 auxiliary flow A77-11844 axisyaoetnc inlet SmBlation of flight-type engine fan noise in the [HASi-C8-2747] H77-10056 NASA-Lewis 9115 anechoic wind tunnel [BASA-TH-X-73540] H77-11050 AHGLE OF AltiCK B Experimental investigation of the boundary layer BACKSCATTBBIBG on a rotating cylinder Measurement of wake vortex strength by Beans of A77-10208 acoustic back scattering Pressure distributions over frontal /nose/ A77-11712 surfaces of bodies of revolution in transonic BALL BEABIHGS flow at angles of attack of 0 to 10 deg Bearing restoration by grinding A77-10664 [HASA-CB-149188] 877-11101 Influence of aircraft angle of attack on high G BASE BEATIBG cockpit design Normal impingement of a supersonic jet on a plane: [AD-A025083] 877-11043 A basic study of shock-interference heating ABGULAB BESOLOTIOB [AD-A021511] 877-10026 Compressor blade setting angle accuracy study, BEBDIBG DIAGBAHS volume 1 An experimental study of the nonlinear stiffness [BASA-CB-135068-VOL-1] B77-11046 of a rotor blade undergoing flap, lag and twist A8ISOTBOPIC PLOIDS deformations Anisotropic radiatively coupled wedge flow [BASA-CB-137969] 877-10009 A77-10218 BIBLIOGBAPHIES AHISOIBOPI Compilation of measures to increase the fatigue Investigation of a bearingless helicopter rotor strength of aircraft structures concept having a composite primary structure [LBF-TB-126/75J M77-11147 [NASA-CB-2637] N77-10044 BIBD-AIBCBAFI COLLISIOBS A8IISaBHABI§B RABFABE AIBCB&F1 Bird hazards to aircraft: Problems and prevention Catapult launch fatigue investigation of the model of bird/aircraft collisions Book S-2 E airplane A77-10697 [AD-A024071] H77-11038 Competition for airspace - Bird strikes and ATHOSPBEBIC HODELS aircraft operations Development of predictive wake vortex transport A77-11261 model for terminal area wake vortex avoidance BLADE TIFS [AD-A029049/4] 877-11002 An experimental study of the nonlinear stiffness ATHOSPBEBIC 1EBFBBAIOBE of a rotor blade undergoing flap, lag and twist Emissions of an AVCO Lycoming 0-320-DIAD air deformations cooled light aircraft engine as a function of [BASA-CB-137968] 877-10008 fuel-air ratio, timing, and air temperature and BLOBING humidity Three-component measurements on a model of a light [NASA-TH-X-73500] 877-10058 STOL aircraft with chordwise blowing ATBOSPBEBIC TDBBOIEHCE [ESA-TT-299] 877-10052 Effects of atmospheric conditions on the operating BLOB! BODIES characteristics of supersonic cruise aircraft Flow of a radiating gas over a blunt body with [IAF PAPEB 76-112] A77-10912 intense vaporization ATTITDDB COBTE01 A77-10416 The stochastic control of the F-8C aircraft using BO-105 BELICOPTBB the multiple model adaptive control /HHAC/ method Uingeless rotor dynamics in high speed flight A77-12428 A77-11280 ATTITDDE STABILITY BOATTAILS Dual-spin spacecraft dynamics under conditions of An improved projectile boattail, part 2 a rotating unbalanced platform and rotor asymmetry [AD-A024073] 877-11016 [IAF PAPEB 76-019] A77-10882 BODIES OF BBVOLOTIOB AUTOMATIC COBTBOL Pressure distributions over frontal /nose/ Reliability of automated flight service stations surfaces of bodies of revolution in transonic A77-10442 flow at angles of attack of 0 to 10 deg Display/control reguirements for vrOL aircraft A77-10664 [BASA-CB-145026] 877-11030 Flow interaction near the tail of a body of AOTOHATIC PILOTS revolution. I - Plow exterior to boundary layer Effects of atmospheric conditions on the operating and wake characteristics of supersonic cruise aircraft [ASHE PAPEB 76-PE-B] A77-10855 [IAF PAPEB 76-112] A77-10912 Flow interaction near the tail of a body of AVAILABILITY revolution. II - Iterative solution for flow Reliability of automated flight service stations within and exterior to boundary layer and wake A77-1014I42 [ASaE PAPEB 76-FE-N] A77-10856 AVIOHICS BOEIBG AIBCBAFT Estimating procedures associated with aircraft TC-14 - All blow and no puff general design modifications details [SAME PAPEE 1101] A77-12181 A77-10525 AXIAL PLOR BOBDIBG A note on the acoustic effect of non-uniformly Advances in engineering science, volume 1 distributed stator rows [NASA-CP-2001-VOL-1] N77-10230 A77-10347 BOBOB-BPOXI COHFODBDS Compressor blade setting angle accuracy study, Program for establishing long-time flight service volume 1 performance of composite materials in the center [NASA-CE-135068-VOL-1] 877-11046 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 CANTILEVER BBABS An integral equation method for boundary An experimental study of the nonlinear stiffness interference in a perforated-nail wind tunnel at of a rotor blade undergoing flap, lag and twist transonic speeds deformations [AD-A023U93] N77-10023 [NASA-CB-137969] H77-10009 Test verification of a transonic airfoil design CANTILE7EB BBHBBBS employing active diffusion control Application of optimality criteria to automated [AD-A02U297] N77-10029 structural design BOUNDABY LAYBB EQUATIONS A77-10207 The hypertoolicity of integral equations of CABBON FIBEB BEINFOBCED PLASTICS momentum in a three-dimensional incompressible Theoretical and experimental investigations on laminar boundary layer landing gear spring blades out of fiber A77-10665 reinforced plastic for small aircraft BOUNDARY IAYBB FLOI [ESA-TT-312] S77-10162 Flow interaction near the tail of a body of CARBURETORS revolution. I - Flow exterior to boundary layer Effect of air temperature and relative humidity at and wake various fuel-air ratios on exhaust emissions OB [ASMS PAPEB 76-FE-fl] A77-10855 a per-mode basis of an Avco Lycoming 0-320 DIAD Some problems of unsteady flow about aircraft light aircraft engine. Volume 2: Individual A77-12560 data points Supersonic flows numerical computation for [NASA-TB-X-73507] N77-10066 steady inviscid flowfield CABGO AIBCBAFT A77-12565 Application of advanced technology to future BOONDABY 1AYBB SEEABATION long-range aircraft Controlled and uncontrolled flow separation in [SA8E PAPEE 1126] A77-12191 three dimensions CABBIEBS [LB-591] N77-10999 An analysis of the Intrastate air carrier BOUNDARY LATEB STABILITY regulatory forum. Volume 1: Summary report Experimental investigation of the boundary layer [AD-A023761] N77-10031 on a rotating cylinder CASCADE FLOH A77-10208 Unsteady pressure distributions on oscillating BODNDAHY LAYEB TRANSITION airfoils in a supersonic cascade Experimental investigation of the boundary layer A77-10771 on a rotating cylinder Forces on unstaggered airfoil cascades in unsteady A77-10208 in-phase motion BODNDABY LAYEBS [ASME PAPEB 76-FE-S] A77-10854 Influence of wind tunnel wall boundary layers on Lifting-surface theory of straight cascades of two dimensional transonic tests swept blades [AAAF-NT-76-13] 877-10083 A77-12218 BOUNDARY VALUE PBOBLEHS Finite element and difference methods for cascades Thermal analysis of flight vehicle compartment A77-12557 structure CASCADE RIND TUNNELS A77-12509 Two-dimensional cold-air cascade study of a A transonic hodograph theory for aerofoil design film-cooled turbine stator blade. 3: Effect of A77-12564 hole size on single-row and multlrow ejection BUFFETING [NAS4-TM-X-3H12] • N77-11007 Buffeting problems leading and trailing edge CATAPULTS flow separation Fatigue investigation of the E-2B/C nose landing [AAAF-NT-76-7] N77-10050 gear New buffeting acquisition methods data [AD-A02I4072] N77-11010 acquisition, military aircraft CATHODE BAI TUBES [AAAF-NT-76-8] N77-10051 Rationale and description of a coordinated cockpit BDBNING TIME display for aircraft flight management Experimental study of combustion time in two-stage [NASA-TM-X-3457] N77-110t4 combustion process CAOCBY INTEGRAL FORHULA A77-12511 Lifting surface theory for rectangular wings BYPASSES N77-10347 Selection cf compressor pressure ratio of small CENTBIFOGAL COBPBESSOBS GTE installed in bypass turbojet engine fan duct Centrifugal compressor and pump stability, stall A77-12513 and surge; Proceedings of the Conference, New Orleans, La., March 22-25, 1976 A77-10026 The effect of rotor blade wakes on centrifugal C-130 AIBCBAFT compressor diffuser performance - A comparative Full temperature r ange protective system for experiment fastener areas o f carrier-based naval aircraft A77-10032 [AD-A024523) N77-10210 Experimental investigation of the near-surge flow Program for establishing long-time flight service in a high performance centrifugal compressor performance of composite materials in the center A77-10036 wing structure o f C-130 aircraft. Phase 1: Strength of compressor wheels of low-ductility Ground/flight acceptance tests alloys [NASA-CS-1150i)3] N77-11032 A77-10383 C-1U1 AIBCBAFT CH-17 HELICOPTEB Test verification of a transonic airfoil design Application of Liapunov model - Tracking parameter employing active diffusion control identification for the CH-47 helicopter [AD-A021297] N77-10029 A77-12160 CALIFOBHIA CUEHICAL COMPOSITION An analysis of the Intrastate air carrier Development of aircraft brake materials regulatory forum Volume 1: summary report [ASLE PREPRINT 76-LC-1B-3] A77-11195 [AD-A023761 ] N77-10034 CIVIL AVIATION CAMBBBED KINGS Concorde navigation Applications of linearised supersonic wing theory A77-10200 to the calculation of some aircraft interference Beyond supersonic transport flows [IAF PAPER ISL-76-66] A77-1Q972 A77-12566 Co-operation in the European aircraft CANOPIES manufacturing industry and among the scheduled Aray preliminary e valuation YOH-58A helicopter airlines /Brancker Memorial Lecture/ with a flat-plat e canopy A77-11311 [AD-A024501] N77-11039

~~A-6 SUBJECT INDEX COHPDTEBIZED DESIGN~~

Transport progress an practice: Air transport in Design considerations for laminar flow control Africa - East African Airways Corporation aircraft Experience N77-10366 A77-11312 digh speed computer studies of vortex motions in Reliability applied to landing gear and hydraulics relation to aircraft wake turbulence A77-12116 [AD-A024290] 877-11013 Aircraft loadability parameters - Some results of COMPOSITE BAIEBIALS an airline survey Advanced design composite aircraft, the next step [SAVE PAPEB 1116] A77-12201 for composites New orientations of intergovernoental [SAKE PAPEE 1105] A77-12181 organizations of civil aviation Program for establishing long-time flignt service A77-12«70 performance of composite materials in the center The technical basis for a national civil aviation wing structure of C-130 aircraft. Pnase U: research, technology, and development /BT 6 D/ Ground/flight acceptance tests policy; Proceedings of the Workshop Conference, [BASA-CH-145043] N77-11032 Crystal city, Va., March 10-12, 1976 Development of a graphite horizontal stabilizer A77-12927 [AD-A023767] N77-11036 An analysis of the Intrastate air carrier High temperature thermocouple system for advanced regulatory forum. Volume 1: Summary report aircraft turbine engines [AD-A023761] N77-10031 [AD-A025500] N77-11062 An analysis of the intrastate air carrier COHPOSIIE STBDCTUEES regulatory forum. Volume 2: Technical report Investigation of a bearingless helicopter rotor [AD-A023762] N77-10035 concept having a composite primary structure Civil uses of remotely piloted aircraft [NASA-CR-2637 ] N77-10014 [NASA-CB-13789U] N77-100K7 COBPBESSIBLB FLOW Civil uses of remotely piloted aircraft Compressible subcritical flow through axially [NASi-CR-137895] N77-10018 symmetric sharp-lipped orifices and nozzles Toward new heights air transportation in the A77-12555 Soviet Union COBPBESSOB BLADES [NASA-TT-F-172148 ] N77-11019 Compressor blade setting angle accuracy study, CLIMBING FLIGHT volume 1 Best-range flight conditions for cruise-climb [NASA-CB-135068-VOL-1J H77-110"6 flight of a jet aircraft Compressor blade setting angle accuracy study. N77-10379 Volume 2: Data compilation COCKPITS [NiSA-CR-135068-VOL-2] N77-11047 Investigation into the optimum use of advanced COHPBESSOB BOTOBS displays in future transport aircraft The rotating stator concept. Experimental A77-1159

~~A-7 COBPDTEBIZED SIMULATION SUBJECT INDEX~~

Practical requirements in industry in COOLING SYSTEMS computerized aerodynamic calculations for aircraft Air-cooled turbine cascade effectiveness criterion A77-12552 A77-12503 The development of a computer aided airfoil design COBBOSION TESTS procedure including preliminary wind tunnel riot corrosion studies of four nickel-base experiments on a low Reynolds number high lift superalloys: B-1900, NASA-TRH VIA, 713C and IN738 section, volume 1 [NASA-TM-X-73479] N77-10183 [AD-A024361] N77-10023 COST ANALYSIS COMPOTEBIZED SIH01ATIOB B. 6 D. project cost and schedule realism - A risk Simulating the last 100 ft computer-generated analysis approach images for landing training A77-12455 477-10648 LCC analysis of flight recorder for F-4 Mild Eguation solution accuracy in calculating jet Weasel aircraft engine characteristics [AD-A023830] N77-10512 477-12502 COST EFFECTIVENESS Simplified simulation models for control studies Civil uses of remotely piloted aircraft of turbojet engines [NASA-CB-137894] N77-10047 [NASA-CB-149107] N77-10061 CBACK PBOPAGATION High speed computer studies of vortex motions in Estimating fatigue-crack lives for aircraft - relation to aircraft wake turbulence Tecnniques [AD-4024290] N77-11013 A77-11477 COHCOBDE AIBCBAFT Advances in engineering science, volume 1 Concorde navigation [NAS4-CP-2001-VOL-1] N77-10230 A77-10200 Analog computation assessment of the risk of Concorde - Endurance flights results structural failure due to crack growth under 477-12114 random loading Concorde maintenance as seen by the designer - The [4D-A025266] N77-11042 maintenance program Current practice on estimating crack growth damage A77-12115 accumulation with specific application to CONDUCTIVE HEAT TBAfiSFEH structural safety durability and reliability Thermal analysis of flight vehicle compartment [AD-A025499] N77-11478 structure CBACKING (FBACTOBIHG) 477-12509 Magnetic particle inspection of aviation engine CONFEBENCES vanes Centrifugal compressor and pump stability, stall A77-11606 and surge; Proceedings of the Conference, New CBACKS Orleans, La., March 22-25, 1976 Fracture toughness of 8mm 2024-13 non clad plate A77-10026 with long central cracks European Hotorcraft and Powered Lift Aircraft [FOK-B-1879] H77-11449 Forum, 1st, University of Southampton, CBOSS FLOB Southampton, England, September 22-24, 1975, Penetration and mixing of liguid injected into Proceedings supersonic transverse gas stream 477-11276 A77-12515 The technical basis for a national civil aviation CHDCIFOBM SINGS research, technology, and development /BT & D/ Application of circulation control rotor policy; Proceedings of the Workshop Conference, technology to a stopped rotor aircraft design Crystal City, Va., March 10-12, 1976 X-wing V/STOL 477-12927 A77-11277 Prediction Methods for Jet V/STOL Propulsion CBODE OIL Aerodynamics, volume 1 The production and refining of crude oil into [AD-A024022] N77-10068 military fuels Prediction Methods for Jet V/STOL Propulsion [AD-A024652] N77-11207 Aerodynamics, volume 2 CBDISING FLIGHT [4D-4024023] N77-10069 Effects of atmospheric conditions on the operating Advances in engineering science, volume 1 characteristics of supersonic cruise aircraft [NASA-CP-2001-VOL-1] N77-10230 [IAF P4PEB 76-112] 477-10912 Conference on the Development of Fire-Besistant Best-range flight conditions for cruise-climb Aircraft Passenger Seats flight of a jet aircraft [NASA-TM-X-73144 ] N77-11111 N77-10379 COBFIGOB4TIOB HAHAGEMEHT CBYOGBBIC EQDIPHEST Conceptual designs for a modular remotely piloted The cryogenic wind tunnel vehicle H77-10368 [AD-A023844] N77-11035 CBYOGEHIC FLUID STORAGE COHTOOBS An exploratory study to determine the integrated Calculation of multi-contour thin-nailed technological air transportation system ground structures by the method of sections requirements of liguid-hydrogen-fueled subsonic, [NASA-TT-F-17284] N77-11029 long-haul civil air transports COHTBOL COHFIGOBED VEHICLES [NASA-CB-2699] N77-10033 Application of Liapunov model - Tracking parameter identification for the CH-47 helicopter A77-12460 COHTBOL SIHDLAT10B DATA ACQUISITION Simplified simulation models for control studies New buffeting acquisition methods data of turbojet engines acquisition, military aircraft [NASA-CB-149107] 877-10061 [AAAF-NT-76-8] N77-10051 COHTBOL SUBFACES DATA COBBELATIOH The design, analysis and testing of a low budget Critical analysis of comparisons between flight wind tunnel flutter model with active test results and wind tunnel test predictions in aerodynamic controls, volume 2 subsonic and supersonic transport aircraft [AD-A024480] N77-10090 [NASA-TT-F-17185] N77-10049 CONTBOLLEBS DATA HANAGEHEHT Linear regulator design for stochastic systems by Dynamic-stress-data management for aeromechanical a multiple time scales method testing of tnrbomachinery [NASA-CB-149099] H77-10432 477-12175 COiVECTIVE FLOM DC 10 AIBCBAFT The influence of vortex shedding on the generation Interface between maintainability and commercial of sound by convected turbulence aircraft spares support A77-10197 A77-10

~~A-8 SUBJECT IBOEX BIGIIB DBSIGI~~

Haintaining transport aircraft DIBASIC PBOGBAHHIIG 477-12069 Computational alternatives to obtain time optimal DBFORBAIIOB jet engine control j An experimental study of the nonlinear stiffness [SASl-CB-149106] - B77-10060 of a rotor blade undergoing flap, lag and twist DTBABIC BBSPOHSB deforaations Botor dynamic state and paraaeter identification [HASA-CB-137968] H77-10008 from simulated forward flight transients, part 2 DELTA ilBGS [BASA-CB-137961] B77-10004 Free vortex sheets Hethods studies on system identification from A77-12559 transient rotor tests Applications of linearised supersonic ving theory [BASA-CB-137965] B77-10005 to the calculation of some aircraft interference Additional experiments with a four-bladed cyclic flows pitch stirring model rqtor, part 2 of second A77-12566 yearly report Hechanism of stabilization of the 'separation [HASA-CB-137966] 877-10006 point* of a vortex daring flow of a stream at DTBABIC STBDCTDBAL A1ALTSIS low subsonic velocity over a delta wing Beducing vibration-by structural modification [HASA-TT-F-17283] H77-10012 helicopter fuselage model Vortex/jet/wing viscous interaction theory and A77-11279 analysis Calculation of vibration modes and resonance t*D-A025290] H77-11017 frequencies of the Horthrop HF-5 DESIGB ABALISIS [HLB-TB-75050-U] H77-11U50 Design considerations for laminar flow control aircraft H77-10366 Analysis and design of ejector diffuser for B-2 AIBCBAFT optimum thrust Fatigue investigation of the E-2B/C nose landing [AD-A025U91] H77-11356 gear DIFFEBB8TIAL IBEBBAL 4BA1ISI3 CAD-A024072] H77-11040 Thermal analysis of flight vehicle compartment BCOHOMIC AHiLTSIS structure Civil uses of remotely piloted aircraft A77-12509 [HASA-CB-137895] H77-10048 DIFFOSEBS BISBH7ALOES The effect of rotor blade wakes on centrifugal Eigenvalue/eigenvector control via spectral compressor diffuser performance - A conparative characterization - An application to helicopter experiment hover dynamics A77-10032 A77-10338 Study of flow swirl influence on axiradial EIGBHVECTOBS diffuser effectiveness Eigenvalue/eigenvector control via spectral A77-12520 characterization - An application to helicopter DIGITAL COBPOTEBS hover dynamics Terminal area guidance along curved paths: A A77-10338 stochastic control approach BJEC10BS H77-10383 Analysis and design of ejector diffuser for DIGITAL TECBBIQQES optimum thrust Dynamic-stress-data management for aeromechanical [AD-A025491 ] H77-11356 testing of turbomachinery ELEVATORS (COHTBOL SOBFACES) A77-12175 Optimal control for the rolling pullout maneuver DISPLAT DEVICES of a modern fighter aircraft Simulating the last 100 ft computer-generated A77-12444 images for landing training EHISSIOB SPECTBA A77-10648 The impact of emissions standards on the design of Investigation into the optimum use of advanced aircraft gas turbine engine combustors displays in future transport aircraft [HASA-TH-X-73490] H77-10063 A77-11594 EHD PLATES Display/control reguirements for VIOL aircraft An investigation of the effect on aerodynamic [HASA-CR-145026] N77-11030 forces caused by the addition of end plates to Rationale and description of a coordinated cockpit helicopter rotor blades display for aircraft flight management [AD-A023541] N77-10024 [NASA-TH-X-3457] N77-11044 EBEBGT COBSEBVAIIOB DBAG BEDOCTIOI Aircraft fuel conservation technology. Task force An improved projectile boattail, part 2 report, September 10, 1975 [AD-A02U073] N77-11016 [.NASA-TH-X-74295] H77-11055 DBOHE AIBCBAFT EHBBGI DISSIPATIOB VTOL RPVS - A technology assessment wingtip vortex dissipator for aircraft A77-12000 [NASA-CASE-LAR-11645-1] N77-10001 DDAL SPIH SPACECBAFT EHBBGI POLICY Dual-spin spacecraft dynamics under conditions of Baseline energy forecasts and analysis of a rotating unbalanced platform and rotcr asymmetry alternative strategies for airline fuel [IAF PAPEB 76-019] A77-10882 conservation DOCTED PLOM [PB-255351/9] H77-10690 The finite element method applied to fluid mechanics BNBHGI STOBAGE A77-12558 Survey of hydrogen energy application projects DTBABIC CBABftCTBBISTICS A77-12778 Method of discrete modeling and its application to BHBfiGT TECHHOLOGT estimation of TF30 engine variables Design consideration for the Darrieus rotor [NASA-TH-X-3443 ] 877-11057 wind turbines DTBABIC COBTBOL A77-12872 Simplified simulation models for control studies BBGIBS COBTBOL of turbojet engines Method of discrete modeling and its application to [NASA-CR-149107] N77-10061 estimation of TF30 engine variables DTBABIC BODBLS [8ASA-TM-X-3443] N77-11057 Additional experiments with a four-bladed cyclic EBGIBE DESIGB pitch stirring model rotor, part 2 of second £xpenmental investigation of the near-surge flow yearly report in a high performance centrifugal compressor [NASA-CB-137966] N77-10006 A77-10036 Hethod of discrete modeling and its application to Program system for computer calculations of jet estimation of TF30 engine variables engine characteristics Russian book [SASA-TH-X-3443] N77-11057 A77-10349

