NASA SP-7037 (90)

AERONAUTICALENGINEERING

r--- v'^sr" V

A SPECIAL BIBLIOGRAPHY

WITH INDEXES

Supplement 90

DECEMBER 1977

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION

https://ntrs.nasa.gov/search.jsp?R=19780009043 2020-03-30T03:06:03+00:00Z

ACCESSION NUMBER RANGES

Accession numbers cited in this Supplement fall within thefollowing ranges:

STAR(N-10000 Series) N77-30065—N77-34092

IAA (A-10000 Series) A77-443 14-A77-51633

This bibliography was prepared by the NASA Scientific and Technical Information Facilityoperated for the National Aeronautics and Space Administration by Informatics InformationSystems Company.

NASA SP-7037 (90)

AERONAUTICAL ENGINEERING

A Special Bibliography

Supplement 90

A selection of annotated references to unclas-sified reports and journal articles that wereintroduced into the NASA scientific and tech-nical information system and announced inNovember 1977 in

• Scientific and Technical AerospaceReports (STAR)

• International Aerospace Abstracts (IAA)

Scientific and Technical Information Office DECEMBER 1977NATIONAL 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 Administrationthis publication has been prepared by the National Aeronautics and Space Administrationfor the joint use of both agencies and the scientific and technical community concerned withthe field of aeronautical engineering. The first issue of this bibliography was published inSeptember 1970 and the first supplement in January 1971. Since that t ime, month lysupplements have been issued

This supplement to Aeronautical Engineering -- A Special Bibliography (NASA SP-7037)lists 351 reports, journal articles, and other documents originally announced in November1977 in Scientific and Technical Aerospace Reports (STAR) or in International AerospaceAbstracts (IA A)

The coverage includes documents on the engineering and theoretical aspects of design,construction, evaluation, testing, operation, and performance of aircraft (including aircraftengines) and associated components, equipment, and systems. It also includes research anddevelopment in aerodynamics, aeronautics, and ground support equipment for aeronauticalvehicles.

Each entry in the bibliography consists of a standard bibliographic citation accompaniedin most cases by an abstract The listing of the entries is arranged in two major sections, IAAEntries and STAR Entries, in that order. The citations, and abstracts when available, arereproduced exactly as they appeared originally in IAA and STAR, including the originalaccession numbers from the respective announcement journals. This procedure, which savestime and money, accounts for the slight variation in citation appearances

Three indexes — subject, personal author, and contract number — are includedAn 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 areavailable at $5 00 per document up to a maximum of 20 pages The charge for each additionalpage is 25 cents Microfiche"1 are available at the rate of $1 50 per microfiche for documentsidentified by the # symbol following the accession number A number of publications, because oftheir special characteristics, are available only for reference in the AIAA Technical InformationService Library Minimum airmail postage to foreign countries is $1 00 Please refer to the accessionnumber, 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 isordinarily given on the last line of the citation The most commonly indicated sources and theiracronyms or abbreviations are listed below If the publication is available from a source other thanthose listed, the publisher and his address will be displayed on the availability line or in combinationwith 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 inthe STAR citation Price codes are given in the tables on page vn of the current issueof STAR

Microfiche111 is available regardless of age for those accessions followed by a § symbol

Initially distributed microfiche under the NTIS SRIM (Selected Research in Microfiche) isavailable at greatly reduced unit prices For this service and for information concerningsubscription to NASA printed reports, consult the NTIS Subscription Unit

NOTE ON ORDERING DOCUMENTS When ordering NASA publications (those followedby the * symbol), use the N accession number NASA patenS applications (only thespecifications are offered) should be ordered by the US-Patent-Appl-SN numberNon-NASA publications (no asterisk) should be ordered by the AD. PB. or other reportnumber shown on the last line of the citation, not by the N accession number It isalso advisable to cite the title and other bibliographic identification

Avail SOD (or GPO) Sold by the Superintendent of Documents. U S Government PrintingOffice, in hard copy The current price and order number are given following theavailability line (NTIS will fill microfiche requests, at the standard $300 price, forthose documents identified by a # symbol)

Avail NASA Public Document Rooms Documents so indicated may be examined at orpurchased from the National Aeronautics and Space Administration. Public DocumentsRoom (Room 126). 600 Independence Ave. SW. Washington. DC 20546. or publicdocument rooms located at each of the NASA research centers, the NASA SpaceTechnology Laboratories, and the NASA Pasadena Office at the Jet PropulsionLaboratory

U) A microfiche is a transparent sheet of film 105 by 148 mm in size containing as many as 60 to 98 pages ofinformation reduced to micro images (not to exceed 26 1 reduction)

Avail ERDA Depository Libraries Organizations in U S cities and abroad that maintaincollections of Energy Research and Development Administration reports, usually inmicrofiche form, are listed in Nuclear Science Abstracts Services available from theERDA and its depositories are described in a booklet. Science Information Availablefrom the Energy Research and Development Administration (TID-4550), which may beobtained without charge from the ERDA Technical Information Center

Avail Univ Microfilms Documents so indicated are dissertations selected from DissertationAbstracts and are sold by University Microfilms as xerographic copy (HC) and microfilmAll requests should cite the author and the Order Number as they appear in thecitation

Avail USGS Originals of many reports from the U S Geological Survey, which may containcolor illustrations, or otherwise may not have the quality of illustrations preserved in themicrofiche or facsimile reproduction, may be examined by the public at the libraries ofthe USGS field offices whose addresses are listed in this introduction The librariesmay be queried concerning the availability of specific documents and the possibleutilization of local copying services, such as color reproduction

Avail HMSO Publications of Her Majesty's Stationery Office are sold in the U S by PendragonHouse. Inc (PHI), Redwood City, California The U S price (including a service andmailing charge) is given, or a conversion table may be obtained from PHI

Avail BLL (formerly NLL) British Library Lending Division. Boston Spa. Wetherby, Yorkshire.England Photocopies available from this organization at the price shown (If none isgiven, 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 Issuing Activity, or Corporate Author, or no indication of availability Inquiries as to theavailability of these documents should be addressed to the organization shown in thecitation as the corporate author of the document

Avail U S Patent Office Sold by Commissioner of Patents. U S Patent Office, at the standardprice of 50 cents each, postage free

Other availabilities If the publication is available from a source other than the above, thepublisher and his address will be displayed entirely on the availability line or in combinationwith the corporate author line

GENERAL AVAILABILITY

All publications abstracted in this bibliography are available to the public through the sourcesas indicated in tbe^STAR Entries and IAA Entries sections It is suggested that the bibliographyuser contact his own library or other local libraries prior to ordering any publication inasmuch asmany of the documents have been widely distributed by the issuing agencies, especially NASAA 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 00foreign All questions relating to the subscriptions should be referred to NTIS. Ann Subscrip-tions. 5285 Port Royal Road. Springfield Virginia 22161

VI

ADDRESSES OF ORGANIZATIONS

American Institute of Aeronauticsand Astronautics

Technical Information Service750 Third AveNew York. NY 10017

British Library Lending Division.Boston Spa. Wetherby. Yorkshire.England

Commissioner of PatentsU S. Patent OfficeWashington. D C. 20231

Pendragon House. Inc899 Broadway AvenueRedwood City. California 94063

Superintendent of DocumentsU S Government Printing OfficeWashington. D C 20402

University MicrofilmsA Xerox Company300 North Zeeb RoadAnn Arbor. Michigan 48106

Energy Research and DevelopmentAdministration

Technical Information CenterPO Box 62Oak Ridge. Tennessee 37830

ESA-Space Documentation ServiceESRIN

Via Galileo Galilei00044 Frascati (Rome) Italy

Her Maiesty's Stationery OfficeP O Box 569. S E 1London. England

NASA Scientific and Technical InformationFacility

PO Box8757B W I Airport. Maryland 21240

National Aeronautics and SpaceAdministration

Scientific and Technical InformationOffice (NST-6)

Washington. D C 20546

National Technical Information Service5285 Port Royal RoadSpringfield, Virginia 22161

University Microfilms, LtdTylers GreenLondon, England

U S Geological Survey1033 General Services Administration

BuildingWashington. D C 20242

U S Geological Survey601 E Cedar AvenueFlagstaff. Arizona 86002

U S Geological Survey345 Middlefield RoadMenlo Park. California 94025

U S Geological SurveyBldg 25. Denver Federal CenterDenver. Colorado 80225

Zentralstelle fur Luftfahrtdoku-mentation und -Information

8 Munchen 86Postfach 880Federal Republic of Germany

VII

TABLE OF CONTENTSIAA Entries 499STAR Entries 523

Subject Index A-1Personal Author Index B-1Contract Number Index C-1

TYPICAL CITATION AND ABSTRACT FROM STAR

NASA SPONSOREDDOCUMENT

NASA ACCESSIONNUMBER

TITLE.

AUTHORS.

CONTRACTOR GRANT.

REPORTNUMBERS.

tf»»N77-10048*1 Lockheed Missiles and Space Co. Sunnyvale. ••-

Calif Research and Development Div

FCIVIL USES OF REMOTELY PILOTED AIRCRAFT SummeryReportJon R Aderhold. G Gordon, and George W Scott Jul 1976 •*•28 p ref

Avail NTIS-*-*. (Contract NAS2-8935)^.(NASA-CR-137895. LMSC-D057322)

HC A03/MF A01 CSCL QIC •«The economic, technical and environmental implications of

remotely piloted vehicles (RVP) are examined The time frameis 1980-85 Representative uses are selected, detailed functionaland performance requirements are denved for RPV systems, andconceptual system designs are devised Total system costcomparisons are made with non-RPV alternatives The potentialmarket demand for RPV systems is estimated Environmentaland safety requirements are examined, and legal and regulatoryconcerns are identified A potential demand for 2.000-11,000RVP systems is estimated Typical cost savings of 25 to 35%compared to non-RPV alternatives are determined There appearto be no environmental problems, and the safety issue appearsmanageable Author

.AVAILABLE ONMICROFICHE

—CORPORATESOURCE

.PUBLICATIONDATE

.AVAILABILITYSOURCE

. COSATICODE

TYPICAL CITATION AND ABSTRACT FROM IAA

NASA SPONSORED.

AIAA ACCESSION I""* A77-10214 • It Resizing procedure for structures under com-mimnrrt J,-̂ .hin«H mechanical and thermal loading. H M AdelmarTiNASA,NUMBER -

TITLE.

PUBLICATIONDATE,

Langley Research Center, Hampton, Va) and R Narayanaswami(Old Dominion University, Norfolk, Va.). AIAA Journal, vol 14,

.Oct 1976, p 1484-1486 6 refs e ~]The fully-stressed design (FSD) appears to be the most widely L-

used approach for sizing of flight structures under strength andminimum-gage constraints Almost all of the experience with FSDhas been with structures primarily under mechanical loading asopposed to thermal loading. In this method the structural sizes areiterated with the step size, depending on the ratio of the total stressto the allowable stress In this paper, the thermal fully-stressed design(TFSD) procedure developed for problems involving substantialthermal stress is extended to biaxial stress members using a VonMises failure criterion The TFSD resizing procedure for uniaxialstress is restated and the new procedure for biaxial stress members isdeveloped Results are presented for an application of the twoprocedures to size a simplified wing structure S D

• AVAILABLE ONMICROFICHE

-AUTHORS

—AUTHOR'SAFFILIATION

VIM

AERONAUTICALENGINEERING A Special Bibliography (Suppl. 90)

DECEMBER 1977

IAA ENTRIES

A77-44316 # Analysis/theory of controlled configuredstructures S D Gratke and J G Williams (Vought Corp, Dallas,Tex ) American Institute of Aeronautics and Astronautics, AircraftSystems and Technology Meeting, Seattle, Wash., Aug 22-24, 1977,Paper 77-1212 8p

Modern swept wing aircraft wing substructure has traditionallybeen configured with the shear carrying spars oriented along lines ofconstant chord percentage, i e, 30% chord, 50% chord, etc Thisarrangement may produce leading edge up wing twist during flexuralloading resulting in undesirable wing and aircraft performance Theleading edge up rotation increases the angle of attack of the outboardportion of the wing causing the tip to stall at a lower airplane angleof attack than the remainder of the wing This stalled tip at high glevels no longer produces lift and increases drag, therefore, reducingthe aircraft performance To alleviate this problem of stalled tips,built in leading edge down twist has been built into the wing This isvery costly from a manufacturing standpoint, and has a detrimentaleffect on the aircraft during negative g maneuvers by having a built inangle of attack increase (Author)

A77-44317 ff Analysis methods and computer programsdeveloped for the YC-15 STOL flight test program H K Cheney(Douglas Aircraft Co , Long Beach, Calif ) American Institute ofAeronautics and Astronautics, Aircraft Systems and TechnologyMeeting, Seattle, Wash, Aug 22-24, 1977, Paper 77-1215 7 p 6refs

New analysis methods and advanced instrumentation were usedto evaluate the flight test performance of the YC-15 STOL transportThe computations required to analyze various performance itemswere combined into computer programs These programs organizethe measured data into convenient formats, calculate basic performance parameters, standardize test results to final values, andprovide a summary of the performance obtained during a test runPrograms were developed for powered-lift equilibrium flight pathangle, takeoff distance, and landing distance performance Equilibnum flight-path performance potential was computed for climb,descents, level flight acceleration, and approaches to stall Amodified Inertial Navigation System (INS) was used to improve theaccuracy of rate-of-change of energy during flight maneuvers and as abackup to Laser Tracking System data for takeoff and landingperformance The development of the computer programs, in-teresting analysis features, and the quality of results obtained fromthe YC-15 Flight Test Program are described in this caper (Author)

A77-44318 § A digital data acquisition and reductionsystem for flight testing general aviation aircraft. R J Freuler and MJ Hoffmann (Ohio State University, Columbus, Ohio) American

Institute of Aeronautics and Astronautics, Aircraft Systems andTechnology Meeting, Seattle, Wash, Aug. 22-24, 1977, Paper77-1216 9p

A digital data acquisition and reduction system has beenimplemented for flight testing of light general aviation aircraft Thepackage has been assembled from off-the-shelf components and isintended for use in aircraft, where minimum weight and low powerrequirements are of primary concern The design objectives for thepackage were to provide an accurate, timely, and relatively low costdata acquisition and reduction system for flight test aircraftenvironments while maintaining flexibility in application, reliabilityin performance, and a capability for in-flight data reductionDiscussion of the design constraints and objectives which were metand those which had to be compromised is presented A completesystem description at both the hardware and software levels isincluded (Author)

A77-44319 * # Flight test results for an advanced technologylight airplane D L Kohlman American Instituteof Aeronautics andAstronautics, Aircraft Systems ana Technology Meeting, Seattle,Wash, Aug 22-24, 1977, Paper 77-1217 9 p 11 refs Grant NoNGR-17-002-072

A single engine light airplane was modified by the installation ofa wing with reduced area. Fowler flaps, Kruger flaps, and spoilersFlight test results show that zero-lift drag was reduced 13 8% and atrimmed maximum lift coefficient of 2 73 was achieved Gustresponse was significantly reduced and excellent roll control wasachieved with spoilers Several design features employed in the newwings have excellent potential for incorporation in future lightairplanes (Author)

A77-44320 ff An integrated approach to the problem ofaircraft icing D W Newton (Cessna Aircraft Co , Aircraft Radio andControl Div , Boonton, N J ) American Institute of Aeronautics andAstronautics, Aircraft Systems and Technology Meeting, Seattle,Wash. Aug 22-24, ,~<*/7, Paper 77-1218 10 p 9 refs

The paper is addressed to the need for a definition of theintensity of icmg conditions in terms of meteorological parameterswhich the forecaster can predict, the manufacturer can design to, andthe pilot can identify Contradictions in present regulatory andmeteorological definitions of icing conditions are discussed, and amethod of resolving them is suggested A discussion of the FAR 25icing envelopes as engineering rather than meteorological standards ispresented The question of whether a mean effective drop diameter isrepresentative of the drop size spectrum within an icing cloud isconsidered Definitions of icing intensity are suggested, and a methodof flight test data acquisition allowing determination of the intensityof icing conditions encountered is described (Author)

A77-44321 # Characteristics of fighter aircraft. G 0Madelung (Panavia Aircraft GmbH, Munich, West Germany).American Institute of Aeronautics and Astronautics, Aircraft Sys-tems and Technology Meeting, Seattle, Wash, Aug. 22-24, 1977,Paper 77-1219 7p

The history of fighter aircraft is reviewed, taking into accountearly developments, the introduction of the jet aircraft, and the

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fighters which were developed in the mid-50's The current situationwith respect to the requirements for new fighter designs isinvestigated Attention is given to V/STOL concepts in connectionwith airfield vulnerability considerations, low level/high speedpenetration, fan-jet engines, terrain following radar systems, thevariable sweep wing, the improvement of air-to-air combat capabilityin connection with design changes involving a decrease in wingloading, the 'look-down' capability of radar, the significance ofavionics, refinements in aircraft propulsion systems, aspects ofpost-stall maneuverability, the desirability to overcome the limita-tions of the fixed gun, and the development of unmanned fighteraircraft_ G R

A77-44322 # Parametric study of advanced long rangemilitary/commercial cargo transports. R H Lange and E S Bradley(Lockiieed-Georgia Co , Marietta, Ga ) American Institute of Aero-nautics and Astronautics, Aircraft Systems and Technology Meeting,Seattle, Wash , Aug 22-24, 1977, Paper 77-1221. 8 p 19 refs

This paper describes the results of Lockheed parametric designstudies of the performance and economics of advanced technologymilitary/commercial cargo transports envisioned for operation in the1985 and 1995 time period The design parameters investigatedinclude payloads from 220,000 to 550,000 pounds and ranges from3,500 to 5,500 nautical miles All configurations have supercriticalwings, advanced composite materials, relaxed static stability, and lownoise levels The application of laminar flow control (LFC) technol-ogy on the performance of an advanced military transport is alsopresented (Author)

A77-44323 * // Mass flow requirements for LFC wing design.A J Srokowski (NASA, Langley Research Center, High-SpeedAerodynamics Div , Hampton, Va ) and S A Orszag (MIT, Cam-bridge, Mass ) American Institute of Aeronautics and Astronautics,Aircraft Systems and Technology Meeting, Seattle, Wash , Aug22-24, 1977, Paper 77-1222 16 p 31 ref"

The problem of determining optimum suction mass flowrequirements for LFC wings is addressed Some previous methods forpredicting the extent of laminar flow over swept wings with suctionare briefly reviewed These range from the purely empirical to thoseutilizing tabulated linear stability computations The present methodis described This method solves the linear, incompressible stabilityequations by spectral techniques The maximum temporal amplification of boundary layer crossflow and 2 D disturbances is deter-mined for waves of a given frequency Group velocities are used tointegrate these amplification rates along the wing to yield thelogarithmic amplitude ratio or 'N factor' of the disturbance The 'Nfactor' calibration of a computer code utilizing this method isdescribed, using experimentally determined transition data Themethod is shown to be as consistent as previously used 'fixedwavelength'methods (Author)

A77-44324 * n Advanced turboprop technology developmentJ F Dugan (NASA, Lewis Research Center, Cleveland, Ohio), D PBencze, and L J Williams (NASA, Ames Research Center, MoffettField, Calif ) American Institute of Aeronautics and Astronautics,Aircraft Systems and Technology Meeting, Seattle, Wash, Aug.22-24, 1977, Paper 77-1223 16 p 17 refs

In order for new short-medium range transports to offersignificantly lower operating costs than potential derivatives ofcurrent designs using advanced technology, the efficiency improvements of high-speed turboprop propulsion systems may be requiredRecent studies indicate that the fuel savings of advanced turbopropaircraft appears to be 10 to 20 percent relative to equivalenttechnology turbofan aircraft These fuel savings are certainly largeenough to warrant further research to establish the viability ofturboprop transport aircraft The studies have identified the technology requirements in propeller design for high efficiency and lownoise, fuselage noise attenuation, propeller and gear box mainte-nance, and engme-airframe integration This paper presents a reviewof present research in each of these areas and describes the future

plans for continued development ot tne technology for advancedturboprop transport aircraft (Author)

A77-44325 * H Nonaxisymmetnc nozzle technology program -An overview B L Berrier (NASA, Langley Research Center,High-Speed Aerodynamics Div , Hampton, Va ), J L Palcza (U SNaval Air Propulsion Test Center, Trenton, N J ), and G K Richey(USAF, Flight Dynamics Laboratory, Wright-Patterson AFB, Ohio)American Institute of Aeronautics and Astronautics, Aircraft Sys-tems and Technology Meeting, Seattle, Wash, Aug. 22-24, 1977,Paper 77-1225 12 p 21 refs

Nonaxisymmetnc nozzles, with in-flight thrust vectoring and/orreversing capabilities, provide the potential for substantial gains infighter aircraft performance, maneuvering, survivabihty and groundhandling This paper presents an overview of some of the currentprograms to develop nonaxisymmetric nozzle technology for futureaircraft applications The initial phase of this program, which consistsof a series of subscale model tests, engine/nozzle studies, systemintegration studies and simulation studies, has been initiatedSuccessful completion of this program will allow designers of futureaircraft to consider, with high confidence, the integration ofnonaxisymmetric nozzle concepts to improve aircraft mission per-formance effectiveness, survivabihty and cost (Author)

A77-44326 * ft Effect of an integrated scramjet installation onthe subsonic performance of an aircraft designed to Mach 6 cruise PJ Johnston, J L Pittman (NASA, Langley Research Center,High-Speed Aerodynamics Div , Hampton, Va ), and J K Huffman(NASA, Langley Research Center, Subsonic-Transonic AerodynamicsDiv , Hampton, Va ) American Institute of Aeronautics and Astro-nautics, Aircraft Systems and Technology Meeting, Seattle, Wash,Aug 22-24, 1977, Paper 77-1230 11 p 8 refs

Various factors contributing to the high drag caused by theinstallation of a six-module scramjet engine were determined fromwind tunnel tests at Mach numbers from 02 to 0 7 Methods foralleviating this drag were also explored The external exhaust nozzle,required for good cruise performance, was a major contributor Ofthe drag produced by the engine modules, a significant fraction wasattributable to wall divergence in the combustor Good dragsimulation could be achieved by using a single fuel injection struthaving approximately the same cross-sectional area as the three usedon the full-scale engine External exhaust nozzle fences had a smallbut beneficial effect on maximum L/D and a flap which diverted theflow away from the inlet was effective in decreasing drag but only atlow angles of attack (Author)

A77-443Z7 # Powered lift - Its impact on YC-14 materialsand structures P J Harradme (Boeing Aerospace Co, Seattle,Wash ) American Institute of Aeronautics and Astronautics, AircraftSystems and Technology Meeting, Seattle, Wash , Aug 22-24, 1977,Paper 77-1231 8p

As a result of the selection of the upper surface powered liftsystem for the YC-14, thermal and acoustic environments became amajor factor in the design of wing and aft fuselage structures Thethermal environment governed the selection of flap materials andnecessitated use of a heat shield to piotect the aluminum alloy wingbox upper surface The flap and aft fuselage structural concepts werestrongly influenced by the acoustic environment in takeoff andapproach conditions Cost and weight effective design solutions weredeveloped within state of the art practices, reinforced by analysis andtesting The designs have been verified by full scale ground and flighttests (Author)

A77-44328 # Cast aluminum structures technology D DGoehler (Boeing Co , Seattle, Wash ) American Institute of Aero-nautics and Astronautics, Aircraft Systems and Technology Meeting,Seattle, Wash, Aug 22-24, 1977, Paper 77-1232 8 p USAF-supported research •

The CAST project has the objective to establish necessarystructural and manufacturing technologies and to demonstrate theintegrity, producibility, and reliability of cast aluminum primary

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A77 44336

airframe structures The program goal is to demonstrate a minimumof 30% acquisition cost savings with no weight penalty Currentprojections show that by applying CAST technology to the possibleC-14 production program, savings of over $100 million could beobtained G R

A77-44329 ff Advanced composites and advanced metallic*meet the challenge of design-to-cost. L Ascani and L Lackman(Rockwell International Corp, Los Angeles Aircraft Div., LosAngeles, Calif) American Institute of Aeronautics and Astronautics,Aircraft Systems and Technology Meeting, Seattle, Wash, Aug22-24, 19?7. Paper 77-1234 10 p

Aircraft technology is continually developing innovative con-cepts to produce aircraft with higher performance and lower costThis is particularly true in the field of aircraft structures, since thestructural airframe is a large fraction of the total cost and weight ofan aircraft Advanced structural concepts, which include integralstructure of advanced composites and superplastically-formed/diffusion bonded (SPF/DB) titanium, promise to produce significantreductions in airframe costs and weights Design studies using bothtypes of structure on a new-generation aircraft are compared toconventional materials and methods of construction (Author)

A77-44330 * !• Application of powered lift and mechanicalflap concepts for civil short-haul transport aircraft design. J AConlon and J V Bowles (NASA, Ames Research Center, MoffettField, Calif ) American Institute of Aeronautics and Astronautics,Aircraft Systems and Technology Meeting, Seattle, Wash, Aug22-24, 1977, Paper 77-1237 9p 10refs

The objective of this paper is to determine various design andperformance parameters, including wing loading and thrust loadingrequirements, for powered-lift and mechanical flap conceptualaircraft constrained by field length ana community noise impactMission block fuel and direct operating costs (DOC) were found foroptimum designs As a baseline, the design and performanceparameters were determined for the aircraft using engines withoutnoise suppression The constraint of the 90 EPNL noise contourbeing less than 2 6 sq km (1 0 sq mi) in area was then imposed Theresults indicate that for both aircraft concepts the design grossweight, DOC, and required mission block fuel decreased with fieldlength At field lengths less than 1100 m (3600 ft) the powered liftaircraft had lower DOC and block fuel than the mechanical flapaircraft but produced higher unsuppressed noise levels The noisegoal could easily be achieved with nacelle wall treatment only andthus resulted in little or no performance or weight penalty for allstudied aircraft (Author)

A77-44331 § Thrust augmenting ejector technology forNavy aircraft K A Green and J D Cyrus (US Naval MaterialCommand, Naval Air Development Center, Warmmster, Pa)American Institute of Aeronautics and Astronautics, Aircraft Sys-tems and Technology Meeting, Seattle, Wash, Aug 22-24, 1977,Paper 77-1239 12 p 18refs

The employment of V/STOL aircraft in the Navy is consideredin connection with a number of operational advantages which couldbe obtained by using such aircraft One of the propulsion conceptsexplored involves the employment of wing or fuselage mountedthrust augmenting ejectors Ejector technology has, in large measure,evolved from the XFV-12 A program. However, much remains to bedone in this area The design of a long-range technology developmentplan is discussed Attention is given to corner flows and wall jets, thedesign of compact d iff users, primary nozzles, a jet-diffuser ejector,reaction control augmenters, scaling effects, and prediction methods

G R

A77-44332 # Design criteria for aircraft warning, cautionand advisory alerting systems. J E Veitengruber (Boeing Com-mercial Airplane Co , Seattle, Wash ) American Institute of Aero-nautics and Astronautics, Aircraft Systems and Technology Meeting,Seattle, Wash., Aug 22-24, 1977, Paper 77-1240 9 p FAA-supported research

An overbundance of warning, caution and advisory alerts willexist in the cockpits of future commercial transport aircraft ifcurrent cockpit design trends are not altered Coupled with thisproliferation of alerts is a lack of correlation between alert typeapplications and significance The potential for pilot saturationand/or confusion exists with these alerts A study was performed forthe FAA to identify these problem areas and to develop designguidelines for alerting systems in new aircraft Recommendationsresulting therefrom include (1) improve pilots' audio/visual environ-ment by minimizing exposure to unnecessary alerts, (2) incorporatecentral alphanumeric alert readout devices, and (3) improve categori-zation and/or pnontization of alerts (Author)

A77-44333 ff Head-up display in commercial aviation. R JPhaneuf and J E O'Brien (Air Line Pilots Association, Washington,D C ) American Institute of Aeronautics and Astronautics, AircraftSystems and Technology Meeting, Seattle, Wash , Aug. 22-24, 1977,Paper 77-1241 10 p 40 refs

The potential role of head up display in U S commercialaviation as viewed by the airline pilot is summarized A brief reviewof the development of such systems is presented with emphasis onthe problems encountered and the time intervals involved Followinga presentation of a candidate head-up display system, the paperanalyzes the remaining problems which must be resolved before sucha system is likely to see widespread usage in the U S airline industry

(Author)

A77-44334 # The effect of terrain near airports on signifi-cant low level wind shear D F Sowa (Northwest Orient Airlines, StPaul, Minn ) American Institute of Aeronautics and Astronautics,Aircraft Systems and Technology Meeting, Seattle, Wash, Aug22-24, 1977, Paper 77-1242 5 p

Unique terrain near an airport can cause significant low levelwind shear to exist under certain meteorological conditions Thepresence of severe turbulence can compound the shear problem Theterrain near two airports, Anchorage, Alaska and Portland, Oregon, isdiscussed along with specific weather patterns that produce windshear at each airport Specific procedures are given that enable a pilotto identify the shear by type Operational techniques that effectivelyreduce the effect of the shear and the intensity of the turbulence atAnchorage are given (Author)

A77-44335 U Case studies m aircraft design U Haupt (U SNaval Postgraduate School, Monterey, Calif ) American Institute ofAeronautics and Astronautics, Aircraft Systems and TechnologyMeeting, Seattle, Wash. Aug 22-24, 1977, Paper 77-1244 10 p 11refs

A survey is given of various trends m aircraft design and indesign education A discussion of these trends indicates that a newgeneration of designers will have to be highly capable in a broad fieldfrom sophisticated methods to practical engineering experienceNeither engineering science curricula nor engineering technologycurricula can tx expected to prepare designers for this broad field Aproposal for a fresh approach is submitted where continuingeducation provides design-oriented courses for those engineers whochoose a career in design It will be necessary to prepare design-oriented text material and course outlines for design-orientedcourses The preparation of design-oriented text material as well asother aspects are discussed in some detail (Author)

A77-44336 * ~ Wing design by numerical optimization R MHicks (NASA, Ames Research Center, Moffett Field, Calif ) and P AHenne (Douglas Aircraft Co , Long Beach, Calif) American Instituteof Aeronautics and Astronautics, Aircraft Systems and TechnologyMeeting, Seattle, Wash , Aug 22-24. 1977, Paper 77-1247 8 p 11refs

A study was conducted to assess the feasibility of performingcomputerized wing design by numerical optimization The designprogram combined a full potential, inviscid aerodynamics code witha conjugate gradient optimization algorithm Three design problemswere selected to demonstrate the design technique The first involved

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modifying the upper surface of the inboard 50% of a swept wing toreduce the shock drag subject to a constraint on wing volume Thesecond involved modifying the entire upper surface of the sameswept wing (except the tip section) to increase the lift-drag ratiosubject to constraints on wing volume and lift coefficient The finalproblem involved modifying the inboard 50% of a low-speed wing toachieve good stall progression Results from the three cases indicatethat the technique is sufficiently accurate to permit substantialimprovement in the design objectives (Author)

A77-44337 * ft Optimum acoustic design of free-running lowspeed propellers A I Ormsbee and C J Woan (Illinois, University,Urbana, III ) American Institute of Aeronautics and Astronautics,Aircraft Systems and Technology Meeting, Seattle, Wash, Aug22-24, 1977, Paper 77-1248 6p 8 refs Grant No NGR-14-005-194

A theoretical analysis is conducted concerning the effect ofblade loading on the noise output of a free-running propeller in axialmotion The minimization of the mean square sound pressure at apoint in space is considered, taking into account constraints onpropeller thrust and torque Attention is given to aerodynamicequations, acoustic equations, the expansion of the aerodynamicvariables, and the nonlinear programming formulation G R

A77-44339 # The profile descent F L Cunningham (FAA,Washington, D C ) American Institute of Aeronautics and Astro-nautics, Aircraft Systems and Technology Meeting, Seattle, Wash ,Aug 22-24, 1977, Paper 77-1251 5p

This new air traffic control procedure is being implemented atall airports that accommodate high performance, turbine poweredaircraft Profile descent is designed to permit the operator to descendin a clean configuration at idle thrust to the final approach courseDelays caused by demand exceeding airport acceptance will beabsorbed at higher altitudes and not in the terminal area In additionto a significant arrival burn savings, safety, noise abatement, andstandardization of arrival procedures will be enhanced (Author)

A77-44340 H Role of future automated flight deck displaysin improving operating costs J W Lukms (Boeing CommercialAirplane Co , Seattle, Wash ) American Institute of Aeronautics andAstronautics, Aircraft Systems and Technology Meeting, Seattle,Wash , Aug 22-24, 1977, Paper 77-1252 10 p

This independent paper discusses the role of future automatedflight deck displays and systems which will improve the operatingeconomics of commercial jet airplanes. As an introduction to thepresent trends of rising operating costs, an overview of the situationthat the airlines are facing is given This is followed by some generalcomments on new design technology for aerodynamic, structural andengine optimization which will help operating costs on the nextgeneration aircraft A detailed discussion is then provided on cockpitsystems that have recently become available or are expected in thenear future Special attention is given to devices which compute anddisplay information to the flight crews which allows them to fly costoptimal fligtit profiles (Author)

A77-44343 ff Air New Zealand's methods of flying theDC-10 W H Dunn (Air New Zealand, Ltd, Auckland, NewZealand) American Institute of Aeronautics and Astronautics,Aircraft Systems and Technology Meeting, Seattle, Wash., Aug22-24, 1977, Paper 77-1255 8 p

The described methods are concerned with an achievement ofmaximum payloads and minimum fuel costs An average reduction intakeoff power to a value which is about 15 percent below themaximum power available has been obtained with the aid of aderating technique which ensures good aircraft performance safetyA circular slide rule is used for all phases of flight from takeoff tolanding for determining engine power setting and checking engineperformance and aircraft drag Attention is given to the takeoffthrust setting, the effect of runway conditions on performance,performance margins, a method of presentation of takeoff data for

individual runways, an en route climb technique, and aspects ofcruise performance presentation G R

A77-44344 # Applicability of axisymmetnc analysis in pre-dicting supersonic flow through annular cascades H -H Fruehauf(Stuttgart, Umversitat, Stuttgart, West Germany) (American Societyof Mechanical Engineers, Paper 76-Pwr-B, 1976) ASME, Transac-tions, Series A - Journal of Engineering for Power, vol 99, Jan 1977,p 115-120 5 refs Research sponsored by the Deutsche Forschungs-gememschaft

Solutions of the differential equations of the axisymmetncmodel and circumferentially averaged solutions of the differentialequations of the three-dimensional model are compared quantitative-ly for steady supersonic flows through rotating annular cascadesThereby three-dimensional corrections for flow quantities, whichdetermine the applicability of the axisymmetnc analysis, are in-vestigated as a function of geometrical and gas dynamical parametersFinally, these three-dimensional corrections are compared to threedimensional corrections for the solutions of the usual blade-to-blademodel on cylindrical surfaces of revolution for identical annularcascades (Author)

A77-44345 ,<? Stall margin improvement by casing treatment- Its mechanism and effectiveness H Takata (Tokyo, University,Tokyo, Japan) and Y Tsukuda (Mitsubishi Heavy Industries, Ltd ,Takasago, Hyogo, Japan) (American Society of Mechanical Engi-neers, Paper 76-GT-A, 1976 ) ASME, Transactions, Series A - Journalof Engineering for Power, vol 99, Jan 1977, p 121 133 5 refs

Experiments on the effect of casing treatment were carried outusing low-speed axial-flow compressors Results on the overallcompressor performance and on the flow through the blade row aswell as the flow within the treatment slots are presented Then, basedon the experiments, a possible mechanism of the stall marginimprovement is suggested (Author)

A77-44427 * ff An overview of Viking navigation. W J O'Neil(California Institute of Technology, Jet Propulsion Laboratory,pisadena, Calif ) In National Aerospace Meeting. Denver, Colo ,Mpnl 13, 14, 1977, Proceedings Washington,D C, Institute of Navigation, 1977, p 1-8 Contract No NAS7 100

Viking flight path design and inflight control of Viking Ts pathfrom earth launch to Mars landing are described Attention isdirected to the Lander descent, accessible area constraints, orbitinsertion design, and earth departure control Other topics includethe orbital operations plan, the Viking heliocentric trajectory, andMars approach control M L

A77-44431 # Umted's experience with computer generatedvisual systems, April 1977 G V Me Cu I loch (United Air Lines FlightTramma Center Denver, Colo I In National Aerospace Meeting,Denver, Colo , April 13, 14, 1977, ProceedingsWashington, D C , Institute of Navigation, 1977, p 28-30

Experience with three types of simulator visual systems inoperational use is reported The three types are computer generatedimaging (CGI), cinematography, and closed circuit television withmodel board CGI is considered preferable on the basis of economyand operational viability Some apparent d e , not yet experimentallyverified) advantageous features include the gaming area, transport lagand synchronization, visual field, topographic verisimilitude, andvisual attributes The most serious disadvantages are thought toinvolve the light point quality, weather simulation, and sceneperspective For example, while the real light points that define thenight signature of an airport and city have almost infinite variability,the light points in the CGI display have a very limited varietyResearch aimed at establishing transfer-of-learning effectiveness forthe features of CGI systems is urged M L

A77-44432 ft RNAV waypomt charting effects on pilotprocedures, training and workload. R J Adams (Systems Control,

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Inc , West Palm Beach, Fla ) and P Rich (FAA, Washington, D C )In National Aerospace Meeting, Denver, Colo , April 13, 14, 1977,Proceedings Washington, D C , Institute ofNavigation, 1977, p 31-37 7 refs

With consideration of the 1973 report. 'Application of AreaNavigation in the National Airspace System', a summary is presentedof the analytical procedure used to establish waypomt chartingrequirements From this theoretical base, the paper introducesseveral currently used area navigation (RNAV) Standard InstrumentDeparture (SID) and Standard Terminal Arrival Routes (STAR) Theadvantages gained by both the pilot and air traffic control systemthrough the proper use of pilot procedures is quantified by usingdetailed flight test results from the Miami, Denver, and Chicagoterminal areas and also flight simulator results M L

A77-44433 H Terminal area charting for area navigationoperations E D McConkey (Systems Control, Inc, West PalmBeach, Fla ) In National Aerospace Meeting, Denver, Colo , April13, 14, 1977, Proceedings Washington. DC,Institute of Navigation, 1977, p 38-42

A77-44434 ff Fuel conservation for high performance air-craft in the terminal area S C Mohleji (Mitre Corp , Metrek Div ,McLean, Va ) In National Aerospace Meeting, Denver, Colo , April13, 14, 1977, Proceedings Washington, DC,Institute of Navigation, 1977, p 43-46-C 7 refs

In a high density terminal area, speed' control and radarvectoring are typically used to optimize the sequence and assure thespacing of landing aircraft for maximum runway utilization Thepaper describes an approach for the Air Traffic Control (ATC)system in the terminal area to accommodate fuel conserving landingapproaches Analytical results are presented that illustrate the impactof fuel economic design on terminal controllability and airportcapacity Peak hour trade-offs between conserving fuel and maxi-mizing runway utilization are also included in the paper Ananalytical fuel consumption model is used to estimate the fuelbenefits of lifting the 250 knots speed restriction below 10,000 ftmean sea level (MSL), for both arrivals and departures (Author)

A77-44435 ff Probing the airborne Omega environment J JScavullo (FAA, National Aviation Facilities Experimental Center,Atlantic City, N J ) In National Aerospace Meeting, Denver, Colo ,April 13, 14, 1977, Proceedings Washington,D C , Institute of Navigation, 1977, p 53-58 6 refs

Prospective users have begun to request the Federal AviationAdministration (FAA) to certify the Omega Navigation System overoceanic |et routes and over the routes of off-shore oil-lease areas TheFAA has sampled the quality and coverage of Omega signals in manyof these areas Data recorded during a number of probe flights hasbeen consistent with forecasts of coverage as well as with predictedgaps due to large discontinuities along the propagation pathway, suchas the dielectric ice mass on Greenland The paper proposes toextend in-flight data collection all around the world during theimminent rising portion of the next sun spot cycle It outlines a planto develop a bank for the data and to publish a running account ofthe findings under a cooperative industry-government effort

(Author)

A77-44436 ff Aircraft navigation with the limited operation-al phase of the NAVSTAR Global Positioning System L RKruczynski (U S Air Force Academy, Colorado Springs, Colo.) InNational Aerospace Meeting, Denver, Colo, April 13, 14, 1977,Proceedings Washington, D C, Institute ofNavigation, 1977, p 59-68 8 refs Research supported by the GlobalPositioning System Joint Program Office

In 1980, the NAVSTAR Global Positioning System (GPS) willbe in the limited operational phase During this phase, a GPS userwill not generally be able to determine his position using satellitemeasurements only This paper describes the simulation of an aircraftnavigation technique which uses the limited operational phase GPSand barometric altimeter measurements For this research effort, theGPS user was assumed to be a cargo-type aircraft equipped with a

single-frequency, sequentially-tracking GPS receiver and a barometricaltimeter Such equipment is expected to be relatively inexpensiveThe flight profile consisted of a New York to Chicago flight andincluded takeoff and landing maneuvers A small amount of windgusts were simulated To make the simulation more realistic, randomeffects were included in the user and satellite clocks, in theatmospheric radio delays, and in the measurement process itself Thetested navigation algorithm is based on the well-known Kalman filterequations Three different models of aircraft acceleration wereevaluated Results indicate that, for a wide range of filter parameters,navigation errors are generally less than 100 meters Poor geometry,however, results in kilometer-sized position errors. (Author)

A77-44437 ff Helicopter offshore operations W T Kuharand G H Quinn (FAA, Navigation Div, Washington, DC) InNational Aerospace Meeting, Denver, Colo, April 13, 14, 1977,Proceedings Washington, D C, Institute ofNavigation, 1977. p 69-71

The sale of lease sites off the U S coast and in Alaska, for oiland gas exploration and production, has resulted m a need forhelicopter operations in offshore areas in instrument weatherconditions Such operations require an air traffic control system anda navigation capability that will extend to 300 miles from shore, andprovide guidance down to 200 feet above sea level Accuracy andreliability must be at least equal to that available with VOR-DMEThe overall offshore situation is described and FAA and industryefforts to meet the helicopter offshore navigation requirements areexplained (Author)

A77-44438 ff Omega system performance predictions. A DThompson (Boeing Co , Seattle, Wash ) In National AerospaceMeeting, Denver, ,Colo, April 13, 14, 1977, Proceedings

Washington, DC, Institute of Navigation, 1977, p72-81 7 refs

Under normal atmospheric conditions the Omega navigationsystem provides worldwide coverage with a potentially high index ofaccuracy To a large degree the achieved performance dependsheavily upon the processing algorithm employed in the mobileterminal This dependence is illustrated for two classes of receiverswhich were configured to emulate hyperbolic regimes based uponalternate station selection criteria Both receiver sets were exercisedon a worldwide basis for position fix ensemble sizes of three, fourand five transmitter stations Results are given in terms of contoursand histograms of the predicted rms position error and capsulestatistics of the overall global performance (Author)

A77-44439 ff VLF pulse timing - Limitations and potentialas a companion to Omega R G Brown (Iowa State University ofScience and Technology, Ames, Iowa) In National AerospaceMeeting, Denver, Colo, April 13, 14, 1977, Proceedings

Washington, DC, Institute of Navigation, 1977, p82-87 9 refs Research supported by the Iowa State University ofScience and Technology

The potential accuracy of VLF pulse (envelope) timing isseverely limited by vagaries of the propagation medium andatmospheric noise due to spherics These limitations are discussed indepth The conclusion is that VLF pulse-timing accuracy corre-sponding to about 5 n mi should be possible over very long rangesup to 5000 n mi A hypothetical system employing pulse trans-mitters co-located at the Omega sites is explored It is proposed thatsuch a pulse system and the present phase-only Omega system couldserve to complement each other as a coarse-fine system (Author)

A77-44440 An analysis of helicopter rotor response due togusts and turbulence M Judd and S J Newman (Southampton,University, Southampton, England) Vertica, vol 1, no 3, 1977, p179-188 8 refs

Analyses are presented for the rotor and vehicle response togusts and turbulence The nature of helicopter alleviation factors isdiscussed and the rotor response to sinusoidal gusts is used to buildup the aircraft spectral behaviour The formulation of a more

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detailed study of step and ramp gust response is described briefly andpreliminary results presented 'Author)

A77-44441 Main rotor wake/tail rotor interaction J WLeverton, J S Pollard, and C R Wills (Westland Helicopters, Ltd ,Yeovil, Somerset, England) (European Rotorcraft and Powered LiftAircraft Forum, 1st, University of Southampton, Southampton,England, Sept 22-24, 1975) Vertica, vol 1, no 3, 1977, p 213-2215 refs

An experimental procedure is worked out for isolating the noiseresulting from interaction of the tail rotor and vortices shed from themain rotor, to determine the frequency and amplitude characteristicsof the interaction noise A theoretical model is described, and theexperimental arrangement, using a ground array of microphones anddata from on-board microphones, is also described Interaction noisesignals were difficult to simulate on the computer, and the pulsesignal was consistently distorted by the analysis procedures Revers-ing the sense of rotation of the tail rotor abated some of the peculiarburbling deep-throated interaction noise The study is consideredapplicable to any impulsive or semi-impulsive noise source, somenoise sources commonly considered steady-state are actually impul-sive in character R D V

A77-44442 On the static pressure in the wake of ahovering rotor A R S Bramwell (City University, London,England) (European Rotorcraft and Powered Lift Aircraft Forum,1st, University of Southampton, Southampton, England, Sept22-24, 1975) Vertica, vol 1, no 3, 1977, p 223-230 7 refs

One of the basic assumptions of the classical airscrew momen-tum theory is that the static pressure m the airscrew wake is the sameas that of the surrounding air Consideration of the wake as the airset in motion by the vortex sheets shed by the individual blades leadsto the conclusion that, even when the number of blades is infinite,the final wake static pressure is different from that of thesurrounding air, in fact, the static pressures are determined by therequirement that the total head should be the same throughout theflow The difference between the wake and ambient static pressuresis greatest when the axial velocity is zero, i e , for the hovering rotorA corresponding modification to the momentum theory shows thatthe ratio of the induced velocity in the wake to that at the rotor ismuch less than that given by the standard momentum theory, withcorresponding increase in the contraction ratio Tests on a smallrotor m the hovering condition confirm that a static pressuredifference does exist although it is not so large as suggested by thetheory, but this is thought to be due to the fact that the wake fromthe rotor was probably far from the ideal wake assumed by thetheory The work suggests that a reappraisal of the momentumrelationships in hovering flight and at low axial speeds should bemade (Author)

A77-44443 The remotely piloted helicopter A JFaulkner and I A Simons (Westland Helicopters, Ltd, Yeovil,Somerset, England) Vertica, vol 1,no 3, 1977, p~231-238

This article describes some of the fundamental problemsassociated with current fixed wing remotely piloted vehicles,particularly during launch and recovery, and introduces the idea of asmall remotely piloted helicopter in the role of real time surveillanceand reconnaissance It is argued that a co-axially rotored helicopterwith a plan-symmetric fuselage is the most suitable configuration forremote piloting as it offers the simplest form of pilot controls,minimises rotor cross-couplings and permits a cartesian mode ofoperation The problems associated with the aerodynamic shape ofthe fuselage are indicated and the importance of automatic stabiliza-tion is discussed in some detail Finally a brief account is given ofsome experimental flight testing carried out on a small scale co-axialhelicopter (Author)

A77-44444 On the validity of lifting line concepts in rotoranalysis T Van Molten (Delft, Techmsche Hogeschool, Delft,Netherlands) (European Rotorcraft and Powered Lift Aircraft

Forum, 1st, University of Southampton, Southampton, England,Sept 22-24, 19751 Vertica, vol 1, no 3, 1977, p 239-254

Using the acceleration potential description of flow fieldscombined with a matched asymptotic expansion technique, ahigher-order lifting line theory can be developed which takes intoaccount all the unsteady, yawed flow effects encountered byhelicopter blades This theory points out several errors in the usuallifting line methods of rotor analysis (Author)

A77-44453 * ~ Macroscopic study of time unsteady noise ofan aircraft engine during static tests B J Clark, M F Heidmann,and W J Kreim (NASA, Lewis Research Center, Cleveland, Ohio)Acoustical Society of America, Meeting, 92nd, San Diego, Calif.,Nov 16-19, 1976, Paper 14 p 9 refs

Static tests of aircraft engines can exhibit greater than 10 dBrandom unsteadiness of tone noise levels because flow disturbancesthat prevail near test site facilities are ingested Presumably suchchanges are related to installation and test site features This paperpresents some properties of unsteady noise observed at a NASA-Lewis facility during tests of a Lycommg YF-102 turbofan engineTime and spatial variations m tone noise obtained from closelyspaced far-field and inlet duct microphones are displayed Long (0 5sec) to extremely short (0001 sec) intermittent tone bursts areobserved Unsteadiness of the tone, its harmonics, and the broadbandnoise show little similarity In the far-field, identity of tone bursts isretained over a directivity angle of less than 10 deg In the inlet duct,tone bursts appear to propagate axially but exhibit little circum-ferential similarity They show only slight relationship to tone burstsobserved in the far field The results imply an intermittent generationof random mixtures of propagating duct modes (Author)

A77-44456 * # Simulation of flight-type engine fan noise mthe NASA-Lewis 9 x 1 5 anechoic wind tunnel M F Heidmann andD A Dietrich (NASA, Lewis Research Center, Cleveland, Ohio)Acoustical Society of America, Meeting, 92nd, San Diego, Calif,Nov 16-19, 1976, Paper 24 p 26 refs

A major problem in the measurement of aircraft engine fannoise is the difficulty of simulating, in a ground-based facility, thenoise that occurs during flight Flight-type noise as contrasted to theusual ground static test noise exhibits substantial reductions in both(1) the time unsteadiness of tone noise and (2) the mean level oftones calculated to be nonpropagating or cut off A model fandesigned with cut-off of the fundamental tone was acousticallytested in the anechoic wind tunnel under both static and tunnel flowconditions The properties that characterize flight type noise wereprogressively simulated with increasing tunnel flow The distinctlylobed directivity pattern of propagating rotor/stator interactionmodes was also observed The results imply that the excess noiseattributed to the ingestion of the flow disturbances that prevail nearmost static test facilities was substantially reduced with tunnel flowThe anechoic wind tunnel appears to be a useful facility for appliedresearch on aircraft engine fan noise under conditions of simulatedflight (Author)

A77-44457 * # Core noise source diagnostics on a turbofanengine using correlation and coherence techniques A Karchmer andM Reshotko (NASA, Lewis Research Center, Cleveland, Ohio)Acoustical Society of America, Meeting, 92nd, San Diego, Calif.,Nov 16-19, 1976, Paper 27 p 7 refs

Fluctuating pressure measurements at several locations withinthe core of a turbofan engine were made simultaneously withfar-field acoustic measurements Correlation and coherence tech-niques were used to determine the relative amplitude and phaserelationships between core pressures at these various locations andbetween the core pressures and far-field acoustic pressure The resultsindicate that the combustor is a low-frequency source region foracoustic propagation through the core nozzle and out to the far-fieldSpecifically, it was found that the relation between source pressureand the resulting sound pressure involves a 180 deg phase shift andan amplitude transfer function which varies approximately as

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frequency squared This is shown to be consistent with a simplifiedmodel using fluctuating entropy as a source term (Author)

A77-44460 * ft Effects of forward velocity on noise for a J85turbojet engine with multitube suppressor from wind tunnel andflight tests J R Stone. J H Miles, and N B Sargent (NASA, LewisResearch Center, Cleveland, Ohio) Acoustical Society of America,Meeting, 92nd, San Diego, Calif, Nov 16-19, 1976, Paper. 30 p 28refs

Flight tests and wind tunnel noise tests using a J85 engine withsome representative jet exhaust noise suppressors are reportedCapabilities and limitations of the two types of experimentalmethods are evaluated with emphasis on investigation of forwardvelocity effects The suppressor arrangement was a 104 elliptical-tubenozzle configuration, with or without an acoustically lined shroudThe suppressor noise levels are found not reduced as much byforward velocity as expected for unsuppressed jets The directivityand forward velocity effects appear more similar to predicted trendsfor internally generated noise than for unsuppressed |et noise R D V

A77-44461 * rf OTW noise correlation for several nozzle/winggeometries using a 5 1 slot nozzle with external deflectors U vonGlahn and D Groesbeck (NASA, Lewis Research Center, Cleveland,Ohio) Acoustical Society of America, Meeting, 92nd, San Diego,Calif, Nov 16-19, 1976, Paper 28 p 9 refs

Acoustic spectral data obtained from a model-scale study ofseveral OTW configurations with a 5 1 slot nozzle using variousexternal deflectors are correlated in terms of deflector geometry andflow parameters Variations in the deflector geometry includedeflector size and deflector angle In addition, geometry variations inflap setting and nozzle chordwise location are included Threedominant noise sources are correlated fluctuating lift noise, flaptrailing edge noise, and jet mixing noise Aerodynamic charac-teristics, including lift and thrust measurements, obtained for thevarious configurations are summarized (Author)

A77-44462 * if Flight effects on exhaust noise for turbojetand turbofan engines - Comparison of experimental data withprediction J R Stone (NASA, Lewis Research Center, Cleveland,Ohio) Acoustical Society of America, Meeting, 92nd, San Diego,Calif, Nov 16-19, 1976, Paper 20 p 23 refs

Recent experiments on the effects of flight on jet engineexhaust noise have produced apparently conflicting results Some ofthese results do not agree with projections based on classical jet noisetheories nor with experimental results from model jet simulatedflight tests It has been shown that in some of the cases reported, theproper corrections were not made to account for the distributednature of the jet noise sources It is shown herein that the remainingdiscrepancies can be reconciled by considering the combined effectsof jet mixing noise, internally generated engine exhaust noise, andshock noise This paper demonstrates that static and in-flight jetengine exhaust noise can be predicted with reasonable accuracy whenthe multiple-source nature of the problem is taken into accountJet-mixing noise is predicted from an improved version of the NASAinterim prediction method Provisional methods of estimatinginternally generated noise and shock noise flight effects are used,based partly on existing prediction methods and partly on recentlyreported engine data (Author)

A77-44513 An interpretation of the Army standard hotday in operational terms W G Bousman (U S Army, Air MobilityResearch and Development Laboratory, Moffett Field, Calif)American Helicopter Society, Journal, vol 22, July 1977, p 10-12

A technique for interpreting a military helicopter design point,using the U S Army standard hot day concept specifying tempera-ture and pressure altitude conditions for successful hover maneuversby the rotorcraft, is proposed The method relates the verticalperformance capability (VPC) of the machine to the climatology of aselected region using the distribution of hours per day over a yearwhen the aircraft is capable of meeting its specified vertical

performance requirements Cumulative probabilities of elevation andtemperature for the region and VPC as a function of design pressurealtitude and temperature and of service time over the year arestudied RD V

A77-44514 Engine control stabilizing compensation-testing and optimization J R Alwang (Boeing Vertol Co, Phila-delphia, Pa ) and C A Skarvan (General Motors Corp., Detroit DieselAllison Div , Indianapolis, Ind) American Helicopter Society,Journal, vol 22, July 1977, p 13-18

A discussion of engine control compensation for power turbinespeed governing system stabilization is presented Testing of variouscontrol compensation techniques in a dynamic helicopter environ-ment is described with analytical correlation between computersimulation and test results Extrapolation from test to aircraftconfiguration for defining compensation requirements through theoperating extremes is illustrated (Author)

A77-44515 Emergency-power benefits to multi-enginehelicopters. R D Semple, J H Yost, E W King, J E Gonsdives(Boeing Vertol Co , Philadelphia, Pa ), and W Thompson (U SArmy, Ballistics Research Laboratory, Aberdeen Proving Ground,Md ) American Helicopter Society, Journal, vol 22, July 1977, p27-33

Emergency power to enable military twin-engine or multi-enginehelicopters to recover from emergency situations with one engineinoperative is discussed Requirements of an emergency powersystem, cost, test substantiation, operational power checkout, andengine materials assessments (turbine blade life, strength of thematerials, turbine blade temperature, and blade-root stress) arestudied Reductions in forced and crash landings, and in forcedjettisoning of stores, are obvious benefits, but advantages from safertakeoffs with heavier loads, safe rooftop operations, lower vulnera-bility to hostile action, and overall system cost reduction are alsoexpected from enhanced engine-out capability Application ofemergency power would necessitate prompt hot-end inspection andreplacement of hot engine components R D V

A77-44550 Air transport noise reduction R J Koemg(FAA, Environmental Research Branch, Washington, D C ) NoiseControl Engineering, vo\ 8, May-June 1977, p 120-130.41 refs

Aircraft noise regulation and trends in noise reduction tech-nology are discussed In particular, the noise abatement programincorporated in the FAA's Five-Year Environmental Plan (1976-80),involving noise reductions at the design level, modification of airportand flight procedures, attainment of compatible land use in airportzones, and retiring or modification of existing aircraft that do notmeet noise abatement standards, is considered Noise level contoursfor aircraft with low-bypass-ratio and high-bypass-ratio turbofanengines are given, and the FAA rule of 1977 governing takeoff,sideline and approach noise limits is discussed Aspects of aircraftacoustic design related to jet noise, fan noise, turbine and combustortechnology, airframe noise, acoustic treatment of nacelle ducts,mufflers, and aircraft and nacelle configurations are also considered,together with acoustic testing techniques. J M B

A77-44565 The effect of boundary layer changes due totransient heat transfer on the performance of an axial-flow aircompressor N R L Maccallum (Glasgow, University, Glasgow,Scotland) and A D Grant (Strathclyde, University, Strathclyde.Scotland) Society of Automotive Engineers, International Auto-motive Engineering Congress and Exposition, Detroit, Mich, Feb28-Mar 4, 1977, Paper 770284 10 p 17 refs

The results of an investigation concerning flow over a hotconvex surface are incorporated in an exploratory method forpredicting the characteristics of a multistage axial-flow compressorThe application of the method is illustrated with the aid of anexample involving the conditions in a compressor at the end of arapid deceleration at an altitude of 12,200 m from maximum speedto flight idle speed, prior to a possible acceleration The objective of

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the investigation is to predict the change in the characteristics of areal, three-dimensional compressor due to heat transfer G R

A77-44570 Position finding using distance measurements(Localisation par mesures de distance) P Hugon (Institut Francaisde Navigation, Pans, France) Navigation (Paris), vol 25, July 1977,p 269-275 In French

Fairly inexpensive data acquisition and reception devices forobtaining fixes on positions on a great-circle route with measure-ments of successive phases are discussed Conditions for reception ofLF and VLF emissions from coastline stations and the circuitry ofon-board receivers are discussed Suitable approximations for practi-cal navigation work and estimates of distance error are attended to

R DV

A77-44571 A special-purpose pocket calculator for avia-tion and maritime navigation (Une calculatrice de poche specialepour la navigation aenenne et maritime) M Zimeray (SocieteSonotec, Pans, France) Navigation (Pans), vol. 25, July 1977, p276-284 In French

The NAV-60 special-purpose pocket calculator dedicated toaviation navigation computation problems is described, and threeprograms are run through in detail (correction of speed given byDME equipment, combination of current vectors, solving aircraftspeed triangle and same adapted to ship navigation) with keystrokesequences indicated and explained Some of the NAV-60 pre-programmed capabilities are indicated, and the dual-function key-board (English symbols) with both conventional slide-rule functionsand navigation-dedicated functions is described Direct conversionsfrom deg/mm/sec or hr/mm/sec to decimals and vice versa, and keysfor dead reckoning, VOR fixes, VOR-aided navigation, and rhumb-line navigation, are appreciated, and equivalent interpretations foraviation and maritime navigation are offered R D V

A77-44572 Outlook for utilization of the North Atlanticair space in 1978 (Perspectives d'utihsation de I'espace aerienI'Atlantique Nord en 1978) J Fournier (Compagnie Nationale AirFrance, Pans, France) Navigation (Paris), vol 25, July 1977, p313-324 In French

Termination of the Loran-A system, new conditions associatedwith the introduction of the Omega and INS navigational systems,requirements for transatlantic aircraft under MNPS (MinimumNavigation Performance Specifications), and system adjustments andproblems are discussed Training and retraining of crews and ofnavigators in particular, Omega and INS system errors and adjust-ments at introduction and in-flight, error detection, and flightanalysis are discussed The navigation systems of Concorde, Boeing747, and Boeing 707 are described and characterized in this context

R D V

A77-44738 Software implementation of a PN spreadspectrum receiver to accommodate dynamics C R Cahn, D KLeimer, C L Marsh (Magnavox Government and Industrial Electro-nics Co , Torrance, Calif ), F J Huntowski, and G D Larue (U SArmy, Satellite Communications Agency, Fort Monmouth, N J )IEEE Transactions on Communications, vol COM-25, Aug 1977, p832-840 8 refs

An experimental project was undertaken to modify an existingground PN modem (AN/USC-28, ADM version) for flight test Asoftware implementation of the digital tracking algorithms wasselected where a HP-2100A minicomputer controls carrier frequencyand PN code phase via digital phase shifters The Costas demodulatorfor extracting PSK data resides entirely in software, and iscompletely segregated from PN tracking In laboratory testing of thereceiver with simulated dynamics and in actual flight tests, thedemonstrated performance was found to approach closely the goalsestablished by the analyses and simulations (Author)

A77-44783 An electro-optic airspeed sensor M J Rudd(Bolt Beranek and Newman, Inc , Cambridge, Mass I, G A DuBro,and D G Kim (USAF Dynamics Laboratory, Wright-Patterson AFB

Ohio) In Electro-optical Systems Design Conference and Inter-national Laser Exposition, New York, N Y , September 14-16, 1976,Proceedings of the Technical Program Chicago,Industrial and Scientific Conference Management, Inc, 1976, p384-392 13 refs

The Optical Convolution Velocimeter, an electro-optic airspeedsensor capable of measuring airspeeds from 2 to 120 mph, isdescribed Flow in the airstream is visualized by a shadowgraphoptical system and the speed at which the shadowgraph crosses agrating is measured as a frequency The shadowgraph optical system,relevant optical theory, and calculations of the signal strength areexamined The velocimeter is an absolute velocity sensor which needsno calibration The device operates under adverse environmentalconditions, is inexpensive since it does not contain high precision ordelicate parts, and provides a digital output (frequency proportionalto velocity) M L

A77-44812 General principles of automatic TV trackersF J Thomas and C A Winsor (Martin Marietta Aerospace, Orlando,Fla) In Electro-optical Systems Design Conference and Inter-national Laser Exposition, New York, N Y , September 14 16, 1976,Proceedings of the Technical Program Chicago,Industrial and Scientific Conference Management, Inc, 1976, p683-694

Various techniques of electro-optical signal processing have beendeveloped to provide fire control and missile systems with anautomatic tracking capability Of particular interest are those trackerconcepts that have been developed to operate with real-time imagingsystems, especially those compatible with standard televisionformats This paper reviews the general principles of automatic TVtrackers and examines similarities and differences in such areas astracking aperture, video processing concepts, and error detectionalgorithms In addition, performance metrics and system applicationsare briefly discussed (Author)

A77-44814 Scanned laser visual system C R Dnskell(US Army, Orlando, F la) and A M Spooner (Redifon FlightSimulation, Ltd, Crawley, Sussex, England) In Electro-opticalSystems Design Conference and International Laser Exposition, NewYork, N Y, September 14-16, 1976, Proceedings of thp TechnicalProgram Chicago, Industrial and Scientific Con-ference Management, Inc , 1976, p 738-743

A description is presented of an advanced, high-resolutionwide-angle visual system for military flight simulation The lasercamera of the system employs two high power ion lasers, includingan argon laser to provide green and blue primary colors and akrypton laser to supply the red primary color The output beamsfrom the lasers are combined and fed to the laser camera with the aidof fiber-optics components Attention is given to aspects of imagegeneration, a description of the laser visual system, the field of viewand resolution, the optical layout, problems of focussing, and aspectsof attitude control G R

A77-44815 ff A new concept of static stability and its flighttesting in supersonic flight G Sachs (Darmstadt, TechmscheHochschule, Darmstadt, West Germany) Journal of Aircraft, vol 14,Sept 1977, p 874-880 13 refs

The current concept of static stability is not adequate forsupersonic flight since it does not account for the influence of forcesand moments due to altitude perturbations, which have a significanteffect on the longitudinal motion A new concept is proposed thataccounts for altitude influence in an adequate manner This concept,which is closely related to constant energy considerat on, is based ona dynamic stability analysis with particular reference to theexponential characteristic modes of the airplane Furthermore, it isshown that the well-known relation between static stability and thevariation of elevator angle with speed is not valid in supersonic flightAs a consequence, the flight test methods currently used fordetermining static stability also are not adequate for supersonicflight A new flight test method is proposed that provides an

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indication of static stability using the variation of elevator angle withaltitude (or dynamic pressure, respectively) The points addressedmay be of particular significance in regard to existing flying qualitiesrequirements and criteria (Author)

A77-44816 # An investigation of the near-field wake behinda full-scale test aircraft L J Mertaugh, R B Damania (MississippiState University, Mississippi State, Miss), and F L Paillet (USAF,Flight Dynamics Laboratory, Wright-Patterson AFB,_Ohio) Journalof Aircraft, vol 14, Sept 1977, p 894-902 10 refs "Contracts NoF33615-72-C-1052, No F36615-74-C-3066

Th»ee-dimensional velocity field measurements were made onthree transverse measurement planes located at 7 7, 33 3, and 61 2in behind the inboard wing trailing edge of an aircraft in flight Thetest aircraft featured a distributed suction boundary-layer controlsystem Test data were obtained at various lift coefficients and withboth zero and full flap deflections Flowfield measurements weremade with a total-vector hot-film probe mounted to a boom andtraversing mechanism attached to the rear fuselage of the testaircraft The velocity measurements allowed computation of all threecomponents of vorticity at the 7 7-in plane and the normal (to themeasurement plane) component of vorticity at the other two planesThe test results are presented as a series of contours of the variousvorticity component values in the measurement planes The forma-tion of a concentrated core of axial vorticity is noted The test dataare also compared to the predictions of.a two-dimensional inviscidwake calculation based on measured wing loading for the L-19

(Author)

A77-44817 * H Stream tube analysis of a hydrogen-burningscramjet exhaust and simulation technique N A Talcott, Jr and JL Hunt (NASA, Langley Research Center, High-Speed Aero-dynamics Div , Hampton, Va ) Journal of Aircraft, vol 14, Sept1977, p 918-920 7 refs

A scramjet/airframe integration program and a technique forsimulating thermally perfect scramjet exhaust flows (freon/argon gasblends) is studied to extend the technique to more complicated flowsapproaching the actual exhaust flow in complexity The state of theflow and the accuracy of the substitute gas simulation are analyzedin the case of a shock discontinuity present Findings are scramjetexhaust flow is essentially frozen throughout the expansion at Mach6 and Mach 8, flow behind moderate shocks remains frozen, thetechnique can accurately track static distributions in scramjetexhaust flows (shocked or unshocked) R D V

A77-44S18 # Comparative flutter calculations for the Vig-gen aircraft V J E Stark (Saab Scania AB, Lmkopmg, Sweden) andD E Cooley (USAF, Flight Dynamics Laboratory, Wright-PattersonAFB, Ohio) Journal of Aircraft, vol 14, Sept 1977, p 920,921 11refs

Aeroelastic calculations for the canard wing configuration of theSaab-Scania Viggen are discussed, with three-dimensional effects andinterference effects taken into cognizance Linear combinations ofgiven functions of two variables were fitted by the method of leastsquares to measured modal deflections, one combination wasdetermined for each trapezoidal wing panel The given functions areproducts of chordwise and spanwise factors special polynomialswith vanishing 2nd-order and 3rd-order derivatives at free paneledges Discontinuous deflection functions can be employed to obtaincontrol surface deflections This and a variant method producedresults in close agreement While a large flutter margin is predicted,the results apply to zero angle of incidence R D V

A77-44819 # Leading-edge vortex effect on the flutterspeed V J E Stark (Saab-Scania AB, Lmkopmg, Sweden) Journalof Aircraft, vol 14, Sept 1977, p 921,922 7 refs

An approximate method developed by Pines (1958) for predict-ing a reduction in the flutter speed brought about by vortex effects isreconsidered A small flutter frequency is not assumed A correctionfactor devised effected a significant increase in predicted flutterspeed, the flutter speed reduction due to loading-edge vortex effect is

plotted A satisfactory flutter margin is shown to remain in spite ofthe possible reduction brought about by the vortices R D V

A77-44824 # Characteristic time emissions correlations -The T-63 helicopter gas turbine combustor A M Mellor (PurdueUniversity, West Lafayette, Ind ) Journal of Energy, vol 1,July-Aug 1977, p 257-262 11 refs US Environmental ProtectionAgency Grant No R-802650

Gaseous pollutant emissions from conventional diffusion flameT-63 combustors are correlated as functions of combustor geometryand inlet conditions in terms of a characteristic time model Newaspects of the present study show partial inclusion of effects ofalternate fuel properties, suggest a generalization of the LipfertN0(x) correlation, compare advanced film injected and prevaporiz-mg/premixmg with conventional combustors, and demonstrate aquantitative relation between emissions of unburned hydrocarbonsand CO (Author)

A77-44946 * f/ Generalized Theodorsen solution for singularintegral equations of the airfoil class M H Williams (PrincetonUniversity, Princeton, N J ) Quarterly of Applied Mathematics, vol35, July 1977, p 213-224 10 refs Grant No NGR-31-001-197

A class of singular integral equations is considered which arise invarious two-dimensional mixed boundary-value problems with simpleharmonic time variation A problem typical of this class is that ofdetermining the lifting pressure distribution on an oscillating airfoilin an unbounded incompressible potential flow It is shown thatTheodorsen's (1935) solution to this problem, with some modifica-tion, is valid for a general class of unsteady kernel functions Thetechnique employed is to consider an equivalent steady problem andthen show that the unsteady resolvent and unsteady homogeneoussolution can be written directly in terms of the steady solutions anda single frequency-dependent function which reduces to theTheodorsen function for the steady kernel P T H

A77-44957 # ONERA aerodynamic research work on heli-copters J -J Phillippe and C Armand (ONERA, Chatillon-sous-Bagneux, Hauts-de-Seine, France) (NATO, AGARD, Symposium onRotorcraft Design, Moffett Field, Calif, May 16-19, 1977) ONERA,TPno 1977 42E, 1977 20 p 35 refs

Research involving two- or three-dimensional flows and studieson rotors are surveyed Some basic research topics include an airfoilstudy in steady flow, the unsteady performance of airfoils, a bladetip study in steady flow, and a vortex interaction wind tunnelsimulation The principle of the method used for calculation of theforces acting on the rotor is described and applied to the cases of arigid blade rotor and a flexible blade rotor Two rotor test rigs, onelocated in an 8 m wind tunnel, the other located in a 3 m windtunnel, are considered Measuring techniques and results for totalforces on helicopter or convertible, absolute pressures on the blades,identification of the boundary layers, smoke visualizations, androtating blade deformations are examined M L

A77-44959 Technology comes to general aviation FlightInternationa/, vol 112, Aug 27, 1977, p 617-620, 627, 628

The paper reports on various studies being undertaken by NASAfor the development of advanced technology, already available tomodern military aircraft and commercial transports, for the lighteraircraft of general aviation These studies include the supercriticalwing, airframe drag reduction, crashworthmess, spin resistance,turbine engines, quiet propellers,and improved autopilots P T H

A77-45171 # Feasibility demonstration of the earth refer-enced maneuvering flight path display J F Watler, Jr (NorthropCorp, Hawthorne, Calif ) and W G Mulley (U S Naval MaterialCommand, Naval Air Development Center, Warmmster, Pa)American Institute of Aeronautics and Astronautics, Guidance andControl Conference, Hollywood. Fla, Aug 8-10, 1977, Paper77-1114 9p

A description is presented of the maneuvering flight path displayconcept The concept was formulated under Navy sponsorship during

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the period from 1952 to 1963 The concept was developed inresponse _to three basic requirements, including greater aircraftweapon system performance, increased flight safety, and decreasedpilot training The maneuvering flight path display provides bothcommand and actual guidance and control information to the pilotAttention is given to details regarding the development of the flightpath display, a feasibility demonstration, deviations from the flightpath during the landing approach, and pilot workload levels duringthe landing approach G R

A77-45173 Operational reliability and reliability testingMt Prospect, III , Institute of Environmental Sciences, 1977 76 p$600

Reliability standards and reliability testing of avionics com-ponents and aircraft are discussed Topics of the papers includeimplementation of a complete reliability testing program andmodification of inadequate environmental, electronics and vibrationmonitoring, the operational influences on avionics reliability, studiedthrough mathematical modeling and field data, the CombinedEnvironments Reliability Testing (CERT) used by the U S Air ForceFlight Dynamics Laboratory to evaluate components of high-performance aircraft, an analysis of discrepancies between labora-tory-test performance and operational performance of avionicscomponents, criteria for the formulation of adequate vibration tests,the detection of latent defects through vibration testing, and the useof statistical decision theory to assess cost-effective vibroacoustic testplans applied to the Space Shuttle J M B

A77-45387 Nonlinear lifting-surface theory for yawed andbanked wings in ground proximity (Nichthneare Tragflachentheoriefur schiebende und hangende Flugel in Bodennahe) G Binder(Braunschweig, Technische Universitat, Braunschweig, WestGermany) Zeitschrift fur- Flugwissenschaften und Weltraum-forschung, vol 1,July-Aug 1977, p 241-249 24 refs In German

For wings with arbitrary planform in ground proximity, placedat an angle of yaw with respect to the free stream and at an angle ofbank relative to the ground plane, the aerodynamic characteristicsare calculated by means of lifting-surface theory The ground effectis taken into account using the image technique The vortex systemsof the real wing and of the image wing are inclined against theground plane The perturbation velocities induced by the image wingare taken into consideration completely using the methods of KGersten and D Hummel A comparison of the theoretical resultswith experimental data shows that the aerodynamic characteristics ofwings in unsymmetncal flow near the ground are well predicted bythe theory (Author)

A77-45388 The theoretical determination of the basepressure in supersonic flow (Theoretische Bestimmung des Basis-druckes bei Uberschallstromung) M Tanner (AerodynamischeVersuchsanstalt, Gottmgen,. West Germany) Zeitschrift furFlugwissenschaften und Weltraumforschung, vol 1, July Aug 1977,p 249-259 35 refs In German

The reported investigation is concerned with an extension of thetheory for the determination of the base pressure in the case of atwo-dimensional nonpenodic dead water flow developed by Tanner(1972, 1973) The theory in its previous form is only valid forcompressible flows without shock waves The extended theory is totake into consideration also an occurrence of shock waves The basicconcepts of the theory are discussed for two-dimensional flow andfor axisymmetric flow The velocity and density distribution in thewake is examined and the effects of the various factors on the basepressure are considered The results obtained with the aid of the newtheory are found to agree with experimental data in a number ofcases G R

A77-45391 Experience gained in adjusting the mathe-matical model of the VFW 614 short-haul aircraft by use ofmeasured eigenfrequencies (Erfahrungen zur Korrektur desRechenmodells mit gemessenen Eigenfrequenzen am Beispiel desVerkehrsflugzeugs VFW 614) H Zimmerman, D Collmann

(Vereimgte Flugtechnische Werke-Foi^Ker GmbH, Bremen, WestGermany), and H G Natke (Hannover, Technische Universitat,Hanover, West Germany) Zeitschrift fur Flugwissenschaften undWeltraumforschung, vol 1, July-Aug 1977, p 278-285 6 refs InGerman

A procedure is presented which provides a means for adjustingcomputed pharactenstic quantities of natural modes of vibration ofan elastomechamcal structure to fit measured ones By minimizingthe square of the difference between computed and measured kineticenergy an appropriately weighted and normalized expression isderived which contains only measured eigenfrequencies and nomeasured mode shapes, i e , the fit is performed for quantities whichcan be measured very accurately The equations that are used showthat the computed mode shapes are improved at the same time Theprocedure was applied to practical examples in order to gainexperience with it The passenger aircraft VFW 614 especially wassubjected to detailed investigations These showed that the methodmay not be used in the manner of an automatic procedure Inparticular a careful selection and assignment of measured frequenciesis necessary In some cases an iterative repetition of the procedure isrequired (Author)

A77-45460 A tryout of a rigid airship under tropicalconditions (Erprobung eines Pralluftschiffs unter tropischen Bedin-gungen) H -P Barthelt and R Roth (Deutsche Forschungs- undVersuchsanstalt fur Luft- und Raumfahrt, Institut fur Physik derAtmosphare, Oberpfaffenhofen, West Germany) DFVLR-Nachrichten, July 1977, p 852-855 In German

An investigation was conducted concerning the possibility to use-airships for an alleviation of transport problems in developingcountries with a weak infrastructure The investigation included theoperation of an airship in the African states of Ghana and UpperVolta Flights were made between Accra, Kumasi, and OuagadougouThe results of the investigation show that the employment possibili-ties of airships for the solution of transport problems in countrieswith a weak infrastructure are mainly limited by the characteristicsof the airship itself The maintenance of a state of floating in acertain position appears difficult, taking into account the necessityto compensate for environmental effects and changes regarding theairship-related parameters G R

A77-45491 Interactive graphics in aircraft gas turbineengine design E N Nilson (United Technologies Corp , Pratt andWhitney Aircraft Group, East Hartford, Conn ) In Interactivecomputer graphics in engineering. Proceedings of the Winter AnnualMeeting, New York, N Y, December 5-10, 1976 Meeting sponsoredby the American Society of Mechanical Engineers New York,American Society of Mechanical Engineers, 1977, p 58-69 5 ref s

Applications of computer interactive graphics in the design ofaircraft gas turbine engine components are discussed and illustratedLibraries and shared data bases for interactive programs andmodifications of programs, finite-element mappings of turbineblades, forging die lines for fan blades in perspective view, andlongitudinal sections through engines are exhibited as typicaldisplays Drastic reductions in design and development lead time arerecognized as the major driving force in acceptance of interactivegraphics Continuous rotation, zooming, translation, rotation, andperspective in apparent 3D format, allowing see through, exploded,or opaque views, are noted among the advantages of interactivegraphics R D V

A77-45501 # Effects of technology level on V/STOL air-craft S G Kalemans and R A Cea (Grumman Aerospace Corp,Bethpage, N Y ) American Institute of Aeronautics and Astro-nautics, Aircraft Systems and Technology Meeting, Seattle, Wash,Aug 22-24, 1977, Paper 77-1238 5p

Two V/STOL fighter aircraft were postulated for a mid/late-80'sIOC (initial operational capability!, based on low-risk technologyforecasts The larger of the two aircraft represented the upper-middlerange of the Hi-Low spectrum, the smaller aircraft represented the

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low-middle range The effect of variations from the projectedtechnology on aircraft performance were calculated It is shown thatfor a VTOL aircraft, the most critical factors are empty aircraftweight and losses in lift due to remgestion and engme-airframeinterference All other areas of design can be subordinated to thesefactors in the pursuit of a viable aircraft V P

A77-45502 ft Preliminary design and analysis of advancedmilitary transports E A Barber, L W Noggle (Boeing AerospaceCo , Seattle, Wash ), and I H Rettie (USAF, Aeionautical SystemsDiv , Wright-Patterson AFB, Ohio) American Institute of Aero-nautics and Astronautics, Aircraft Systems and Technology Meeting,Seattle, Wash , Aug 32-24, 1977, Paper 77-1224 9 p

Design solutions for a strategic airlift mission of 3600-nmi radiusand 400,000-lb pay load are examined Various design criteria areconsidered, including life cycle cost, direct operating cost and fuelefficiency Emphasis is given to comparisons of various body crosssections A 1985 technology base is established, and the impact ofadvanced technology and design is evaluated The implications ofcommercial commonality with a military transport are discussed

(Author)

A77-45503 ft The timing of technology - Commercial trans-port aircraft. J E Sterner (Boeing Co , Seattle, Wash) AmericanInstitute of Aeronautics and Astronautics, Aircraft Systems andTechnology Meeting, Seattle, Wash, Aug 22-24, 1977, Paper77-1200 17 p

An investigation is conducted of the factors that control theacqusition and the technology of new aircraft, taking into accountthe current situation and the potential of about 100% improvementin passenger miles per gallon over the pre-1970 aircraft It is pointedout that the combination of traffic growth and replacement of theolder, less efficient, and noisier aircraft brings with it opportunity fortechnological infusion Attention is given to the composition of theopen market, the U S aircraft obsolescence situation, the U S cyclicbuying situation, the noise regulation situation, the significance ofnew technology, long-term technological benefits, technology ap-plicable to the next generation, and the magnitude of the nextbuying cycle G R

A77-45505 ff Advanced Technology Wing /ATW/ selectionand design J R Ellis and J L Mans (Vought Corp, Dallas, Tex )American Institute of Aeronautics and Astronautics, Aircraft Sys-tems and Technology Meeting, Seattle, Wash, Aug 22-24, 1977,Paper 77-1210 6p

Two full scale structural wing boxes of advanced design will befabricated and tested in this advanced development program Thedesigns were selected from candidate wing box concepts that wererated for cost, weight, technology improvement, damage tolerance,and the 'abilities' The selected wing concepts are presented anddiscussed Development testing is underway on this program andsignificant tests and test results are reviewed Final wing box designdrawings are scheduled to be released in mid-August 1977 Fabrica-tion of both demonstration articles is scheduled for completion inmid-September 1978 with testing complete by February 1979

(Author)

A77-45506 # Results of a feasibility study to add canardsand ADEN nozzle to the YF-17 H R Wasson. G R Hall (NorthropCorp, Hawthorne, Calif |, and J L Palcza (U S Naval AirPropulsion Test Center, Trenton, N J ) American Institute ofAeronautics and Astronautics, Aircraft Systems and TechnologyMeeting, Seattle, Wash, Aug. 22-24, 1977, Paper 77-1227 10 pContract No N00014-76-C-1411

The paper deals with an aerodynamic analysis and designfeasibility study concerning the addition of canards and the 2 DADEN (augmented deflecting exhaust nozzle) to the YF-17 aircraftThe results of the aerodynamic study showed that addition of theADEN nozzle and canards did little to improve the turn rate andtrimmed lift-drag polars They did provide considerable direct liftcontrol and aircraft pointing capability, as well as increased controland increased pitch rate at low dynamic pressure The design

feasibility study showed that addition of the ADEN nozzle andcanards is readily achievable through structural modifications andmodifications of the aircraft control system (using existing actua-tors) Taking into consideration the structural, weight, and controlsystem requirements, the size of the canards could be reduced to 75ft of included area, making it possible to accommodate the canardwithout increasing the aircraft gross weight significantly and toremain within the stability limits imposed by the modified controlsystem V P.

A77-45507 ft Vectored-engme-over-wing configuration de-sign P D Whitten and R W Woodrey (General Dynamics Corp ,Fort Worth, Tex ) American Institute of Aeronautics and Astro-nautics, Aircraft Systems and Technology Meeting, Seattle, Wash,Aug 22-24, 1977, Paper 77-1228 8p

A Vectored-Engme-Over-Wing (VEO-Wing) aircraft configura-tion designed for an advanced tactical aircraft mission is presentedEngineering data developed for this powered-lift concept illustratesits design features Aircraft performance estimates are presented tomeasure the capability of the concept for the tactical role (Author)

A77-45508 * # Aerodynamics of horizontally-opposed aircraftengine installations S J Miley, E J Cross, Jr, D L Lawrence, andJ K Owens ((Mississippi State University, Mississippi State, Mess )American Institute of Aeronautics and Astronautics, Aircraft Sys-tems and Technology Meeting, Seattle, Wash , Aug 22-24, 1977,Paper 77-1249 10 p 9 refs Grant No NsG-1083

The goal of cooling installation design is to provide adequatecooling air flow to the engine with a minimum drag penalty Toachieve this goal, attention must be given to certain aerodynamicfactors involved in the design problem In the present paper, thefactors which influence the aerodynamic design of horizontally-opposed engine cooling installations are discussed with particularreference to the performance of the aircraft in terms of the dynamicpressure generated for the power output of the engine, the gams orlosses through the propeller, proper inlet design, altitude effects onthe orifice characteristics of the engine, and exit area sizing Resultsof a flight research program showed that the inlet design has asignificant influence on cooling effectiveness and drag, the inletshould be designed for low velocity ratios and should avoid smallradii of curvature in its geometry The influence of the propeller onthe inlet appears to cause the stagnation point on the lip to movetoward the inside V P

A77-45509 fi The use of probability analysis in aircraftcertification and its effects on maintenance and equipment main-tenance J J Treacy (FAA, Seattle, Wash ) American Institute ofAeronautics and Astronautics, Aircraft Systems and TechnologyMeeting, Seattle, Wash , Aug 22-24, 1977, Paper 77-1256 5 p

The paper surveys the procedures, particularly the use ofnumerical probability analysis, which the Federal Aviation Adminis-tration expects to use in finding compliance with Federal AviationRegulation (FAR) 25 1309 as amended by Amendment 25-23. Anew draft of the 'Systems Design Analysis' Advisory Circular is alsodescribed The use of numerical probability analysis in the certifica-tion of the 747 Automatic Ground Rollout System and the 727Automatic Performance Reserve System is reviewed, and main-tenance and reliability requirements are considered M L.

A77-45510 # Compliance with amended FAR 25.1309 -DC-10 case history V Vanakojis (Douglas Aircraft Co , Long Beach,Calif) American Institute of Aeronautics and Astronautics, AircraftSystems and Technology Meeting, Seattle, Wash, Aug 22-24, 1977,Paper 77-1257 6p 5 refs

The Douglas DC-10 Automatic Landing System was certified inaccordance with the requirements of Advisory Circular 120-28,complying with the intent of all requirements of FAR 25 1309 aschanged by Amendment 25-23 The design, analysis, and test of theAutomatic Landing System was impacted by the regulatory agencyinterpretations of these requirements Methods in analysis and testing

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were developed to show compliance with the 'extremely improbable'fault criteria for single and/or multiple failures within the automaticpilot, sensors, and peripheral equipment comprising the AutomaticLanding System The numerical probability analysis was usedextensively to support the overall design and resulted in somereliability requirements and special tests for the Automatic LandingSystem (Author)

A77-45511 ff Control of rare events by aircraft systemdesign regulation - Impact on operations H F Heap, F S Nowlan(United Air Lines, Inc , San Francisco, Calif ), and J L Dolby (SanJose State University, San Jose, Calif ) American Institute ofAeronautics and Astronautics, Aircraft Systems and TechnologyMeeting, Seattle, Wash , Aug 22-24, 1977, Paper 77-1258 B p .

A situation is encountered with certain aircraft systems where itmay be possible for a relatively unlikely sequence of failures to causea loss of the system's function that will have consequences that arecritical to the operating safety of the airplane This paper discussesthe difficulties that the control of rare events by the proposedsystem design regulation would cause operators First, the rationaleof the design incident rate of 10 to the -9th is examined Next, thisnumber is put in perspective by a review of United States air carriersafety statistics Then, maintenance capabilities are reviewed, and thenonproductive activities that these regulations would force on anairplane operator are identified (Author)

A77-45512 # YC-14 flight test results R L McPherson(Boeing Co , Seattle, Wash ) American Institute of Aeronautics andAstronautics, Aircraft Systems and Technology Meeting, Seattle,Wash , Aug 22-24, 1977, Paper 77-1259 8 p 7 refs

Two YC-14 prototypes were built as part of the Air Force'sAdvanced Medium STOL Transport program The flight test programwas conducted by the Joint Test Force comprising The BoeingCompany, the Air Force Flight Test Center, and the Air Force Testand Evaluation Center, with participation by NASA The primarypurpose of the flight test program was to evaluate a unique form ofpowered lift referred to as upper surface blowing (USB) The testprogram began with the first flight on August 9, 1976, and lasted oneyear This paper summarizes the flight test activities by discussing thedevelopment, envelope expansion, and operational use, and empha-sizes the performance and stability and control test results (Author)

A77-45513 # Central integrated test system /CITS/ - Checkthree times K Derbyshire (Rockwell International Corp, LosAngeles, Calif ) American Institute of Aeronautics and Astronautics,Aircraft Systems and Technology Meeting, Seattle, Wash, Aug22-24, 1977, Paper 77-1260 11 p

The highly sophisticated onboard test system described wasdeveloped for the B-1 aircraft Its implementation is based on the useof an onboard digital computer and a stored real-time softwareprogram to control the data acquisition, data processing, and datadiscrimination operations for performing the B-1 aircraft tests Thesystem automatically and continuously tests the operability of theaircraft subsystems, the basic approach involves making a preprogrammed decision based on the outcome of a specific test In thenonavionics computer program, over 4000 fully automatic tests areperformed each second The system has the capability to output,display, and record in excess of 1250 malfunction codes that providefault detection/isolation information for over 1000 nonavionicsLRU's (Line Replaceable Units) The present stage of developmentof the test system, the implementation and verification of thehardware and software, flight test utilization, and the planned use ofthe CITS in an operational environment are discussed V P

A77-45524 Active control technology A Simpson (Bris-tol, University, Bristol, England) and H P Y Hitch (British AircraftCorp, Weybndge, Surrey, England) Aeronautical Journal, vol 81,June 1977, p 231-246 35 refs

Active Control Technology (ACT), defined as the use ofconventional single-output feedback control systems in a multi-input.

multi output role to improve aircraft performance and decreaseoverall cost, is discussed Aspects of ACT as applied to fixed-wingcraft, including aerodynamic stability requirements, ride improve-ment, internal load distribution, gust load alleviation, flutter speedenhancement, center of gravity control, envelope limiting and fatiguereduction, are considered ACT functions as applied to rotorcraft,including mechanical linkages between the pilot control and thecyclic pitch-producing mechanisms, as well as longitudinal andlatitudinal controls, are also mentioned Advances in ACT, such asthe development of multivanable multi input adaptive controls, theuse of redundant (e g, quadruplex) design to achieve systemreliability, and the introduction of digital computers, miniaturizedelectronics and electrohydrauhc valves, are reviewed Research intothe aerodynamics of unusual surfaces, the aerodynamics of conven-tional controls operating at high frequencies, and mathematicalmodeling of the compatibility of ACT functions is suggested J M B

A77-45525 The measurement of performance, stabilityand control characteristics of a high subsonic jet aircraft innon-steady flight conditions employing high accuracy instrumenta-tion techniques J A Mulder (Delft, Techmsche Hogeschool, Delft,Netherlands) Aeronautical Journal, vol 81, June 1977, p 24725815 refs

A77-45719 Validation of an airport simulation model. JF Gilsinn (National Bureau of Standards, Applied Mathematics Div ,Washington, DC) In Winter Simulation Conference, 8th, Gaithers-burg, Md, December 6-8, 1976, Proceedings Volume 1

New York, Institute of Electrical and ElectronicsEngineers, Inc , 1976, p 273-277 8 refs

This paper describes the validation of an airport simulationmodel, called DELCAP for DELay CAPacity, the two quantitieswhich it measures, for use in estimating the traffic rates attainable atmajor busy U S airports The simulation model outputs arecompared to those of other models for simple cases to which bothapply and to actual throughput data for several airports, withdifferences usually less than 6 to 8 percent (Author)

A77-45871 ECM methods for aircraft engine manufactureG R Dearth (General Electric Co , Fairfield, Conn ) Society ofManufacturing Engineers, Paper MR76-705, 1976 19 p

Production-tested applications of electrochemical machining tothe manufacture of aviation engine system parts, in bulk removal andin shaping of hard-to machine materials, are reviewed brieflyDefinitions are presented for electrochemical machining, electro-chemical (electrolytic) grinding, shaped tube electrolytic machining,electrostream |et impingement techniques, and static electrochemicalmachining, and their optimum applications are mentioned Require-ments for proper and economic utilization of electrochemical metalremoval operations are stated R D V

A77-45925 Fuel conservation through airplane main-tenance Exxon Air World, vol 29, no 3, 1977, p 64-69

Maintenance (or restoration) of an aerodynamically cleanaircraft surface and its payoff in minimizing drag, andconcomitantlycontributing to holding fuel cost increases down, are discussedOut-of-flush rivet heads and seals, skin joints protruding into theairflow, leaks, door misalignment, rough skin patches, and dents canadd to drag and result in fuel burn penalties While contributionsfrom any of these factors may be minimal, they can add up andinteract Fuel burn penalties are figured against maintenance/repaircosts for many such items, and accounting experience shows sizablesavings through maintenance of aerodynamic cleanness The 'top ten'drag-enhancing and fuel-penalty problems are listed, and somerepresentative irregularities are illustrated R D V

A77-46136 * The computer for design and optimization GN Vanderplaats (NASA, Ames Research Center, Moffett Field,Calif ) In Computing in applied mechanics. Proceedings of theWinter Annual Meeting, New York, NY, December 5-10, 1976

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New York, American Society of MechanicalEngineers, 1976, p 25-48 69 refs

Computerized design using numerical optimization techniques isdiscussed and guidelines for writing analysis computer codes that canbe readily coupled to optimization codes are presented Thefollowing numerical optimization techniques are examined randomsearch, sequential unconstrained minimization, direct constrainedoptimization, and one-dimensional search A number of designapplications are considered including high speed airfoil lift maximiza-tion, the preliminary design of a wing, design of a planar tower foroptimal geometry, and the conceptual design of a tactical fighteraircraft B J

A77-46262 Stereographtc projections in air traffic controlsystems E D Gmgench (Raytheon Co , Goleta, Calif ) Navigation,vol 24, Summer 1977, p 95-101 5 refs

The mathematical technique chosen to present targets frommany radars on a single two-dimensional plane is discussed Defini-tions and orientations with respect to longitudes, latitudes, andmathematical coordinate systems are contained in Section 2Supporting diagrams are also included The derivation of projectionequations from earth points to coordinates in the stereographicplane, and the rotation of radar azimuth into the systems plane tocompensate for the varying orientation of North in different radarplanes, and the derivation of the equations for mapping a radar targetfrom a radar plane to a systems plane are presented (Author)

A77-46263 * A digital goniometer for VOR S A Meer(NASA, Goddard Space Flight Center, Greenbelt, Md ) Navigation.vol 24, Summer 1977, p 102111 6 refs

A new VOR (VHP omnirange) goniometer design whichpromises to improve the reliability and maintainability of the VORground stacion is described The heart of the new concept is the useof two digital phase shifters to produce the rotating figure-of-eightpattern of conventional VOR Using digital circuits, the goniometeradjustments and calibration reduce to timing adjustments of binarysignals A common clock used for timing the digital phase shiftersalso synchronizes the 30 Hz modulation of the 9 96 kHz reference

(Author)

A77-46264 RNAV control for airborne surveys A NFhor (NOAA, National Ocean Survey, Rockville, Md ) (Institute ofNavigation, Annual Meeting, 31st, Washington, D C, June 24, 1975)Navigation, vol 24, Summer 1977, p 132-141 7 refs

This paper describes the theory, development, and use of aComputer Generated Area Navigation (RNAV) Waypomt GridSystem for airborne surveys Control for these surveys is provided byaircraft equipment utilizing the VOR/DME navigation facilities ofthe National Airspace System Bearings and distances (waypomts)from existing facilities are generated by a computer program usingcoordinate search and geodetic computation techniques from anavigation facility data base The resultant waypomt grid data, in aform easily used in the aircraft's RNAV equipment, providesaccurate position and guidance information for the survey (Author)

A77-46348 # Numerical modeling of helicopter piloting(Modelowame pilotazu smiglowca metoda numeryczna) KSzumanski lnstytutLotnictwa.Prace.no 67, 1976, p 3-32 10 refsIn Polish

An approach to digital simulation of helicopter piloting andhelicopter maneuvers is worked out in detail Time intervals aresubdivided into narrower and narrower slices, with the helicopterequations corrected for each successive step, so that data describingthe maneuver can be acquired without violating maneuver con-straints A model of helicopter dynamics in unsteady flight iselaborated and characteristics of subumts of the digital model aredescribed Several subroutines are discussed, for dealing with powerrequirements in unsteady flight conditions, lift rotor drive, systemequlibnum, narrowing the grid mesh, pilot-machine interaction, anillustrative example is discussed. R D V

A77-46349 tf Static electricity in aviation and way« ofaverting its effects (Efektrycznosc rtatyczna w lotnictwie orazsposoby zabezpieczema przed je] skutkami) K Zuchowicz InstytutLotn/ctwa, Prace, no 67, 1976, p 33-46 17 refs In Polish

Effects of static electricity on aircraft in flight are reviewedCharging mechanisms (via self-charging or induction) and modes ofdischarge (corona, spark, ribbon), static electricity effects on thefunctioning of electronic on-board equipment, and ways of copingwith accumulation of static charges are discussed Devices fordischarging static electricity and optimum placement of such devices *at strategic points on the fuselage are described R D V

A77-46401 Gas turbines - Status and prospects. Proceed-ings of the Symposium, London, England, February 4, 5, 1976.Symposium sponsored by the Institution of Mechanical EngineersLondon and New York, Mechanical Engineering Publications, Ltd (IMech E Conference Publications, No 1976-1), 1976 164 p $27

Aspects of gas turbine evolution are considered along with thestatus and the prospects of the aircraft gas turbine, the design of gasturbines for the industrial and the marine field, the airline viewpoint,gas turbines in the RAF from a maintenance engineering viewpoint,the Royal Navy's experience with main propulsion gas turbines, thestatus and prospects of the industrial gas turbine, and the designer'sdilemma with unmanned controls and the gas turbine user Attentionis also given to a new maintenance concept applied in the design of anew industrial gas turbine in the 100 MW class, experience with gasturbines in the field by a British petroleum company, gas turbines ina powered distribution system, monitoring for preventive main-tenance in the small fleet, gas turbine power for large hovercraft, andthe gas turbine in the gas transmission environment G R

A77-46403 The aircraft gas turbine - Status and prospectsR M Denning and T Jordan (Rolls-Royce /1971/, Ltd , BristolEngine Div , Bristol, England) In Gas turbines - Status andprospects. Proceedings of the Symposium, London, England,February 4, 5, 1976 London and New York,Mechanical Engineering Publications, Ltd , 1976, p 17-26.

A review is conducted of the effects of the evolution of the gasturbine on subsonic transport aircraft Future improvements in fueleconomy are considered, taking into account propulsive efficiencychanges, gas producer thermal efficiency changes, and componentefficiency improvements Aspects of aero-mechanical design for lowcost and weight are considered along with environmental factors inengine design, questions of maintenance and reliability, conditionmonitoring, and turbine blade life G R

A77-46405 The airline viewpoint C B Redgate (BritishAirways, Overseas Div , London, England) In Gas turbines - Statusand prospects. Proceedings of the Symposium, London, England,February 4, 5, 1976 London and New York,Mechanical Engineering Publications, Ltd , 1976, p 35-48

A description is presented of the lines of action taken by aBritish airline to reduce operating costs and improve safetystandards Attention is given to maintenance considerations, aspectsof reliability, questions of maintainability, and engine maintenancecost Details of engine health monitoring are discussed, taking intoaccount visual external inspections, internal inspection by borescope,X-ray and isotope techniques, ultrasonic and eddy current tech-niques, oil systems monitoring, flight deck instrument monitoring,engine performance trend plotting, and airborne integrated datasystems G R

A77-46406 Gas turbines in the RAF from a maintenanceengineering viewpoint W H Dainty (RAF, London, England) InGas turbines - Status and prospects, Proceedings of the Symposium,London, England, February 4, 5, 1976 Londonand New York, Mechanical Engineering Publications, Ltd, 1976, p49-55

The current size and cost of the RAF aircraft gas turbine fleet isreviewed against the background of the military operational and

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environmental requirements Developments leading to improvementsin performance, and trends in reliability and overhaul life arereviewed The latest approaches to the adoption of new maintenancepolicies and engine fleet management are described, following anexamination of the economics of military operations, in the light ofincreasing operating and maintenance costs The potential for furthereconomies is shown to be greatly enhanced by adopting newmaintenance concepts made possible by EHM techniques and thelatest breed of modular gas turbines (Author)

A77-46411 Monitoring for preventive maintenance in thesmall fleet D C Johnson and D Dickinson (British Airways, Barry,Wales) In Gas turbines - Status and prospects, Proceedings of theSymposium, London, England, February 4, 5, 1976

London and New York, Mechanical EngineeringPublications, Ltd , 1976, p 105-115

The performance of gas turbine engines in service can bemonitored with a view to failure prevention using relatively simpleand inexpensive techniques readily available to the small fleetoperator A description of important parameters to be monitoredand how this may be achieved is given Application of monitoringprogrammes to two current engines is described and the improve-ments in the reliability and economics illustrated (Author)

A77-46412 Gas turbine power for large hovercraft P AYerbury (British Rail Hovercraft, Ltd , Dover, England) In Gasturbines - Status and prospects. Proceedings of the Symposium,London, England, February 4, 5, 1976 Londonand New York, Mechanical Engineering Publications, Ltd , 1976, p117-124

Economic competition considerations related to ships determinethe overall cost levels which are acceptable for hovercraft and, inturn, the proportion that can be allocated to the power unit In thisconnection, ultimate gas turbine performance may have to besacrificed to a certain extent to obtain the appropriate economicconditions The selection of a gas turbine for a craft employed on theDover to Boulogne cross-channel route is discussed along with certaindifficulties related to corrosion attack Approaches used to overcomethe initial problems are discussed Attention is given to hovercraft gasturbine requirements and the importance of air filtration, gas turbinedesign modifications, corrosion resistance within the engine, the partplayed by the operator, the life development program, and financialconsiderations G R

A77-46494 # The design of complex navigation systems(Proektirovame slozhnykh navigatsionnykh sistem) L Ts LipchinMoscow, Izdatel'stvo Mashmostroenie, 1976 176 p 79 refs InRussian

Theoretical and technological aspects of the design and fabrication of airborne navigation systems are covered Operating principles,analysis of the design of navigational computing systems, require-ments and specifications, optimized design and production, toleranceassignments and cost control, and testing and checkout are discussedat length Some examples and specification passages are cited by wayof illustration R D V

A77-46508 H Process development for fabricating sculptureddecorative interior aircraft panels using sheet molding compounds GS Kobayashi and E R Pelton (Boeing Co, Seattle, Wash) InDiscover reinforced plastics, Proceedings of the Thirty-secondAnnual Conference, Washington, D C, February 8-11, 1977

New York, Society of the Plastics Industry, Inc , 1977,p 2-A-1 to 2-A-9

A77-46516 # Composite tanks for aerospace vehicle applica-tion R E Landes and E E Morris (Structural CompositesIndustries, Inc. Azusa, Calif) In Discover reinforced plastics.Proceedings of the Thirty-second Annual Conference, Washington,DC, February 8-11, 1977 New York, Societyof the Plastics Industry, Inc, 1977, p 11-B-1 to 11-B-10

Pressure vessels fabricated from Kevlar/stamless steel and Kev-lar/alummum composites were subjected to fatigue cycling, sustainedloading and hydrostatic burst tests to determine their suitability foruse in aerospace vehicles Six 61-cm Kevlar/cryoformed stainless steeltanks and six 97-cm Kevlar/alummum tanks were involved in thetesting The Kevlar/stamless steel vessels, which exhibited very highpressure resistance, also provide a 25 to 30% weight saving overcomparable- noncomposite titanium vessels Both the Kevlar/stamlesssteel and Kevlar/alummum sphere designs demonstrated nonfrag-mentation and controlled-failure features, when failure was inducedduring pressure cycling, localized noncatastrophic leakage wasobserved J M B

A77-46519 *' Composite horizontal stabilizer for the B-1 -Design, fabrication and test W Ludwig, H Erbacher, and G Lubin(Grumman Corp , Bethpage, N Y ) In Discover reinforced plastics.Proceedings of the Thirty-second Annual Conference, Washington,D C , February 8-11, 1977 New York, Societyof the Plastics Industry, Inc , 1977, p 15-B-1 to 15-B-9

The composite design for the stabilizer was developed to satisfyall of the form, fit and functional requirements of the B-1 aircraftand to be competitive with the metal stabilizer on both a weight andproduction cost basis • Actual weights of the composite stabilizershow a 15% savings for the total stabilizer and 21% for the compositetorque box over the existing metal configuration Cost savings of 17to 20% are estimated in production The design that evolved fromthis effort, the test data generated to validate the concept, thefabrication procedures used and production cost comparisons arepresented (Author)

A77-46520 * # Composite hubs for low cost turbine enginesC C Charms (NASA, Lewis Research Center, Cleveland, Ohio) InDiscover reinforced plastics, Proceedings of the Thirty-secondAnnual Conference, Washington, DC, February 8-11, 1977

New York, Society of the Plastics Industry, Inc , 1977,p 15-C-1 to 15-C-7 5 refs

A detailed stress analysis is performed using NASTRAN todemonstrate theoretically the adequacy of composite hubs for lowcost turbine engine applications The results show that compositehubs are adequate for this application from the steady state stressviewpoint (Author)

A77-46575 F-18 Diends advanced fighter concepts D EFink Aviation Week and Space Technology, vol 107, Sept 5, 1977,p 38-41,43

The article presents the advanced concepts being developed forthe F-18 Hornet fighter aircraft for use by the Navy and MarineCorps A comparison is made between the F-18 and the YF-17,highlighting those characteristics of the F 18 which make itparticularly suitable for carriers Descriptions of several otherfeatures of the F-18 are discussed including the accessibility of thecannon and ammunition drum, the possibility of quick enginechanges, and the F404 twin turbojet engines The fuel system isdescribed in terms of its basic operation, aerial refueling, and thematerials of its construction The flight control system is fullydiscussed including a description of the cockpit layout, computersystem, and safety devices S C S

A77-46606 ;; The arrow wing - Its potentialities and draw-backs with regard to m-flight aerodynamic research J E Chacksfteld(British Aircraft Corp, Ltd, Military Aircraft Div , Warton Aero-drome, Lanes, England) Aircraft Engineering, vol 49, Aug 1977, p4-8

A description of the features involved in a new integrated designfor the optimization of the arrow wing planform is presented Thesemodifications include the revision of the shape of the pure wing, andaerodynamic features such as L/D optimization, the addition of LEflaps and the attainment of near-scale Reynolds numbers for thewing section, planform variations, the nacelle location, wing-nacelleinterference, and wing-fuselage interaction The features of this new

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design which are dependent on the aircraft's overall structure arereviewed A list of the factors requiring comprehensive subsonic andsupersonic in flight research is included S C S

A77-46614 * H Computational methods to obtain timeoptimal let engine control R J Basso and R J Leake (Notre Dame,University, Notre Dame, Ind.) In Annual Allerton Conference onCircuit and System Theory, 14th, Monticello, III , September29-October 1, 1976, Proceedings. Urbana, III.,University of Illinois, 1976, p 652-661 10 refs Grant NoNsG-3048

Dynamic Programming and the Fletcher-Reeves ConjugateGradient Method are two existing methods which can be applied tosolve a general class of unconstrained fixed time, free right endoptimal control problems New techniques are developed to adaptthese methods to solve a time optimal control problem with statevariable and control constraints. Specifically, they are applied tocompute a time optimal control for a jet engine control problem

(Author)

A77-46617 fj Singular perturbation analysis approach forsystems with highly coupled dynamics. A J Calise (DynamicsResearch Corp , Wilmington, Mass) In Annual Allerton Conferenceon Circuit and System Theory, 14th, Monticello, III, September29-October 1, 1976, Proceedings Urbana, III,University of Illinois, 1976, p. 793-806 15 refs

This paper proposes a procedure for applying singular perturba-tion methods to separately analyze state dynamics even when theyare highly coupled The intent is to expand the family of problems towhich these methods can be successfully applied In particular severalproblems in flight mechanics are identified Numerical results for theminimum time to climb problem are given where the procedure isused to separate altitude and flight path angle dynamics to produce aclosed-form solution for lift (Author)

A77-46618 * ,7 Characteristics of the boundary-layer equa-tions of the minimum time-to-climb problem M D Ardema (NASA,Ames Research Center, Moffett Field, Calif) In Annual AllertonConference on Circuit and System Theory, 14th, Monticello, III ,September 29-October 1, 1976, ProceedingsUrbana, III , University of Illinois, 1976, p 807-817 7 refs

In many singular perturbation solutions of optimal controlproblems, the most difficult numerical task is to solve the boundary-layer equations However, these equations have a special structurethat may often be used to expedite their solution This paper beginsby noting the general nature of the boundary-layer equations foroptimal control problems These results are then applied to theaircraft minimum time-to-climb problem A specific numericalexample is considered to illustrate the characteristics of the solutionof the boundary-layer equations for this problem (Author)

A77-46621 * ~ Linear regulator design for stochastic systemsby a multiple time scales method D Teneketzis and N R Sandell,Jr (MIT, Cambridge, Mass) In Annual Allerton Conference onCircuit and System Theory, 14th, Monticello, III , September29-October 1, 1976, Proceedings Urbana, III ,University of Illinois, 1976, p 860-874 32 refs. Grant NoNGL-22-009-124, Contract No E(49-18)-2087

This paper develops a hierarchically-structured, suboptimalcontroller for a linear stochastic system composed of fast and slowsubsystems It is proved that the controller is optimal in the limit asthe separation of time scales of the subsystems becomes infinite Themethodology is illustrated by design of a controller to suppress thephugoid and short period modes of the longitudinal dynamics of theF-8 aircraft (Author)

A77-46630 Satellite communications for the mobileservice W Luksch (ESA, Paris, France) In New themes for spaceMankind's future needs and aspirations, Proceedings of the Bi-centennial Space Symposium, Washington, D C , October 6-8, 1976.

San Diego, Calif, American AstronauticalSociety, 1977, p 45-58 (AAS 76-045)

The paper discusses the current and future use of satellites forthe mobile communications service Starting with the currentsatellites produced for the maritime and aeronautical services (withparticular reference to the two programs in which the EuropeanSpace Agency is involved - Marots and Aerosat), the paper proceedsto discuss possible future growth in this field and analysis near-termdevelopments in maritime and aeronautical communications, in-cluding the prospects for a possible integration of the two servicesThe sparingly studied subject of the use of satellites for land mobileapplications is analyzed with attention to institutional and regulatoryproblems which may be anticipated The paper concludes with anoverview analysis of the future of all types of satellite communica-tion service to mobile platforms (Author)

A77-46801 It A-7 titanium nose gear development S HYarbrough (Vought Corp , Dallas, Tex ) Society for ExperimentalStress Analysis, Spring Meeting, Dal/as, Tex, May 15-20, 1977,Paper. 23 p

An investigation of the A-7 aircraft nose gear failures, togetherwith a history of galvanic corrosion on the wear surfaces and stresscorrosion cracks in the housing forging plane led to a program for theredesign and testing of the nose gear shock strut components,substituting titanium for previously used critical aluminum housingsThe original design and testing of the nose landing gear assembly isreviewed along with its service history The redesign trade study andseveral tests are described including the wear test program, staticand fatigue tests, second fatigue and wear tests, the first drop testseries, carrier suitability tests, test bearing pressures, and flighttesting It is concluded that the A-7 titanium gear has proven aneffective substitute for the original aluminum gear, and that itsincreased cost and weight are justified S C S

A77-46805 fi Flutter-suppression studies on an actively con-trolled variable-geometry wind-tunnel model. R Stearman, J Long(Texas, University, Austin, Tex ), and L Lehman (Stanford Univer-sity, Stanford, Calif) Society for Experimental Stress Analysis,Spring Meeting, Dal/as, Tex , May 15-20, 1977, Paper 46 p 7 refsUSAF-supported research

Active flutter suppression design concepts proposed for avariable-geometry aircraft were studied for cases in which a seriousdegradation in flutter margin occurs when the wing of the aircraft isswept into the vicinity of the tail An effective flutter suppressionmechanism was first identified on a simple low-cost semirigidwind-tunnel flutter model of this configuration The preliminarystudies led to the design and wind tunnel testing of a moresophisticated aeroelastic flutter model of this basic geometryExperiments on the more sophisticated model confirmed that fluttermargins could be significantly improved by employing rapidly-responding aerodynamic controls activated by optimal feedback

(Author)

•

A77-46807 § Aircraft composite primary structures inBrazil H W Smith (Kansas, University, Lawrence, Kan ) Society forExperimental Stress Analysis, Spring Meeting, Dallas, Tex, May15-20, 1977, Paper. 17 p 12 refs

A variety of glass fiber and resin combinations were used tomake tension and fatigue specimens A trapezoidal component wasalso manufactured, instrumented and tested Foil type strain gagesand dial gages were used as primary sensors Load cells were alsoused The component was a hollow trapezoidal cantilever, rigidlysupported at the root and loaded at the free end Data is reported forthe pure flexure and pure torsion tests, and for the destruction testin bending Specimens cut from the broken component were testedin tension and compression Derived values of strength and modulusof elasticity are reported Unidirectionally reinforced specimens hadthe highest values of stress and modulus (2800 kg/sq cm and 160,000kg/sq cm) and the random mat composites had the lowest values(941 kg/sq cm and 91,000 kg/sq cm) (Author)

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A77-46808 H Durability testing of the A-7D compositeouter-wing panel E G Smith, J H Pimm, and J F Mall (VoughtCorp , Dallas, Tex ) Society for Experimental Stress Analysis, SpringMeeting. Dallas, Tex , May 15-20, 1977, Paper 29 p

The purpose of the reported test program was to increaseconfidence in the use of composite material and to qualify the outerpanel for unrestricted flight The outer-wing tested consists of astructurally complete left-hand outer panel The outer wing panel hasa span of 96 inches The main wing box structure of the outer panelis constructed of advanced composite materials Attention is given toa description of the test article, the test plan, the durability (fatigue)test, environmental conditioning, fatigue cycling, an elevated temper-ature fatigue test, and a residual strength test G R

A77-46825 ff Investigation of landing gear deck obstructioneffects by drop testing J E Evans (Vought Corp, Dallas, Tex )Society for Experimental Stress Analysis, Spring Meeting, Da/las,Tex , May 15-20, 1977. Paper 9 p

A unique drop test facility has been designed to simulate thecarrier deck environment during high speed landings of carrier-basedaircraft This paper reviews the criteria used in the Navy S-3A landinggear design and discusses laboratory tests conducted to determine thedeck obstruction effects on landing gear loads Data gathered duringsubsequent flight testing at NATC, Maryland, is compared with thatobtained in the laboratory (Author)

A77-46838 # Accelerated environmental conditioning of theA-7D composite outer wing G Bourland (Vought Corp, Dallas,Tex ) Society for Experimental Stress Analysis, Spring Meeting,Dallas, Tex, May 15-20, 1977, Paper 13 p Contract NoF33615-73-C-5066

The environmental conditioning used to simulate long-termmoisture and temperature effects on an advanced-composite outer-wing assembly for the A-7D aircraft is described Structural featuresof the outerwmg assembly, which consists primarily of a graphite/epoxy substructure and a graphite/boron/epoxy hybrid skin, arediscussed, estimates of the seven-year moisture absorption inlaminates of various thicknesses are determined on the basis of35-day conditioning at a temperature of 150 F and 100% relativehumidity Fatigue and residual strength tests performed after theenvironmental conditioning are used to assess the operationaldurability of the assembly over seven years of land-based service

JM B

A77-46848 ff Variable geometry air cycle machine J Tseka(United Technologies Corp , Hamilton Standard Div , Windsor Locks,Conn ) and G C Letton, Jr (USAF, Aeronautical Systems Div ,Wright-Patterson AFB, Ohio) ASME, SAE, AIAA, ASMA, andAlChE, Intersociety Conference on Environmental Systems, 7th, SanFrancisco, Calif, July 11-14. 1977, ASME Paper 77-ENAs-7. 9 pMembers, $1 50, nonmembers, $3 00 >

There is a continuing need to develop environmental controlsystem (ECS) concepts which give increased performance or reduceaircraft penalties Use of a variable-geometry air cycle machine is oneapproach for achieving improved ECS performance over a wide rangeof operational conditions with less overall aircraft penalty Aprogram to develop an Advanced Environmental Control System(AECS) has resulted in the development of a variable-geometrybootstrap air cycle machine which includes both a variable-geometryturbine nozzle and compressor diffuser The reasons for selecting avariable-geometry air cycle machine and its impact on AECS weightand engine bleed air consumption are discussed This paper showshow single-acting movable turbine nozzle and compressor diffuservanes were implemented in the bootstrap air cycle machine toachieve desired efficiencies over flow ranges of 4 1, which is twicethat achievable by existing state-of-the-art air cycle machines Thevariable-geometry air cycle machine underwent a flight-worthinesstest program Included are discussions on performance levelsachieved and mechanical acceptability of the design (Author)

A77-46849 ft A comparison of ECS controls G T Puhl(USAF, Flight Dynamics Laboratory, Wright-Patterson AFB, Ohio)ASME, SAE, AIAA, ASMA, and AlChE, Intersociety Conference onEnvironmental Systems, 7th, San Francisco, Calif .July 11-14, 1977,ASME Paper 77-ENAs-8 20 p 12 refs Members, $1 50, non-members, $3 00

The study presented in this paper consists of a comparison ofthe conventional control implementation, fluidic control imple-mentation developed under contract by the AFFDL, and hypo-thetical digital electronic control implementations in non-redundantand dual-redundant configurations for an F-4 Aircraft Cabin-AirConditioning System The Cabin-Air Conditioning System of the F-4Aircraft was selected as the baseline system due to the availability ofdata for this system and the contractually developed fluidic controlimplementation for a comparable system The digital electroniccontrol model of this study was assumed to employ sensors andactuators in an identical manner to the fluidic control implementa-tion for the purpose of providing a direct comparison The differentcontrol implementations are compared on the basis of performance,control reliability, relative production and maintenance costs, andsurvivability and adaptability (Author)

A77-46851 ff A rotating high pressure water condenser andseparator J W Crawford (USAF, Flight Dynamics Laboratory,Wright-Patterson AFB, Ohio) ASME, SAE. AIAA, ASMA, andAlChE, Intersociety Conference on Environmental Systems, 7th, SanFrancisco, Calif. July 11-14, 1977, ASME Paper 77-ENAs-10 14 p.5 refs Members, $1 50, nonmembers, $3 00 Contract NoF33615-74-C-3039

A new concept has been developed to remove water from thebleed air stream of an aircraft Advanced Environmental ControlSystem (AECS) The new concept is a rotating high pressurecondenser and water separator The water separator is rotated by anelectric motor to provide a radial centrifugal force on the condensedwater droplets to move them to a collection volume where they areexpelled The rotation also provides a uniform fin matrix tempera-ture by causing periodic movement of the matrix between the coldside inlet and outlet Finally, rotation provides self-cleaning of anysnow particles that come from the upstream turbine by reversing theflow direction over the matrix each revolution Design rationale,performance test results as a component and as part of the systemand component structural and environmental qualification testresults will be presented An overview of the AECS including thefunction of the water separator in the system will be presented

(Author)

A77-46904 ff Design-to-cost in action R L Bidwell (USDepartment of Defense, Product Engineering Services Office, Alex-andria, Va ) American Society of Mechanical Engineers, DesignEngineering Conference and Show, Chicago, III, May 9-12, 1977,Paper 77-DE-9 8 p Members, $1 50, nonmembers, $3 00

The design-to-cost management philosophy instituted by theU S Department of Defense to analyze and control cost overrunsincurred by contractors is discussed Case histories involving suc-cesses and failures in obtaining adequate product cost estimates fromdefense contractors and subcontractors during the design phase aregiven, and a detailed set of criteria for evaluating the acceptability ofa contractor's design-to-cost program is provided. Emphasis is placedon identifying and controlling the most costly elements in a design,incorporating production and support costs into design-phase esti-mates and expressing costs in terms of man-hours of production andmaterial costs J M B

A77-46915 ff Fatigue life prediction of complex structuresB N Leis (Battelle Columbus Laboratories, Columbus, Ohio)American Society of Mechanical Engineers, Design EngineeringConference and Show, Chicago, III, May 9-12, 1977, Paper 77-DE-46 8 p 52 refs Members, $1 50, nonmembers, S3 00 USAF-sponsored research

Analytical procedures for predicting finite-fatigue life for simplenotched coupons are reviewed One problem in adapting these

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procedures to making life predictions for complex components andstructures is that of the multiplicity of crack initiation sites andmechanisms which determine the fatigue life of such structures Ithas been observed that the service environment and the magnitudeand character of the service loading are responsible for determiningwhich of the many potential initiation sites and mechanisms controlfailures This paper examines available technology for fatigue analysisof complex structures in which the multiplicity of initiation sites andmechanisms control the life of the structure It was concluded thatthose techniques most likely to yield accurate predictions were basedon the critical location concept Complexities in the use of thisconcept in fatigue analysis are defined and the concept is illustratedby application to the fatigue analysis of a component configurationwhich simulates a joint in an airframe Finally, the use of the criticallocation concept as an aid to understanding the mechanisms offatigue improvement fasteners is discussed. (Author)

A77-46975 The Mirage-2000 (Le Mirage 2000) J.Monsset Air et Cosmos, vol 15, May 21, 1977, p 27-29, 31, 33 InFrench

The Mirage-2000, scheduled for test flight in October, 1978, isdescribed Choice of the delta wing configuration and the aero-dynamic analyses and design programs leading to development of theaircraft are reviewed, the hydraulic servocommand system, radar,autopilot and data processing system chosen for the plane are alsoconsidered Use of boron and carbon-fiber composites to reduceweight and retractable wing components to provide versatile per-formance is discussed The propulsion system, which renders theMirage 2000 capable of high-altitude flight at speeds of Mach 2 3 to2 5, is described Data on acceleration, payload and fuel capacity,range and operational altitude ceiling of the aircraft are also given Inaddition, aspects of the landing gear, including the graphite hybridbrakes and electrohydraulic controls, are mentioned J M B

A77-46984 ff Increasing jet-engine thrust by water-augmentation (Povysheme tiagi vozdushno-reaktivnogo dvigateliaputem ballastirovamia strui zabortnoi vodoi) I M Chernyi and A IKravtseva (Akademna Nauk Ukramskoi SSR, Institut Gidromekaniki,Kiev, Ukrainian SSR) Gidromekhanika, no 36, 1977, p 41-46 5refs In Russian

The feasibility of using water-augmented air jets for thepropulsion of high-speed vessels is analyzed A solution is obtainedwith allowance for losses in the inlet main and atomizer, for theresistance of the water intake mechanism, and for the mixing lossesin the nozzle The gam resulting from water-augmentation iscomputed V P

A77-47005 Upstream influence on the near field of aplane turbulent jet A K M F Hussain and A R Clark (Houston,University, Houston, Tex ) Physics of Fluids, vol 20, Sept 1977, p

I 1416-1426 47 refs NSF Grant No GK-32626, Contract NoIM00014-68-A-0402-0008

Experiments investigating the effects of the mean and turbu-lence characteristics of the upstream boundary layer on the evolutionof the flow in the near field of a plane jet for four initial conditionsare described The study was carried out for two asymptotic initialmean velocity profiles, i e , the laminar 'top-hat' profile and the fullydeveloped turbulent profile For the latter case, the flow is vortical,while for the initially laminar cases, two free shear layers of oppositevorticity grow separately and merge downstream The growth rate oflongitudinal turbulence intensity and the mass flux are higher whenthe initial boundary layer is laminar than when turbulent B J

A77-47090 i An optical technique for measuring vibratorymotion in rotating machinery F Bien and M Camac (AerodyneResearch, Inc. Bedford, Mass) AIAA Journal, vol 15, Sept. 1977,p 1257-1260 7 refs Research sponsored by the Aerodyne Research,Inc

A method to measure the frequency and amplitude of vibrationin a rotating element is presented Using optical interferometric

techniques, the flexure and torsion of a gas turbine compressor bladeis shown to be measurable over the entire 360 deg of rotationVibrations are shown to be measurable independent of blade rotationspeed, the effects of misalignment in system are shown to be small.Angular deflections from 0 5 to 500 mrad were measured in the testsystem (Author)

A77-47108 * # Flow characteristics in an expansion tunnel asinferred from velocity measurements C G Miller and W J Friesen(NASA, Langley Research Center, Space Systems Div , Hampton,Va ) AIAA Journal, vol 15, Sept 1977, p 1364-1366 6 refs

A photoiomzation technique was used to study flow charac-teristics in an expansion tunnel Vertical surveys of the axialcomponent of flow velocity just downstream from the nozzle exitwere obtained, and estimates of freestream density were inferredfrom the velocity measurement technique The pitot pressure wasmeasured and compared to the average axial component of velocityas a function of time for the two cases when air and C02 were usedas test gases Vertical velocity and static density profiles at the nozzleexit are presented for the case when CO2 was used as test gasExperimental results were used to determine the diameter anduniformity of the test core at the nozzle exit and the duration of thequasi-steady flow period These data are relevant to evaluation of thesuitability of operating an expansion tube as an expansion tunnelThe expansion tunnel is an expansion tube with a conical nozzlepositioned at the exit of the acceleration section, so that nozzleentrance flow conditions are hypersonic and characterized byhypervelocity M L

A77-47136 Thermal stability of transition metal mono-carbide fibers in refractory composites prepared by unidirectionalsolidification (Stabilite thermique des fibres de monocarbures demetaux de transition dans les composites refractaires elabores parsolidification unidirectionnelle) J F Stohr, T Khan, MRabmovitch, and H Bibrmg (ONERA, Chatillon-sous-Bagneux,Hauts-de-Seme, France) In International Conference on theStrength of Metals and Alloys, 4th, Nancy, France, August 30-September 3, 1976, Proceedings Volume 2Nancy, Ecole Nationale Supeneure de la Metallurgy et de ('Industriedes Mines, 1976, p 569-573 13 refs In French

The thermal stability of Cotac composites was studied with theintention of determining their suitability for aircraft turbines Cotacalloys consist mainly of Co, Ni, Cr, and also of a transition metalcarbide Composite stability during thermal cycling and Cotaccomposite stability in the presence of a thermal gradient normal tothe fibers were determined Fiber degradation during thermal cyclingplays a ma|or role in the plastic deformation of the matrix, and, byincreasing the resistance to plastic flow of the matrix, it was possibleto develop two new composites which are practically unaffected bythermal cycling to 1100 C The Cotac composites were basicallyunaffected by thermal gradients perpendicular to the fibers of 100C/mmup to 1100C ML

A77-47199 H Aircraft laboratories and experience in usingthem for the development of methods and means of remote sensingof earth resources (Samoletnye laboratom i opyt ikh ispol'zovannapn obrabotke metodov i sredstv distantsionnykh issledovannzemnykh resursov) la L Ziman, M lu Sazhko, and V S TsitovichIn Space studies of earth resources Methods and means ofmeasurement and data processing Moscow,Izdatel'stvo Nauka, 1976, p 275-280 In Russian

A77-47200 # Space experiment simulation using an aircraftlaboratory (Modehrovanie kosmicheskogo eksperimenta s pomo-shch'iu samoletnoi laboratom) G A Avanesov, I V Barinov, V DGlazkov, la L Ziman, and V I Tarnopol'skn In Space studies ofearth resources Methods and means of measurement and dataprocessing Moscow, Izdatel'stvo Nauka, 1976, p280-290 6 refs In Russian

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A two-year program devoted to the airborne simulation ofprocedures of satellite remote sensing of earth resources is reviewedThe structure of the airborne system is described with attentiongiven to remote sensors, preliminary and thematic processingequipment, and recording instruments A functional diagram of theairborne system is presented and an optical system for themultispectral scanning system and a system for separating radiativefluxes are considered Use of simulation data in elaborating ground-based means of data processing and interpretation is discussed B J

A77-47248 Aerodynamics of a confined jet with variabledensity F R Steward and A G Guruz (New Brunswick, University,Fredencton, Canada) Combustion Science and Technology, vol 16,no 1-2, 1977, p 29-45 12 refs National Research Council ofCanada Grant No A-1942

A similarity parameter has been obtained for a confinedturbulent jet system of constant cross section for which the nozzlefluid and the surrounding fluid have different densities Thisparameter was derived from the time smoothed equations of motionwith certain simplifying assumptions Velocity, temperature andtracer concentration profiles were measured on such a system withthe similarity parameter, called the nomsothermal Craya-Curtetnumber, varied over a range of 0 22 to 12 The experimental datawere correlated with the similarity parameter in a manner whichsupports its validity (Author)

A77-47257 The development and simulation of an auto-matic gunnery system for advanced fighter aircraft W P Summers,G J Komechak, and W S Bennett (General Dynamics Corp , FortWorth, Tex ) In Annual Simulation Symposium, 10th, Tampa, Fla ,March 16-18, 1977, Record of ProceedingsTampa, Fla , Annual Simulation Symposium, Long Beach, Calif,IEEE Computer Society, 1977, p 385-399

A predominant error source in modern airborne gunnerysystems is the inability of the pilot to track a target under highlydynamic conditions A search for methods and techniques forimproving aerial gunnery led to two approaches for improvinggunnery effectiveness The first approach, the coupling of the firecontrol system with the aircraft's flight control system to provideautomatic tracking of the target, and the second approach, atramable gun mechanization were evaluated by simulation, and theresults are presented in this paper On the basis of results, significantimprovement in effectiveness can be achieved in comparison to themanual tracking method used in modern fighters (Author)

A77-47271 ft The military utility of very large airplanes andalternative fuels W T Mikolowsky (Rand Corp , Washington, D C ),L W Noggle (USAF, Aeronautical Systems Div, Wright-PattersonAFB, Ohio), and W L Stanley (Rand Corp, Santa Monica, Calif)Astronautics and Aeronautics, vol 15, Sept 1977, p 46-56 21 refs

The paper describes a study with the objectives of evaluatingvery large airplanes (VLA's) in the context of existing and possiblefuture Air Force missions and determining the most attractivealternative fuel for these airplanes The chemical fuel alternativesconsidered are liquid hydrogen, liquid methane, and synthetic JP,each of which can be readily synthesized from coal The nuclear-fueled VLA was a fourth candidate aircraft The cost and energyeffectiveness of these basic aircraft-fuel combinations in typicalrange, radius, and station-keeping missions was estimated It wasconcluded that overall, a conventional hydrocarbon jet fuel remainsthe most attractive fuel for military aircraft Nuclear propulsion isattractive only for station-keeping missions requiring large stationradii VLA's are especially attractive if the capability to airlift U Sforces world-wide without reliance on overseas bases is a majorrequirement P T H

A77-47333 The RPV - Complement to manned systems.Proceedings of the Fourth Annual Symposium, Washington, D C,June 5-9, 1977. Symposium sponsored by the National Association

for Remotely Piloted Vehicles Dayton, Ohio, National Associationfor Remotely Piloted Vehicles, 1977 182 p $25

Attention is given to complementary roles for RPVs in supportof tactical manned aircraft, an operational concept for a battlefieldsurveillance RPV system (Canadair CL-227), RPV applications of theTomahawk cruise missile, and the Aquila mmi-RPV program Theselection of optimum RPV operational launch and recovery tech-niques, tethered hover flight tests of a vertical attitude takeoff andlanding RPV, the development of ai. ultra-low-cost gas turbine forRPV applications, and the development of the Multiple DroneControl System are also considered B J

A77-47334 # Complementary roles for RPVs in support oftactical manned aircraft C A Zraket and S E Rose (Mitre Corp,Bedford, Mass ) In The RPV - Complement to manned systems,Proceedings of the Fourth Annual Symposium, Washington, D C,June 5-9, 1977 Dayton, Ohio, National Associa-tion for Remotely Piloted Vehicles, 1977, p 1-7

As a result of new technology in computer, sensor andcommunications electronics, it is feasible for the aircrew of tacticalstrike aircraft to control a supporting force of 'smart' RPVs whichare able to operate semi-autonomously in a number of missionswithout continual remote control The RPVs have the inherentcapability to electronically sense the threat environment, takeself-initiated evasive maneuvers and transmit this data to other RPVsand the manned aircraft By providing this information to thedata-processing capability distributed among the aircraft, the RPVsand ground tactical control centers, it will be feasible, in real time, toreconfigure the overall attack against the most recently perceivedthreat The use of RPVs in support of tactical manned aircraftpromises to significantly reduce the cost and to increase the size andeffectiveness of the total fleet (Author)

A77-47335 tt Operational concept for a battlefield surveil-lance RPV system /Canadair CL-227/ J P Kezr (Canadair, Ltd ,Montreal, Canada) In The RPV - Complement to manned systems,Proceedings of the Fourth Annual Symposium, Washington, D C,June 5-9, 1977 Dayton, Ohio, National Associa-tion for Remotely Piloted Vehicles, 1977, p 8-12

An operational concept is described for a battlefield surveillanceRPV system designed to provide field commanders with an organiccapability for real-time surveillance over enemy terrain, immediateacquisition of targets and fire adjustment-target designation TheRPV system comprises Control Stations, RPV Stations and RPVswith Payloads, it is the Canadair CL-227 system The systemscharacteristics provide the basis for an operational concept wherebyRPV preparation, take-off, landing and servicing is undertaken wellto the rear while control during a mission is exercised by a forwardstation The phases of such an operation are described together witha maintenance concept (Author)

A77-47336 # RPV applications of Tomahawk cruise missileR A Lynch, J D Sutliff, L E Murphy, Jr, and W R Karmazm(General Dynamics Corp, Convair Div , San Diego, Calif) In TheRPV • Complement to manned systems. Proceedings of the FourthAnnual Symposium, Washington, DC, June 5-9, 1977

Dayton, Ohio, National Association for RemotelyPiloted Vehicles, 1977, p 13-18

The versatility and durability of the Tomahawk cruise missileincorporated into an RPV system are recommended Originallydesigned for submarine launch, the Tomahawk in its RPV format canbe launched from ground, vehicles, shipboard, or aircraft, with aquick-disconnect 1000-lb payload and a range of 1500 nautical miRecoverability and prompt reusability are additional advantages ofthe weapon system. Reconnaissance, jamming and chaffing nuisancemissions, and strikes against hard targets and sheltered or revettedaircraft are possible applications R D V

A77-47337 § Tactical expendable drone system /TEDS/ 0H Caperton (Northrop Corp , Ventura Div , Newbury Park, Calif)In The RPV - Complement to manned systems. Proceedings of the

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Fourth Annual Symposium, Washington, D C, June 5-9, 1977Dayton, Ohio, National Association for Remote-

ly Piloted Vehicles, 1977, p 19-23 'Tactical combat uses of TEDs (tactical expendable drones) in

strike and support missions are outlined, and results of validation andflight tests are presented Decoy service against hostile AAA and/orSAM, deployment as a diversionary decoy strike force, penetrationaid as area-distributed jammer, and target acquisition supportapplications are described Saturation and dilution of hostile defensesystems are emphasized Production, storage, maintenance, combatdeployment, and launches of TEDs are outlined R D V

A77-47338 ft The development of the XMQM-105 Aquilammi-RPV system F D Schnebly (Lockheed Missiles and Space Co ,Inc. Sunnyvale, Calif) In The RPV - Complement to mannedsystems. Proceedings of the Fourth Annual Symposium, Washington,D C., June 5-9, 1977 Dayton, Ohio, NationalAssociation for Remotely Piloted Vehicles, 1977, p 24-32

The Army's Aquila program began in January 1975 with theobjective of demonstrating the application of mmi-RPV technologyto missions of surveillance, artillery fire adjustment and laserdesignation. This paper reviews major events during the course of theprogram with emphasis on technical, scheduling and programmaticaspects Particular emphasis is placed on the system aspects ofmim-RPVs and innovative test approaches Film and video highlightsof launch and recovery operations are shown along with imaging datafrom onboard sensors B J

A77-47339 ff U S /F R G. advanced tactical RPV require-ments as analyzed by Boeing and Dormer D J O'Brian, P HSchweizer (Boeing Co, Seattle, Wash ), and J Spintzyk (DormerGmbH, Fnednchshafen, West Germany) In The RPV - Complementto manned systems. Proceedings of the Fourth Annual Symposium,Washington, D C , June 5-9, 1977 Dayton, Ohio,National Association for Remotely Piloted Vehicles, 1977, p 33-40

Tactical combat requirements for effective use of remote pilotedvehicles (RPV) are assessed for a central European scenario Relianceon RPVs is found best advised when combat attrition rates are highand a certain range of fixed or transient targets are to be engaged,mixes of RPVs and manned aircraft are considered Alert capability,survivability on the ground, 24-hr all-weather capability, and RPVuse as escorts and precursors are highlighted Recommended reconmissions include detailed zone reconnaissance of concentratedarmor, area activity sampling along communication routes, and bombdamage assessment after strikes Low cost, modest personnelrequirements, and saving of trained personnel for other tasks areemphasized. R D V

A77-47340 // Selection of optimum RPV operational launchand recovery techniques W J Potocki (Rockwell InternationalCorp, Missile Systems Div, Columbus, Ohio) In The RPV -Complement to manned systems. Proceedings of the Fourth AnnualSymposium, Washington, D C , June 5-9, 1977Dayton, Ohio, National Association for Remotely Piloted Vehicles,1977, p 41-49

A qualitative study of production, technology, and cost controlproblems in working out optimum launch and recovery techniquesfor combat RPVs (remotely piloted vehicles) is presented Cost/benefit/risk analysis and life cycle cost analysis studies are describedCandidate systems and hardware for RPV launch and recoveryoperations are listed and compared. The study is recommended as anattack on problems not amenable to detailed quantitative pro-cedures, while offering reasonably rapid convergence to the mostappropriate candidates to be given closer attention in systemdevelopment. R D V

A77-47341 # Tethered hover flight tests of a vertical at-titude takeoff and landing remotely piloted vehicle W H Eilertson(U S Naval Material Command, David W Taylor Naval ShipResearch and Development Center, Bethesda, Md ) In The RPV -Complement to manned systems. Proceedings of the Fourth Annual

Symposium, Washington, DC, June 5-9, 1977Dayton, Ohio, National Association for Remotely Piloted Vehicles,1977, p 50-58 6 refs

Vertical attitude takeoff and landing offers attractive advantagesto the Navy in that ship interface problems are alleviated. A 560-lbdemonstration vehicle was designed to assess these advantages Thisvehicle will be flight tested to assess vertical hover capability in theturbulent aerodynamic wake generated by a ship's superstructurewhile underway The design incorporates a close coupled canard/delta wing configuration Components from the Harpoon missile areutilized Tethered flight tests in hover were recently demonstratedsuccessfuly. (Author)

A77-47342 ff The mim-RPV, cost effectiveness in a tacticalenvironment E A Rose, Jr and J H Budiansky (E-Systems, Inc,Falls Church, Va ) In The RPV - Complement to manned systems.Proceedings of the Fourth Annual Symposium, Washington, D C ,June 5-9, 1977 Dayton, Ohio, National As-sociation for Remotely Piloted Vehicles, 1977, p 59-65.