~~A-9 BIGIH IILBTS SDBJEC1 IND3I~~

High-nickel alloys for gas turbines High temperature thermocouple system for advanced 477-11325 aircraft turbine engines Future trends in aero gas turbine design. II - [AD-A025500] N77-11062 Unconventional engines Seduction of gaseous pollutant emissions from gas A77-11595 turbine combustors using hydrogen-enriched jet Signal-treatment methods during aircraft-engine fuel inspection based on vibroacoustic noises [NASA-CB-119116] N77-11198 A77-11603 BXPEBIHEHIAL DESIGN Equation solution accuracy in calculating jet Conceptual designs for a modular remotely piloted engine characteristics vehicle A77-12502 [40-4023811] N77-11035 Heat-pipe regenerator for gas turbine engine BXTEBSALLI BLOiN FLAPS 477-12528 New developments in blown flap noise technology Two-phase turbine engines using gas-liquid [NASA-CB-115086] N77-10013 mixture accelerated in nozzles Noise generating by interaction between subsonic A77-12680 jets and blown flaps Supersonic variable-cycle engines [DLB-FB-76-20] N77-10067 [NASA-TB-X-73521] 1177-10059 ENGINE ISLETS Inlet noise suppressor design method based upon the distribution of acoustic power with mode t-H AIBCHiFl cutoff ratio LCC analysis of flight recorder for F-4 mid N77-10311 Heasel aircraft ENGINE NOISE [4D-4023830] N77-10512 Experimental clean combustor program: Noise study F-5 AIBCHAFT [NASA-CB-135106] N77-10061 Calculation of vibration modes and resonance Simulation of flight-type engine fan noise in the frequencies of the Northrop NF-5 NASA-Lewis 9X15 anechoic wind tunnel [NLB-TB-75050-U] N77-11450 [NASA-TH-X-73510] N77-11050 F-8 AIBCBAFT Effects of forward velocity on noise for a J85 The stochastic control of the F-8C aircraft using turbojet engine with multitube suppressor from the multiple model adaptive control /MHAC/ method wind tunnel and flight tests 477-12128 [NASA-TB-X-73512] N77-11051 Design of active controls for the N4SA F-8 digital Macroscopic study of time unsteady noise of an fly-by-wire airplane aircraft engine during static tests N77-10377 [NASA-TH-X-73556] N77-11052 Linear regulator design for stochastic systems by Core noise source diagnostics on a turbofan engine a multiple time scales method using correlation and coherence techniques [NASA-CB-119099] S77-10132 [NASA-TB-X-73535] N77-11053 F-15 4IBCB4FT ENGINE TESTS A wind tunnel captive aircraft testing technique Dynamic-stress-data management for aeromechanical [AD-A023690] N77-11037 testing of turbomachinery F-27 AIBCB4FT A77-12175 Certification of the replacement of glass fabric System considerations for reliable strain data per mat. spec. 5.670/1, with glass fabric per from gas turbine engines mat. spec. 5.670 in the F27 plastic sandwich A77-12176 wing-and-stabilizer-leading edges noting Supersonic variable-cycle engines shear strength and sandwich stiffness [NASa-TH-X-73521] N77-10059 [FOK-B-1876] N77-11122 ENGINES FABBICATION High temperature thermocouple system for advanced Design and fabrication of an 8000 PSI aircraft *urbine engines control-by-wire actuator for flight testing in a [AD-A025500] N77-11062 T-2 C airplane ENVIBONHEHTAL SOBVEIS [AD-A021487] N77-11065 Baseline energy forecasts and analysis of F4BBICS alternative strategies for airline fuel Certification of the replacement of glass fabric conservation per mat. spec. 5.670/1, with glass fabric per [PB-255351/9] N77-10690 mat. spec. 5.670 in the F27 plastic sandwich ESTIMATING wing-and-stabilizer-leading edges noting Methods studies on system identification from shear strength and sandwich stiffness transient rotor tests [FOK-B-1876] N77-11122 [NASA-C8-137965] N77-10005 FANS E7AFOB4TION Simulation of flight-type engine fan noise in the Flow of a radiating gas over a blunt body with NASA-Lewis 9X15 anechoic wind tunnel intense vaporization [NASA-TB-X-73510] N77-11050 A77-10416 FATIGUE (BATEBIALS) EVASIVE ACTIOSS Investigation of a faearingless helicopter rotor The pursuit-evasion problem of two aircraft in a concept having a composite primary structure horizontal plane [NASA-CH-2637] N77-10011 A77-12M52 Design mechanical properties, fracture toughness, EXBADST DIFFDSEBS fatigae properties, exfoliation and Analysis and design of ejector diffuser for stress-corrosion resistance of 7050 sheet, optimum thrust plate, hand forgings, die forgings and extrusions [AD-A025H91 ] N77-11356 [4D-A021609] N77-10195 EXHAUST GASES F4TIGOE LIFE • Emissions of a

~~A-10 SUBJECT IHDEX PLIGHT TESTS~~

Current practice on estimating crack growth damage FIXED RINGS accumulation with specific application to Controlled and uncontrolled flow separation in structural safety durability and reliability three dimensions [AD-A025U99] H77-11178 [LF-591] N77-10999 F4TIGOE TESTS FLAPPIHG Dispersion of fatigue test data for cast Botor dynamic state and parameter identification, gas-turbine blades in association uith from simulated forward flight transients, part 1 structural and technological factors [BASA-CB-137963] H77-10003 A77-12579 FIAT PLATES Catapult launch fatigue investigation of the model Army preliminary evaluation YOH-58A helicopter S-2 E airplane with a flat-plate canopy [AD-A021071 ] N77-11038 [AD-A021501 ] N77-11039 Mechanism of material fatigue during the crack FLEXIBLE BODIES initiation stage Performance analysis of flexible aircraft with [ICAF-DOC-895] N77-11111 active control Application of design data derived from fatigue B77-10378 tests mth service-like load sequences for life FLIGHT CHABACTEBISTICS prediction wing structures of transport On the status of V/STOL flight aircraft N77-10367 [LBF-FB-109/76] N77-11415 FLIGHT CONDITIONS FEEDBACK COHTBOL Best-range flight conditions for cruise-climb Eigenvalue/eigenvector control via spectral flight of a jet aircraft characterization - An application to helicopter N77-10379 hovej dynamics FLIGHT COHTBOL A77-10338 Effects of atmospheric conditions on the operating FIGBTEB AIBCBAFT characteristics of supersonic cruise aircraft Israel's pride of Lions Kfiv fighter aircraft [IAF PAPEB 76-112] A77-10912 program On the status of V/STOL flight A77-10521 N77-10367 Optimal control for the rolling pullout maneuver Preliminary design-lift/cruise fan research and of a modern fighter aircraft technology airplane flight control system 477-12141 [NASA-CB-137971] H77-11061 The pursuit-evasion problem of two aircraft in a Helicopter yaw axis augmentation investigation horizontal plane [AD-4021512 ] N77-11066 477-12152 FLIGHT ISSTBOHENTS Results of recent NASA studies on automatic spin Investigation into the optimum use of advanced prevention for fighter aircraft displays in future transport aircraft N77-10381 A77-11594 Military rocket aircraft: Inherent constraints FLIGHT PATHS and their uses Terminal area guidance along curved paths: A N77-11186 stochastic control approach FILB COOLIBG N77-10383 Film cooling with injection through slots FLIGHT BECOBDEBS A77-10773 LCC analysis of flight recorder for F-4 Wild Two-dimensional cold-air cascade study of a weasel aircraft film-cooled turbine stator blade. 3: Effect of [AD-A023830] N77-10512 holo s^ze on single-row and multirow ejection FLIGHT BOLES [NASA-TM-X-3412] N77-11007 Design of active controls for the NASA F-8 digital Investigation of slot cooling for high-speed fly-by-wire airplane aircraft N77-10377 [AD-A02U316] N77-11061 FLIGHT SAFBTI FIHITB DIFFEBEICB THBOBI A systems approach to all weather landings Analytic and experimental study of turbine rotor 477-10138 blade temperature FLIGHT SIMULATION A77-12522 Structural tests of aerodynamic surfaces - 4 Methods for elliptic problems in external systems approach to analysis and design aerodynamics 477-12206 A77-12554 Botor dynamic state and parameter identification, Compressible subcritical flow through anally from simulated forward flight transients, part 1 symmetric sharp-lipped orifices and nozzles [NASA-CB-137963] N77-10003 A77-12555 Botor dynamic state and parameter identification Subsonic flows in turbomachines from sinulated forward flight transients, part 2 477-12556 [NAS4-CB-137961] N77-10001 Finite element and difference methods for cascades Besults of recent NAS4 studies on automatic spin 477-12557 prevention for fighter aircraft Transonic flows calculation by integral S77-10381 equation, relaxation and finite difference methods FLIGHT SIHDLATOBS 477-12561 Simulating the last 100 ft computer-generated Advances in engineering science/ volume 1 images for landing training [NASA-CP-2001-VOL-1] H77-10315 477-10618 FINITE BLEHEIT METHOD FLIGHT TESTS Finite element and difference methods for cascades A systems approach to all weather landings A77-12557 477-10138 The finite element method applied to fluid mechanics Hingeless rotor dynamics in high speed flight 477-12558 477-11280 Calculation of gas-turbine engine blades by the A wing on th<3 SA.311 Gazelle helicopter and its finite element method effects 477-12583 477-11282 Advances in engineering science, volume 1 Concorde - Endurance flights results [NASA-CP-2001-VOL-1] N77-10315 477-12111 Calculation of vibration modes and resonance Critical analysis of comparisons between flight frequencies of the Horthrop NF-5 test results and wind tunnel test predictions in [HLB-TB-75050-0] H77-11<150 subsonic and supersonic transport aircraft FIBE FIGBTIIG [N4S4-TT-F-17185] H77-10019 Aircraft ground fire suppression and rescue Besults of recent N4S4 studies on automatic spin systems. Characteristics of kinematic jet fuel prevention for fighter aircraft fires cascading and rod fuel geometries H77-10381 [AD-A021417] 877-11022

~~4-11 FLOS CHABACTEBISTICS SUBJECT INDEX~~

A fli-ght investigation of piloting techniques and FBEE JETS crosswind limitations during visual STOL-type Noise generating by interaction between subsonic landing operations jets and blown flaps [NASA-TN-D-82814] 1177-11001 [DLB-FB-76-20] 1177-10067 FLOI CHABACTEBISTICS FUEL CO8BDSTIOH Transonic performance of Hach 2.65 auxiliary flow Experimencal study of combustion time in two-stage axisyametnc inlet combustion process [NASA-CR-27117] N77-10056 A77-12511 FLO» COEFFICIENTS FUEL CONSUMPTION An application of the suction analog for the The fuel approach to control emissions from aircraft analysis of asymmetric flow situations [IAF PAPEB 76-111] A77-10411 N77-10350 Eguation solution accuracy in calculating jet FLOI OISIBIB01IOH engine characteristics Approximate transonic profile flow with shock A77-12502 A77-10251 Transonic flow theory of airfoils and wings supersonic flows numerical computation for N77-10351 steady mviscid floufield Baseline eiergy forecasts and analysis of A77-12565 alternative strategies for airline fuel Applications of linearised supersonic wing theory conservation to the calculation of some aircraft interference [PB-255351/9] N77-10690 flows FOEL-AIB BATIO A77-12566 Emissions of an AVCO Lycoming 0-320-DIAD air The AFFDL-Bielsen flow-field study cooled light aircraft engine as a function of [AD-A023755] H77-11015 fuel-air ratio, timing, and air temperature and FLOI HEASUBEHENT humidity Experimental investigation of the near-surge flow [NASA-TS-X-73500] N77-10058 in a high performance centrifugal compressor Effect of air temperature and relative humidity at A77-10036 various fuel-air ratios on exhaust emissions on FLOI STABILITY a per-mode basis of an Avco Lycoming 0-320 DIAD Centrifugal compressor and pump stability, stall light aircraft engine. Volume 2: Individual and surge; Proceedings of the Conference, New data points Orleans, La., March 22-25, 1976 [NASA-TM-X-73507] N77-10066 A77-10026 FUSELAGES FLOI THEOBI Reducing vibration by structural modification Subsonic flows in turbomachines helicopter fuselage model A77-12556 A77-11279 FLOW VISUALIZATION Fuselage analytical weight estimation method Penetration and mixing of liguid injected into [SAyE PAPEB 1102] A77-12182 supersonic transverse gas stream Catapult launch fatigue investigation of the model A77-12515 S-2 E airplane Holographic flow visualization of aircraft wakes [AD-A021071 ] N77-11038 [NASA-CH-119182] N77-11365 FLUID DYNAMICS Computational methods and problems in aeronautical fluid dynamics Book GAME THEOBY A77-12551 The pursuit-evasion problem of two aircraft in a Improved c-cmjutational treatment of transonic flow horizontal plane about swept wings A77-12152 N77-10348 GAS DYNAMICS Transonic flow theory of airfoils and wings Nonlinear analysis of flows generated by the 1177-10351 impulsive motion of a vedge Transients in turbocompressors effect of A77-12630 unsteady flow on compressor performance GAS TUBBINE EBGIHES [AD-A024275] H77-11112 High-nickel alloys for gas turbines FLUID INJECTION A77-11325 Penetration and mixing of liquid injected into Future trends in aero gas turbine design. II - supersonic transverse gas stream Unconventional engines A77-12515 A77-11595 FLDID JETS System considerations for reliable strain data Determination of magnitudes of the parameters from gas turbine engines characterizing ducted airscoop operation A77-12176 downstream for airplane deceleration Experimental study of combustion time in two-stage A77-12521 combustion process FLOTTEB A77-12511 The design, analysis and testing of a low budget Selection of compressor pressure ratio of small wind tunnel flutter model with active GTE installed in bypass turbojet engine fan duct aerodynamic controls, volume 2 A77-12513 [AD-A02UII80] 1177-10090 Study of flow swirl influence on axiradial FLDTTEB ASALYSIS diffuser effectiveness Development of a graphite horizontal stabilizer A77-12520 [AD-A023767] N77-11036 Heat-pipe regenerator for gas turbine engine FLY BI IIBS CONTBOL A77-12528 Design and fabrication of an 8000 FSI Dispersion of fatigue test data for cast control-by-wire actuator for flight testing in a gas-turbine blades in association with T-2 C airplane structural and technological factors tAD-A02i4i(87] N77-11065 477-12579 FLYIBG PLATFOBUS Calculation of gas-turbine engine blades by the Dual-spin spacecraft dynamics under conditions of finite element method a rotating unbalanced platform and rotor asymmetry A77-12583 [IAF PAEEB 76-019] A77-10882 The impact of emissions standards on the design of FEACTDBB STBEBGTH aircraft gas turbine engine conbustors Design igecnanical properties, fracture toughness, [HASA-TM-X-73U90] H77-10063 fatigue properties, exfoliation and Hot corrosion studies of four nickel-base stress-corrosion resistance of 7050 sheet, superalloys: B-1900, HASA-TBI VIA. 713C and IH738 plate, hand forgings, die forgings and extrusions [NASA-TM-X-731479] N77-10183 [AD-A024609] N77-10195 GAS IUBBIHES Fracture toughness of 8mm 202U-T3 non clad plate High temperature thermocouple system for advanced with long central cracks aircraft turbine engines [FOK-B-1879] H77-11

~~1-12 SDBJECI IBDBI HIPBRSOBIC SHOCK~~

Beduct'.OD of gaseous pollutant emissions froa gas HBLICOPTBB BBSIGB turbine coabastors using hydrogen-enriched jet Advanced coctrol systems for helicopters fuel •" A77-11278 [HASA-CB-1119146] N77-11198 Seducing vibration by structural modification (3EHEBAL A7IATIOH AIBCHAFT helicopter fuselage aodel Landing practices of general aviation pilots in A77-11279 single-engine light airplanes A aethod for estimating the weight of aircraft [BASA-TN-D-8283] H77-11033 transaissions GLASS FIBEB BEIHFOBCBO PLASTICS [SAKE TAPEB 1120] A77-12191 Strength of glass-fibre-reinforced plastics at HELICOPTEB EEBFOBflAHCE one-sided heating aircraft ablative thermal Hingeles= rotor dynamics in high speed flight protection coatings A77-11280 [IAF PAPEB 76-200] A77-10939 A wing on the SA.341 Gazelle helicopter and its Theoretical and experimental investigations on effects landing gear spring blades out of fiber A77-11282 reinforced plastic for small aircraft Army preliminary evaluation roH-58A helicopter [ESA-TT-312] B77-10162 with a flat-plate canopy CLASS FIBEBS [AD-A024501] B77-11039 Certification of the replacement of glass fabric Helicopter reliability growth evaluation per oat. spec. 5.670/1, with glass fabric per [AD-A025265] B77-11011 mat. spec. 5.670 in the F27 plastic sandwich BELICOPIEB TAIL BOTOBS ving-and-stabilizer-leading edges noting Investigation of a bearingless helicopter rotor shear strength and sandwich stiffness concept having a composite primary structure [FOK-R-1876] N77-11122 [SASA-CB-2637] H77-100U4 GBAPHITE BELICOPTEBS Development of a graphite horizontal stabilizer The helicopter air service passenger program: A [AD-A023767] U77-11036 retrospect GBAPHS (CHARTS) [PB-25M830/3] B77-10036 V/STOL rotary propulsion systems: Noise Helicopter yaw axis augmentation investigation prediction and reduction. Volume 2: Graphical [AD-A024512] S77-11066 prediction methods HIGH ACCELEEATIOB [AD-A027390/1] N77-10054 Influence of aircraft angle of attack on high G GBINDING (HATEBIAL BEHOVAL) cockpit design Bearing restoration by grinding [ AD-A02S083] B77-110U3 [NASA-CB-1119188] N77-1140U HIGH ALTITUDE TESTS GBODSD SUPPOBT EQOIPHEHI The impact of emissions standards on the design of Aircraft ground fire suppression and rescue aircraft gas turbine engine combustors systems Characteristics of kinematic jet fuel [NASA-I1J-X-731*90] M77-10063 fires cascading and rod fuel geometries BIGH SPEED [AD-A021I417] N77-11022 Hingeless rotor dynamics in hign speed flight GBODND TESTS A77-11280 Ground test of the D shaped vented thrust HIGH TEHPSBAJOHB TESTS vectoring nozzle Development of aircraft brake materials [NASA-Cii-137959] N77-11107 [ASLE PREPRINT 76-LC-1B-3] A77-11195 COST LOADS HODOGBAPHS Optimal ride control for the Twin Otter, STOL A transonic hodograph theory for aerofoil design aircraft A77-12561 A77-10336 HOLOGBAPHI Holographic flow visualization of aircraft wakes [HASA-CB-1t9182] N77-11365 H HOVERIHG STABILITY HABDRABE Eigenvalue/eigenvector control via spectral Final approach performance monitor characterization - An application to helicopter fAD-A02U513/0] N77-11021 hover dynamics BABHONIC HOTIOB A77-10338 Forces on unstaggered airfoil cascades in unsteady Rotor impedance measurements at model scale in-phase motion test rig for rotating shaft hovering stability [ASME "APES 76-FE-S] A77-10854 A77-11281 HEAT EXCHANGEES HUMAN PACTOBS ENGIBEEBIHG Heat-pipe regenerator for gas turbine engine Advances in engineering science, volume 1 A77-12528 [NASA-CP-2001-VOL-Q] H77-10345 HEAT PIPES HIDBOGEN FUELS Heat-pipe regenerator for gas turuine engine Survey of nyarogen energy application projects A77-12523 A77-12778 BEAT BBSISTAB1 ALLOYS An exploratory study to determine tne integrated High-nickel alloys for gas turbines technological air transportation system ground A77-11325 requirements of liguid-hydrogen-fueled subsonic, BEAT TBABSFEB long-haul civil air transports Advances ia engineering science, volume U [NASA-CR-2699] N77-10033 f HASA-CP-2001-VOL-U] N77-10345 Hydrojen-fueled sabsonic aircraft: A perspective HEAT TBANSFEB COEFFICIENTS N77-1031U Heat transfer in tube entrance segment with HIDBOGEN-BASED ENEBGT initial flow swirl and transverse infection Survey of hydrogen energy application projects A77-12517 A77-12778 HELICOPTEB COBTBOL HIPBBBOLIC FUSCTIOHS Eigenvalue/eigenvector control via spectral The nyperbolicity of integral equations of characterization - An application to helicopter momentum in a three-dimensional incompressible hover dynamics laminar ooundary layer A77-10338 A77-10665 Advanced control systems for helicopters HIPEBSONIC FLIGHT A77-11270 Off-design regimes of asymmetric nozzles with A wing on the SA.311 tazelle helicopter and its supersonic inlet velocity effects A77-12504 A77-11282 HYPEBSOHIC SHOCK Application of Liapunov model - Tracking parameter Flow of a radiating gas over a blunt body with identification for the CH-47 helicopter intense vaporization A77-12U60 A77-10U16