A cost effectiveness analysis to examine RPV deployment indefense suppression, 'loiter mine' and jamming is describedScenarios are used to develop rationale for cost effectivenesstradeoffs that demonstrate aid to manned systems in the battlefield.Mission profiles in hypothetical but reasonable European scenariosare used as a background for the analysis Examples of low costcomponent technology and manufacturing techniques being used todevelop operational systems, and representative RPV hardware, areincluded (Author)

A77-47343 # Synergistic growth of ITCS to a tactical RPVC2 system D Barrow (Motorola, Inc , Government Electronics Div ,Scottsdale, Ariz ) In The RPV - Complement to manned systems.Proceedings of the Fourth Annual Symposium, Washington, D C ,June 5-9, 1977 Dayton, Ohio, National Associa-tion for Remotely Piloted Vehicles, 1977, p 66-70 Navy-supportedresearch

This paper presents a brief technical overview and summary oftest results on the Integrated Target Control System (ITCS)developed by Motorola under contract to Naval Air SystemsCommand A wideband anti-jam data link developed under aMotorola Independent Research and Development program is alsodiscussed ITCS was developed as a set of control stations operatingat ranges to 250 nautical miles and associated target avionics It is themost modern, operational, integrated system in existence today forcommand, control, and tracking of unpiloted vehicles The tech-nology and hands-on experience gamed from the ITCS program aredirectly applicable to tactical RPV command, control, and informa-tion transfer problem. The proven hardware and operational ex-perience gained from ITCS coupled with demonstrated hardware andstate-of-the-art technology from the Motorola anti-jam widebanddata link provide the basis for an advanced design, high performance,cost effective RPV command, control, and information transfersystem (Author)

A77-47344 <? Development of an ultra-low-cost gas turbineC F Baerst and W M Norgren (AiResearch ManufacturingCompany of Arizona, Phoenix, Ariz ) In The RPV - Complement tomanned systems, Proceedings of the Fourth Annual Symposium,Washington, D C, June 5-9, 1977 Dayton, Ohio,National Association for Remotely Piloted Vehicles, 1977, p 71-78USAF-supported research

By utilizing the aerodynamic components from a high-production, low-cost truck engine turbocharger, a new generation ofultra-low-cost turbine engines is developed A series of engines in the100- to 200-pound thrust class, under development by Garrett/AiResearch. is presented. One engine is a simple conversion of theModel T-18A turbocharger to an engine with 100-pounds thrust Asecond version redesigns the turbine and adds a sudden expansionburner for augmentation and produces about 200-pounds thrustBoth engines were fabricated and successfully run in sea level thruststands Testing of these prototypes proved the performance capabili-

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ty of this concept and provided the basis for future enginedevelopment (Author)

A77-47345 # Multiple Drone Control development R EWinkler (Sperry Rand Corp, Sperry Univac Div , Salt Lake City,Utah) In The RPV - Complement to manned systems. Proceedingsof the Fourth Annual Symposium, Washington, D C, June 5-9,1977 Dayton, Ohio, National Association forRemotely Piloted Vehicles, 1977, p 79-84

This paper discusses the development of the Multiple DroneControl (MDC) System and its application in the use of multipleRPVs for operational EW missions The system evolution fromone-on-one control, using the AN/UPQ-3 Microwave CommandGuidance System (MCGS), to the Multiple Drone Control/StrikeSystem (MDC/SS) is described MDC/SS, currently completingDT&E and IOT&E flight testing, is discussed, including flight'testresults and operational capabilities Other potential apphcat^ns ofthe i_unent configuration are noted and possible fluure evolution ofthe system is discussed (Author)

A77-47346 # An alternate recovery system for the AquiibG R Seemann, K L Phillips, G L Harris, H E Krachman, JHertenstem, and G Brown (Developmental Sciences, Inc, City ofIndustry, Calif) In The RPV - Complement to manned systems,Proceedings of the Fourth Annual Symposium, Washington, D C,June 5-9, 1977 Dayton, Ohio, National Associa-tion for Remotely Piloted Vehicles, 1977, p 85-88 Grant NoDAAJ02-76-C-0039

A soft-landing variant recovery system for the Aquila mim-RPVis described A hydraulic drag brake arrangement is employed for testhorizontal deceleration and an air mattress to facilitate verticaldeceleration The arrangements can be set up within 2 hr anddismantled within 2 hr The RPV can be hauled to launch site andfrom recovery site in a pickup truck R D V

A77-47347 # Development of a small, low cost turbojetengine with thrust augmentation W C Elrod, H E Wright, 6 LWolfe, Jr, J D Durmak (USAF, Institute of Technology, Wright-Patterson AFB, Ohio), and D B Wilkinson (USAF, Aero-PropulsionLaboratory, Wright-Patterson AFB, Ohio) In The RPV - Com-plement to manned systems, Proceedings of the Fourth AnnualSymposium, Washington, DC, June 5-9, 1977Dayton, Ohio, National Association for Remotely Piloted Vehicles,1977, p 89-95 7 refs

Turbosuperchargers from two manufacturers were successfullyconverted to turbojet engines, with engine run up from idle tomaximum thrust while limiting the turbine inlet temperature to 1250K The smaller of the two turbosupercharge systems selected forconversion (designated J-1 and J-3 engines) was the first to beconverted to a turbojet engine (the J-1 unit) and subsequently theconventional combustor was replaced with a catalytic reactor (thendesignated the J-3 unit) The J-3 engine weighed 13 15 kg (29 Ib-m)excluding the oil system and produced 133N (30 Ib-f) thrust with aturbine inlet temperature of 1250 K while operating on hydrogen asa fuel The larger turbosupercharger designated the J-2 unit operatingwith JP-4 as a fuel and limiting the turbine inlet temperature to 1250K produced 330 N (74 5 Ib-f) thrust dry and 483 N (109 Ib-f) withafterburner The thrust specific fuel consumption ranged from 2 2 to3 6 (Author)

A77-47348 ft Microcomputer RPV stabilization and controlsystem R C Eslmger (Sperry Rand Corp/Sperry Flight Systems,Phoenix, Ariz.) In The RPV - Complement to manned systems,Proceedings of the Fourth Annual Symposium, Washington, D C ,June 5-9, 1977 Dayton, Ohio, National Associa-tion for Remotely Piloted Vehicles, 1977, p. 96-101.

Utilization of a microcomputer in a typical mim-midi typeremote piloted vehicle (RPV) system is explored, with attentiongiven to software development. Built-in testing procedures andautomatic checkout, in addition to in-flight RPV control and

stabilization, are realizable with availability of 16-bit microprocessorswith high-density memories capable of functioning over the fullrange of military environments Input/output signals processed bythe microcomputer in the RPV system are tabulated and discussed

R D V

A77-47349 // An evaluation of future RPV automatic navi-gation systems G J Me Keel (Rockwell International Corp , MissileSystems Div , Columbus, Ohio) In The RPV - Complement tomanned systems, Proceedings of the Fourth Annual Symposium,Washington, D C , June 5-9, 1977 Dayton, Ohio,National Association for Remotely Piloted Vehicles, 1977, p102-108 Contract No F33657-75-C-0518

A combination of dead reckoning and position fixing systems isrecommended as best suited to future navigation system require-ments for remote-piloted vehicles (RPV) designed for electronicwarfare, reconnaissance, or selective strike sorties Strapdown mertialdead reckoning is given preference over the gimballed mertial variant,and position fixes can be obtained from hne-of-sight, over-horizon,or correlator type (terrain contour, radiometric) systems R D V

A77-47350 ti Advanced avionics for the Advanced RemotelyPiloted Vehicle /ARPV/ J L Perry, V K Goyal, and D R Ziesig(Systems Consultants, Inc, Dayton, Ohio) In The RPV - Com-plement to manned systems. Proceedings of the Fourth AnnualSymposium, Washington, DC, June 5-9, 1977Dayton, Ohio, National Association for Remotely Piloted Vehicles,1977, p 109-116 16refs Contract No F33615-75-D-1125

The Advanced Remotely Piloted Vehicle (ARPV) is a new AirForce weapons system intended to perform Reconnaissance (Recce),Electronic Warfare (EW), and Strike missions in support of mannedtactical aircraft A single multi-mission multipurpose ARPV designappears more cost-effective than a proliferation of different RPVdesigns, each tailored to a specific mission. The ARPV's hardwareand software must be capable of rapid change, from mission tomission To achieve this required flexibility while maintaining lowlife cycle cost, the Air Force Avionics Laboratory (AFAL) launchedan investigation of the use of advanced multiplexing and micro-computer techniques to the ARPV The results of this effort arepresented, and include a proposed data bus architecture which is alogical extension of the Air Force's Digital Avionics InformationSystem (DAIS) (Author)

A77-47351 # A miniature rotary-wing RPV G D Summers,E G Greene (Atlantic Research Corp , Alexandria, Va ), and D AMartin (US Navy, Washington, D C ) In The RPV - Complement tomanned systems, Proceedings of the Fourth Annual Symposium,Washington, D C , June 5-9, 1977 Dayton, Ohio,National Association for Remotely Piloted Vehicles, 1977, p117-120

A miniature, rotary-wing, RPV, designed and built by AtlanticResearch Corporation, has been shown to be stable in flight andcapable of carrying various reconnaissance payloads The experi-mental aircraft has flown in several test configurations Averageall-up weight, including fuel for an hour and payload, has beenapproximately 26 pounds Payloads have included a televisioncamera and broadcast transmitter, a TV camera and a fiber-opticair-to-ground link, and a motion-picture camera The objective of them-house project was to demonstrate system feasibility It isenvisioned that, with further system development, this type of RPVcan complement manned systems in a variety of functions, both incivil and in military applications (Author)

A77-47352 # Remote rate control for RPVs J Hirsch (U SNaval Ocean Systems Center, San Diego, Calif) In The RPV -Complement to manned systems. Proceedings of the Fourth AnnualSymposium, Washington, D C , June 5-9, 1977Dayton, Ohio, National Association for Remotely Piloted Vehicles,1977, p 121-124 11 refs

The paper proposes a tactile control system which wouldprovide the ground controller of an RPV with the sensitivity to

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detect the error rate of change and enable him to be alert to a fastbuildup of error Tactile signals would be used to present rateinformation as an alternative to 'quickening' a visual display Thevideo-tactile system would use two channels of information toprovide a natural and instinctive method of control The rateinformation could be extracted and telemetered to a controloperator as tactile stimuli B J

A77-47353 ff Ducted-fan VTOL RPV system R A Johnsonand R D Small (General Dynamics Corp , Convair Div , San Diego,Calif ). In The RPV - Complement to manned systems. Proceedingsof the Fourth Annual Symposium, Washington, D C, June 5-9,1977 Dayton, Ohio, National Association forRemotely Piloted Vehicles, 1977, p 125-131

A ducted-fan RPV research test vehicle which is a small,four-foot duct diameter airframe that will be capable of hover andtransition to forward flight has been developed The principlefeatures of this airframe are its ability to take off and land verticallyin confined and unprepared areas and the capacity for non-pilottrained personnel to operate the vehicle simply and safely Groundtests were conducted on the vehicle to verify the thrust and controlmoments statically and to demonstrate controllability and transitioncharacteristics on a tether rig B J.

A77-47354 ff Ku-band integrated circuit receiver E JCrescenzi, Jr, C M Krowne, and F A Marki (Watkins-Johnson Co ,Palo Alto, Calif ) In The RPV - Complement to manned systems.Proceedings of the Fourth Annual Symposium, Washington, D C ,June 5-9, 1977 Dayton, Ohio, National Associa-tion for Remotely Piloted Vehicles, 1977, p 132-137 6 refsResearch supported by the Watkins-Johnson Co, Grant NoDAAB07-75-C-1366

A 15 GHz receiver front-end module for RPV applications hasbeen designed and constructed using thin film microstrip technologyThe complete circuit is contained in a simple 5 cu cm hermeticmodule The module contains an RF filter, a single stage GaAs FETbalanced amplifier, an image reject mixer, and a GaAs FET voltagetuned oscillator A 7 1 to 7 8 dB noise figure was achieved over the14 4 to 15 4 GHz range, including the IF amplifier contribution

B J

A77-47472 Ways of increasing the resources /potentiallives/ of gas turbine engines P A Viter (Kazanskn Motorostroitel'-nyi Zavod, Kazan, USSR) (Problemy Prochnosti, vol 8, Dec 1976,p 94-96) Strength of Materials, vol 8, no 12, Sept 1977, p1472-1475 Translation

The paper discusses some of the technical decisions whichenabled both the reliability and the service life of a Soviet civiltransport jet engine to be increased Thus, the principle of combinedfinal design stages and mastery of production of the parts wasfollowed Special studies were carried out to obtain high frettingcorrosion resistance of contact surfaces of the blade shrouding of thefirst stage of the low pressure compressor Accelerated stand tests

'were performed When engines were removed prematurely fromservice, a system of local repair was developed and introduced forfurther improvement of the remaining part of the service life P T H

A77-47501 Fatigue 1977, Proceedings of the Conference,Cambridge University, Cambridge, England, March 28-30, 1977Conference sponsored by the Metals Society Metal Science, vol 11,Aug-Sept 1977 167 p

Several aspects of metal fatigue are discussed Topics includefatigue problems in service, initiation and propagation of shortcracks, fatigue crack propagation, and interaction effects Experi-mental and theoretical studies are described, often with respect tofatigue behavior in steel or aluminum alloys Attention is directed tothe effects of notches and persistent slip bands Fatigue problemsinvolving aircraft structures are considered M L

A77-47503 Fatigue problems in service - Aircraft struc-tures. P J E Forsyth (Royal Aircraft Establishment, MaterialsDept., Farnborough, Hants., England) (Metals Society, FatigueConference, Cambridge, England, Mar 28-30, 19771 Metal Science,vol 11,Aug.-Sept 1977, p 293-302 11 refs

The sources of structural fatigue loads in aircraft are described,and examples of fatigue at joints in airframe parts are discussed Thereasons for joints being fatigue-sensitive points are considered, andthe effects of cladding on the fatigue strength of aluminum alloys isexamined Features of metal plates and their microstructure arecharacterized. Fatigue is discussed with attention to wing sparfailures, riveted joints, major lug joints, fuselage and wing apertures,and fillet radii on machined parts It is concluded that an increase inthe size of small flows or the introduction of cladding, which causesa considerable adverse effect on plain fatigue strength, hardlychanges the fatigue behavior of built-up structures By means ofcareful design and improved crack growth resistance, damage causedby fatigue can be reduced M L

A77-47537 ff Application of the finite element techniquecombined with the collocation method to subsonic lifting surfaceproblems M Hashimoto, K Washizu (Tokyo, University, Tokyo,Japan), and M Ikegawa (Hitachi Co , Ltd , Tokyo, Japan) InInternational Symposium on Finite Element Methods in FlowProblems, 2nd, Santa Marghenta Ligure, Italy, June 14-18, 1976,Preprints Genoa, International Centre for Com-puter Aided Design, 1976, p 149-158 11 refs

In the present paper, a finite element technique combined withthe collocation method is formulated to obtain numerical solutionsof an integral equation which determines the airload distributionacting on a wing placed in an incompressible uniform flow Anemphasis is placed on the continuity requirement for the shapefunction of the airload distribution It is shown that the accuracy ofnumerical results obtained by the present finite element technique isencouraging Although examples treated in the present paper arelimited, extensions of the present technique to other integralequations are straight-forward (Author)

A77-47539 * # Application of finite element approach totransonic flow problems M M Hafez, E M Murman (FlowResearch, Inc, Kent, Wash), and L C Wellford (Southern Cali-fornia, University, Los Angeles, Cali f) In International Symposiumon Finite Element Methods in Flow Problems, 2nd, Santa MarghentaLigure, Italy, June 14-18, 1976, PreprintsGenoa, International Centre for Computer Aided Design, 1976, p175-187 25 refs Contract No NAS1-4246

A variations! finite element model for transonic small distur-bance calculations is described Different strategy is adopted insubsonic and supersonic regions Blending elements are introducedbetween different regions In the supersonic region, no upstreameffect is allowed If rectangular elements with linear shape functionsare used, the model is similar to Murman's finite differenceoperators Higher order shape functions, non-rectangular elementsand discontinuous approximation of shock waves are also discussed

(Author)

A77-47540 ff Application of finite element method for thesolution of transonic flow A Ecer and H U Akay (Middle EastTechnical University, Ankara, Turkey) In International Symposiumon Finite Element Methods in Flow Problems, 2nd, Santa MarghentaLigure, Italy, June 14 18, 1976, PreprintsGenoa, International Centre for Computer Aided Design, 1976, p191-201 10 refs NATO Project 823

A vanational formulation for the solution of steady, mviscidtransonic flow problem is presented An iterative scheme is definedto solve the resulting nonlinear equations which are derived using thefinite element method Subsonic and supersonic flow regions aretreated separately in this procedure Stability of the procedure foreach region is discussed and numerical results are presented for twoairfoil configurations (Author)

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A77-47542 * ff Analysis of transonic flow over lifting andoscillating airfoils S T K Chan and M R Brashears (LockheedMissiles and Space Co , Inc , Huntsville, Ala ) In InternationalSymposium on Finite Element Methods in Flow Problems, 2nd,Santa Marghenta Ligure, Italy, June 14-18, 1976, Preprints

Genoa, International Centre for Computer AidedDesign, 1976, p 219-230 11 refs Contract No NAS1 13786

Finite element procedures are presented for the numericalsolution of transonic flow over lifting and oscillating airfoils based onsmall disturbance theory The algorithm is simple and effective inhandling the mixed flow problem and, for airfoil in free air, treatsthe entire flow domain by making use of the far field asymptoticsolution Numerical results are presented and compared withexperimental data and those obtained by finite difference relaxationtechniques (Author)

A77-47543 ff Mixed finite element models and dual iterativemethods for transonic flow L C Wellford.Jr (Southern California,University, Los Angeles, Calif) and M M Hafez (Flow Research,Inc , Kent, Wash ) In International Symposium on Finite ElementMethods in Flow Problems, 2nd, Santa Marghenta Ligure, Italy, June14-18, 1976, Preprints Genoa, InternationalCentre for Computer Aided Design, 1976, p 233-245 9 refs

In this paper, finite element solutions for the transonic smalldisturbance formulation are developed Mixed vanational principlesare constructed for transonic flow These mixed vanational principlesare implemented using finite element approximations Dual iterativemethods combining a direct solution step and a gradient step areconstructed for solution of the resulting equation Numerical resultsare presented for flow about a circular arc airfoil (Author)

A77-47544 ff Transonic flow simulation by the finite ele-ment method via optimal control R Glowmski (Pans VI, Umversite,Paris, France), J Periaux (Avions Marcel Dassault-Breguet Aviation,St Cloud, Hauts-de-Seme, France), and O Pironneau (Institut deRecherche d'lnformatique et d'Automatique, Rocquencourt,Yvelmes, France) In International Symposium on Finite ElementMethods in Flow Problems, 2nd, Santa Marghenta Ligure, Italy, June14-18, 1976, Preprints Genoa, InternationalCentre for Computer Aided Design, 1976, p 249-259 7 refs

In this paper we discuss a new method for solving the transonicequations for compressible potential flow We construct severaloptimal control problems of distributed parameter systems whichhave for solution the solution of the transonic equation Theseoptimal control problems are discretized by the finite elementmethod and solved by the conjugate gradient algorithm Thus weobtain a new class of methods which converge also for flows withshocks and which is well adapted to two or three dimensional flowsaround multi-bodies airfoils (Author)

A77-47561 Problems in predicting aircraft noise exposureA H Odell (Port Authority of New York and New Jersey, NewYork, N Y ) Noise Control Engineering, vol 9, July-Aug 1977, p32-37 21 refs

A theory is proposed to calculate aircraft noise exposure interms of the subjective reaction of the exposed population byevaluating the combination of aircraft noise along with psychologicalfactors such as the time of day, season, background noise, etcCritical areas in noise exposure calculation are identified includingthe plotting of turns after takeoff and the variability of noise levelsfrom aircraft at a fixed point Suggestions are made for improvingthe degree of technical accuracy in calculating noise levels, such as(1) a statistical study of actual noise levels produced by each type ofaircraft as function of stage length, (2) calculation of turning flightpaths as function of aircraft type and takeoff weight, and (3)development and use of more accurate attenuation data forextrapolation of measured levels to more distant points, bothvertically and laterally (Author)

A77-47625 * Aircraft interior sandwich panel developmentR A Anderson and G A Johnson (Boeing Commercial Airplane

Co , Seattle, Wash ) Journal of Fire and Flammability, vol 8, July1977, p 364-381 7 refs NASA-supported research

Three resin systems (bismaleimide, polyimide and modifiedphenolic) and several decorative films for use in aircraft interiorpanelling were subjected to flammabihty, smoke and gas emission,and toxicity testing Cost, weight and appearance were also takeninto account in assessing the feasibility of the materials foriapplications in passenger seating areas as well as in unoccupied1

compartments (galleys, lavatories, closets) Heat release studies andburn-through tests provided an additional measure of the fire safetycharacteristics of the panelling A modified phenolic resin system andTedlar-polycarbonate decorative film were selected as the mostpromising candidates for replacing conventional epoxy resin-impregna'ed fiberglass materials J M B

A77-47667 tt Calculation of the aerodynamic characteristicsof a wing moving at subsonic speed, in the case of a weak shock-waveeffect on the wing (Raschet aerodmamicheskikh kharaktenstik kryla,dvizhushchegosia s dozvukovoi skorost'iu, pri slabom vozdeistvu nanego udarnoi volny) N A Gritsenko and M I Nisht AkademnaNauk SSSR. Izvestua, Mekhanika Zhidkosti i Gaza, July-Aug 1977,p 149-154 In Russian

A77-47669 # Configuration of free vortices trailing off awing of finite span (Forma svobodnykh vikhrei kryla konechnogorazmakha) A A Gruzdev Akademna Nauk SSSR, Izvestua, Mekha-nika Zhidkosti i Gaza, July-Aug 1977, p 159-163 10 refs InRussian

The progressive deformation of a pair of trailing vortices bytheir own induction is analyzed with allowance for the influence ofthe wing and the vortices attached to it It is assumed that smallperiodic far-field disturbances are absent and that the rate ofdownwash is specified A system of integrodifferential equationsdescribing the motion of the vortices is solved by a successiveapproximation technique The configuration of vortex filaments inthe flow is identified, and the behavior of points along the vortexfilaments at successive intervals of time is illustrated and discussed

V P

A77-47674 Rearrangement of vortex structures in thewake behind a body and in a jet V I Likhoperskii and S G Popov(Moskovskn Gosudarstvennyi Umversitet, Moscow, USSR) IMoskov-skn Umversitet, Vestnik, Seriia I - Matematika, Mekhanika, Mar -Apr1977, p 106-112 I Moscow University Mechanics Bulletin, vol 32,no 1-2, 1977, p 40-45 11 refs Translation

An investigation of vortex-street stability is conducted in whichthe decay and rearrangement of systems of point vortices in an idealincompressible fluid are studied analytically The analysis agrees withexperiments in which symmetrical vortex streets are rearranged intocheckerboard streets in a wake flow It is confirmed that symmetricalvortex streets excited acoustically in a jet are rearranged symmetri-cally at h/l greater than 1 (where I is the distance between adjacentvortices of one row and h is the distance between rows) and thenassume a checkerboard pattern B J

A77-47675 Flight control I - The aircraft as controlledsystem (Flugregelung I - Das Flugzeug als Regelstrecke) RBrockhaus (Braunschweig, Technische Universitat, Braunschweig,West Germany) Munich, R Oldenbourg Verlag, 1977 239 p 66refs In German $14 20

Objectives and procedures of flight control are examined, takinginto account flight control as a section of control technology, flightcontrol in its relation to the performance of objectives of flightmechanics, a historical review of flight control developments,currently employed types of control systems, and new advancesrelated to the area of flight control The system of equations ofaircraft dynamics is considered and aspects related to the charac-terization of aircraft dynamics are discussed Attention is given tothe definition of the parameters of flight mechanics, the derivationof the system of differential equations, a description of the forces

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and moments which act upon the aircraft, wind effects, thelinearization of the system of equations, its solution, the representa-tion of the homogeneous solution with the aid of time vectors,approximation procedures for estimating the dynamical charac-teristics of the controlled system, and the reaction of the aircraft inresponse to signals G R

A77-47699 # The insertion or elimination of fuselage sec-tions and the balancing of aircraft (Inserzione o rimozione di sezionidi fusohera e centramento dei velivoli) S Chiesa (Torino, Poh-tecnico, Turin, Italy) Ingegneria, May-June 1977, p 129-134 InItalian

Equations describing the center of gravity for aircraft subject tovarious insertions or reductions of fuselage length, both in anteriorand posterior positions, are given The equations may be used inrebalancing aircraft or in the formulation of increased or decreasedfuselage-capacity designs, as well as designs accommodating differentengine capacities The equations derived relate the longitudinalcoordinate of the center of gravity to the length and weight of theinserted or eliminated section and to the location of the insertion orelimination, an iterative method is suggested for obtaining approxi-mate analytical results J M B

A77-47813 ff Royal Air Force assessment flights. D WBroughton (RAF College, Cranwell, Lines, England) Journal ofNavigation, vol 30, Sept 1977, p 339-343

Early transpolar and trans Atlantic flight tests of the Omeganavigational system when the system was not fully operational(1973, 1976) are described Omega error autocorrelation waschecked with time, height and accuracy relations were checked,signal reception and loss of signal from distant stations are reported,and errors are described (cumulative frequency, % radial errorswithin circular error probability contour) Positioning of hardwareused is outlined briefly R D V

A77-47816 § Some mathematical aspects of air traffic sys-tems V W Attwooll (Royal Aircraft Establishment, Air TrafficStudies Div, Farnborough, Hants, England) IRoyal Institute ofNavigation, Meeting, London, England, Jan 26, 1977) Journal ofNavigation, vol 30, Sept 1977, p 394-411. Discussion, p 411-4147refs

Queuing problems applied to airport arrival and departure flowsare discussed and debated System capacity, channels available forstream flow, size (length) of queues, types of queues (steady-state ortime-varying, departure runway queues and holding stack queues),waiting times and delays, random arrival times, and (customer)acceptance (servicing) rates are considered Acceptance slots forregular and irregular arrivals, delays attributed to the airline companyor to ATC or airport ground servicing, and ways of minimizingperturbations in schedules are considered, and results of somecomputer simulation studies are outlined Cost penalties for delayedaircraft upsetting normal flows are weighed critically in the discus-sion R D V

A77-47817 ft The presentation of information in combataircraft L T J Salmon (Royal Aircraft Establishment, Farn-borough, Hants, England) (Royal Institute of Navigation, Meeting,London, England, Nov 17, 19761 Journal of Navigation, vol 30,Sept 1977, p 415-421

Recent advances in computerized and automated navigation andnavigation data display for combat aircraft are summarized andclassified Classification of navigation tasks and navigation aspects ofcombat missions distinguishes macronavigation (to the target area)and micronavigation (release and guiding of weapon onto target, withstatic or dynamic micronavigation depending on whether the target isstationary or mobile/random) Navigation-related features of over-water and overland reconnaissance missions and strike missions arecontrasted, and projection displays and head-up displays of naviga-'tion data are compared R D V

A77-47814 # Flight experience with Omega R H NBradley (Laker Airways, London, England) Journal of Navigation,vol 30, Sept 1977, p 343-352

Minor deviations from satisfactory performance are reported forthe Omega navigation system in three years of flying experience withOmega backed up by Doppler One hardware failure per year turnedup (a timing card fault, 10 V power supply failure, and a stuckbutton), all detectable pre-flight, no in-flight equipment malfunc-tions occurred Some off track excursions are to be corrected whenVLF stations are added to the network The lane ambiguityresolution program is seen as the major remaining difficulty andstumbling block to acceptance Setting of flags, particularly the AMB(lane ambiguity) flag, m response to random and obscure causes,presenting warnings that 'may mean something or may meannothing', is judged a recurring annoyance Interactive use of theOmega and Doppler systems is found helpful R D V

A77-47815 # An American Omega navigation evaluationprogramme - 1975-1977 P R J Reynolds (Pan American WorldAirways, Inc , New York, N Y ) Journal of Navigation, vol 30, Sept1977, p 352-358

The evaluation program involved several phases of in-flight testsof Omega hardware systems on fifty-odd B-707/300 aircraft over avariety of trans-Atlantic, trans-Pacific, and Western Hemisphere (N-S)runs Comparative costs of Omega vs mertial navigation systemcomponents and their effectiveness, worldwide availability of ade-quate Omega signal coverage. Omega in-lane accuracy and in-lanestability, hardware reliability, and operator compatibility of thecontrol/display units were assessed Types of Omega systems madeavailable by different manufacturers, types of antennas, effects ofsudden ionospheric disturbances and sudden phase anomalies, andmodal interference were examined Low-cost and practical 'crutches'for poor-coverage regions (such as far SW Pacific) are considered arubidium atomic clock and VLF signals stable to the Omegastandard R D V

A77-47879 Computers and wind tunnels - Complementaryaids to aircraft design A B Haines (Aircraft Research Association,Ltd, Bedford, England) Aeronautical Journal, vol 81, July 1977, p306-321 48refs

A survey of the life and career of Dietrich Kuchemann ispresented with reference to his work on developing methods tocalculate the flow over sweptback wings and alleviating adverse rootand tip effects, and his research on the SST Advances for externalcowl design (eg , a podded nacelle) and for three-dimensionalsweptback wing-body combinations are described in full Prospectsand critical areas for combining the use of computers with windtunnel experimentation are outlined, concluding that (1) the numberof configurations needed for tunnel testing will be reduced, (2) theability to forecast the aerodynamics of the full-scale aircraft wouldbe increased, and (3) the quality of tunnel data and types of testingwould be increased S C S

A77-47950 ff Runway utilization coefficients (II coefficientedi utilizzazione di pista) E Rosini (Aeronautica Militare, ServizioMeteorologico, Rome, Italy) Rivista di Meteorologia Aeronautica,vol 37, Apr -June 1977, p 145-148 In Italian

An index of the usability of airport runways which is dependentonly on wind direction and velocity is discussed In particular,monthly, seasonal and yearly levels of maximum wind velocityperpendicular and transverse to different runways are formulatedusing electronic data processing of synoptic wind velocity anddirection measurements. Tables of utilization coefficients for Fiumi-cino Airport (Rome), which has 18 runway configurations, are given

JM.B.

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STAR ENTRIES

N77-30069*# Amerind Publishing Co Pvt Ltd New Delhi(India)AIRCRAFT EQUIPMENTIn its Soviet Aircraft and Rockets (NASA-TT-F-770) 1977p 140-157 Transl into ENGLISH from the book Znakomtessamolet i raketa Moscow, Transport Publisher. 1971

Avail NTIS HCA13/MFA01 CSCL01DThe complex of functionally interconnected instruments and

devices for controlling flight engine operations electrical systemscommunications and vital systems for passengers and crew isdescribed The aggregates of the aircraft automatic equipmentare also discussed A R H

N77 30065*# Amerind Publishing Co Pvt Ltd. New Delhi(India)SOVIET AIRCRAFT AND ROCKETSN A Zhemchuzhin, M A Levin, I A Merkulov, V I Naumov0 A Pozhidayev S P Frolov and V S Frolov 1977 277 pTransl into ENGLISH of the book 'Znakomtes, samolet i raketa'Moscow, Transport Publishers 1971 Sponsored by NASA(NASA-TT-F-770, TT-74-52007) Avail NTISHC A13/MF A01 CSCL 01A

An overview of Soviet development and accomplishmentsin aeronautics and astronautics is presented along an assessmentof the technologies required for aircraft or rocket flight

N77 30O66*# Amerind Publishing Co Pvt Ltd New Delhi(India)IN HERCULEAN FLIGHTIn its Soviet Aircraft and Rockets (NASA-TT-F-770) 1977p 1-12 Transl into ENGLISH from the book'Znakomtes samoleti raketa Moscow, Transport Publishers. 1971

Avail NTIS HCA13/MFA01 CSCL 01AMajor developments in the history of Soviet aviation are

summarized and the objectives and accomplishments of variousmanned and unmanned space flight programs are discussed

A R H

N77-30067*# Amerind Publishing Co Pvt Ltd, New Delhi(India)AIRCRAFTIn its Soviet Aircraft and Rockets (NASA-TT-F-770) 1977p 24-80 Transl into ENGLISH from the book Zankomtes.samolet i raketa Moscow, Transport Publishers 1971

Avail NTIS HC A13/MF A01 CSCL 01AThe physical principles of flight, and the consideration of

atmospheric composition and aerodynamic forces in the designand construction of various types of aircraft are discussed Flightcharacteristics are described for i.dhcopters, rotary-wing aircraftshort and vertical takeoff aircraft, and tailess or variable geometrywing aircraft Flow characteristics at various speeds are alsodiscussed ARH

N77-30068*# Amerind Publishing Co Pvt Ltd. New Delhi(India)AIRCRAFT ENGINESIn its Soviet Aircraft and Rockets (NASA-TT-F-770) 1977p 81-139 Transl into ENGLISH from the book "Znakomtes.samolet i raketa" Moscow. Transport Publishers. 1971

Avail NTIS HC A13/MF A01 CSCL 21EThrust and weight requirements of aircraft engines in general

are discussed The- characteristics^ and operating principles ofvarious types of an Loathing and rocket ei.gmes are described

A R H

N77-30070*# "Amerind Publishing Co Pvt Ltd New Delhi(India)INSTRUMENTS AND METHOD OF AIR NAVIGATIONIn its Soviet Aircraft and Rockets (NASA-TT-F-770) 1977p 158-177 Transl into ENGLISH from the book "Znakomtes,samolet i raketa" Moscow Transport Publishers, 1971

Avail NTIS HCA13/MFA01 CSCL 17GTopics discussed include magnetic and astronavigation

instruments, flight beyond ground visibility aircraft radionavigation instruments and communication radio sets, instrumentlanding systems and ground controlled landing systems ARH

N77-30071*# Amerind Publishing Co Pvt Ltd New Delhi(India)AIRCRAFT CYBERNETICSIn its Soviet Aircraft and Rockets (NASA-TT-F-770) 1977p 178-197 Transl into ENGLISH from the book Znakomtes,samolet i raketa Moscow Transport Publishers. 1971

Avail NTIS HCA13/MFA01 CSCL 01CThe use of computers for aircraft control, flight simulation,

and mertial navigation is explored The man-machine relationproblem in aviation is addressed Simple and self-adaptingautopilots are described and the assets and liabilities of digitalnavigation techniques are assessed ARH

N77-30073# Army Aviation Systems Command, St Louis MoSystems Analysis OfficeFLYING. MAINTENANCE. AND THE SALE OF PARTS TOTHE FIELD INTERACTIVE MODELS FOR AH-1 AND CH-47SYSTEMS Final ReportValentin C Berger and Blame T Stone Apr 1977 61 p refs(AD-A039193, DRSAV-D-77-6. USAVSCOM-TR-77-24) AvailNTIS HC A04/MF A01 CSCL 01/3

Computer-generated graphic displays are used to investigatethe relationships of AH-1 and CH-47 fleet flying hours, and ofmaintenance occurences of short and long duration during selectedpeacetime and wartime (RVN) periods The rationale for observedrelationships is explored in detail and the discussion is sup-ported with the results of correlation analyses A similar approachis used to explore the relationships existing between monthlygross sales of stock-funded airframe parts to the field and thenumber of short and long duration maintenance events, andbetween those sales and monthly fleet flying hours The AH-1and CH-47 fleets are examined during a peacetime period of1-1/2 fiscal years The two elements of the study are shown tobe complementary and suitable for the construction of interactivemodels of operations and supply support A probable connectionis postulated between managed field maintenance supportactivities and the cost-effectiveness of On Condition Maintenance(OCM) world-wide team visits GRA

N77-30074# Battelle Columbus Labs , OhioARMY AVIATION MANUFACTURING TECHNOLOGYPROGRAM GUIDANCE Final Report. 1 Feb 1975 - 17 May1976H J Hennmg and T G Byrer Jun 1976 156 p refs(Contract DAAJ01-75-C-0448)(AD-A040821. DRSAV-76-30) Avail NTIS HC A08/MF A01CSCL 01/3

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This program is aimed at formulating a realistic five yearplan for developing and implementing advanced manufacturingtechnologies to the production of Army helicopters and recommen-ding modifications in the operation of the Army AviationManufacturing Technology program to realistically accommodatethe plan Author (GRA)

N77-30079 Air Force Inst of Tech Wright-Patterson AFB,OhioNUMERICAL SOLUTION OF THE CONICALLY SYMMETRICNAVIER-STOKES EQUATIONS FOR HYPERSONIC FLOWAT ANGLE OF ATTACK Ph D ThesisDavid Scott McRae 1976 113 pAvail Univ Microfilms Order No 77-9475

Solutions were obtained for hypersonic flow over sharp conesat high angle of attack by integrating the Navier-Stokes equationssubject to a conical symmetry assumption A physically basedtechnique (normal stress damping) was demonstrated forcontrolling starting transients and for reducing or eliminatingnumerical oscillations occuring at shock discontinuties during theintegration The general features which appeared in experimentwere shown to appear in the results of the integration, includingthe proper behavior in laminar flow, of the viscous layer andthe vortical singularity The adequacy of the conical symmetryassumption is indicated for the turbulent regime on conicalbodies Dissert Abstr

N77-30085*# Old Dominion Univ Research Foundation NorfolkVaEXPERIMENT AND ANALYSIS ON THE FLOW PROCESSDYNAMICS OF THE NASA-LANGLEY EIGHT FOOTTRANSONIC PRESSURE TUNNEL Semiannual ProgressReport. 1 May 1976 - 28 Feb 1977Ping Tcheng (Old Dominion Univ) 28 Feb 1977 39 p(Grant NsG-1079)(NASA-CR-154806) Avail NTIS HC A03/MF A01 CSCL01A

A dynamic response test performed in a eight foot transonicpressure tunnel is described The dynamics of the flow processof the wind tunnel at transonic conditions were obtainedDescriptions of the test conditions, instrumentation presentationof raw data analysis of data, and finally based on experimentalevidences, an attempt to construct an input output relationshipof the flow process from the viewpoints of control engineeringare included Author

N77-30086*# Flow Research Inc . Kent WashSTUDY OF DESIGN AND ANALYSIS METHODS FORTRANSONIC FLOW Final ReportEarll M Murman Jul 1977 14 p refs(Contract NAS2-8847)(NASA-CR-152041 NOTE-118) Avail NTISHC A02/MF A01 CSCL 01A

An airfoil design program and a boundary layer analysiswere developed Boundary conditions were derived for ventilatedtransonic wind tunnels and performing transonic wmdtunnel wallcalculations A computational procedure for rotational transonicflow in engine inlet throats was formumated Results andconclusions are summarized Author

N77-30087# Deutsche Forschungs- und Versuchsanstalt fuerLuft- und Raumfahrt, Cologne (West Germany)EXPERIMENTAL INVESTIGATION CONCERNING THEREDUCTION OF WAVE DRAG OF POINTED SYMMETRICALWINGS OF EQUAL VOLUME WITH SUBSONIC LEADINGEDGE AND BELL-SHAPED PLANFORM FOR DIFFERENTTHICKNESS DISTRIBUTIONS IN THE SPANWISE ANDCHORDWISE DIRECTIONSFnedrich Keunes 15 Sep 1975 38 p refs In GERMANENGLISH summary Translation was announced as N76-30175(DLR-FB-75-62) Avail NTIS HCA03/MFA01 DFVLR CologneDM 1540

Drag measurements were made for a family of wings in a30 by 30 sq cm supersonic wind tunnel to test the theory thatzero lift wave drag for pointed symmetrical wings of finite thickness

and equal volume may be reduced by varying the wing planformand the chordwise and spanwise thickness distribution Becauseof the influence of the model support and the approximate estimateof the skin friction necessary for determining the wave drag, noagreement was found with the theory which is valid for thewave drag of wings only The flow behavior during the testsindicate that the shock wave boundary layer interaction must

' be considered Author

N77-30088*# Boeing Vertol Co. Philadelphia PaCOMPARISON OF DYNAMIC STALL PHENOMENA FORPITCHING AND VERTICAL TRANSLATION MOTIONSFinal ReportT Fukushima and L U Dadone Washington NASA Jul1977 184 p refs Sponsored in part by US Army(Contract NAS1-14056)(NASA-CR-2793, 0238-10007-1) Avail NTISHC A09/MF A01 CSCL 01A

Test data for vertical translation motions of the V0012 andV23010-1 58 airfoils were compared with force pitch andoscillation data to determine qualitative differences in dynamicstall behavior Chordwise differential pressure variations wereexamined in detail for the test conditions displaying dynamicstall The comparison revealed a number of differences both inthe onset of stall and in the progression separation as a functionof the type of motion The evidence of secondary stall eventsfollowing the recovery from initial stall were found to be dependenton the type of motion, but additional data will be needed toincorporate vertical translation effects into the empirical approxi-mation of dynamic stall Author

N77-30089*# National Aeronautics and Space AdministrationLewis Research Center, Cleveland, OhioCOLD AIR PERFORMANCE OF A 12 766 CENTIMETER TIP-DIAMETER AXIAL-FLOW COOLED TURBINE 2 EFFECTOF AIR EJECTION ON TURBINE PERFORMANCEJeffrey E Haas and Milton G Kofskey Aug 1977 37 p refsPrepared in cooperation with Army Air Mobility Res and DevelopLab Cleveland(NASA-TP-1018) Avail NTIS HC A03/MF A01 CSCL21E

An air cooled version of a single-stage, axial-flow turbinewas investigated to determine aerodynamic performance withand without air ejection from the stator and rotor blades surfacesto simulate the effect of cooling air discharge Air ejection ratewas varied from 0 to 10 percent of turbine mass flow for boththe stator and the rotor A pnmary-to-air ejection temperatureratio of about 1 was maintained Author

N77-30O92# Analytical Sciences Corp, Reading, MassAN EXTENDED KALMAN FILTER FOR ESTIMATINGAERODYNAMIC COEFFICIENTS Final Report. Sep. 1975 -Sep 1976Charles M Brown. Jr Eglm AFB Fla AFATL Dec 197671 p refs(Contract F08635-76-C-0117)(AD-A040594, TASC-TR-636-1, AFATL-TR-158) Avail NTISHC A04/MF A01 CSCL 20/4

This report describes an extended Kalman filter (EKF)algorithm developed to estimate the aerodynamic coefficients ofprojectiles based on discrete free-flight trajectory measurementsThese measurements consist of three spatial positions and threeangular orientations, relative to a fixed inertial coordinate systemand time-of-flight at 50 downrange positions along the trajectoryThe algorithm is based upon a nonlinear six-degree-of-freedommodel of a rotationally symmetric rigid body, and it incorporatesa stochastic measurement model that approximates the condi-tions which exist in a ballistic test range GRA

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N77-30094# National Aerospace Lab. Amsterdam (Netherlands)Flight Dynamics DivAERODYNAMIC DATA AND OFF-DESIGN CHARACTERIS-TICS OF THE MODIFIED QUASI ELLIPTICAL AIRFOILSECTION NLR 7101J Zwaaneveld 3 Feb 1976 40 p refs(Contract NIVR-1723)(NLR-TR-76012-U) Avail NTIS HC A03/MF A01

Transonic wind tunnel tests were performed to determinethe two dimensional aerodynamic characteristics of the 14 1 %thick modified quasi-elliptical airfoil section NLR 7101 Themodification concerns the introduction of aft-camber in order toobtain rear loading The tests were conducted in the NLR PilotTunnel at Mach numbers ranging from 03 to 0825 at anglesof attack up to maximum lift The Reynolds number based onthe chord was about two million at the design condition Lift,drag, and pitching moment coefficients are presented andoff-design characteristics in terms of drag divergence onset ofrear separation lift divergence and maximum lift are discussed

Author (ESA)

N77-30095# Techmsche Hochschule. Darmstadt (West Ger-many) Inst fuer FlugtechmkSYSTEMATIC PRESSURE DISTRIBUTION AND FORCEMEASUREMENTS OF TWO YAWED SLENDER WINGS[SYSTEMATISCHE DRUCKVERTEILUNGS- UND KRAFTMESSUNGEN AN ZWEI SCHIEBENDEN SCHLANKENFLUEGELN]Bernhard Wagner 9 Feb 1976 125 p refs In GERMANSponsored by Deut Forschungsgememschaft(IFD-2/76/I) Avail NTIS HC A06/MF A01

Pressure distribution and force measurements were carriedout on two thin slender wings over a wide yaw and angle ofattack range in a wind tunnel The main object of the investigationswas a comparison of the linear slender wing theory withmeasurements at small angle of attack especially for the caseof a vortex sheet coming from a lateral edge during yawedflight Measurements were also earned out at larger angles ofattack in order to prepare test results for a possible transfer ofthe aspiration force analogy to arbitrary wing forms and to yawedwings ESA

N77-30096# Techmsche Hochschule, Darmstadt (West Ger-many) Inst fuer FlugtechmkA METHOD FOR CALCULATING FLOW AROUND A YAWEDSLENDER WING AT SMALL ANGLE OF ATTACK [EINVERFAHREN ZUR BERECHNUNG DER STROEMUNG UMSCHIEBENDE SCHLANKE FLUEGEL BEI KLEINER ANSTEL-LUNG]Bernhard Wagner 29 Feb 1976 63 p refs In GERMAN(IFD-4/76) Avail NTIS HC A04/MF A01

An extension of Jones' slender wing theory is proposed,which takes into account a vortex sheet coming from a lateraledge during yawed flight The integral equation for the vorticityof the wake region is solved stepwise by descretization Formulasare developed for the vorticity, pressure distribution, andaerodynamic coefficients of slender wings of arbitrary planformThe limiting case of the infinitely long yawed wing is consid-ered separately ESA

N77-30097# Techmsche Hochschule, Darmstadt (West Ger-many) Inst fuer FlugtechmkSOME QUADRATURE METHODS FOR LIFTING WINGTHEORY [UEBER EINIGE QUADRATURVERFAHREN FUERDIE TRAGFLUEGELTHEORIE]Xaver Hafer and Bernhard Wagner 1977 28 p refs InGERMAN(IFD-5/76) Avail NTIS HC A03/MF A01

A method is described for the quadrature in span widthdirection which employs the properties of orthogonal polynomialssimilar to the method of Multhopp and Van de Vooren Thequadrature is also executed over each half span width Theeffectiveness of the method was investigated by samplecalculations for the extended lifting line theory ESA

N77-30099| Naval Postgraduate School. Monterey, CalifSTATISTICAL ANALYSIS OF US NAVY MAJOR AIRCRAFTACCIDENT RATES. PILOT AND AIRCRAFT TIME-DEPENDENT VARIABLES M S ThesisAbdur Rashid Mar 1977 63 p refs(AD-A040096) Avail NTIS HC A04/MF A01 CSCL 01/2

Aircraft accident rates by month were analyzed for random-ness, cyclic pattern or increasing/decreasing trends for all attack,fighter and propeller type aircrafts The technique of Runs testwas employed to the runs above and below the median Theanalysis of pilot/aircraft time dependent variables was alsodone for both accident and non-accident pilots/aircrafts Thehypothesis tested was. the accidents per hundred pilots/aircraftswere the same for each category of pilot/aircraft variable Thechi square one sample test, the chi square test for K independentsamples and the Mann-Whitney U test were used for the analysisThe aircrafts considered for the analysis of pilot variables wereA-4, A-7 and F-4, and the aircraft considered for the analysisof aircraft variable was F-4 Author (GRA)

N77-30100# BioTechnology. Inc Falls Church. VaFORMAT PRACTICES FOR DOCUMENTING TIME CRITI-CAL HARZARDOUS PROCEDURES Final ReportTheodore J Post Jun 1976 32 p refs(Contract N00014-72-C-0101)(AD-A036369) Avail NTIS HC A03/MF A01 CSCL 01/3

The report relates to a study to determine whether reformat-ting relevant sections of the pilots Naval Air Training andOperating Procedures Standardization manual was a feasiblemeans of improving the success achieved in ejecting from disabledaircraft GRA

N77-30101*# Ohio Univ. Athens Dept of ElectricalEngineeringINTERACTIVE LORAN-C TO GEOGRAPHIC AND GEO-GRAPHIC-TO-LORAN-C COMPUTATIONLynn M Piecuch and Robert W Lilley Aug 1977 6 p refs(Grant NGR-36-009-017)(NASA-CR-153985. TM-52) Avail NTIS HC A02/MF A01CSCL 17G

The LORAN program is stored in CMS disk files for use byAvionics Engineering Center terminal users A CMS EXEC filenamed LORAN controls program operation The user types LORANand the program then prompts for data input and producesoutput on the terminal The FORTRAN program refers to a diskfile of LORAN master data giving station locations, coding delays,repetition rate and station pair identification letters For Geograph-ic-to-LORAN conversion, no iterative computations are required,the program is a straightforward coordinate conversion basedupon the techniques descnbed by the Navy For LORAN-to-Geographic conversion, the original Navy program required adead-reckoned position, near the actual unknown fix, to begincomputations No iteration was performed to obtain the LORANfix. but internal program errors occurred at execution time if thedead-reckoned fix were displaced from the actual fix by morethan a few minutes of latitude or longitude In order to enhanceusefulness of the program for the terminal user an iterativeroutine was added which allows a single dead-reckoned positionto be entered from the master data file for each LORAN chainThe results compare exactly with the LORAN-C navigation chartand provide adequate benchmark data for general aviation flightplanning and data analysis Author

N77-30102# National Bureau of Standards, Washington. D CInst for Basic StandardsVISUAL RANGE CONCEPTS. INSTRUMENTAL DETERMIN-ATION. AND AVIATION APPLICATIONSC A Douglas and R L Booker Jun 1977 362 p refsSponsored by the FAA(NBS-Mono-159 LC-77-7343) Avail NTIS MF A01. SODHCS500

Principles procedures and instruments used in the measure-ment of visual range are reviewed The fundamental conceptsof the visual range of objects and lights are discussed Operationalaspects of the several classes of atmospheric attenuation meters

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are reviewed and representative instruments are described Thedevelopment of the NBS transmissometer its validation andapplication to aviation operations is presented An error analysisis made of the effects of instrument errors and of differences inobserver thresholds on visibility measurements A chronologicalreview of the development and application of the runway visualrange concept is included together with a discussion of cloudheight measurements Author

N77-30103# Missouri Univ. Rolla Dept of ElectricalEngineeringNAVIGATION CHECKPOINTING USING HORIZON COR-RELATION Final Report. 1 Mar 1975 - 28 Feb 1977Gordon E Carlson Apr 1977 30 p refs(Contract N00014-75-C-0639. NR Proj 387-076)(AD-A039946. CSR-77-5) Avail NTIS HC A03/MF A01 CSCL17/7

A summary of the analysis performed on the horizoncorrelation navigation checkpointing system is presented Thisincludes a brief description of the system concept and the analysistechniques used The tradeoff and performance results aresummarized and indicate that the theoretical feasibility of thesystem has been established Author (GRA)

N77-30104# Sandia Labs. Albuquerque, N MexSIMULATION OF INERTIAL INPUTS TO A STRAPDOWNPLATFORM FOR INERTIAL GREAT CIRCLE TRAJECTO-RIESFarrell J Perdreauville Jan 1977 28 p refs(Contract EI29-D-789)(SAND-76-0620) Avail NTIS HC A03/MF A01

Equations are developed for computing mertial accelerationsand angular rates that would be measured by the accelerometersand gyroscopes in a strapdown mertial platform The accelerationsand angular rates are computed for a body that is moving in anmertial great circle trajectory A FORTRAN computer code whichimplements the calculations is listed ERA

N77-30105# Deutsche Forschungs- und Versuchsanstalt fuerLuft- und Raumfahrt. Brunswick (West Germany) lost fuerFlugfuehrungMONTE CARLO SIMULATIONS OF VOR/DME HOLDINGPROCEDURES BASIC IDEAS AND APPLICATIONSHolger Schnuerer 17 Mar 1977 25 p refs In GERMAN,ENGLISH summary Report will also be announced as translation(ESA-TT-419)(DLR-FB-77-08) Avail NTIS HC A02/MF A01. DFVLR CologneDM 1370

Using DME in addition to VOR allows a better use of theairspace for holding procedures in civil aviation As yet thereare no procedures for the construction of the airspace to bereserved for a safe execution of these holding procedures, whichhave been agreed by the international authorities A method forthe construction of holding areas of different probabilities isdescribed, where the simulation of flight paths in a computerusing the Monte-Carlo technique has a special importance Thesimulation allows the application of an extensive and detailederror model In addition the locally different physical conditionsmay be taken into consideration Both factors are most importantfor a safe and economical use of the airspace Author (ESA)

N77-30106# Naval Postgraduate School Monterey CalifINTRODUCTORY INVESTIGATION OF THE RANGEMEASURING SYSTEM/DATA COLLECTION SYSTEM(RMS-2/DCS) M S ThesisWilliam F H Berthiaume Mar 1977 62 p refs(AD-A039921) Avail NTIS HC A04/MF A01 CSCL 17/7

Various aspects of the operation of the Range MeasuringSystem/Data Collection System (RMS-2/ DCS), which isemployed by the United States Army Combat DevelopmentsExperimentation Command (USACDEC) at the Hunter LiggettMilitary Reservation California were investigated Systemdevelopment, operation and reliability were summarized and twoproblem areas associated with RMS-2/ DCS identified

Author (GRA)

N77-30107*# LTV^ Aerospace Corp Dallas, Tex VoughtSystems DivF 8 OBLIQUE WING STRUCTURAL FEASIBILITY STUDYE Koltko, A Katz, M A Bell W D Smith R Lauridia, C TOverstreet, C Klapprott T F Orr C L Jobe, and F G WyattNov 1975 151 p refs(Contract NAS4-2266)(NASA-CR-154841, Rept-2-57000/5R-3239) Avail NTISHC A08/MF A01 CSCL 01C

The feasibility of fitting a rotating oblique wing on an F-8aircraft to produce a full scale manned prototype capable ofoperating in the transonic and supersonic speed range wasinvestigated The strength, aeroelasticity, and fatigue life of sucha prototype are analyzed Concepts are developed for a newwing a pivot a skewing mechanism, control systems that operatethrough the pivot and a wing support assembly that attachesin the F-8 wing cavity The modification of the two-place NTF-8Aaircraft to the oblique wing configuration is discussed Author

N77-30108# Naval Air Test Center, Patuxent River, MdA PROGRAM FOR INCREASED FLIGHT FIDELITY INHELICOPTER SIMULATIONC Woomer and D Carico 27 Apr 1977 22 p refs(AD-A039324, NATC-TM-77-1-RW) Avail NTISHC A02/MF A01 CSCL 14/2

Increased emphasis has been placed on the need for andusefulness of major aviation training devices - flight simulatorsA description of a modern trainer and the status of currentsimulation is provided High fidelity is necessary to achieve hightraining transfer to the aircraft The authors describe the needfor and a proposed basic approach to technical simulator flighttesting designed to achieve high fidelity Ideas were formulatedas a result of the authors participation in the development andvalidation of the SH-2 F Weapons System Trainer Device 2F106 Navairtestcen participates in the program as a technicaladvisor on flight fidelity Major contributions are aircraft testingfor the establishment of criteria data followed by simulatorevaluation both performed by engineering test pilots and flighttest engineers These evaluations used established and disciplinedflight test techniques and should be common place in thedevelopment and validation of flight trainers An extensive tableof criteria data tests is provided for reference Typical instrumenta-tion tables for both the aircraft and trainer are includedSpecific comments are made concerning trainer testing problemsand the priorities of tests A discussion is included on simulatordata gathering techniques appropriate parameters and equipmentneeded The scope of a visual system evaluation is presented,along with a description of its usefulness in additional testingof the basic trainer Author (GRA)

N77-30109# Naval Postgraduate School Monterey. CalifENERGY MANAGEMENT DISPLAY FOR AIR COMBATMANEUVERING M S ThesisStuart Robinson Powne Mar 1977 90 p refs(AD-A040198) Avail NTIS HC A05/MF A01 CSCL 01/4

A skill and task analysis of air combat maneuvering wasperformed This analysis indicated that a device to aid the pilotto maneuver the aircraft to its aerodynamic limits might be useful,but such a device might be ineffective due to a high level ofsensory saturation The concept for design of the project waspredicated upon projected use of future displays for fighter aircraftin air combat maneuvering, pilot training and flight safetyaspects The test energy maneuverability display was designedusing a microprocessor for dedicated control The display formatwas based on color coding various specific power regions andpresenting them in the pilot s peripheral vision An experimentwas designed and executed to determine if the pilot could respondto the specific power color codes and maintain performance ofcritical pilot tasks An analysis of test variance indicated nosignificant degradation of pilot performance with the introduction

, of color coding to the peripheral vision Author (GRA)

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N77-30110# Rock Island Arsenal, III General Thomas JRodman LabAIRCRAFT GUN ICING EVALUATIONMax L Coppock and Merrill D Gerke Jan 1977 135 p(AD-A039834. RIA-R-TR-77-021) Avail NTISHC A07/MF A01 CSCL 19/6