~~A-13 IMPEDANCE HEASOBBBBNTS SUBJECT IHDEX~~

IMPEDANCE MEASUBEMENTS J-85 ENGINE Rotor impedance measurements at model scale Effects of forward velocity on noise for a J85 test rig for rotating shaft hovering stability turbojet engine with multitube suppressor from 477-11281 wind tunnel and flight tests INCOMPHESSIB1E BOONDABI LiYEB [NASA-TM-X-735112] N77-11051 The hyperbolicity of integral equations of JET AIRCRAFT momentum in a three-dimensional incompressible Best-range flight conditions for cruise-climb laminar boundary layer flight of a jet aircraft A77-10665 N77-10379 INCOBPBESSIELE FLOI JET AIRCRAFT NOISE Forces on unstaggered airfoil cascades in unsteady A test facility for aircraft jet noise reduction. II in-phase motion A77-118114 [ASME PAPEB 76-FE-S] A77-1085U JET ENGINE FDELS Lifting-surface theory of straight cascades of An exploratory study to determine the integrated swept blades technological air transportation system ground A77-12218 requirements of liquid-hydrogen-fueled subsonic, Methods for elliptic problems in external long-haul civil air transports aerodynamics [NAS1-CB-2699] N77-10033 A77-12554 Aircraft ground fire suppression and rescue The finite element method applied to fluid mechanics systems. Characteristics of kinematic jet fuel 477-12558 fires cascading and rod fuel geometries INCONEL (THiDEBAEK) [AD-A021C4U7] N77-11022 High-nickel alloys for gas turbines JET ENGINES 477-11325 Program system for computer calculations of jet INFLUENCE COEFFICIENT engine characteristics Russian book Applications of linearised supersonic wing theory A77-103119 to the calculation of some aircraft interference Laser air-jet engine earth-based pulse flows radiation created thrust A77-12566 A77-11887 INLET FLO* JET FLAPS Heat transfer in tube entrance segment with Performance of steady and intermittent blowing jet initial flow swirl and transverse injection flaps and spanwise upper surface slots 477-12517 [AD-A0243614 J N77-10027 INLET NOZZLES On the status of V/STOL flight Off-design regimes of asymmetric nozzles with N77-10367 supersonic inlet velocity JET FLOH A77-1250« Effects of jets, wakes, and vortices on lifting INSTRUMENT LANDING SYSTEMS surfaces Final approach performance monitor [NAS4-TM-X-7397H] N77-10998 [4D-A028513/0] U77-11021 JET IMPINGEMENT INTEGRAL EQUATIONS Pressure loss coefficient of impingement cooled Transonic flows calculation by integral leading edge system of a turbine blade equation, relaxation and finite difference methods A77-10772 477-12561 Determination of magnitudes of the parameters An extended integral equation method for the characterizing ducted airscoop operation steady transonic flow past a two-dimensional downstream for airplane deceleration aerofoil 477-12521 477-12562 Mormal impingement of a supersonic jet on a plane: An integral equation method for boundary 4 basic study of shock-interference neating interference in a perforated-wall wind tunnel at [4D-4024511 ] N77-10026 transonic speeds JET MIXING FLOH [40-4023493] N77-1002J Penetration and mixing of liquid injected into INTERNATIONAL COOEEBATION supersonic transverse gas stream Co-operation in the European aircraft A77-12515 manufacturing industry and among the scheduled JET PROPULSION airlines /Brancker Memorial Lecture/ Project SQUID: A cooperative program ot 477-11311 fundamental research related to jet propulsion INTERNATIONAL LAN [AD-A02HOOD ] N77-11059 Responsioilities and assurances with regard to JET VANES cargo transport - Air transport law Magnetic particle inspection of aviation engine 477-121472 vanes INTERNATIONAL RELATIONS 477-11606 New orientations of intergovernmental organizations of civil aviation A77-12U70 INVISCID FLOW LAHINAR BOUNDARY LAYER Approximate transoric profile flow with shock The hyperbolicity of integral equations of 477-10251 momentum in a tncee-dimensional incompressible Methods for elliptic problems in external laminar boundary layer aerodynamics A77-10e65 A77-1255H LAMINAR FLOH Supersonic flows numerical computation for Numerical solutions for laminar and turbulent steady inviscid tlowfield viscous flow over single and multi-element 477-12555 airfoils using body-fitted coordinate systems ISRAEL N77-10355 Israel's priae of Lions Kfiv fighter aircidlt Design considerations for laminar flow control prog ram aircratt A77-1052M N77-10366 ITERATIVE SOLUTION LANDING GEAR Flow interaction near the tail of a bcdy of Reliaoility applied to landing gear and hydraulics revolution. II - Iterative solution for flow A77-12116 witnin and exterior to boundary layer and wake Theoretical and experimental investigations on [ASME PAPEB 76-FE-N] A77-10B56 landing gear spring blades out of tiaer Finite element and difference methods for cascades reinforced plastic for snail aircraft A77-12557 [E5A-IT-312] H77-10162 SUBJECT INDEX HATHEHATICAL BODELS

Fatigue investigation of the E-2B/C nose landing Study of small turbofan engines applicable to gear single-enjine light airplanes [AD-4021072] B77-11040 [NASA-Ca-137911 ] B77-11051 L4SEB APPLICATION LINEAR SISTEHS Laser air-]et engine earth-based pulse On tne identification of state-denvative-coupled radiation created thrust systems 477-11887 A77-12118 LATTICE PAEABETEBS Linear regulator design for stochastic systems by Application of the nonlinear vortex-lattice a multiple time scales method concept to aircraft-interference problems [SASA-CB-119099] N77-10132 N77-10349 LIQUID HYDROGEN LAI (JURISPRUDENCE) Lh2 airport reguirements study Beyond supersonic transport [UASA-CR-2700] N77-10032 [IAF PAPEB ISL-76-66] A77-10972 An exploratory study to determine tae integrated An analysis of the Intrastate air carrier technological air transportation system ground regulatory forum. Volume 1: Summary report requirements of liguid-nydrogen-fueled subsonic, [AD-H023761 ] N77-10031 long-haul civil air transports An analysis of the intrastate air carrier [BASA-CH-2699] N77-10033 regulatory forum. Volume 2. Technical report LIQUID-VAPOR INTERFACES [AD-A023762] N77-10035 Two-phase turbine engines using gas-liguid LEADING EDGES mixture accelerated in nozzles Pressure loss coefficient of impingement cooled 477-12680 leading edge system of a turbine blade LOADING BATE 477-10772 Hechanism of material fatigue during tne crack Buffeting problems leading and trailing edge initiation stage flow separation [ICAP-DOC-395 ] N77-11111 [AAAF-NT-76-7] N77-10050 LOADS (FORCES) LEGAL LIABILITY Influence of aircraft angle of attack on high G New orientations of intergovernmental cockpit design organizations of civ^.1 aviation [AD-A025083] N77-11013 477-12170 LONGITUDINAL STABILITY Responsibilities and assurances with regard to High supersonic aerodynamic characteristics of cargo transport - Air transport law five irregular planform wings with A77-12172 systematically varying wing fillet geometry LIAPDNOV FOHCTIOBS tested in the NASA/LaHC 1-foot UPHT (LEG 2) Application of Liapunov model - Tracking parameter (L4454/B) identification for the CH-17 helicopter [NASA-CB-117628] N77-10010 477-12160 Calculation of the longitudinal aerodynamic LIFE (DDRABILITI) characteristics of wing-flap configurations with A second look at relationships for estimating externally blown flaps peacetime aircraft attrition [BASA-Ca-2705] N77-11006 [AD-4023681] N77-11023 LO1 COST LIFT DEVICES Combustor design for low cost expendable turbojets European flotorcraft and Powered Lift Aircraft [4D-A021511] N77-10070 Forum, 1st, University of Southampton, LOR SPEED HIND TUNNELS Southampton, England, September 22-21, 1975, Experiments on the feasibility of aero-acoustic Proceedings measurements in the 3-m low speed wind tunnel A77-11276 of the DFVLR-AVA Lifting-surface theory of straight cascades of [ESA-TT-311 ] N77-10873 swept blades 477-12218 LIFT FANS M Performance of 1.15-pressure-ratio fan stage at flACa HOHBEB several rotor blade setting angles with reverse Assessment of variable-cycle engines for Hach 2.7 flow supersonic transports [N4SA-TB-X-3151 ] N77-11008 [NASA-TM-X-73977] 877-10065 Preliminary design-lift/cr«ise fan research and MACROSCOPIC EQDATIOHS technology airplane flight control system Macroscopic study of time unsteady noise of an [NASA-CE-137971] N77-11061 aircraft engine during static tests LIFTING BODIES [NASA-TM-X-73556] N77-11052 Free vortex sheets MAGNETIC BBASUBEMENT 477-12559 Magnetic particle inspection of aviation engine Relaxation near a sonic line transonic flow vanes past subsonic lifting aircraft A77-11606 477-12563 MAGNUS EFFECT Lifting surface theory for rectangular wings Experimental investigation of the boundary layer N77-10317 on a rotating cylinder An application of the suction analog for the A77-10208 analysis of asymmetric flow situations An improved projectile boattail, part 2 N77-10350 [AD-4021073] N77-11016 Effects of jets, wakes, and vortices on lifting MANGANESE OXIDES surfaces High temperature thermocouple system for advanced [NASA-TB-i-7397U ] N77-10998 aircraft turbine engines LIFTING ROTORS [AD-A025500] K77-11062 Methods studies on system identification from BASS FLOW transient rotor tests Heat transfer in tube entrance segment with [NASA-CB-137965] N77-10005 initial flow swirl and transverse injection LIGHT AIRCRAFT A77-12517 Emissions of an 4VCO Lycoming 0-320-DIAD air BATEBIALS TESTS cooled light aircraft engine as a function of Development of aircraft brake materials fuel-air ratio, timing, and air temperature and [ASLE PREPRINT 76-LC-1B-3] A77-11195 humidity BATHBBATICAL BODELS [NASA-TH-X-73500] N77-10058 Subsonic flows in turbomachines Theoretical and experimental investigations on A77-12556 landing gear spring blades out of fiber The establishment of safe separations between reinforced plastic for small aircraft aircraft in flight [ESA-TT-312] N77-10162 [NLB-HP-75011-0] N77-11020

~~A-15 MCDONNELL DOUGLAS AIBCBAFT SUBJECT INDEX~~

A second look dt relationships for estimating NEAR WAKES peacetime aircraft attrition Application of the nonlinear vortex-lattice [AD-A023681] N77-11023 concept to aircraft-interference problems MCDONNELL DOUGLAS AIBCBAFT N77-10349 The next-generation subsonic transport NETHERLANDS [SAKE PAPER 1127] A77-12195 Research on adhesive bonding and surface MEASOBE AND INTEGRATION characteristics of metals at Fokker-VFH Lifting surface theory for rectangular uings [FOK-R-1815 ] N77-11405 N77-10347 NICKEL ALLOTS MECHANICAL IMPEDANCE High-nickel alloys for gas turbines Rotor impedance measurements at model scale A77-11325 test rig for rotating shaft hovering stability Dispersion of fatigue test data for cast A77-11281 gas-turoine olaaes in association with MECHANICAL PBOPEBTIES structural and technological factors Strength of glass-fibre-reinforced plastics at A77-12579 one-sided heating aircraft anlative thermal riot corrosion studies of four nickel-base protection coatings superalloys: B-1900, NASA-TEH VIA, 713C and IS738 [IAF PAPIE 76-200] A77-10939 [ NASA-Til-X-73479] N77-10183 METAL BONDING NITROGEN OXIDES Research on adhesive bonding and surface Advanced combustion techniques for controlling NO characteristics of metals at Fokker-VFM sub x emissions of nigh altitude cruise aircraft [FOK-R-1816] N77-11105 [NASA-TH-X-73473] N77-10062 METAL FATIGDE NOISE INTENSITY Dispersion of fatigue test data for cast Noise generating by interaction between subsonic gas-turbine blades in association with jets and blown flaps structural and technological factors [DLH-FB-76-20J N77-10067 A77-12579 Effects of forward velocity on noise for a J85 Analog computation assessment of the risk of turbojet engine with multitube suppressor from stiuctural failure due to crack growth under wind tunnel and flight tests random loading [NASA-TH-X-73542] N77-11051 [AD-A025266] N77-11042 NOISE MEASDBEMENT ilechanism of material fatigue during the crack Rotational noise measurement in a wind tunnel by initiation stage total sampling synchronization [ICAF-DOC-895] N77-11441 A77-11284 MICBOiAVE LANDING SYSTEMS Experiments on tne feasibility of aero-acoustic Simulation ot an automatically-controlled STOL measurements in the 3-m low speed wind tunnel aircraft in a microwave landing system multipath of tne DFVLB-AVA environment [ESA-TT-311] N77-10873 [NASA-JH-X-731511] N77-11063 Core noise source diagnostics on a turbofan engine MILITARY AIBCBAFT using correlation and coherence techniques VTOL fiPVs - A technology assessment [rfASA-TM-X-73535] N77-11053 A77-12000 NOISE REDUCTION Operational mass properties data for military A note on the acoustic effect of non-uniformly aircraft - Data formulation, presentation and distributed stator rows usage A77-10317 [SAME PAPEB 1147] A77-12202 A test facility for aircraft jet noise reduction. II A second look at relationships for estimating A77-11844 peacetime aircraft attrition V/STOL rotary propulsion systems: Noise (AD-A023681] N77-11023 prediction and reduction. Volume 1: MILITABI HELICOPTEBS Identification of sources, noise generating A wing on the SA.341 Gazelle helicopter and its mechanisms, noise reduction mechanisms, and effects prediction methodology A77-11282 [AD-A027389/6] N77-10053 MISSILES V/STOL rotary propulsion systems: Noise Military rocket aircraft: Inherent constraints prediction and reduction. Volume 2: Graphical and their uses prediction methods N77-11186 [AD-A027390/4] " 1)77-10054 MISSION PLANNING V/STOL rotary propulsion systems: Noise Civil uses of remotely piloted aircraft prediction and reduction. Volume 3: Computer [NASA-CB-137894] N77-10047 program users manual MODAL BESPONSE [AD-A027363/1] N77-10055 A note on the acoustic effect of non-unlformly Inlet noise suppressor design method based upon distributed stator rows the distribution of acoustic power with mode A77-10347 cutoff ratio MDLIIPATB TRANSMISSION N77-10311 Simulation of an automatically-controlled STOL NONDESTRUCTIVE TESTS aircraft in a microwave landing system multipath Signal-treatment methods during aircraft-engine environment inspection based on vibroacoustic noises [NASA-TH-X-73154] N77-11063 A77-11603 Magnetic particle inspection of aviation engine vanes N A77-11606 HASA PBOGBAHS NONFLAMMABLE HATEBIALS Design of active controls for the SASA F-6 digital Conference on the Development of Fire-Besistant fly-by-wire airplane Aircraft Passenger Seats N77-10377 [NASA-TM-X-731U4] N77-11111 NAVIEB-STOEES EQUATION NOSES (FOBEBODIES) Numerical solutions for laminar and turbulent Pressure distributions over frontal /nose/ viscous flow over single and multi-element surfaces of bodies of revolution in transonic airfoils using body-fitted coordinate systems flow at angles of attack of 0 to 10 deg N77-10355 A77-10664 Vortex/jet/wing viscous interaction theory and NOTCH TESTS analysis Fracture toughness of 8mm 2024-T3 non clad plate [AD-A025290] N77-11017 with long central cracks NAVIGATION AIDS [FOK-B-1879] N77-11II49 Rationale and description of a coordinated cockpit NOZZLE DESIGN display for aircraft flight management Off-design regimes of asymmetric nozzles with fNASA-TM-X-3457] N77-11044 supersonic inlet velocity A77-12504

~~A-16 SUBJECT IBDBI PBBDICTIOB 1ULISIS IBCHIIQOBS~~

BOZZLB EFFICIESCY PBBFOBB4BCE PBEDICTIOI Ground test of the D shaped vented thrust Critical analysis of comparisons between flight vectoring nozzle test results and wind Tunnel test predictions in [H1SA-CB-137959] H77-11107 subsonic and supersonic transport aircraft BOZZLB PLOi [B4S4-TT-F-17185] B77-10019 Determination of magnitudes of the paraaeters PBBFOBB4BCE TESTS characterizing dncted airscoop operation Performance analysis of flexible aircraft with downstream for airplane deceleration active control 477-12521 B77-10378 Coipressible subcritical flov through axially PEBTDBB4fIOI THEOBI symmetric sharp-lipped orifices and nozzles Improved computational treatment of transonic flow A77-12555 about swept wings Two-phase torbine engines using gas-liquid B77-10348 mxtnre accelerated in nozzles Performance analysis of flexible aircraft with 477-12680 active control BOZZLB GEOHBTEY B77-10378 Ground test of the D shaped vented thrust PHYSIOLOGICAL FACTOBS vectoring nozzle Investigation and analysis of the human factors in [SASA-CB-137959] B77-11107 aircraft accidents BOZZLB THBOST COEFFICIEBTS 477-10500 Off-design regimes of asymmetric nozzles vith PILOT PBBFOBHANCE supersonic inlet velocity A flight investigation of piloting techniques and 477-12504 crosswind limitations during visual STOL-type BOHEBICAL ABALYSIS landing operations Computational methods and problems in aeronautical [B4S4-TH-D-8284] B77-11001 fluid dynamics Book Display/control requirements for VTOL aircraft 477-12551 [S4S4-CB-145026] B77-11030 Inverse transonic airfoil design including viscous Landing practices of general aviation pilots in interaction single-engine light airplanes B77-10354 [N4S4-TH-D-8283] B77-11033 Helicopter yaw axis augmentation investigation [AD-A024512] 1177-11066 PILOT TBAIBIBG OBLIQUE IIBGS Simulating the last 100 ft computer-generated An analytical study for subsonic obligue wing images for landing training transport concept A77-10648 [NASA-CB-137896] B77-100U5 PLASTIC COATIBGS An analytical study for subsonic obligue wing Full temperature range protective system for transport concept fastener areas of carrier-based naval aircraft [NASA-CB-137897] K77-10046 [4D-4024523] 877-10210 OPTIBAL COBTBOL POLLUTION COHTBOL Optimal ride control for the Twin Otter, STOL The fuel approach to control emissions from aircraft aircraft [IAF PAPEB 76-111] A77-10911 477-10336 Experimental clean combustor program: Boise study Optimal control for the rolling pullout maneuver [NASA-CB-135106] B77-10064 of a modern fighter aircraft POBOUS BALLS A77-12444 Heat transfer in tube entrance segment with OEIFICE FLOI initial flow swirl and transverse injection Compressible subcritical flow through anally A77-12517 symmetric sharp-lipped orifices and nozzles POSITIOBIBG A77-12555 Compressor blade setting angle accuracy study, OUTLET FLOI volume 1 Study of flow swirl influence on axiradial [BASA-CB-135068-VOL-1] B77-11046 diffuser effectiveness Compressor blade setting angle accuracy study. 477-12520 Volume 2: Data compilation OXIDATION [NASA-CB-135068-VOL-2] B77-11047 Hot corrosion studies of four nickel-base POSTFLI6HT ANALYSIS superalloys: B-1900, NASA-TBH VIA, 713C and IB738 Concorde - Endurance flights results [B4SA-TB-X-73479] N77-10183 A77-12114 POTBBTIAL FLOH Flow interaction near the tail of a body of revolution. I - Flow exterior to boundary layer PASSEBGBB AIBCBAFT and wake Intercity VIOL aircraft - A Hawker Siddeley review [ASSE PAPEB 76-FE-H] 477-10855 A77-11283 Flow interaction near the tail of a body of Application of advanced technology to future revolution. II - Iterative solution for flow long-range aircraft within and exterior to boundary layer and wake [SAME PAPBB 1126] A77-12194 [4SHB P4PEB 76-FE-B] 477-10856 An analytical study for subsonic obligue wing I he finite element method applied to fluid mechanics transport concept 477-12558 [NASA-CB-137896] N77-10045 POSDBB (PAB1ICLES) An analytical study for subsonic obligue wing Magnetic particle inspection of aviation engine transport concept vanes [HASA-CB-137897] B77-10046 477-11606 P4SSEBGEBS PBEDICTIOB ANALYSIS TECHBIQOES 4ircraft loadability parameters - Some results of Estimating fatigue-crack lives for aircraft - an airline survey Techniques [SANE PAPEB 1146] 477-12201 A77-11477 The helicopter air service passenger program: 4 Fuselage analytical weight estimation method retrospect [SABE PAPEB 1102] A77-12182 [PB-254830/3] B77-10036 Prediction Bethods for Jet V/STOL Propulsion PEBFOBATEO SHELLS Aerodynamics, volume 1 An integral eguation method for boundary (AD-A024022] N77-10068 interference in a perforated-wall wind tunnel at Prediction Methods for Jet V/STOL Propulsion transonic speeds Aerodynamics, volume 2 [AD-A023493] N77-10023 [AD-4024023] N77-10069 The AFFDL-Bielsen flow-field study [AD-A023755] N77-11015