This report discusses the results of icing tests conducted onthe M28A1 Turret the 762mm M134 Gun the 40mm. M129Grenade Launcher and the 20mm, M195 Gun The results indicatethat all of the weapons can be fired without catastrophic damageafter accumulating as much as 1 1/4 inches ice on the muzzleThe use of gas deflectors and/or flash suppressors allow theweapons to be fired without any damage occurring from iceaccumulation of up to 1 1/4 inches The turret suffered onlyminor limitations of movement when coated with 1 1/4 inchesof ice The extreme limits of elevation could not be attaineddue to ice jamming the stops but about 85 percent of theexcursion distance was operable A build-up of over 3/8 inchesof ice on one side of the turret will limit the azimuth movementin one direction only A heavy ice build-up cannot pass theclose gap between turret and aircraft fairing behind the turretThis situation can be prevented by pointing the guns into thewind causing the ice build-up to be on the front turret surface

Author (GRA)

N77-30111# Naval Postgraduate School Monterey, CalifDECISION-MAKING AND OPTIMIZATION IN AIRCRAFTDESIGNUlnch Haupt Feb 1977 61 p refs(AD-A039464 NPS-67HP77021 A) Avail NTISHC A04/MF A01 CSCL 01/2

The state of the art in aircraft design is surveyed with regardto the decision-making process It is shown that the empiricalapproach to decision-making as it is generally practiced inhardware design has inherent limitations There is an increasingneed to consider uncertainties and preferences explicitly Thisleads to a new design outlook combining the experience of old-timedesigners with an analytical approach to complex problems Anoutline is given for the development of practice-oriented textmaterial as a most essential step toward preparing engineersfor new tasks in design and decision-making Author (GRA)

N77-30112# Naval Air Test Center Patuxent River MdTHE DEVELOPMENT OF PRIMARY EQUATIONS FOR THEUSE OF ON-BOARD ACCELEROMETERS IN DETERMININGAIRCRAFT PERFORMANCEW R Simpson 19 Apr 1977 28 p refs(AD-A039174. NATC-TM-76-3-&M, Avail NTISHC A03/MF A01 CSCL 01/1

Primary equations for the use of on-board accelerometerdata (both flight path and body mounted) for determining aircraftperformance are developed Primary equations are thosemathematical relationships which relate measured quantities touseful parameters They are distinguished from secondary andanalysis equations in that the latter are used to either standardizeor separate effects in the data Reference materials are cited,or methods are presented for obtaining all parameters necessaryin the use of the primary equations In cases where sufficientreference materials are not available, the equations are derivedAn equation summary is presented for the user who does notwish to go through the development procedures Author (GRA)

N77-30113| Naval Ship Research and Development Center.Bethesda. Md Ship Performance DeptSEAKEEPING CHARACTERISTICS OF A PRELIMINARYDESIGN FOR A SEA LOITER AIRCRAFTAlvin Gersten Jose Bonilla-Norat, and Lawrence Murray Feb1977 137 p refs(AD-A040062, SPD-748-02) Avail NTIS HC A07/MF A01CSCL 01/3

A model of a proposed sea loiter aircraft has undergoneexperiments in the hullborne model at various headings to regularand random waves The principal goal of the investigation wasto provide data for evaluating the habitabihty characteristics of

this concept The results will also be used to validate computerpredictions Transfer functions are presented in this report, asare plots and tables of standard deviation values and significantvalues of vehicle response in a seaway The effect on motionsof varying model weight and the effectiveness of dampingplates in reducing motions are discussed In general, neither ofthese is found to significantly alter the unusual transfer functionsobtained for this craft The motions of a buoy, whose configurationwas selected to provide wave surface following characteristicsand which was also subjected to waves in the towing tank arediscussed in an appendix Author (GRA)

N77-30114# Naval Weapons Center China Lake, CalifGATOR/AV-8A ENVIRONMENTAL CAPTIVE FLIGHTVIBRATION RESPONSE TESTS Final Report. Oct 1974 -Jan. 1976K T Katsumoto and W W Paramenter Feb 1977 104 p(AD-A036498 NWC-TP-5883) Avail NTIS HC A06/MF A01CSCL 01/3

A series of flights using an AV-8A aircraft and the GATORweapon (Navy version Mk 7 dispenser) were made Vibrationand acoustic responses were measured for this externally carriedordnance during typical flight conditions Acceleration powerspectral density plots are presented and test levels arerecommended GRA

N77-30115# Auburn Univ Ala Engineering ExperimentStationAUTOMATIC TARGET HAND-OFF USING CORRELATIONTECHNIQUES Final Report. 5 Dec 1975 - 31 Jan 1977J S Boland III, L J Pnnson, G R Kane, M A Honnell, andE G Peters 31 Jan 1977 145 p refs(Contract DAAH01-76-C-0396)(AD-A036435) Avail NTIS HC A07/MF A01 CSCL 17/8

The problem of automatic hand-off of a target from a precisionpointing and tracking system (PTS) to an imaging missile seekeris considered in this report The approach taken is to search forthe target in the seeker field of view (FOV) using the PTS videoas a reference When the target is located the seeker line ofsight is adjusted automatically such that the target is at thecenter of its FOV at which point the seeker tracker can lock onto the target Location of the target in the seeker FOV can bestbe accomplished using correlation techniques The approachtaken is to consider the most accurate but yet most costly incomputation time and hardware requirements Tradeoffs are thenconsidered in order to obtain a real-time correlator (i e onewhich can compute the correlation surface at the rate of theincoming live video from the seeker) The effect of these trade-offson correlation accuracy and other system performance criteria isgiven A correlation algorithm is chosen and an implementationof this algorithm is given An alternate implementation usingan analog adoer rathe, than a digital adder tree is recom-mended GRA

N77-30116# Bolt, Beranek. and Newman. Inc Cambridge, MassDEVELOPMENT OF PROTOTYPE OPTICAL CONVOLUTIONAIRSPEED SENSOR Final Report. Jan - Sep 1976Michael J Rudd Wright-Patterson AFB, Ohio AFFOL Jan1977 89 p refs(Contract F33615-76-C-3051. AF Proj 1987)(AD-A039469. BBN-3380. AFFDL-TR-76-132) Avail NTISHC A05/MF A01 CSCL 01/4

This report describes the continued development of the OpticalConvolution Airspeed Indicator This relatively inexpensiveinstrument measures true airspeed by projecting a shadowgraphimage of the wake from a small heater onto grating and measuringthe ripple frequency of the turbulence crossing the gratingMeasurements were made on the structure of the turbulent wakeso that the heater size and grating can be optimized A newtype of signal processor called a correlation discriminator, wasdeveloped to measure the frequency of the signal in the presenceof a large amount of noise An active heater protection circuitwas built to prevent it from burning out when there is no airflow The effects of environmental conditions on the sensor

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were examined and they can all be met although the effects ofrain and icing require further study A new improved PrototypeMark 2 was built and tested There were significant changesin reading at angles of attack and sideslip above 10 to 15 deg

GRA

N77-30117# Naval Postgraduate School. Monterey, CalifAM EVALUATION Of A RASTER SCAN DISPLAY FOR USEIN AN AIRCRAFT INFORMATION HANDLING SYSTEMM S ThaoioWalton Lewis Hogan, Jr Mar 1977 99 p refs(AO-A039652) Avail NTIS MF A01 CSCL 09/2

The work described herein was part of continuing researchin the area of computer aided information management and displayas applied to air operations on an aircraft carrier The purposeof this study was to evaluate the Hughes CONOGRAPHIC-12Graphics Display Terminal in a computer graphics-aided aircraftinformation handling system The approach taken in this studywas to implement a realistic aircraft information handling systemon a Digital Equipment Corporation PDP-11/50 minicomputerwithin the conventions of the C programming language and theUNIX operating system at the Naval Postgraduate SchoolComputer Laboratory The study includes a description of previousefforts in the area, a description of the CONOGRAPHIC-12hardware and the software written to evaluate the display terminalThe study also includes an evaluation of the CONOGRAPHIC-12display terminal as both a dynamic interactive display terminaland a repeater-only terminal at six representative stations

Author (GRA)

N77-30118# Vought Corp. Dallas. TexMASTER MONITOR DISPLAY APPLICATIONS STUDY FORTHE A-7E Final Raport. Rflor 1973 - Jon 1S77R H Sanderlm and P E Greer Jan 1977 82 p(Contract N62269-76-C-0198)(AD-A039882. Rept-2-57110-TR-3367. NADC-77075-30)Avail NTIS HC A05/MF A01 CSCL 01/4

A study program to define the conceptual requirements andimplementation schemes for the incorporation of a Master MonitorDisplay (MMD) into an A-7E has been completed The studyidentifies the candidate functions for display on the MMD thatwere selected from the existing A-7E cockpit functions, defineswhat is to be displayed on the MMD corresponding to the currentwarnings, cautions, advisories and auxiliary data with referenceto flight modes, and defines the implementation interfacerequirements The study results reported in this document verifythe feasibility of utilizing the integrated display concept in anA-7E aircraft to replace certain cockpit functions presentlyperformed with dedicated indicators and instruments

"Author (GRA)

N77-30119*# Naval Air Propulsion Test Center, Trenton. NJROTOR BURST PROTECTION PROGRAM EXPERIMENTA-TION TO PROVIDE GUIDELINES FOR THE DESIGN OFTURBINE ROTOR BURST FRAGMENT CONTAINMENTRINGS Final Roport. 1 1972 - 1978G J Mangano. J T Salvmo, and R A De Lucia Mar 197753 p refs(NASA-CR-135166. NAPTC-PE-98) Avail ' NTISHC A04/MF A01 CSCL 21E

The results of a program of rotor burst containmentexperimentation that provides guidelines for the design of optimumweight turbine rotor disk fragment containment rings arepresented The guidelines were derived by establishing therelationships between a measure of the ring's capability to containfragment energy with respect to it s weight and other significantring and rotor variables such as the (1) rotor tip diameter (2)number of rotor fragments, and (3) ring radial thickness andaxial length The experiments consisted mainly of bursting 14and 31 inch diameter turbine rotors into encircling containmentrings made from centnfugally cast 4130 steel Rules are givenfor achieving optimum weight ring designs Author

N77-30120# Rockwell International Corp, Columbus. OhioAircraft DivFLIGHT TEST OF AN 8000 poi LIGHTWEIGHT HYDRAULICSYSTEM (LHS) Final Roport, 23 Jun 1373 - 23 Apr 1977Joseph N Demarchi and Robert K Hanmg Apr 1977 88 prefs(Contract N62269-76-C-0254)(AD-A039717. NR77H-21. NADC-77098-30) Avail NTISMF A01 CSCL 13/7

An 8000 psi hydraulic lateral control system was installedin a T-2C airplane Four pilots evaluated the test installation,accumulating 115 flight hours Operational characteristics werevery similar to the original 3000 psi system The 8000 psiinstallation functioned exceptionally well Successful completionof this project confirmed that 8000 psi lightweight hydraulicsystems can be designed, fabricated, and maintained withoutspecial techniques or state-of-the-art advances Author (GRA)

N77-30121# Detroit Diesel Allison Indianapolis, IndAN EXPERIMENTAL INVESTIGATION OF A SUBSCALEVARIABLE PRESSURE RATIO HIGH THRU FLOW TURBINEFinal Technical Report, Jan - Doc. 1973D J Helton, H G Lueders. and J R Arvm Wright-PattersonAFB Ohio AFAPL Feb 1977 91 p(Contract F33615-76-C-2068. AF Proj 3066)'(AD-A039823L. AFAPL-TR-77-7) Avail NTISHC A05/MF A01 CSCL 21/5

This program investigates the aerodynamics of a subscalemodel of a variable pressure ratio high through flow turbineThe problem areas are small limit loading margin. High rotorrelative inlet Mach number, low aspect ratio bladmg. large rotorturning and low hub/tip radius ratio GRA

N77-30122# Aeronautical Systems Div . Wright-Patterson AFB.OhioAN ATTEMPT TO CORRELATE NORMAL VORTICITIESWITH TOTAL PRESSURE DISTORTION PATTERNS AT THEENTRANCE TO A GAS TURBINE ENGINE Final Report.Jun 1974 - Aug 197SStephen M Clark Feb 1977 89 p refs(AD-A040370. ASD-TR-76-34) Avail NTIS HC A05/MF A01CSCL 21/5

An attempt is made to predict the worst-case pressuredistortion produced by a distortion screen at the entrance to agas turbine engine using only steady-state total pressuremeasurements The vector sum of radial and circumferentialvorticity, called normal vorticity is compared to both thedifference between steady-state and worst-case distortionpatterns, and the standard deviation of the high response pressuremeasurements called turbulence Average values of turbulenceand vorticity are found to be unrelated to the increase in distortionbetween steady-state and worst-case pressure measurementsProbe-by-probe analysis of the data indicates that a correlationmay exist between vorticity and the distortion increase Althougha final prediction technique is not developed, an improved testprogram and refined data analysis techniques are outlined

Author (GRA)

N77-30124# Naval Research Lab Washington. D CQUANTITATIVE TLC ANALYSIS OF AMINE ANTIOXIDANTSIN HIGH-TEMPERATURE JET ENGINE LUBRICANTSPaul J Sniegoski Apr 1977 9 p refs(AD-A039909, NRL-MR-3490) Avail NTIS HC A02/MF A01CSCL 11/8

A quantitative thin-layer chromatography (TLC) method witha relative standard deviation of four percent is described for theanalysis of commonly used amme anttoxidants in high-temperaturejet engine lubricants The method is convenient in that afterdevelopment of the plates, the components develop characteristicvisible colors suitable for analysis Author (GRA)

W77-30125# Naval Air Engineering Center. Lakehurst. N JGround Support Equipment Dept

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NON-INTEGRATED GAS TURBINE cMGINE DIAGNOSTICSTRADEOFF ANALYSIS Final Technical Report. Jul 1976 -Jul. 1976H C MacLaughlm 10 May 1977 93 p refs(AD-A039494. NAEC-GSED-100) Avail NTISHC A05/MF A01 CSCL 21/5

Diagnostic equipment and techniques to be included in anon-integrated system to detect and isolate the four must prevalentmalfunctions in Navy aircraft gas turbine engines were selectedEach of twenty-five candidate elements were considered on thebasis of technical feasibility, cost-effectiveness and diagnosticneed Gas path analysis, with trending, and borescope inspectionwere selected as the most effective methods to diagnose theleading engine malfunctions (63%), foreign object damage andhot section distress Other elements to be included in the proposedembryonic system are called oil analysis, time temperaturerecording indicator/low cycle fatigue counters vibration testerstrim testers test system vibration equipment, vibration signalanalysis equipment, temperature sensing system tester, and JetcalAnalyzer Oil analysis techniques being developed indicate asignificant improvement compared to spectrometnc analysis ofdiagnostic purposes A summary of specific elements for utilizationat each of three levels of maintenance and an -engineeringdevelopment plan with proposed implementation milestones areincluded Author (GRA)

N77-30126# Air Force Inst of Tech . Wright-Patterson AFB,Ohio School of EngineeringPARAMETRIC PERFORMANCE EVALUATION OF A JETENGINE DERIVED FROM A TURBOCHARGERM S. ThesisRichard B Brown Mar 1977 119 p(AD-A039116, AFIT/GAE/AE/76D-2) Avail NTISHC A06/MF A01 CSCL 21/5

Previous conceptual studies have shown that it is feasibleto construct a low-thrust, jet engine, based on a productionturbocharger at relatively low cost A parametric evaluation wasperformed on a turbojet engine derived from an AiResearch1 5 lb(m)/sec airflow turbocharger unit to determine its staticperformance characteristics and the maximum attainable thrustwithout augmentation or major component modification Theperformance of various turbine housing/nozzle combinations wasmeasured in steady state operation using a much improvedinstrumentation system, together with various system improve-ments Parameters were measured on a common time base andplotted to depict the total performance of the unit over itsusable range Maximum thrust obtained was 97 Ib(f). exceedingthe initially predicted theoretical value of 67 lb(f) by 45% Datawas reduced to coded 3 digit numbers for programming andplotting using the CDC 6600 computer The results were machineplots depicting the performance characteristics of the unaugmen-ted engine for use in further studies including augmentation Inaddition, computer performance programs for coded raw datawere written for future data reduction and analysis

Author (GRA)

N77-30128 Purdue Umv , Lafayette IndEFFECTS OF CONTROL LAWS AND RELAXED STATICSTABILITY ON VERTICAL RIDE QUALITY OF FLEXIBLEAIRCRAFT PhD ThesisPhilip Arnold Roberts 1976 112pAvail Umv Microfilms Order No 77-7522

Ride quality is shown to be relatively invariant under variouspopular control laws Handling quality variations are shown tobe major contributors to ride quality variations on both vehiclesRelaxed static stability is artificially implemented on the studyvehicles to investigate its effects on ride quality The B-52Hride quality is generally degraded when handling characteristicsare automatically restored by a feedback control to the originalvalues from relaxed stability conditions The B-1 shows littleride quality sensitivity to the same analysis due to the smallrigid body contribution to load factors at the flight conditioninvestigated Dissert Abstr

N77-30129*# National Aeronautics and Space AdministrationAmes Research Center, Moffett Field Calif

ESTIMATES OF THE EFFECTIVENESS OF AUTOMATICCONTROL IN ALLEVIATING WAKE VORTEX INDUCED ROLLEXCURSIONSBruce E Tinlmg Aug 1977 15 p(NASA-TM-73267 A-7127) Avail NTIS HC A02/MF A01CSCL 01C

Estimates of the effectiveness of a model following typecontrol system in reducing the roll excursion due to a wakevortex encounter were obtained from single degree of freedomcomputations with inputs derived from the results of wind tunnel,flight and simulation experiments The analysis indicates thatthe control power commanded by the automatic system mustbe roughly equal to the vortex induced roll acceleration ifeffective limiting of the maximum bank angle is to be achieved

Author

N77-30132*fjl Systems Technology Inc. Hawthorne. CalifDEVELOPMENT OF AN INTEGRATED CONFIGURATIONMANAGEMENT/FLIGHT DIRECTOR SYSTEM FOR PILOTEDSTOL APPROACHES Final ReportRoger H Hoh. Richard H Klein, and Walter A JohnsonWashington NASA Aug 1977 90 p refs(Contract NAS2-6441)(NASA-CR-2883 TR-1015-4) Avail NTIS HC A05/MF A01CSCL 01C

A system analysis method for the development of anintegrated configuration management/flight director system forIFR STOL approaches is presented Curved descending decelera-ting approach trajectories are considered Considerable emph-asis is placed on satisfying the pilot centered requirements(acceptable workload) as well as the usual guidance and controlrequirements (acceptable performance) The Augmentor Wing JetSTOL Research Aircraft was utilized to allow illustration byexample and to validate the analysis procedure via mannedsimulation Author

N77-30134JJI Texas Umv . Austin Dept of AerospaceEngineering and Engineering MechanicsWIND TUNNEL EXPERIMENTS ON AN ACTIVELY CON-TROLLED. VARIABLE GEOMETRY FLUTTER MODELFinal Report. 1 Feb 1976 - 31 Jan 1977Jeff Long Mar 1977 109 p refs(Contract F44620-76-C-0072)(AD-A039216. AFOSR-77-0638TR) Avail NTISHC A06/MF A01 CSCL 20/4

A reduction in flutter margin can occur for variable geometryaircraft when the wing of the aircraft is swept into the vicinityof the tail Experiments on an aeroelastic wind tunnel modelwith active aerodynamic controls demonstrated that the fluttermargins of these configurations can be increased throughtechniques other than the standard structural modificationsImproved margins were attained experimentally by employingrapidly responding aerodynamic controls activated by an optimalfeedback Author (GRA)

N77-30135# Toronto Umv (Ontario) Inst for AerospaceStudiesA LABORATORY INVESTIGATION INTO FLIGHT PATHPERTURBATIONS DURING STEEP DESCENTS OF V/STOLAIRCRAFT Final Report. Sep 1972 - Jun 1976L D Reid. B Etkm H W Tenmssen, and P C HughesWright-Patterson AFB Ohio AFFDL Aug 1976 401 p refsSponsored in part by the Natl Res Council of Canada(Contract F33615-73-C-3013. AF Pro) 8219)(AD-A040101 AFFDL-TR-76-84) Avail NTISHC A18/MF A01 CSCL 01/2

A study into the prediction of V/STOL aircraft flight pathperturbations during steep landing approaches is presented Adiscussion of possible approaches to the problem is reviewedThe fixed probe approach, where two point space/time correlationsare measured in a boundary layer wind tunnel along the glideslope is derived is detail A second in the moving probe approachis which a suitable three component velocity probe is movedalong the glide slope in a boundary layer wind tunnel and the

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time history of the resulting measurements used to determinethe response of the aircraft A candidate moving probe apparatusis analyzed and its feasibility evaluated Two similar boundarylayer wind tunnels are used to generate simulations of theplanetary shear layer The properties of the 8 x 8 in tunnel aredescribed along with the associated instrumentation Author

N77-30136# Advisory Group for Aerospace Research andDevelopment Pans (France)A STUDY OF STANDARDIZATION METHODS FOR DIGITALGUIDANCE AND CONTROL SYSTEMSMay 1977 548 p refs(AGARD-AR-90, ISBN-92-835-1244-8) Avail NTISHC A23/MF A01

Standardization methods for digital guidance and controlsystems are examined, particularly with regard to data transmissiontechniques and high level programming languages Discussionof the general problems and techniques is included as well asreports on the particular experiences of the individual nationsAnnexes contain full details of the techniques studied and includecomparisons of data transmission methods and high levellanguages These comparisons are designed to outline the releventfeatures of the different techniques Author

N77-30180*# Boeing Commercial Airplane Co. Seattle WashDESIGN AND FABRICATION OF G R AP H ITE-EPOXYBOLTED WING SKIN SPLICE SPECIMENS Technical Report.Fob 1976 - May 1977R W Johnson and J E McCarty May 1977 54 p refs(Contract NAS1-14327)(NASA-CR-145216 06-44503) Avail NTISHC A04/MF A01 CSCL 11D

Graphite-epoxy bolted joint specimens were designed andfabricated These specimens were to be representative of aside-of-body wing skin splice with a 20-year life expectancy ina commercial transport environment Preliminary tests were

' performed to determine design values of bearing and net tensionstresses Based upon the information developed a three-fastener-wide representative wing skin splice was designed for a load of2627 KN/m (15 000 Ibf/m ) One joint specimen was fabricatedand tested at NASA The wing skin splice failed at 106 percentof design ultimate load This joint design achieved all staticload objectives Fabrication of six specimens together with theirloading fixtures was completed and the specimens were deliveredto NASA-LRC Author

N77-30221# Aeronautical Research Council, London (England)Structures DeptEFFECT OF INTERSPERSED PERIODS OF HEATING ONFATIGUE CRACK INITIATION AND PROPAGATION INCM001 (RR58) CLAD SHEETF E Kiddle Jul 1976 33 p refs Supersedes RAE-TR-76092and ARC-37041(AD-A041014 ARC-CP-1366 RAE-TR-76092 ARC-37041)Avail NTIS HCA03/MFA01 CSCL 11/6

Fatigue tests have been conducted to study the effect ofinterspersed periods of heating on the initiation and early growthof cracks from holes in clad sheet and also on later stages ofcrack propagation The tests were under flight simulation loadingand the material was CM001 (RR58) clad aluminium alloy sheetInterspersed heating reduced the lives tn initiate and grow cracksto 2mm and this is attributed to the softening of strain hardenedmaterial at the crack tip. but no effect was observed for longercrack lengths When load was applied during the periods ofheating creep redistribution of local stress retarded the growthof short and long cracks Further work is underway to investigatefatigue-heat interactions under different load-temperaturesequences, other forms of material and over a wider range ofcrack lengths Author (GRA)

N77-30249# Boeing Commercial Airplane Co Seattle, WashEXPLORATORY OF DEVELOPMENT OF DURABILITY OFADHESIVE BONDED JOINTS Final Report. 1 Fob 1974 -Oct. 1976

J A Marceau and J CyMcMillan Oct 1976 160 p refs(Contract F33615-74-C-5065 AF Proj 7381)(AD-A039864, D6-41317-2. AFML-TR-76-173) Avail NTISHC A08/MF A01 CSCL 1 1/4

The objectives of the program were to evaluate stresseddurability test methods to use these methods to test adhesivebonding materials and processes and to develop a correlationbetween laboratory test results and in-service performance Thetest method evaluation was completed early in the program andresults were published in an interim technical reportAFML-TR-75-3. Durability of Adhesive Bonded Joints February1975 Four stressed durability test methods were selected forthe test program (1) A thick-adherend lap-shear specimen(Mode I and Mode II loading) (2) A thick-adherend doublecantilever beam (DCB) specimen (Mode I loading), (3) A thinadherend DCB specimen (wedge test. Mode I loading) and (4)A thick adherend single cantilever beam (SCB) specimen forhoneycomb sandwich evaluation (Mode I and Mode II loading)Alloy adherend surface treatment adhesive primer and adhesiveinteractions were evaluated The materials and processes usedwere (1) Alloys 2024-T3 2024-T3 clad (1230 alloy) 7075-T6,and 7075-T6 clad (7072 alloy) (2) Adhesives FM 123-2and EA 9628 250 F curing adhesives and AF 143 and PL729-3 350 F curing adhesives (3) Primers BR 123 non-corrosion-mhibiting primer. BR 127 corrosion-inhibiting primer,and EC 3917 and PL 728 corrosion-inhibiting primers for usewith the two 350 F curing adhesives, (4) Adherend surfacetreatment processes Optimized FPL etch, chromic acidanodize and phosphoric acid anodize and (5) Aluminumhoneycomb core Standard core. Dura-Core and CR IIIcorrosion-resistant cores and phosphoric acid anodized core

GRA

N77 30261# RAND Corp, Santa Monica. CalifTHE POTENTIAL ROLE OF TECHNOLOGICAL MODIFICA-TIONS AND ALTERNATIVE FUELS IN ALLEVIATING AIRFORCE ENERGY PROBLEMS Interim ReportJ R Gebman. W L Stanley, J P Weyant, and W T MikolowskyDec 1976 170 p refs(Contract F49620-77-C-0023)(AD-A039597, R-1829-PR) Avail NTIS HC A08/MF A01CSCL 21/4

This report examines short- and long-term measures to reducethe consumption of petroleum jet fuels by the Air Force Engineretrofits and aerodynamic modifications to existing aircraft cansave significant quantities of jet fuel, however savings in fuelexpenditures are not enough to offset high initial costs of engineretrofits If accomplished early in an aircraft's life cycle, relativelylower costs of modest aerodynamic modifications may berecoverable through savings in fuel expenditures Synthetic JPfuels derived from oil shale or coal appear to be the most attractivefuture alternatives to petroleum jet fuels If the foreign oil cartelmaintains its price-setting effectiveness and synthetic fuelsindustry develops in the United States, development of an AirForce capability to interchangeable use fuels derived from crudeoil. oil shale or coal could be economically attractive and enhancethe Air Force's position in the jet fuel marketplace

Author (GRA)

N77-30301# Naval Ship Keseaich and Development CenterBethesda, Md Aviation and Surface Effects DeptPERFORMANCE PREDICTION METHOD FOR A WING-IN-GROUND EFFECT VEHICLE WITH BLOWING UNDER THEWING Final Report. Sep 1976 - Mar 1977David G Rousseau and Roger W Gallington Mar 1977 37 prefs(AD-A039829 DTNSRDC/ASED-379) Avail NTISHC A03/MF A01 CSCL 01/3

Recent efforts in theoretical analysis and experimentalobservations have moved the concept of power-augmented flightin ground effect toward practicality With the addition of liftand drag due to external airflow end-plate leakage, water skinfriction wave drag effects and wave clearance constraints aflow model can be made capable of effective comments Theanalysis shows that there are wave drag and wave clearance

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related limits to many aspects of the vehicle configuration Themost important of which are cruising height and aspect ratio inthat they have a very large effect on transport efficiencyUnfortunately the low flying high aspect ratio cases are ruledout due to wave impact problems Testing of a point designvehicle arrived at through the use of analysis such as the oneof this report needs to be performed as final verification of theaccuracy of the design procedure Author (GRA)

N77-30421# Analytical Methods Inc Bellevue WashINVESTIGATIONS OF THREE-DIMENSIONAL FLOWSEPARATION ON FUSELAGE CONFIGURATIONS FinalReport. May 1975 - May 1976Frank A Dvorak Brian Maskew and Frank A Woodward Mar1977 96 p refs(Contract DAAJ02-75-C-0036)(AD-A039382 USAAMRDL-TR-77-4) Avail NTISHC A05/MF A01 CSCL 20/4 —

A method is described for calculating the complete pressuredistribution on a body with separated flow Tne boundary layercharacteristics are calculated along several streamlines up tothe point where separation is predicted The separated flow ismodeled by streamwise panels of uniform vorttcity attached tothe body near the predicted separation line Comparisons arepresented of calculated and experimental pressure distributionsfor a cylinder a sphere and the B0105 fuselage The resultsare in fair agreement but there are certain features of the resultsand restrictions of the source/vortex mviscid model which needimprovement Author (GRA)

N77-30444*jjl Old Dominion Umv Research Foundation NorfolkVaSENSOR FOR MEASURING INSTANTANEOUS ANGLE OFATTACK OF HELICOPTER BLADES Progress Report. Jul1976 - Jul 1977P Stephen Barna and Henry W Liu Aug 1977 47 p(Grant NsG-1143)(NASA-CR-154808) Avail NTIS HC A03/MF A01 CSCL14B

Various research activities are reported in the following areas(1) improving and testing probes (2) theoretical studies of probemotion and (3) improving research facilities It is concludedthat a satisfactory solution to the problem of measuring angleof attack of helicopter blades may be found in the near future

Author

N77-30476# Boeing Commercial Airplane Co Renton WashAN EXTENDED PREDICTION MODEL FOR AIRPLANEBRAKING DISTANCE AND A SPECIFICATION FOR ATOTAL BRAKING PREDICTION SYSTEMS. VOLUME 2Final Report, Aug 1975 - Dec 1976M K Wahi. S M Warren and H H Straub Wright-PattersonAFB Ohio ASD Mar 1977 185 p(Contract F33657-74-C-0129)(AD-A039967 ASD-TR-77-6-Vol-2) Avail NTISHC A09/MF A01 CSCL 01/2

This report details the results from the sensitivity study portionof the Combat Traction II Phase II (Extended) Program andalso contains the calculations resulting from prediction equationformulation for the B-52 KC-135 and F-111 airplanes GRA

N77-30422| Textron Bell Aerospace Co duffaio N YNUMERICAL SOLUTION OF COMPLETE FLOWS AROUNDEXTERNAL STORES Final Report. Aug 1974 - Dec 1976Z Popmski W L Rushmore and S W Zelazny Dec 197673^ p refs(Contract F4460-75-C-0003)(AD-A039213 Rept-9236-927001 AFOSR-77-0621TR) AvailNTIS HC A04/MF A01 CSCL 20/4

A computer code, based on a finite element algorithm wasdeveloped to solve the governing equations for a three-dimensionalflow around a spnencally blunted cone at an angle of attackThe solution is valid for a boundary layer region including theflow separation in the cross-flow direction in the leeward areaThe required initial and boundary conditions for this solution areobtained from a finite difference computer program for laminarcompressible three-dimensional boundary layer flow Extensionof the analysis to include the turbulent transport using the mixinglength theory and a two-equation turbulence model is describedThe results demonstrate the capability of the finite elementmethod to predict the three-dimensional boundary region flowwith cross-flow separation in the leeward area and to modelthe effects of turbulent flow Author (GRA)

N77-3O439 Pennsylvania Umv, PhiladelphiaMICROWAVE HOLOGRAPHIC IMAGING OF AIRCRAFTWITH SPACEBORNE ILLUMINATING SOURCEPh D ThesisTomislav Angel Dzekov 1976 274 pAvail Umv Microfilms Order No 77-10158

The conceptual development of a method for providing highangular resolution and accurate angular position estimates forsurveillance and traffic control of aircraft is reviewed The methodis based on the use of a large random array of conformallylocated receiving elements and a CW microwave source locatedon a geostationary satellite In the vicinity of the earth s surfaceand above the array a roughly cylindrical volume of several hundredkilometers in diameter is illuminated The interference pattern ofthe direct signal from the satellite and the signals reflected fromaircraft in the illuminated volume is sampled by the arrayelements at discrete locations and then interrogated digitally toobtain useful target data Dissert Abstr

N77-30480# Sikorsky Aircraft Stratford ConnTHE 3000-HP ROLLER GEAR TRANSMISSION DEVELOP-MENT P R O G R A M VOLUME 6 RELIABILITY ANDMAINTAINABILITY REPORT Final ReportG F Gardner K R Cormier, and B Trustee Jan 1977 179 prefs(Contract DAAJ02-69-C-0042 DA Proj 1G1-62207-AA-72)(AD-A039381 USAAMRDL-TR-73-98F-Vol-6 UTRC/30974)Avail NTIS HC A09/MF A01 CSCL 13/9

This report presents a summary of the testing conductedduring the development of a 3000-HP Roller Gear TransmissionDuring this program a helicopter transmission using a 1985reduction ratio roller gear transmission was designed manufac-tured and subjected to extensive testing A reliability analysisshows that a fully developed roller gear transmission offerscomparable reliability to a conventional two-stage planetary unitHowever, relating the development testing of the roller geartransmission to project the reliability is premature at this stageThe analysis does show that on-condition maintenance of theroller gear transmission is feasible A summary of the testingand development of the roller gear transmission is includedDetailed reports on the design, manufacture, and bench andaircraft testing have been published separately Author (GRA)

N77-30481# Boeing Commercial Airplane Co Seattle WashTHE 3-D STRESS ANALYSIS OF A TURBINE BLADESFinal ReportC M Lewis R A Samuel and F Yen Mar 1977 86 p(Contract DAAG46-75-C-0072)(AD-A039176 D6-42735, AMMRC-CTR-77-14) Avail NTISHC A05/MF A01 CSCL 21/5

This report presents a demonstration of the usefulness ofthe ATLAS system in performing three-dimensional elastic stressanalysis of a turbine blade Modeling detaijs for a shroudeduncooled turbine blade are outlined and program execution anddata management techniques are discussed GRA

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N77-30905*# Bolt Beranek and Newman Inc Canoga ParkCalifCOHERENCE AND PHASE TECHNIQUES APPLIED TONOISE DIAGNOSIS IN THE NASA AMES 7 TIMES 10-FOOTWIND TUNNEL NO 1J F Wilby A G Piersol P E Rentz and T D Scharton 18 Jul1977 62 p refs(Contract NAS2-8382)(NASA-CR-152039. BBN-3559) Avail NTISHC A04/MF A01 CSCL 20A

Measurements have been made of coherence and phasespectra for the acoustic field in a subsonic wind tunnel Thedata are interpreted in terms of simple analytical models forpropagating and diffuse noise fields including the presence ofuncorrelated noise signals It is found that low frequency noisepropagates upstream and downstream from the fan with thenoise in the test section arriving in the upstream direction Highfrequency sound is generated in the test section and propagatesupstream and downstream In the low frequency range the ratioof diffuse to propagating energy is about eight for all locationsin the test section diffuser and settling chamber the value ofthe ratio increases with frequency Author

N77-3O9O6*# National Aeronautics and Space AdministrationAmes Research Center Moffett Field CalifACCURACY OF THE KIRCHOFF FORMULA IN DETERMIN-ING ACOUSTIC SHIELDING WITH THE USE OF A FLATPLATERalph E Gabnelsen and Joseph E Davis Aug 1977 20 prefs Prepared in cooperation with US Army Air Mobility Resand Develop Lab Moffett Field Calif(NASA-TM-73261 A-7111) Avail NTIS HC A02/MF A01CSCL 20A

It has been suggested that if get engines of aircraft wereplaced at above the wing instead of below it the wing wouldprovide a partial shielding of the noise generated by the enginesrelative to observers on the ground The shielding effects of anidealized three-dimensional barrier in the presence of anidealized engine noise source was predicted by the Kirchoffformula Based on the good agreement between experimentalmeasurements and the numerical results of the current study, itwas concluded that the Kirchoff approximation provides a goodqualitative estimate of the acoustic shielding of a point sourceby a rectangular flat plate for measurements taken in the farfield of the flat plate at frequencies ranging from 1 kHz to20 kHz At frequencies greater than 4 kHz the Kirchoffapproximation provides accurate quantitative predictions ofacoustic shielding Author

N77-30922(f Deutsche Forschungs- und Versuchsanstalt fuerLuft- und Raumfahrt Goettmgen (West Germany)THE CALCULATION OF FLOW FIELDS ABOUT THREEDIMENSIONAL BODIES IN HIGH ALTITUDE (FREE-MOLECULAR FLOW OF NEUTRAL ATOMS)Walter Wuest 26 May 1975 69 p refs In GERMAN ENGLISHsummary Translation was announced as N76-27969(DLR-FB-75-45) Avail NTIS HC A04/MF A01 DFVLRGoettmgen DM 32 30

On bodies with single molecular reflection (plane walls orsurfaces with convex curvature) in free molecular flow the localforces and the flow field can be calculated exphcitely On bodieswith multiple molecular reflection (e g surfaces with concavecurvature), where from one point of the surface another onecan be seen an interaction of the diffusely reflected moleculesoccurs which is calculated for some simple shapes Author

N77-31O05*# California Univ Berkeley Inst of GovernmentalStudiesINTERACTIONS OF TECHNOLOGY AND SOCIETY IM-PACTS OF IMPROVED AIRTRANSPORT A STUDY OFAIRPORTS AT THE GRASS ROOTSTodd La Porte Stephen Rosenthal, Stuart Ross. Kai N Lee andEdith Levme Washington NASA Jul 1977 396 p refs(Grant NGR-05-003-471)(NASA-CR-2871) Avail NTIS HC A17/MF A01 CSCL01E

The feasibility of applying a particular conception of technol-ogy and social change to specific examples of technologicaldevelopment was investigated The social and economic effectsof improved airport capabilities on rural communities wereexamined Factors which led to the successful implementationof a plan to construct sixty small airports in Ohio are exploredjnd implications derived for forming public policies evaluatingair transportation development and assessing technoloav Author

N77-31072*# National Aeronautics and Space AdministrationLangley Research Center Langley Station. VaA COMPARISON OF THE RESULTS OF DYNAMIC WIND-TUNNEL TESTS WITH THEORETICAL PREDICTIONS FORAN AEROMECHANICAL GUST-ALLEVIATION SYSTEM FORLIGHT AIRPLANESEric C Stewart and L Tracy Redd Washington Sep. 197747 p refs(NASA-TN-D-8521. L-11352) Avail NTIS HC A03/MF A01CSCL 01A

Dynamic wind tunnel tests have been conducted on a1/6-scale model of a general aviation airplane equipped withan all-mechanical gust alleviation system which uses auxiliaryaerodynamic surfaces to drive the flaps The longitudinal shortperiod motions were studied under simulated gust conditions inorder to verify the mathematical model used in a previous studyto predict the performance of tKe full scale system and determinethe amount of normal acceleration alleviation which could beattained The model responses were measured for differentconfigurations with the system active and without the systemactive for comparison The tests confirmed the general re-lationships between the experimental variables and the modelresponses predicted by the mathematical model, but there weresignificant differences in the magnitudes of the responses Theexperimental results for the model were used to estimate areduction of 30 percent in the rms normal acceleration responseof a similar full scale airplane in atmospheric turbulence Author

N77-31073/J/ Advisory Group for Aerospace Research andDevelopment. Pans (France)UNSTEADY AIRLOADS IN SEPARATED AND TRANSONICFLOWApr 1977 273 p In ENGLISH partly in FRENCH Presentedat the 44th Meeting of the AGARD struct and Mater Panel.Lisbon, 19-20 Apr 1977(AGARD-CP-226, ISBN-91-835-0197-7) Avail NTISHC A12/MF A01

The prediction and description of the separated flowenvironment and the essential effects of airframe response onindividual aircraft components is reviewed along with flutter,aeroelastic instabilities, and other static and dynamic aeroelasticproblems Analytical approaches, wind tunnel tests as well asflight test techniques are included

N77-31074))/ Hawker Siddeley Aviation Ltd. Kingston uponThames (England)UNSTEADY AIRLOADS IN SEPARATED AND TRANSONICFLOWC L Bore In AGARD Unsteady Airloads in Separated andTransonic Flow Apr 1977 9 p

Avail NTIS HC A12/MF A01The papers dealing with unsteady loads arising from separated

flow that were presented at the AGARD Fluid Dynamics Panel ssymposium on Prediction of Aerodynamic loading are reviewedThe principal topics discussed include dynamic phenomena ansmgfrom aircraft maneuvers transient dynamic stall loads, andmethods for predicting buffet Author

N77-31075*# National Aeronautics and Space AdministrationAmes Research Center. Moffett Field. CalifSEPARATED-FLOW UNSTEADY PRESSURES AND FORCESON ELASTICALLY RESPONDING STRUCTURESC F Coke, D W Riddle, and C Hwang (Northrop Corp,Hawthorne Calif) In AGARD Unsteady Airloads in Separated

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and Transonic Flow Apr 1977 25 p refs

Avail NTIS HC A12/MF A01 CSCL01CBroadband rms. spectral density, and spatial correlation

information that characterizes the fluctuating pressures and forcesthat cause aircraft buffet is presented The mam theme is toshow the effects of elasticity In order to do so. data are presentedthat were obtained in regions of separated flow on wings ofwind-tunnel models of varying stiffness and on the wing of afull-scale aircraft Reynolds number effects on the pressurefluctuations are also discussed Author

N77-31076# General Dynamics/Fort Worth. TexPREDICTION OF TRANSONIC AIRCRAFT BUFFET RE-SPONSEAtlee M Cunningham. Jr and David B Benepe. Sr In AGARDUnsteady Airloads in Separated and Transonic Flow Apr 197721 p refsAvail NTIS HCA12/MFA01

A method for predicting aircraft buffet response is brieflyreviewed Rigid wind tunnel model fluctuating pressure data areused to form buffet forcing functions to which airplane responsesare calculated with a mathematical dynamic model of the airplaneBuffet pressure data on the wing are used to estimate fluctuatingloads on the horizontal tail By including the extremes o'phasing and contributions of symmetric and antisymmetnc airplaneresponses, predicted upper and lower bounds are establishedThe method is applied to a variable sweep fighter aircraft andpredicted results are compared with flight test data The typesof buffeting flow considered for various wing sweep angles includeseparated and vortex flows as well as oscillating shocks Thecurrent method is compared with three other methods in thecorrelation with flight test data The inherent scatter of flightdata is discussed as well as probable sources of the scatter Amechanism is described by which wing torsional motion andshock oscillation couple to produce relatively severe buffetingconditions at a forward wing sweep The importance of consideringbuffet fatigue damage on secondary structure is discussed

Author

N77-31077# Royal Aircraft Establishment. Farnborough(England) Aerodynamics DeptTHE DYNAMIC RESPONSE OF WINGS IN TORSION ATHIGH SUBSONIC SPEEDSG F Moss and D Pierce In AGARD Unsteady Airloads inSeparated and Transonic Flow Apr 1977 21 p refs

Avail NTIS HCA12/MFA01The structural response of aircraft wings to aerodynamic

excitation at conditions appropriate to maneuvers at high subsonicspeeds is discussed Reference is made to wind tunnel experimentsusing models specially designed to deform under test in a realisticway as well as rigid models of conventional construction Theprimary torsion mode of vibration of the wings tended to bestrongly excited under some aerodynamic flow conditions onthe flexible models used, and in some cases the amplitude waslarge and similar to single-degree-of-freedom flutter in characterData from some flight tests is quoted to demonstrate that thistype of response may well occur in practice Author

N77-31078| Messerschmidt-BoelKow G m b H , Munich (WestGermany)EVALUATION OF VIBRATION LEVELS AT THE PILOT SEATCAUSED BY WING FLOW SEPARATIONJ Becker and K Dau (Vereimgte Flugtechmsche Werke-FokkerGmbH Bremen West Germany) In AGARD Unsteady Airloadsin Separated and Transonic Flow Apr 1977 28 p refs

Avail NTIS HCA12/MFA01Examples of the evaluation of vibration levels on the pilot

seat are presented The first deals with the results of low speedmeasurements on a strake wing model with and without flapand slats including the effect of leading edge blowing, in theincidence region 0 less than or equal to alpha less than or

equal to 90 deg The second example demonstrates the resultsobtained by the method based on measurements of fluctuatingpressures on rigid models for two configurations with 25 and45 degree wing sweep in the high subsonic region (07 lessthan or equal to M less than or equal to 0 85) Author

W77-31079# Royal Aircraft Establishment. Bedford (England)MEASUREMENTS OF BUFFETING ON TWO 65 DEG DELTAWINGS OF DIFFERENT MATERIALSD C Mabey and G F Butler In AGARD Unsteady Airloadsin Separated and Transonic Flow Apr 1977 14 p refs

Avail NTIS HC A12/MF A01Measurements of buffeting were made on two 65 deg delta

wings one made of steel and the other of magnesium Anondimensional buffet excitation parameter was derived frommeasured values of the rms buffeting response and totaldamping ratio The materials were selected so that the resonantfrequencies of the wings were almost the same, while giving asignificant variation of response and damping ration under identicalfree stream conditions The wings were tested at Mach numbersof 0 35 07 and 1 4 and the Reynolds number was varied overa wide range The results showed that the buffet excitationparameter for the first bending model was virtually identical forboth wings and was independent of Reynolds number exceptat very low Reynolds numbers A significant level of aerodynamicdamping was measured on the magnesium wing and theexperimental values agreed well with estimates made using slenderwing theory Author

N77-3108Oj|l British Aircraft Corp Preston (England)' MilitaryAircraft DivDYNAMIC LOADING OF AIRFRAME COMPONENTSC G Lodge and M Ramsey In AGARD Unsteady Airloads inSeparated and Transonic Flow Apr 1977 26 p refs

Avail NTIS HCA12/MFA01The design of modern combat aircraft is discussed in terms

of structural fatigue life Unsteady loads due to separated flowconditions in maneuvering flight are examined Dynamic loadson a modern variable sweep wing combat aircraft are predictedmaking use of wing tunnel model tests and results from flighttests The predictions are compared with available prototype flightmeasurements Author

N77-31081/C Vereimgte Flugtechmsche Werke GmbH. Bremen(West Germany)AIRFRAME RESPONSE TO SEPARATED FLOW ON THESHORT HAUL AIRCRAFT VFW 614Helmut Zimmermann and Guenter Krenz In AGARD UnsteadyAirloads in Separated and Transonic Flow Apr 1977 9 prefsAvail NTIS HCA12/MFA01

Using the VFW 614 aircraft as an example the influence ofan intermittent jet flow on sub-structures outside known jetboundaries is illustrated Effects comparable to those due to theengine jet are caused also by the wake of movable wing partssuch as spoilers and airbrakes The VFW 614 is used again as~n example to illustrate the occurrence of horizontal tail buffetdue to flow disturbances for outside the spoiler wake region,and to describe the steps taken to eliminate this type of buffetSeveral examples of flow separation with ensuing buffeting whichtypically occur in the course of flight trials, and measures tocombat these disturbances are discussed Author

N77-31082# Aeritaha S p A Torino (Italy)TAIL RESPONSE TO PROPELLER FLOW ON A TRANSPORTAIRPLANEL Chesta In AGARD Unsteady Airfoads in Separated andTransonic Flow Apr 1977 13 p

Avail NTIS HCA12/MFA01The results of a flight investigation on tail vibrations on

transport aircraft and the measures taken to overcome thesubsequent problems are described Factors studied include (1)

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the source of vibrations, (2) the flight conditions in which theyoccur, and (3) the impact of the vibration level on the fatiguelife It is concluded that the three propeller blades and theassociated airscrews are the excitation source of the vibrations

Author

N77-31083# Saab-Scania Lmkoping (Sweden) AerospaceDivFLUTTER CALCULATION FOR THE VIGGEN AIRCRAFTWITH ALLOWANCE FOR LEADING EDGE VORTEX EF-FECTIn AGARO Unsteady Airloads in Separated and Transonic FlowApr 1977 7 p refs

Avail NTIS HCA12/MFA01An application in a flutter calculation for the Viggen aircraft

of a program system for aeroelastic calculations is briefly describedThe result which (S checked against an indepedent calculationshows that a large flutter margin exists For increasing angle ofincidence, however the margin may decrease due to the effectof the leading edge vortices An estimate of the decrease wasobtained by applying a correction factor based on measuredpressure distributions for steady flow to the calculated liftdistribution ° Author

N77-31084# Air Force Flight Dynamics Lab Wright-PattersonAFB Ohio Dynamics LabA BRIEF OVERVIEW OF TRANSONIC FLUTTERPROBLEMSWalter J Mykytow In AGARD Unsteady Airloads in Separatedand Transonic Flow Apr 1977 13 p refs

Avail NTIS HCA12/MFA01A framework of industrial flutter problems with particular

emphasis on the impact for the speed region is provided Flutterstability boundaries are given re-emphasizing the critical designconditions present in the transonic flight region The re-emphasisis accomplished using results from research flutter model testsaircraft design and development model tests and aircraft flightdamping measurements B B

N77-31085# National Aerospace Lab Amsterdam (Netherlands)UNSTEADY AIRLOADS ON AN OSCILLATING SUPERCRITI-CAL AIRFOILN Tijdeman P Schippers and A J Pearsoon In AGARDUnsteady Airloads in Separated and Transonic Flow Apr 197715 p refsAvail NTIS HCA12/MFA01

Results are presented of unsteady pressure measurementson a two-dimensional model of the supercritical NLR 7301 airfoilperforming pitching oscillations about an axis at 40 per cent ofthe chord Author

N77-31086# General Dynamics/ Convair San Diego, CalifTHE TRANSONIC OSCILLATING FLAP A COMPARISONOF CALCULATIONS WITH EXPERIMENTSR Magnus and H Yoshihara (Boeing Co Seattle) In AGARDUnsteady Airloads in Separated and Transonic Flow Apr 19775 p refs Sponsored by AF

Avail NTIS HCA12/MFA01Finite difference calculations based on the exact inviscid

equations for an oscillating flap on an airfoil at M = 0 875 arecompared to the Tijdeman-Schippers experimental results Viscouseffects were incorporated in a phenomenological manner usingviscous displacement ramps Reasonably good agreement wasobtained, but with a significant discrepancy in the shock motionsattributable to a mismatch in the surface pressures upstream ofthe shock Recalculation at M = 0 854 yielded results in goodoverall agreement with the experiments at M = 0 875 for boththe steady and the unsteady cases Author

N77-31087*# National Aeronautics and Space AdministrationAmes Research Center Moffett Field CalifEFFICIENT SOLUTION OF UNSTEADY TRANSONIC FLOWSABOUT AIRFOILS

W F Ballhaus and P M Goorjian (Informatics Corp. Palo Alto,Calif) In AGARD Unsteady Airloads in Separated and TransonicFlow Apr 1977 11 p refs Prepared in cooperation withAAMRDLAvail NTIS HCA12/MFA01 CSCL 01A

An implicit finite difference procedure was developed forthe efficient solution of unsteady transonic flow fields Samplecomputations illustrate applications of procedures to aerodynamicproblems Solutions are presented that illustrate three types ofshock wave motion that can result from airfoil control surfaceoscillations The significant effect of wind tunnel wall conditionson these shock wave motions is demonstrated Solutions arealso presented for a simple aeroelastic problem in which theflow field equations and the structural motion equations areintegrated simultaneously in time Both stable and unstableaeroelastic interactions are considered The procedure is adaptedto compute unsteady aerodynamic force coefficients by the mdicialmethod Author

N77-31089| Royal Aircraft Establishment Farnborough(England) Structures DeptA PRACTICAL FRAMEWORK FOR THE EVALUATION OFOSCILLATORY AERODYNAMIC LOADING ON WINGS INSUPERCRITICAL FLOWH C Garner In AGARD Unsteady Airloads in Separated andTransonic Flow Apr 1977 15 p refs

Avail NTIS HC A12/MF A01An approximate theoretical treatment is devised in terms of

nonlinear steady surface pressure and linear oscillatory loadingThe steady data are taken either from transonic small perturbationtheory or from static measurements of surface pressure Theresulting theoretical or semi-empirical method can take accountof stream Mach number mean incidence mode of oscillation,frequency and amplitude The calculations are organized into acomputer program the scope and broad details of which areoutlined Its first application is in support of a wind tunnel studyof a rigid half wing with freedom to rotate about a swept axisThe experiment provides measurements of steady and oscillatorypressure distributions over the range of Mach number from 0 60to 0 86 The oscillatory results are compared with calculationsfrom linearized theory and from the present method in itstheoretical and semi-empirical forms Like the dynamic experi-ments the calculations show large differences between oscillatorychordwise load distributions under subcntical and supercriticalconditions In particular the region surrounding a Shockwaveexhibits large and rapid changes in both amplitude and phaseof the measured loading which are reproduced qualitatively inthe calculations The resulting generalized aerodynamic forcesare found to depend significantly on the development ofsupercritical flow The method should provide an economicalindication of the influence of mean flow on the flutter aerodynamicsin the lower transonic regime Author

N77-3109O*# Boeing Commercial Airplane Co, Seattle WashFlutter Research GroupAPPLICATION OF A FINITE DIFFERENCE METHOD TO THEANALYSIS OF TRANSONIC FLOW OVER OSCILLATINGAIRFOILS AND WINGSWarren H Weatherill, James D Sebastian (Boeing ComputerServices Inc Seattle) and F Edwards Ehlers In A G A R DUnsteady Airloads in Separated and Transonic Flow Apr 197713 p refs(Contract NAS1-14204)Avail NTIS HC A12/MF A01 CSCL 01A

A finite difference method for solving the unsteady flowabout harmonically oscillating wings is investigated The procedureis based on separating the velocity potential into steady andunsteady parts and linearmg the resulting unsteady differentialequation for small disturbances Solutions are obtained usingrelaxation procedures The means for improving the solutionstability characteristics of the relaxation process are explored Adirect procedure is formulated which permits obtaining solutionsfor combinations of Mach number and reduced frequency forwhich the relaxation process has proved unstable The pressuredistribution for an aspect ratio 5 rectangular wing oscillating inpitch is presented Author

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N77-31093*# National Aeronautics and Space AdministrationLangley Research Center Langley Station. VaSUBSONIC AND SUPERSONIC LONGITUDINAL STABIUTYAND CONTROL CHARACTERISTICS OF AN AFT-TAILFIGHTER CONFIGURATION WITH CAMBERED ANDUNCAMBERED WINGS AND CAMBERED FUSELAGESamuel M Dollyhigh Sep 1977 79 p refs(NASA-TN-D-8472. L-11424) Avail NTIS HC A05/MF A01CSCL 01A

The longitudinal aerodynamic characteristics of a fighterairplane concept has been determined through an investigationover a Mach number range from 0 50 to 2 16 The configurationincorporates a cambered fuselage with a single externalcompression horizontal ramp inlet, a clipped arrow wing twinhorizontal tails, and a single vertical tail The wing camber surfacewas optimized in drag due to lift and was designed to be selftrimming at Mach 1 40 and at a lift coefficient of 0 20 Thefuselage was cambered to preserve the design wing loadingson the part of the theoretical wing enclosed by the fuselageAn uncambered of flat wing of the same planform and thicknessratio distribution was also tested Author

N77-31094*# Vought Corp, Hampton. VaNONPLANAR WING LOAD-UNE AND SLENDER WINGTHEORYJohn DeYoung Washington NASA Aug 1977 78 p refs(Contract NAS1-13500)(NASA-CR-2864) Avail NTIS HC A05/MF A01 CSCL 01A

Nonplanar load line slender wing, elliptic wing, and infiniteaspect ratio limit loading theories are developed These are quasitwo dimensional theories but satisfy wing boundary conditionsat all points along the nonplanar spanwise extent of the wingThese methods are applicable for generalized configurations suchas the laterally nonplanar wing, multiple nonplanar wings orwing with multiple winglets of arbitrary shape Two dimensionaltheory infers simplicity which is practical when analyzingcomplicated configurations The lateral spanwise distribution ofangle of attack can be that due to winglet or control surfacedeflection, wing twist, or induced angles due to multiwmgs.multiwinglets. ground, walls, jet 01 fuselage In quasi twodimensional theory the induced angles due to these extraconditions are likewise determined for two dimensional flowEquations are developed for the normal to surface induced velocitydue to a nonplanar trailing vorticity distribution Applicationexamples are made using these methods Author

N77-31099# Virginia Polytechnic Inst and State Univ.Blacksburg Dept of Aerospace and Ocean EngineeringTHE FLOW ABOUT A SLENDER PROPELLER-DRIVEN BODYIN A TEMPERATURE STRATIFIED FLUIDT F Swean. Jr and J A Schetz Mar 1977 115 p refs(Contract N00014-75-C-0763 ARPA Order 1910 NR Pro)062-481)(AD-A040847 VPI-Aero-062) Avail NTIS HC A06/MF A01CSCL 20/4

The turbulent wake produced by a stern propeller-driven bodyin a temperature stratified fluid is measured using thermocouplesand pitot tubes of various size, a yawhead probe, a cross-wirehot wire, and a straight-wire hot wire The velocity and thermalboundary layers on the body upstream of the propeller are alsoexamined Mean flow velocities, static pressure, flow angularity,and mean temperature distributions are reported at fivedownstream stations The testing was conducted in a six ft bysix ft subsonic wind tunnel A significant increase in mixing rateis produced by the propeller in the region of 4 0 body diametersdownstream Temperature fluctuation is mild across the wakeexcept in the vicinity of the propeller tips where it becomesrelatively large GRA

A high-speed rotor model designated the RB-CCR (reverseblowing circulation control rotor) was evaluated in the hovermode The model was tested as a two- and four-bladed rotorwith several rotor configurations In general the hover testsdemonstrated that a good figure of merit can be obtained overa large range of collective pitch angles A comparison ofconfigurations at various collective angles showed a steadyimprovement in performance with increasing collective pitch angleThe RB-CCR model demonstrated that the high-speed rotor canhover with a zero mechanical collective pitch angle at a figureof merit of about 0 50 GRA

N77-31104# Royal Aircraft Establishment, Farnborough(England) Aerodynamics DeptITERATIVE CALCULATION OF FLOW PAST A THICKCAMBERED WING NEAR THE GROUNDC C L Sells London Aeron Res Council 1977 26 p refsSupersedes RAE-TR-76053. ARC-36856(ARC-CP-1370 RAE-TR-76053. ARC-36856) Avail NTISHC A03/MF A01. HMSO £1 75 PHI

The method to compute the steady low-speed mviscid flowpast a wing in free air, is extended to take account of groundeffect The basic method represents the perturbation due to thewing by iteratively computed distributions of sources and doubletson the wing chordal surface at each iteration the ground effectis represented by the images m the ground plane of thesedistributions, the strengths of which are calculated from thecomputed errors in the boundary conditions on upper and lowersurfaces For a given angle of incidence (and Mach number),several heights above the ground in succession can be treated,with some economy in computing time Results are presentedfor a two-dimensional section (RAE 100) and for two variantsof a wing of airbus type Comparisons with another methodfor the RAE section suggest that the present method generallyneeds at least three iterations, and that for very accurateresults at low ground heights further work on the program isneeded Author (ESA)

N77-31106jjl Royal Aircraft Establishment Farnborough(England) Aerodynamics DeptITERATIVE DESIGN TECHNIQUES FOR THICK CAMBEREDWINGS IN SUBCRITICAL FLOWC C L Sells London Aeron Res Council 1977 61 p refsSupersedes RAE-TR-76027. ARC-36857(ARC-CP-1371 RAE-TR-76027. ARC-36857) Avail NTISHC A04/MF A01. HMSO £3, PHI

The development of computer programs to design camberand twist distribution, and in some applications thicknessdistributions for a wing without dihedral in steady mviscidincompressible (or subcntical) flow is described The method forcomputing steady, mviscid, subcntical flow past a thick cam-bered wing is extended to design applications Four problemsare considered (1) given thickness and doublet (first-order loading)distributions. (2) given thickness and upper-surface pressuredistributions. (3) given loading and upper-surface pressuredistributions. (4) a hybrid of (2) and (3) in which the thicknessis specified everywhere except near the root and is determinednear the root when the doublet distribution is constrained toexhibit spanwise invariance in that region Convergence for thefirst problem is excellent For all problems, good convergence isobtained outboard For the single case reported of the secondproblem, convergence was secured near the root but cannot yetbe guaranteed Near the root, slow convergence was obtainedfor the third problem, rather better convergence for the fourthproblem This hybrid option is tentatively recommended

Author (ESA)

N77-31100# Naval Ship Research and Development Center.Bethesda, Md Dept of Aviation and Surface EffectsHOVER EVALUATION OF CIRCULATION CONTROL HIGHSPEED ROTORKenneth R Reader Jun 1977 42 p refs(AD-A040921. AERO-1239. DTNSRDC-77-0034) Avail NTISHC A03/MF A01 CSCL 01/3

N77-31106jjl Royal Aircraft Establishment, Farnborough(England) Aerodynamics DeptA WIND-TUNNEL INVESTIGATION OF THE EFFECTS OFFLAP SPAN AND DEFLECTION ANGLE. WING PLANFORMAND A BODY ON THE HIGH-UFT PERFORMANCE OF A28 DEG SWEPT WING

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0 A Lovell London Aeron Res Council 1977 199 p refsSupersedes RAE-TR-76030, ARC-36936(ARC-CP-1372. RAE-TR-76030. ARC-36936) Avail NTISHC A09/MF A01. HMSO £8. PHI

Lift, drag and pinching moment were measured over anextensive range of configurations of the high-lift system on awing of basic aspect ratio 8 35 and with a trailmg-edge planformextension and a body added The results were analyzed andcompared with two linear-theory prediction methods Themeasured increments in lift generated by the various elementsof the high-lift system were lower than the predicted levels Anexploratory analysis of the drag results showed that 'thelift-dependent drag factor was considerably underestimated bythe linear theory, particularly when the slat was deployed Thelimitations of the planar vortex sheet used in the theory andthe neglect of viscous effects are suggested as the principalreasons for the difference between experiment and theoryDeflection of the flap produced a load, which acted at a distanceforward of the mean quarter chord of the flap, that was practicallyindependent of incidence and flap span The wing/body interfer-ence effect was insensitive to flap span and there was someevidence of a download being generated on the rear body whenthe high-lift system was deployed The performance of the high-liftsystem was downgraded when the wing planform was extendedin the root region and this was attributed to the greaternon-uniformity of the spanwise loading Author (ESA)

N77-311C3)? General Dynamics/Fort Worth. TexASD ADVANCED PROGRAM RESEARCH INLET DATAANALYSIS REPORT FOR 1/5 2-SCALE MODEL INLET TESTSFinal Hoport. 14 Jul. 1978 - 1 Sop. 1978Charles C Mann and Jack E Garner Jan 1977 90 p refs(Contract F33615-75-C-5289)(AD-A040707. ASD-TR-76-35) Avail NTIS HC A05/MF A01CSCL 21/5

The analysis of wind-tunnel data from tests of a 1/5 2-scaleinlet research model covered was conducted Inlet design andengine/inlet compatibility cnteria are based on the F101-GE-100engine characteristics and requirements Detailed inlet flow-fieldanalyses are discussed Inlet pressure recovery distortion, andcompatibility parameters are presented for a basic configurationfrom Mach 0 55 to Mach 2 0 Data for an alternate configurationare presented for Mach 055 to 1 5 A limited amount of dataare also presented for other configurations that were tested

Author (GRA)

W77-311C3(? Naval Ship Research and Development Center.Bethesda. Md Aviation and Surface Effects DeptWIND TUNNEL RESULTS OIF A 10-PERCENT SCALEPOWERED SCAT VTOL AIRCRAFT Intonm Koport. Jul. -Oct. 1973David G Lee and David W Lacey Mar 1977 31 p refs(AD-A040313. DTNSRDC/ASED-371) Avail NTISHC A03/MF A01 CSCL 01/3

The low-speed aerodynamic characteristics of a 10-percentscale powered SCAT (Surveillance, Communications. ASMDWarning, and Targeting) configuration were investigated in the8- by 10-foot subsonic north wind tunnel Force and momentdata were obtained for both powered and unpowered VTOLfixed-wing aircraft Analysis of the data indicate that theconfiguration is statically stable in both pitch and yaw and thatcontrol is adequate for both axes The addition of a largeaft-mounted radome did not significantly change longitudinalcharacteristics, but did increase lateral-directional stability Twowings of different airfoil sections were evaluated a NACAdesign and a bebeck design The Liebeck wing section increasedlift over that generated by the NACA baseline wing section

Author (GRA)

N77-31110|jl Frost Engineering Development Corp. Englewood,ColoDESIGN AND EVALUATION METHODS FOR OPTIMIZINGEJECTION SEAT CUSHIONS FOR COMFORT AND SAFETYFinal Roport. Jul 1987 - Jun 1938

Ernest L Stech Feb 1977 134 p refs(Contract F33615-67-C-1912. AF Pro) 7231)(AD-A036035. AMRL-TR-68-126. Rept-338-7) Avail NTISHC A07/MF A01 CSCL 01/3 _

Two kinds of cushions, passive and inflatable, were developedusing analytic and empirical optimization procedures to enhanceboth comfort and safety Comfort tests were run on a series ofpolyurethane foams, an inflatable seat cushion, and two operationalseat cushions Load-deflection and damping coefficient data werealso obtained Results of the tests showed that comfort increasesas cushion thickness or inflation pressure increases Analogcomputer results using a smgle-degree-of-freedom model of thehuman body demonstrated an increasing overshoot with increasingthickness or inflation pressure except for low density polyurethanefoam Optimization curves for comfort versus dynamic overshootwere generated and used in the design of the optimizedcushions GRA

N77-31111# Army Test and Evaluation Command AberdeenProving Ground MdSAFETY (AVIATION MATERIAL) Final Report9 Dec 1976 52 p Supersedes Report no MTP-7-3-5(AD-A041021 TOP-7-3-506) Avail NTIS HC A04/MF A01CSCL 01/3

The document identifies existing test methodology andtechniques necessary to determine the degree to which aviationmateriel meets the safety requirements stated in the requirementsdocuments These procedures cover the requirements aircraftarmament, airframe. ejection seat, electronic, mechanical andmiscellaneous hazards relating to Army aircraft A guide for lasersafety is included for use when lasers are mounted in Armyaircraft Author (GRA)

W77-31112# National Transportation Safety Board Washington.D C Bureau of TechnologyUS AIR CARRIER ACCIDENTS INVOLVING FIRE. 1993THROUGH 1974 AND FACTORS AFFECTING THE STATIS-TICS17 Feb 1977 64 p refs(PB-266883/8. NTSB-AAS-77-1) Avail NTISHC A04/MF A01 CSCL 01B

Statistical data on U S air carrier accidents involving firefrom 1965 through 1974 are compared with similar data forthe proceeding decade While fire still occurs in about 20 percentof the accidents in scheduled passenger operations, the ratio offatalities from all causes to exposed occupants declined 65 percentin this study period and the ratio of fatalities from the effectsof fire and smoke to exposed occupants declined 37 percentThe almost exclusive use in this study period of turbojet-poweredaircraft their improved reliability, and the use of kerosene-typefuel are factors influencing the statistics GRA

N77-31113# Taussig Associates Canaan. N HBRITISH AIRWAYS AN ANALYSIS OF EFFICIENCY ANDCOST LEVELS Final RoportWilliam M Taussig May 1977 68 p(Contract DOT-OST-PS-70292)(PB-268060/1. OST-PS-70292) Avail NTISHC A04/MF A01 CSCL 01B

The cost and efficiency data publicly available for BritishAirways is summarized and used to develop comparisons withU S air carriers GRA

N77-31114# National Transportation Safety Board Washington.D C Bureau of TechnologyBRIEFS OF ACCIDENTS INVOLVING AERIAL APPLICATIONOPERATIONS. U S GENERAL AVIATION 1975 AccMontRoport1975 292 p(PB-267654/2. NTSB-AMM-77-11) Avail NTISHC A13/MF A01 CSCL01B

Facts, conditions, circumstances and probable causes aregiven for 429 general aviation aerial application accidents occunngin 1975 Additional statistical information is tabulated by typeof accident phase of operation, injury index, aircraft damage,pilot certificate injuries and causal/factods) GRA

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N77-31116# National Transportation Safety Board. Washington.D C Bureau of TechnologyBRIEFS OF ACCIDENTS INVOLVING AMATEUR/HOMEBUILT AIRCRAFT. US GENERAL AVIATION. 19761975 74 p(PB-2676b2/6, NTSB-AMM-77-9) Avail NTISHC A04/MF A01 CSCL 01B

Reports of U S general aviation accidents involving amateur/home built aircraft occurring in 1975 are presented Includedare 114 accident briefs. 23 of which involve fatal accidentsThe facts, conditions, circumstances and probable cause(s) factorls)for each accident are given Additional statistical information istabulated by type of accident, phase of operation injury index,aircraft damage, pilot certificate injuries and causal/factorls)

GRA

N77-31118j)l National Transportation Safety Board. Washington.D C Bureau of TechnologyBRIEFS OF ACCIDENTS. INVOLVING CORPORATE/EXECUTIVE AIRCRAFT. US GENERAL AVIATION. 19761975 55 p(PB-267651/8. NTSB-AMM-77-8) Avail NTISHC A04/MF A01 CSCL 01B

General aviation corporate/executive aircraft accidentsoccurring in the U S in 1975 are reported Included are 63accident briefs. 17 of which involve fatal accidents The b"efformat presents the facts, conditions, circumstances and probablecause(s) for each accident Additional statistical information istabulated by type of accident, phase of operation, injuries andcausal/factorsls) GRA

N77-31117# National Transportation Safety Board, WashingtonD C Bureau of TechnologyBRIEFS AND ACCIDENTS INVOLVING MISSING ANDMISSING LATER RECOVERED AIRCRAFT. US GENERALAVIATION. 13761975 111 p(PB-267650/0, NTSB-AMM-77-7) Avail NTISHC A06/MF A01 CSCL 01B

One hundred twenty-nine general aviation missing and missinglater recovered accidents occurring in the US in 1975 arereported Each brief presents the facts conditions, circumstances,and probable cause(s) for each accident Additional statisticalinformation is tabulated by type of accident, phase of operationinjury index, aircraft damage, pilot certificate injuries and causalfactor(s» GRA

N77-31118# National Transportation Safety Board. WashingtonD C Bureau of TechnologyBRIEFS OF ACCIDENTS INVOLVING ALCOHOL AS ACAUSE/FACTOR. US GENERAL AVIATION. 197611 Fob 1977 44 p(PB-267649/2. NTSB-AMM-77-6) Avail NTISHC A03/MF A01 CSCL 01B

A publication containing reports on all U S general aviationaccidents occurring in 1975. involving alcohol impairment as acause/factor is reviewed Included are 49 accident briefs. 42 ofwhich involve fatal accidents The brief format presents the factsconditions, circumstances and probable cause(s)/factor(s) for eachaccident Additional statistical information is tabulated by typeof accident phase of operation, injury index aircraft damage,pilot certificate, injuries and causal factor(s) GRA

N77-31119# National Transportation Safety Board Washington.D C Bureau of TechnologyBRIEFS OF FATAL ACCIDENTS INVOLVING WEATHER ASA CAUSE/FACTOR. US GENERAL AVIATION 1976.1975 303 p(PB-267648/4 NTSB-AMM-77-5) Avail NTISHC A14/MF A01 CSCL 01B

Reports of 283 fatal U S general aviation accidents involvingweather as a cause/factor for" the year of 1975 are summarizedshowing the facts, conditions circumstances, and probablecause(s) for each accident Additional statistical information istabulated on all accidents involving weather as a cause/factor

by type of accident phase of operation, injury index, aircraftdamage, pilots certificate, injuries and cause/factor(s) GRA

N77-31120# National transportation Safety Board. Washington.D C Bureau of Technology ~~BRIEFS OF ACCIDENTS INVOLVING ROTORCRAFT USGENERAL AVIATION. 19761975 173 p

(PB-267647/6. NTSB-AMM-77-4) Avai'l NTISHC A08/MF A01 CSCL 01B

Accidents occunng in 1975 involving US general aviationrotorcraft are reported Included are 309 accident briefs. 26 ofwhich involve fatal accidents The brief format presents the facts,conditions, circumstances, and probable cause(s) for each accidentAdditional statistical information is tabulated by type of accident,phase of operation, injury index, aircraft damage, pilot certificate,injuries and causal factorls) GRA

N77-31121# National Transportation Safety Board Washington,D C Bureau of TechnologyBRIEFS OF ACCIDENTS INVOLVING TURBINE POWEREDAIRCRAFT. US GENERAL AVIATION. 19761975 76 p(PB-267646/8, NTSB-AMM-77-3) Avail NTISHC A05/MF A01 CSCL 01B

A publication containing reports of U S general aviationturbine powered aircraft accidents occurring in 1975 is reviewedIncluded are 110 accident briefs, 26 of which involve fatalaccidents The brief format presents the facts conditions,circumstances and probable cause(s) for each accident Additionalstatistical information is tabulated by type of accident, phase ofoperation, injury index, aircraft damage, pilot certificate, injuriesand cause/factorls) GRA

N77-31122# National Transportation Safety Board Washington,D C Bureau of TechnologyBRIEFS OF ACCIDENTS INVOLVING MIDAIR COLLISIONS.US GENERAL AVIATION. 19761975 48 p(PB-267645/0. NTSB-AMM-77-2) Avail NTISHC A03/MF A01 CSCL 01B

A publication containing reports of U S general aviation midaircollision accidents occurring in 1975 is reviewed Included are29 accident files 13 of which involve fatal accidents The briefformat presents the facts, conditions circumstances, and probablecause(s) for each accident Additional statistical information istabulated by kind of flying, phase of operation, injury index,aircraft damage, pilot certificate, injuries and causal factorls)

GRA

N77-31123# National Transportation Safety Board. Washington,D C Bureau of TechnologyLISTINGS OF ACCIDENTS/INCIDENTS BY AIRCRAFTMAKE AND MODEL. US CIVIL AVIATION. 19751975 198 p(PB-267644/3 NTSB-AMM-77-1) Avail NTISHC A09/MF A01 CSCL 01B

A publication containing a listing of all U S civil aviationaccidents/incidents occurring in calendar year 1975 sorted byaircraft make and model is reviewed Included are the File number,aircraft registration number, date and location of the accident,aircraft make and model and injury index for all 4431 accidents/incidents occurring in the period ERA

N77-31124| National Aviation Facilities Experimental Center.Atlantic City. N JAIR TRAFFIC CONTROL EXPERIMENTATION AND EVAL-UATION WITH THE NASA ATS-6 SATELLITE.VOLUME 2 DEMONSTRATION OF SATELLITE-SUPPORTED COMMUNICATIONS AND SURVEILLANCEFOR OCEANIC AIR TRAFFIC CONTROL Final Report. Sap1974 - Apr 1976

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Francis W Jefferson Apr_l976 88 p refs

(FAA-NA-75-64-Vol-2 FAA-RD-75-1732-Vol-2) Avail NTISHC A05/MF A01 CSCL 17/7

Demonstrations of satellite supported communications forapplication to oceanic air traffic control were conducted as partof an international ATS 6 L-band satellite test program Voicedata and dependent surveillance communications between airtraffic controllers at a ground terminal and pseudopilots in twoairborne aircraft were performed via the ATS 6 satellite andground station A simulated aircraft terminal was also employedEach terminal provided up to six simulated data link aircraft,through computer software, for traffic loading purposes Dependentsurveillance was demonstrated through data link automatic aircraftposition reports Position data were obtained from an mertialnavigation system and an Omega navigation system in the aircraftIndependent surveillance was demonstrated using the NASAPLACE system and the ATS 6 and ATS 5 satellites Author

N77-31125*# National Aeronautics and Space AdministrationLangley Research Center, Langley Station, VaA DESCRIPTION OF THE SOFTWARE ANALYSIS FROMFUGHT AND SIMULATION DATA OF THE COURSE CUTLIMITER IN THE TCV B-737 AREA NAVIGATIONCOMPUTERCharles E Knox and David A Hmton Aug 1977 21 p refs(NASA-TM-74061) Avail NTIS HC A02/MF A01 CSCL 17G

During automatic horizontal path captures, the (TerminalConfigured Vehicle) B-737 airplane maintained smaller thandesigned path intercept angles and experienced a sawtooth bankangle oscillation during its turn towards the path From flightdata it was determined that these anomalies were caused bythe improper output of trie course cut limiter in the horizontalpath control law The output from the course cut limiter did notobtain its full value and it was calculated stepwise discontm-uously The automatic horizontal path captures were thenconducted on the TCV B-737 airplane real-time simulation Thepath intercept angles were maintained properly and no bankangle oscillation was encountered Data showed that the coursecut limiter was calculated <rt its full value in a continuous mannerThe intermediate calculations of the course cut limiter m theairplane s navigation computer were rewritten and reseated insuch a manner that truncation errors could be minimized Thehorizontal path capture tests were then reflown The airplanemaintained the proper path intercept angle and no bank angleoscillations occurred on any of the tests Author

N77-31126# Stanford Research Inst Menlo Park, CalifDEFINITION OF A DATA COLLECTION SYSTEM FOR USARMY TACTICAL MICROWAVE LANDING SYSTEMEVALUATION Final Report. Mar - Sep 1976J H Pnedigkeit and P G Stoltz Sep 1976 65 p(Contract DAAB07-75-C-0906)(AD-A041230. SRI-4462-Suppl ECOM-75-0906-SF) AvailNTIS HC A04/MF A01 CSCL 01/2

The data to be collected for flight test performance evaluationof Tactical Microwave Landing System (TMLS) by the Army isdefined Data rates, data formats, and data processing require-ments are developed Data recording options are considered anda preliminary design for a TMLS airborne data collection systemis presented GRA

N77-31127# Naval Research Lab, Washington. D CA SIMPLE CLOSED-FORM SOLUTION OF A POSITION-FIXING PROBLEM Interim ReportBen H Cantrell 15 Apr 1977 10 p(AD-A039303 NRL-8115) Avail NTIS HCA02/MFA01 CSCL17/7

A closed-form solution was obtained for the problem of findingan object s location given ranges to four stations of known locationThe method is simple, involving only simple algebra such asaddition and multiplication and the evaluation of a few trigonomet-ric functions Only three stations are required for the solution ifsome other a priori information is available such as height abovethe earth or the azimuth Author (GRA)

N77-3113O*# National Aeronautics and Space AdministrationAmes Research Center, Moffett Field CalifACOUSTICALLY SWEPT ROTOR Patent ApplicationFrednc H Schmitz (Army Air Mobility R and D Lab MoffettField Calif) Donald A Boxwell (Army Air Mobility R and DLab Moffett Field Calif) and C Rande Vause, inventors (toNASA) (Army Air Mobility R and D Lab . Moffett Field, Calif)Filed 8 Sep 1977 36 p Sponsored by NASA(NASA-Case-ARC-11106-1, US-Patent-Appl-SN-831633) AvailNTIS HC A03/MF A01 CSCL 20A

Impulsive noise reduction is provided in a rotor blade byacoustically sweeping the chord line from root to tip so thatthe acoustic radiation resulting from the summation of potentialsingularities used to model the flow about the blade tend tocancel for all times at an observation point in the acoustic farfield NASA

N77-31131*# National Aeronautics and Space AdministrationLyndon B Johnson Space Center, Houston TexSURFACE FINISHING Patent ApplicationJack A Kmzler James T Heffernan. Leroy G Fehrenkamp,inventors (to NASA) and William S Lee Filed 6 Apr 197726 p(NASA-Case-MSC-12631-2. US-Patent-Appl-SN-785279) AvailNTIS HC A03/MF A01 CSCL01C

An airfoil configuration and manufacturing process is describedfor reducing or eliminating air turbulence created by surfaceirregularities in the metal due to rivets wrinkles butt-joints, andthe like An article adapted for relative motion with a fluidenvironment is finished by coating the surface with a fluid adhesive,covering the adhesive with a sheet of flexible film material undertension and setting the adhesive while maintaining tension onthe film material so that the tensioned film material is bondedto the surface by the adhesive NASA

N77-31133*# Princeton Univ. N JAN IN-FLIGHT SIMULATION OF APPROACH ANDLANDING OF A STOL TRANSPORT WITH ADVERSEGROUND EFFECT Final ReportDavid R Ellis [1976] 58 p refs(Contract NAS1-11543)(NASA-CR-154875) Avail NTIS HC A04/MF A01 CSCL01C

The results of an in-flight simulation program undertaken tostudy the problems of landing a representative STOL transportin the presence of adverse ground effects are presented Landingswere performed with variations in ground effect magnitude groundeffect lag. and thrust response Other variations covered theeffects of augmented lift response. SAS-failures, turbulence,segmented approach, and flare warning The basic STOL airplanerequired coordinated use of both stick and throttle for consistentlyacceptable landings, and the presence of adverse ground effectsmade the task significantly more difficult Ground effect lag andgood engine response gave noticeable improvement, as didaugmented lift response Author

N77-31134*# National Aeronautics and Space AdministrationLangley Research Center, Langley Station, VaSTUDIES OF FRICTION AND WEAR CHARACTERISTICSOF VARIOUS WIRES FOR WIRE-BRUSH SKIDSRobert C Dreher Washington Sep 1977 32 p refs(NASA-TN-D-8517. L-11625) Avail NTIS HC A03/MF A01CSCL 01C

The friction and wear characteristics of 22 types and sizesof wires for potential use in wire-brush skids were studied Thesecharacteristics were determined by placing brushes made fromcandidate wires on a belt sander whose moving belt simulatedlanding roll-out distance At the same time the drag force andwear behavior were monitored Data were obtained over distancesup to 3048 m (10.000 ft) at preselected bearing pressures of172 to 1034 kPa (25 to 150 psi) In general, the friction coefficientdeveloped by the candidate wires was found to be independentof bearing pressure and ranged between 0 4 and 0 6 under thetest conditions of this investigation The friction coefficient wasnot degraded when the surface was wetted and appears to beindependent of wire diameter except perhaps when wire size is

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relatively large compared with the surface asperities Generally,the high friction demonstrated by the soft materials wasaccompanied by high wear rates, conversely the hard materialsprovided greater wear resistance but offered lower friction Forall test wires, the wear was shown to increase with increasingbearing pressure, in general, for the same bearing pressure, wearincreased with increasing wire diameter and decreased whenthe surface was wetted Author

N77-31136*jjl National Aeronautics and Space AdministrationHugh L Dryden Flight Research Center Edwards CalifAN IMPROVED FREE WING FOR AN AIRCRAFT PatentApplicationChester H Wolowicz. inventor (to NASA) Filed 8 Sep 197720 p(NASA-Case-DFRC-10092-1 US-Patent-Appl-SN-831634)Avail NTIS HC A02/MF A01 CSCL01C

A free wing is attached to a fuselage of an aircraft in amanner such that the wing is free to pivot about a spanwiseaxis forward of its aerodynamic center The wing is angularlydisplaced about the axis by aerodynamic pitching moments,resulting from lift, and is trimmed through a use of a trimmablefree stabilizer comprising a floating canard mounted on a strutrigidly connected to the wing and forwardly projected there-from NASA

N77-31136))/ Army Aviation Engineering Flight Activity. EdwardsAFB. CalifAIRWORTHINESS AND FLIGHT CHARACTERISTICSEVALUATION C-12A AIRCRAFT Final Report. 25 Oct1975 - 14 Feb 1976Joseph C Watts, Vernon L Diekmann Raymond B Smith. JohnE Hannon and William A Morton Oct 1976 203 p(AD-A040239, USAAEFA-75-08) Avail NTISHC A10/MF A01 CSCL 01/3

The United States Army Aviation Engineering Flight Activityconducted an airworthiness and flight characteristics evaluationof a C-12A aircraft serial number 73-22250, from 25 October1975 through 14 February 1.976 The aircraft was tested atEdwards Air Force Base (field elevation 2302 feet), PasoRobles (field elevation 836 feet), and Lake Tahoe (field elevation6262 feet) California During the evaluation 71 flights totaling68 75 productive flight hours were conducted Performance andhandling qualities of the C-12A were evaluated under a varietyof operating conditions with emphasis on operation in thenormal mission configuration near the maximum gross weightof 12 500 pounds The test aircraft was evaluated against therequirements of Federal Aviation Regulation Part 23. the BeechAircraft Corporation prime item development specification, andmilitary specification MIL-F-8785BIASG) to assist in determiningoperational mission capabilities Two handling qualities deficiencieswere identified These were the mam landing gear wheel lockup tendency which occurred when applying brakes during landing,and the lack of adequate stall warning above 20,000 feetpressure altitude Twenty shortcomings were noted includingfour stability and control shortcomings two lighting systemshortcomings, and 14 reliability and maintainability shortcomingsThe C-12A failed to meet the single-engine service ceilingdual-engine cruise ceiling, and the 30000-foot altitude cruiseairspeed guarantees Two enhancing features were the locationof the landing light switches and the rudder boost, which greatlyreduced pilot workload during asymmetric power conditions

Author (GRA)

N77-31137jjl Naval Air Test Center. Patuxent hiver. MdFLIGHT CONTROL TESTING OF THE VAK-191B AIR-CRAFTRobert L Traskos 24 May 1977 8 p refs(AD-A040535. NATC-TM-77-1-SA) Avail NTISHC A02/MF A01 CSCL 01/3

The U S Navy/Federal Republic of Germany Joint FlightTest Program, using the VAK-191B aircraft, was conducted toexpand the base of VSTOL technology During the flight program,an integrated test block approach was considered mandatoryfor the acquisition of the required data in the limited flight time

available Ground and captive rig tests were used, when applicable,to supplement data acquisition In spite of the configuration ofthe captive rig, which precluded its use in the documentation ofengine exhaust flow, it was considered a valuable tool in controlsystem and engine test and for pilot familiarization

Author (GRA)

N77-31138jjl Army Air Mobility Research and DevelopmentLab, St Louis Mo Systems Research Integrated OfficeSINGLE-ROTOR HELICOPTER DESIGN AND PERFORM-ANCE ESTIMATION PROGRAMS VOLUME 1- METHODOL-OGY Final ReportMilton A Schwartzberg Roger L Smith James L Means, HaroldY H Law. and David P Chappell Jun 1977 91 p rets(AD-A040803. SRIO-77-1-Vol-1) Avail NTISHC A05/MF A01 CSCL 01/3

Computer programs, designated SSP-1 and SSP-2. have beenprepared for (1) the preliminary design of single-rotor helicoptersto meet specified mission requirements and (2) the estimationof the performance of single-rotor helicopters of known geometryand with known engine characteristics The present volume isone of a beries describing those computer programs It detailsthe methodology on which all of those programs are based

Author (GRA)

N77-31139# Logistics Management Inst Washington D CSENSITIVITY OF ARMY HELICOPTER OPERATING ANDSUPPORT COSTS TO CHANGES IN DESIGN AND LOGISTICPARAMETERSJohn D Forster May 1977 54 p refs(Contract SD-321)(AD-A040353 LMI-75-1/4) Avail NTIS HC A04/MF A01CSCL 01/3

This study assesses Army helicopter 0 and S costs andSupport Investment (SI) costs in order to assure that the degreeof hardware design and logistic parameter sensitivity included incost estimates accurately reflects actual expenditure sensitivi-ties Army 0 and S cost data sources, methodology andapproaches are examined and selected cost improvements isolatedand evaluated Strengths of the current costing structure arenoted so that they can be carried forward and improved uponto assure accurate representation of new systems to the DSARC0 and S data sources reviewed include reliability maintainabilityand field reported cost data The present methodology andapproaches for both Baseline (Program Manager's) Cost Estimates(BCE) and Independent Parametric Cost Estimates (IPCE) areassessed The dominant O and S costs are found to be Manpower,Replenishment Spares, and Initial Spares For Manpower andInitial Spares, simplified models are discussed which give OASDvisibility into the critical sensitivities of Army helicopter O andS costs Of the parameters examined for the selected helicopters0 and S costs are most sensitive to the Mean Time BetweenDynamic Component Removals (MTBRDC) The report concludeswith a discussion of bounding values of Army helicopter 0 andS cost that can be expected if extreme values of critical 0 andS cost driving parameters, including those assumed in the costestimate's approach are encountered in actual practice GRA

N77-31140# Naval Air Development Center Warmmster. PaAir Vehicle Technology DeptSTATISTICAL REVIEW OF COUNTING ACCELEROMETERDATA FOR NAVY AND MARINE FLEET AIRCRAFTSemiannual Summary Report. 1 Jan 1962 - 31 Dec 1976Alan M Kaniss 1 May 1977 159 p Revised(AD-A041266) Avail NTIS HC A08/MF AOJ CSCL 01/2

This is a semi-annual progress report, and it presents aspecialized summary of the data in the counting accelerometerprogram Statistics describing Navy and Marine aircraft cumulativeg-count exceedances are calculated and tabulated Thesetabulations are separated by calendar time and into four majorcategories of fleet experience Navy Training. Navy Combat.Manne Training, and Marine Combat These data show that theload rate distributions (counts at 1000 hours) for most modelsand most g-levels have a non-normal distribution Within a model(F-4B. F-8H etc) differences in the average load rates existwhen data are separated by calendar time or mission category

Author (GRA)

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W77-31141

P377-31101// Boeing Aerospace Co . Seattle. Wash MilitaryAirplane DevelopmentINNOVATIVE AIRCRAFT DESIGN STUDY (IADS) TASK 2.VOLUME 1 Final RoportE A Barber. D G Blattner, R C Sutton. and M J MailhiotJun 1977 186 p refs(Contract F33615-76-C-0122)(AD-A041234) Avail NTIS HC A09/MF A01 CSCL 01/3

The study was concerned with the conceptual design andevaluation of military heavy logistics transport aircraft enteringservice in the 1990-2000 time period Design paylaods of200.000-600 000 Ib and design ranges of 3600-7200 nm wereconsidered Takeoff field length was 8.000 ft in most casesSuitability for commercial usage was a major objective Comput-er aided design techniques were employed extensively for airplanesynthesis and analysis The study was accomplished in two phasesPhase I included parametric design and analysis of transports inthe payload/ range categories cited above An advanced technologyreview, including evaluations and sensitivity analyses, wasaccomplished These studies indicated that substantial gams werepossible in reducing operating costs by incorporating both thelow risk technology and innovative designs available in 1985.and advanced technology such as composite structures availableat a later time Additional effort is required to identify this increasedcost of higher risk advanced technology to determine its costeffectiveness In Phase II. a baseline mission requiring 3600 nmradius and 400.000 Ib payload was selected GRA

This paper presents a summary of test results from severalhelicopter shipboard test programs Data are presented from theHH-2D test on the FF-1052 class USS W S SIMS in 1970. theSH-2F on the FF-1052 class USS BOWEN in 1974. and theHH-3F on the WHEC Class USCG HAMILTON in 1975Improvements in NATOPS manual information are highlightedin the areas of wind and/or airspeed limitations, cockpitindications, and helicopter performance information for bothlevel flight and climb and descent Shipboard deck strength andlanding gear capabilities are addressed and a statistical database is presented from which extrapolations to the sea state 5environment may be made Author (GRA)

W77-311C6j? Naval Postgraduate School. Monterey. CalifA STUOV Of SPECTRUM LOADING AND RANGE-PAIRCOUNTING METHOD EFFECTS ON CUMULATIVE FATIGUEDAMAGE M.S. ThocfoJohn Scon Atkinson. Jr Mar 1977 118p refs(AD-A039651) Avail NTIS HC A06/MF A01 CSCL 01/3

This thesis is a study of cumulative fatigue damage Variationsin cumulative fatigue damage resulting from block loading spectraand randomized cycle loading spectra are investigated Fatiguedamage results show the merit of counting load cycles usingthe range-pair counting method Complete FORTRAN computerprogram documentation enables this thesis to serve as a programuser's manual Author (GRA)

W77-311C2# Army Aviation Systems Command St Louis MoSystems Analysis OfficeCH-47 MEDIUM LIFT HELICOPTER EFFECTIVENESSEVALUATION PROGRAM RUN BOOK Final ReportMark E Barkley and John A Weaver Jun 1977 37 p refs(AD-A041462. DRSAV-D-77-10/2 USAAVSCOM-TR-77-31)Avail NTIS HC A03/MF A01 CSCL 01/3

This report offers a general description of the Medium LiftHelicopter Effectiveness Evaluation Program instructions forpreparing input data and job control language (JCL) card decks,and for consolidating these decks It also offers definitions ofthe input/output variables a listing of the JCL, a sample outputlisting, and a glossary of the terms used Author (GRA)

M77-31143# Royal Aircraft Establishment. Bedford (England)Aerodynamics DeptCOMPARATIVE PERFORMANCE MEASUREMENTS OFTWO HELICOPTER BLADE PROFILES IN HOVERINGFLIGHTM J Riley and P Brotherhood London Aeron Res Council1977 55 p refs Supersedes RAE-TR-74008, ARC-35289(ARC-R/M-3792, RAE-TR-74008 ARC-35289) Avail NTISHC A04/MF A01 HMSO £5 PHI

A new blade profile RAE(NPL)9615, was developed for theLynx helicopter using two-dimensional aerfoil tests The complexnature of the rotor environment makes it essential to confirmthat the designed improvements are realized in flight The presenttests, planned before the Lynx first flew, have simultaneouslycompared the new profile with the NACA 0012 profile in hoveringflight Each profile took the form of a fairing or glove' on apair of opposing blades of the Wessex helicopter and both localsurface pressures and wake pitot pressures were measured Theflight results confirm the comparative reduction in local supersonicvelocity and in shock-induced profile drag for the new profileHowever differences between flight and tunnel attributable tothree-dimensional effects are evident The results also indicatethe complex nature of the flow due to blade vortex interactionand small translation velocities Author IESA)

N77-311<W)S( Naval Air Test Center. Patuxent River, MdSUMMARY OF HELICOPTER AIRFRAME TESTING IN THESHIPBOARD ENVIRONMENTHerman G Kolwey 29 Apr 1977 12 p refs(AD-A039748, NATC-TM-77-2RW) Avail NTISHC A02/MF A01 CSCL 01/3

N77-31143# Rockwell International Corp. Columbus. OhioMissile Systems DivAHPV SYSTEM/DESIGN THADE STUDY. VOLUME 0:LAUNCH AND RECOVERY26 Apr 1976 162 p(Contract F33657-75-C-0518)(AD-A039591. C76-1324/034C-Vol-4) Avail NTISHC A08/MF A01 CSCL 01/3

On the basis of trade-off analysis of Launch and RecoverySystems for ARPV. the conventional take-off and landing methodusing high lift wing (STOL) technique, own thrust and arrestinggear system emerged as the undisputable leader among thecandidate systems The next system in succession is the STOLconfiguration using modified SATS catapult conventional gearand arrester gear The third best system comes out to be aSTOL CONFIGURATION - WHEELED DOLLY (STEERABLE)ARRESTER GEAR and INTEGRAL AIR CUSHION In the fourthplace (again in absence of cheap SATS catapults), the HybridTruck Launcher with STOL and Arrester Gear SKIDS is the finalviable candidate which can be effective as a tactical ARPV systemLaunch and Recovery Method GRA

(377-31147# Air Force Instrument Flight Center. Randolph AFB.TexALTITUDE WARNING SIGNAL SYSTEM EVALUATION FinalReportKenneth J Kerkenng, Gerald C Armstrong, and Dolores M TylerApr 1977 23 p(AD-A039365. USAFIFC) Avail NTIS HC A02/MF A01 CSCL01/4

The Research and Development Division. USAF InstrumentFlight Center (USAFIFC/RD) conducted a pilot factors evaluationof the Harowe Altitude Warning Signal System (AWSS) todetermine its acceptability for use in Air Force aircraft The systemhas the primary function of assisting pilots in attaining andmaintaining assigned or desired (command) altitudes A secondaryfunction, the approach mode, was incorporated in the AWSS toexamine the concept of altitude warning during landing approach-es Thirteen sorties were flown in a NT-38 Talon Subject pilotswere selected from IFC personnel The overall concept andoperation was found to be acceptable by half of the subjectpilots Half of the subject pilots felt the information provided bythe system did not justify the increased workload The normaland approach modes of operation were found to be acceptablein concept, operation, and accuracy The system in its presentconfiguration is not acceptable for installation in trainer andsingle place aircraft due to the unacceptable increase in cockpitworkload Author (GRA)

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N77-31148*# Cincinnati Univ. Ohio Dept of AerospaceEngineering and Applied MechanicsTHE EFFECT OF AMBIENT CONDITIONS ON CARBONMONOXIDE EMISSIONS FROM AN IDUNG GAS TURBINECOMBUSTOR M.S. TtwsisAnand K Subramamam 1977 99 p refs(Grant NsG-3045)(NASA-CR-154986) Avail NTIS HC A05/MF A01 CSCL21E

A test program employing a gas turbine combustor isoutlined, the results of which quantize the effects of changes inambient temperature and humidity on carbon monoxide emissionsat simulated idle operating conditions A comparison of theexpenmental results with analytical results generated by a kineticmodel of the combustion process, and reflecting changing ambientconditions, is given It is demonstrated that for a complete rangeof possible ambient variations, significant changes do occur inthe amount of carbon monoxide emitted by a gas turbine atidle, and that the analytical model is reasonably successful inpredicting changes Author

N77-3114S*jjf General Electric Co. Cincinnati. Ohio AdvancedEngineenng and Technology Programs DeptNASA/NAVY UFT/CRUISE FAN. PHASE 1. DESIGNSUMMARYSep 1977 276 p refs(Contract NAS3-20046)(NASA-CR-135242 R77AEG180) Avail NTISHC A11/MF A01 CSCL 21E

The initial design of the LCF459 lift/cruise fan system isdocumented The LCF459 is a 1 5 meter diameter turbotiplift/cruise fan whose design point pressure ratio is 1 32 at a tipspeed of 353 meters per second The gas source for the tipturbine is the YJ97-GE-100 engine Author

N77-31160# Federal Aviation Administration. Washington. DCNOISE LEVELS FOR TURBOJET POWERED AIRPLANESAND LARGE PROPELLOR DRIVEN AIRPLANES: NOTICE OFPROPOSED RULE MAKING2Aug 197681 p refsAvail NTIS HCA05/MFA01 CSCL 20A

A proposed amendment to Part 36. Appendix C of the FederalAviation regulations covenng turbojet powered and subsonic largepropeller dnven airplanes is discussed Effective perceived noiselevels are listed for available and future technology aircraft atsideline, takeoff, and approach Author

N77-31163*jjl National Aeronautics and Space AdministrationLewis Research Center, Cleveland. OhioEFFECTS OF TEMPERATURE TRANSIENTS AT FAN INLETOF A TURBOFAN ENGINEMahmood Abdelwahab Sep 1977 40 p refs(NASA-TP-1031. E-0162) Avail NTIS HC A03/MF A01 CSCL21E

The effects of fan inlet temperature transients on theperformance and stability of a turbofan engine were determinedThe experiment was conducted at 90 and 74 percent oflow-pressure-rotor military speed (9525 rpm) and with fan inlettemperature distortions having circumferential extents of 90 deg180 deg. 270 deg. and 360 deg Temperature transients werecontrolled by varying the magnitude and rate of change of theinlet temperature rise The engine response ranged from amomentary compressor pressure disturbance to low-pressure-compressor stall The compressor distortion limits decreased withdecreasing low-pressure-rotor speed and increased with increasingcircumferential extent of distortion Analysis of the datasuggests strongly that the distortion limits of the compressorare a function of a critical magnitude of inlet temperature riseand are independent of the temperature nse rate Author

N77-31164*jjl National Aeronautics and Space AdministrationLewis Research Center Cleveland. OhioDEVELOPMENT AND VERIFICATION OF REAL-TIME.HYBRID COMPUTER SIMULATION OF F10O-PW-100(3)TURBOFAN ENGINE

John R Szuch. Kurt Seldner. and David S Cwynar Sep 197775 p refs(NASA-TP-1034. E-9090) Avail NTIS HCA04/MFA01 CSCL21E

A real time, hybrid computer simulation of a turbofan engineis described Controls research programs involving that engineare supported by the simulation The real time simulation isshown to match the steady state and transient performance ofthe engine over a wide range of flight conditions and powersettings The simulation equations. FORTRAN listing, and analogpatching diagrams are included Author

N77-31165*# National Aeronautics and Space AdministrationLewis Research Center. Cleveland, OhioADVANCED TURBOPROP TECHNOLOGY DEVELOPMENTJ F Dugan D P Bencze. and L J Williams 1977 39 prefs Presented at Aircraft Systems and Technol Meeting. Seattle22-24 Aug 1977 sponsored by AIAA(NASA-TM-73729. E-9290) Avail NTIS HC A03/MF A01CSCL 21E

The efficiency of high-speed turboprop propulsion systemsis considered with emphasis on fuel savings Specific topicsdiscussed include (1) high efficiency and low noise of propellerdesign. (2) fuselage noise attenuation. (3) propeller and gearbox maintenance and (4) engine-airframe integration J M S

N77-31166*| Illinois Univ. Urbana Oept of Aeronauticaland Astronautical EngineeringPROPELLER STUDY PART 1 INTRODUCTION ANDOVERVIEWAllen I Ormsbee Jul 1977 16 p 3 Vol(Grant NCR-14-005-194)(NASA-CR-155002, AAE-77-12-PM,UILU-ENG-77-0512-PM) Avail NTIS HC A02/MF A01 CSCL01C

A general aerodynamic-acoustic theory was developed fordetermining the acoustical design of propellers used on generalaviation aircraft Data from the theoretical investigation wereapplied in the design of a propeller whose thrust and torquewere measured during a senes of YO-3A aircraft flight tests

Author

N77-31167*jjl Illinois Univ. Urbana Dept of Aeronauticaland Astronautical EngineenngPROPELLER STUDY PART 2: THE DESIGN OF PROPEL-LERS FOR MINIMUM NOISEAllen I Ormsbee and Chung-Jin Woan Jul 1977 203 p refs3 Vol(Grant NGR-14-005-194)(NASA-CR-155005. AAE-77-13-Pt-2.UILU-ENG-77-0513-Pt-2) Avail NTIS HCA10/MFA01 CSCLQIC

The design of propellers which are'efficient and yet produceminimum noise requires accurate determinations of both the flowover the propeller Topics discussed in relating aerodynamicpropeller design and propeller acoustics include the necessaryapproximations and assumptions involved, the coordinate systemsand their transformations, the geometry of the propeller blade,and the problem formulations including the induced velocity,required in the determination of mean lines of blade sections,and the optimization of propeller noise The numerical formulationfor the lifting-line model are given Some applications andnumerical results are included Author

N77-31158*# Illinois Univ. Urbana Dept of Aeronauticaland Astronautical EngineeringPROPELLER STUDY. PART3 EXPERIMENTAL DETERMIN-ATION OF THRUST AND TORQUE ON THE YO-3AAIRCRAFTAllen I Ormsbee. S A Siddiqi. and K R Sivier Sep 197760 p refs 3 Vol(Grant NGR-14-005-194)(NASA-CR-155003. AAE-77-14-Pt-3. UILU-ENG-77-0514)Avail NTIS HC A04/MF A01 CSCL 01C

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N77-31161

Instrumentation and procedures for obtaining m-flightmeasurements of the torque and thrust of a propeller mountedon a YO-3A aircraft are described Problems encountered in thestudy are discussed and methods for eliminating these difficultiesare suggested Author

N77-31161# Pratt and Whitney Aircraft Group West PalmBeach, Fla Government Products DivADVANCED COOLED TURBINE AIRFOIL AERODYNAMICINVESTIGATION Final Report. 15 Sep 1975 - 30 Jan1977W G Hess Feb 1977 55 p(Contract F33615-76-C-2009)(AD-A041137. AFAPL-TR-76-113) Avail NTISHC A04/MF A01 CSCL 21/5

Several correctively cooled trailing edge designs wereinvestigated with the objective of eliminating the need for filmcooling on the airfoil suction side A 43 4% reduced solidityfirst stage turbine vane having potential application for anadvanced Air Force fighter engine was selected for the evaluationThe final design eliminates film cooling on the suction side anduses the wavy criss-cross slot as the cooling scheme for thetrailing edge section The cooling design was incorporated intoa cascade test airfoil using the radial wafer fabrication techniqueThe airfoil was constructed by photoetchmg the cooling designinto the individual wafers bonding the wafers together andmachining the bonded block into the airfoil shape The airfoilwas subsequently evaluated in an airfoil cascade test to determinethe aerodynamic and cooling performance The aerodynamic profileloss of the reduced solidity radial wafer airfoil was reduced56% relative to a baseline 43 4% reduced solidity configurationwith film cooled suction surface and was 30% under the programgoal The wavy criss-cross slot design used in the trailing edgesection proved to be an efficient cooling technique, and eliminatedthe need for suction side film cooling GRA

N77-3il62# Thermal Technology Labs, Buffalo, N YDEVELOPMENT OF LIGHTWEIGHT TRANSFORMERS FORAIRBORNE HIGH POWER SUPPLIES Interim Report. Jan.1976 - Jun 1976D I Lockwood, R I McNall. Jr and R L Haumesser Dec1976 90 p refs(Contract F33615-75-C-2014 AF Pro| 3145)(AD-A041515. AFAPL-TR-76-102) Avail NTISHC A05/MF A01 CSCL 09/1

Several major developments have occurred in this programAs is often the case in research they did not occur exactly inaccordance with the original plan The total program however isessentially on schedule New techniques for fabrication of piewound transformers were developed which yielded superiordesigns This development was followed by the developmentof computer aided design programs for pie wound transformersSeveral 10KW transformers have been fabricated and subjectedto a variety of tests Based on the results of these tests boththe 10KW and 200 KW transformers will be pie rather thanlayer wound A 10KW transformer rectifier system is presentlybeing integrated with a breadboard inverter for final verificationOunng the first half of this program, a numerical method wasdeveloped for the solution of the nonlinear lumped parametertransformer model This model was developed under theprevious contract, but no stable solution had been found Thepresent solution is for a resistive load and work is continuing toinclude leakage inductance, shunt capacitance, and an arbitraryload impedance The present program has been implementedon the HP 9830 machine As mentioned above, pie woundtransformer design programs have been written These are forinteractive design on the HP 9830 and are not self optimizingroutines A decision should be made as to the ultimate applicationof these programs before a decision whether or not to implementthem on the CDC 6600 is reached ' GRA

N77-31163# Rolls-Royce Ltd. Derby (England)FAN SUPERSONIC FLUTTER PREDICTION AND TESTANALYSIS

D G Halhwell London Aeron Res Council 1977 24 prefs Supersedes ARC-36374(ARC-R/M-3789. ARC-36374) Avail NTIS HCA02/MFA01.HMSO £3 PHI

The aerodynamic and vibration characteristics of unstalledsupersonic flutter in fan assemblies having part-span shrouds orclappers are described It is briefly compared and contrastedwith stall flutter The importance of frequency and modeshapeanalyses is stressed and. supersonic flutter prediction methodsare examined, commencing with the modeshape parameterUnsteady work theory leads to the study of aerodynamic dampingwith the prediction of flutter mode speed and wave directionThroughout, emphasis is given to the support of design analysisby test data, from laboratory measurements on stationary modelsto full scale engine altitude test chamber behavior Finally, theeffect on flutter of some of the opening criteria in engine serviceis considered Author (ESA)

N77-31168# California Research and Technology. Inc . WoodlandHillsNUMERICAL ANALYSES OF SOFT BODY IMPACTS ONRIGID AND DEFORMABLE TARGETS Intenm TechnicalReport. Jul - Dec 1975M Rosenblatt, G E Eggum. L A DeAngelo. and K NKreyenhagen Dec 1976 96 p refs(Contract F33615-75-C-5052)(AD-A040030 AFML-TR-76-202) Avail NTISHC A05/MF A01 CSCL 21/5

A two-dimensional finite difference code, WAVE-L, was usedto investigate the impact of soft bodies (birds) on both rigidand deformable targets The soft body was numerically modeledas a water sphere Three impact cases were examined impactsonto rigid targets (both normal and oblique), impact onto adeformable target (a stainless steel disk) and impact onto theedge of a typical jet engine fan blade For the impacts ontorigid targets the finite difference calculation was used to obtainthe pressures produced at impact, the distribution of pressureover the target and the total force exerted on the target Thesecalculations were compared with experimentally measured valuesThe impact onto a stainless steel disk was also modeled withthe finite difference code Plate deformation, impact pressuresand forces were calculated The fan blade impacts were modeledin two phases The impact loading pressures and forces werecalculated with the finite difference model The blade was thenmodeled with a three dimensional finite element code. NON-SAP, using the finite difference pressures on impact

Author (GRA)N77-31169I Princeton Univ. N J Dept of Aerospace andMechanical ScienceRESEARCH ON NOISE GENERATED BY DUCTED AIR-FUELCOMBUSTION SYSTEMS Final Report. Mar 1971 - Mar1977E G Plett and M Summerfield Mar 1977 32 p refs(Contracts N00014-67-A-0151-0029 N00014-75-C-0507)(AD-A039957. AMS-1327) Avail NTIS HC A03/MF A01CSCL 21/5

Throughout the research program, emphasis has been placedon obtaining a better understanding of the importance ofcombustion as a source of noise in jet engines This has beenpursued in terms of theoretical modeling and experimentalinvestigations A theoretical model was developed to allowcomputation of the role internal sources as well as externalsources Calculations based on reasonable approximationsindicated that for subsonic jet velocities, internal sources couldbe much more important than the jet noise sources Experimentsin a cold flow with cylindrical struts immersed in the flow togenerate unsteadiness demonstrated this effect More to thepoint, experiments with a ducted combustor also verified thatthe combustion though occurring inside the duct, causesunsteadiness in the exhaust flow which is directly responsiblefor noise generation The noise thus attributable to the combustionwas found to be dominant over jet noise for subsonic jets toMach numbers of approximately 06 A unified theory ofcombustion noise generation was developed Direct verificationof the importance of the various source terms was begun Initialresults suggest that at least several of the terms are important

GRA

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N77-31175

N77-31170# Bolt Beranek and Newman Inc. Canoga ParkCalifCALCULATION OF SIDE LINE NOISE LEVELS DURINGTAKEOFF Technical Report. Aug. - Sep 1976John F Mills Sep 1976 30 p refs(Contract F33615-76-C-0507)(AD-A040624 BBN-3298 AMRL-TR-76-123) Avail NTISHC A03/MF A01 CSCL 01/5

This report discusses an improved analytical approach forcomputing the sideline noise generated by aircraft during takeoffroll The relationship accounts for the effects of acceleration onthe typical shape of noise radiation pattern from a static full-powerground runup This simplified model is suitable for handcalculations or direct implementation into NOISEMAP, thecomputerized procedure used by the Air Force to generate contoursof equal noise exposure about airbases resulting from aircraftflight and ground runup operations For the Boeing707-300 aircraft, the new simplified model yielded results within0 5 db of those obtained with more complex computationalprocedures involving the effects of forward speed on the jetnoise output GRA

N77-31171jj! Exxon Research and Engineering Co Linden. NJGovernment Research LabDEVELOPMENT OF A CATALYTIC COMBUSTOR FORAIRCRAFT GAS TURBINE ENGINES Final Technical Report.22 May 1975 - 22 Sep 1976Vincent J Simmski and Henry Shaw 22 Sep 1976 166 prefs(Contract F33615-75-C-2033)(AD-A040135. EXXON/GRU 1BFA76 AFAPL-TR-76-80) AvailNTIS HC A08/MF A01 CSCL 21/5

The pollution problems associated with unburned hydrocar-bons and carbon monoxide in the idle mode, and NOx andsmoke production in the power mode of aircraft gas turbineOperation can be minimized using hybrid catalytic combustionA hybrid catalytic combustor consists of a fuel-rich precombustorsecondary air quenching zone and monolithic catalyst stagewhich rapidly oxidizes CO and UHC produced in the pre-combustorThe concentration of thermally-produced NOx in the pre-combustoris very low because of the lack of oxygen However, the formationof NOx precursors such as HCN and NH3 produced under fuelnch conditions must be considered Data showed that nitrogeneousspecies produced in the rich pre-combustion zone were efficientlyconverted to NOx by catalysts under the very lean mixtureconditions that result from the secondary air quench Theequivalence ratio in the pre-combustor was varied from 0 5 to1 5. while the overall mixture, after secondary air injection, wasin the range of 0 1 to 0 3 GRA

N77-31172# General Electric Co. Cincinnati. Ohio AircraftEngine GroupDIGITAL SHAFT ENCODER Final Technical Report. Feb.1974 - Oct. 1976William R Spencer and Howard B Kast Dec 1976 65 p(Contract F33615-74-C-2007)(AD-A040706. R77AEG194. AFAPL-TR-76-106) Avail NTISHC A04/MF A01 CSCL 21/5

This report documents the design, test, and development ofa high temperature digital rotary position transducer Use ofmagnetic sensors in this shaft encoder eliminates the need forbrushes or light sources to create the eight-bit digital outputsignal Included in the project were environmental testing andon-engine operation A digital electronic readout instrument wasbuilt to aid circuit development and testing The simpleconstruction of the encoder makes this device well suited foraircraft engine applications Author (GRA1

N77-31173# Iowa State Univ of Science and TechnologyAmes Engmeenng Research InstMULTISTAGE AXIAL-FLOW TURBOMACHINERY WAKEPRODUCTION. TRANSPORT. AND INTERACTION InterimReport. 1 Sep 1976 - 3O Sep 1976

Douglas P Schmidt and Theodore H Okiishi Nov 1976 237 prefs(Contract AF-AFOSR-2916-76)(AD-A041108 ISU-ERI-AMES-77130. TCRL-7AFOSR-77-0720TR) Avail NTIS HC A11/MF A01 CSCL13/7

The first year results of a study of multistage axial-flowturbomachme wake production transport and interaction aredescribed in this report Evidence indicating how the noiselevel measured at the inlet of a low speed, multistage, axial-flowresearch compressor was found to vary appreciably with inletguide vane and stator row relative circumferential positioningwith the largest amount of noise reduction occurring at theblade passing frequency The results of detailed slow- (cobraprobe and surface pressure taps) and fast-response (hot-wire)measurements made within the research compressor flow fieldto aid in understanding the physics involved are shown inscalar and vector plots and tables Significant local changes inblade-section aerodynamic performance and flow field appearancewith variation in stationary blade row placement were observedalthough corresponding improvement of overall efficiency couldnot be ascertained Several interesting periodically unsteadyaspects of the flow field and its measurement are demonstratedand some conclusions about blade row interaction are pro-posed Author (GRA)

N77-31174*# National Aeronautics and Space AdministrationAmes Research Center. Morten Field. CalifA FAILURE EFFECTS SIMULATION OF A LOW AUTHORITYFLIGHT CONTROL AUGMENTATION SYSTEM ON A UH-1HHELICOPTERLloyd D Corliss and Peter D Talbot Aug 1977 46 p refsPrepared in cooperation with USAAMRDL. Moffett Field. Calif(NASA-TM-73258. A-7097) Avail NTIS HC A03/MF A01CSCL 01C

A two-pilot moving base simulator experiment was conductedto assess the effects of servo failures of a flight control systemon the transient dynamics of a Bell UH-1H helicopter The flightcontrol hardware considered was part of the V/STOLAND systembuilt with control authorities of from 20-40% Servo hardoverand oscillatory failures were simulated in each control axisMeasurements were made to determine the adequacy of thefailure monitoring system time delay and the servo center andlock time constant, the pilot reaction times, and the altitudeand attitude excursions of the helicopter at hover and 60 knotsSafe recoveries were made from all failures under VFR conditionsPilot reaction times were from 05 to 075 sec Reduction ofmonitor delay times below these values resulted in significantlyreduced excursion envelopes A subsequent flight test wasconducted on a UH-1H helicopter with the V/STOLAND systeminstalled Series servo hardovers were introduced in hover andat 60 knots straight and level Data from these tests are includedfor comparison Author

N77-31175*# National Aeronautics and Space AdministrationAmes Research Center. Moffett Field. CalifA MATHEMATICAL FORCE AND MOMENT MODEL OF AUH-1H HELICOPTER FOR FLIGHT DYNAMICS SIMULA-TIONSPeter D Talbot and Uoyd 0 Corliss Jun 1977 45 p refsPrepared in cooperation with USAAMRDL Moffett Field. Calif(NASA-TM-73254. A-7080) Avail NTIS HC A03/MF A01CSCL 01C

A model of a UH-1H helicopter was developed to supportflight simulations and for developmental work on an avionicssystem known as V/STOLAND system Equations and numericalvalues of constants used to represent the helicopter are presentedResponses to stop inputs of the cyclic and collective controlsare shown and compared with flight test data for a UH-1HThe model coefficients were adjusted in an attempt to get aconsistent match with the flight time histories at hover and60 knots Response matching was obtained at 60 knots, butthe matching at hover was not as successful Pilot evaluationsof the model, both fixed and moving base, were made Author

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N77-31516

promise to be superior to any comtemporary airplanes in termsof cost-effectiveness and energy-hydrocarbon jet fuel, whethermanufactured from oil shale, coal or crude oil. remains themost attractive aviation fuel for future Air Force use Policyrecommendations are made pertaining both to alternative fuelsand to advanced-technology large airplanes Future research anddevelopments are also identified Author (GRA)

N77-31355*# National Aeronautics and Space AdministrationLewis Research Center. Cleveland, OhioASDAR (AIRCRAFT TO SATELLITE DATA RELAY) FLIGHTTEST REPORTEdward J Domino, Robert R Lovell Martin J Conroy and DavidH Gulp Aug 1977 21 p(NASA-TM-73744 E-9311) Avail NTIS HC A02/MF A01CSCL 17B

The aircraft to Satellite Data Relay (ASDAR) an airbornedata collection system that gathers meteorological data fromexisting aircraft instrumentation and relays it to ground user viaa geo-synchronous meteorological satellite, is described and theresults of the first test flight on a commercial Boeing 747 aircraftare presented The flight test was successful and verified systemperformance in the anticipated environment Author

N77-31368# Naval Ocean Systems Center San Diego CalifAN/PRC-S6 HELMET RADIO SET UPGRADING RECOM-MENDED MODIFICATIONS REQUIRE MINIMAL RE-SOURCES BUT PROMISE CONSIDERABLE IMPROVEMENTIN RELIABILITY OPERABILITY. AND LOGISTICS SUPPORTTechnical Document, Jul 1976 - Apr 1977T H Townsend 15 May 1977 29 p refs(AD-A041190, NOSC/TD-105) Avail NTIS HC A03/MF A01CSCL 17/2

A field change, printed as an appendix to this document, isrecommended as the means of accomplishment for most of thecorrective actions suggested here It includes new on/off andpush-to-talk switches a microphone with windscreen a longermicrophone boom an improved squelch adjustment, improved-reliability parts, more-stable tuning and sidetone Action bydepot and navelex is also recommended Author (GRA)

N77-31384# Mississippi State Univ Mississippi State Engineer-ing Industrial Research StationA STUDY OF THE CHARGE AND CURRENT INDUCED ONAN AIRCRAFT IN AN EMP SIMULATOR FACILITYPART 1 THE FORMULATION PART 2 THE SIN-GULARITY EXPANSION METHOD PART 3 THENUMERICAL RESULTS Final ReportClayborne D Taylor Keh-Tong Chen Terry T Crow and MuraliKumbale Dec 1976 168 p refs(Grant AF-AFOSR-2961-76)(AD-A039507 AFOSR-77-0636TR) Avail NTISHC A08/MF A01 CSCL 18/3

A study of the aircraft skin current and charge is made foran aircraft under the illumination of the electromagnetic fieldproduced by a nuclear EMP simulator This work is motivatedby the need to relate the response of an aircraft in the EMPsimulator to the response of an aircraft under actual EMPillumination The analysis toward a specific EMP simulator atKirtland AFB New Mexico however, the methodology presentedis applicable to other types of simulator facilities Author (GRA)

N77 31389# TOR. Inc , Los Angeles. CalifFOUNDATION OF THE MAGNETIC FIELD INTEGRALEQUATION CODE FOR THE CALCULATION OF THEELECTROMAGNETIC PULSE EXTERNAL INTERACTIONWITH AIRCRAFT Final ReportMaurice I Sancer. Scott Siegel and A D Varvatsis Apr 1977147 p refs

(Contract F29601-75-C-0067)(AD-A039953. AFWL-TR-76-279) Avail NTISHC A07/MF A01 CSCL 01/3

This report presents the equations that are programmed alongwith their derivations and the underlying theory The code

determines the current density and charge density induced en amodel of an aircraft The equations that are programmed resultfrom patch zoning the aircraft model in order to obtain a solutionto the frequency domain representation of the magnetic fieldmtergral equation The intent is to obtain solutions for a continuousspectrum that includes the low and resonant range of frequen-cies corresponding to the bulk of the energy in a typical EMPspectrum Author (GRA)

N77-3144O*# National Aeronautics and Space AdministrationLangley Research Center. Langley Station. VaHEAT-TRANSFER AND PRESSURE MEASUREMENTS ONA SIMULATED ELEVON DEFLECTED 30 DEG NEAR FLIGHTCONDITIONS AT MACH 7Charles B Johnson, Allan H Taylor, (Vought Corp, Hampton,Va), and Irving Wemstem Sep 1977 36 p refs(NASA-TM-X-3563, L-11524) Avail NTIS HC A03/MF A01CSCL 20D

Heat transfer rates and pressures were obtained on an elevonplate (deflected 30 deg) and a flat plate upstream of the elevonin an 8 foot high-temperature structures tunnel The flight Reynoldsnumber and flight total enthalpy for altitudes of 26 8 km and28 7 km at Mach seven were duplicated The heat transfer andpressure data were used to establish heating and pressureloads The measured heating was compared with severaltheoretical predictions, and the closest agreement obtained witha Schultz-Grunow reference enthalpy method of calculation

Author

N77 31477# ARO. Inc. Arnold Air Force Station TennLASER VELOCIMETER UTILIZATION IN JET ENGINEALTITUDE TEST CELLS Final Report. Oct 1976 - Jun.1976D 0 Barnen AEDC Jun 1977 36 p refs(AD-A041019. ARO-ETF-TR-76-147. AEDC-TR-77-21) AvailNTIS HC A03/MF A01 CSCL 14/2

The feasibility of utilizing a laser velocimeter (LV) in turbineengine testing in an altitude test cell was investigated Aone-component LV and associated environmental control system(ECS) were designed, fabricated and installed in Test Cell J-2of the Engine Test Facility (ETF) LV measurements made onthe centerlme of an F101 engine at one axial station downstreamof the nozzle exit are presented and compared to the calculatedexit velocity Design data are presented on the vibidtion levelsand temperatures encountered by the LV over a range of engineoperating conditions It was found that sufficient natural seedmaterial existed in the exhaust flow to allow the LVto characterizethe exit velocity of a turbojet engine during altitude testing

Author (GRA)

N77-31607# Timken Co Canton OhioTAPERED ROLLER BEARING DEVELOPMENT FOR AIR-CRAFT TURBINE ENGINES Final Report. 8 Mar. 1976 -8 Mar 1977Peter S Orvos Wright-Patterson AFB Ohio AFAPL Apr 197792 p refs(Contract F33615-76-C-2019)(AD-A041317 AFAPL-TR-77-6) Avail NTISHC A05/MF A01 CSCL 21/5

Finite element methods were used to structurally analyzevarious potential high speed tapered roller bearing cage designsThese cage designs included roller guided and race guidedconfigurations The two approaches used in the analysis werefirst to model the full cage using beam elements and thenintensively analyze a segment using solid elements In summaryit was determined that centrifugal forces mostly affect high speedcage stress and deformation, and the race guided cage exhibitsthe greatest strength Author (GRA)

N77-31616# Johns Hopkins Univ, Baltimore Md Dept ofMechanics and Materials ScienceULTRASONIC DETECTION OF FATIGUE DAMAGE INAIRCRAFT COMPONENTS Annual Report, 1 Mar • 28 Feb1977

544

N77-31529

Robert E Green. Jr and Robert B Pond. Sr Mar 1977114 p refs(Contract F44620-76-C-0081)(AD-A04OO09. AFOSR-77-0658TR) Avail NTISHC A06/MF A01 CSCL 11/6

The purpose of the present research is to extend and applythe ultrasonic techniques developed under AFOSR Contract NoF44620-71-C-O062 to the detection of fatigue damage in testspecimens which are made from materials and possess geometriestypical of actual aircraft components Ultrasonic attenuationmeasurements made simultaneously with fatigue tests onaluminum alloy bars gave warning of crack formation and eminentfracture much earlier than conventional ultrasonic methods Similartests are currently being run on aluminum alloys possessinggeometnes typical of actual aircraft components Analysis ofacoustic emission measurements made simultaneously withultrasonic attenuation measurements dunng fatigue testing haverun into difficulty because of the lack of a proper acoustic emissioncharacterization system which would permit optimum separationof the defect created acoustic emission signals from thebackground noise GRA

N77-31529# TRW Defense and Space Systems Group. RedondoBeach. CalifADVANCED HIGH SPEED ROLLER BEARING INSPECTIONTECHNIQUES Final Report. 30 Oct 1976 - 1 Apr. 1977Jerold L Jacoby and Jack R Bohn May 1977 80 p refs(Contract F33615-76-C-2147)(AD-A042121. AFAPL-TR-77-32) Avail NTISHC A05/MF A01 CSCL 14/2

A comprehensive survey of state-of-the-art precision measure-ment techniques applicable to dimensional inspection of rollersfor high speed bearings (greater than 20 million DN) wasundertaken Particular attention was given to noncontactingtechniques which would permit automated 100% inspection ofthe rollers for use in such bearings The measurement techniqueswere evaluated to determine their utility for incorporation into acost-effective roller inspection system A concept for a fullyautomated roller inspection system is described It provides forthe preparation, inspection, re-oiling and sorting of the rollerswith minimal human supervision The system is conceived to beself-contained so that it can operate independent of environmentalconstraints It can be developed by adapting existing technologyto the specific requirements for roller inspection Author (GRA)

'Milton M Klein 2 Feb 1977 23 p refs(AD-A040704. AFGL-TR-77-0033. AFGL-AFSG-361) AvailNTIS HC A02/MF A01 CSCL 04/1

Experimental and theoretical programs are being conductedto aid in the development of an operational Warm Fog DispersalSystem using ground based heat sources To help determineoptimum heat and thrust combinations for the system, investiga-tions have been made of the buoyant motion of heated turbulentjets in co-flowing, that is, same direction ambient winds Totake account of the ground effect an analysis has been madeof the experimental data for the planar |et at the point of lift-offin terms of the local Froude number at this point From thiscorrelation a procedure has been developed for determining thelift-off point, using the ambient wind and initial velocity andtemperature of the jet as input variables A new jet trajectorymay now be easily calculated with only a simple modificationof the original method in which the ground effect was ignored

GRA

N77-31922# Bolt. Beranek. and Newman. Inc, Canoga Park,CalifSELECTION OF MINIMUM DAY/NIGHT LEVELS FORNOISEMAP CONTOUR CALCULATIONSDwight E Bishop Nov 1976 15 p(Contract F33615-76-C-0507 AF Proj 7231)(AD-A040623, BBN-10189. AMRL-TR-76-124) Avail NTISHC A02/MF A01 CSCL 01/5

This report discusses guidelines for the minimum Day/ NightLevel (DNL) values that should be used with NOISEMAP typecomputations to (1) insure adequate accuracy of the lowestcontour level for a given set of aircraft operations, and (2) minimizethe number of machine computations and thereby reduceoperating costs An analysis is made of the errors introduced inthe DNL contour values due to truncation of the partial DNLcutoff determined by the single event noise level or the numberof aircraft operations for a particular flight path For a givenairbase and fixed volume of aircraft operations, the cutoff occursat higher single event noise levels as the number of aircraftflight paths or aircraft classes are increased Finer detail indescribing the aircraft operations results in the cutoff noise levelsbeing raised with an increased error at the edges of the DNLgnd computations, but with a corresponding decrease in themachine running time These DNL cutoff guidelines have beenincorporated into version 3 4 of NOISEMAP Author (GRA)

N77-31637*|jl Old Dominion Umv Research Foundation, NorfolkVaVIBRATION ANALYSIS OF ROTOR BLADES WITH ANATTACHED CONCENTRATED MASS Technical Report,1 Jun - 16 Aug 1976V R Murthy and P S Barna Aug 1977 191 p refs(Grant NsG-1143)(NASA-CR-154987) Avail NTIS HC A09/MF A01 CSCL20K

The effect of an attached concentrated mass on the dynamicsof helicopter rotor blades is determined The point transmissionmatrix method was used to define through three completelyautomated computer programs the natural vibrational characteris-tics (natural frequencies and mode shapes) of rotor blades Theproblems of coupled flapwise bending chordwtse bending, andtorsional vibration of a twisted nonuniform blade and its specialsubcase pure torsional vibration are discussed The orthogonalityrelations that exist between the natural modes of rotor bladeswith an attached concentrated mass are derived The effect ofpitch rotation, and point mass parameters on the collective,cyclic, scissor, and pure torsional modes of a seesaw rotorblade is determined Author

N77-31722# Air Force Geophysics Lab. Hanscom AFB, MassA METHOD FOR DETERMINING THE POINT OF LIFT-OFFAND MODIFIED TRAJECTORY OF A GROUND-BASEDHEATED TURBULENT PLANAR JET IN A CO-FLOWINGWIND

N77-32012# Northrop Corp. Hawthorne. Calif Aircraft DivWAVE DRAG REDUCTION FOR AIRCRAFT FUSELAGE-WING CONFIGURATIONS VOLUME 1 ANALYSES ANDRESULTS Final Report. 30 Jun 1975 - 30 Oct 19/6C W Chu J Der, Jr. and H Ziegler Warmmster Pa NADCOct 1976 143 p refs(Contract N62269-75-C-0537)(AD-A040997, NOR-76-190-Vol-1 NADC-77157-30-Vol-1)Avail NTIS HC A07/MF A01 CSCL 05/2

An optimization procedure has been developed to minimizethe wave drag of an aircraft fuselage-wing configuration subjectto constraints imposed by design requirements The theory,methods computer programs and results are presented m thisreport in two volumes This volume describes analyses, resultsand the optimization procedure The procedure makes use ofthe Latin Square sampling technique and the Three-DimensionalMethod of Characteristics The former is used to efficiently samplethe family of configurations, and the latter is used to accuratelycalculate the wave drags of the sampled configurations Thecalculated wave drag coefficients are then used to derive afunctional dependence of the wave drag on the geometric variablesthat define the family of configurations The minimum wave dragconfiguration can be obtained by minimizing the wave dragfunction subject to a given set of constraints The wave dragreduction procedure is demonstrated using an F-4 type configura-tion as the baseline The results are presented and discussed