~~A-17 PBBSSDBB DISTBIBOTIOH SDBJBCT IHDBX~~

Helicopter reliability growth evaluation [AD-1025265] H77-110111 PBESSUBB DIST8IBOTIOB Pressure distributions over frontal /nose/ B4DI4NT BE4TIBG surfaces of bodies of revolution in transonic Flow of a radiating gas over a blunt body with flow at angles of attack of 0 to 10 deg intense vaporization 477-10664 477-10416 Unsteady pressure distributions on oscillating B4DI4TIVE BEAT IB4HSFEB airfoils in a supersonic cascade Anisotropic radiatively coupled wedge flow 477-10771 477-10218 Structural tests of aerodynamic surfaces - 4 BE4CTIOB KINETICS systems approach to analysis and design Project SQUID: 4 cooperative program of 477-12206 fundamental research related to jet propulsion Some problems of unsteady flov about aircraft [4D-4024004] N77-11059 477-12560 BE4L TIME OPBBATIOH 4 transonic hodograph theory for aerofoil design Hethod of discrete modeling and its application to 477-12564 estimation of TF30 engine variables Transonic flov theory of airfoils and wings [H4SA-TH-X-3443] N77-11057 1177-10351 BB4IIACBEO FLOI The inviscid pressure field on the tip of a Calculation of the flow around a swept wing, semi-infinite mng and its application to the taking into account the effect of the formation of a tip vortex three-dimensional boundary layer. Part 1: King [N4S4-CB-2748] 1177-11345 with turbulent boundary layer PBBSSOBB DBOF [SLB-TB-75076-0] S77-11011 Pressure loss coefficient of impingement cooled BECT4HGUL4E RINGS leading edge system of a turbine blade Lifting surface theory for rectangular wings 477-10772 N77-10347 PBBSSDBE GBADIEHTS BEFIBIBG Film cooling with injection through slots The production and refining of crude oil into 477-10773 military fuels PRODUCTION EN6IBEBBIHG [4D-4024652] 877-11207 The production and refining of crude oil into BEFBACIOBI HET4L ALLOTS military fuels High-nickel alloys for gas turbines [AD-A024652] S77-11207 477-11325 PBOJECT MANAGEMENT BEGBNEB4TOBS Concorde maintenance as seen by the designer - The Heat-pipe regenerator for gas turbine engine maintenance program 477-12528 477-12115 EEIHFOECING FIBEBS B. & D. project cost and schedule realism - 4 risk Theoretical and experimental investigations on analysis approach landing gear spring blades out of fiber 477-12455 reinforced plastic for small aircraft PBOJECTILES [ESA-TT-312] N77-10162 An improved projectile boattail, part 2 BBL4X41ION METHOD (D4THEHATICS) [AD-A024073] N77-11016 Transonic flows calculation by integral PBOPDLSIOH SISTBB PBEFOEB4HCE equation, relaxation and finite difference methods V/STOL rotary propulsion systems: Noise 477-12561 prediction and reduction. Volume 1: Relaxation near a sonic line transonic flow Identification of sources, noise generating past subsonic lifting aircraft mechanisms, noise reduction mechanisms, and 477-12563 prediction methodology BELIABILITY AN4LISIS [AD-4027389/&] ST7-10053 A systems approach to all weather landings V/STOL rotary propulsion systems: Noise A77-10438 prediction and reduction. Volume 2: Graphical Reliability of automated flight service stations prediction methods 477-10442 [AD-4027390/4] N77-10054 Beliability applied to landing gear and hydraulics V/STOL rotary propulsion systems: Noise 477-12116 prediction and reduction. Volume 3: Computer System considerations for reliable strain data program users manual from gas turbine engines [4D-A027363/1] N77-10055 477-12176 Assessment of variable-cycle engines for Mach 2.7 BELIABILITY ENGIKEEBIBG supersonic transports Small axial compressor technology, volume 1 [N4S4-TM-X-73977] N77-10065 [N4S4-CB-134827-VOL-1] N77-11048 Prediction Methods for Jet V/STOL Propulsion BEHOTB COBTEOL Aerodynamics, volume 1 •C.22', the new French target drone [AD-4024022] N77-10068 477-11625 Prediction Hethods for Jet V/STOL Propulsion REMOTELY PILOTED VEHICLES Aerodynamics, volume 2 'C.221, the new French target drone [AD-A024023] N77-10069 477-11625 PBOTBCTIVB COATINGS VIOL BPVs - 4 technology assessment Full temperature range protective system for 477-12000 fastener areas of carrier-based naval aircraft Civil uses of remotely piloted aircraft [4D-4024523] N77-10210 [NASA-CB-137894] N77-10047 PSYCHOLOGICAL F4CTOBS Civil uses of remotely piloted aircraft Investigation and analysis of the human factors in [NASA-CR-137895] N77-10048 aircraft accidents Combustor design for low cost expendable turbojets 477-10500 [AD-A024541] N77-10070 POLSEO LASEBS Conceptual designs for a modular remotely piloted Laser air-jet engine earth-based pulse vehicle radiation created thrust [AD-4023844] N77-11035 477-11887 4 wind tunnel captive aircraft testing technique PDHP IHPELLEBS [AD-4023690] N77-11037 Strength of compressor wheels of low-ductility BESE4BCH 4ND DEVELOPMENT alloys 4pplication of advanced technology to future 477-10383 long-range aircraft [SAKE P4PEB 1126] 477-12194 fi. & D. project cost and schedule realism - 4 risk analysis approach 477-12455 SUBJECT I8DEI S-2 AIBCBAFf

Survey of hydrogen energy application projects Aeroelastic analysis for helicopter rotor blades A77-12778 with time-variable, non-linear structural twist The technical basis for a national civil aviation and multiple structural redundancy: research, technology/ and development /BT & D/ Mathematical derivation and program user's manual policy; Proceedings of the Workshop Conference, [NASA-CB-2638] B77-10556 Crystal City, Va., March 10-12, 1976 BOTATIHG BODIES A77-12927 Dual-spin spacecraft dynamics under conditions of BESOHAHT FBEQOEBCIES a rotating unbalanced platform and rotor asymmetry Calculation of vibration modes and resonance [IAF PAPEB 76-019] A77-10882 frequencies of the Northrop NP-5 EOTATIB6 CYLIBDEBS [NLB-TB-75050-D] H77-11U50 Experimental investigation of the boundary layer BEDSE on a rotating cylinder Estimating procedures associated with aircraft A77-10208 aodifications EOTATIHG SHAFTS [SAME PAPEB 1101] A77-12181 Botor impedance measurements at model scale BEVEBSED F1OI test rig for rotating shaft hovering stability Performance of 1.15-pressure-ratio fan stage at A77-11281 several rotor blade setting angles with reverse BOTOB AEBODTNAHICS flow Dual-spin spacecraft dynamics under conditions of [NASA-TH-i-3451] N77-11008 a rotating unbalanced platform and rotor asymmetry BEYHOLDS BOBBEE [IAF PAPEB 76-019] A77-10882 The development of a computer aided airfoil design Application of circulation control rotor procedure including preliminary wind tunnel technology to a stopped rotor aircraft design experiments on a low Beynolds number high lift X-wing V/STOL section, volume 1 A77-11277 [AD-A024361 ] N77-10028 Hingeless rotor dynamics in high speed flight The cryogenic wind tunnel A77-11280 N77-10368 Botor impedance measurements at model scale BIGID BOTOBS test rig for rotating shaft hovering stability Hingeless rotor dynamics in high speed flight A77-11281 A77-11280 Design consideration for the Darrieus rotor Sensitivity of hingeless rotor blade flap-lag wind turbines stability in hover to analytical modelling A77-12872 assumptions Botor dynamic state and parameter identification, [NASA-CB-137967] N77-10007 from simulated forward flight transients, part 1 An experimental study of the nonlinear stiffness [BASA-CB-137963 ] N77-10003 of a rotor blade undergoing flap, lag and twist Botor dynamic state and parameter identification deformations from simulated forward flight transients, part 2 [NASA-CB-137968] B77-10008 [SASA-CB-1 37964] N77-10004 BISK Aeroelastic analysis for helicopter rotor blades B. & D. project cost and schedule realism - A risk with time-variable, non-linear structural twist analysis approach and multiple structural redundancy: A77-12455 Mathematical derivation and program user's manual BOCKB1 EHGIHE DESIGH [NASA-CB-2638] S77-10556 Laser air-]et engine earth-based pulse BOIOB BLADES radiation created thrust The effect of rotor blade wakes on centrifugal A77-11887 compressor diffuser performance - A comparative SOCKETS experiment Military rocket aircraft: Inherent constraints A77-10032 and their uses A note on the acoustic effect of non-uniformly N77-11186 distributed stator rows B01LEB BEABIBGS A77-10317 Bearing restoration by grinding An experimental study of the nonlinear stiffness [NASA-CB-149188] N77-11H04 of a rotor blade undergoing flap, lag and twist BOLLIBG deformations Optimal control for the rolling pullout maneuver [NASA-CE-137969] N77-10009 of a modern fighter aircraft BOTOB BLADES (TtJBBOHACHIBEBI) A77-12*W Analytic and experimental study of turbine rotor BOTAEY HIHG AIBCBAFT blade temperature European Botorcraft and Powered Lift Aircraft A77-12522 Forum, 1st, University of Southampton, Botor dynamic state and parameter identification, Southampton, England, September 22-214, 1975, from simulated forward flight transients, part 1 Proceedings [HASA-CB-137963] S77-10003 A77-11276 Botor dynamic state and parameter identification Application of circulation control rotor from simulated forward flight transients, part 2 technology to a stopped rotor aircraft design [NASA-CB-137964] B77-1000

~~i-19 SANDSICH STBOCTOBES SUBJECT IIDEX~~

SAHD1ICH STBUCTUBES SOUND GENEB4TOBS Certification of the replacement of glass fabric The influence of vortex shedding on the generation per mat. spec. 5.670/1, vith glass fabric per of sound by convected turbulence mat. spec. 5.670 in the F27 plastic sandwich 477-10197 wing-and-stabilizer-leading edges noting SPACE LAI shear strength and sandwich stiffness Beyond supersonic transport [FOK-B-1876] N77-11122 [IAF P4PEB ISL-76-66] A77-10972 SCHEDULING SPACE TB4NSPOBTATION B. 6 D. project cost and schedule realism - 4 risk Beyond supersonic transport analysis approach [IAF P4PEB ISL-76-66] 477-10972 477-12455 SPACBCBAFT DESIGN SEATS Dual-spin spacecraft dynamics under conditions of Conference on the Development of Fire-Resistant a rotating unbalanced platform and rotor asymmetry 4ircraft Passenger Seats [IAF P4PEB 76-019] 477-10882 [N4S4-TH-X-73144] N77-11111 SP4BE PABTS SEPARATED FLO! Interface between maintainability and commercial Transonic performance of Hach 2.65 auxiliary flow aircraft spares support axisymmetric inlet A77-10483 [NASA-CB-2747] N77-10056 SPBCTBDH ANALYSIS Viscous interaction with separation in transonic Signal-treatment methods during aircraft-engine flow inspection based on vibroacoustic noises [NASA-TT-F-17187 ] 1177-10997 A77-11603 Controlled and uncontrolled flow separation in SPIN REDUCTION three dimensions Besults of recent N4S4 studies on automatic spin [LB-591 ] N77-10999 prevention for fighter aircraft SEBVICE LIFE N77-10381 Interface between maintainability and commercial SQDID PBOJECT aircraft spares support Project SQUID: 4 cooperative program of 477-10183 fundamental research related to jet propulsion SHALE OIL [AD-A024004] N77-11059 The production and refining of crude oil into STABILITY AUGKENTATIOB military fuels The stochastic control of the F-8C aircraft using [AD-A024652] N77-11207 the multiple model adaptive control /MMAC/ method SHAEP LEADIHG EDGES 477-12428 Study of the subsonic flow around a sharp leading STABILIZERS (FLUID DYNAMICS) edge Development of a graphite horizontal stabilizer [444F-NT-76-14] N77-10017 [AD-A023767] N77-11036 SHOCK LAYEBS STALLING Anisotropic radiatively coupled wedge flow Centrifugal compressor and pump stability, stall 477-10218 and surge; Proceedings of the Conference, New SHOCK I4VE INTBBACTION Orleans, La., Harch 22-25, 1976 Nonlinear analysis of flows generated by the A77-10026 impulsive motion of a wedge SIANDABDS 477-12630 Operational mass properties data for military Normal impingement of a supersonic jet on a plane: aircraft - Data formulation, presentation and 4 basic study of shock-interference heating usage [AD-A024511] N77-10026 [SAKE PAPEB 1147] A77-12202 SHOCK RAVES STATIC LOADS Improved computational treatment of transonic flow An experimental study of the nonlinear stiffness about swept wings of a rotor blade undergoing flap, lag and twist N77-10348 deformations SHOBT TAKEOFF AIBCBAFT [N4S4-CB-137968] N77-10008 Optimal ride control for the Twin Otter, STOL STATIC TESTS aircraft Macroscopic study of time unsteady noise of an 477-10336 aircraft engine during static tests Three-component measurements on a model of a light [NASA-TH-X-73556] N77-11052 STOL aircraft with chordwise blowing STATOB BLADES [ES4-TT-299] N77-10052 Two-dimensional cold-air cascade study of a 4dvanced transonic aerodynamic technology film-cooled turbine stator blade. 3: Effect of N77-10365 hole size on single-row and multirow ejection A flight investigation of piloting techniques and [NAS4-TH-X-3442] N77-11007 crosswind limitations during visual STOL-type STATOBS landing operations A note on the acoustic effect of non-uniformly rNASA-T»-D-8284] N77-11001 distributed stator rows Simulation of an automatically-controlled STOL A77-10347 aircraft in a microwave landing system multipath STEADY FLOI environment 4n extended integral equation method for the [NASA-TH-X-73154] N77-11063 steady transonic flow past a two-dimensional SIGNAL TO BOISE BATIOS aerofoil Signal-treatment methods during aircraft-engine 477-12562 inspection based on vibroacoustic noises Supersonic flows numerical computation for 477-11603 steady inviscid flowfield SIZIHG (SHAPING) A77-12565 Resizing procedure for structures under combined STBELS mechanical and thermal loading Development of aircraft brake materials 477-1021U [ASLE PBEPBINT 76-LC-1B-3] 477-11195 SIZING (SDBFACE TREATMENT) STOCB4STIC PBOCBSSES Preliminary sizing and performance evaluation of The stochastic control of the F-8C aircraft using supersonic cruise aircraft the multiple model adaptive control /MHAC/ method [NASA-TB-X-73936] N77-11031 A77-12428 SLENDEB ilNGS Terminal area guidance along curved paths: A Free vortex sheets stochastic control approach A77-12559 N77-10383 SLOTS Linear regulator design for stochastic systems by Film cooling with injection through slots a multiple time scales method A77-10773 [NASA-CB-149099] N77-10432 Investigation of slot cooling for high-speed STOKES FLOi aircraft The finite element method applied to fluid mechanics [AD-A024316] N77-11061 A77-12558

~~A-20 SUBJECT ISDBI 30PEESOIIC TBAiSPOBTS~~

STBAIB GAGES An analytical study for subsonic oblique wing Systeo considerations foe reliable strain data transport concept froa gas turbine engines ' [SASA-CB-137897] H77-10046 177-12176 SBCTIOH SIBESS ABALISIS An application of the suction analog for the Advances in engineering science, volume 1 analysis of asymmetric flow situations [BAS1-CP-2001-VOL-1] H77-10230 H77-10350 STHESS COBCBHfBiTIOH SOBS Estimating fatigue-crack lives for aircraft - Calculation of multi-contour thin-walled Techniques structures by the method of sections 177-11477 [B1SA-TT-F-17281J B77-11029 STBESS HE1SOBEBEBT SOPBBCBITICAL FLOI Dynamic-stress-data nanagement for aerooecbanical Approximate transonic profile flow with shock testing of tnrbomachinery 177-10251 A77-12175 SOPBBCMTICAL HUGS STBOCTOBU 1IALISIS Practical requireaents in industry in Besizing procedure for structures under combined computerized aerodynamic calculations for aircraft mechanical and thermal loading 177-12S52 177-10211 Transonic flow theory of airfoils and wings Structural tests of aerodynamic surfaces - A H77-10351 systems approach to analysis and design Advanced transonic aerodynamc technology A77-12206 1177-10365 SIBDCTDBA1 DBSIGH SUPBBSONIC AIBCBAFT Besizing procedure for structures under combined Applications of linearised supersonic King theory mechanical and thermal loading to the calculation of some aircraft interference A77-10211 flows Advanced design composite aircraft, the next step 177-12566 for composites Study of the subsonic flow around a sharp leading [SAKE PAPEB 1105] 477-12181 edge STBOCTOBAL DBSIGH CHITEBIA [AAAF-NT-76-11] H77-10017 Application of optimality criteria to automated 1 computational system for aerodynamic design and structural design analysis of supersonic aircraft. Part 2: A77-10207 User's manual Beducing vibration by structural modification [NASi-CB-2716] H77-11005 helicopter fuselage model Investigation of slot cooling for high-speed 177-11279 aircraft STBUCTOBiL FAILOBE [AD-1024316] H77-11061 Analog computation assessment of the risk of SOPKBSOBIC AIHFOILS structural failure due to crack growth under Unsteady pressure distributions on oscillating random loading airfoils in a supersonic cascade [AD-A025266] N77-11042 177-10771 STBOCTOB1L VIBBATIOH Nonlinear analysis of flows generated by the Beducing vibration by structural modification impulsive motion of a wedge helicopter fuselage model 177-12630 A77-11279 SUPBBSOHIC COHBUSTIOS STBOCIOBAL IEIGHT Penetration and mixing of liguid injected into Estimating procedures associated with aircraft supersonic transverse gas stream modifications 177-12515 [SAKE PAPER 1101] A77-12181 Supersonic variable-cycle engines Fuselage analytical weight estimation method [NASA-TS-X-7352U] H77-10059 [SAKE PAPEB 1102] A77-12182 SUPEBSOHIC COBBEBCIU AIB TB1HSPOBT A method for estimating the Height of aircraft Assessment of variable-cycle engines for Hach 2.7 transmissions supersonic transports [SAKE PAPEB 1120] A77-12191 [N1SA-TH-X-73977J H77-10065 Assessment of variable-cycle engines for Bach 2.7 StJPBBSOBIC DIFFOSEBS supersonic transports Experimental investigation of the near-surge flow [NAS1-TH-X-73977] N77-10065 in a high performance centrifugal compressor SOBCBITICA1 FI01 177-10036 Compressible subcritical flow through axially SOPEBSOBIC FLOI symmetric sharp-lipped orifices and nozzles Supersonic flows numerical computation for A77-12555 steady inviscid flowfield SOBSOHIC AIBCBAFT 177-12565 'C.22', the new French target drone Normal impingement of a supersonic jet on a plane: A77-11625 A basic study of shock-interference heating The next-generation subsonic transport [1D-A021511] S77-10026 [SAKE PAPEB 1127] A77-12195 SOPKBSOBIC IBLETS Belaxation near a sonic line transonic flow Off-design regimes of asymmetric nozzles with past subsonic lifting aircraft supersonic inlet velocity A77-12563 177-12501 Hydrogen-fueled subsonic aircraft: A perspective SOPBBSONIC NOZZLES 877-10311 Off-design regimes of asymmetric nozzles vith SOBSOHIC FLOB supersonic inlet velocity Methods for elliptic problems in external 177-12501 aerodynamics Some supersonic wind tunnel nozzle boundary layer A77-12551I characteristics Subsonic flows in turbomachines [AD-A021980] N77-11018 A77-12556 SOPBBSOHIC SPEEDS Study of the subsonic flow around a sharp leading High supersonic aerodynamic characteristics of edge five irregular planform wings with [AAAF-NT-76-1D] N77-10017 systematically varying wing fillet geometry SDBSOBIC SPEED tested in the NASA/LaBC 1-foot OPHT (LEG 2) Hechanism of stabilization of the 'separation (L415A/B) point1 of a vortex during flow of a stream at [NAS1-CB-117628] N77-10010 low subsonic velocity over a delta wing SOPBBSOHIC TB1NSPOBTS [NASA-TT-F-17283] N77-10012 Effects of atmospheric conditions on the operating An analytical study for subsonic obligue wing characteristics of supersonic cruise aircraft transport concept [IAF P1PEB 76-112] 177-10912 [NASA-CB-137896] B77-10015

~~A-21 SOPBBSONIC 1180 TDBHELS SUBJECT IHDEI~~

Preliminary sizing and performance evaluation of TAIL SURFACES supersonic cruise aircraft Flow interaction near the tail of a body of [NASA-TH-X-73936] N77-11031 revolution. I - Flow exterior to boundary layer SOPEBSONIC USD TUHNBLS and wake Some supersonic wind tunnel nozzle boundary layer [ASHE PAPEB 76-FE-M] A77-10855 characteristics Flow interaction near the tail of a body of [AD-A024980] H77-11018 revolution. II - Iterative solution for flow SDBFACE GEOHETBI within and exterior to boundary layer and wake Structural tests of aerodynamic surfaces - A [ASMS PAPEB 76-FE-N] A77-10856 systems approach to analysis and design TARGET DBOHE AIBCBAFT A77-12206 •C.22', the new French target drone SOEFACE PEOPEBTIES A77-11625 Research on adhesive bonding and surface TECHNOLOGICAL FORECASTING characteristics of metals at Fokker-VFH The next-generation subsonic transport [FOK-B-1816] 877-11405 [SAiE PAPEB 1127] A77-12195 SDBFACE REACTIONS The technical basis for a national civil aviation Effects of jets, wakes, and vortices on lifting research, technology, and development /BT G D/ surfaces policy; Proceedings of the Borkshop Conference, [NASA-TM-X-73974] N77-10998 Crystal City, Va., Harch 10-12, 1976 SOEGES A77-12927 Centrifugal compressor and pump stability, stall TECHNOLOGY ASSESSMENT and surge; Proceedings of the Conference, New VTOL BPVs - A technology assessment Orleans, La., March 22-25, 1976 A77-12000 A77-10026 Civil uses of remotely piloted aircraft Experimental investigation of the near-surge flow [SASA-CB-137894] N77-10047 in a high performance centrifugal compressor Civil uses of remotely piloted aircraft A77-10036 [NASA-CB-137895] N77-10048 SIEPT iIHGS Small axial compressor technology, volume 1 Advances in engineering science, volume 4 [BASA-CB-134827-VOL-1] N77-11048 [NASA-CP-2001-VOL-4] N77-10345 TECHNOLOGY UTILIZATION Improved computational treatment of transonic flow Application of advanced technology to future about swept wings long-range aircraft N77-10348 [SAME PAPEB 1126] A77-12194 Calculation of the flow around a swept wing, Military rocket aircraft: Inherent constraints taking into account the effect of the and their uses three-dimensional boundary layer. Part 1 : Hing N77-11186 with turbulent boundary layer TBMPEBATUBE DISTRIBUTION [NLR-TB-75076-U] H77-11011 Analytic and experimental study of turbine rotor SIIBLIHG blade temperature Heat transfer in tube entrance segment with A77-12522 initial flow swirl and transverse injection TERMINAL GUIDANCE A77-12517 Terminal area guidance along carved paths: A Study of flow swirl influence on axiradial stochastic control approach diffuser effectiveness N77-10383 A77-12520 TEST FACILITIES SYSTEM EFFECTIVENESS A test facility for aircraft jet noise reduction. II Beliability of automated flight service stations A77-11844 A77-10442 - TESTING TIME The helicopter air service passenger program: A Mechanism of material fatigue during the crack retrospect initiation stage [PB-254830/3] N77-10036 [ICAF-DOC-895] N77-11441 SYSTEM FAILDBES THERMAL CONTBOL COATINGS Reliability applied to landing gear and hydraulics Strength of glass-fibre-reinforced plastics at A77-12116 one-sided heating aircraft ablative thermal SYSTEMS ANALYSIS protection coatings A systems approach to all weather landings [IAF PAPEB 76-200] A77-10939 A77-10438 THERMAL FATIGUE Reliability of automated flight service stations Dispersion of fatigue test data for cast A77-10442 gas-turbine blades in association with On the identification of state-derivative-coupled structural and technological factors systems A77-12579 A77-12448 THERMAL STBESSES SYSTEMS ENGINEEBING Resizing procedure for structures under combined Final approach performance monitor mechanical and thermal loading [AD-A028513/0] N77-11024 A77-10214 THERMOCOUPLES High temperature thermocouple system for advanced aircraft turbine engines T-2 AIBCBAFT [AD-A025500] N77-11062 Design and fabrication of an 8000 PSI THEBBODYNAMIC CICLES control-by-wire actuator for flignt testing in a Future trends in aero gas turbine design. II - T-2 C airplane Unconventional engines [AD-A024487] N77-11065 A77-11595 T-39 AIBCBAFT THBBBODT.NABIC EFFICIENCY Preliminary design-lift/cruise fan research and Air-cooled turnine cascade effectiveness criterion technology airplane flight control system A77-12503 [NASA-CR-137971] B77-11064 THEBMODYNAHIC PBOPEBTIES TABLES (DATA) Development of aircraft brake materials Operational mass properties data for military [ASLE PflEPBINT 76-LC-1B-3] A77-11195 aircraft - Data formulation, presentation and THEBMOELASTICITY usage Calculation of gas-turbine engine blades by the [SAKE PAPEB 1147] A77-12202 finite element method Small axial compressor technology, volume 2 A77-12583 tables THIN AIRFOILS [NASA-CB-134827-VOL-2] 877-11049 Approximate transonic profile flow with shock A77-10251 Forces on unstaggered airfoil cascades in unsteady in-phase motion [ASME PAPEB 76-FE-S] A77-10854