GRA

545

M77-31176

W77-31178°/jf National Aeronautics and Space AdministrationLangley Research Center Langley Station VaVORTEX-UFT ROLL-CONTROL DEVICE Potent ApplicationJohn E Lamar. inventor (to NASA) Filed 21 Mar 1977 11 p(NASA-Case-LAR-11868-2. US-Patent-Appl-SN-779429) AvailNTIS HC A01/MF A02 CSCL 01C

A wing is described which constitutes a roll control devicefor aircraft of cropped, arrow-type planform with thin leadingand side edges having a pivotable tip to alter the crop angle ofthe wing during flight Increasing the crop angle causes thewing side edge to become a trailing edge thereby reducing thewing surface area which the leading edge and side edge shedvortex systems can act against This reduction also diminishesthe strength of the shed vortex system Decreasing the cropangle causes opposite results NASA

N77-31177# Techmsche Hochschule Darmstadt (West Ger-many) Inst fuer FlugtechnikINVESTIGATION OF FLIGHT DYNAMICS DURING ROLL[UNTERSUCHUNG DEB FLUGDVNAMIK BEIM ROLLER]]H D Fmck and G Sachs 5 Apr 1976 58 p refs InGERMAN(IFD-8/76) Avail NTIS HC A04/MF A01

The dynamics of a highly maneuverable subsonic aircraftduring multiple roll around the length axis were investigatedwith a 6 deg of freedom computer program The nonlineardependencies on the aerodynamic forces and moments are takeninto account The effect of the dynamic derivation of lateralmotion on the overall motion is shown The relationship betweenthe position of the overall rotation vector and the velocity vectoris represented ESA

N77-31178# Techmsche Hochschule. Darmstadt (West Ger-many) Inst fuer FlugtechnikRECOGNITION CRITEHJON AND PRODUCTION OF EASILYSOLVABLE MODELS FOR FLIGHT MECHANICAL OPTIG30Z-ATION PROBLEMS [EHKENNUNG8KHITGRJUM UNOERZEUGUNG LEICHT LOE8QAREB MODELLE FUERFLUGMECHANISCHE OPTIK3IEKIUNGSPHOBLEME]Bernd Faber 12 Nov 1976 118p refs In GERMAN(IFD-9/76) Avail NTIS HC A06/MF A01

A simplification scheme is presented for obtaining easilysolvable flight mechanical optimization models based on point-wiseoptimization, which allows attaining the least number of physicalapproximations Several extensively described examples show thatnew optimization statements can be obtained easily by usingtne scheme The point-wise method is applicable in combinationwith a solution scheme ESA

N77-3117BjJ! National Aerospace Lab. Amsterdam (Netherlands)Flight Dynamics DivHANDLING QUALITY CRITERIA DEVELOPMENT FORTRANSPORT AIRCRAFT WITH FLY-BY-WIRE PRIMARYCONTROL SYSTEMSH A MOOIJ 9 May 1977 124 p refs(Contracts NIVR-1745. RB-RLD-1973-1 1)(NLR-TR-74141-U) Avail NTIS HC A06/MF A01

The introduction of fly-by-wire primary flight control systemsin certain cateoones of future transport aircraft, makes it highlydesirable to ..utiate further studies into handling quality cntenafor future guidance m system design and airworthiness certifica-tion The handling Quality cntena for such aircraft must be basedon parameters which describe the combination of the aircraftand its closed-loop flight control system Approach flight simulationand compensatory tracking, performed on a moving base flightsimulator as applied to a conceptual jet transport developedaround the relaxed static stability concept, is described Thefrequency of the dominant mode of the pitch attitude controlsystem and the effectiveness of the direct-lift-control-system werethe parameters varied Results of the flight simulator experimentand a pilot-aircraft system analysis are discussed In the literatureproposed criteria (two-aircraft state vanable weighted sum andthe pilot-m-the-loop criteria) are evaluated against simulator resultsobtained in this program Author (ESA)

R)77-31180# National Aerospace Lab , Amsterdam (Netherlands)Flight Dynamics DivTHE NEED OF STICK FORCE STABILITY FOR ATTITUDE-STABILIZED AIRCRAFT. PART 1H A MOOIJ and M F C vanGool 19 Mar 1976 62 p refs(Contracts NIVR-1745 RB-RLD-1975-1 1)(NLR-TR-76125-U) Avail NTIS HC A04/MF A01

After introductory background information on the landingapproach piloting task and some arguments for expanding theknowledge of handling quality criteria for certain advancedtransport designs, results are given of the flight tests related tothe effect of positive stick force stability on the longitudinalcontrollability in the landing approach of an attitude-stabilizedaircraft Positive stick force stability reduced airspeed deviationsfrom the reference speed and the subjective pilot effort spenton airspeed holding for the aircraft configuration investigatedBased on the results obtained, follow-up testing, using a jettransport aircraft during visual approaches, is recommended

Author (ESA)

N77-31184# Naval Air Propulsion Test Center Trenton NJDept of Propulsion Technology and Project EngineeringWAPTC FACILITY MODIFICATIONS REQUIRED FORALTITUDE TESTING OF CURRENT V/STOL ENGINE FinalReportJoseph F Boytos and John Lezniak May 1977 42 p refs(AD-A041608. NAPTC-PE-102) Avail NTISHC A03/MF A01 CSCL 21/5

Modifications were made to NAPTC altitude chamber 3E toprovide the capability to test current V/STOL aircraft enginesA test program was conducted with a F402 vectored-thrustturbofan engine to evaluate the modifications and verify facilityoperational capability Author (GRA)

W77-31218// Kaman Sciences Corp Colorado Springs ColoAN EVALUATION OF BOUNDARY LAYER FORCES ANDMEASUREMENT METHODS Final ReportJ C Nickell. V D Peckham. and T F V Meagher Oct 1976146 p refs(Contract DNA001-75-C-0038)(AD-A040947. K-76-118UIR), DNA-4202F) Avail NTISHC A07/MF A01 CSCL 20/4

An analysis has been performed of the effects of asymmetrichypersonic boundary layer transition on conical reentry vehiclesrelative to the forces and moments acting on the vehicle Therelative importance of boundary layer thickening increased surfacemass transfer, and changes in skin friction have been addressedand the effects of each of these terms on the vehicle forcesand moments have been estimated This analysis indicates thatboundary layer thickening is the most significant factor occuringduring boundary layer transition and may be a source oftransient vehicle instability during the boundary layer transitionevent GRA

N77-313340 RAND Corp Santa Monica. CalifAN EVALUATION OF VERY LARGE AIRPLANES ANDALTERNATIVE FUELS Interim ReportW T Mikolowsky L W Noggle. W F Hederman and R EHorvath Dec 1976 401 p refs(Contract F49620-77-C-0023)(AD-A040532. R-1889-AF) Avail NTIS HC A18/MF A01CSCL 01/3

Very large airplanes using alternative fuels are examined inthe context of existing and possible future Air Force missionsSynthetic jet fuel (JP), liquid methane liquid hydrogen, and nuclearpropulsion are the fuel alternatives selected for detailed analy-sis Conceptual designs of airplanes using each of these fuelswere developed and estimates were made of their life-cycle costand life-cycle energy consumption Mission analyses wereperformed to determine the effectiveness of the alternativeairplanes in strategic airlift specifically and in the station-keepingrole in general Results indicate that for most military applicationsairplanes with gross weights in excess of one million pounds

546

N77-32013

N77 32013# Northrop Corp Hawthorne, CalifWAVE DRAG REDUCTION FOR AIRCRAFT FUSELAGE-WING CONFIGURATIONS. VOLUME 2 MANUAL FORCOMPUTER PROGRAMS Final Report. 30 Jun 1976 -30 Oct 1976C W Chu. J Der Jr and H Ziegler Oct 1976 379 p(Contract N62269-75-C-0537)(AD-A040998. NOR-76-190-Vol-2. NADC-77 1 57-30-Vol-2)Avail NTIS HCA17/MFA01 CSCL 05/2

An optimization procedure has been developed to minimizethe wave drag of an aircraft fuselage-wing configuration subjectto constraints imposed by design requirements The theory,methods, computer programs and results are presented in thisreport in two volumes This volume is the user's manual for thecomputer programs The input/output information is describedin detail Listings of the programs are given and samples ofbuilt-in program diagnostic messages are explained Also includedare the logical structures of the programs and the descriptionsof the subroutines which in combination with the program listingscan be used for possible future modification, improvement, orextension of these computer programs GRA

547

SUBJECT INDEXAERONAUTICAL ENGINEERING/ A Special Bibliography (Suppl 90)

Typical Subject Index Listing

DECEMBER 1977

AEBOD11ABIC LOAPS-Early operation experience on the EBDA/HASA 100 kv

wind turbine rotor blade loads(HASA-TB-I-71601) H77-10610

TITLEREPORTNUMBER

The title is used to provide a description of the subiect matter When the title isinsufficiently descriptive of the document content a title extension is addedseparated from the title by three hyphens The NASA or AIAA accession numberis included in each entry to assist the user in locating the abstract in the abstractsection of this supplement If applicable a report number is also included as anaid in identifying the document

i-» AIBCBAFTStatistical analysis of OS Navy najor aircraftaccident rates, pilot and aircrafttime-dependent variables[AD-AOQ0096] K77-30099

1-7 AIBCBAFTA-7 titanium nose gear development

A77-«6801Accelerated environmental conditioning of the A-7D,composite outer wing

A77-46838Raster monitor display applications study for the

A-7E[AD-A039882] N77-30118

ACCBIEBATBD LIIB TESTSAccelerated environmental conditioning of the 1-7Dcomposite outer ving

A77-U6838ACCBIBBOBBTBBS

The development of primary equations for the nseof on-board accelerometers in determiningaircraft performance[AD-A03917<(] N77-30112

Statistical review of counting accelerometer datafor Davy and Marine fleet aircraft[AD-A041266] H77-31110

&COOSTIC SIHaiAIIOtfSimulation of flight-type engine fan noise in the

HASA-Levis 9 x 15 anechoic wind tunnel»77-a<|fl56

ADHESIVE BOBDII6Eiploratory of development of durability of

adhesive bonded joints[AD-A039864] H77-30219

Surface finishing of metal airfoils byadhesive bonding[HASA-CASB-HSC-12631-2] H77-31131

ABBIA1 BECOHIilSSAHCBAircraft laboratories and experience in nsing them

for the development of methods and means ofremote sensing of earth resources

A77-0.7199Space experiment simulation using an aircraft

laboratoryA77-17200

An evaluation of future BPV automatic navigationsystems

A77-II73U9Advanced avionics for the Advanced BemotelyPiloted Vehicle /ABPV/

A77-47350

A miniature rotary-wing BPVA77-47351

&EBOACOUSTICSCore noise source diagnostics on a tnrbofan engine

nsing correlation and coherence techniquesA77-tt<l<l57

AEBODTHABIC CflABACTBBISTICSFlight test results for an advanced technology

light airplaneC A I A A PAPEH 77-1217] A77-«q3i9

nonlinear lifting-surface theory for yawed andbanked wings in ground proximity

A77-45387The arrow wiug - Its potentialities and drawbacks

with regard to in-flight aerodynamic researchA77-H6606

Calculation of the aerodynamic characteristics ofa wing moving at subsonic speed, in the case ofa weak shock-wave effect on the wing

A77-47667Aerodynamic data and off-design characteristics of

the modified quasi-elliptical airfoil sectionHLB 7101[HLB-TB-76012-0] S77-3009U

in experimental investigation of a subscalevariable pressure ratio high thru flow tarbine[AD-A0398231] H77-30121

ABHODTIABIC COBFFICIEHTSin extended Kalman filter for estimating

aerodynamic coefficients[AD-AOU0594] H77-30092

AEBODIIABIC COHFISOBATIOHSInvestigations of three-dimensional flow

separation on fuselage configurations[AD-A039382] B77-30H21

An improved free wing for an aircraft[HASA-CASB-FBC-10092-1 ] H77-31135

lave drag reduction for aircraft fuselage-wingconfigurations. Volume 1: Analyses and resultsCAD-A040997] 1177-32012

AEBODTHiBIC DBAGAerodynamics of horizontally-opposed aircraft

engine installationsC A I A A PAPBB 77-12U9] A77-45508

Rave drag redaction for aircraft fuselage-wingconfigurations. Volume 1: Analyses and resultsIAD-A010997] N77-32012

AEBODYHAHIC FOHCBSSystematic pressure distribution and force

measurements of two yawed slender wings[IFD-2/76/I] H77-30Q95

Separated-flow unsteady pressures and forces onelastically responding structures

N77-31075AEBODTBABIC IOAOS

Optimum acoustic design of free-running low speedpropellers[ A I A A PAPBB 77-1248] A77-4H337

Application of the finite element techniquecombined with the collocation method to subsoniclifting surface problems

A77-47537Unsteady Airloads in Separated and Transonic Flow

[AGABD-CP-226] F77-31073Unsteady airloads in separated and transonic flow

B77-3107IIUnsteady airloads on an oscillating supercriticalairfoil

B77-31085A practical framework for the evaluation of

oscillatory aerodynamic loading on wings insupercritical flow

H77-31089

A-1

AEBODYBAHIC BOISE SUBJECT IJDEI

Statistical review of counting accelerometer datafor Havy and Harine fleet aircraftflD-AOl 12661 H77-311I10

AEBOD1BABIC 80ISBHam rotor wake/tail rotor interaction

A77-44441Propeller study. Part 2: The design of

propellers for minimum noise[BASA-CB-155005] H77-31157

4EBODYBAHIC STABILITYA new concept of static stability and its flighttesting in supersonic flight

A77-4U815A brief overview of transonic flutter problems

B77-31084AEBODISAHIC STALLING

Stall margin improvement by casing treatment - Itsmechanism and effectiveness in axial flowcompressorsf A S B E EAPEB 76-GT-A] A77-44345

Comparison of dynamic stall phenomena for pitchingand vertical translation motions[HASA-CB-27931 H77-30088

AEBODYBAaTCSAerodynamics of a confined jet with variable density

A77-47248Configuration of free vortices trailing off a wing

of finite spanA77-47669

Aircraft Soviet technologyH77-30067

Investigation of flight dynamics during roll[IFD-8/76] H77-31177

AEBOELASTICIT!Flutter-suppression studies on an actively

controlled variable-geometry wind-tunnel modelA77-<16805

AERONAUTICAL EHGIBBEBIBGThe computer for design and optimization with

applications to aircraft design, etcA77-46136

Design-to-cost in action[ASBE PAPEB 77-DB-9] A77-46904

Soviet aircraft and rockets[BASA-TT-F-770] N77-30065

Aircraft Soviet technologyN77-30067

Visual range: Concepts, instrumentaldetermination, and aviation applications[BBS-BONO-159] H77-30102

Propeller study. Part 1: Introduction and overview[BASA-CB-155002] H77-31156

Propeller study. Part 2: The design ofpropellers for minimum noise[BASA-CB-155005] H77-31157

AEBOHAOTICSIn Herculean flight Soviet aviation history

H77-30066HEROSAT SATELLITES

Satellite communications for the mobile service[AAS 76-045] A77-46630

Air traffic control experimentation and evaluationwith the HASA ATS-6 satellite. Volume 2:Demonstration of satellite-supportedcommunications and surveillance for oceanic airtraffic control[FAA-BA-75-64-V01-2] B77-31124

iEBOSPACE ERGHEEBIBGCase studies in aircraft design

[ A I A A PAPEB 77-1201] A77-44335Soviet aircraft and rockets

[BASA-TT-F-770] H77-30065HiSA/Havy lift/cruise fan. Phase 1: Design summary

[BASA-CB-135242] H77-31K19iEBOSPACE VEHIC1ES

Composite tanks for aerospace vehicle applicationA77-46516

*IB BBEATBIiG EBGIBESAircraft engines

B77-30068AIB COIDITIOBIB6 EQOIPHBHT

Variable geometry air cycle machine foraircraft environmental control tnrbomachinesCASHE PAPEB 77-EHAS-7] A77-46848

A comparison of ECS controls EnvironmentalControl Systems for F-4 air conditioning[ASHE PAPEB 77-EBAS-81 A77-46849

AIB COOLIIGCold air performance of a

12.766-centmeter-tip-diameter axial-flow cooledturbine. 2: Effect of air ejection on turbineperformance[BASA-TP-1018] F.77-30089

AIB FLO!Besearch on noise generated by ducted air-fuel

combustion systems[AD-A039957J B77-31169

AIB IITAKESAerodynamics of horizontally-opposed aircraft

engine installations[AIAA PAPBB 77-1249] A77-45508

AIB LAOBCHIBGTactical expendable drone system /TEDS/

A77-47337AIB HAVIGATIOH

Probing the airborne Omega environmentA77-44435

Aircraft navigation with the limited operationalphase of the RAVSTAB Global Positioning System

A77-44436Helicopter offshore operations oil and gas

exploration and productionA77-44437

A special-purpose pocket calculator for aviationand maritime navigation

A77-44571Outlook for utilization of the north Atlantic air

space in 1978A77-44572

The design of complex navigation systemsBnssian book

A77-46494Boyal Air Force assessment flights of Omega

Navigation systemA77-47813

Flight experience with OmegaA77-47814

An American Omega navigation evaluation programme- 1975-1977

A77-47815Instruments and method of air navigation

H77-30070Bavigation checkpointing using horizon correlation[AD-A039946] B77-30103

AIB POLLOTIOHCharacteristic time emissions correlations - The

T-63 helicopter gas turbine combnstorA77-44824

AIB PDBIFICATIOIA rotating higa pressure water condenser andseparator for aircraft environmental controlsystemC A S H E PAPEB 77-EHAS-10] A77-46851

AIB TBAFFIC COBTBOLThe profile descent ATC for aircraft descent

( A I A A PAPEB 77-1251] A77-44339Fuel conservation for high performance aircraft in

the terminal areaA77-44434

Validation of an airport simulation modelA77-45719

Stereographic projections in air traffic controlsystems

A77-46262Some mathematical aspects of air traffic systems

A77-47816Honte Carlo simulations of YOB/DUE holding

procedures. Basic ideas and applications[DLB-FB-77-08] B77-30105

Hicrowave holographic imaging of aircraft withspaceborne illuminating source

B77-30439Air traffic control experimentation and evaluation

with the BASA ATS-6 satellite. Volume 2:Demonstration of satellite-supportedcommunications and surveillance for oceanic airtraffic controlfFAA-BA-75-6U-VOL-2] H77-31121

AIB TBAHSPOBTATIOBIn Herculean flight Soviet aviation history

B77-30066Interactions of technology and society: Impacts

of improved airtransport. A study of airportsat the grass roots in rural communities[HASA-CB-2871] B77-31005

A-2

SUBJECT IBDEI AIBCBAFT DESIGS

British Airways: An analysis of efficiency andcost levels[PB-268060/1] H77-31113

AIBBOE1E BQOIFBBBTAn electro-optic airspeed sensor airborneoptical convolution velociaeter

A77-44783Aircraft equipment

H77-30069Definition of a data collection system for OS Ar»ytactical microwave landing system evaluation[AD-A041230] H77-31126

Developnent of lightweight transforners forairborne high power supplies[AD-A041515] H77-31162

AIBBOBHB/SPAC1BOBBE COBPDTBBSCentral integrated test systea /CITS/ - Check

three times for onboard testing of B-1aircraftCAIAA PAPEB 77-1260] &77-45513

Complementary roles for BPVs in support oftactical Banned aircraft

A77-47334Holtiple Drone Control development for BPV andelectronic warfare applications

A77-47345Advanced avionics for the Advanced Benotely

Piloted Vehicle /ABPV/A77-47350

AIBCBiPTSoviet aircraft and rockets[BASA-TT-F-770] H77-30065

Foundation of the uagnetic field integral equationcode for the calculation of the electronagneticpulse external interaction with aircraft[AD-A039953J B77-31389

AIBCBAFT ACCIDBIT IBV8STIGATIOBBriefs of accidents involving aerial applicationoperations, U.S. General Aviation 1975[PB-267654/2] H77-31114

Briefs of accidents involving amateur/home builtaircraft, OS general aviation, 1975[PB-267652/6] H77-31115

Briefs of accidents, involving corporate/executiveaircraft, OS general aviation, 1975[PB-267651/8] H77-31116

Briefs and accidents involving missing and missinglater recovered aircraft, OS general aviation,1975[PB-267650/0] H77-31117

Briefs of accidents involving alcohol as acause/factor, OS general aviation, 1975[PB-267649/2] H77-31118

Briefs of accidents involving rotorcraft OSgeneral aviation, 1975[PB-267647/6] H77-31120

Briefs of accidents involving turbine poweredaircraft, OS general aviation, 1975[PB-267646/8] B77-31121

Briefs of accidents involving midair collisions,OS general aviation. 1975[PB-267645/0] B77-31122

Listings of accidents/incidents by aircraft makeand model, OS civil aviation, 1975[PB-267644/3] B77-31123

AIBCBAFt ACCIDE1TSOS air carrier accidents involving fire, 1965

through 1974 and factors affecting the statistics[PB-266883/8] H77-31112

Briefs of fatal accidents involving weather as acause/factor, OS general aviation 1975,[PB-267648/4] 877-31119

ilBCBAFT BBAKBSAn alternate recovery system for the Aqmla

mini-BPV soft landingA77-147316

AIBCB1FT CABilBBSInvestigation of landing gear deck obstruction

effects by drop testingA77-46825

Summary of helicopter airframe testing in theshipboard environment[AD-A039748] H77-31W

AIBCBAFT COBBOBICATIOBSoftware implementation of a PB spread spectrum

receiver to accommodate dynamics SHFpseadonoise communication link foraircraft/satellites

A77-44738

Satellite communications for the mobile service[AAS 76-045] A77-46630

ASDAB (aircraft to satellite data relay) flighttest report[HASA-TB-73744] B77-31355

AIBCBAFT COBPABTBBHTSAircraft interior sandwich panel development

A77-47625AIBCBAFT COBFIGOBATIOHS

Parametric study of advanced long rangemilitary/commercial cargo transports[ A I A A PAPEB 77-1221] A77-44322

The remotely piloted helicopterA77-44443

Comparative flutter calculations for the Viggenaircraft

A77-44818»ectored-engina-over-wing configuration design

[AIAA PAPBB 77-1228] A77-45507The arrow wing - Its potentialities and drawbacks

with regard to in-flight aerodynamic researchA77-46606

F-8 obligue wing structural feasibility study[NASA-CB-154841] B77-30107

AIBCBAFT COBSTBDCZIOH BATZBIALSPowered lift - Its impact on YC-14 materials andstructures[AIAA PiPEfi 77-1231] A77-44327

Cast aluminum structures technology for TC-14airframes[AIAi PAPBB 77-1232] A77-44328

Advanced composites and advanced metallics meetthe challenge of design-to-cost[AIAA PAPEB 77-1234] A77-44329

Composite horizontal stabilizer for the B-1 -Design, fabrication and test

A77-46519Aircraft composite primary structures in Brazil

A77-46807Durability testing of the A-7D composite

outer-wing panelA77-46808

Accelerated environmental conditioning of the A-7Dcomposite outer wing

A77-I16838AIRCBAFT COBIBOL

Active control technology aircraft designA77-4552I!

The measurement of performance, stability andcontrol characteristics of a high subsonic jetaircraft in non-steady flight conditionsemploying high accuracy instrumentation techniques

A77-45525Flight control. I - The aircraft as controlled

system German bookA77-47675

Aircraft cyberneticsN77-30071

7orter-lift roll-control device[HASA-CASB-LAB-11868-2] H77-31176

Bandling guality criteria development fortransport aircraft with fly-by-wire primarycontrol systems[HLB-TB-74141-0] H77-31179

AIBCBAFT DBSIGBFlight test results for an advanced technology

light airplane[ A I A A PAPEB 77-1217] A77-44319

Characteristics of fighter aircraft[AIAA PAPBB 77-1219] A77-4U321

Parametric study of advanced long rangemilitary/commercial cargo transports[AIAA PAPEB 77-1221] A77-B1322

Bass flow requirements for LFC wing designLaminar Flow Control[AIAA PAPEB 77-1222] A77-4Q323

Advanced composites and advanced metallics meetthe challenge of design-to-cost[AIAA PAPBB 77-1234] A77-OU329

Application of powered lift and mechanical flapconcepts for civil short-haul transport aircraftdesign[AIAA PAPBB 77-1237] A77-H4330

Thrust augmenting ejector technology for Navyaircraft[AIAA PAPEB 77-1239] A77-44331

Case studies in aircraft design[ A I A A PAPBB 77-1244] A77-44335

A-3

AIBCBAFT EBGIHES SBEJECT IIDBX

Wing design by numerical optimization[AIAA PAPEB 77-1217] A77-14336

Effects of technology level on V/STOL aircraft[AHA PAPEB 77-1238] A77-45501

Prelimnary design and analysis of advancedmilitary transportsf&IAi PAPEB 77-1221] A77-45502

The timing of technology - Commercial transportaircraft[AIAA PAPEB 77-1200] A77-45503

Results of a feasibility study to add canards andADEN nozzle to the YF-17 AugmentedDeflecting Exhaust Nozzle[AIAA PAPEB 77-1227] A77-45506

Vectored-engine-over-wing configuration design[AIAA PAPEB 77-1228] 477-15507

Control of rare events by aircraft systen designregulation - Impact on operations[AIAA PAPEB 77-1258] A77-45511

YC-11 flight test results[AIAA PAPEB 77-J2591 A77-15512

Active control technology aircraft design477-45521

The computer for design and optimization withapplications to aircraft design, etc

A77-16136F-18 blends advanced fighter concepts

A77-16575A-7 titanium nose gear development

A77-16801Flutter-suppression studies on an activelycontrolled variable-geometry Hind-tunnel model

A77-16805The Mirage-2000

A77-16975O.S./F.B.G. advanced tactical BPV requirements as

analyzed by Boeing and DormerA77-17339

Selection of optimum BPV operational launch andrecovery techniques

A77-17310The insertion or elimination of fuselage sections

and the balancing of aircraftA77-17699

Computers and wind tunnels - Complementary aids toaircraft design

A77-47879Aircraft Soviet technology

U77-30067Study of design and analysis methods for transonic

flow[NASA-CB-152041] H77-30086

Decision-making and optimization in aircraft design[AD-A039464] H77-30111

Seakeeping characteristics of a preliminary designfor a sea loiter aircraft[AD-4010062] N77-30113

Innovative Aircraft Design Study (IADS) task 2,volume 1[AD-A041231] N77-31111

Have drag reduction for aircraft fuselage-wingconfigurations. Volume 2: Hannal for computerprograms[AD-A040998] H77-32013

AIBCBBFT EBGIHESHacroscopic study of time unsteady noise of anaircraft engine during static tests

477-11153The effect of boundary layer changes due to

transient heat transfer on the performance of anaxial-flow air compressor[SAE PAPEB 770281] A77-11565

Interactive graphics in aircraft gas turbineengine design

A77-15191Aerodynamics of horizontally-opposed aircraftengine installations[AIAA PAPEB 77-12191 A77-15508

ECU methods for aircraft engine manufactureelectrochemical machiningrSHE PAPSB HB76-70S] A77-45871

The aircraft gas turbine - Status and prospectsA77-16403

The airline viewpoint in gas turbine enginelow cost operations

A77-16U05Gas tnrbines in the BAF from a maintenance

engineering viewpointA77-16406

Honitonng for preventive maintenance in the smallfleet

A77-16111Says of increasing the resources /potential lives/

of gas turbine enginesA77-17172

Aircraft enginesH77-30068

Non-integrated gas turbine engine diagnosticstradeoff analysis[AD-A039191] H77-30125

NAPTC Facility modifications reguired for altitudetesting of current V/STOL engine[AD-A011608] N77-31184

Tapered roller bearing development for aircraftturbine engines[AD-A011317] B77-31507

AIBCBAFT EQtJIPUBHTThe use of probability analysis in aircraft

certification and its effects on maintenance andequipment maintenance[ A I A A PAPEB 77-1256] A77-B5509

Variable geometry air cycle machine foraircraft environmental control turbooachinesC A S H E PAPEB 77-EHAS-7] A77-16818

A rotating high pressure water condenser andseparator for aircraft environmental controlsystem[ASHE PAPEB 77-EHAS-10] A77-96851

Aircraft equipmentN77-30069

Aircraft gun icing evaluation[AD-A039831] N77-30110

Microwave holographic imaging of aircraft withspaceborne illuminating source

877-30439Safety (aviation material)

[AD-A041021] N77-31111Dltrasonic detection of fatigue damage in aircraft

components[AD-A010009] B77-31516

AIBCBAPT FUELSThe military utility of very large airplanes and

alternative fuelsA77-07271

AIBCBAPT BAZABDSAn integrated approach to the problem of aircraft

icing[AIAA PAPEB 77-1218] A77-44320

Statistical analysis of OS Navy major aircraftaccident rates, pilot and aircrafttime-dependent variables[AD-A040096] N77-30099

AIBCBAFT IISTBOBBJTSDesign criteria for aircraft warning, caution and

advisory alerting systems[ A I A A PAPEB 77-1210] A77-44332

Dnited's experience with computer generated visualsystems, April 1977 for aircraft cockpits

A77-41431The presentation of information in combat aircraft

A77-17817Aircraft equipment

H77-30069AIBCBAFT LABDIIG

The profile descent ATC for aircraft descent[AI4A PAPEB 77-1251] A77-4H339

Fuel conservation for high performance aircraft inthe terminal area

A77-44434Feasibility demonstration of the earth referenced

maneuvering flight path display[AIAA PAPEB 77-1111] A77-45171

The need of stick force stability forattitude-stabilized aircraft, part 1[HLB-TB-76125-0] H77-31180

AIBCBAFT BAIBTBSAICEThe use of probability analysis in aircraft

certification and its effects on maintenance andegnipment maintenance[ A I A A PAPBB 77-1256] A77-15509

Central integrated test system /CITS/ - Checkthree times for onboard testing of B-1aircraft[AIAA PAPEB 77-1260] A77-15513

Fuel conservation through airplane maintenance477-45925

SUBJECT IHDBI 1IBPOII PBOFILBS

Gas turbines ID the BAP from a maintenanceengineering viewpoint

A77-46406Bonitoring for preventive maintenance in the small

fleetA77-46411

Flying, Maintenance, and the sale of parts to thefield: Interactive models for AH-1 and CH-47systems[AD-A039193J 1177-30073

»IBCBAFT BAHDTEBSFeasibility demonstration of the earth referenced

maneuvering flight path display[AIAA PIPES 77-1114] !77-a5171

Complementary roles for BPVs in support oftactical canned aircraft

A77-47334Energy aanageient display for air combat maneuvering

[AD-A040198] H77-30109Investigation of flight dynamics daring roll

[IFD-8/76] H77-31177(IBCBAPT HODBLS

Experience gained in adjusting the mathematicalmodel of the VPS 614 short-haul aircraft by useof measured eigenfregnencies

A77-45391Listings of accidents/incidents by aircraft Bake

and model, OS civil aviation, 1975[PB-267644/3] H77-31123

Foundation of the magnetic field integral equationcode for the calculation of the electromagneticpulse external interaction vith aircraft[AD-A039953] H77-31389

AIBCBAFT IOISBOTS noise correlation for several nozzle/ving

geometries using a 5:1 slot nozzle with externaldeflectors Over The iing configurations

A77-4U461Sir transport noise reduction

A77-44550Problems in predicting aircraft noise exposure

A77-47561Calculation of side line noise levels during takeoff

[AD-A040624] H77-31170Selection of minimum day/night levels for noisemap

contour calculations aircraft noiseabatement in airport planning[AD-A040623] H77-31922

AIBCB1PT PBBFOBBASCEAnalysis/theory of controlled configured structures

t i l A A PJPEB 77-1212] A77-4«316Analysis methods and computer programs developed

for the JC-15 STOL flight test programt A I A A PAEEB 77-1215] A77-44317

Parametric study of advanced long rangemilitary/commercial cargo transports[ilAA PAPBB 77-1221] A77-44322

Effect of an integrated scramjet installation onthe subsonic performance of an aircraft designedto Bach 6 cruiset A I A A PAPEB 77-1230] A77-44326

yc-14 flight test results[AIAA PJPEB 77-1259] A77-45512

The measurement of performance, stability andcontrol characteristics of a high subsonic jetaircraft in non-steady flight conditionsemploying high accuracy instrumentation technigues

A77-U5525The development of primary equations for the use

of on-board accelerometers in determiningaircraft performance[AD-A0391741 H77-30112

Effects of control lavs and relaxed staticstability on vertical ride quality of flexibleaircraft

H77-3012SUnsteady Airloads in Separated and Transonic Flow

XAGABD-CP-226] B77-31073AIBCBAFT PILOIS

In Herculean flight Soviet aviation historyH77-30066

Statistical analysis of OS Davy major aircraftaccident rates, pilot and aircrafttime-dependent variables[AD-A040096] 177-30099

Briefs of accidents involving amateur/home builtaircraft, OS general aviation, 1975[PB-267652/6] B77-31115

Briefs of accidents involving alcohol as acause/factor, US general aviation, 1975CPB-267649/2] 1177-31118

AIBCBAFT PBODBCTIOHECH methods for aircraft engine manufacture

electrochemical machining[SHE PAPBB BB76-705] A77-45871

A r m y aviation manufacturing technology programguidance[AO-A040821] 877-30074

AIBCBAFI BE1UBILITIOperational reliability and reliability testing

BookA77-45173

The use of probability analysis in aircraftcertification and its effects on maintenance andequipment maintenanceC A I A A PAPBB 77-1256] A77-45509

Airworthiness and flight characteristicsevaluation C-12A aircraft[AD-A040239] B77-31136

AIBCBAFT SAFBZIControl of rare events by aircraft system design

regulation - Impact on operations[AIAA PAPBB 77-1258] A77-45511

AIBCBAFT STABILITY& new concept of static stability and its flight

testing in supersonic flight_ A77-44815

Experience gained in adjusting the mathematicalmodel of the VFB 614 short-haul aircraft by useof measured eigenfreguencies

A77-45391The measurement of performance, stability andcontrol characteristics of a high subsonic jetaircraft in non-steady flight conditionsemploying high accuracy instrumentation techniques

A77-45525Bicroconputer SPV stabilization and control system

A77-47348Prediction of transonic aircraft buffet response

N77-31076The need of stick force stability for

attitude-stabilized aircraft, part 1[BLB-TB-76125-0] H77-31180

AIBCBAFT STBOCTOBBSAnalysis/theory of controlled configured structures

[AIAA PAPBE 77-1212] A77-44316Powered lift - Its impact on IC-14 materials and

structures[AIAA PAPEB 77-1231] A77-44327

Cast aluminum structures technology for YC-14airframestAIAA PAPBB 77-1232] A77-44328

Process development for fabricating sculptureddecorative interior aircraft panels using sheetmolding compounds

A77-46508Fatigue problems in service - Aircraft structures

A77-47503Design and fabrication of graphite-epoxy bolted

wing skin splice specimens[HASA-CB-145216] N77-30180

Dynamic loading of airframe componentsH77-31080

A study of the charge and current induced on anaircraft in an EBP simulator facility. Part 1:The fornnlation. Part 2: The singularityexpansion method. Part 3: The numerical results[AD-A039507] H77-31384

AIBCBAFT SOB7IVABILITIBriefs and accidents involving missing and missing

later recovered aircraft, OS general aviation,1975[PB-267650/0] H77-31117

AIBCBAFT iAKBSAn investigation of the near-field wake behind a

full-scale test aircraftA77-44816

Estimates of the effectiveness of automaticcontrol in alleviating wake vortex induced rollexcursions[HASA-TB-73267] H77-30129

AIRFOIL PBOFILBSGeneralized Theodorsen solution for singular

integral equations of the airfoil classA77-44946

AIBFOILS SUBJECT IBDEX

Aerodynamic data and off-design characteristics ofthe modified gaasi-elliptical airfoil sectionNLB 7101[NLB-TR-76012-0] N77-30094

Comparative performance aeasurenents of tvohelicopter blade profiles in hovering flight[ARC-R/H-3792] H77-31143

AIBFOILSAnalysis of transonic flow over lifting andoscillating airfoils

A77-47542Study of design and analysis methods for transonic

flowCNASA-CB-152041] H77-30086

Comparison of dynamic stall phenomena for pitchingand vertical translation motions[NASA-CB-2793] N77-30088

Unsteady airloads on an oscillating supercriticalairfoil

N77-31085Efficient solution of unsteady transonic flows

about airfoilsN77-31087

Application of a finite difference method to theanalysis of transonic flow over oscillatingairfoils and wings

N77-31090Surface finishing of metal airfoils by

adhesive bonding[HASA-CASE-HSC-12631-2] H77-31131

Advanced cooled turbine airfoil aerodynamicinvestigationrAD-A041137] R77-31161

AIBP BABESExploratory of development of durability of

adhesive bonded joints[AD-A039864] H77-30249

Dynamic loading of airframe componentsN77-31080

Airframe response to separated flow on the shorthaul aircraft VFW 614

H77-31081Summary of helicopter airframe testing in the

shipboard environmentfAD-A039748] H77-311<t<l

A study of spectrum loading and range-paircounting method effects on cumulative fatiguedamageCAD-A039651] N77-31145

Ultrasonic detection of fatigue damage in aircraftcomponents[AD-A040009] H77-31516

SIBLIHE OPEBATIOHSAir New Zealand's methods of flying the DC-10

[AIAA PAPEB 77-1255] A77-44343Terminal area charting for area navigationoperations

A77-44433The airline viewpoint in gas turbine engine

low cost operations477-46105

An American Omega navigation evaluation programme- 1975-1977

A77-47815Some mathematical aspects of air traffic systems

A77-H7816British Airways: An analysis of efficiency andcost levels[PB-268060/1} N77-31113

AIBPOBT PLABNIHGValidation of an airport simulation aodel

A77-45719Selection of minimum day/night levels for noisemapcontour calculations aircraft noiseabatement in airport planning[AD-A040623] H77-31922

AIBPOBTSThe effect of terrain near airports on significant

low level wind shearC A I A A PAPEB 77-1242] A77-44334

Bunway utilization coefficients based on windvelocity and direction dependence only

A77-47950Interactions of technology and society: Impacts

of improved airtransport. A study of airportsat the grass roots in rural communities[NASA-CB-2871] H77-31005

AIHSBIPS1 tryont of a rigid airship under tropicalconditions

A77-15460AIBSFEED

Effects of forward velocity on noise for a 085turbojet engine with Bnltitube suppressor fromwind tunnel and flight tests

A77-44460An electro-optic airspeed sensor airborneoptical convolution velocimeter

A77-44783Leading-edge vortex effect on the flutter speed

A77-44819Development of prototype optical convolution

airspeed sensor[AD-A039469] H77-30116

ALTITUDE COHIBOLA new concept of static stability and its flight

testing in supersonic flightA77-44815

Altitude warning signal system evaluation[AD-A039365] H77-31147

ALTITUDE TESTSBAPTC Facility modifications required for altitude

testing of current V/STOL enginerAD-A041608] H77-31184

Laser velocimeter utilization in jet enginealtitude test cellsCAD-A041019] H77-31477

AtOHIMUBComposite tanks for aerospace vehicle application

A77-46516ALOHIHOH ALLOTS

Cast aluminum structures technology for IC-14airfraaes[ A I A A PAPER 77-1232] A77-44328

AHIHESQuantitative TLC analysis of amine antioxidants in

high-temperature jet engine lubricants[AD-A039909] N77-30124

1BBCHOIC CUHBEBSSimulation of flight-type engine fan noise in the

BASA-Lewis 9 x 15 anechoic wind tunnelA77-4U456

AISLE OF ATTACKNumerical solution of the conically symmetric

Havier-Stokes equations for hypersonic flow atangle of attack

N77-30079Numerical solution of complete flows aroundexternal stores[AD-A039213] H77-30122

Sensor for measuring instantaneous angle of attackof helicopter blades[NASA-CB-151808] N77-304UU

AHBULAH FLOIApplicability of axisymmetric analysis in

predicting supersonic flow through annularcascadesCASHE PAPEB 76-pfB-B] A77-<»434«

AHTIOIIDASTSQuantitative TLC analysis of amine antioxidants in

high-temperature jet engine lubricantsCAD-A039909] N77-30124

APPBOACHDevelopment of an integrated configuration

management/flight director system for pilotedSTOL approaches[NASA-CB-2883] H77-30132

AREA iAVIGATIOIBHAV waypoint charting effects on pilot

procedures, training and workloadA77-44432

Terminal area charting for area navigationoperations

A77-44433BHAV control for airborne surveys

A77-H626I1The presentation of information in combat aircraft

A77-47817A description of the software analysis from flight

and simulation data of the course cut limiter inthe TC7 b-737 area navigation computer[HASA-TH-74061] H77-31125

ARBBSTHG GBABABPV system/design trade study. Volume 4: Launch

and recovery[AD-A039591] B77-31146

A-6

SOBJECT IIDSX BOOHDABY LAYEB EQDATIOBS

ABBOI HISSThe arrow King - Its potentialities and drawbacks

with regard to in-flight aerodynamic researchA77-B6606

ASTiOBAVISATIOJInstruments and method of air navigation

H77-30070ASIHPTOTIC HEIBODS

On the validity of lifting line concepts in rotoranalysis

177-44444ATL»»TIC OC11I

Outlook for utilization of the Horth Atlantic airspace in 1978

A77-a<l572ATBOSPHBBIC CIBCOLATIOB

Hover evaluation of circulation control high speedrotor[AD-AOII0921 ] H77-31100

ATHOSPHBHIC BIFBCTSStatic electricity in aviation and ways of

averting its effectsA77-46349

ATHOSPHBBIC BLBCTBICITtStatic electricity in aviation and ways of

averting its effectsA77-46319

AHOSPBBBIC IDBBOLBHCBThe effect of terrain near airports on significant

low level «ind sheart&IAA PAPEB 77-1242] A77-44334

ATOBSThe calculation of flow fields about threedinensional bodies in high altitude(free-molecular floy of neatral atons)CDLB-FB-75-45] H77-30922

ATS 6Air traffic control experinentation and evaluation

kith the HASA ATS-6 satellite. Volume 2:Demonstration of satellite-supportedcommunications and surveillance for oceanic airtraffic control[PiA-HA-75-60-701-2] H77-31129

ATTACK AIBCBAFTGATOH/AV-8A environmental captive flight vibration

response testsCAD-A036498] H77-301114

AOTOH1TIC C01TBOLThe development and simulation of an automatic

gunnery systei for advanced fighter aircraftA77-47257

AOTOBATIC FLIGHT COHTBQLActive control technology aircraft design

A77-45524Aircraft cybernetics

H77-30071Estimates of the effectiveness of automaticcontrol in alleviating wake vortex induced rollexcursionstHASA-TB-73267] H77-30129

AOTOHATIC LAIDIHG COBTEOlCompliance with amended FAB 25.1309 - DC-10 casehistory Automatic landing SystemI A I A A PAPER 77-12573 A77-45510

AOTOHATIC PILOTSAircraft cybernetics

H77-30071AOTOHATIC TBST BQOIEHBHT

Central integrated test system /CITS/ - Checkthree times for onboard testing of B-1aircraftIAIAA PAPBB 77-1260] A77-45513

Bicrocompnter BP7 stabilization and control systemA77-47348

Advanced high speed roller bearing inspectiontechniques[AD-A042121] H77-31529

AOII1IABI BOWEB SOOBCBSEmergency-power benefits to multi-engine helicopters

A77-44515AVIOHICS

Operational reliability and reliability testingBook

A77-45173Synergistic grovth of ITCS to a tactical BPV C2system Integrated Target Control System

A77-47343

Advanced avionics for the Advanced BenotelyPiloted Vehicle /ABPV/

A77-47350Aircraft equipment

H77-30069A X I A L FLOI TOBBIIBS

Cold air performance of a12.766-ceutimeter-tip-diameter axial-flow cooledturbine. 2: Effect of air ejection on turbineperformance[HASA-TP-1018] N77-30089

multistage axial-flov turbomachinery vakeproduction, transport, and interaction[AD-A041108] H77-31173

AIISIBBETBIC FLOIApplicability of axisymmetric analysis in

predicting supersonic flow through annularcascades[ASHE PAPEB 76-PWB-B] A77-aa3»4

The theoretical determination of the base pressurein supersonic flow

A77-45388AZIBDTB

A simple closed-form solution of a position-fixingproblem[AD-A039303] H77-31127

BB-1 AIBCBAFT

Central integrated test system /CITS/ - Checkthree times for onboard testing of B-1aircraft[AIAA PAPEB 77-1260] A77-45513

Composite horizontal stabilizer for the B-1 -Design, fabrication and test

A77-46519B-52 AIBCBAFT

Effects of control laws and relaxed staticstability on vertical ride quality of flexibleaircraft

H77-30128BASE PBESSOBE

The theoretical determination of the base pressurein supersonic flow

A77-05388BBTEBAGES

Briefs of accidents involving alcohol as acause/factor, OS general aviation, 1975CPB-267649/2] H77-31118

BIBDSNumerical analyses of soft body impacts on rigid

and defornable targets[AD-A040030] H77-31168

BLOIT BODIESnumerical solution of complete flows around

external storesCAD-A039213] H77-30422

BODI-IIBG COIFIGDBATIOHSOTV noise correlation for several nozzle/wing

geometries using a 5:1 slot nozzle with externaldeflectors Over The Wing configurations

A77-1H461F-8 obligue wing structural feasibility study

[NASA-CB-150841] N77-30107A wind-tunnel investigation of the effects of flap

span and deflection angle, wing planform and abody on the high-lift performance of a 28 degswept wing[ABC-CP-1372] N77-31106

An improved free wing for an aircraft[HASA-CASE-FBC-10092-1 ] H77-31135

Rave drag reduction for aircraft fuselage-wingconfigurations. Volume 2: Manual for computerprograms[AD-A040998] H77-32013

BOEIIG 717 AIBCBLPTProcess development for fabricating sculptured

decorative interior aircraft panels using sheetmolding compounds

A77-46508BODIDABI LATEB EQOATIOIS

Characteristics of the boundary-layer equations ofthe minimum time-to-cliob problem

A77-Q6618

A-7

BOOHDABT LAYBB FLOi SBBJECT IHDEI

BOOHDABY LATEB PLOBThe effect of boundary layer changes due to

transient heat transfer on the performance of anaxial-flow air compressorfSAE PAEEB 77028*4] A77-44565

BODHDABY LAYEB TBABSITIOBAn evaluation of boundary layer forces and•easareient methods[AD-A090947] H77-31218

BOOHDABT LAIEFSOpstream influence on the near field of a planetnrbalent jet

A77-47005BOOSDABI TILDE PBOB1EBS

Generalized Theodorsen solution for singularintegral equations of the airfoil class

A77-44946Application of finite element approach to

transonic flov problemsA77-47539

numerical solution of complete flovs aroundexternal stores[AD-A039213] N77-30422

BBAKIBG

An extended prediction model for airplane brakingdistance and a specification for a total brakingprediction systems, volume 2[AD-A039S67J H77-30176

B0FFBTIHGPrediction of transonic aircraft buffet response

H77-31076Beasnrements of buffeting on two 65 deg deltamngs of different materials

H77-31079

C-15 AIBCBAFTAnalysis methods and computer programs developed

for the YC-15 STOL flight test program[AIAA PAEEB 77-1215] A77-44317

CABIH ATHOSPBEBESA comparison of ECS controls EnvironmentalControl Systems for ?-4 air conditioningCASHE PAEEB 77-EUAS-8] A77-46849

CALCOLATOBSA special-purpose pocket calculator for aviation

and maritime navigationA77-44571

CAHBEBED ilBGSIterative calculation of flov past a thickcambered vino, near the groundtABC-CP-1370] N77-31104

Iterative design techniques for thick camberedwings in snbcritical flov[ABC-CE-1371] H77-31105

CilABD COBFIGOBATIOHSComparative flutter calculations for the Viggen

aircraftA77-44818

Besults of a feasibility study to add canards andADEH nozzle to the YF-17 AugmentedDeflecting Exhaust Hozzle[AIAA PAPEB 77-1227) A77-45506

CAPTIVE TESTSFlight control testing of the VAK-191B aircraft[AD-A040535] 877-31137

CABBOI HOHOXID8The effect of ambient conditions on carbon

monoxide emissions froa an idling gas turbinecombastor[NASA-CB-154986] H77-31148

CABGO AIBCBAFTParametric study of advanced long range

military/commercial cargo transportsCAIAA PAFEB 77-1221] A77-44322

An evaluation of very large airplanes andalternative fuels[AD-A040532] H77-31334

CASCADE FLOWApplicability of axisymmetric analysis in

predicting supersonic flow through annularcascades[ASBE PAFEB 76-PWH-B] A77-44344

CASES (COHTAISBBS)Stall margin improvement by casing treatment - Its

mechanism and effectiveness in axial flovcompressors[ASHE EAEEB 76-GT-A] A77-Q4345

CAST ALLOTSCast aluminum structures technology for TC-11

airframes[AIAA PAPEB 77-1232] A77-<I<I328

CATALTSISDevelopment of a catalytic conbnstor for aircraft

gas turbine engines[AD-A040135] H77-31171

CEBTIFICATIOHThe use of probability analysis in aircraftcertification and its effects on maintenance andequipment maintenance[AIAA PAEBB 77-1256] A77-45509

CH-47 HELICOPTBBFlying, maintenance, and the sale of parts to the

field: Interactive models for AH-1 and CH-47systems[AD-A039193 ] H77-30073

CH-47 medium lift helicopter effectivenessevaluation program run book[AD-A041H62] H77-31142

CHROBATOGBAEBIQuantitative TLC analysis of amine antioxidants in

high-temperature jet engine lubricants[AD-A039909] H77-30124

CIVIL AVIATIOITerminal area charting for area navigation

operationsA77-44433

Monitoring for preventive gaintenance in the smallfleet

A77-46<H1Flight experience vith Omega

A77-47814Briefs of accidents involving aerial application

operations, U.S. General Aviation 1975[PB-267654/2] H77-31114

CLIHBIiG FLIGHTCharacteristics of the boundary-layer equations of

the minimum time-to-climb problemA77-46618

CLODD HEIGHT IHOICATOHSVisual range: Concepts, instrumental

determination, and aviation applications[HBS-HOHO-159] H77-30102

COCKPITSDesign criteria for aircraft naming, caution and

advisory alerting systemsC A I A A PAEEB 77-1240] A77-44332

CODBBSDigital shaft encoder

[AD-A040706] H77-31172COBBAT

Energy management display for air combat maneuvering[AD-A040198] H77-30109

COBBOSTIOB CHABBBBSBesearch on noise generated by ducted air-fuel

combustion systemsCAD-A039957] H77-31169

Development of a catalytic combustor for aircraftgas turbine engines[AD-A040135] H77-31171

COBBABD AID COITBOLDevelopment of an integrated configuration

management/flight director system for pilotedSTOL approaches[BASA-CB-2883] B77-30132

COBBEBCIAL AIBCBAFT

Head-up display in commercial aviation[AIAA PAPEB 77-1241] A77-44333

Bole of future automated flight deck displays inimproving operating costs[AIAA PAPBB 77-1252] A77-44340

The timing of technology - Commercial transportaircraft[AIAA PAPEB 77-1200] A77-45503

Innovative Aircraft Design Study (IADS) task 2,volume 1[AD-A041234] H77-31141

COBBOHICATIOBAH/EBC-56 helmet radio set upgrading. Becommended

modifications require minimal resources batpromise considerable improvement in reliabilityoperability, and logistics support[AD-A041190] H77-31368

A-8

SWJBCJ COITBOL SIBOIATIOH

COBBOIICATJOI SATBILITESSoftware implementation of a PR spread spectrumreceiver to accommodate dynamics SBFpseadonoi.se coaannication link foraircraft/satellites

A77-44738Satellite coBiunications for the aobile service

[A1S 76-015] A77-46630COBPIBX SISTBBS

The design of coaplez navigation systeasBassian book

A77-46494Singular perturbation analysis approach forsystems with highly coopled dynamics vithapplication to optiaal aircraft flight control

A77-46617Fatigue life prediction of complex structures[iSHE PAPBB 77-DE-46] A77-46915

COHPOSIIE BATBBliLSComposite horizontal stabilizer for the B-1 -

Design, fabrication and testA77-46519

Composite hnbs for low cost turbine enginesstress analysis using 8ASTRSB

A77-46520Dnrability testing of the A-7D conposite

outer-wing panelA77-46808

COBPOSITE STBDCtUBESAdvanced coaposites and advanced aetallics Beet

the challenge of design-to-cost[AIAA PAPEB 77-12311] A77-44329

Aircraft composite primary structures in BrazilA77-46807

COBPBBSSIBIB FLO!Transonic flow simulation by the finite element

method via optimal controlA77-47544

COBPBBSSOB B1ADBSAn optical technique for Beasnring vibratory

Botion in rotating aachineryA77-47090

COBPBBSSOB BFFICIEICIStall margin improvement by casing treatment - Its

mechanism and effectiveness in axial flowcompressors[ASBE PAPEB 76-GT-A] A77-44345

COHPOTEB GRAPHICSInteractive graphics in aircraft gas turbine

engine designA77-45«91

An evaluation of a raster scan display for use inan aircraft infornation handling system[AD-A039652] H77-30117

COBPOIEB P806BABSAnalysis methods and computer programs developed

for the YC-15 STO1 flight test programCAIAA PIPES 77-1215] A77-44317

A special-purpose pocket calculator for aviationand nantiae navigation

A77-44571Software implementation of a PH spread spectrnareceiver to accomnodate dynamcs SBFpseadonoise commnnication link foraircraft/satellites

A77-44738StceaBtabe analysis of a hydrogen-burning scranjetexhaust and simulation technigne

A77-44817Interactive LOBAH-C to geographic and

geogtaphic-to-LOBAB-C computationCHASA-CB-153985) H77-30101

Simulation of inertial inpnts to a strapdownplatform for inertial great circle trajectories[SAHD-76-0620] B77-30104

numerical solution of complete flows aroundexternal storesCAD-A039213] B77-30122

CH-47 aediam lift helicopter effectivenessevaluation program ran book[AD-A.041462] H77-31142

A study of spectrum loading and range-paircounting method effects on cumulative fatiguedamage[AD-A039651] B77-31145

COBPOTBB lECHBIfiOESUnited1s experience with coaputer generated visualsystems. April 1977 for aircraft cockpits

A77-44431

BBAV control for airborne surveysA77-06261I

Computational methods to obtain time optimal jetengine control

A77-46614COBCOTBBIZBD OBSI6B

Sing design by numerical optimization[AIAA PAPEB 77-1207] A77-44336

Interactive graphics in aircraft gas turbineengine design

A77-45491The computer for design and optimization withapplications to aircraft design, etc

A77-46136Composite hubs for low cost turbine enginesstress analysis using BASTBAH

A77-Q6520Computers and wind tunnels - Complementary aids to

aircraft designA77-47879

Iterative design technignes for thick camberedwings in subcritical flow[ABC-CP-1371] R77-31105

Single-rotor helicopter design and perforaanceestimation programs. Volume 1: Methodology[AD-A040803] N77-31138

Innovative Aircraft Design Study (IADS) task 2,volume 1[AD-iOU123«] H77-311U1

Development of lightweight transformers forairborne high power supplies[AD-A041515] N77-31162

lave drag reduction for aircraft fuselage-wingconfigurations. Volume 1: Analyses and resultstiD-AO!»0997] S77-32012

COBPOTEBIZED SZBDLATIOHValidation of an airport simulation model

A77-«5719Flying, aainteuance, and the sale of parts to the

field: Interactive models for AH-1 and CH-U7systems[AD-A039193] H77-30073

Development and verification of real-time, hybridcomputer simulation of F100-PH-100(3) tnrbofanengine[HASA-TP-1034] H77-31154

COHFEBE1CESSas turbines - Status and prospects; Proceedings

of the Symposium, London, England, February 4,5, 1976

A77-46H01The BPV - Complement to manned systems;

Proceedings of the Fourth Annual Symposium,Washington, D.C., June 5-9, 1977

A77-47333Fatigue 1977; Proceedings of the Conference,

Cambridge Oniversity, Cambridge, England, Harch28-30, 1977

A77-47501Unsteady Airloads in Separated and Transonic Flow

[AGABD-CP-226] B77-31073COHFIGOBATIOB BAIAGBHBBT

Development of an integrated configurationmanagement/flight director system for pilotedSTOL approaches[HASA-CB-2883] H77-30132

COBTCAL BODIBSnumerical solution of the conically symmetric

Navier-Stokes eguations for hypersonic flow atangle of attack

H77-30079COHTAIBBKBT

Botor burst protection program: Experimentationto provide guidelines for the design of turbinerotor burst fragment containment ringsCHASi-CB-135166] H77-30119

COMIB01 COIFISBBBD TBHIC1ESActive control technology aircraft design

A77-45524COBIBOL SIBOL&TIOi

Validation of an airport simulation modelA77-45719

The development and simulation of an automaticgunnery system for advanced fighter aircraft

A77-47257

A-9

COHTEOL STABILITY SOEJECT IBDEX

COHTEOL STABILITYEffects of control laws and relaxed static

stability on vertical ride quality of flexibleaircraft

B77-30128COBTBOL SOBFACES

Rind tunnel expennents on an actively controlled,variable geometry flatter model[AD-A039216] H77-3013H

vortex-lift roll-control device[ HASA-CASE-LAB-11868-2] N77-31176

COBTBOLLABILITIHandling quality criteria development for

transport aircraft with fly-by-wire primarycontrol systems[BLB-TB-74141-U] B77-31179

The need of stick force stability forattitude-stabilized aircraft, part 1rHLR-TB-76125-0] B77-31180

COBVBCTIVE BBAI TBAHSFBBAdvanced cooled turbine airfoil aerodynanic

investigation[AD-A011137] B77-31161

COOLIHGAdvanced cooled turbine airfoil aerodynamicinvestigation[AD-A041137] B77-31161

COOBDIBiTE TflABSPOBHATIOISStereographic projections in air traffic control

systemsA77-46262

COBBELATIOI COBFJICIBBTSnavigation checkpointing asing horizon correlation[AD-A039946] B77-30103

COSBOHADTSIn Herculean flight Soviet aviation history

N77-30066COSI ABA1YSIS

Design-to-cost in action[ASBE PAEEE 77-DE-9] A77-46904

Selection of optimum BPV operational launch andrecovery techniques

A77-1I7340British Airways: An analysis of efficiency and

cost levelstPB-268060/1] H77-31113

Sensitivity of Army helicopter operating andsupport costs to changes in design and logisticparameters[AD-A040353] H77-31139

COST BFFECTIVEBBSSThe airline viewpoint in gas turbine engine

low cost operationsA77-46405

D.S./F.R.G. advanced tactical RPV requirements asanalyzed by Boeing and Dormer

A77-47339The mini-BPV, cost effectiveness in a tactical

environmentA77-47342

Synergistic growth of ITCS to a tactical RPT C2system Integrated Target Control System

A77-II7343COST BEDDCTIOH

Bole of future automated flight deck displays inimproving operating costs[AIAA PAPEB 77-1252] A77-44340

Composite horizontal stabilizer for the B-1 -Design, fabrication and test

A77-46519Complementary roles for BPVs in support oftactical manned aircraft

A77-47334CRACK IBIIUTIOB

Fatigue life prediction of complex structuresCASHE PAPEB 77-DE-46] A77-46915

CBASB IBJDBIESBriefs of accidents involving amateur/home built

aircraft, OS general aviation, 1975[PB-267652/6] H77-31115

Briefs of fatal accidents involving weather as acause/factor, US general aviation 1975,[PB-2676H8/U] B77-31119

CBASBBSBriefs of accidents involving aerial application

operations, U.S. General Aviation 1975[PB-267654/2] B77-31114

CBITBBIAHandling quality criteria development for

transport aircraft with fly-by-wire primarycontrol systems[BLB-TB-74141-U] B77-31179

CBOSS COOPLIBSSingular perturbation analysis approach for

systems with highly coupled dynamics withapplication to optimal aircraft flight control

A77-46617CBDISE RISSILBS

BPT applications of Tomahawk cruise missileA77-47336

COSHIOISDesign and evaluation methods for optimizing

ejection seat cushions for comfort and safety[AD-A036035] H77-31110

CTBEEHETICSAircraft cybernetics

H77-30071CILIHDBICAL BODIES

Rearrangement of vortex structures in the wakebehind a body and in a jet

A77-47674

DATA ACQUISITIONA digital data acquisition and reduction system

for flight testing general aviation aircraftCAIAA PAPEB 77-1216] A77-44318

Definition of a data collection system for DS Armytactical microwave landing system evaluation[AD-A041230] N77-31126

DATA PBOCESSIHGSpace experiment simulation using an aircraft

laboratoryA77-47200

DATA BBDBCTIOHA digital data acquisition and reduction system

for flight testing general aviation aircraft[AIAA PAPEB 77-1216] A77-U4318

DATA STOBAGBIntroductory investigation of the Bange Reasnring

system/data collection system (BHS-2/DCS)[AD-A039921] S77-30106

DATA TBABSHISSIODIntroductory investigation of the Bange Heasnringsystem/data collection system (BHS-2/DCS)[AD-A039921] B77-30106

DC 10 AIBCBAFTAir New Zealand's methods of flying the DC-10

[AIAA PAPEB 77-1255] A77-HH3H3Compliance with amended FAB 25.1309 - DC-10 casehistory Automatic Landing System[AIAA PAPEB 77-1257] A77-U5510

DECELEBATIOBAn alternate recovery system for the Aquila

mini-BPV soft landingA77-17346

DECISIOS BAKIIGDecision-making and optimization in aircraft design[AD-A039464] N77-30111

DECOYSTactical expendable drone system /TEDS/

A77-47337DBHOaiDIFICATIOB

A rotating high pressure water condenser andseparator for aircraft environmental controlsystem[ASBE PAPEB 77-EBAS-10] A77-46851

DELTA BIHGSThe Rirage-2000

A77-46975Measurements of buffeting on two 65 deg delta

wings of different materialsH77-31079

DBPLOIBEBTThe mini-BPV, cost effectiveness in a tactical

environmentA77-47342

DESCBBTA laboratory investigation into flight path

perturbations during steep descents of T/STOLaircraft[AD-A040101] B77-30135

DESIGBSoviet aircraft and rockets

[BASA-TT-F-770] S77-30065

A-10

SUBJECT IIDEX DIBASIC TESTS

DESIGI ABALTSISCase studies ID aircraft design

CAIAA PAPBB 77-1244] A77-44335Advanced Technology Sing /ATI/ selection and design[ilAA PAPEB 77-12103 A77-45505

The design of complex navigation systemsBnssian book

A77-46494D.S./F.B.G. advanced tactical BPV requirements as

analyzed by Boeing and DornierA77-47339

Stody of design and analysis methods for transonicflo*[HASA-CB-152041] H77-30086

Botor burst protection program Experimentationto provide guidelines for the design of turbinerotor borst fragment containment rings[RASA-CB-135166] H77-30119

Propeller stndy. Part 1: Introduction and overview[HASA-CB-155002] B77-31156

Propeller stndy. Part 2: The design ofpropellers for minimum noise[BASA-CB-1550053 B77-31157

DIA6IOSISBon-integrated gas turbine engine diagnosticstradeoff analysis[AD-A0394943 H77-30125

DIFFBACTIOIAccuracy of the Kirchoff formula in deterniningacoustic shielding vith the nse of a flat plate[BASA-TH-73261] B77-30906

DIFFBSI01 SELDIBGAdvanced composites and advanced metallics meet

the challenge of design-to-cost[AIAA PAPEB 77-123*3 A77-44329

DIGITAL 1AVI6ATIOBA digital goniometer for VOB

A77-I16263BHAT control for airborne surveys

A77-46264The design of complex navigation systens

Bnssian bookA77-46494

Aircraft cybernetics1177-30071

DIGITAL SIBOLATIOBHumerical modeling of helicopter piloting

A77-46348DIGITAL StSTBHS

A digital data acquisition and reduction systemfor flight testing general aviation aircrafttilAA PAPEB 77-12163 A77-44318

A stndy of standardization methods for digitalguidance and control systens[AGA8D-AB-903 H77-30136

Digital shaft encoder[AD-A0407063 H77-31172

DIGITAL TSAISCOCBBSDigital shaft encoder[AD-A0407063 H77-31172

DISFLAT DRVICESDesign criteria for aircraft warning, caution and

advisory alerting systems[AIA4 PAFBB 77-1240] A77-44332

Bole of: future automated flight deck displays inimproving operating costs[AIAt PAPEB 77-12523 A77-44340

Onited's experience with computer generated visualsystems, April 1977 for aircraft cockpits

A77-4Q431Scanned laser visual system for militaryflight simulation

A77-44814Feasibility demonstration of the, earth referenced

maneuvering flight path displayC A I A t PAPBB 77-111*3 A77-45171

Bemote rate control for BPTsA77-47352

Energy management display for air combat maneuver ing[AD-A0401983 H77-30109

An evaluation of a raster scan display for use inan aircraft information handling system[AD-A039652] H77-30117

Raster monitor display applications study for theA-7BCAD-40398823 H77-30118

DISfAICE HEASOBIBG BQOTPHEHTPosition finding using distance measurements

in hyperbolic navigationA77-44570

Bonte Carlo simulations of VOB/DBE holdingprocedures. Basic ideas and applications[DLB-FB-77-083 H77-30105

DIOBBAL TABIAIIOISSelection of minimum day/night levels for noisemap

contour calculations aircraft noiseabatement in airport planning[AD-A040623] B77-31922

DBAG EEDOCTIOSHass flov requirements for LFC ving design

Laminar Flow Control[ A I A A PAPEB 77-12223 A77-44323

Effect of an integrated scranjet installation onthe subsonic performance of an aircraft designedto Bach 6 cruise[AIAA PAPBB 77-12303 A77-44326

Fuel conservation through airplane maintenanceA77-45925

Experimental investigation concerning thereduction of wave drag of pointed symmetricalwings of equal volume with subsonic leading edgeand bell-shaped planform for different thicknessdistributions in the spanwise and chordwisedirections[DLB-FB-75-623 F77-30087

iave drag reduction for aircraft fuselage-wingconfigurations. Volume 2: Hanual for computerprograms[AD-A040998] H77-32013

DBOBB VEHICLESTactical expendable drone system /TEDS/

A77-47337Haltiple Drone control development for BPV and

electronic warfare applicationsA77-47345

DBOP TESTSInvestigation of landing gear deck obstruction

effects by drop testingA77-46825

DUCTED FAHSDucted-fan TTOL BPV system

A77-47353DUCTED FLOI

Besearch on noise generated by ducted air-fuelcombustion systems[AD-A0399573 B77-31169

DIBABIC LOADSDynamic loading of airframe components

N77-31080DIBABIC HODBLS

Prediction of transonic aircraft buffet responseS77-31076

DIM IIC PBOGBASBIBGComputational methods to obtain time optimal jet

engine controlA77-146614

DYIAHIC BBSPOISEExperiment and analysis on the flow process

dynamics of the HASA-Langley eight foottransonic pressure tunnel[BASA-CB-1518063 H77-30085

An extended prediction model for airplane brakingdistance and a specification for a total brakingprediction systems, volume 2[AD-A0399673 H77-30176

The dynamic response of wings in torsion at highsubsonic speeds

B77-31077Airframe response to separated flow on the short

haul aircraft VFB 614B77-31081

Tail response to propeller flow on a transportairplane

B77-31082DIBABIC TESTS

Propeller stndy. Part 1: Introduction and overview[BASA-CB-1550023 B77-31156

Propeller study. Part 3: Experimentaldetermination of thrust and torgne on the TO-3AaircraftCRASA-CB-155003] H77-31158

A-11

BABTB BESOOBCBS SOBVBI AIBCBAFT SUBJECT IBDBX

BABTB BESOOECES SDBVEI AIRCRAFTAircraft laboratories and experience in using them

for the development of methods ana Deans ofremote sensing of earth resources

A77-47199ECOBOHIC AIAIISIS

The timing of technology - Commercial transportaircraftfAIAA PAPBB 77-12001 A77-4550J

EFFECTIVE FEBCBIVED BOISE LEVELSProblems in predicting aircraft noise exposure

A77-47561EFFICIEHC!