~~A-22 SUBJECT IBDBI TUBBIHB BLADES~~

THIH IIALLED SBEL1S TBAHSOBIC FLOB Calculation of multi-contour thin-walled Approximate transonic profile flow with shock structures by the method of sections A77-10251 [NASA-TT-F-17284] S77-11029 Pressure dlstrioutions over frontal /nose/ THBEE DIHEHSI08AL BOOHDABS L4YEB • surfaces of bodies of revolution in transonic The hyperbclicity of integral equations of flow at angles of attack of 0 to 10 deg momentum in a three-dimensional incompressible A77-1066U laminar boundary layer Transonic flows calculation by integral A77-10665 equation, relaxation and finite difference methods Advances in engineering science, volume 4 A77-12561 [NASA-CP-2001-VOL-4] 1177-10345 An extended integral eguation method for the Calculation of the flow around a swept wing, steady transonic flow past a two-dimensional taking into account the effect of the aerofoil three-dimensional boundary layer. Part 1: Wing A77-12562 with turbulent boundary layer Belaxation near a sonic line transonic flow [NLB-TR-75076-U] H77-11011 past subsonic lifting aircraft THBEE DIBEHSIOBAl FLOB A77-12563 Finite element and difference methods for cascades A transonic hodograph theory for aerofoil design A77-12557 A77-12561 Numerical studies of three-dimensional breakdown Test verification of a transonic airfoil design in trailing vortex wakes employing active diffusion control [KASA-CB-137888] N77-10014 [AD-A024297] N77-10029 Controlled and uncontrolled flow separation in Transonic performance of Mach 2.65 auxiliary flow three dimensions axisymmetric inlet [LR-591] N77-10999 [NASA-CB-2717] N77-10056 TBBDS1 ADGHEHTA1IOH Influence of wind tunnel wall boundary layers on Selection of compressor pressure ratio of snail two dimensional transonic tests GTE installed in bypass turbojet engine fan duct [AAAF-NT-76-13] N77-10083 A77-12513 Advances in engineering science, volume 1 Analysis and design of ejector diffuser for [NASA-CP-2001-VOL-4] N77-10315 optimum thrust Improved computational treatment of transonic flow [AD-A025491] H77-11356 about swept wings IHHOST BEVERSAL N77-10318 Determination of magnitudes of the parameters Transonic flow theory of airfoils and wings characterizing ducted airscoop operation N77-10351 downstream for airplane deceleration Inverse transonic airfoil design including viscous A77-12521 interaction THEOSI VECTOB CONTBOL N77-10354 Ground test of the D shaped vented thrust Viscous interaction with separation in transonic vectoring nozzle flow [NASA-CR-137959] N77-11107 [NASA-TT-F-17187] N77-10997 TILT BOTOB BESEABCB AIBCBAF1 EBOGBAH TBANSOHIC SPEED B. & D. project cost and schedule realism - A risk Advanced transonic aerodynamic technology analysis approach 1177-10365 A77-12455 IBANSONIC MIND TDNNELS TIHB OPTIHAL COHTBOL An integral eguation method for boundary Computational alternatives to obtain time optimal interference in a perforated-wall wind tunnel at jet engine control transonic speeds [NASA-CR-149106] N77-10060 [AD-A023493] N77-10023 TRACKING FILTEBS IBAHSPOBT AIBCBAFT Application of Liapunov model - Tracking parameter Maintaining transport aircraft identification for the CH-47 helicopter A77-12069 A77-12460 The next-generation subsonic transport IBAILING EDGES [SAKE PAPEB 1127] A77-12195 Free vortex sheets LH2 airport requirements study A77-12559 [BASA-CB-2700] H77-10032 Buffeting problems leading and trailing edge Critical analysis of comparisons between flight flow separation test results and wind tunnel test predictions in [AAAP-NT-76-7] N77-10050 subsonic and supersonic transport aircraft Application of the nonlinear vortex-lattice [HASA-TI-F-17185] N77-10049 concept to aircraft-interference problems Hydrogen-fueled suosonic aircraft: A perspective H77-10349 N77-10344 TBANSIENT LOADS The cryogenic wind tunnel Rotor dynamic state and parameter identification, N77-10368 from simulated forward flight transients, part 1 Application of design data derived from fatigue [NASA-CR-137963] N77-10003 tests with service-like load seguences for life Rotor dynamic state and parameter identification prediction wing structures of transport from simulated forward flight transients, part 2 aircraft [NASA-CB-137961] N77-10004 [LBF-FB-109/76] N77-11445 XBANSLAIIOBAL HOTION TBOSSES Experimental study of the aerodynamics of a Application of optimality criteria to automated helicopter rotor in translational flight. Two structural design dimensional simulation of the effects due to A77-10207 cyclic variations of the velocity vector TURBINE BLADES [AAAF-NT-76-20] 1177-10019 Pressure loss coefficient of impingement cooled TBANSHISSIONS (HACHIHE ELBHBHTS) leading edge system of a turbine blade A method for estimating the weight of aircraft A77-10772 transmissions Film cooling mth injection through slots [SAKE PAPEB 1120] A77-12191 A77-10773 TEABS08IC COBPBBSSOBS Lifting-surface theory of straight cascades of Compressor blade setting angle accuracy study. swept blades Volume 2: Data compilation A77-12218 [SASA-CB-135068-VOL-2] N77-11047 Air-cooled turbine cascade effectiveness criterion Small axial compressor technology, volume 1 A77-12503 [NASA-CR-134827-VOL-1] H77-11048 Dispersion of fatigue test data for cast Small axial compressor technology, volume 2 gas-turbine blades in association with tables structural and technological factors INASA-CB-134827-VOL-2] H77-110U9 A77-12579

~~A-23 TDBBISE EHGIHES SUBJECT INDEX~~

Calculation of gas-turbine engine blades by the Combustor design for low cost expendable turbojets finite element method [AD-A024541 ] N77-10070 A77-12583 TDBBOflACHIHEBI Design consideration for the Darrieus rotor Subsonic flows in turbomachines wind turbines A77-12556 A77-12872 IDEBDLENCE EFFECTS Investigation of slot cooling for high-speed The influence of vortex shedding on the generation aircraft of sound by convected turbulence (AD-A024316] N77-11061 477-10197 TDEBIHE ENGINES IOBBOLEN1 BODHDABX LAIEB Dynamic-stress-data management for aeromechanical Flow interaction near the tail of a body of testing of turbomachinery revolution. I - Flow exterior to boundary layer A77-12175 and wake Two-phase turbine engines using gas-liguid [ASME PAPEB 76-FE-M] A77-10855 mixture accelerated in nozzles Flow interaction near the tail of a body of A77-12680 revolution. II - Iterative solution for flow TOBBIHE IHSTBOHEHTS within and exterior to boundary layer and wake System considerations for reliable strain data [ASME PAPEB 76-FE-N] A77-10856 from gas turbine engines Calculation of the flow around a swept wing, 477-12176 taking into account the effect of the TUBBINE PDBPS three-dimensional boundary layer. Part 1: King Centrifugal compressor and pump stability, stall with turbulent ooundary layer and surge; Proceedings of the Conference, New [NLR-TE-75076-U] N77-11011 Orleans, La., March 22-25, 1976 Some supersonic wind tunnel nozzle boundary layer A77-10026 characteristics TDBBINE IHEELS [AD-A024980] N77-11018 Strength of compressor wheels of low-ductility TUBBOLENT HAKES alloys Measurement of wake vortex strength by means of A77-10383 acoustic back scattering TORBOCOHPBESSOHS A77-11712 Selection of compressor pressure ratio of small High speed computer studies of vortex motions in GTE installed in bypass turbojet engine fan duct relation to aircraft wake turbulence A77-12513 [AD-A024290] N77-11013 The rotating stator concept. Experimental TWISTING performance characteristics compared with the An experimental study of the nonlinear stiffness conventional compressor of a rotor blade undergoing flap, lag and twist [AD-A024465] N77-11411 deformations Transients in turbocompressors effect of [NASA-CB-137969] N77-10009 unsteady flow on compressor performance 110 DIMENSIONAL BODIES [AD-4024275] N77-11412 An extended integral equation method for the TDEBOFAN ENGINES steady transonic flow past a two-dimensional Selection of compressor pressure ratio of small aerofoil GTE installed in bypass turbojet engine fan duct 477-12562 A77-12513 Numerical solutions for laminar and turbulent Macroscopic study of time unsteady noise of an viscous flow over single and multi-element aircraft engine during static tests airfoils using body-fitted coordinate systems [NASA-TH-X-73556] N77-11052 N77-10355 Core noise source diagnostics on a turbofan engine liO DIMENSIONAL FLOi using correlation and coherence techniques The influence of vortex shedding on the generation [NASA-TH-X-73535] N77-11053 of sound by convected turbulence Study of small turbofan engines applicable to 477-10197 single-engine light airplanes Methods for elliptic problems in external [NASA-CH-137944] N77-11054 aerodynamics Method of discrete modeling and its application to 477-12554 estimation of TF30 engine variables The finite element method applied to fluid mechanics [NASA-TH-X-3443] H77-11057 477-12558 The rotating stator concept. Experimental Experimental study of the aerodynamics of a performance characteristics compared with the helicopter rotor in translational flight. Two conventional compressor dimensional simulation of the effects due to [4D-4024465] N77-11411 cyclic variations of the velocity vector T0BBOFAHS [AAAF-ST-76-20] N77-10019 A note on the acoustic effect of non-uniformly 110 FH4SE FLOI distributed stator rows Two-phase turbine engines using gas-liquid 477-10347 mixture accelerated in nozzles TOBBOGENEBATOBS A77-12680 Design consideration for the Darrieus rotor wind turbines A77-12872 u TDBBOJET ENGINE CONTBOL O.S.S.B. Equation solution accuracy in calculating jet Toward new heights air transportation in the engine characteristics Soviet Onion A77-12502 [NASA-TT-F-17248] 877-11019 TURBOJET E1GINES OH-1 HELICOPTER Selection of compressor pressure ratio of small Helicopter reliability growth evaluation GTE installed in bypass turbojet engine fan duct [AD-A025265] B77-11041 A77-12513 UNSTEADY FLOI Penetration and nixing of liquid injected into Unsteady pressure distributions on oscillating supersonic transverse gas stream airfoils in a supersonic cascade A77-12515 A77-10771 Heat transfer in tube entrance segment with Some problems of unsteady flow about aircraft initial flow swirl and transverse injection 477-12560 A77-12517 Transients in turbocompressors effect of Computational alternatives to obtain time optimal unsteady flow on compressor performance jet engine control [4D-4024275] N77-11412 [HASA-CF-149106] H77-10060 DFPEB SURFACE BLOIB FLIPS Simplified simulation models for control studies New developments in blown flap noise technology of turbojet engines [HASA-CB-145086] N77-10013 [NASA-CB-149107] H77-10061

~~A-24 SUBJECT IBDBI •BIGHT AHALTSIS~~

OBBAB TBiiSPOBfATIOi Prediction Bethods for Jet V/STOL Propulsion Intercity VTOL aircraft - A Havker Siddeley review Aerodynamcs, volume 2 A77-11283 [AD-A024023] ~' N77-10069 The helicopter air service passenger program: A Display/control requirements for VTOL aircraft retrospect [NASA-CB-145026] B77-11030 [PB-25U830/3] B77-10036 Analysis and design of ejector diffnser for OSES HAHOALS (COHEDTEB PBOGBAIS) optiiuo thrust V/STOL rotary propulsion systems: Noise [AD-A025491] B7.7-11356 prediction and redaction. Volume 3: Computer VIBBATIOB DABPIBG program users manual Reducing vibration by structural modification [AD-A027363/1] H77-10055 helicopter fuselage model Aeroelastic analysis for helicopter rotor blades A77-11279 with tine-variable, non-linear structural tvist VIBBATIOB BODE and multiple structural redundancy: Calculation of vibration modes and resonance Hatheaatical derivation and program user's manual frequencies of the Borthrop HF-5 [HASA-CB-2638] H77-10556 [HLB-TB-75050-m N77-11450 A computational system for aerodynamic design and VISCODS FLOf analysis of supersonic aircraft. Part 2: Inverse transonic airfoil design including viscous User's manual interaction [NASA-CB-2716] H77-11005 H77-10354 Numerical solutions for laminar and turbulent viscous flow over single and multi—element airfoils using body-fitted coordinate systems V/STOL AIBCBAFI B77-10355 Application of circulation control rotor Vortex/jet/mng viscous interaction theory and technology to a stopped rotor aircraft design analysis X-wing V/STOL [AD-A025290] N77-11017 A77-11277 VOBIBI BBEAKDOBN Intercity VTOL aircraft - A Havker Siddeley review Mingtip vortex dissipator for aircraft A77-11283 [NASA-CASE-LAB-11645-1] N77-10001 V/STOL rotary propulsion systems: Noise Hechanism of stabilization of the 'separation prediction and reduction. Volume 1: point' of a vortex during flow of a stream at Identification of sources, noise generating low subsonic velocity over a delta wing mechanisms, noise reduction mechanisms, and [NASA-TT-F-17283] S77-10012 prediction methodology Numerical studies of three-dimensional breakdown [AD-A027389/6] N77-10053 in trailing vortex wakes V/STOL rotary propulsion systems: Noise [NASA-CB-137888] B77-10014 prediction and reduction. Volume 2: Graphical VOBIBX SHEETS prediction methods Free vortex sheets [AD-A027390/4] N77-10054 A77-12559 V/STOL rotary propulsion systems: Hoise High speed computer studies of vortex motions in prediction and reduction. Volume 3: Computer relation to aircraft wake turbulence program users manual [AD-A024290] N77-11013 [AD-A027363/1] N77-10055 Vortex/jet/wing viscous interaction theory and On the status of V/STOL flight analysis N77-10367 [AD-A025290] N77-11017 V/STOL aircraft noise prediction (3et propulsors) VORTICES computer program The influence of vortex shedding on the generation [AD-A028765/6] N77-11045 of sound by convected turbulence Preliminary design-lift/cruise fan research and A77-10197 technology airplane flight control system Measurement of wake vortex strength by means of [NASA-CB-137971] N77-11064 acoustic back scattering VACDOH A77-11712 Influence of vind tunnel wall boundary layers on Application of the nonlinear vortex-lattice two dimensional transonic tests concept to aircraft-interference problems [AAAF-NT-76-13] N77-10083 N77-10349 VAHES Effects of jets, wakes, ana vortices on lifting A note on the acoustic effect of non-uniformly surfaces distributed stator rows [NASA-TM-X-73974] N77-10998 A77-10347 Development of predictive wake vortex transport VARIABILITY model ror terminal area wake vortex avoidance Supersonic variable-cycle engines [AD-A029049/4 ] N77-11002 [NASA-TM-X-73524] N77-10059 The inviscid pressure field on the tip of a VELOCITY DIS1BIBOTIOH semi-infinite wing and its application to the Heasurement of wake vortex strength by means of formation of a tip vortex acoustic back scattering [NASA-CB-2748] N77-11345 A77-11712 Experimental study of the aerodynamics of a helicopter rotor in translational flight. Two w dimensional simulation of the effects aue to IAKES cyclic variations of the velocity vector Tne effect of rotor blade wakes on centrifugal [AAAF-NT-76-20] N77-10019 compressor diffuser performance - A comparative VENTS experiment Ground test of the D shaped vented thrust A77-10032 vectoring nozzle Numerical studies of tbree-dimensional breakdown [NASA-CB-137959 ) N77-11107 in trailing vortex wakes VEBTICAL TAKEOFF AIBCBAFT [HASA-CB-137888] N77-10014 Intercity VTOL aircraft - A Hawker Siddeley review •EDGE FLOI A77-11283 ADisotropic radiatively coupled wedge flow VTOL BPVs - A technology assessment A77-10218 A77-12000 Nonlinear analysis of flows generated by the A method for estimating the weight of aircraft impulsive motion of a wedge transmlssions A77-12630 [SAWE PAPEB 1120] A77-12191 •BIGHT ANALYSIS Prediction Methods for Jet V/STOL Propulsion fuselage analytical weight estimation method Aerodynamics, volume 1 [SAWE PAPEfi 1102] A77-12182 [AD-A024022] N77-10068 Weight ana balance considerations in the design of the A-10A close air support aircraft [SAKE PAPEB 1104) A77-12183

~~A-25 RBIGBT EEDDCTIOH SDBJECI IHDBX~~

A method for estimating the "eight of aircraft Calculation of the longitudinal aerodynamic transmissions characteristics of wing-flap configurations with (SARE PAPEB 1120] 477-12191 externally blown flaps Aircraft loadability parameters - Some results of [NASA-CB-2705] N77-11006 an airline survey IING LOADING (SAKE PAPEB 1116] A77-12201 Preliminary sizing and performance evaluation of Operational mass properties data for military supersonic cruise aircraft aircraft - Data formulation, presentation and [HiSA-TH-X-73936] H77-11031 usage RING PLAHPOBHS CSAHE PAPEB 11173 A77-12202 High supersonic aerodynamic characteristics of (EIGHT REDUCTION five irregular planform wings with Application of optimality criteria to automated systematically varying wing fillet geometry structural design tested in the NASA/LaBC 4-foot OPHT (LEG 2) A77-10207 (LA45A/B) Estimating procedures associated mth aircraft [NASA-CB-147628] N77-10010 modificatioDS RING PBOFILES [SAWE PAPEB 1101] A77-12181 The hyperbolicity of integral equations of Advanced design composite aircraft, the next step momentum in a three-dimensional incompressible for composites laminar boundary layer [SAKE PAPEB 1105] A77-12184 A77-10665 RIND EFFECTS Some problems of unsteady flow about aircraft Optimal ride control for the Twin Otter, STOL A77-12560 aircraft Buffeting problems leading and trailing edge A77-10336 flow separation RIND TUNNEL BODELS [AAAF-NT-76-7] N77-10050 Experimental investigation of the boundary layer Program for establishing long-time flight service on a rotating cylinder performance of composite materials in the center A77-10208 wing structure of C-130 aircraft. Phase 4: The design, analysis and testing of a low budget Ground/flight acceptance tests wind tunnel flutter model with active [NASA-CB-145043] N77-11032 aerodynamic controls, volume 2 RING SLOTS [AD-A024480] N77-10090 Performance of steady and intermittent blowing jet Simulation of flight-type engine fan noise in the flaps and spanwise upper surface slots NASA-Lewis 9X15 anechoic wind tunnel [AD-A024364] N77-10027 [NASA-TM-X-73540 ] N77-11050 Three-component measurements on a model of a light RIND TUNNEL BOZZLES STOL aircraft with chordwise blowing Some supersonic wind tunnel nozzle boundary layer [ESA-TT-299] N77-10052 characteristics RING TIP VOBTICES [AD-A024980] N77-11018 Wingtip vortex dissipator for aircraft RIND TDNNEL TESTS [NASA-CASE-LAR-11645-1] N77-10001 Botational noise measurement in a wind tunnel by RING TIPS total sampling synchronization The inviscid pressure field on the tip of a A77-112814 semi-infmite wing and its application to the Performance of steady and intermittent blowing 3et formation of a tip vortex flaps and spanwise upper surface slots [NASA-CB-2748] N77-11345 [AD-A024364] N77-10027 RINGS The development of a computer aided airfoil design Application of optimality criteria to automated procedure including preliminary wind tunnel structural design experiments on a low Reynolds number high lift A77-10207 section, volume 1 Application of design data derived from fatigue [AD-A024361] N77-10028 tests with service-like load sequences for life Test verification of a transonic airfoil design prediction wing structures of transport employing active diffusion control aircraft [AD-A024297] N77-10029 [ LBF-IB-109/76] N77-11<445 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 TAR New Buffeting acguisition methods data Helicopter yaw axis augmentation investigation acquisition, military aircraft [AD-A024512] N77-11066 [AAAJ-NT-76-fl] N77-10051 1C-14 AIBCBAFT Influence of wind tunnel wall boundary layers on YC-14 - All blow and no puff general design two dimensional transonic tests details [AAAF-NT-76-13] N77-10083 A77-10525 The AFFDL-Nielsen flow-field study [AD-A023755] N77-11015 A wind tunnel captive aircraft testing technique [AD-A023690] S77-11037 HIND TUNNEL RAL1S Influence of wind tunnel wall boundary layers on two dimensional transonic tests [ AAAF-NT-76-13] N77-10083 RIND TUNNELS The cryogenic wind tunnel N77-10368 Acoustical evaluation of the NASA Langley V/STOL wind tunnel [NASA-CB-145087] N77-11068 BIHDPORBBED GENEBATOBS Design considefation for the Darrieus rotor wind turbines A77-12872 Early operation experience on the EBDA/NASA 100 kB wind turbine rotor blade loads [NASA-TH-X-71601 ] N77-106MO RING FLAPS Three-component measurements on a model of a light STOL aircraft with chordwise blowing [ESA-TT-299] N77-10052

~~A-26 PERSONAL AUTHOR INDEX~~

~~AERONAUTICAL ENGINEERING//) Special Bibliography (Suppl 80) FEBRUARY 1977~~

~~Typical Personal Author Index Listing~~

PERSONALAUTHOR BOBBOOS. C. I. Simulation of an automatically-controlled STOL ABKHIPOV, A. H. aircraft in a microwave landing system nultipatb Dispersion of fatigue test data for cast environment gas-turoine blades in association with [HASA-TB-it-7315't} M77-11063 structural and technological factors A77-12579 ABMAND, C. Rotational noise measurement in a wind tunnel by total sampling synchronization A77-11281 ABNOLD, J. B. Army preliminary evaluation YOH-58A helicopter with a flat-plate canopy Listings m this index are arranged alphabetically by personal author The title [AD-A02M501] N77-11039 of the document provides the user with a brief description of the subject matter AfiPASI, D. J. The report number helps to indicate the type of document cited (eg NASA Method of discrete modeling and its application to report translation NASA contractor report) The accession number is located estimation of TF30 engine variables beneath and to the right of the title eg N77 11063 Under any one authors [ NASA-TM-X-3M3 ] N77-11057 name the accession numbers are arranged m sequence with the IAA accession ASHIZAIA, H. Development of a graphite norizontal stabilizer numbers appearing first [AD-A023767] S77-11036 ATHANS, H. The stocnastic control of the F-8C aircraft using the multiple model adaptive control /MMAC/ method A77-12U28 ADAHS, G. J. AYEAS, P. Dual-spin spacecraft dynamics under conditions of Experimental investigation of the near-surge flow a rotating unbalanced platform and rotor asymmetry in a high performance centrifugal compressor [IAF PAPER 76-019] A77-10882 A77-10036 ADELHAH. B. M. Resizing procedure for structures under combined mechanical and thermal loading B A77-10214 BAGHDADI, S. ADEBHOLD, J. B. The effect of rotor blade wakes on centrifugal Civil uses of remotely piloted aircraft compressor diffuser performance - A comparative [NASA-CH-137894] N77-100t7 experiment Civil uses of remotely piloted aircraft A77-10032 [r)ASA-CE-137895] N77-10CW8 BAILEY, F. B. AKHHEDZIANOV, A. B. Improved computational treatment of transonic flow Equation solution accuracy in calculating jet aoout swept wings engine characteristics N77-103U8 A77-12502 BA1ASHO?, B. F. AKHEEHENKO, V. L. Dispersion of fatigue test data for cast Strength of compressor wheels of low-ductility gas-turbine blades in association with alloys structural and technological factors A77-10383 A77-12579 AKSELBOD, S. KB. BALLHiOS, I. F. Equation solution accuracy in calculating jet Improved computational treatment of transonic flow engine characteristics about swept wings A77-12502 N77-10348 ALDEB, G. H. BANEBJEE, D. Compressible subcritical flow through anally Botor dynamic state and parameter identification, symmetric sharp-lipped orifices and nozzles from simulated forward flight transients, part 1 A77-12555 [NASA-C8-137963] N77-10003 ALEKSAHDBOV, A. G. Methods studies on system identification from Magnetic particle inspection of aviation engine transient rotor tests vanes [NASA-CB-137965] H77-10005 A77-11606 BABCHOKOV, A. I. ALGBB, B. S. Laser air-jet engine Aircraft ground fire suppression and rescue A77-11887 systems. Characteristics of kinematic jet fuel BABDAOD. J. fires cascading and rod fuel geometries Critical analysis of comparisons between flight [AD-A02DHH7] H77-11022 test results and wind tunnel test predictions in ALTABBS, H. S. subsonic and supersonic transport aircraft Aircraft ground fire suppression and rescue [HASA-TT-F-17185] N77-10049 systems. Characteristics of kinematic jet fuel BABIHOV, 7. A, fires cascading and rod fuel geometries The hyperbolicity of integral equations of [AD-A021DU7] H77-11022 momentum in a three-dimensional incompressible AHLICKE, B. B. laminar boundary layer Numerical solutions for laminar and turbulent A77-1066S viscous flow over single and multi-element BABOH, J. B. airfoils using body-fitted coordinate systems Anisotropic radiatively coupled wedge flow H77-10355 A77-10218 ABGIBIS, J. B. The finite element method applied to fluid mechanics A77-12558

~~B-1 BASTICK, H. PERSONAL AOTHOB INDEX~~

BABTICK, H. BRASHEARS, H. B. The production and refining of crude oil into Development of predictive wake vortex transport military fuels model for terminal area wake vortex avoidance [AD-A024652 ] N77-11207 [AD-A0290-49/4] H77-11002 BASH, I. T. BBBHNAN, M. J. Final approach performance monitor Intercity VIOL aircraft - A Hanker Siddeley review tAD-4028513/0] N77-11024 A77-11283 BASSO, B. J. BRBNHAN, T. C. Computational alternatives to obtain tine optimal Simplified simulation models for control studies jet engine control of turbojet engines tNAbA-CR~149106 ] N77-100oO [NASA-Cfi-149107] N77-10061 BATY, D. 1. BBBIEB, G. D. Rationale and description of a coordinated cockpit LH2 airport requirements study display for aircrart flignt nanagement [NASA-C8-2700] H77-10032 tNASA-TM-X-3457] N77-11044 BRILEY, I. B. BAILI, A. D. <3. The invlscld pressure field on tne tip of a Fuselage analytical weight estimation method semi-infinite wing and its application to the [SAUL PAPER 1102] A77-12182 lormation of a tip vortex BELSON, J. [ NASA-CR-2748] N77-11345 Simulating the last 100 ft BHOiH, C. E. A77-10648 High speed computer studies of vortex motions in BENNETT, J. A. relation to aircraft wake turbulence Design considerations tor laminar flow control [AD-A024290] N77-11013 aircraft BBOB8, S. C. N77-103bo Simulation of an automatically-controlled STOL BERUAHD-G0ELJ.E, B. aircraft in a microwave landing system multipath Influence of wind tunnel wall boundary layers on environment two dimensional transonic tests [ iUStt-TH-i-7315U] N77-11063 [AAAF-HT-76-13] N77-10083 BROIN, T- i. BEBBIER, F. C.. Effects of atmospheric conditions on tne operating Performance of steady and intermittent blowing jet characteristics of supersonic cruise aircraft flaps and spanwise upper surface slots [IiF PAPiii 76-112] A77-10912 [AD-A024364] N77-10027 BRUTOM, W. H. BIELAUA, B. L, Metnod of discrete modeling and its application to Investigation or a bearingless helicopter rotor estimation of TF30 engine variables concept having a composite primary structure [NASA-TM-X-3H43 ] N77-11057 [NASA-CE-2637 ] N77-10044 BOGAYEV, B. P. Aeroelastic analysis for helicopter rotor blades Toward new neights with time-variable, non-linear structural twist [NASA-TT-F-17248] N77-11019 and multiple structural redundancy: BOLL, H. L. datnematlcal derivation and program user's manual Bearing restoration by grinding [NASi-CB~2638] N77-1055b [NASA-CH-149188] N77-11404 BILLINGS, B. £. BOHKIN, F. V. Survey of hydrogen energy application projects Laser air-jet engine A77-12778 A77-11887 BLAKNEY, D. F, BDBNUAH, D. C. V/STOL aircraft noise prediction (jet propulsors) {Measurement of wake vortex strength by means of [AD-A028765/6] N77-11045 acoustic back scattering BLOKPOEI, H. A77-11712 Bird hazards to aircraft: Problems and prevention BDHBOOS, C. N. of bird/aircraft collisions Simulation of an automatically-controlled STOL A77-10697 aircraft in a microwave landing system multipath BOEBS10EL, J. B. environment A transonic hodograph theory for aerofoil design [NASA-TM-X-73154] 1177-11063 A77-12561 BOILER, R. 9. BOGGS, I. A. A wind tunnel captive aircraft testing technique Full temperature range protective system for [AD-A023690] N77-11037 fastener areas of carrier-based naval aircraft [AD-A024523] N77-10210 BOGOHOLOV, E. H. Air-cooled turoine cascade effectiveness criterion CALVERT, B. J. A77-12503 Concorde navigation BOLDING, R. H. A77-10200 The design, analysis and testing of a low budget CAHHADAY, R. L. wind tunnel flutter model with active Landing practices of general aviation pilots in aerodynamic controls, volume 2 single-engine light airplanes [AD-A024M80] N77-10090 [NASA-TN-D-8283] N77-11033 BOBGMAN, D. C. CASSDALE, R. P. 6 D. project cost and schedule realism - A risk Rotor impedance measurements at model scale analysis approach A77-11281 A77-12455 CARLSON, K. T. BOWED, R. An analysis of the intrastate air carrier ' The production and refining of crude oil into regulatory forum. Volume 2: Technical report military fuels [AD-A023762] N77-10035 [AD-A024652] N77-11207 CABLSOS, L. it BRADLEY, E. S. Inverse transonic airfoil design including viscous An analytical study for subsonic oblique wing interaction > transport concept N77-10354 fNASA-CB-137896] N77-10045 CABBAiAY, N. J. An analytical study for subsonic oblique wing Aircraft loadability parameters - Some results of transport concept an airline survey [NASA-CR-137897] N77-10046 [SAHE PAPER 1146] A77-12201 BBANGEB, J. CARROLL, R. L. Mechanism of material fatigue during the crack Application of Liapunov model - Tracking parameter initiation stage identification for the CH-47 helicopter [ICAF-DOC-895] N77-11141 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 DABBBRG, J. B. CHAHPIBE, B. A. Sone supersonic wind tunnel nozzle boundary layer A flight investigation of piloting techniques and characteristics crosswind limitations daring visual STOL-type [AD-A024980J B77-11018 landing operations DAVIBS. B. E. [BASA-TS-D-8284] H77-11001 Design mechanical properties, fracture toughness, CBAPPBLL. B. S. fatigue properties, exfoliation and The rotating stator concept. Experimental stress-corrosion resistance of 7050 sheet, performance characteristics compared with the plate, hand forgings, die forgings and extrusions conventional compressor [AD-A024609] 877-10195 [AD-A021465] H77-11411 DEAL, P. L. CHAB1AT, A. F. A flight investigation of piloting technigues and Holographic flow visualization crosswind limitations during visual STOL-type [NASA-CB-1U9182] N77-11365 landing operations CHATTOT, J. J. [HASA-TH-D-8284] H77-11001 Viscous interaction with separation in transonic DEAH, B. C., JB. flow Centrifugal compressor and pump stability, stall [MASA-T1-F-17187] N77-10997 and surge; Proceedings of the Conference, New CHEH, S. H. Orleans, La., March 22-25, 1976 Bearing restoration by grinding A77-10026 [HASA-CB-149188] N77-11404 DEBOBD, J. B. CHENEY, H. C., JB. High-nickel alloys for gas turbines Investigation of a bearingless helicopter rotor A77-11325 concept having a composite primary structure DEJABHBTTE, F. B. [NASA-CB-2637] N77-100U4 Lifting surface theory for rectangular wings CHIEN, ft. T. N77-1031I7 Normal impingement of a supersonic jet on a plane: DELEBY, J. A basic study of shock-interference heating Viscous interaction with separation in transonic [AD-A024511] N77-10026 flow CHOO, L. C. [NASA-TT-F-17187] N77-10997 Development of predictive wake vortex transport OEBABCHI, J. N. model for terminal area wake vortex avoidance Design and fabrication of an 8000 PSI [ AD-A0290U9/U] N77-11002 control-by-wire actuator for flight testing in a CLARK, B. J. T-2 C airplane Macroscopic study of time unsteady noise of an [AD-A02U487] N77-11065 aircraft engine during static tests DENNING, B. H. £ NASA-TH-X-73556] JJ77-11052 Future trends in aero gas turbine design. II - CLABK, 1. E. Unconventional engines Helicopter yaw axis augmentation investigation A77-11595 [AD-A024512] N77-11066 DIETRICH, D. A. CLAYTON, B. B. Simulation of flight-type engine fan noise in the Beduction of gaseous pollutant emissions from gas NASA-Lewis 9X15 anechoic wind tunnel turbine combustors using hydrogen-enriched jet [NASA-TM-X-735140] N77-11050 fuel DILLS, T. [NASA-CB-1491«6] N77-11198 Operational mass properties data for military COLEHJN, B. G. aircraft - Data formulation, presentation and A computational system for aerodynamic design and usage analysis of supersonic aircraft. Part 2: [SAKE PAPER 11t7] A77-12202 User's manual DIXOB, C. J. [NASA-CR-2716] N77-11005 Vortex/jet/wing viscous interaction theory and , CONIAI, G. 5. analysis Helicopter reliaoility growth evaluation [AD-A025290] N77-11017 [AD-A025265] N77-11041 DOBBS, S. I. C03GBOVE, O. V. Application of optimality criteria to automated Emissions of an ATCO Lycoming 0-320-DIAD air structural design cooled light aircraft engine as a function of A77-10207 fuel-air ratio, timing, and air temperature and DONE, G. T. S. humidity Reducing vibration by structural modification [NASA-TM-X-73500] N77-10058 A77-11279 Effect of air temperature and relative humidity at DODGHTY, B. I. various fuel-air ratios on exhaust emissions on Competition for airspace - Bird strikes and a per-mode basis of an Avco Lycoming Q-320 DIAD aircraft operations light aircraft engine. Volume 2: Individual A77-11261 data points D01E1L, E. H. CNASA-TH-X-73507] N77-10066 An experimental study of the nonlinear stiffness CBBSS, S. T. of a rotor blade undergoing flap, lag and twist Botor dynamic state and parameter identification deformations from simulated forward flight transients, part 2 [NASA-CH-137968] , 1177-10008 [NASA-CR-137964 ] N77-1000U An experimental study of the nonlinear stiffness Additional experiments with a four-bladed cyclic of a rotor blade undergoing flap, lag and twist pitch stirring model rotor, part 2 of second deformations yearly report [NASA-CB-13796:)] N77-10009 [NASA-CR-137966] N77-10006 DBOKONOV, A. S. CURRY, B. E. Study of flow swirl influence on axiradial Display/control requirements for VIOL aircraft dlffuser effectiveness [NASA-CB-1U5026] N77-11030 A77-12520 CORTISS, H. C., JB. DDNCAN, P. S. Sensitivity of hingeless rotor blade flap-lag A note on the acoustic effect of non-uniformly stanility in hover to analytical modelling distributed stator rows , assumptions A77-10347 [NASA-CR-137967] N77-10007 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. FOSS, I. Ei. JR. The finite element method applied to fluid mechanics Assessment of variable-cycle engines for Bach 2.7 A77-12558 supersonic transports [NASA-TB-X-73977] 877-10065 FOOLKES, B. B., OB. Terminal area guidance along curved paths: A E01ABDS, B. stochastic control approach The productioo and refining of crude oil into . H77-10383 nilitary fuels FOOBHEI, B. B. [AD-A021652] N77-11207 Holographic flow visualization BICHHBB, L. J. [NASA-CB-119182] B77-11365 An analysis of the intrastate air carrier FBICK, J. regulatory forum. Volume 2: Technical report Improved computational treatment of transonic flow [AD-A023762] N77-10035 about swept wings ELGIN, J. B. H77-10318 Anisotropic radiatively coupled wedge flow FBTBOBG, G. C. A77-10218 Hot corrosion studies of four nickel-base ELLIOTT, 0. G. superalloys: B-1900, HASA-TBW VIA, 713C and IH738 Two-phase turbine engines [NASA-TB-X-73179] B77-10183 A77-12680 FOCHS, i. P. ELI, I. L. A systems approach to all weather landings Performance of steady and intermittent bloving ]et 477-10138 flaps and spanwise upper surface slots FOQOA, B. B. [AD-A021361] H77-10027 Beliability of automated flight service stations EHGLE, B. B. A77-10112 Current practice on estimating crack growth damage accumulation with specific application to structural safety durability and reliability [AD-A025199] H77-11478 GAIGNEBET, E. ESKEB, D. I. New buffeting acquisition methods Ground test of the D shaped vented thrust [AAAF-NT-76-8] B77-10051 vectoring nozzle GALLAGBEB, J. [NASA-CB-137959] N77-11107 Current practice on estimating crack growth damage EVANS, P. F. accumulation with specific application to Numerical studies of three-dimensional breakdown structural safety durability and reliability in trailing vortex wakes [AD-A025199] B77-11178 [NASA-CR-137888] N77-10011 GALLAGHEB, J. P. BVEBTZ, E. Estimating fatigue-crack lives for aircraft - Noise generating by interaction between subsonic Technigues ]ets and blown flaps A77-11177 CDLR-FB-76-20] N77-10067 GALLIPPI, B. J. Development of a graphite horizontal staoilizer [AD-A023767] N77-11036 GABABEDIAN, P. B. FALCAO, A. F. DE O. Transonic flow theory of airfoils and wings Lifting-surface theory of straight cascades of B77-10351 swept blades GAOKBOGEB, D. B. 477-12218 Rotor impedance measurements at model scale FAVIEB, D. 477-11281 Experimental study of the aerodynamics of a GAVIH, P. helicopter rotor in translational flight. Two Concorde maintenance as seen by the designer - The dimensional simulation of the effects due to maintenance program • cyclic variations of the velocity vector 477-12115 [AAAF-NT-76-20] N77-10019 GEPBABT, L. S. FBDOBOV, I. I. A systems approach to all weather landings Heat-pipe regenerator for gas turbine engine 477-10138 477-12528 GEBA, J. FEDOBOV, V. M. Design of active controls for the NASA F-8 digital Analytic and experimental study of turbine rotor fly-by-wire airplane blade temperature N77-10377 477-12522 GEBHABZ, J. J. FEBBI, A. Compilation of measures to increase the fatigue Investigation of slot cooling for high-speed strength of aircraft structures aircraft [LBF-Tfl-126/75] N77-11117 [AD-A021316] N77-11061 GIBSON, J. S. FETTEBHAM, O. E., JB. New developments in blown flap noise technology Preliminary sizing and performance evaluation of [NASA-CH-115086] N77-10013 supersonic cruise aircraft V/STOL aircraft noise prediction (}et propulsors) [NASA-TH-X-73936J N77-11031 [ AD-A028765/6] 1177-11015 FEUELL, L. L. GILIABD, G. B. Conference on the Development of Fire-Resistant Effects of atmospheric conditions on the operating Aircraft Passenger Seats cnaracteristics of supersonic cruise aircraft [NASA-TM-X-73111] N77-11111 [IAF PAPER 76-112] 477-10912 FILECCIA, G. L. GLASGOH, J. C. A systems approach to all weather landings Eariy operation experience on the EBDA/N4SA 100 kH A77-10138 wind turbine FISBBEIH, B. 0. [NAS4-TH-X-71601 ] N77-10610 Selection of compressor pressure ratio of small GODFBIEO, L. B. GTE installed in bypass turbojet engine fan duct Certification of the replacement of glass fabric A77-12513 per mat. spec. 5.670/1, with glass fabric per FISHEB, B. D. mat. spec. 5.670 in the F27 plastic sandwich 4 flight investigation of piloting technigues and wing-and-stabilizer-leading edges crosswind limitations during visual STOL-type [FOK-R-1876] N77-11122 landing operations . GOEBEL, F. L. [NASA-TN-D-B281] N77-11001 Conceptual designs for a modular remotely piloted FOLLIOT, B. G. vehicle New orientations of intergovernmental [4D-A023811] N77-11035 organizations of civil aviation 477-12170 PEBSOBAL AOTBOH INDEX BOLLEY, II. E.