British Airways: An analysis of efficiency andcost levelsrPB-268060/1] U77-31113

EJBCTIOB SEATSFormat practices for documenting time critical,

harzardons proceduresfAD-A036369] H77-30100

Design and evaluation methods for optimizingelection seat cushions for comfort and safety[AD-A036035] N77-31110

BJECTOBSThrust angienting ejector technology for Navy

aircraftTAIAA PAPEB 77-1239] A77-44331

ELASTIC BEHD1HGComparative flatter calculations for the Viggen

aircraftA77-44818

ELECTBIC POiEB SOFFLIESDevelopment of lightweight transformers forairborne high power suppliesrAD-AO<H5l5] N77-31162

BLECTBO-OETICiL EFFECTAn electro-optic airspeed sensor airborneoptical convolution velocimeter

A77-44783ELECIBO-OETICS

General principles of automatic TV trackersfor fire control and missile tracking

A77-44812BLBCTBOCBBBICAL BACBIBIBG

ECB methods for aircraft engine manufactureelectrochemical machining[SHE EAPEB BB76-7051 A77-45871

ELECTBOBAGHEIIC FDLSESVLF pulse timing - Limitations and potential as a

companion to OmegaA77-44439

A study of the charge and current induced on anaircraft in an EUP simulator facility. Part 1:The formulation. Part 2: The singularityexpansion method. Part 3: The numerical resultsTAD-A0395071 N77-31384

Foundation of the magnetic field integral egnationcode for the calculation of the electromagneticpulse external interaction with aircraft[AD-A0399S31 H77-31389

ELBCTBOJIC COITBOtSynergistic growth of ITCS to a tactical BPV C2system Integrated Target Control System

A77-47343Multiple Drone Control development for BPV and

electronic warfare applicationsA77-47345

An evaluation of future BPV automatic navigationsystems

A77-47349Advanced avionics for the Advanced BemotelyPiloted Vehicle /ABPV/

A77-47350ELECTBOBIC BOODLES

Ku-band integrated circuit receiver front endmodule for BPV

A77-473SUELECTROSTATIC CBABGE

Static electricity in aviation and ways ofaverting its effects

A77-46349ELEV01S

Beat-transfer and pressure measnreaents on asimulated eleven deflected 30 deg near flightconditions at Bach 7ftlASA-TB-X-3563] H77-31440

EBEBGT COMSBBVATIOHFuel conservation for high performance aircraft in

the terminal areaA77-44434

Fuel conservation through airplane maintenanceA77-45925

The potential role of technological modificationsand alternative fuels in alleviating Air Forceenergy problemsTAD-A039597] H77-30261

EBEBGI POLICYThe potential role of technological modifications

and alternative fuels in alleviating Air Forceenergy problems[AD-A039597] S77-30261

EBGIBB COBTBOLEngine control stabilizing compensation-testing

and optimizationA77-44514

Computational methods to obtain time optimal jetengine control

A77-46614EBGIBB COOLABTS

Aerodynamics of horizontally-opposed aircraftengine installationsC A I A A PAPBB 77-1249] J77-45508

EHGIBB DBSIGBInteractive graphics in aircraft gas turbine

engine designA77-45091

Gas turbines - Status and prospects; Proceedingsof the Symposium, London, England, February 4,5, 1976

A77-46401The aircraft gas turbine - Status and prospects

A77-46403Gas turbine power for large hovercraft

A77-46412Development of an ultra-low-cost gas turbine

for BPV applicationsA77-47344

Development of a small, low cost turbojet enginewith thrust augmentation for BPV

A77-47347Bays of increasing the resources /potential lives/

of gas turbine enginesA77-47472

Aircraft enginesH77-30068

EHGIBB FAILUREBays of increasing the resources /potential lives/of gas turbine engines'

A77-47472BHGIBE BOISB

Hacroscopic study of time unsteady noise of anaircraft engine during static tests

A77-44453Simulation of flight-type engine fan noise in the

NASA-Lewis 9 x 15 anechoic wind tunnelA77-44456

Core noise source diagnostics on a tnrbofan engineusing correlation and coherence technigues

A77-44457Effects of forward velocity on noise for a J85

turbojet engine with mnltitnbe suppressor fro*wind tunnel and flight tests

A77-44460Flight effects on exhaust noise for turbojet and

tnrbofan engines - Comparison of experimentaldata with prediction

A77-44462EBGIBE TBSTIBS LABORATORIES

HAPTC Facility modifications required for altitudetesting of current V/STOL engineCAD-A041608] H77-31184

EBGIBB TESTSMacroscopic study of time unsteady noise of an

aircraft engine during static testsS77-44453

Engine control stabilizing compensation-testingand optimization

A77-44514Development of an ultra-low-cost gas turbine

for BPV applicationsS77-47344

A-12

SUBJECT IIOBI FIHITB BLBBBIT HETHOD

EIVIB01BBIT ERECTSThe effect of ambient conditions on carbon

monoxide emissions from an idling gas turbinecombnstor[HASA-CB-154986] B77-31148

EIVIB01HER BODBLSThe mini-BPV, cost effectiveness in a tactical

environmentA77-47342

EITIBOlBBlTiL COITBOLVariable geometry air cycle machine foraircraft environmental control tnrbomachines[ASBE PIPES 77-BBAS-7] A77-46848

A comparison of ECS controls EnvironmentalControl Systems for F-4 air conditioning[ASBE PAPBB 77-EHAS-8) A77-46849

BITIBOIBE1TAI. IBSTSAccelerated environmental conditioning of the A-7Dcomposite outer wing

477-116838EQOATIOHS OF BOTIOS

Simalation of inertia! inputs to a strapdownplatform for inertial great circle trajectories[SAHD-76-0620J B77-30104

The development of primary equations for the useof OD-board accelerometers in determiningaircraft performance[AD-A039174] 1177-30112

BBBOB COBBBCTHG DEVICESBemote rate control for BPVs

A77-47352BSTXBATIHG

An extended Kalman filter for estimatingaerodynamic coefficients[AD-A040594] H77-30092

EZBADST flat SIBOLATIOBFlight effects on ezhaast noise for turbojet andturbofan engines - Comparison of experimentaldata Kith prediction

A77-44462Streamtnbe analysis of a hydrogen-burning scranjetexhanst and simulation technique

A77-44817EXHAUST GASES

Characteristic time emissions correlations - TheT-63 helicopter gas turbine combastor

A77-44824The effect of ambient conditions on carbonmonoxide emissions from an idling gas turbinecombnstorCHASA-CB-1549861 N77-31148

EZTEBIAL STOBBSnumerical solntion of complete flovs aroundexternal stores[AD-A039213] H77-30422

BXTBBBALLT BLOII FLAPSOTB noise correlation for several nozzle/wing

geometries using a 5:1 slot nozzle with externaldeflectors Over The ling configurations

A77-44461

P-4 AIBCBAFTA comparison of ECS controls EnvironmentalControl systems for F-4 air conditioningUS BE PAPEB 77-BBAS-8) A77-46849

F-8 AIBCBAFTLinear regulator design for stochastic systems by

a multiple time scales method vithapplication to F-8 aircraft longitudinal control

A77-46621F-8 oblique ving structural feasibility study[HASA-CB-154841] B77-30107

F-18 AIBCBAFIF-18 blends advanced fighter concepts

A77-46575F-111 AIBCBAFT

ASD advanced program research inlet data analysisreport for 1/5.2-scale model inlet testsIAD-A040707J H77-31108

FATIGUE (BATEBIALS)A study of spectrum loading and range-paircounting method effects on cumulative fatiguedamagefAD-A039651] B77-31145

FATI60E LITEFatigue life prediction of complex structures

CASHB PAPBB 77-DB-46] A77-46915

Fatigue 1977; Proceedings of the Conference,Cambridge University, Cambridge, England, Barch28-30, 1977

A77-47501Fatigue probleas in service - Aircraft structures

A77-47503FATI60B TESTS

Ultrasonic detection of fatigue damage in aircraftcomponents[AD-A040009] H77-31516

FEASIBILITY AIALISISFeasibility demonstration of the earth referenced

maneuvering flight path display[ A I A A PAPEB 77-1114] A77-45171

Besnlts of a feasibility study to add canards andADEH nozzle to the IF-17 AugmentedDeflecting Exhaust Hozzle[ A I A A PAPEB 77-1227) A77-45506

F-8 obliqae ving structural feasibility study[BASA-CH-154841] H77-30107

FI6BTBB AIBCBAFTCharacteristics of fighter aircraft

C & I A A PAPBB 77-1219] " A77-44321Honaxisyametric nozzle technology program - An

overview for fighter aircraft engines[ A I A A PAPBB 77-1225] A77-4M325

Effects of technology level on 7/STOL aircraftC A I A A PAPBB 77-1238] A77-H5501

Besnlts of a feasibility study to add canards andADE8 nozzle to the TF-17 AugmentedDeflecting Exhaust Nozzle[ A I A A PAPEB 77-1227] A77-45506

Tectored-engine-over-wing configuration designC A I A A PAPEB 77-1228] A77-45507

The Birage-2000A77-46975

The development and simulation of an automaticgunnery system for advanced fighter aircraft

A77-U7257The BPV - Complement to manned systems;Proceedings of the Fourth Annual Symposium,Washington, D.C., June 5-9, 1977

A77-47333The mni-BPV, cost effectiveness in a tactical

EnvironmentA77-47342

The presentation of information in combat aircraftA77-47817

Energy management display for air combat maneuvering[AD-A040198] B77-30109

Flutter calculation for the viggen aircraft withallowance for leading edge vortex effect

H77-31083Subsonic and supersonic longitudinal stability and

control characteristics of an aft-tail fighterconfiguration vitb cambered and uncambered vingsand cambered fuselage[HASA-TH-D-8472] N77-31093

Statistical rev lev of counting accelerometer datafor Ravy and Barine fleet aircraft[AD-A041266] H77-31140

FIL1BBHT IIHDIISComposite tanks for aerospace vehicle application

A77-46516FIIITB DIFFBBEBCB THEOBI

The transonic oscillating flap: A comparison ofcalculations with experiments

H77-31086Efficient solution of unsteady transonic flows

about airfoilsH77-31087

Application of a finite difference method to theanalysis of transonic flow over oscillatingairfoils and wings

H77-31090Burnerical analyses of soft body impacts on rigid

and deformable targets[AD-A040030] H77-31168

FIIITB BLEBBIT HETHODApplication of the finite element technique

combined with the collocation method to subsoniclifting surface problems

A77-47537Application of finite element approach totransonic flow problems

A77-47539Application of finite element method for the

solntion of transonic flowA77-47540

a-13

FIB.B COBTBOL SUBJECT IIDEX

Analysis of transonic flow over lifting andoscillating airfoils

A77-47542Hixed finite element models and dual iterative

methods for transonic flowA77-47543

Transonic flow simulation by the finite elementmethod via optimal control

A77-47544PIEE COHTBOL

General principles of automatic TV trackersfor fire control and missile tracking

A77-44812The development and simulation of an automatic

gunnery system for advanced fighter aircraftA77-47257

FIBE PBEVESTIOHAircraft interior sandwich panel development

A77-47625FIBBS

DS air carrier accidents involving fire, 1965through 197* and factors affecting the statistics[PB-266883/8] 1177-31112

FLAHHABILITY.Aircraft interior sandwich panel development

A77-47625FLAPS (COHTBOL SOBFACES)

The transonic oscillating flap: A comparison ofcalculations with experiments

N77-31086FL1GBT CHABSCTEBISTICS

Analysis methods and computer programs developedfor the YC-15 STOL flight test program[AIAA PAEEB 77-1215] A77-44317

Flight effects on exhaust noise for turbojet andturbofan engines - Comparison of experimentaldata with prediction

A77-44462Aircraft Soviet technology

H77-30067Airworthiness and flight characteristics

evaluation C-12A aircraftTAD-A0102391 N77-31136

FLIGHT COBDITIOBSAn interpretation of the Army standard hot day inoperational terms for helicopter hover

A77-44513The measurement of performance, stability andcontrol characteristics of a high subsonic jetaircraft in non-steady flight conditionsemploying high accuracy instrumentation techniques

A77-15525Briefs of fatal accidents involving weather as acause/factor, OS general aviation 1975,[PB-2676i(8/(l] N77-31119

FLIGHT COITBOLAnalysis/theory of controlled configured structures

[AIAA PAPEB 77-1212] A77-44316Validation of an airport simulation model

A77-45719Numerical modeling of helicopter piloting

A7 7-4 6 348Singular perturbation analysis approach forsystems with highly coupled dynamics withapplication to optimal aircraft flight control

A77-46617Hicrocompnter BPV stabilization and control system

A77-47348Flight control. I - The aircraft as controlled

system German bookA77-47675

Flight control testing of the VAK-191B aircraft[AD-A040535] H77-31137

A failure effects simulation of a low authorityflight control augmentation system on a DB-1HhelicopterrsASA-TH-73258] B77-31174

FLIGHT BAZABDSThe effect of terrain near airports on significant

low level wind shear[AIAA PASBB 77-12112] A77-44334

FLIGHT IBSTBOHBHTSBead-up display in commercial aviation

CAIAA PAPEB 77-12H1] A77-44333Bole of future automated flight deck displays in

improving operating costs[AIAA PAPEB 77-1252] A77-44340

Aircraft equipmentB77-30069

Instruments and method of air navigationH77-30070

Energy management display for air combat maneuvering[AD-A040198] 877-30109

Master monitor display applications study for theA-7EPAD-A039882] H77-30118

FLIGHT HECHAHICSBecognition criterion and production of easily

solvable models for flight mechanicaloptimization problems[IFD-9/76] H77-31178

FLIGHT OPTIHIZATIOHBole of future automated flight deck displays in

improving operating costs[AIAA PAPEB 77-1252] A77-44340

FLIGHT PATHSAn overview of Viking navigation

A77-04427Feasibility demonstration of the earth referenced

maneuvering flight path display[AIAA PAPBB 77-1114] A77-B5171

A laboratory investigation into flight pathperturbations during steep descents of V/STOLaircraft[AD-A040101] B77-30135

FLIGHT SAFETYEmergency-power benefits to multi-engine helicopters

A77-44515FLIGHT SIHOLATIOH

Onited's experience with computer generated visualsystems, April 1977 for aircraft cockpits

A77-44431Simulation of flight-type engine fan noise in theBASA-Lewis 9 x 15 anechoic wind tunnel

A77-44456Scanned laser visual system for military

flight simulationA77-44814

Bumerical modeling of helicopter pilotingA77-46348

A program for increased flight fidelity inhelicopter simulation[AD-A039234] N77-30108

A mathematical force and moment model of a DH-1Hhelicopter for flight dynamics simulations[SASA-TB-73254] S77-31175

FLIGHT TESTSAnalysis methods and computer programs developed

for the 1C-15 STOL flight test program[AIAA PAPBH 77-1215] A77-44317

A digital data acquisition and reduction systemfor flight testing general aviation aircraft[AIAA PAPEB 77-1216] A77-44318

Flight test results for an advanced technologylight airplane[AIAA PAPEB 77-1217] A77-44319

A new concept of static stability and its flighttesting in supersonic flight

A77-44815An investigation of the near-field wake behind a

full-scale test aircraftA77-44816

A tryont of a rigid airship under tropicalconditions

A77-45460IC-14 flight test results[AIAA PAPBB 77-1259] A77-45512

Central integrated test system /CITS/ - Checkthree times for onboard testing of B-1aircraft[AIAA PAPEB 77-1260] A77-45513

Tethered hover flight tests of a vertical attitudetakeoff and landing remotely piloted vehicle

A77-47341multiple Drone Control development for BPV andelectronic warfare applications

A77-47345Boyal Air Force assessment flights of Omega

Navigation SystemA77-47813

GATOB/AV-8A environmental captive flight vibrationresponse tests *[AD-A036498] H77-30114

Flight test of an 8000 psi Lightweight HydraulicSystem (LHS)[AD-A039717] H77-30120

A-14

SUBJECT IIDBI GBABS

Definition of a data collection system for OS Anytactical microwave landing system evaluation[AD-A041230] B77-31126

Flight control testing of the VAK-191B aircraft[AD-A040535] H77-31137

Comparative perfornance measurements of twohelicopter blade profiles in hovering flight[iBC-B/8-3792] H77-31143

iSDiH (aircraft to satellite data relay) flighttest reportCHASA-T8-73744] H77-31355

FLIGHT TBAIHIHGA program for increased flight fidelity inhelicopter simulation[AD-A039234] R77-30108

FLOS CBAEACTBEISTICSFlov characteristics in an expansion tannel as

inferred from velocity measurementsA77-47108

FLO! DISTBIBDTIOROn the validity of lifting line concepts in rotor

analysisA77-44444

Aerodynamics of a confined jet with variable densityA77-47248

The calculation of flov fields about threedioensional bodies in high altitude(free-nolecolar flow of central atoms)tDLB-FB-75-45] S77-30922

Iterative calculation of flov past a thickcanbered King near the groundCABC-CP-1370 J (T77-31101

FLOI BQOATIOISApplicability of azisymmetric analysis inpredicting supersonic flov through annularcascadesCASHE PAPEB 76-PRB-B] 177-44344

FLOID BECHAHICSHultistage axial-flow tnrbonachinery wake

production, transport, and interaction[AD-A01111083 H77-31173

FLOTTBEFlutter-suppression studies on an activelycontrolled variable-geometry wind-tunnel model

A77-46805FLOTTBB AHALISIS

Conparative flutter calculations for the Viggenaircraft

A77-44818An optical technique for measuring vibratory

motion in rotating machineryA77-47090

Flutter calculation for the Viggen aircraft withallowance for leading edge vortex effect

H77-31083FLI BI RIBE COBTROL

Handling gnality criteria development fortransport aircraft with fly-by-wire primarycontrol systems[RLB-TB-74141-U] N77-31179

FOG BISPBBSAIA method for determining the point of lift-off and

modified trajectory of a ground-based heatedturbulent planar jet in a co-flowing wind[AD-A040704] H77-31722

FOBBATFormat practices for documenting tine critical,

harzardous procedures[AD-A036369] H77-30100

FOBHI16 TBCHRIQOESProcess development for fabricating sculptured

decorative interior aircraft panels using sheetmolding compounds

A77-46508FOBTBAB

CB-47 medium lift helicopter effectivenessevaluation program run bookCAD-A041462] R77-31142

FBEB BOLECOLAB FI01The calculation of flow fields about three

dimensional bodies in high altitude(free-molecular flow of neutral atoms)[DLB-FB-75-45] H77-30922

FBEE TIBBATIOBExperience gained in adjusting the mathematical

model of the VFR 614 short-haul aircraft by useof measured eigenfreguencies

A77-45391

FRICTIORStudies of friction and wear characteristics of

various wires for wire-brush skids[HASA-TH-D-8517] H77-31131!

FUEL COHBOSTIOHBesearch on noise generated by ducted air-fuel

coobustlon systems[AD-A039957] 877-31169

FUEL CORSOBPXIORlir Few Zealand's methods of flying the DC-10

C A I A A PAPEB 77-1255] 177-44343Fuel conservation for high performance aircraft in

the terminal area177-44434

Fuel conservation through airplane'aaintenanceA77-45925

FULL SCALE TBSI5An investigation of the near-field wake behind a

full-scale test aircraftA77-44816

FUSELAGESThe insertion or elimination of fuselage sections

and the balancing of aircraft477-47699

Investigations of three-dimensional flowseparation on fuselage configurationsCAD-A039382] H77-30421

SAS OERSITIAerodynamics of a confined jet with variable density

177-47248SAS TDBBIRE BHGIHES

Engine control stabilizing compensation-testingand optimization

177-44514Interactive graphics in aircraft gas turbine

engine design477-45491

Gas turbines - Status and prospects; Proceedingsof the Symposium, London, England, February 4,5* 1976

A77-46401The aircraft gas turbine - Status and prospects

A77-46403The airline viewpoint in gas turbine engine

low cost operationsA77-46405

Gas turbines in the BAF from a maintenanceengineering viewpoint

A77-46406Monitoring for preventive maintenance in the small

fleet&77-46411

Gas turbine power for large hovercraftA77-46412

Development of an ultra-low-cost gas turbinefor BPV applications

A77-47344Rays of increasing the resources /potential lives/of gas turbine engines

177-47472An attempt to correlate normal vorticities with

total pressure distortion patterns at theentrance to a gas turbine engine[AD-A040370] R77-30122

The effect of ambient conditions on carbonmonoxide emissions from an idling gas turbinecombustor[RASA-CB-154986] H77-31148

Development of a catalytic combustor for aircraftgas turbine engines[1D-A040135] 877-31171

GAS TOBBIHESAn optical technique for measuring vibratory

motion in rotating machineryA77-47090

Hon-integrated gas turbine engine diagnosticstradeoff analysis[AD-A039494] H77-30125

The 3-D stress analysis of a turbine bladesCAD-A039176J R77-30481

GEABSThe 3000-HP roller gear transmission development

program. Volume 6: Beliability andmaintainability report[AD-1039381] B77-30480

A-15

GEHBBAL AVIATION AIBCBAFT SOEJECT IHDEI

GEHEBiL AVIATION AIBCBAFTA digital data acquisition and redaction system

for flight testing general aviation aircraft[AIA4 PAPEB 77-1216] A77-44318

Technology cones to general aviationmilitary/commercial/ transport technologytransfer by NASA

A77-44959A comparison of the results of dynamic wind-tunneltests with theoretical predictions for anaerosechanical gust-alleviation system for lightairplanes[NASA-TN-D-8521] N77-31072

Briefs of accidents involving aerial applicationoperations, D.S. General Aviation 1975[PB-267654/2] N77-31114

Briefs of accidents involving amatenr/home builtaircraft, OS general aviation, 1975[PB-267652/6] H77-31115

Briefs of accidents, involving corporate/executiveaircraft, DS general aviation, 1975CPB-267651/8] N77-31116

Briefs and accidents involving missing and missinglater recovered aircraft, OS general aviation,1975rPB-267650/0] H77-31117

Briefs of fatal accidents involving weather as acause/factor, DS general aviation 1975,CPB-267648/4] S77-31119

Briefs of accidents involving rotorcraft DSgeneral aviation, 1975[PB-267647/6] H77-31120

Noise levels for turbojet powered airplanes andlarge propeller driven airplanes: Notice ofproposed rule making

N77-31150GEOH2TBY.

Rind tunnel experiments on an actively controlled,variable geometry flutter modelCAD-A039216] 877-30134

GLASS FIBEB BBIBFOBCBD FUSTICSAircraft composite primary structures in Brazil

A77-116807GLOBAL POSITIONING STSTEB

Aircraft navigation with the limited operationalphase of the NAVSTAB Global Positioning System

A77-44436GOHIOHETEBS

A digital goniometer for VOBA77-46263

GBAPBITB-EFOXT COBFOSITE HATEBIALSAccelerated environmental conditioning of the A-7Dcomposite outer wing

A77-46838Design and fabrication of graphite-epoxy bolted

wing skin splice specimens[NASA-CB-145216] N77-30180

GBEAT BBITAIBBritish Airways: An analysis of efficiency andcost levelsCPB-268060/1] H77-31113

GBEAT CIBCLESSimulation of inertial inputs to a strapdown

platform for inertial great circle trajectoriesfSAND-76-0620] N77-30104

GBODBD BASED CO1TBOLOperational concept for a battlefield surveillance

BPV system /Canadair Cl-227/A77-47335

The development of the XHQS-105 Agnila mini-BPVsystem

A77-47338Bemote rate control for BPTs

A77-47352GBODBD EFFECT

Nonlinear lifting-surface theory for yawed andbanked wings in ground proximity

A77-45387GBOOHD EFFECT <AEBODYiABICS)

Iterative calculation of flow past a thickcambered wing near the ground[ABC-CP-1370] N77-31104

An in-flight simulation of approach and landing ofa STOL transport with adverse ground effect[NASA-CB-154875] H77-31133

A method for determining the point of lift-off andmodified trajectory pf a ground-based heatedturbulent planar jet in a co-flowing wind[AD-A040704] N77-31722

GBOBND EFFECT BACHIHESGas turbine power for large hovercraft

A77-46412Performance prediction method for a wing-in-gronnd

effect vehicle with blowing under the wingCAD-A039829] H77-30301

GBOOHD TESTSDucted-fan VIOL BPV system

A77-47353GONBBBY TBAIHIHG

The development and simulation of an automaticgunnery system for advanced fighter aircraft

A77-47257GDIS (OBDBAHCE)

Aircraft gun icing evaluation[AD-A039834] H77-30110

COST ALLEVIATOBSAn analysis of helicopter rotor response due to

gusts and turbulenceA77-44440

A comparison of the results of dynamic wind-tunneltests with theoretical predictions for anaeromechanical gust-alleviation system for lightairplanes[NASA-TN-D-8521] H77-31072

HHEAD-OP DISPUIS

Head-up display in commercial aviationC A I A A PAPBB 77-1241] A77-44333

Feasibility demonstration of the earth referencedmaneuvering flight path display[AIAA PAPEB 77-1114] A77-45171

The presentation of information in combat aircraftA77-47817

BEAT TBABSFBBThe effect of boundary layer changes due to

transient heat transfer on the performance of anaxial-flow air compressortSAE PAPEB 770284] A77-44565

Beat-transfer and pressure measurements on asimulated elevon deflected 30 deg near flightconditions at Hach 7[NASA-IB-I-3563] N77-31440

BELICOPTEB COHTBOtThe remotely piloted helicopter

A77-44443A failure effects simulation of a low authority

flight control augmentation system on a OH-1BhelicopterCHASA-TB-73258] H77-31174

BELICOFTEB DBSISNThe remotely piloted helicopter

A77-44443An interpretation of the Army standard hot day in

operational terms for helicopter hoverA77-44513

Army aviation manufacturing technology programguidance[AD-A040821] N77-30074

Single-rotor helicopter design and performanceestimation programs. Volume 1: Hethodology[AD-A040803] N77-31138

Sensitivity of Army helicopter operating andsupport costs to changes in design and logisticparametersCAD-A040353] S77-31139

Summary of helicopter airframe testing in theshipboard environmentCAD-A039748] B77-31144

BELICOPTEB ENSUESEngine control stabilizing compensation-testing

and optimizationA77-44514

Emergency-power benefits to multi-engine helicoptersA77-44515

Characteristic time emissions correlations - TheT-63 helicopter gas turbine combnstor

A77-44824HBLICOPTEB PBBFOBflAHCE

An analysis of helicopter rotor response due togusts and turbulence

A77-44440OHEBA aerodynamic research work on helicopters

CONEBA, IP HD. 1977-42E] A77-44957Numerical modeling of helicopter piloting

A77-46348

A-16

SUBJECT HDII IHSTBOBBNT LAHDI1G SISTERS

Single-rotor helicopter design and performanceestimation programs. Volume 1: Bethodology[AD-A040803] B77-31138

HBtlCOPIlB Tin, IOTOBSBain rotor make/tail rotor interaction

A77-44441HELICOPTBB iilBS

Bain rotor wake/tail rotor interactionA77-44441

On the static pressure in the vake of a hoveringrotor

A77-44442BI1ICOPTEBS

Helicopter offshore operations oil and gasexploration and production

A77-44437any aviation manufacturing technology program

guidance[AD-A040821] 877-30071

A program for increased flight fidelity inhelicopter simulation[AD-A039234] H77-30108

Automatic target hand-off using correlationtechniques[AD-A036435] H77-30115

The 3000-HF roller gear transmission developmentprogram. Volume 6: Beliability andmaintainability report[AD-A039381J 877-30480

HIGH ALTITODEThe calculation of flov fields about three

dimensional bodies in high altitude(free-molecular flow of neutral atoms)[DLB-FB-75-45] H77-30922

HIGH TEBPEBATOBB AIBA method for determining the point of lift-off and•odified trajectory of a ground-based heatedturbulent planar jet in a co-flowing wind[AD-A040704] H77-31722

HIGH TBHPEBATOBB LOBBICAIISQuantitative TLC analysis of amine antiozidants in

high-temperature jet engine lubricants[AD-A039909] N77-30124

HIGH TOLTAGBSDevelopnent of lightweight transformers forairborne high power suppliesCAD-AOB1515] H77-31162

HOBIZOBNavigation checkpointing using horizon correlation[AD-A039946] H77-30103

HOT iBATBBBAn interpretation of the Army standard hot day inoperational terms for helicopter hover

A77-44513HOVBBHG

On the static pressure in the vake of a hoveringrotor

A77-44442Tethered hover flight tests of a vertical attitudetakeoff and landing renotely piloted vehicle

A77-47341Ducted-fan VTOL BPV systen

A77-47353HOVEBIIG STABIUTI

Hover evaluation of circulation control high speedrotor[AD-A040921] H77-31100

Comparative performance measurements of twohelicopter blade profiles in hovering flight[ABC-B/B-3792] H77-31143

BOBSComposite hubs for low cost turbine engines

stress analysis using BASTBAHA77-46520

BOBAI FACTOBS B86IIBBBII6Design criteria for aircraft warning, caution and

advisory alerting systems[AIAA PSFED 77-1240] A77-443J2

Design and evaluation methods for optimizingejection s«at cushions for comfort and safety[AD-A03603S] H77-31110

BTBBID COBPOIEBSDevelopment and verification of real-time, hybrid

computer simulation of P100-PB-100 (3) turbofanengine[HASA-TP-1034] 877-31154

HTDBAD1IC BOBIPBEITFlight test of an 8000 psi Lightweight Hydraulic

System (LBS)CAD-A039717] B77-30120

An extended prediction model for airplane brakingdistance and a specification for a total brakingprediction systems, volume 2(AD-A039967] H77-30476

BIDBOCABBOH COSBOSTIOIThe effect of ambient conditions on carbon

monoxide emissions from an idling gas turbinecocbnstor(HASA-CB-154986] H77-31148

HIDBOGBI FOELSStreamtnbe analysis of a hydrogen-burning scramjet

exhaust and simulation techniqueA77-44817

HIPEBBOLIC NAVIGATIONOmega system performance predictions

A77-44438Position finding using distance measurements

in hyperbolic navigation877-44570

HTPEBSOBIC AIBCBAFTEffect of an integrated scramjet installation on

the subsonic performance of an aircraft designedto Bach 6 cruise[ A I A A PAPEB 77-1230] A77-44326

HIPBBSOIIC FLIGHTBeat-transfer and pressure measurements on a

simulated elevon deflected 30 deg near flightconditions at Bach 7[HASA-TH-I-3563] H77-31440

BIPEBSOBIC FLO!numerical solution of the conically symmetric

Bavier-Stokes equations for hypersonic flow atangle of attack

1177-30079HIPEBSOHIC SPEED

An evaluation of boundary layer forces andmeasurement methods[AD-A040947) H77-3121'8

ICE FOBHATIOHAn integrated approach to the problem of aircraft

icingC A I A A PAPEB 77-1218] A77-44320

Aircraft gun icing evaluation[AD-A039834] H77-30110

ICE PBEVB1TI01An integrated approach to the problem of aircraft

icing[AIAA PAPEB 77-1218] A77-44320

IHAGE COBBELATOBSAutomatic target hand-off using correlation

techniques[AD-A036435] B77-30115

IBPACT TESTSNumerical analyses of soft body impacts on rigid

and deformable targetsTAD-A040030] N77-31168

IB-FLIGHT BOHITOBIHGAn in-flight simulation of approach and landing of

a STOL transport with adverse ground effect[NASA-CB-154875] N77-31133

IIDEIES (DOCOBBITATION)Listings of accidents/incidents by aircraft make

and model, OS civil aviation, 1975[PB-267644/3] N77-31123

I1EBTIAL NAVIGATIONOutlook for utilization of the North Atlantic air

space in 1978A77-44572

Aircraft cyberneticsN77-30071

HBBTIAL PLATPOBHSSimulation of inertial inputs to a strapdown

platform for inertial great circle trajectories[SAHD-76-0620] N77-30104

IILET FLOWEffects of temperature transients at fan inlet of

a turbofan engine[NASA-TP-1031] N77-31153

1HSTBOBEIT LABDING STSTEBSInstruments and method of air navigation

877-30070

A-17

IgTEGBATED CIBCOITS SUBJECT IHDBX

IgTEGBATED CIBCDITSKu-band integrated circuit receiver front end

module for BPVA77-47354

IIVISCID FLOSApplication of finite element method for thesolution of transonic flow

A77-H7540ITERATIVE SOIOIIO*

Hixed finite element models and dual iterativemethods for transonic flov

A77-47543

JET HTIIIG FLOiAerodynamics of a confined jet with variable density

A77-47248JET THBOST

Development of a small, low cost turbojet enginewith thrust augmentation for BPY

A77-47347JOISTS IJOICTIOSSJ

Exploratory of development of durability ofadhesive bonded joints[AD-A039864] H77-30249

J-85 EBGI1EEffects of forward velocity on noise for a J85turbojet engine with mnltitnbe suppressor froawind tunnel and flight tests

A77-44460JET AIBCBAJT

The profile descent ATC for aircraft descent[AIAA PAEEB 77-1251] A77-44339

The measnrenent of perfornance, stability andcontrol characteristics of a high subsonic jetaircraft in non-steady flight conditionsemploying high accuracy instrumentation techniques

A77-45525Noise levels for turbojet powered airplanes and

large propeller driven airplanes: Notice ofproposed rule making

N77-31150JBI ilBCBAFI BOISE

Simulation of flight-type engine fan noise in theNASA-lewis 9 i 15 anechoic wind tunnel

A77-4U456Core noise source diagnostics on a tnrbofan engine

using correlation and coherence technignesA77-44457

Flight effects on exhaust noise for turbojet andturbofan engines - Comparison of experimentaldata with prediction

A77-44462Accuracy of the Kirchoff formula in determining

acoustic shielding with the use of a flat plateCNASA-TB-73261 ] 1177-30906

JET ESGIIE FUELSThe military utility of very large airplanes and

alternative fuelsA77-47271

The potential rule of technological modificationsand alternative fuels in alleviating Air Forceenergy problems[AD-A039597] N77-30261

An evaluation of very large airplanes andalternative fuels[AD-A040532] H77-31334

JET EHGISBSComputational methods to obtain time optimal jet

engine controlA77-46614

Increasing jet-engine thrnst by water-augmentationA77-46984

Quantitative TLC analysis of anine antioxidants inhigh-temperature jet engine lubricants[AD-A0399091 H77-30124

parametric performance evaluation of a jet enginederived from a turbocharger[AD-A039116] B77-30126

Research on noise generated by ducted air-fnelcombustion systems[AD-A039957] 1177-31169

laser velocimeter utilization in jet enginealtitude test cells[AD-A041019] H77-31477

JET EIBAOSTEffects of forward velocity on noise for a J85turbojet engine with nnltitube suppressor fromwind tunnel and flight tests

A77-44460Streamtube analysis of a hydrogen-burning scramjetexhaust and simulation tecbnigne

A77-44817JET FLOf

Rearrangement of vortex structures in the wakebehind a body and in a jet

A77-07674

KALUAH FILTERSAn extended Kalian filter for estimating

aerodynamic coefficients[AD-A040594] H77-30092

KBBHEL FDICTIOISGeneralized Theodorsen solution for singular

integral equations of the airfoil classA77-44946

LiBIJAB FLOiHass flow requirements for LFC wing design

Laminar Flow Control[AIAA PAPER 77-1222] A77-44323

LAHDI1G GEARA-7 titanium nose gear development

A77-46801Investigation of landing gear deck obstruction

effects by drop testingA77-46825

LASER APPLICATIONSScanned laser visual system for military

flight simulationA77-44814

LASERSLaser velocimeter utilization in jet engine

altitude test cellsCAD-A041019] H77-31477

LATEBAL COHTROLEstimates of the effectiveness of automatic

control in alleviating wake vortex induced rollexcursions[HASA-TH-73267] N77-30129

Vortex-lift roll-control device[HASA-CASE-lAB-11868-2] N77-31176

LAOICHINGSelection of optimum RPV -operational lannch and

recovery techniquesA77-47340

LEADIIG EDGE SIBBPAnalysis/theory of controlled configured structures

[AIAA PAPBB 77-1212] A77-44316LEADIIG EDGES

Leading-edge vortex effect on the flutter speedA77-44819

Experimental investigation concerning thereduction of wave drag of pointed symmetricalwings of egual volume with subsonic leading edgeand bell-shaped planfort for different thicknessdistributions in the spanwise and chordwisedirections[DLB-FB-75-62] H77-30087

Flutter calculation for the viggen aircraft withallowance for leading edge vortex effect

H77-31083LIFE (DDBABILITI)

Durability testing of the A-7D compositeouter-wing panel

A77-46808LIFT DEVICES

Vortex-lift roll-control device[NASA-CASE-LAB-11868-2 ] H77-31176

LIFT DBAS RATIOExperimental investigation concerning the

reduction of wave drag of pointed symmetricalwings of equal volume with subsonic leading edgeand bell-shaped planform for different thicknessdistributions in the spanwise and chordwisedirections[DLB-FB-75-62] B77-30087

Performance prediction method for a wing-in-groandeffect vehicle with blowing under the wing[AD-A039829] H77-30301

A-18

SUBJECT I1DBI HEASOBIIG IBSTBOBEBTS

LIFT FABSHiSA/Havy lift/cruise fan. Phase 1: Design summaryrBASA-CB-135242] 877-31149

LIFTIIG BOOHSBonlinear lifting-surface •theory for yawed and

banked wings in ground proximityA77-45387

Analysis of transonic flov over lifting andoscillating airfoils

A77-47542Sone quadrature methods for lifting wing theory[IFD-5/76] H77-30097

LIGHT ilBCBAFTFlight test resnlts for an advanced technology

light airplane[AliA PIPES 77-1217] A77-44319

Technology comes to general aviationmilitary/commercial/ transport technologytransfer by NASA

A77-44959Hicrocompnter EPV stabilization and control system

A77-47348A miniature rotary-wing BPv

A77-47351Briefs of accidents, involving corporate/executiveaircraft, DS general aviation. 1975[PB-267651/8] H77-31116

LIBEAB STSTEBSLinear regulator design for stochastic systems by

a multiple tiie scales method withapplication to F-8 aircraft longitudinal control

A77-46621LOAD DISTBIBDTIOI (FOBCES)

Application of the finite elenent techniquecontained with the collocation method to subsoniclifting surface problems

A77-47537LOADS (FOBCES)

A study of spectrum loading and range-paircounting method effects on cumulative fatiguedamageCAD-A039651) H77-31145

LOCKBBBD AIBCBAFTPropeller study. Fart 3: Experimental

determination of thrust and torque on the TO-3AaircraftCHASA-CB-155003] H77-31158

LOGISTICS BABAGEBEBTFlying, maintenance, and the sale of parts to the

field: Interactive models for AH-1 and CB-47systems[AD-A039193] H77-30073

Sensitivity of Army helicopter operating andsupport costs to changes in design and logisticparameterstAD-AO10353] H77-31139

LOBGIXUDIBAL CO IT BO LLinear regulator design for stochastic systems bya multiple time scales method withapplication to F-8 aircraft longitudinal control

A77-46621Subsonic and supersonic longitudinal stability and

control characteristics of an aft-tail fighterconfiguration with cambered and uncanbered vingsand cambered fuselage[HASA-TS-D-8472] H77-31093

The need of stick force stability forattitude-stabilized aircraft, part 1tBLB-TB-76125-D] 1177-31180

LOBGUODIBAL STABILITYSubsonic and supersonic longitudinal stability and

control characteristics of an aft-tail fighterconfiguration vith cambered and uncambered vingsand cambered fuselagetHASA-TB-D-8472] B77-31093

LOB AS CInteractive LOBAH-C to geographic andgeographic-to-LOBAB-C computation(BASA-CB-153985J H77-30101

LOB COSTComposite hubs for low cost turbine enginesstress analysis using BASTBAB

A77-46520Development of an ultra-low-cost gas turbine

for BFV applicationsA77-47344

Development of a small, low cost turbojet enginewith thrust augmentation for BPV

A77-47347

MBAGIBSIOH

Heasnrements of buffeting on two 65 deg deltawings of different materials

B77-31079BAGBETIC IBDOCIIOI

A study of the charge and current induced on anaircraft in an BHP simulator facility. Part 1:The formulation. Part 2: The singularityexpansion method. Part 3: The numerical resnlts[AD-A039507] H77-31384

BALFOBCTIOBSA failure effects simulation of a low authority

flight control augmentation system on a OH-1Hhelicopter[BASA-TB-73258] H77-31174

BAH BACBIBE SISTESSInteractive graphics in aircraft gas turbine

engine designA77-45491

RAIAGEflEIT AIALISISDesign-to-cost in action

[ASHE PAPEB 77-DE-9] A77-46904BABAGEREHT IBFOHBATIOB STSTEBS

An evaluation of a raster scan display for use inan aircraft information handling system[AD-A0396521 H77-30117

BABBED SPACE FLIGHTIn Herculean flight Soviet aviation history

H77-30066BABOALS

Format practices for documenting time critical,harzardous procedures[AD-A036369] H77-30100

BAFPIBGStereographic projections in air traffic control

systemsA77-46262

BHAV control for airborne surveysA77-46264

B&BIIE PBOPBLSIOSGas turbine power for large hovercraft

A77-46412BaBITIBE SATELLITES

Satellite communications for the mobile service[AAS 76-045] A77-46630

BASKET BBSEABCHThe timing of technology - Commercial transport

aircraft( A I A A P&PBB 77-1200] A77-45503

HABOTS (ESI)Satellite communications for the mobile service

C A A S 76-045] A77-46630BABS LAIDIBG

An overview of Viking navigation177-44427

BASS BALABCBThe insertion or elimination of fuselage sections

and the balancing of aircraftA77-47699

BASS DISTBIBOTIOHVibration analysis of rotor blades with an

attached concentrated mass[HASA-CB-154987] B77-31537 i

BASS FLOB FACTOBSBass flow requirements for LFC wing design

Laminar Flow Control[AIAA PAPEB 77-1222] A77-44323

HATBBBATICAL BODELSExperience gained in adjusting the mathematical

model of the VP9 614 short-haul aircraft by useof measured eigenfreguencies

A77-45391Validation of an airport simulation model

A77-45719Some mathematical aspects of air traffic systems

A77-47816An extended Kalman filter for estimating

aerodynamic coefficients[AD-A010594] H77-30092

A mathematical force and moment model of a DB-1Bhelicopter for flight dynamics simulations[BASA-TH-73254J 877-31175

B2ASDBIBG IBSTBOBKBISSensor for measuring instantaneous angle of attack

of helicopter blades[BASA-CB-154808]. B77-30444

A-19

HECHABTCAL DBIVES SUBJECT IBDEX

BECHAHICAL DBIVESThe 3000-HP roller gear transmission development

program. Volume 6: Reliability andmaintainability report[AD-1039381] H77-30480

BECHAHICAI PBOPEBTIESAircraft composite primary structures in Brazil

477-46807BETA I. BOIDIBG

Advanced composites and advanced metallics meetthe challenge of design-to-costfAIAA PAPEB 77-1234] 477-44329

HETiL P4TI6DBFatigue 1977; Proceedings of the Conference,

Cambridge University, Cambridge, England, (larch28-30, 1977

477-47501Fatique problems in service - Aircraft structures

477-47503BETA! GBIBDIBG

ECU methods for aircraft engine manufactureelectrochemical machiningfSHE PAPEB BE76-705] 477-45871

HETAl HiTBIX COHPOSITESComposite tanks for aerospace vehicle application

477-46516Thermal stability of transition metal monocarbide

fibers in refractory composites prepared byunidirectional solidificationfOHEBl, IP HO. 1977-62] 477-47136

BETA I SOBFACESSurface finishing of metal airfoils byadhesive bondingCBASA-CASE-BSC-12631-2] H77-31131

BETEOBOLOGICAL PABABETEBSAn integrated approach to the problem of aircraft

icingCAIA4 PAPEB 77-12181 477-44320

BETEOBOLOGIC41 SATELLITESASDAB (aircraft to satellite data relay) flighttest reportCHASA-TB-73744] B77-31355

BICBOPBOCESSOBS4 special-purpose pocket calculator for aviation

and maritime navigation477-44571

Bicrocooputer BPV stabilization and control systemA77-47348

BICBOSTBIP TBABSHISSIOB LIKESKu-band integrated circuit receiver front end

module for BPV477-47354

BICBORAVE IBAGBBTBicrowave holographic imaging of aircraft vith

spaceborne illuminating sourceB77-30439

BICBOIAVE LAIDIIG SISTEBSDefinition of a data collection system for OS Army

tactical microvave landing system evaluation[AD-A041230] B77-31126

HIDAIB COLLISIOISBriefs of accidents involving midair collisions,

OS general aviation, 1915tPB-267645/0] N77-31122

BILITABI AIBCBiFTParametric study of advanced long range

military/commercial cargo transportsT A I A A PAPEB 77-1221] 477-44322

Advanced composites and advanced metallics meetthe challenge of design-to-costCAIAA PAPEB 77-1234] A77-44329

Thrust augmenting ejector technology for FavyaircraftCAIAA PAPEB 77-1239] A77-44331

Scanned laser visual system for militaryflight simulation

A77-44814Preliminary design and analysis of advanced

military transportsCAI4A PAPEB 77-1224] 477-45502

Gas turbines in the BAF from a maintenanceengineering viewpoint

477-46406Investigation of landing gear deck obstructioneffects by drop testing

477-46825The military utility of very large airplanes and

alternative fuels477-47271

BillTAB! ATIATIOIBoyal Air Force assessment flights of OmegaNavigation System

A77-47813Definition of a data collection system for US Army

tactical microwave landing system evaluationIAD-A041230] B77-31126

BILITABI HELICOPTERSAn interpretation of the Aray standard hot day in

operational terms for helicopter hoverA77-44513

Sensitivity of Army helicopter operating andsupport costs to changes in design and logisticparameters[AD-4040353] H77-31139

BILITABI TBCHHOLOGICharacteristics of fighter aircraft

C A I A A PAPES 77-1219] A77-44321General principles of automatic TV trackers

for fire control and missile trackingA77-44812

BIHIBOB OBAGAerodynamics of horizontally-opposed aircraft

engine installationsC A I A A PAPEB 77-1249] A77-45508

BISSILE IAOMCHBBSBPV applications of Tomahavk cruise missile

477-47336BISSILE SIGHATOBBS

Automatic target hand-off using correlationtechniquesCAD-4036435] H77-30115

BISSILE TBACKI1GGeneral principles of automatic TV trackers

for fire control and missile tracking477-44812

80LDIHG B4TBBIALSProcess development for fabricating sculptureddecorative interior aircraft panels using sheetmolding compounds

A77-46508B01ITOBS

flaster monitor display applications study for theA-7ECAD-A039882] H77-30118

BOHTE CABLO BBIHODBonte Carlo simulations of VOB/DBE holding

procedures* Basic ideas and applicationsCDLB-FB-77-08] H77-30105

BOBTALITTBriefs of fatal accidents involving veather as a

cause/factor, OS general aviation 1975,CPB-267648/4] ' H77-31119

BOLTIEIGIHE VESICLESEmergency-power benefits to multi-engine helicopters

477-44515

•ASA PBOGBABSTechnology comes to general aviationmilitary/commercial/ transport technologytransfer by HASA

A77-44959Experiment and analysis on the flow process

dynamics of the NASA-Langley eight foottransonic pressure tunnelCBASA-CB-154806] H77-30085

IASTBABComposite hubs for low cost turbine enginesstress analysis using BASTBAB

A77-46520HATOBAL GAS

Helicopter offshore operations oil and gasexploration and production

A77-44437»AVIEB-StOK2S BQDATIOH

numerical solution of the conically symmetricBavier-Stokes equations for hypersonic flov atangle of attack

H77-30079lAVIGATIOg AIDS

Head-up display in commercial aviationCAIAA PAPBB 77-1241] 477-44333

Aircraft navigation with the limited operationalphase of the HAVSTAB Global Positioning System

477-44436

4-20

SUBJECT HDBI OHBGi NAVIGATION ST.STBB

1 special-purpose pocket calculator for aviationand maritime navigation

A77-44571A digital goniometer for ?OB

A77-46263B8AV control for airborne surveys

A77-46264Boyal Air Force assessment flights of Omega

navigation Systei177-47813

Flight experience with OnegaA77-47814

An American Omeqa navigation evaluation programme- 1975-1977

A77-47815The presentation of information in combat aircraft

A77-47817Interactive 10BAB-C to geographic andgeographic-to-LOBAH-C computation[NASA-CB-153985J H77-30101

NAVIGATION IISIBOIBHISThe design of complex navigation systemsBossian book

A77-46«9»Instruments and method of air navigation

H77-30070NATSTAB SATB11ITBS

Aircraft navigation vith the limited operationalphase of the BAVSTAB Global Positioning System

A77-44436BATT

Statistical review of connting accelerometer datafor Bavy and Harine fleet aircraft[AD-A041266] H77-31140

•BAB FIELDSAn investigation of the near-field Hake behind afall-scale test aircraft

A77-4<l816Upstream influence on the near field of a planeturbulent jet

A77-47005NITBOSBN OH DBS

Development of a catalytic combnstor for aircraftgas turbine engines[AD-A040135] H77-31171

BOISEBoise levels for turbojet powered airplanes and

large propeller driven airplanes: Hotice ofproposed rule naking

B77-31150Research on noise generated by ducted air-fuelcombustion systems[AD-A039957J H77-31169

•OISE IBTEISITTProblems in predicting aircraft noise exposure

A77-17561Boise levels for turbojet povered airplanes andlarge propeller driven airplanes: Hotice ofproposed role mailing

B77-31150Calculation of side line noise levels during takeoff

[AD-AOH0624] H77-31170Selection of minimum day/night levels for noisemap

contour calculations aircraft noiseabatement in airport planningCAD-A040623] B77-31922

•OISE BEASUBBHBNTCore noise source diagnostics on a tnrbofan engine

using correlation and coherence techniquesA77-44057

Coherence and phase techniques applied to noisediagnosis in the RASA Ames 7 times 10-foot Hindtunnel no. 1CHASA-CB-152039] H77-30905

BOISE PBOPAGATIOBCoherence and phase techniques applied to noise

diagnosis in the HASA Ames 7 tiles 10-foot Kindtunnel no. 1fHASA-CB-152039) B77-30905

•OISE BBDOCflOIOptimum acoustic design of free-running low speed

propellers[AIAA PAPBB 77-1248] A77-44337

Rain rotor sake/tail rotor interactionA77-44041

Effects of forward velocity on noise for a J85turbojet engine vith mnltitube suppressor fromHind tunnel and flight tests

A77-44460

Air transport noise reductionA77-44550

Accuracy of the Kirchoff formula in determiningacoustic shielding vith the use of a flat plate[NASA-TH-73261] B77-30906

Acoustically swept rotorCBASA-CASB-ABC-11106-1 ] H77-31130

Boise levels for turbojet povered airplanes andlarge propeller driven airplanes: Hotice ofproposed rule making

B77-31150Propeller study. Part 2: The design of

propellers for minimum noise[BASA-CB-155005] B77-31157

•OISB TOLEBANCBProblems in predicting aircraft noise exposure

A77-07561•OILIHBAB BQUATIOHS

Characteristics of the boundary-layer equations ofthe minimum time-to-cllnb problem

A77-46618HOSE iHBBLS

A-7 titanium nose gear developmentA77-46801

BOTCH TESTSFatigue life prediction of complex structures

CASHE PAPBB 77-DE-46] A77-4691510ZZLB DESISB

Bonaxisymmetric nozzle technology program - Anoverview for fighter aircraft engines[AIAA PAPEB 77-1225] A77-44325

Besults of a feasibility study to add canards andADEB nozzle to the IF-17 AugmentedDeflecting Exhaust Nozzle[AIAA PAPBB 77-1227] A77-45506

BOZZ1B FtOBFlow characteristics in an expansion tunnel as

inferred from velocity measurementsA77-47108

Aerodynamics of a confined jet with variable densityA77-47248

BOZZLB GEOBETBIOTI noise correlation for several nozzle/winggeometries using a 5:1 slot nozzle with externaldeflectors Over The »ing configurations

A77-44461•DBEBICAL ABALTSIS

The use of probability analysis in aircraftcertification and its effects on maintenance andequipment maintenance[AIAA PAPBB 77-1256] A77-45509

The coaputer for design and optimization withapplications to aircraft design, etc

A77-B6136Numerical solution of the conically symmetricBavier-Stokes egnations for hypersonic flow atangle of attack

H77-30079Numerical analyses of soft body impacts on rigid

and deformable targets[AD-&040030] H77-31168

Foundation of the magnetic field integral equationcode for the calculation of the electromagneticpulse external interaction vith aircraftfAD-A039953] H77-31389

NOSEBICAt FLOI VISUALIZATIONTransonic flov simulation by the finite element

method via optimal controlA77-47544

OBLIQOB WINSSF-8 oblique wing structural feasibility study

[NASA-CB-154841] N77-30107OFFSHORE BBBBGX SOOBCBS

Helicopter offshore operations oil and gasexploration and production

A77-44437OIL SIPLOBATIOB

Helicopter offshore operations oil and gasexploration and production

A77-44437OBEGA NAVIGATION STSTEB

Probing the airborne Omega environmentA77-44435

Omega system performance predictionsA77-44438

A-21

OBBOABD EQDIPHEHT SUBJECT IBDEX

VLP pulse timing - Limitations and potential as acompanion to Omega

A77-44439Outlook for utilization of the North Atlantic air

space in 1978A77-4U572

Boyal Air Force assessment flights of Oneganavigation System

A77-I17813Flight experience with Omega

A77-47814An American Onega navigation evaluation programme

- 1975-1977A77-47815

OBBOABD EQOIEHBBXCentral integrated test system /CITS/ - Check

three tines for onboard testing of B-1aircraftCAIAl PiPEB 77-12601 A77-45513

OPEBATIOHS BESEABCBSensitivity of Army helicopter operating and

support costs to changes in design and logisticparameters[AD-A040353] H77-31139

OPTICAL HBASOBIHG IBSTBDHBBTSAn electro-optic airspeed sensor airborneoptical convolution velocimeter

A77-44783An optical technique for measuring vibratory

motion in rotating machineryA77-47090

OPTICAL BAB6E FIBDEBSVisual range: Concepts, instrumental

determination, and aviation applicationsCHBS-HOHO-159] H77-30102

OPTICAL SCABBSBSScanned laser visual system for militaryflight simulation

A77-44814OPTIHAL COBTBOL

Singular perturbation analysis approach for ,systems mth highly coupled dynaiics withapplication to optimal aircraft flight control

A77-46617Linear regulator design for stochastic systems by

a multiple time scales method withapplication to F-8 aircraft longitudinal control

A77-46621Transonic flov simulation by the finite element

method via optimal controlA77-47544

OPTIBIZATIOIThe computer for design and optimization with

applications to aircraft design, etcA77-46136

Decision-making and optimization in aircraft design[AD-A039464] N77-30111

Design and evaluation methods for optimizingejection seat cushions for comfort and safetyfAD-A036035] B77-31110

OSCILLATUG PLOBAnalysis of transonic flow over lifting and

oscillating airfoilsA77-47542

OSCI1LATIOBSThe transonic oscillating flap: A comparison of

calculations with experimentsH77-31086

Application of a finite difference method to theanalysis of transonic flow over oscillatingairfoils and wings

B77-31090

EilELSProcess development for fabricating sculptureddecorative interior aircraft panels using sheetmolding compounds

A77-46508Aircraft interior sandirich panel development

A77-47625PASSESGZB AIBCBAJT

The insertion or elimination of fuselage sectionsand the balancing of aircraft

A77-47699DS air carrier accidents involving fire, 1965

through 1974 and factors affecting the statisticsCPB-266883/8] H77-31112

Briefs of accidents, involving corporate/executiveaircraft, US general aviation, 1975[PB-267651/8J B77-31116

Airworthiness and flight characteristicsevaluation C-12A aircraft[AD-A040239] H77-31136

FAILOADSAir Hew Zealand's methods of flying the DC-10

[AIAA PAPBB 77-1255] A77-44343A miniature rotary-sing BPV

A77-47351PEBFOBBAHCB

cold air performance of a12.766-centimeter-tip-diameter axial-flow cooledturbine. 2: Effect of air ejection on turbineperformance[BASA-TP-1018] H77-30089

PEBPOBBASCE PBEOICTIOBOmega system performance predictions

A77-14438Leading-edge vortex effect on the flatter speed

A77-44819An attempt to correlate normal vorticities vith

total pressure distortion patterns at theentrance to a gas turbine engine[AD-A040370] S77-30122

A laboratory investigation into flight pathperturbations during steep descents of V/STOLaircraft[AD-A040101] B77-30135

Performance prediction method for a wing-in-gronndeffect vehicle with blowing under the wingtAD-A039829] H77-30301

Single-rotor helicopter design and performanceestimation programs. Volume 1: Methodology[AD-A040803] H77-31138

PEBFOBHAHCB TESTSSeakeeping characteristics of a preliminary design

for a sea loiter aircrafttAD-A040062] B77-30113

Parametric performance evaluation of a jet enginederived from a tnrbocharger[AD-A039116] B77-30126

PEBTDBBATIOBA laboratory investigation into flight path

perturbations during steep descents of V/STOLaircraft[AO-A040101] B77-30135

PBBTuBBATIOH THBOBTSingular perturbation analysis approach for

systems with highly coupled dynamics withapplication to optimal .aircraft flight control

A77-46617Characteristics of the boundary-layer egnations of

the minimum time-to-climb problemA77-46618

PHASE SHIFT CIRCUITSA digital goniometer for 'OB

A77-46263PBOTOIOBIZATIOB

Flow characteristics in an expansion tunnel asinferred from velocity measurements

A77-47108PILOT PEBFOBflABCK

BBAV waypoint charting effects on pilotprocedures, training and workload

A77-4»432Energy management display for air combat maneuvering

CAO-A040198] B77-30109Evaluation of vibration levels at the pilot seat

caused by wing flow separationB77-31078

PILOT TBAIBIIGBBAV waypoint charting effects on pilot

procedures, training and workloadA77-4U432

Flight test of an 8000 psi Lightweight HydraulicSystem (LHS)[AD-A039717] B77-30120

PITCHIBG BOSBSISComparison of dynamic stall phenomena for pitching

and vertical translation motionsfBASA-CH-2793] 177-30088

PLASTIC AIBCBiFT STBOCTDBBSAircraft composite primary structures in Brazil

A77-46807

A-22

SDBJECI non BiDIO BECEIVEBS

PL1SIIC COATIIGSSurface finishing of metal airfoils byadhesive bonding[SASA-CASE-BSC-12631-2] B77-31131

POLLOTIOB COBTBOLAir transport noise reduction

A77-U4550POSITIOH (LOCATIOB)

Introductory investigation of the Bange Beasoringsystem/data collection systen (BBS-2/DCS)[AD-A039921] H77-30106

A simple closed-fora solation of a position-fixingproblem[AD-A039303] H77-31127

Digital shaft encoder[AD-A040706] H77-31172

POSITIOI BBBOBSOnega system performance predictions

A77-44438POSITIOB IIDICATOBS

Position finding using distance measurementsin hyperbolic navigation

A77-44570POTB1T1A1 FlOi

Transonic flow simulation by the finite elenentlethod via optimal control

A77-47544COIEBED LIFT AIBCBAFI

Powered lift - Its impact on YC-14 materials andstructures(AIAA PAPEB 77-1231] A77-44327

Application of povered lift and mechanical flapconcepts for civil short-haul transport aircraftdesign[AIAA PAPEB 77-1237) A77-44330

Oil noise correlation for several nozzle/vinggeometries using a 5:1 slot nozzle with externaldeflectors Over The Ring configurations

A77-44461Vectored-engine-over-wing configuration design[AIAA PAPEB 77-1228] A77-15507

PBEDICTIOB ABALYSIS TBCHBIQOESFatigue life prediction of complex structures

(ASBE PAPEB 77-DE-46] A77-46915Fan supersonic flutter: Prediction and testanalysis[ABC-B/B-3789] H77-31163

PBESSDBE DISTBIBOTIOHOn the static pressure in the wake of a hovering

rotorA77-44442

Generalized Theodorsen solution for singularintegral equations of the airfoil class

A77-44946Experiment and analysis on the flov process

dynamics of the BASA-Langley eight foottransonic pressure tunnel[BASA-CB-154806] N77-30085

Systematic pressure distribution and forcemeasurements of two yawed slender wings[IFD-2/76/I] H77-30095

An attempt to correlate normal vorticities vithtotal pressure distortion patterns at theentrance to a gas turbine engine[AD-A040370] H77-30122

Separated-flow unsteady pressures and forces onelastically responding structures

B77-31075A practical framework for the evaluation ofoscillatory aerodynamic loading on wings insupercritical flow

H77-31089PBESSOBE UASOBEBBBTS

Heat-transfer and pressure measurements on asimulated elevon deflected 30 deg near flightconditions at Bach 7[BSSA-TB-I-3563] B77-31400

PBESSOBE VESSEL DESIGBComposite tanks for aerospace vehicle application

A77-46516PBOBABIIITT TBEOBI

The use of probability analysis in aircraftcertification and its effects on maintenance andegnipment maintenance(AIAA PiPEB 77-1256] A77-45509

PBOBLEB SOLVIBGBecognitioQ criterion and production of easilysolvable models for flight mechanicaloptimization problemsCIFD-9/76] B77-31178

PBODDCTIOB EIGIIEEBIBGSelection of optimum BPV operational launch and

recovery techniquesA77-47340

A r m y aviation manufacturing technology programguidance[AD-A040821] B77-30074

PBOGBABBIBG LANGUAGESA study of standardization methods for digital

guidance and control systems(AGABD-AB-90] B77-30136

PBOPBLLBB BLADESOpt imum acoustic design of free-running low speed

propellers[ A I A A PAPEB 77-1248] A77-44337

PBOPELLBB DBIVEThe flow about a slender propeller-driven body in

a temperature stratified fluid[AD-A040847] H77-31099

Boise levels for turbojet powered airplanes andlarge propeller driven airplanes: Botice ofproposed rule making