GOGOLBV, I. G. BALL, G. F. Study of flow swirl influence on axiradial The inviscid pressure field on the tip of a diffuser effectiveness semi-infmite wing and its application to the A77-12520 formation of a tip vortex GOLDEHBEBG, K. [HASA-CB-2718] H77-11345 Structural tests of aerodynamic surfaces - A BALL, H. G. systems approach to analysis and design Transonic flows A77-12206 A77-12561 GOODE, H. B. BASAO, B. Landing practices of general aviation pilots in Bearing restoration by grinding single-engine light airplanes [ NASA-CR-149183] N77-11404 [NASA-TN-D-8283] N77-11033 ifANCOCK. G. J. GOODWIN, F. K. Some problems of unsteady flow about aircraft Calculation of the longitudinal aerodynamic A77-12560 characteristics of wing-flap configurations with HAUIHG, B. K. externally blown flaps Design and fabrication of an 8000 PSI [NASA-CR-2705] N77-11006 control-by-wire actuator for flight testing in a GORDON, G. T-2 C airplane Civil uses of remotely piloted aircraft [AD-A024487 ] M77-11065 [NASA-CH-137894] N77-10047 BABDIB, L. V. Civil uses of remotely piloted aircraft Transients in turbocompressors [NASA-CR-137895] N77-10048 [AD-A024275] H77-11U12 GOHODETSKII, V. B. HARRIS, B. F. Strength of compressor wheels of low-ductility Analog computation assessment of the risk of alloys structural failure due to crack growth under A77-10383 random loading GOTLIEB. P. [AD-A025266] H77-11012 Preliminary design-lift/cruise fan research and HABTILL, B. E. technology airplane flight control system Program for establishing long-time flight service [NASA-CR-137971] N77-11064 performance of composite materials in the center GBEEBE, C. S. wing structure of C-130 aircraft. Phase 4: The stochastic control of the F-8C aircraft using Ground/flight acceptance tests the multiple model adaptive control /MMAC/ method [NASA-Ci-145043] N77-11032 A77-12428 BARLEY, A. V. GBEEBE, B. L. Development of a graphite horizontal stabilizer Comoustor design for low cost expendable turbo^ets [AD-A023767] N77-11036 [ AD-A024541 ] N77-10070 HAYS, L. G. GREY. J. Two-phase turbine engines The technical basis for a national civil aviation 477-12680 research, technology, and development /BT £ D/ HECKHANN, G. policy; Proceedings of the Workshop Conference, New buffeting acguisition methods Crystal City, Va., Harch 10-12, 1976 [AAAF-NT-76-8] N77-10051 A77-12927 UEIDHANH, 0. F. GBIFFITH, I. C. Simulation of flight-type engine fan noise in the Transients in turbocompressors NASA-Lewis 9X15 anechoic wind tunnel [AD-A024275] N77-11412 [NASA-TH-X-73540] N77-11050 GBOSCHE. F. B. Macroscopic study of time unsteady noise of an Experiments on the feasibility of aero-acoustic aircraft engine during static tests measurements in the 3-m low speed wind tunnel [N4SA-TH-X-73556 ] N77-11052 of the DFV1E-AVA BESSBAM, F. H. [ESA-TT-311] N77-10873 Conceptual designs for a modular remotely piloted GDEST. I. C. B. vehicle Concorde navigation [AD-A023844] N77-11035 A77-10200 HBBITT, B. L. GUILLERBIHET, 1. Computational methods and problems in aeronautical Experimental study of the aerodynamics of a fluid dynamics helicopter rotor in translational flight. Two A77-12551 dimensional simulation of the effects due to BILLHAH, B. E. cyclic variations of the velocity vector Investigation into the optimum use of advanced [AAAF-NT-76-20] N77-10019 displays in future transport aircraft GOHEBOV, KB. S. 477-11594 Eguation solution accuracy in calculating ]et BITCH, B. engine characteristics Practical requirements in industry 477-12502 A77-12552 HO, T.-L. Development of aircraft brake materials H [ASLE PBEPBINT 76-LC-1B-3] 477-11195 HACKEIT, J. E. HOFFBAN, B. C. Numerical studies of three-dimensional breakdown Display/control requirements for VTOL aircraft in trailing vortex wakes [NAS4-C8-145026] B77-11030 [NASA-CB-137888] N77-10014 HOHBHBHSEB, K. B. BAGBOP, E. Rotor dynamic state and parameter identification, . Co-operation in the European aircraft from simulated forward flight transients, part 1 manufacturing industry and among the scheduled [NASA-CH-137963] B77-10003 airlines /Brancker Memorial Lecture/ Rotor dynamic state and parameter identification A77-11311 from simulated forward flight transients, part 2 BAIGHT, C. B. [NASA-CB-137964] N77-10004 Test verification of a transonic airfoil design Methods studies on system identification from employing active diffusion control transient rotor tests [AD-A024297] N77-10029 [NASA-CB-137965] S77-10005 BALE, I. J. Additional experiments with a four-bladed cyclic Best-range flight conditions for cruise-climb pitch stirring model rotor, part 2 of second flight of a ]et aircraft yearly report N77-10379 [NASA-CB-137966] N77-10006 BILL, A. i. HOLLEY, B. B. A flight investigation of piloting techniques and Optimal ride control for the Twin Otter, STOL crosswind limitations during visual STOL-type aircraft landing operations 477-10336 [HASA-TH-D-828U] 877-11001

~~B-5 HOLLISTEB. H. H. PEBSOHAL ADTHOB INDEI~~

HOLLISTEB, I. B. KEBPKE, E. B. Display/control requirements for VTOL aircraft Emissions of an AVCO Lycoming 0-320-DIAD air [>)ASA-CB-145026] N77-11030 cooled light aircraft engine as a function of BOLflAH, F. F. fuel-air ratio, timing, and air temperature and Compressor blade setting angle accuracy study, humidity volume 1 [NASA-TH-X-73500] N77-10058 [NASA-CB-135068-VOL-1 ] N77-11046 KEHPKB, E. B. Compressor blade setting angle accuracy study. Effect of air temperature and relative humidity at Volume 2: Data compilation various fuel-air ratios on exhaust emissions on [ NASA-CH-135068-VOL-2] N77-11047 a per-mode basis of an Avco Lycoaing 0-320 DIAD Small axial compressor technology, volume 1 light aircraft engine. Volume 2: Individual [NASA-CS-134827-VOL-1 ] N77-11048 data points Small axial compressor technology, volume 2 [NASA-TM-X-73507] N77-10066 [NASA-CR-134827-VOL-2] N77-11049 KHALATOV, A. A. HONBATH, J. Heat transfer in tube entrance segment with An analytical study for subsonic oblique wing initial flow swirl and transverse injection transport concept A77-12517 [NASA-CR-137896] S77-10045 KIDWELL, J. B. BORE, H. S. Compressor blade setting angle accuracy study, The influence of vortex shedding on the generation volume 1 of sound by convected turbulence [NASA-Cfl-1350b3-VOL-1 ] N77-11046 A77-10197 Compressor blade setting angle accuracy study. HUBEB, H. Volume 2: Data compilation Hingeless rotor dynamics in high speed flight [NASA-CR-135063-VOL-2] N77-11047 A77-11280 Small axial compressor technology, volume 1 HDGHES, A. D. [NASA-CR-134827-VOL-1] H77-110U8 Beducing vibration by structural modification Small axial compressor technology, volume 2 A77-11279 [NASA-CB-134827-VOL-2] N77-11049 UDBN, B. V. KILEBO, A. B. S. The fuel approach to control emissions from aircraft Transport progress in practice: Air transport in [IAF PAPER 76-111] A77-10911 Africa - East African Airways Corporation HWANG, J. D. Experience B. S D. project cost and schedule realism - A risk A77-11312 analysis approach KILGOBE, R. A. A77-12455 The cryogenic wind tunnel N77-10368 KIZEB, J. A. Program for estaolishing long-time flight service IAHKIH, V. I. performance of composite materials in the center Program system for computer calculations of jet uing structure of C-130 aircraft. Phase 1: engine characteristics Ground/flight acceptance tests A77-10349 [NASA-CR-145043] N77-11032 ILLINGWOBTH, C. B. KLBINBAN, D. L. Computational methods and problems in aeronautical Display/control requirements for VTOL aircraft fluid dynamics [NASA-CB-145026] N77-11030 A77-12551 KLEVANSKII, V. H. INTANO, G. F. Penetration and mixing of liquid injected into Helicopter yaw axis augmentation investigation supersonic transverse gas stream [AD-A024512] N77-11066 A77-12515 ISKAKOV, K. S. KLOEPPEL, V. Analytic and experimental study of turbine rotor Noise generating by interaction between subsonic blade temperature jets and blown flaps A77-12522 [DLB-FB-76-20] N77-10067 IZOKH, V. V. KNAGG, J. A. Signal-treatment methods during aircraft-engine Estimating procedures associated with aircraft inspection based on vibroacoustic noises modifications A77-11603 [SAKE PAPER 1101] A77-12181 KOEBNEB, B. Three-component measurements on a model of a light STOI aircraft with chordwise blowing JACOBSON, I. 0. [ESA-TT-299] N77-10052 Experimental investigation of the boundary layer KOHL, F. J. on a rotating cylinder Hot corrosion studies of four nickel-base A77-10208 superalloys: B-1900, NASA-THW VIA, 713C and IN738 JOHANI, T. [NASA-Tfl-X-73479] N77-10183 A systems approach to all weather landings KONOV, V. I. A77-10438 Laser air-jet engine JOBHSOS, i. B. A77-11887 Aircraft ground fire suppression and rescue KOBBSBEEG, B. J. systems. Characteristics of kinematic ]et fuel An investigation of the effect on aerodynamic fires cascading and rod fuel geometries forces caused by the addition of end plates to [AD-A02i)4«7] H77-11022 helicopter rotor blades [AD-A023541] N77-1002U KOTLIAB, L. K. K Determination of magnitudes of the parameters KABDIL, O. A. characterizing ducted airscoop operation Application of the nonlinear vortex-lattice downstream concept to aircraft-interference problems A77-12521 N77-10349 KODBTIDBS, D. A. KAECHHEB, A. Conference on the Development of Fire-Besistant Core noise source diagnostics on a turbofan engine Aircraft Passenger Seats using correlation and coherence techniques [NASA-TM-X-7311<1] N77-11111 [HASA-Tfl-X-73535] N77-11053 KOTICH. G. KEHP, H. H. Performance of 1.15-pressure-ratio fan stage at Forces on unstaggered airfoil cascades in unsteady several rotor blade setting angles with reverse in-phase motion flow [ASHE PAPER 76-FE-S ] A77-10854 [NASA-TH-X-3451] U77-11008

~~B-6 PEBSOBAL AOTBOB IHDEI BAHGIBB, K. 1.~~

KOZHEVHIKOV, A. V. LBE, I. B. Heat transfer in tube entrance segment with The stochastic control of the F-8C aircraft using initial flow swirl and transverse injection the unltiple model ada£"iive control /BHAC/ nethod 177-12517 A77-12128 EOZLOV, I. A. LEHBAH, G. B. Strength of compressor wheels of low-ductility Development of a graphite horizontal stabilizer alloys [AD-A023767] S77-11036 A77-10383 LEDTIB, E. G. KBABBENBOEHL, B. Pressure distributions over frontal /nose/ Maintaining transport aircraft surfaces of bodies of revolution in transonic A77-12069 flow at angles of attack of 0 to 10 deg KBAFT, E. B. A77-10664 An integral equation method for boundary LBVABT, F. interference in a perforated-nail Kind tnnnel at Study of the subsonic flow around a sharp leading transonic speeds edge [AD-A023493] 1177-10023 [AAAF-HT-76-14] B77-10017 KEEIB, I. J. LBBIS. G. E. Macroscopic study of tine unsteady noise of an Preliminary design-lift/cruise fan research and aircraft engine during static tests technology airplane flight control system [NASA-TH-X-73556] H77-11052 [NASA-CB-137971] H77-11064 KBUTOVA. H. B. LIHDBSBADB, B. Thermal analysis of flight vehicle compartment VTOL BPVs - A technology assessment structure A77-12000 A77-12509 LIBSCOTT. B. S. EOLIICKI, P. V. Early operation experience on the EBDA/NA5A 100 kH Influence of aircraft angle of attack on high G wind turbine cockpit design [MASA-TH-X-71601] H77-10640 [AD-A025083] H77-110..3 LITTLE, L. J. KDHCHAL, K. Preliminary design-lift/cruise fan research and The production and refining of crude oil into technology airplane flight control system military fuels [HASA-CB-137971] 1177-11064 [AD-A024652] N77-11207 LOCK, B. C. KDBOSAKA, H. Computational methods and problems in aeronautical Unsteady pressure distributions on oscillating fluid dynamics airfoils in a supersonic cascade A77-12551 A77-10771 Methods for elliptic problems in external KVITKA, A. L. aerodynamics Calculation of gas-turbine engine blades by the A77-12554 finite element method LOKAI, H. V. A77-12583 Heat-pipe regenerator for gas turbine engine A77-12528 LOSBB, J. E. Interface between maintainability and commercial LACBOIS, A. H. aircraft spares support Fracture toughness of 8mm 2024-T3 non clad plate A77-10483 with long central cracks LOHAK, B. [FOK-B-1879] N77-11U49 Application of design data derived from fatigue LANDiEBEB, L. tests with service-like load sequences for life Flow interaction near the tail of a body of prediction revolution. I - Flow exterior to boundary layer [LBF-FB-109/76] 1177-11445 and wake LDCKBIHG, J. Bi [ASHE PAPEB 76-FE-M] A77-10855 An application of the suction analog for the Flow interaction near the tail of a body of analysis of asymmetric flow situations revolution. II - Iterative solution for flow 1177-10350 within and exterior to boundary layer and wajce LONDBI, J. L. [ASHE PAPER 76-FE-N] A77-10856 A computational system for aerodynamic design and LSHGEBEUX, P. analysis of supersonic aircraft. Part 2: 'C.221, the new French target drone User*s manual A77-11625 [NASA-CB-2716] 1177-11005 LARUELLE, G. LYSTAD, H. D. Study of the suosonic flow around a sharp leading Catapult launch fatigue investigation of the model edge S-2 E airplane CAAAF-NT-76-14 ] N77-10017 [ AD-A024071 ] ' 1177-11038 LAUGHBIDGE, F. I. Fatigue investigation of the E-2B/C nose landing Aircraft ground fire suppression and rescue gear systems. Characteristics of kinematic ]et ±uel [AD-A024072] N77-11040 fires cascading and rod fuel geometries [ 4D-A024447] N77-11022 LEAKE, B. J. M Computational alternatives to obtain tine optimal MAGLIOZZI, B. ]et engine control V/STOL rotary propulsion systems: Noise [ilASA-CB-149106] H77-100oO prediction and reduction. Volume 1: Simplified simulation models for control studies Identification ot sources, noise generating of turbojet engines mechanisms, noise reduction mechanisms, and [NASA-CB-149107] N77-10061 prediction oethodology 1EAVY. G. C. [AD-A027389/6] N77-10053 Weight and balance considerations in the design of V/STOL rotary propulsion systems: Noise the A-10A close air support aircraft preaiction and reduction. Volume 2: Graphical [SAKE PAPEB 1101] A77-12183 prediction netflods LEBALLEUE, J. C. [ AD-A027390/4] N77-1005U Viscous interaction with separation in transonic V/STOL rotary propulsion systems: Noise flow prediction and reduction. Volume 3: Computer [NASA-TT-F-17187 ] N77-10997 program users oanual LEBODC, P. OD-A027363/1 ] N77-10055 Concorde - Endurance flights results HANGLBB, K. H* A77-12114 Computational met nods and prooletas in aeronautical fluid dynanics A77-12551

~~B-7 BABESCA, C. PEESOSiL 10THOB IBDEX~~

Free vortei sheets BILES, J. B. A77-12559 Effects of forward velocity on noise for a J85 HAEESC4, C. turbojet engine with multitube suppressor from Experimental study of the aerodynamics of a wind tunnel and flight tests helicopter rotor in translational flight. Two [NASA-TB-X-73542] N77-11051 dimensional simulation of the effects due to BILLAR, D. A. J. cyclic variations of the velocity vector The rotating stator concept. Experimental [AAAF-NT-76-20] N77-10019 performance characteristics compared with the HARGASOH, B. J. conventional compressor Effects of ]ets, wakes, and vortices on lifting [AD-A02UU65] H77-11411 surfaces BILLER, Bl B. [N&SA-TH-X-7397U] N77-10998 Full temperature range protective system for BABSH, O. P. fastener areas of carrier-based naval aircraft The next-generation subsonic transport [AD-A024523] H77-10210 [SAKE PAPER 1127] A77-12195 BILLEB, S. C. BABSH, H. Future trends in aero gas turbine design. II - Subsonic flows in turbomachines Unconventional engines A77-12556 A77-11595 HAIO, a. B. BIRSKII, V. B. Landing practices of general aviation pilots in Flow of a radiating gas over a blunt body with single-engine light airplanes intense vaporization [NASA-TN-D-8283] N77-11033 A77-10t16 HCCABTHI, J. F., JB. BITB4, B, Analog computation assessment of the risk of Approximate transonic profile flow with shock structural failure due to crack growth under 477-10251 random loading HITTELBACH, F. G. [AD-A025266] N77-11012 The helicopter air service passenger program: A BCCOBBICK, B. B. retrospect On the status of V/S1OL flight [PB-25t830/3] N77-10036 N77-10367 BOFFITT, T. P. BCDOHALD, B. Two-dimensional cold-air cascade study of a The inviscid pressure field on the tip of a film-cooled turbine stator blade. 3: Effect of semi-infinite wing and its application to the hole size on single-row and multirow ejection formation of a tip vortex [NASA-TH-X-31U2] H77-11007 [NASA-CB-27U8] N77-11315 HOOK, D. T. BCDONHELL, J. H. Application of the nonlinear vortex-lattice Computational methods and problems in aeronautical concept to aircraft-interference problems fluid dynamics B77-103t9 A77-12551 BOOBE, fi, 0. BCGEHEE, B. L. Performance of 1.15-pressure-ratio fan stage at A test facility for aircraft ]et noise reduction. II several rotor Dlade setting angles with reverse A77-118H4 flow BCKEE, B. G. [NASA-TH-X-3151] N77-11008 Aircraft ground fire suppression and rescue BOOZ, I. E. systems. Characteristics of kinematic jet fuel A second look at relationships for estimating fires cascading and rod fuel geometries peacetime aircraft attrition [AD-A024447] N77-11022 [4D-A023681] N77-11023 BBITZLEB, T. D. BORGAH, L. A. ICC analysis of flight recorder for F-"4 Wild Finite element and difference methods for cascades weasel aircraft 477-12557 [AD-A023830] N77-10512 BOBINO, L. BENDEL, J. H. Performance analysis of flexible aircraft with On the identification of state-derivative-coupled active control systems N77-10378 A77-12UU8 BOBBIS, S. J. BBNDEHHAL1, H. B. Assessment of vanaule-cycle engines for Bach 2.7 Calculation of the longitudinal aerodynamic supersonic transports characteristics of wing-flap configurations with [NASA-TS-X-73977 ] N77-10065 externally blown flaps BOSTON, J. B. [NASA-CR-2705] S77-11006 Experimental investigation of the boundary layer BEHG, P. B. on a rotating cylinder Emissions of an AVCO Lycoming 0-320-DIAD air A77-10208 cooled light aircraft engine as a function of BOSIH, A. V. fuel-air ratio, timing, and air temperature and Experimental study of combustion time in two-stage humidity combustion process [NASA-TM-X-73500] N77-10058 A77-12511 Effect of air temperature and relative humidity at BOSIN, I. I. various fuel-air ratios on exhaust emissions on Heat-pipe regenerator for gas turbine engine a per-mode basis of an Avco Lycoming 0-320 DIAD 477-12528 light aircraft engine. Volume 2: Individual BOKUEBJEE, D. K. data points Pressure loss coefficient of impingement cooled [NASA-TH-X-73507 ] N77-10066 leading edge system of a turbine blade BBRBILL. G. L. A77-10772 §tudy ot small turbofan engines applicable to Film cooling with injection through slots single-engine light airplanes 477-10773 [NASA-CR-1379t«] N77-11054 HIDDLETOH, H. D. A computational system for aerodynamic design and N analysis of supersonic aircraft. Part 2: NAKAYAHA, A. User's manual Flow interaction near the tail of a body of [NASA-CR-2716] N77-11005 revolution. I - Flow exterior to boundary layer BIKDLOVICH, V. I. and wake Signal-treatment methods during aircraft-engine [ASME PAPER 76-FE-M] A77-10855 inspection based on vibroacoustic noises Flow interaction near the tail of a nody of 477-11603 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. OBL4HDEB, B. D. Applications of linearised supersonic wing theory The development of a computer aided airfoil design to the calculation of some aircraft interference procedure including preliminary wind tunnel flows experiments on a low Reynolds number high lift A77-12566 section, volume 1 NABAIAHASHAHI, B. [AD-A02M361 ] N77-10028 Resizing procedure for structures under combined OBBINGEB, 0. mechanical and thermal loading Analog computation assessment of the risk of A77-1021U structural failure due to crack growth under HABBAHOBE, J. C. random loading The development of a computer aided airfoil design [AD-A025266] 877-11012 procedure including preliminary wind tunnel OTTENS, H. B. experiments on a Ion Reynolds number high lift Calculation of vibration modes and resonance section, volume 1 frequencies of the Northrop BF-5 [AD-A024361 ] N77-10028 [NLR-TB-75050-U ] N77-11«50 NAYFEH, A. B. Application of the nonlinear vortex-lattice concept to aircraft-interference problems N77-10349 PAHTELBEV, A. A. BELSOH, B. B. Analytic and experimental study of turbine rotor Application of optimality criteria to automated blade temperature structural design A77-12522 A77-10207 PARKER, J. A. NEHCBENKO, L. I. Conference on the Development of Fire-Besistant Strength of compressor wheels of low-ductility Aircraft Passenger Seats alloys [NASA-TH-X-7311"] N77-11111 A77-10383 PABKBR. B. J. HESTEB07, E. D. Bearing restoration oy grinding Determination of magnitudes of the parameters [NASA-CH-1149188] H77-11101 characterizing ducted airscoop operation PATBL, V. C. downstream Flow interaction near the tail of a body of A77-12521 revolution. I - Flow exterior to boundary layer NEUBEBTB, G. and wake Noise generating by interaction between subsonic [ASME PAPEB 76-FE-M] A77-10855 •jets and blown flaps Flow interaction near the tail of a body of [DLR-FB-76-20] N77-10067 revolution. II - Iterative solution for flow NGUYEN, L. 1. within and exterior to boundary layer and wake Results of recent NASA studies on automatic spin [ASME PAPER 76-FE-N] A77-10856 prevention for fighter aircraft PATTERSON, J. C.. JB. N77-10381 Hingtip vortex dissipator for aircraft NIELSEN, G. I. T. [NASA-CASE-LAH-11645-1 ] N77-10001 An improved projectile boattail, part 2 PATTON, J. H., JB. [AD-A021073] N77-11016 A flignt investigation of piloting technigues and NIELSEN, J. H. crosswind limitations during visual STOL-type Calculation of the longitudinal aerodynamic landing operations characteristics of wing-flap configurations with [NASA-TN-D-828U] N77-11001 externally blown flaps PEAKS, D. J. [NASA-CR-2705] N77-11006 Controlled and uncontrolled flow separation in NIXON, D. three dimensions An extended integral equation method for the [LR-591] N77-10999 steady transonic flow past a two-dimensional PELAGATTI, C. aerofoil Critical analysis of comparisons between flight A77-12562 test results and wind tunnel test predictions in NOLL, B. B. subsonic and supersonic transport aircraft Performance analysis of flexible aircraft with [NASA-TT-F-17185] N77-10049 active control PENBEI, T. B. N77-10378 The AFFDL-Nielsen flow-field study NOBDHACK, G. B. [AD-A023755] N77-11015 Design mechanical properties, fracture toughness, PEBEZ GBIFFO, A. fatigue properties, exfoliation and Investigation and analysis of the human factors in stress-corrosion resistance of 7050 sheet, aircraft accidents plate, hand forgings, die forgings and extrusions A77-10500 [AD-A02M609] N77-10195 PEBKIHS, J. N. NOVAK, B. C. Transients in turbocompressors Investigation of a bearingless helicopter rotor [AD-A024275] N77-11112 concept having a composite primary structure PEBBIEB, P. [NASA-CR-2637] N77-10011 Buffeting problems NTS, B. B. [AAAF-NT-76-7] H77-10050 Responsibilities and assurances with regard to PETEBSON, H. B. cargo transport - Air transport law Development of aircraft brake materials 477-12172 [ASLE PBEPBINT 76-LC-1B-3] A77-11195 PBfBAZBITSKII, G_ B. Thermal analysis of flight vehicle compartment structure OBBIAN, I. C. A77-12509 Landing practices of general aviation pilots in PBTOKB07. 4. B. single-engine light airplanes Dispersion of fatigue test data for cast [NASA-TN-D-8283] 1177-11033 gas-turbine blades in association with OCABROLL, H. J. structural and technological factors Finite element and difference methods for cascades A77-12579 477-12557 PIEBS, H. J. OBASBI. B. Calculation of the flow around a swept wing, Forces on unstaggered airfoil cascades in unsteady taking into account the effect of the in-phase motion three-dimensional boundary layer. Part 1: King [ASHE PAPEB 76-FE-S] 477-10851 with turbulent boundary layer [NLB-TB-75076-0] N77-11011

~~B-9 PILOH, J. C. PEESONAL AOTHOB INDEX~~

PI10N, J. C. EBDDT, N. N. Critical analysis of comparisons between flight V/STOL aircraft noise prediction (jet propulsors) test results and wind tunnel test predictions in [AD-A028765/6] 877-1101)5 subsonic and supersonic transport aircraft BBSHOTKO, H. f NASA-TT-F-17185 ] B77-100"49 Core noise source diagnostics on a turbofan engine PISABENKO, G. S. using correlation and coherence techniques Strength of glass-fibre-reinforced plastics at [NASA-Td-X-73535] 877-11053 one-sided beating BBOTEH, B. P. [IAF PAPER 76-200] A77-10939 Eigenvalue/eigenvector control via spectral PLATOU. A. S. cnaracterization - An application to helicopter An improved projectile boattall, part 2 hover dynamics [AD-A021)073] N77-11015 A77-10338 PLATZEH, H. F. BICE, E. J. Prediction Methods for Jet V/S10L Propulsion Inlet noise suppressor design method based upon Aerodynamics, volume 1 tne distribution of acoustic power with mode [AD-4024022] N77-10068 cutoff ratio Prediction Methods for Jet V/STOL Propulsion N77-10311 Aerodynamics, volume 2 BICUABDS, C. [AD-A02U023] N77-10069 Computational methods and proolems in aeronautical POOL, A. fluid dynamics The establishment of safe separations between A77-12551 aircraft in rlight BILOFF, N., JB. [BLfl-aP-75041-U] , N77-11020 Experimental clean combustor program: Noise study POEIEB, J. H. [NASA-CB-13510b] N77-1C064 The AFFDL-Nielsen flow-field study BOBESTS, A. [AD-A023755] 877-11015 Relaxation near a sonic line POTTER, J. H. A77-12563 Current practice on estimating cracK growth damage BOSENFIELD, S. B. accumulation with specific application to Beyond supersonic transport structural safety duraoility and reliability [IAF PAPEB ISL-76-66] A77-10972 [ AD-A025499] 877-11178 BOSSES, B. H. PEASAD, 0. H. Conference on the Development of Fire-Besistant Optimal control for the rolling pullout maneuver Aircraft Passenger Seats of a modern fighter aircraft [NASA-TM-X-7314U] N77-11111 A77-12it44 BDDEY, B. A. The pursuit-evasion problem of two aircraft in a Advanced combustion techniques for controlling NO horizontal plane sub x emissions of high altitude cruise aircraft A77-12152 [8ASA-TM-X-73473] N77-10062 PEOKHOKOV, A. H. The impact of emissions standards on the design of Laser air-jet engine aircraft gas turbine engine combustors A77-11887 [NASA-TM-X-73U90] 877-10063 PHUST, H. W. , JR. BDSSELL, J. H. Two-dimensional cold-air cascade study of a Assessment of variable-cycle engines for Mach 2.7 film-cooled turbine stator blade. 3: Effect of supersonic transports hole size on single-row and multirow ejection [BASA-TM-X-73977] 877-10065 [NASA-TH-X-3442] N77-11007 PUBSHOUSE, H. Applications of linearised supersonic wing theory to the calculation of some aircraft interference SANDELL, H. B., JB. flows The stochastic control of the F-8C aircraft using A77-12566 the multiple model adaptive control /MMAC/ method PILAEV, A. H. A77-12428 Thermal analysis of flight vehicle compartment Linear regulator design for stochastic systems by structure a multiple time scales method A77-12509 [NASA-CR-119099] 877-10432 SAHTBAH, D. H. Transonic performance of Mach 2.65 auxiliary flow Q axisymmetric inlet QUABA8TA, J. E. [8ASA-CB-27U7] 877-10056 Terminal area guidance along curved paths: A SABGENT, N. B. stochastic control approach Effects of forward velocity on noise for a J85 N77-10383 turbojet engine with multitube suppressor from QUICK, A. V. wind tunnel and flight tests Noise generating by interaction between subsonic [BASA-TM-X-735U2] 877-11051 jets and blown flaps SABHA, I. G. [DLE-FB-76-20] N77-10067 Optimal control for the rolling pullout maneuver of a modern figater aircraft A77-1244II SATYABABAYABA, G. BAJAB, B. Optimal control for the rolling pullout maneuver The pursuit-evasion problem of two aircraft in a of a modern fighter aircraft horizontal plane A77-124U4 A77-12152 SAONDEBS, S. BAKOISKI, I. J. Experimental investigation of the boundary layer Dynamic-stress-data management for aeromechanical on a rotating cylinder testing of turbomachinery A77-10208 A77-12175 SCBIPHOLT, G. J. BEBOBT, J. Calculation of the flow around a swept wing, Experimental study of the aerodynamics of a taking into account the effect of the helicopter rotor in translational flight. Two three-dimensional boundary layer. Part 1: Ming dimensional simulation of the effects due to with turbulent boundary layer cyclic variations of the velocity vector [NLH-TB-75076-0] 877-11011 [ AAAF-NI-76-20] N77-10019 SCBLIBKELHAHN, B. J. BECK, G. B. Research on adhesive bonding and surface Advanced combustion techniques for controlling NO characteristics of metals at Fokker-VFW sub x emissions of high altitude cruise aircraft [FOK-B-1816] 877-11105 [NASA-TH-X-73473] N77-10062

~~B-10 PBBSOBAL AOTHOB IBDEI STUIOV. ?. P.~~

SCHHIDT, A. B. SIBAf, B. S. _• A method for estimating the veigbt of aircraft An analysis of the intrastate air carrier transmissions regulatory forua. Volume 2: Technical report [SAWE PAPEB 1120] A77-12191 [AD-A023762] H77-10035 SCBBADEB, O. E. SIBOHS, I. i. Application of advanced technology to future Advanced control systems for helicopters long-range aircraft A77-11278 [SA»E PAPEB 1126] A77-1219U SIVAEV, V. B. SCBOETZ, 0. Study of flow swirl influence on axiradial Application of design data derived from fatigue diffuser effectiveness tests with service-like load seguences for life A77-12520 prediction SKIHHBB, 6. L. [LBF-FB-109/76] H77-111115 Army preliminary evaluation TOB-58A helicopter Compilation of measures to increase the fatigue with a flat-plate canopy strength of aircraft structures [AD-A021501] B77-11039 [LBF-TB-126/75] N77-11117 SKOBOBATCKII, B. SCBUBfZB, B. Emissions of an AVCO Lycoming 0-320-DIAD air Theoretical and experimental investigations on cooled light aircraft engine as a function of landing gear spring blades out of fiber fuel-air ratio, timing, and air temperature and reinforced plastic for small aircraft humidity [ESA-TT-312] H77-10162 CHASA-TH-X-73500] K77-10058 SCBfAHTZ, P. Effect of air temperature and relative humidity at Advanced design composite aircraft, the next step various fuel-air ratios on exhaust emissions on for composites a pec-mode basis of an Avco Lycoming 0-320 DIAD [SAWE PAPES 1105] A77-1218U light aircraft engine. Volume 2: Individual SCBIEIKHABD, B. G. data points Effects of atmospheric conditions on the operating [NASA-TH-X-73507] H77-10066 characteristics of supersonic cruise aircraft SHITH, K. O. [IAF PAPEB 76-112] A77-10912 Conceptual designs for a modular remotely piloted SCOTT, G. R. vehicle Civil uses of remotely piloted aircraft [AD-A02384II] M77-11035 [BASA-CB-1378911] B77-100U7 SOFBIH, T. G. Civil uses of remotely piloted aircraft Experimental clean combustor program: Noise study [NASA-CB-137895] 1)77-1001(8 [NASA-CB-135106] B77-10064 SCBOGGS, B. B. SOVBAHO, B. Vortex/jet/wing viscous interaction theory and Experimental investigation of the near-surge flow analysis in a high performance centrifugal compressor [AD-A025290] 1(77-11017 A77-10036 SEELIGEB, G. G. SPABGLEB, J. G. Full temperature range protective system for Test verification of a transonic airfoil design fastener areas of carrier-based naval aircraft employing active diffusion control [AD-A024523] N77-10210 [AD-A024297] B77-10029 SEGALL. I. SPABGLEB, S. B. The stochastic control of the F-8C aircraft using Calculation of the longitudinal aerodynamic the multiple model adaptive control /BMAC/ method characteristics of wing-flap configurations with A77-12428 externally blown flaps SBHGEISSEH, C. [NASA-CB-2705] B77-11006 Military rocket aircraft: Inherent constraints SBIBATHKOHAB, S. and their uses Eigenvalue/eigenvector control via spectral N77-11186 characterization - An application to helicopter SHAIKBOTDIBOV, Z. G. hover dynamics Penetration and mixing of liquid injected into A77-10338 supersonic transverse gas stream S1BABHAB, B. O. A77-12515 The development of a computer aided airfoil design SH&MBOTH, S. J. procedure including preliminary wind tunnel The inviscid pressure field on the tip of a experiments on a low Reynolds number high lift semi-infmite wing and its application to the section, volume 1 formation of a tip vortex [AD-A024361] N77-10028 [NASA-CF-2748] H77-11315 The design, analysis and testing of a low budget SBATAYEV. V. G. wind tunnel flutter model with active Calculation of multi-contour thin-nailed aerodynamic controls, volume 2 structures by the method of sections IAD-A024480] N77-10090 [NASA-T1-F-17281] N77-11029 SIBABBS, C. A. SBCHOKIH, V. A. Hot corrosion studies of four nickel-base Experimental study of combustion time in two-stage superalloys: B-1900, BASA-TBil VIA, 713C and IB738 combustion process CNASA-TM-X-73479] N77-10183 A77-12511 STEHiHEIL, E. SaCHOKIB, V. K. Mechanism of material fatigue during the crack Heat transfer in tube entrance segment with initiation stage initial flow swirl and transverse injection [ICAF-DOC-895] B77-11441 A77-12517 STOBE, J. B. Heat-pipe regenerator for gas turbine engine Effects of forward velocity on noise for a J85 A77-12528 turbojet engine with multitube suppressor from SHELIKHOV, S. G. wind tunnel and flight tests Magnetic particle inspection of aviation engine [NASA-TM-X-73542] B77-11051 vanes STBEHLOB. a. A77-11606 Hingeless rotor dynamics in nign speed flight SULIK, L. B. A77-11280 Strength of compressor wheels of low-ductility STBIKB, I. T. alloys The AFFDL-Bielsen flow-field study A77-10383 [AD-A023755] B77-1101S SHBIDEB, K. B. S1BOGOBOV, 0. V. Development of predictive wake vortex transport Experimental study of combustion time in two-stage model for terminal area wake vortex avoidance combustion process [AD-A029049/4] N77-11002 A77-12511 SBOHPBBT, P. STOLOV, V. P. An analytical study for subsonic obligue wing Flow of a radiating gas over a blunt body with transport concept intense vaporization [NASA-CP-137896] N77-100U5 A77-10U16

~~B-11 STOBGEOH, B. t. PBBSOHAL tDTBOB IHDBX~~

STOBGEOH, B. F. TBAYBAB, J, J. Design considerations for laminar flow control An experimental study of the nonlinear stiffness aircraft of a rotor blade undergoing flap, lag and twist N77-10366 deformations SDLLIVAH, T. E. [NASA-CB-137968] H77-10008 Measurement of wake vortex strength by means of An experimental study of the nonlinear stiffness acoustic back scattering of a rotor blade undergoing flap, lag and twist A77-11712 deformations SUNSHINE. B. A. [NASA-CH-137969] S77-10009 An analysis of the intrastate air carrier TBBTIACHENKO, G. B. regulatory forum. Volume 2: Technical report * Strength of glass-fibre-reinforced plastics at [AD-A023762] N77-10035 one-sided heating SflDEBSKI, A. A. [IAF PAPEB 76-200] A77-10939 The rotating stator concept. Experimental TBDHEVA, E. A. performance characteristics compared with the Hechanism of stabilization of the 'separation conventional compressor point1 of a vortex during flow of a stream at [AD-A024465] N77-11411 low subsonic velocity over a delta wing SHIFT, G. [SASA-TT-F-17283] H77-10012 An analytical study for subsonic obligue wing TBDSHIN, T. A. transport concept Analytic and experimental study of turbine rotor [NASA-CB-137896] N77-10045 blade temperature SHITZEB, 0. A77-12522 The production and refining of crude oil into military fuels [AD-A024652] N77-11207 VANOENBEBG, B. Calculation of the flow around a swept wing, taking into account the effect of the TAI, T. C. three-dimensional boundary layer. Part 1: Sing Analysis and design of ejector diffuser for with turbulent boundary layer optimum thrust [NLB-TB-75076-U] N77-11011 [AD-A025491 ] N77-11356 VANDYKE, P. TALANIOV, A. V. High speed computer studies of vortex motions in Experimental study of combustion time in two-stage relation to aircraft wake turbulence combustion process [AD-A024290] N77-11013 A77-12511 VANPAPPEIEBDAB, C. A. TALBOT, J. E. Development of a graphite horizontal stabilizer Effects of atmospheric conditions on the operating [AD-A023767] N77-11036 characteristics of supersonic cruise aircraft VEB, I. L. [IAF PAPEE 76-112] A77-10912 Acoustical evaluation of the NASA Langley V/STOL TENEKETZIS, D. wind tunnel Linear regulator design for stochastic systems by [NASA-CB-145087] N77-11068 a multiple time scales method VETIUTSKAIA, L. B. [NASA-CB-1U9099] N77-10432 Off-design regimes of asymmetric nozzles with TENSI, J. supersonic inlet velocity Buffeting problems A77-12504 [AAAF-NT-76-7] N77-10050 VOLODENKO, B. V. THOHPSOH, J. F. Dispersion of fatigue test data for cast Numerical solutions for laminar and turbulent gas-turbine blades in association with viscous flow over single and multi-element structural and technological factors airfoils using body-fitted coordinate systems A77-12579 N77-10355 VOEOSHKO, P. P. THBESHEB, B. B. Calculation of gas-turbine engine blades by the Design consideration for the Darrieus rotor finite element method A77-12872 A77-12583 TIBBETS, J. G. V/STOL aircraft noise prediction (jet propulsors) [AD-A028765/6] N77-11045 w TINSLEY, H. G. iALKDEM, F. A systems approach to all weather landings Computational methods and problems in aeronautical A77-10438 fluid dynamics TITABENKO, V. V. A77-12551 Nonlinear analysis of flows generated by the Supersonic flows impulsive motion of a wedge A77-12565 A77-12630 IALSB, J. D. TODA, B. Design mechanical properties, fracture toughness, Simulation of an automatically-controlled STOL fatigue properties, exfoliation and aircraft in a microwave landing system multipath stress-corrosion resistance of 7050 sheet, environment plate, hand forgings, die forgings and extrusions [NASA-TM-X-73154] N77-11063 [AD-A024609] N77-10195 TOENSHOFF, D. A. BABE, T. C. High temperature thermocouple system for advanced Small axial compressor technology, volume 1 aircraft turbine engines [NASA-CB-134827-VOL-1] N77-11048 [AD-A025500] N77-11062 Small axial compressor technology, volume 2 TOBLIN. K. B. [NASA-CB-134827-VOL-2] N77-11049 An analytical study for suosonic obligue wing IABNOCK, 1. transport concept An analytical study for subsonic obligue wing [NASA-CE-137896] N77-10045 transport concept TOBBES, B. [NASA-CB-137896] N77-10045 A wing on the SA.341 Gazelle helicopter and its IABSI, Z. D. A. effects Numerical solutions for laminar and turbulent A77-11282 viscous flow over single and multi-element TBABB, P. C. airfoils using body-fitted coordinate systems Centrifugal compressor and pump staoility, stall N77-10355 and surge; Proceedings of the Conference, New BE1LIVEB. A. D. Orleans, La., March 22-25, 1976 Supersonic variable-cycle engines A77-10026 [BASA-TH-X-73524] N77-10059

~~B-12 PEBSOHAL ADIBOB IHDEI ZISK, B. D.~~

WHITCOHB, B. T. ZBLDOVICB, B. L. Advanced transonic aerodynamic technology Determination of aagnitudes of the parameters H77-10365 characterizing ducted airscoop operation SILK, 1. S. downstream BeasQreoent of wake vortex strength by means of A77-12S21 acoustic back scattering ZODOV, V. H. A77-11712 Off-design regimes of asymmetric nozzles with 1ILLIABS, B. B. supersonic inlet velocity Application of circulation control rotor A77-1250D technology to a stopped rotor aircraft design ZTSK, E. 0. A77-11277 High temperature thermocouple system for advanced UILLIS, 0. L. aircraft turbine engines System considerations for reliable strain data [AD-4025500] N77-11062 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

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 BAS2-9177 S77-11064 HAS3-17846 N77-11048 HAS2-9177 H77-11064 N77-11049 NAS3-18024 N77-11046 N77-110K7 CONTRACT KAS3-18544 N77-10064 NUMBER BAS7-100 N77-11198 NAS9-13^47 N77-10010 NCA-OY536-501 Listings in this index are arranged alphanumencally by contract number A77-10336 Under each contract number the accession numbers denoting documents NG1-22-009-124 A77-12428 that have been produced as a result of research done under that contract N77-10432 are arranged in ascending order with the IAA accession numbers appearing N6E-25-001-005 first The accession number denotes the number by which the citation is N77-10355 identified m either the lAAoi STARsecvon NGE-33-016-167 N77-10351 KGE-33-016-201 N77-10351 AF PHOJ. 1367 DOT-FA74WA-3477 NGE-33-018-152 N77-11478 N77-10053 A77-11195 &P PSOJ. 1476 N77-10051 NIVB-1737 K77-11011 N77-10027 H77-10055 KB PBOJ. 078-038 AF PHOJ. 1929 DOT-OS-60078 H77-10035 H77-11059 N77-11042 DOT-OST-60078 NR PBOJ. 215-233 AF PEOJ. 1989 N77-1003U 077-11017 N77-11035 DOT-TSC-988 N77-11002 NSF C-76-12038 AF PBOJ. 3066 E (01-3)-1207 A77-12680 A77-12927 N77-11062 E (01-3)-1228 A77-12680 NSF GK-41482 A77-12448 AF PBOJ. 6813 E(01-3)-12S5 A77-12680 NSG-268 N77-11365 N77-11061 E(19-18)-2087 NSG-1018 A77-12428 AF PBOJ. 7181 N77-10432 NSG-1174 N77-10354 N77-11043 FEA-C-04-50088-00 NSG-1199 N77-10383 AF PBOJ. 8219 N77-10690 NSG-3048 N77-10060 N77-11015 F30602-73-C-0065 N77-10061 AF PBOJ. 9781 A77-10442 N00014-68-A-0196-0002 N77-11013 F33b15-73-C-3056 A77-10855 N77-11061 S77-10027 477-10856 H77-11412 F33615-74-C-2069 N00014-74-C-0151 iF PROJ. 9782 N77-11062 N77-11017 N77-10028 F33615-74-C-3046 N00014-75-C-0055 1177-10090 N77-11042 N77-11207 AF-AFOSB-72-2273 F33615-75-C-3036 N00011-75-C-1143 A77-12428 N77-11035 N77-11059 AF-AFOSB-74-2460A P33615-75-C-3124 N00019-72-C-0512 A77-10207 A77-12184 N77-10195 AP-AFOSB-1998-71 F44620-71-C-0080 H00019-74-C-0267 N77-10028 N77-11013 N77-10210 H77-10090 P44620-73-C-0011 N00156-70-C-1321 AF-AFOSH-2167-72 N77-11023 N77-11036 N77-11061 F44620-75-C-0040 N62269-74-C-0517 AP-AFOSB-2802-75 A77-10218 N77-10029 N77-11412 NASB-2790 N77-10049 N62269-75-C-0311 AF-AFOSK-2922-76 NASH-2792 N77-10012 N77-11065 1177-10355 N77-10997 PBOJ. SQUID N77-11059 ABO PBOJ. P32A-33A [177-11019 SBC-B/EG/85125 1177-11037 N77-11029 A77-10347 ABO PBOJ. P41T-78A NAS1-9559 N77-11068 MF41422206 N77-11036 (177-11037 N4S1-10960 N77-10044 50U-09-33 N77-11044 ABO PBOJ. V41A-B4A N77-10556 505-04 1177-11007 H77-11015 NAS1-11100 H77-11032 1177-11008 AT(04-3) -1075 NAS1-12794 N77-11345 505-05 1177-11057 A77-12872 NAS1-13158 N77-11006 505-08-30-01 N77-11001 Al(11-1)-3077 NAS1-13371 N77-10378 505-10-11-01 1177-11033 N77-10351 NAS1-13653 H77-11030 505-10-21-01 N77-11345 DA PEOJ. 1F1-61102-AH-45 HAS1-13694 N77-10366 505-11-24-02 H77-10998 H77-10044 SAS1-13732 N77-11005 510-56-01 1177-11111 K77-10556 NAS1-13870 N77-10013 513-53-02 H77-11063 DA PBOJ. 1F1-63204-DB-38 NAS1-14137 H77-10032 743-04-01-01 N77-11031 N77-11041 NAS1-14159 N77-10033 DA PEOJ. 111-61102-A-33D NAS2-7613 N77-10003 N77-11016 H77-10004 DA PBOJ. 1T1-61102-A-33H H77-10005 H77-11018 N77-10006 DAAD05-72-C-0131 NAS2-7615 N77-10007 A77-10208 H77-10008 DAAG29-76-G-0045 H77-10009 N77-103D7 NAS2-8582 N77-11054 DAAJ02-73-C-0097 H&S2-8651 S77-10014 H77-11041 HAS2-8663 M77-11107 DOT-FA72BA-2837 NAS2-8679 N77-10056 H77-11024 NAS2-8686 H77-10015 DOT-FA72HA-3099 N77-10046 H77-11045 HAS2-8935 N77-10047 H77-10048

C-1 NASA-Lanqley, 1977 1 Report No 2 Government Accession No 3 Recipient's Catalog No NASA SP-7'">37 (30) 4 Title and Subtitle 5 Report Date AERONAUTICAL ENGINEERING February 1977 A Special Bibliography (Supplement 80) 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 11 Contract or Grant No Washington, De C. 205^6~~

~~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 introduced into the NASA scientific and technical information system in January 1977.~~

~~17 Key Words (Suggested by Author(s)) 18 Distribution Statement Aerodynamics Aeronautical Engineering Aeronaut!cs Unclassified - Unlimited 3 ibliograph ies~~

~~19 Security Qassif (of this report) 20 Security Classif (of this page) 21 No of Pages 22 Price" Unclassified Unclass tfied $4.75 HC~~

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~~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~~

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