B77-31150PEOPBLLEB EFFICIBBCT

Propeller study. Part 1: Introduction and overview[BASA-CB-155002] B77-31156

Propeller study. Part 3: Experimentaldetermination of thrust and torque on the TO-3Saircraft[BASA-CB-155003] B77-31158

PBOPB1LEBSPropeller study. Part 1: Introduction and overview

[NASA-CB-155002] 877-31156Propeller study. Part 2: The design of

propellers for minimum noise[BASA-CB-155005] N77-31157

Propeller study. Part 3: Experimentaldetermination of thrust and torgue on the TO-3Aaircraft(B&SA-CB-155003] B77-31158

PBOPDLSIOB SISTEB PEBFOEHiBCEThe military utility of very large airplanes and

alternative fuelsA77-47271

PSEDDOBOISESoftware implementation of a PB spread spectrum

receiver to accommodate dynamics SHFpsendonoise communication link foraircraft/satellites

A77-44738

QDADBATDBBSSome quadrature methods for lifting wing theory

[IFD-5/76] B77-30097QOALITI COBIBOL

Advanced high speed roller bearing inspectiontechniguesCAD-A042121] B77-31529

QOABTICATITB ABALISISQuantitative TLC analysis of amine antioxidants in

high-temperature jet engine lubricants[AD-A039909] B77-30124

QDEDEIBG TBEOBY.Some mathematical aspects of air traffic systems

A77-47816

RAOAB TABGETSStereographic projections in air traffic controlsystems

A77-46262BADIO FBOBIBG

Probing the airborne Omega environmentA77-44435

BADIO BECBITBBSPosition finding using distance measurements

in hyperbolic navigationA77-44570

A-23

BADIO fBAISalSSIOB SUBJECT IHDEI

Software isplementation of a PH spread spectranreceiver to accommodate dynamics SHFpseadonoise communication link foraircraft/satellites

A77-44738Ku-band integrated circuit receiver front end

nodale for BPVA77-47354

BADIO TEAHSBISSIOBVLF poise timing - Limitations and potential as acompanion to Omega

A77-44439BABJET BBGIBBS

Streamtnbe analysis of a hydrogen-burning scramjetexhaust and Emulation technique

A77-44817BABDOH PBOCESSES

Some mathematical aspects of air traffic systemsA77-47816

BABGEFIBDIB6Introductory investigation of the Range Measuring

system/data collection system (BHS-2/DCS)[AD-A0399211 N77-30106

BBAL TIBE OPEBATIOBOperational concept for a battlefield surveillance

HPV system /Canadair CL-227/A77-47335

Development and verification of real-tine, hybridcomputer simulation of F100-P«-100{3) turbofanengineCHASA-TP-1034] H77-31154

BBCOVEBABLE 1ADBCB VEHICLESThe HPV - Complement to manned systems;Proceedings of the Fourth Annual Synposinm,Washington, D.C., Jnne 5-9, 1977

A77-47333The development of the XBQH-105 Aguila oini-BPV

systemA77-17338

Selection of optimum BPV operational launch andrecovery techniques

A77-47340An alternate recovery system for the Aguila

mini-BPV soft landingA77-47346

BBCTABG01AB IIHGSApplication of a finite difference method to the

analysis of transonic flow over oscillatingairfoils and wings

H77-31090BSEBTBY VESICLES

An evaluation of boundary layer forces andmeasurement methods[AD-A040947] H77-31218

BBGOLATIOBSNoise levels for turbo-jet powered airplanes andlarge propeller driven airplanes: Notice ofproposed rule making

H77-31150BBGDLATOBS

Linear regulator design for stochastic systems bya multiple tine scales method mthapplication to F-8 aircraft longitudinal control

A77-46621BBIBFOBCIB6 FIBBSS

Thermal stability of transition metal monocarbidefibers in refractory composites prepared byunidirectional solidification[OHEBA, IP BO. 1977-62] A77-47136

RELIABILITY ABALISISOperational reliability and reliability testing

BookA77-45173

Altitude warning signal system evaluation[AD-A039365] H77-31147

BBLIABILITT EBGIIBEBIHGCompliance with amended FAB 25.1309 - DC-10 case

history Automatic Landing SystemC A I A A PAPEB 77-1257] A77-45510

Control of rare events by aircraft system designregulation - Impact on operations[AIAA PAPEB 77-1258] A77-45511

Gas turbines in the BAF from a maintenanceengineering viewpoint

A77-46406Ways of increasing the resources /potential lives/of gas turbine engines

A77-47472

A program for increased flight fidelity inhelicopter simulationCAD-A039234) H77-30108

ASDAB (aircraft to satellite data relay) flighttest reportfNASA-TH-73744] H77-31355

BEHOTE COMTBOLcomplementary roles for BPVs in support of

tactical manned aircraftA77-47334

Operational concept for a battlefield surveillanceBPV system /Canadair Ct-227/

A77-47335The development of the IHQH-105 Agnila mini-BPV

systemA77-47338

Bemote rate control for BPVsA77-47352

BEHOTE SBISOBSAircraft laboratories and erperience in using them

for the development of methods and means ofremote sensing of earth resources

A77-47199Space experiment simulation using an aircraftlaboratory

A77-47200BEHOTELT PILOTED VESICLES

The remotely piloted helicopterA77-44443

The BPV - Complement to manned systems;Proceedings of the Fourth Annual Symposium,Washington, D.C., June 5-9, 1977

A77-47333Complementary roles for BPVs in support of

tactical manned aircraftA77-47334

Operational concept for a battlefield surveillanceBPV system /Canadair CL-227/

A77-47335BPV applications of Tomahawk cruise missile

A77-47336Tactical expendable drone system /TEDS/

A77-47337The development of the IHQH-105 Aguila mini-BPVsystem

A77-47338O.S./F.B.G. advanced tactical BPV requirements as

analyzed by Boeing and DornierA77-47339

Selection of optimum BPV operational launch andrecovery techniques

A77-47340Tethered hover flight tests of a vertical attitude

takeoff and landing reiotely piloted vehicleA77-47341

The mini-BPV, cost effectiveness in a tacticalenvironment

A77-47342Synergistic growth of ITCS to a tactical BPV C2system Integrated Target Control System

A77-47343Development of an ultra—low-cost gas turbine

for BPV applicationsA77-473H4

Multiple Drone Control development for apv andelectronic warfare applications

A77-U7345An alternate recovery system for the Agnila

mini-BPV soft landingA77-47346

Development of a small, low cost turbojet enginewith thrust augmentation for BPV

A77-47347Hicrocompnter BPV stabilization and control system

A77-47348An evaluation of future BPV automatic navigation

systemsA77-47349

Advanced avionics for the Advanced BemotelyPiloted Vehicle /ABPV/

A77-47350A miniature rotary-wing BPV

A77-47351Bemote rate control for BPVs

A77-47352Ducted-fan VIOL BPV system

A77-47353

A-24

SUBJECT IIDBX SBPABATOBS

ABPV system/design trade study. Volume 4: Launchand recoveryCAD-A039591] H77-31116

BBSBABCH AID DEVBLOPBBITAdvanced turboprop technology development

CAIAA PAPEB 77-1223] A77-44324BASA/Bavy lift/cruise fan. Phase 1: Design summary[BASA-CB-135242] B77-31149

BBDSABLB LAQICB VEHICLESBPV applications of Tomahawk craise missile

A77-47336BIDII6 QDAUTT

Effects of control lavs and relaxed staticstability on vertical ride quality of flexibleaircraft

877-30128RIGID STBOCXUBES

A tryout of a rigid airship under tropicalconditions

A77-45460BUG SIBOCTDBBS

Botor buirst protection program: Expermentationto provide guidelines for the design of turbinerotor burst fragment containment rings[BASA-CB-135166] H77-30119

SOCKET BHGIBESSoviet aircraft and rockets[BASA-»T-F-770] H77-30065

Aircraft enginesB77-30068

BOCEET VESICLESSoviet aircraft and rockets[BASA-TT-F-770] H77-30065

BOLLInvestigation of flight dynamics daring roll[IPD-8/76] H77-31177

BOLLEB BEABIBGSTapered toller bearing development for aircraftturbine engines[AD-A041317] B77-31507

Advanced high speed roller bearing inspectiontechniques[AD-AO<|2121] B77-31529

BOLLII6 flOBBBTSEstimates of the effectiveness of automaticcontrol in alleviating wake vortex induced rollexcursions[BASA-TH-73267] B77-30129

BOTABI RIBG AIBCHAFTA miniature rotary-wing BPV

A77-S7351Briefs of accidents involving rotorcraft OSgeneral aviation, 1975CPB-267647/6] B77-31120

BOTABI RIIGSAn analysis of helicopter rotor response due togusts and turbulence

&77-44440Bain rotor Bake/tail rotor interaction

A77-44441On the static pressure in the wake of a hovering

rotorA77-44<W2

On the validity of lifting line concepts in rotoranalysis

V77-44444OBEBA aerodynamic research vork on helicopters[OBEBA, IP BO. 1977-42E] A77-44957

Sensor for measuring instantaneous angle of attackof helicopter bladesfHASA-CB-154808J H77-3044«

Hover evaluation of circulation control high speedrotor[AD-A040921] B77-31100

Acoustically swept rotor[BASA-CASB-ABC-11106-1] B77-31130

Single-rotor helicopter design and performanceestimation programs. Volume 1: Methodology[AD-A040803] B77-31138

BOTATIIS BODIESAn optical technigue for teasnring vibratory

motion in rotating machineryA77-47090

BOTOB 1EBOOTIAHICSon the validity of lifting line concepts in rotor

analysisA77-4444H

OBBBA aerodynamic research «ork on helicoptersA, If BO. 1977-42E] A77-4Q957

Comparison of dynamic stall phenomena for pitchingand vertical translation motions[HASA-CB-2793] B77-30088

Acoustically swept rotor(BASA-CASB-ABC-11106-1 ] B77-31130

BOTOB BLADESBover evaluation of circulation control high speed

rotor[AD-A040921] H77-31100

BOTOB BLADES ITOBBORACHIHEBT)Vibration analysis of rotor blades with an

attached concentrated mass[BASA-CB-154987] B77-31537

BOTOB LIFTOn the validity of lifting line concepts in rotor

analysis&77-44H44

BOTOBSBotor burst protection program: Experimentation

to provide guidelines for the design of turbinerotor burst fragment containment ringsCBASA-CB-135166] B77-30119

BDBIATSBunway utilization coefficients based on wind

velocity and direction dependence onlyA77-47950

BOBAL ABEASInteractions of technology and society: Impacts

of improved airtransport. A study of airportsat the grass roots in rural communitiesCBASA-CB-2871 ] B77-31005

SiPEIT FACTOB5OS air carrier accidents involving fire, 1965

through 1974 and factors affecting the statisticsCPB-266883/8] B77-31112

SAFETY HABASBBBITDesign and evaluation methods for optimizing

ejection seat cushions-for comfort and safety[AD-A036035] B77-31110

Safety (aviation material)CAD-A041021] B77-311-I1

SABDIICH STRUCTURESAircraft interior sandwich panel development

A77-47625SATBLLITE-BOB8B liSTBOBEHTS

Space experiment simulation using an aircraftlaboratory

i77-47200SCALE HODELS

A comparison of the results of dynamic wind-tunneltests with theoretical predictions for anaeromechanical gust-alleviation system for lightairplanesCHASA-TH-D-8521] B77-31072

A SO advanced program research inlet data analysisreport for 1/5.2-scale model inlet testsCAD-A040707] B77-31108

SEAPLABESSeakeeping characteristics of a preliminary design

for a sea loiter aircraft[AD-A040062] B77-30113

SEPABATED FLO!Investigations of three-dimensional flow

separation on fuselage configurations[AD-A039382] B77-30421

Unsteady Airloads in Separated and Transonic Flow[AGABD-CP-226] 877-31073

Unsteady airloads in separated and transonic flowB77-31074

Separated-flow unsteady pressures and forces onelastically responding structures

B77-31075Evaluation of vibration levels at the pilot seat

caused by wing flow separationH77-31078

Airframe response to separated flow on the shorthaul aircraft VP9 614

B77-31081SEPABATOBS

A rotating high pressure water condenser andseparator for aircraft environnental controlsystem[ASHB PAPBH 77-EBAS-10] A77-46851

A-25

SERVICE LIFE SUBJECT IIDBX

SERVICE LIFERays of increasing the resources /potential lives/

of gas tarbine enginesA77-47472

SEBVOCOBTBOLA failure effects simulation of a low authority

flight control augmentation system on a UH-1Hhelicopter[ffASA-TH-73258] H77-31174

SHADOBGBftPB PBOTOGBAPBYAn electro-optic airspeed sensor airborneoptical convolution velocimeter

A77-44783SHIPS

AB/PRC-56 helmet radio set upgrading. Becoamendedmodifications require minimal resources butpromise considerable improvement in reliabilityoperability, and logistics support[4D-A041190] H77-31368

SHOCK HAVE PBOPAGJTIOHCalculation of the aerodynamic characteristics of

a wing moving at subsonic speed, in the case ofa weak shock-wave effect on the wing

A77-47667SHOCK HAVES

Efficient solution of unsteady transonic flowsabout airfoils

N77-31087SHOBT HAUL AIBCBAFT

Application of powered lift and mechanical flapconcepts for civil short-haul transport aircraftdesign[AIAA PAPEB 77-1237] A77-44330

Experience gained in adjusting the mathematicalmodel of the VFR 614 short-haul aircraft by useof measured eigenfreguencies

A77-45391Airframe response to separated flow on the short

haul aircraft VFH 614( H77-31081

Advanced turboprop technology development[HASA-TH-73729] H77-31155

SHOBT TAKEOFF AIBCBAFTOTH noise correlation for several nozzle/wing

geometries using a 5:1 slot nozzle with externaldeflectors Over The Sing configurations

A77-44461Development of an integrated configuration

management/flight director system for pilotedSTOL approaches[HASA-CB-2883] H77-30132

An in-flight simulation of approach and landing ofa STOL transport with adverse ground effect[BASA-CB-154875] N77-31133

ABPV system/design trade study. Volume 4: Launchand recovery[AD-A039591] H77-31146

SIIGDLAB IHTEGBAL EQDATIOHSGeneralized Theodorsen solution for singular

integral equations of the airfoil classA77-44946

SKIDDIHGStudies of friction and wear characteristics ofvarious wires for wire-brush skids[HASA-TB-D-8517] H77-31134

SKID (STBOCTOBAL HEBBEB)Design and fabrication of graphite-epoxy bolted

wing skin splice specimens[BASA-CB-145216] H77-30180

A study of the charge and current induced on anaircraft in an EHP simulator facility. Part 1;The formulation. Part 2: The singularityexpansion method. Part 3: The numerical resultsCAD-A039507] B77-31384

SLEHDBB BODIESThe flow about a slender propeller-driven body in

a temperature stratified fluidrAD-AO»0847] B77-31099

SLEBDEB flIGSSystematic pressure distribution and forcemeasurements of two yawed slender wings[IFD-2/76/1] H77-30095

A method for calculating flow around a yawedslender wing at small angle of attack[IFD-4/76] - H77-30096

Bonplanar wing load-line and slender wing theory[BASA-CB-2864] B77-31094

SHALL PEBTOBBAIIOB FLO!Application of finite element approach totransonic flow problems

A77-47539Analysis of transonic flow over lifting and

oscillating airfoilsA77-47542

SOCIAL FACTORSInteractions of technology and society: Impacts

of improved airtransport. A study of airportsat the grass roots in rural communities[BASA-CB-2871] B77-31005

SOFT LABDIBGAn alternate recovery system for the Agnila

mini-BPV soft landingA77-47346

SOLIDIFICATIOHThermal stability of transition metal monocarbide

fibers in refractory composites prepared byunidirectional solidification[OBBBA, IP BO. 1977-62] A77-47136

SODBD PBBSSOBEOptimum acoustic design of free-running low speed

propellers[ A I A A PAPEB 77-1248] A77-44337

SODID iAVESAcoustically swept rotor

C BASA-CASE-iBC-11106-1] H77-31130SPACE BA7IGATIOB

An overview of Viking navigationA77-44427

SPACE SOBVEILLABCE (SPACBBOBRE)Hicrowave holographic imaging of aircraft withspaceborne illuminating source

B77-30439SPACECBAFT TEAJECTOBIES

An overview of Viking navigationA77-44427

SPEED IIDICATOBSAn electro-optic airspeed sensor airborneoptical convolution velocimeter

A77-44783Development of prototype optical convolution

airspeed sensor[AD-A039469] H77-30116

STABILITY AUGSBBTATIO8Active control technology aircraft design

A77-45524STABILIZBBS (AGBBTS)

Composite horizontal stabilizer for the B-1 -Design, fabrication and test

A77-46519STAIBLBSS STEELS

Composite tanks for aerospace vehicle applicationA77-«6516

STAHDABDIZATIOiA study of standardization methods for digital

guidance and control systems(AGABD-AB-90J H77-30136

STATIC BLECTBICITIStatic electricity in aviation and ways ofaverting its effects

A77-46349STATIC PBESSOBB

On the static pressure in the wake of a hoveringrotor

A77-44442STATIC STABILITY

A new concept of static stability and its flighttesting in supersonic flight

A77-44815STATIC TESTS

aacroscopic study of time unsteady noise of anaircraft engine during static tests

A77-44453STATISTICAL AIALISIS

Statistical analysis of US Navy major aircraftaccident rates, pilot and aircrafttime-dependent variables[AD-A040096] H77-30099

OS air carrier accidents involving fire, 1965.through 1974 and factors affecting the statistics[PB-266883/8J 871-31112

STBADT FLOBApplication of finite element method for the

solution of transonic flowA77-47540

A-26

SUBJECT IBDBI SOBFACE BAVIGATIOH

StBELSBeasnrements of buffeting on tvo 65 deg delta

Kings of different latecialsS77-31079

STEBBOSCOPTStereographic projections in aic traffic control

systemsA77-46262

StOCBASTIC PROCESSESLinear regulator design for stochastic systems by

a multiple time scales Bet hod mthapplication to f-8 aircraft longitadinal control

477-46621STBAPDOBB IBBBTIAI G0IBAICB

An evaluation of future BPV automatic navigationsystems

A77-H7349Simulation of inertial inputs to a strapdovnplatfon for inertial great circle trajectories[SAHD-76-0620] H77-30104

STBATIPIED PlOiThe flow about a slender propeller-driven body in

a temperature stratified fluid[AD-A0408B7] H77-31099

STRESS AIALISISThe 3-D stress analysis of a turbine blades[AD-A039176] H77-30481

STBOCTOBAL DESIGBOptiaum acoustic design of free-running lov speed

propellers[AIAA PAPEB 77-12483 A77-4II337

Advanced Technology Ring /ATI/ selection and design[AIAA PAPBB 77-1210] A77-45505

Composite horizontal stabilizer for the B-1 -Design, fabrication and test

A77-46519STBDCTOBAL DES1SI CBITBBIA

Propeller study. Part 1: Introduction and overview[HiSA-CB-155002] H77-31156

STBOCTOBAL FAILOBBFatigne problems in service - Aircraft structures

A77-47503STBOCTOBAL HEIGHT

Innovative Aircraft Design Study (IADS) task 2,volume 1[AD-A041234] N77-31141

SOBCBITICAL PLOBIterative calculation of flow past a thick

cambered wing near the gronnd[ABC-CP-1370] HTJ-31104

Iterative design technignes for thick camberedwings in snbcritical flow[AHC-CP-1371] H77-31105

SOBSOIIC AIBCiAPTThe measurement of performance, stability andcontrol characteristics of a high subsonic jetaircraft in non-steady flight conditionsemploying high accuracy instrunentation techniques

A77-45525SOBSOIIC PLOi

Application of the finite element technigaecombined with toe collocation method to subsoniclifting surface problems

A77-47537Calculation of the aerodynamic characteristics of

a King moving at subsonic speed, ID the case ofa weak shock-wave effect on the wing

A77-17667SOBSOHIC FltJTTEB

Leading-edge vortex effect on the flatter speedA77-44819

Hind tunnel experiments on an actively controlled,variable geometry flutter model[AD-A039216] H77-30134

SOBSOIIC SPEEDEffect of an integrated scramjet installation on

the snbscnic performance of an aircraft designedto Bach 6 cruise[AIAA PAPEB 77-1230] A77-ni|326

The dynamic response of wings in torsion at highsubsonic speeds

H77-31077SOBSOIIC BUD TDBBELS

Coherence and phase techniques applied to noisediagnosis is the RASA Ames 7 times 10-foot windtunnel no. 1[BASA-CB-152039) H77-30905

SOPERCHABGBBSParametric performance evaluation of a jet enginederived from a turbocharger[AD-A039116] H77-30126

SOPEBCBITICAL FLOIA practical framework for the evaluation ofoscillatory aerodynamic loading on wings insupercritical flow

H77-31089SOPEBCBITICAL PBESSOBES

Onsteady airloads on an oscillating supercriticalairfoil

H77-31085SOPBflCBITICAL KISSS

Advanced Technology Ring /ATI/ selection and design[AIAA PAPEB 77-1210] A77-45505

SOPBBHIGB FBBQOBBCIBSKa-band integrated circuit receiver front end

module for BPVA77-07354

SOPBBSOBIC iiaCBAFTThe Hirage-2000

A77-U6975SOPBBSOBIC ilEPOILS

Experimental investigation concerning thereduction of wave drag of pointed symmetricalvings of equal volume with subsonic leading edgeand bell-shaped planform for different thicknessdistributions in the spansise and chordvisedirections[D1B-FB-75-62] H77-30087

SOPEBSOIIC COHBOSIIOHStreamtabe analysis of a hydrogen-burning scramjet

exhaust and simulation techniqueA77-it«817

SDPEBSORIC COHBOSIIOH BABJET EHGIHESEffect of an integrated scramjet installation on

the subsonic performance of an aircraft designedto Bach 6 cruise[ A I A A PAPBB 77-1230] A77-44326

SOPBBSOIIC COHSEBCIAL AIB TBAHSPOBT»ind tunnel results of a 10-percent scale powered

SCAT VIOL aircraft[AD-A040313J H77-31109

SOPBBSOBIC DBASExperimental investigation concerning the

reduction of wave drag of pointed symmetricalwings of equal volume with subsonic leading edgeand bell-shaped planform for different thicknessdistributions in the spanvise and chordvisedirections[DLB-PB-75-62] H77-30087

SOPBBSOIIC FLIGHTA nev concept of static stability and its flight

testing in supersonic flightA77-44815

SOPEBSOIIC FLOIApplicability of axisyometric analysis in

predicting supersonic flow through annularcascades[ASBE PAPBB 76-PiB-B] A77-4U30.H

The theoretical determination of the base pressurein supersonic flow

A77-45388SOPBBSOIIC FLOTTBB

Pan supersonic flatter: Prediction and testanalysis[ABC-S/B-3789] H77-31163

SOPBBSOIIC ISLETSASD advanced program research inlet data analysis

report for 1/5.2-scale model inlet tests[AD-A040707] S77-31108

SOPBBSOIIC TBABSPOBTSThe arrow wing - Its potentialities and drawbacks

vith regard to in-flight aerodynamic researchA77-U6606

SOBFACB PI1ISBIIGProcess development for fabricating sculptured

decorative interior aircraft panels using sheetmolding compounds

A77-46508Surface finishing of metal airfoils by

adhesive bonding[HASA-CASB-BSC-12631-2] H77-31131

SOBFACB BA7IGATIOIPosition finding using distance measurements

in hyperbolic navigationA77-011570

i-27

SOBVEILLABCE SUBJECT IBDBI

A special-purpose pocket calculator for aviationand maritime navigation

A77-44571SOBVBILLARCE

Complementary roles for BPVs in support oftactical Banned aircraft

A77-47334Operational concept for a battlefield surveillance

BPV system /Canadair CL-227/477-117335

The development of the XBQB-105 Aquila mini-BFVsystem

A77-47338SfBFT BIHGS

Analysis/theory of controlled configured structures[AIAA PAEEB 77-1212] A77-44316

Binq design by numerical optimization[ A I A A PSEEB 77-12*71 A77-44336

Wind tunnel experiments on an actively controlled,variable geometry flutter model[AD-A039216] B77-30134

A vind-tunnel investigation of the effects of flapspan and deflection angle, winq planform and abody on the high-lift performance of a 28 degswept wing[ABC-CP-13721 B77-31106

Acoustically swept rotorf HASA-CiSE-lRC-11106-1] H77-31130

SBEPIBACK ilBGSApplication of the finite element technique

combined vith the collocation oethod to subsoniclifting surface problems

A77-47537SIBBETBICAL BODIES

Numerical solution of the conically symmetricBavier-Stokes equations for hypersonic flow atangle of attack

H77-30079STHTHBTIC FDBLS

The potential role of technological modificationsand alternative fuels in alleviating Air Forceenergy problems[AD-A039597] H77-30261

An evaluation of very large airplanes andalternative fuels[AD-A040E32] H77-31334

SISTER EFFECTIVEBESSEstimates of the effectiveness of automatic

control in alleviating wake vortex induced rollexcursions[HASA-TB-73267] N77-30129

CB-U7 medium lift helicopter effectivenessevaluation program run book[AD-A041462] H77-31142

SYSTEB FAILOBESControl of rare events by Aircraft system design

regulation - Impact op operations[AIAA PAPEB 77-1258] A77-45511

A failure effects simulation of a low authorityflight control augmentation system on a OH-1Hhelicopter[BASA-TB-73258] B77-31174

STSTEBS ABALTSISA digital data acquisition and reduction system

for flight testing general aviation aircraftCtlAA PAEEB 77-1216] A77-44318

ASDAB (aircraft to satellite data relay) flighttest report[BASA-TB-73744] B77-31355

T-63 BBGIBECharacteristic time emissions correlations - The

1-63 helicopter gas turbine conbnstorA77-4U824

TACTHB DISCBIBIBiTIOBBenote rate control for BPVs

A77-47352TAIL ASSEHBLIBS

Tail response to propeller flow on a transportairplane

H77-31082TAKEOFF

Calculation of side line noise levels during takeoff[AD-AO<!062<»] H77-31170

TARGET ACQOISITIOHoperational concept for a battlefield surveillance

BPV system /Canadair CL-227/A77-47335

BPV applications of Tomahawk cruise missileA77-47336

Tactical expendable drone system /TEDS/A77-U.7337

Synergistic growth of ITCS to a tactical BPV C2system Integrated Target Control System

A77-47343Automatic target hand-off using correlation

techniquestAD-A036«35] H77-30115

TECBBOLOGICAL FOBBCASTIBG(Effects of technology level on v/STOL aircraft

JAIAA PAPEB 7t1^38) A77-05501TECHIOLOGI &SSBSSBEBT

Characteristics of fighter aircraftC A I A A PAPER 77-1219] A77-a»32i

Advanced turboprop technology development[AIAA PAPEB 77-1223] A77-H4324

Honaxisymmetric nozzle technology program - Anoverview for fighter aircraft engines[AIAA PAPEB 77-1225] A77-44325

Effects of technology level on V/STOL aircraft[AIAA PAPEB 77-1238] A77-B5501

The timing of technology - Commercial transportaircraft[AIAA PAPEB 77-1200] A77-45503

Active control technology aircraft designA77-H5524

An American Omega navigation evaluation programme- 1975-1977

A77-47815Interactions of technology and society: Impacts

of improved airtransport. A study of airportsat the grass roots in rural communities[BASA-CB-2871] H77-31005

Advanced turboprop technology development[HASA-TB-73729] N77-31155

TECHROLOGX UTILIZATIONTechnology comes to general aviation

military/commercial/ transport technologytransfer by N A S A

A77-«»959TELEVISIOB EQDIPBBBT

General principles of automatic TV trackersfor fire control and missile tracking

A77-HB812TELEVISIOM SISTEBS

United*s experience with'computer generated visualsystems, April 1977 for aircraft cockpits

A77-»«431TEBPBBATOBB EFFECTS

Effects of temperature transients at fan inlet ofa turbofan engine[BASA-TP-1031 ] N77-31153

TEHPBBATOBE SBADIEBTSThe flow about a slender propeller-driven body in

a temperature stratified fluid[AD-A040847] B77-31099

Effects of temperature transients at fan inlet ofa turbofan engine[BASA-TP-1031] B77-31153

TEBBIBAL COIFIG9BED VEHICLE PBOGBABA description of the software analysis from flight

and simulation data of the course cut limiter inthe TCV b-737 area navigation computer[BASA-IB-7U061] B77-31125

TEBBIBAL GOIDABCEA description of the software analysis from flight

and simulation data of the course cut limiter inthe TCV b-737 area navigation computer[BASA-TB-74061] B77-31125

TEBRAI8 ASAIISISThe effect of terrain near airports on significant

low level wind shear[AIAA EAPE8 77-1242] A77-44334

TEST FACILITIESOperational reliability and reliability testing

BookA77-45173

TEST VEHICLBSAn investigation of the near-field wake behind a

full-scale test aircraftA77-44816

A-28

SUBJECT HDBI TBABSPOBT AIBCBAPT

TBTBEBIB6Tethered hover flight tests of a vertical attitudetakeoff and landing remotely piloted vehicle

A77-I173141TBEBBAL CICIIBS TESTS

Thermal stability of transition metal •onocarbldefibers in refractory composites prepared byunidirectional solidification[OHEBA, TP HO. 1977-62) A77-Q7136

TBEBBAL STABIIITITheraal stability of transition metal monocarbidefibers in refractory coaposites prepared byunidirectional solidificationrOHBBA, TP SO. 1977-62] A77-47136

TBIB AIBPOILSBixed finite element aodels and dual iterative•ethods for transonic flov

A77-47543TBIB PILBS

Kn-band integrated circuit receiver front endlodnle for BP7

A77-47354TBBEE DIHBHSIOHAL E101

Investigations of three-dimensional flovseparation on fuselage configurationsCAD-A0393821 B77-30421

The calculation of flov fields about threedimensional bodies in high altitude(free-molecular flov of neutral atoms)[DLB-PB-75-45;] H77-30922

THBOSTPropeller study. Part 3: Experimental

determination of thrust and torgne on the YO-34aircraft[BASA-CB-155003] H77-31158

TBBOST AOGBEBtATIOBThrust augmenting ejector technology for Navy

aircraft[AIAA EASES 77-1239] A77-4H331

Increasing jet-engine thrust by Hater-augmentationA77-16984

Development of a snail, low cost turbojet enginevith thrust augmentation for BPV

A77-47347TILT fflBG AIBCBAFT

An improved free «ing for an aircraft[BASA-CASE-PBC-10092-1] B77-31135

TIHB DEPESDEHCBStatistical analysis of OS Havy major aircraft

accident rates, pilot and aircrafttime-dependent variables[AD-A040096] B77-30099

TIBB OPTIBAL COiTBOLComputational methods to obtain time optimal jetengine control

A77-46614Characteristics of the boundary-layer equations of

the minimum time-to-climb problemA77-46618

TIBB SI6BALSVLF pulse timing - Limitations and potential as a

companion to OmegaA77-44039

XTTABIOBA-7 titanium nose gear development

A77-46801tOBQOB

Propeller study, part 3: Experimentaldetermination of thrust and torgne on the TO-3AaircraftfBASA-CB-155003] 1177-31158

tOBSIOIThe dynamic response of vings in torsion at high

subsonic speedsH77-31077

tOIICITY AID SAPETI BAXABDAircraft interior sandvich panel development

A77-47625IBAIBIIG AIBCBAPT

Flight test of an 8000 psi Lightweight HydraulicSystem (IBS)[AD-A039717] B77-30120

TBftlBIBG SIBOLATOBSScanned laser visual system for military

flight simulationA77-44814

TBAJECTOBI ABALXSISSimulation of inertial inputs to a strapdovn

platform for inertial great circle trajectoriestSAHD-76-0620] H77-30104

TBAJECTOBI COBTBOLAn overviev of Viking navigation

A77-44427TBAJECTOBY OPTIBIZATIOB

Bnierical modeling of helicopter pilotingA77-46348

Becognition criterion and production of easilysolvable models for flight mechanicaloptimization problems[IFD-9/76] 877-31178

TB1BSPOBBEBSDevelopment of lightweight transformers for

airborne high power suppliesMD-A041515] H77-31162

TBABSIEBT BBATIHGThe effect of boundary layer changes due to

transient heat transfer on the performance of anaxial-flov air compressor[SAE PAPEB 770284] A77-44565

TBABSITIOB BETALSThermal stability of transition metal monocarbide

fibers in refractory composites prepared byunidirectional solidificationCOBEBA, If HO. 1977-62] A77-47136

TBABSBISSOBETEBSVisual range: Concepts, instrumentaldetermination, and aviation applications[BBS-BOHO-159] H77-30102

TBABSBITTEB BECBI7BBSAB/PBC-56 helmet radio set upgrading. Recommendedmodifications require minimal resources butpromise considerable improvement in reliabilityoperability, and logistics support[AD-A041190] H77-31368

TBABSOBIC PLIGHTA brief overviev of transonic flutter problems

H77-31084TBAHSOHIC PLOR

Application of finite element approach totransonic flov problems

A77-«7539Application of finite element method for the

solution of transonic flovA77-07540

Analysis of transonic flov over lifting andoscillating airfoils

A77-U7512Bixed finite element models and dual iterative

methods for transonic flovA77-U7513

Transonic flov simulation by the finite elementmethod via optimal control

A77-<t75«UStudy of design and analysis methods for transonic

flovCHASA-CH-152041] S77-30086

A method for calculating flov around a yavedslender ving at small angle of attack[IPD-4/76] H77-30096

Unsteady Airloads in Separated and Transonic Plov[AGABD-CP-226] H77-31073

Unsteady airloads in separated and transonic flovH77-31074

Efficient solution of unsteady transonic flovsabout airfoils

H77-31087Application of a finite difference method to the

analysis of transonic flov over oscillatingairfoils and vings

N77-31090TBASSOSIC FLOTTEB

A brief overviev of transonic flutter problemsH77-31084

TBABSOBIC HIBD TDBBBLSExperiment and analysis on the flov process

dynamics of the RASA-Langley eight foottransonic pressure tunnel[HASA-CB-154806] B77-30085

TBABSPOBT AIBCBAPTParametric study of advanced long range

military/commercial cargo transports[AIAA PAPBB 77-1221] A77-44322

Advanced turboprop technology development[AIAA PAPEB 77-1223] A77-44324

A-29

TBABSPOBT PBOPEBTIES SUBJECT IHDEI

Air transport noise reduction477-44550

Preliminary desiqn and analysis of advancedmilitary transportsfAIAA PAPEB 77-1221] ' A77-45502

The timing of technology - Commercial transportaircraftfAIAA PAPEH 77-1200] A77-15503

The aircraft gas turbine - Status and prospectsA77-46403

Airframe response to separated flow on the shorthaul aircraft VFW 611

N77-31081Tail response to propeller flow on a transport

airplaneH77-31082

Briefs of accidents involving turbine poweredaircraft, DS general aviation, 1975fPB-267646/8] N77-31121

Innovative Aircraft Design Study (IADS) task 2,volume 1rAD-A01123l(] N77-31141

Advanced turboprop technology developaentrniSA-TB-73729] N77-31155

TBAHSPOBT PBOPBBTIESMultistage axial-flow turbomachinery wake

production, transport, and interaction[AD-A041108] H77-31173

TBIGOBOSETBIC FOHCTIOSSA simple closed-form solution of a position-fixing

problemTAD-A039303] K77-31127

TBOPICAl BEGIONSA tryout of a rigid airship under tropical

conditionsA77-45460

TDBBISE ELIDESThe 3-D stress analysis of a turbine blades

[AD-A039176] H77-30181Advanced cooled turbine airfoil aerodynamicinvestigationrAD-A041137] N77-31161

TOBBIBE ENGINESComposite hubs for low cost turbine enginesstress analysis using NASTBAN

477-46520TDEBINE EIBADST IOZZLES

Effects of forward velocity on noise for a J85turbojet engine with multitube suppressor fromwind tunnel and flight tests

A77-44460TOHBINE 1BEELS

An analysis of helicopter rotor response due togusts and turbulence

A77-44440Botor burst protection program: Experimentation

to provide guidelines for the design of turbinerotor burst fragment containment ringsCNASA-CB-135166J N77-30119

TOBBIBESAn experimental investigation of a snbscale

variable pressure ratio high thru flow turbine[AD-A039823L] N77-30121

Tapered roller bearing development for aircraftturbine enginesfAD-A041317] N77-31507

TOEBOCOHPBESSOBSStall margin improvement by casing treatment - Its

mechanism and effectiveness in axial flowcompressorsfASHE P4FEB 76-GT-A] 477-44345

The effect of boundary layer changes due totransient heat transfer on the performance of anaxial-flow air compressor[SAE PAPEB 770281] A77-44565

A rotating high pressure water condenser andseparator for aircraft environmental controlsystemF4SBE PAPEF 77-EHAS-10] A77-46851

Multistage axial-flow turbomachinery wakeproduction, transport, and interaction[AD-A011108] N77-31173

TtJBBOFAN EHSJHESMacroscopic study of time unsteady noise of an

aircraft engine during static tests477-44453

Simulation of flight-type engine fan noise in theNASA-Lewis 9 x 15 anechoic wind tunnel

A77-44456

Core noise source diagnostics on a turbofan engineusing correlation and coherence techniques

A77-44457Plight effects on exhaust noise for turbojet and

turbofan engines - Comparison of experimentaldata with prediction

A77-44462Effects of temperature transients at fan inlet of

a tnrbofan engine[NASA-TP-1031 ] H77-31153

Development and verification of real-time, hybridcomputer simulation of F100-PH-100 (3) turbofanenginetNASA-IP-1034] H77-31154

Numerical analyses of soft body impacts on rigidand defomable targets[&D-A040030 ] N77-31168

NAPTC Facility modifications required for altitudetesting of current V/STOL engineCAD-A041608] N77-31184

TOBBOFAHSPan supersonic flutter: Prediction and test

analysisCABC-B/H-3789] H77-31163

TDBBOJET ENGINESFlight effects on exhaust noise for turbojet and

turbofan engines - comparison of experimentaldata with prediction

A77-44462Development of an ultra-low-cost gas turbine

for BP7 applications477-47344

Development of a small, low cost turbojet enginewith thrust augmentation for RPV

A77-47317Briefs of accidents involving turbine powered

aircraft, OS general aviation, 1975fPB-267646/8] S77-31121

Development of a catalytic combustor for aircraftgas turbine enginesCAD-A040135] H77-31171

TOBBOBACHINBBYVariable geometry air cycle machine for

aircraft environmental control turbomachinesC A S H E PAPEB 77-ENAS-7] A77-46818

TOBBOPBOP AIBCBAPTAdvanced turboprop technology development

[AIAA PAPBE 77-1223] A77-44324Advanced turboprop technology development

[NASA-TH-73729] 1177-31155TOBBOLEHCE EFFECTS

An analysis of helicopter rotor response due togusts and turbulence

477-44440Upstream influence on the near field of a planeturbulent jet

A77-47005T0BBOLERT FLOi

The flow about a slender propeller-driven body ina temperature stratified fluid[AD-A040847] H77-31099

TDBBOLEiT JETSDpstream influence on the near field of a plane

turbulent jetA77-47005

Aerodynamics of a confined jet with variable densityA77-47248

A method for determining the point of lift-off andmodified trajectory of a ground-based heatedturbulent planar jet in a co-flowing wind[AD-A040704] N77-31722

TDBHIIG FLIGHTnonlinear lifting-surface theory for yawed and

banked wings in ground proiimty477-45387

TWO DIBEHSIOHAt FLOfGeneralized Theodorsen solution for singular

integral equations of the airfoil class477-44946

The theoretical determination of the base pressurein supersonic flow

A77-45388TIO DIBEHSIONAL JETS

Opstrean influence on the near field of a planeturbulent jet

A77-47005

4-30

SUBJECT IBDEI TOBTICBS

O.S.S.E.Soviet aircraft and rockets

[HASA-TT-F-770] H77-30065IB Herculean flight Soviet aviation history

H77-30066Aircraft Soviet technology

H77-30067Aircraft engines

H77-30068OB-1 BBLICOP1EB

A failure effects simulation of a lov authorityflight control augmentation system on a OH-1Hhelicopter[BASA-TB-73258] B77-31174

A mathematical force and oonent model of a UH-1Hhelicopter for flight dynamos simulationstHASA-TB-73254] H77-31175

ULTBiSOBIC TESTSUltrasonic detection of fatigue damage in aircraft

components[AD-A040009] H77-31516

UBITED STATES OF iHBBICiBriefs of accidents involving alcohol as acause/factor, US general aviation, 1975[PB-267619/2] H77-31118

Briefs of accidents involving tnrbine poweredaircraft, OS general aviation, 1975fPB-267646/8] B77-31121

Briefs of accidents involving midair collisions,US general aviation, 1975CPB-267645/0] H77-31122

Listings of accidents/incidents by aircraft makeand model, US civil aviation, 1975[PB-267641/3] B77-31123

UBSTBADY PIOISeparated-flov unsteady pressures and forces onelastically responding structures

H77-31075Efficient solution of unsteady transonic flowsabout airfoils

H77-31087UPSIBEAH

Upstream influence on the near field of a planeturbulent jet

A77-47005OSES HAHDALS (COBPUTBE PBOGBAHS)

Rave drag reduction for aircraft fuselage-wingconfigurations. Volume 2: flanual for computerprogramsfAD-AO<10998] H77-32013

USES BEQOIBBHBITSU.S./F.H.G. advanced tactical BPV reguirenents as

analyzed by Boeing and DormerA77-47339

V/STOI AIBCBAFTThrust augmenting ejector technology for Havy

aircraft[AIAA PAPBB 77-1239] A77-44331

Effects of technology level on 7/STOL aircraft[AIAA PAPBB 77-1238] A77-45501

A laboratory investigation into flight pathperturbations during steep descents of V/STOLaircraft[AD-A040101] H77-30135

A mathematical force and moment model of a OB-IBhelicopter for flight dynamcs simulationsCHASi-TS-73251] H77-31175

BAPTC Facility modifications regnired for altitudetesting of current V/STOL enginetAD-A041608] H77-31184

TABIABLE 6EOBEIBI SIBOCTUBBSFJ. utter-suppression studies on an actively

controlled variable-geometry wind-tunnel modelA77-46805

Variable geometry air cycle machine foraircraft environmental control tnrbomachines[ASBE PAPEB 77-EHAS-7] A77-46848

VABIAIIOIiL PBIBCIPLESApplication of finite element approach to

transonic flow problemsA77-17539

Application of finite element method for thesolution of transonic flow

A77-47540TELOCITY BEASU1BHEHT

Development of prototype optical convolutionairspeed sensor[AD-A039469] 877-30116

Laser velocimeter utilization in jet enginealtitude test cells[AD-A041019] H77-31477

VEBTICAL LiBDIBGTethered hover flight tests of a vertical attitude

takeoff and landing remotely piloted vehicle477-17341

An alternate recovery system for the Aquila ---mini-BPV soft landing

A77-47346Dncted-fau VIOL BPV system

A77-47353VEBTICAL TAKEOFF

Tethered hover flight tests of a vertical attitudetakeoff and landing remotely -piloted vehicle

A77-B7341Ducted-fan VIOL BPV system

A77-47353VERTICAL TAKEOFF AIBCBAFT

find tunnel results of a 10-percent scale poweredSCAT VIOL aircraft[AD-A0110313] H77-31109

Flight control testing of the VAK-191B aircraft[AD-A040535] N77-31137

VBBI LOB FBBQDBBCIBSVLF pulse timing - Limitations and potential as a

companion to OmegaA77-I4H439

VHF OIHIBANGB BAVIGATIOBA digital goniometer for VOB

A77-46263Bonte Carlo simulations of VOB/DBE holding

procedures. Basic ideas and applications[DLB-FB-77-08] H77-30105

7IBBATIOHEvaluation of vibration levels at the pilot seat

caused by wing flow separationH77-31078

Tail response to propeller flow on a transportairplane

B77-31082VIBEATIOB DABPIR6

Flutter-suppression studies on an activelycontrolled variable-geometry wind-tunnel model

A77-46805VIBBATIOH HEiSDREHEBT

An optical technique for measuring vibratorymotion in rotating machinery

A77-47090VIBSATIOB TESTS

Operational reliability and reliability testing--- Book

A77-45173VIBBATOBT LOADS

Vibration analysis of rotor blades with anattached concentrated mass[BASA-CB-154987] B77-31537

VIDEO DATASpace experiment simulation using an aircraft

laboratoryA77-47200

VIKIHG 1 SPACECB&FTAn overview of Viking navigation

A77-41427VISUAL FLIGHT

Navigation checkpointing using horizon correlation[AD-A039946] B77-30103

VISUAL SIGIALSAltitude warning signal system evaluation

[AD-A039365] B77-311U7WOBTBX STBEBTS

Bearrangement of vortex structures in the wakebehind a body and in a jet

A77-47674VOBTICES

On the validity of lifting line concepts in rotoranalysis

Leading-edge vortex effect on the flutter speedA77-4U819

A-31

VOBTICITY. SUBJECT IBDEX

Configuration of free vortices trailing off a wingof finite span

A77-47669Estimates of the effectiveness of automaticcontrol in alleviating vake vortex induced rollexcursions[HASA-TH-73267] N77-30129

Flutter calculation for the Viggen aircraft withallowance for leading edge vortex effect

B77-31083Vortex-lift roll-control device

rNASA-CASE-LAB-11868-2] H77-31176

VOHtlCITtAn investigation of the near-field vake behind a

full-scale test aircraftA77-44816

An attempt to correlate normal vorticities withtotal pressure distortion patterns at theentrance to a gas turbine engine(AD-A040370] N77-30122

wIAKBS

Bearrangenent of vortex structures in the vakebehind a body and in a jet.

A77-47674Multistage axial-flow tnrbomachinery wake

production, transport, and interaction[AD-A0411081 H77-31173

IABHIIG SYSTEBSDesign criteria for aircraft warning, caution and

advisory alertinq systemsP A I A A PAPER 77-12140] A77-<i4332

Altitude warning signal system evaluationFAD-1039365] H77-31147

BATESA rotating high pressure water condenser and

separator for aircraft environmental controlsystem[ASHE PAPEB 77-ENAS-10] A77-<|6851

iATEE IHJBCTIOHIncreasing jet-engine thrust by vater-augnentation

A77-46984BEAPOH SYSTEBS

F-18 blends advanced fighter conceptsA77-46575

D.S./F.H.G. advanced tactical BPV requirements asanalyzed by Boeing and Dormer

A77-47339Multiple Drone Control development for BPV andelectronic warfare applications

A77-47345An evaluation of future BPV automatic navigation

systemsA77-47349

Advanced avionics for the Advanced EemotelyPiloted Vehicle /ABPV/

A77-47350GATOB/AV-8A environnental captive flight vibration

response testsFAD-A036498] H77-30114

Safety (aviation material)tiD-AOl(1021l H77-31111

HEABStudies of friction and wear characteristics ofvarious wires for wire-brush skids[HASA-TH-D-8517] H77-31134

•BATBEBBriefs of fatal accidents involving weather as acause/factor, OS general aviation 1975,rPB-267648/4] H77-31119

•EIGHT BEDDCTIOHComposite tanks for aerospace vehicle application '

A77-46516BIDEBABD COBBOBICATIOB

Software uplementation of a PH spread spectrumreceiver to accommodate dynamics SBPpsendonoise communication link foraircraft/satellites

A77-44738BIBD BIBECTIOS

Bunway utilization coefficients based on windvelocity and direction dependence only

A77-U7950KBD SBEAB

The effect of terrain near airports on significantlow level wind shearC A I A A PAPEB 77-121123 A77-«u33i

ilHD T0HIEL APP4BATOSFlow characteristics in an expansion tunnel as

inferred from velocity measurementsA77-47108

BIBD TUHHEL BODBLSFlutter-suppression studies on an actively

controlled variable-geometry wind-tunnel modelA77-46805

find tunnel experiments on an actively controlled,variable geometry flutter model[AD-A039216] N77-30.134

HDD TBHIEL BOZZLBSFlow characteristics in an expansion tunnel as

inferred from velocity measurementsA77-47108

HID THBBEL TESISEffect of an integrated scramjet installation on

the subsonic performance of an aircraft designedto Bach 6 cruiseC A I A A PAPBB 77-1230] A77-44326

Simulation of flight-type engine fan noise in theNASA-Lewis 9 x 15 anechoic wind tunnel

A77-44456ONEBA aerodynamic research work on helicopters

[ONEBA. IP HO. 1977-42E] A77-44957Computers and wind tunnels - Complementary aids to

aircraft designA77-«7879

Aerodynamic data and off-design characteristics ofthe modified guasi-elliptical airfoil sectionHLB 7101[SLB-TB-76012-0] H77-3009H

A comparison of the results of dynamic wind-tunneltests with theoretical predictions for anaeronechanical gast-alleviation system for lightairplanes[HA SA-TH-D-85 21] H77-31072

A wind-tunnel investigation of the effects of flapspan and deflection angle, wing planform and abody on the high-lift performance of a 28 degswept wing[ABC-CP-1372] N77-31106

A SO advanced program research inlet data analysisreport for 1/5.2-scale model inlet tests[AD-A040707] H77-31108

Hind tunnel results of a 10-percent scale poweredSCAT VIOL aircraft[AD-A040313] H77-31109

RIBD VELOCITYBnnway utilization coefficients based on wind

velocity and direction1 dependence onlyA77-<(7950

KIHG FLAPSApplication of powered lift and mechanical flap

concepts foe civil short-haol transport aircraftdesign[ A I A A PAPEB 77-1237] A77-H4330

IIIG LOADIBSAnalysis/theory of controlled configured structures

[AIAA PAPEB 77-1212] A77-H4316Application of the finite elenent technigue

combined with the collocation method to subsoniclifting surface problems

A77-U7537Nonplanar wing load-line and slender wing theory

[HASA-CB-2864 ] 1177-31094SIBG OSCILUTIOBS

Dnsteady airloads on an oscillating supercriticalairfoil

877-31085(IBS PASELS

Comparative flutter calculations for the Tiggenaircraft

A77-44818Durability testing of the A-7D composite

outer-wing panelA77-06808

BIBS PLAIFOBBSA wind-tunnel investigation of the effects of flap

span and deflection angle, wing planform and abody on the high-lift perforaance of a 28 degswept wing[iBC-CP-1372] B77-31106

BIBG PBOFILESVing design by numerical optimization

[AlAA PAPEB 77-1247] A77-44336

»-32

SUBJECT IHDBI TC-14 AIBCBAFT

Experimental investigation concerning theredaction of nave drag of pointed symmetricalvings of egaal volume vith subsonic leading edgeand bell-shaped planform for different thicknessdistributions in the spanvise and chordvisedirectionsCDLB-FB-75-62] B77-30087

Perfonance prediction method for a ving-in-gronndeffect vehicle with bloving under the ving[AD-A039829] H77-30301

IIRB SPAIConfiguration of free vortices trailing off a ving

of finite span177-97669

•IIS TIP VOBTICBSBain rotor wake/tail rotor interaction

A77-44441HiGLETS

Honplanar ving load-line and slender ving theory[BASA-CB-2864] H77-31094

WIBGSBass flov reguirements for LFC ving design

laminar Flov Control[AIAA PAPEB 77-1222] A77-44323

Bonlinear lifting-surface theory for yawed andbanked vinqs in ground proximity

A77-45387Accelerated environmental conditioning of the A-7Dcomposite outer ving

A77-46838Calculation of the aerodynanic characteristics of

a ving coving at subsonic speed, in the case ofa veak shock-vave effect on the ving

A77-47667Sone guadratnre methods for lifting ving theory[IPD-5/76] H77-30097

Design and fabrication of graphite-epozy boltedving skin splice specinens[BASA-CB-145216] H77-30180

The dynamic response of vings in torsion at highsubsonic speeds

H77-31077Evaluation of vibration levels at the pilot seat

caused by ving flov separationH77-31078

A practical franevork for the evaluation ofoscillatory aerodynamic loading on vings insupercritical flov

H77-31089An improved free ving for an aircraft[HASA-CASE-FBC-10092-1] H77-31135

•IBBStudies of friction and vear characteristics ofvarious vires for vire-brush skids[HASA-TH-D-8517] H77-31134

WOBKLOADS (PSTCHOPHTSIOLOGT)BBAV vaypoint charting effects on pilot

procedures, training and vorkloadA77-44432

YTil

Bonlinear lifting-surface theory for yaved andbanked vings in ground proximity

A77-45387Systematic pressure distribution and force

measurements of tvo yaved slender vings[IFD-2/76/I] B77-30095

A method for calculating flov around a yavedslender ving at small angle of attack[IFD-V76] B77-30096

TC-14 AIBCEAFTPovered lift - Its impact on TC-14 materials and

structures[AIAA P A P E B 77-1231] A77-44327

Cast aluminum structures technology for TC-14airframesC A I A A PAPEB 77-1232] A77-44328

TC-14 flight test resultstAIAA PAPEB 77-1259] A77-45512

1-33

PERSONAL AUTHOR INDEXAERONAUTICAL ENGINEERING /A Special Bibliography (Suppl 90)

Typical Personal Author Index Listing

DECEMBER 1977

PERSONAL AUTHOR

BOBBOOS, C. I.Simulation of an automatically-controlled STOLaircraft in a microwave landing system multipathenvironmentfHASA-Ts-I-73151) H77-11063

I

TITLE

I

REPORTNUMBER

NASAACCESSION

NUMBER

LiSi,,.aj in this index are arranged alphabetically by personal author The titleof the document provides the user with a brief description of the subject matterThe report number helps to indicate the type of document cited (e g NASAreport translation NASA contractor report) The accession number is locatedbeneath and to the right of the title e g N77 11063 Under any one author sname the accession numbers are arranged m sequence with the IAA accessionnumbers appearing first

ABDELiABAB, B.Effects of temperature transients at fan inlet of

a turbofan enqinerNASA-TP-103n N77-31153

ADABS. B. J.B N A 7 vaypoint charting effects on pilot

procedures, training and workload477-14132

AKAY. B. 0.Application of finite element method for the

solution of transonic flowA77-175UO

ALRAHG, J. B.Enqine control stabilizing compensation-testing

and optimizationV77-11511

ABDEBSOH. B. A.Aircraft interior sandwich panel development

A77-17625ABDEBA, B. D.

Characteristics of the boundary-layer equations ofthe minimum time-to-climb problem

A77-16618ASHAHD, C.

ONEBA aerodynamic research work on helicopters[OHEBA, TP HO. 1977-12E] A77-11957

ABBSTBONG, G. C.Altitude varninq signal system evaluation

fAD-A0393651 N77-31117AB7IH, J. B.

An experimental investigation of a subscalevariable pressure ratio high thru flov turbineCAD-A039823L] H77-30121

ASCABI, L.Advanced conposites and advanced netallics meet

the challenge of design-to-costT A I A A PAPEB 77-1231J A77-U1329

ATEIISOI, J. S.. JB.A study of spectrum loading and range-pair

counting method effects on cumulative fatiguedamage[AD-A039651] H77-31105

ATTROOLL, V. I.Some mathematical aspects of air traffic systems

A77-17816A7AHESO7, 6. A.

Space experiment simulation using an aircraftlaboratory

A77-17200

BAEBST, C. F.Development of an ultra-low-cost gas turbine

A77-17310BALLBAOS, I. P.

Efficient solution of unsteady transonic flowsabout airfoils

N77-31087BABBEB. E. A.

Preliminary design and analysis of advancedmilitary transportsf A I A A PAPBB 77-1221] A77-15502

Innovative Aircraft Design Study (JADS) task 2f

volume 1CAD-A011231J B77-31111

BABIH07, I. T.Space experiment simulation using an aircraft

laboratoryA77-17200

BABKLBT, B. B.CH-17 medium lift helicopter effectiveness

evaluation program run book[AD-A01H462] N77-31112

BABiA, P. S.Sensor for measuring instantaneous angle of attack

of helicopter blades[N&SA-CB-151808] H77-301<1«

Vibration analysis of rotor blades with anattached concentrated mass[HASA-CB-151987] H77-31537

BAEBETT, 0. 0.Laser velocmeter utilization in jet engine

altitude test cells[AD-A011019] H77-31177

BABBOi. D.Synergistic growth of ITCS to a tactical BP7 C2

systemA77-17313

BiBTBELT, H.-P.A tryont of a rigid airship under tropical

conditionsA77-45160

BASSO, B. J.Computational methods to obtain time optimal jet

engine controlA77-H6611

BECKBB, J.Evaluation of vibration levels at the pilot seat

caused by wing flow separationH77-31078

BELL, B. A.F-8 oblique wing structural feasibility study

[HASA-CB-151811] H77-30107BEHCZE, D. P.

Advanced turboprop technology developmentC A I A a PAPEB 77-1223] A77-H132H

Advanced turboprop technology development[HASA-TH-73729] H77-31155

BEIEPE, D. B.. SB.Prediction of transonic aircraft buffet response

H77-31076BEBBETT, I. S.

The development and simulation of an automaticgunnery system for advanced fighter aircraft

A77-07257BEBGEB, 7. C.

Flying, maintenance, and the sale of parts to thefield: Interactive models for AB-1 and CH-17systems[AD-A039193] B77-30073

B-1

BEBBIBB, B. L. PEBSOBAL AOTROB IBDEI

BEBBIEB, B. L.Bonaxisyametric nozzle technology program - An

overview r

[AIAA PAPEB 77-1225] A77-1U325BEBTBIAOBE, 8. f. B.

Introductory investigation of the Bange Beasnrxngsysten/data collection system (BBS-2/DCS)[AD-A039921] H77-30106

BIBBIBG, B.Thermal stability of transition netal monocarbidefibers in refractory composites prepared byunidirectional solidification(OHEBA, TP BO. 1977-621 I77-U7136

BIDBELL. B. L.Design-to-cost in action[ASBE PAPBB 77-DE-9] A77-<1690I|

BIBB, F.An optical technique for measuring vibratory

notion in rotating machineryA77-47090

BIBDEB, 6.Nonlinear lifting-surface theory for yawed and

banked wings in ground pro unityA77-U5387

BISHOP, D. E.Selection of minimum day/night levels for noisemapcontour calculations[AD-A040623] B77-31922

BLATTBBB, D. 6.Innovative Aircraft Design Study (IADS) task 2,

volume 1rAD-A041234] H77-31141

BOBB, J. B.Advanced high speed roller bearing inspectiontechniques[AD-A002121] N77-31529

BOLABD. J. S., IllAutomatic target hand-off using correlationtechniques[AD-A036435] H77-30115

BOIILLA-BOBAt. 3.Seakeeping characteristics of a prelioinary designfor a sea loiter aircraftCAD-A040062] N77-30113

BOOKEB, B. L.Visual range: concepts, instrnnentaldetermination, and aviation applications[NBS-BONO-159] H77-30102

BOBE, C. L.Unsteady airloads in separated and transonic flow

H7 7- 3 107<4BOOBLAID, G.

Accelerated environmental conditioning of the A-7Dconposite outer wing

A77-46838BOOSBAH, I. 6.

Ao interpretation of the Army standard hot day inoperational terns

A77-UII513BOBLBS, J. V.

Application of powered lift and mechanical flapconcepts for civil short-haul transport aircraftdesign[AIAA PAPEB 77-1237] A77-4I1330

BOI8ELL, D. A.Acoustically swept rotor

rHASA-CASB-ABC-11106-1 1 H77-31130BOIIOS, J. F.

HAPTC Facility Modifications required for altitudetesting of current V/ST01 engine[AD-AOB1608] H77-31184

BBADLEI, 2. S.Paranetnc study of advanced long range•ilitary/coanercial cargo transports[AIAA PAPEB 77-12211 A77-u«322

BBADL8T, B. B. I.Flight experience with Oaega

A77-U7811IBBABiELL, A. B. S.

On the static pressure in the wake of a hoveringrotor

BBASBEABS. B, B.Analysis of transonic flow over lifting andoscillating airfoils

A77-<!75«2

BBOCKBAOS. &.Flight control. I - The aircraft as controlled

systemA77-117675

BBOTBEBBOOD, P.Comparative performance neasurements of two

helicopter blade profiles in hovering flightCABC-H/B-3792] H77-311U3

BBOOGHTOB, D. I.Royal Air Force assessment flights

A77-17813BBOBB. C. B., JB.

An extended Kalaan filter for estimatingaerodynamic coefficients[AD-AOI»0594] R77-30092

BBORB, G.An alternate recovery system for the Aquila

A77-H7316BBOIR, B. B.

Parametric performance evaluation of a jet enginederived froa a turbocharger[AD-A039116] H77-30126

BBOIB, B. G.VLP pulse timing - Limitations and potential as a

companion to OmegaA77-IHIU39

BUDIABSKI, J. B.The aini-BPV, cost effectiveness in a tactical

environmentA77-it73»2

BOILBE. G. P.Measurements of buffeting on two 65 deg delta

wings of different materialsH77-31079

BTBBB, I. G.Army aviation manufacturing technology program

guidance[AD-AOI10821 ] N77-30071

CABB, C. B.Software implementation of a PB spread spectrum

receiver to accommodate dynamicsA77-UU738

CAUSE, A. J.Singular perturbation analysis approach for

systems with highly coupled dynamicsA77-16617

CABAC, B.An optical technique for measuring vibratory

motion in rotating machineryA77-U7090

CAIIBELL, B. B.A simple closed-form solution of a position-fixing

problem[AD-A039303] H77-31127

CAPBBTOB, 0. B.Tactical expendable drone system /TEDS/

A77-Q7337CABICO, D.

A program for increased flight fidelity inhelicopter simulation[AD-A03923U] H77-30108

CABLSOB, G. E.Navigation checkpointing using horizon correlation

[AD-A039916] N77-30103CBA, B. A.

Effects of technology level on V/STOL aircraft[AIAA PAPEB 77-1238] A77-45501

CBACKSFIBLD, J. B.The arrow wing - Its potentialities and drawbacks

with regard to in-flight aerodynamic researchA77-16606

CBAHIS, C. C.Composite hubs for low cost turbine engines

A77-H6520CBAB, S. T. K.

Analysis of transonic flow over lifting andoscillating airfoils

A77-U7512CHAPPELL, D. P.

Single-rotor helicopter design and performanceestimation programs. Volume 1: Bethodology[AD-AO«0803] H77-31138

B-2

PBBSOBAL ADTBOB IHDBI DBIOBBG, J.

CBEH, K. I.A study of the charge and current induced on anaircraft in an EBP simulator facility. Part 1:The femulation. Part 2: The singularityexpansion nethod. Part 3: The numerical results(AD-A039507) 877-31381

CBEBET, H. K.Analysis nethods and computer programs developed

for the TC-15 STOL flight test program[AIAA PAPEE 77-1215] A77-44317

CHEBHYI, I. B.Increasing jet-engine thrust by water-augmentation

A77-46984CBBSTi, L.

Tail response to propeller flow on a transportairplane

H77-31082CBIESA, S.

The insertion or elimination of fuselage sectionsand the balancing of aircraft

A77-47699CBO, C. B.

Wave draq reduction for aircraft fuselage-wingconfigurations. Volume 1: Analyses and results[AD-A040997] N77-32012

Wave drag reduction for aircraft fuselage-wingconfigurations. Volume 2: Bannal for computerprograms[AD-A040998] H77-32013

CLASH, A. B.Dpstream influence on the near field of a planeturbulent jet

A 77-17 005CLARK. B. J.

Hacroscopic study of time unsteady noise of anaircraft engine during static tests

A77-44453CL&BK, S. H.

An attempt to correlate normal vorticities withtotal pressure distortion patterns at theentrance to a gas turbine engine[AD-A040370] H77-30122

COKE, C. F.Separated-flow unsteady pressures and forces on

elastically responding structuresH77-31075

COLLfliHH, D.Experience gained in adinsting the mathematical

model of the VFB 611 short-haul aircraft by useof measured eigenfreguencies

A77-45391COHLOB. J. A.

Application of powered lift and mechanical flapconcepts for civil short-haul transport aircraftdesign[ A I A A PAPEB 77-1237] A77-44330

COHBOY, B. J.ASDAR (aircraft to satellite data relay) flight

test report[HASA-TH-73744] N77-31355

COOLBY, 0. E.Comparative flutter calculations for the Viggen

aircraftA77-44818

COPPOCK, B. I.Aircraft gun icing evaluation

[AD-A039834] H77-30110COBLISS, L. 0.

A failure effects simulation of a low authorityflight control augmentation system on a DH-1Hhelicopter[NASA-TB-73258] H77-31174

A mathematical force and moment model of a OH-1Bhelicopter for flight dynamics simulations[HASA-TH-73254] H77-31175

COBHIBB, K. B.The 3000—HP roller gear transmission development

program. Volume 6: Beliability andmaintainability report[AD-A039381] H77-30480

CBABFOBD. J. H.A rotating high pressure water condenser and

separatortASBE PAPEB 77-EBAS-10] A77-46851

CBESCB1ZI, E. 3., JB.Ku-band integrated circuit receiver

A77-47354

CBOSS, B. J., JB.Aerodynamics of horizontally-opposed aircraft

engine installations[ A I A A PAPEB 77-1249] A77-45508

CBOI, T. T.A study of the charge and current induced on an

aircraft in an EHP simulator facility. Part 1:The formulation. Part 2: The singularityexpansion method. Part 3: The numerical results[AD-A039507] H77-31384

GULP, 0. B.ASDAR (aircraft to satellite data relay) flight

test report[HASA-TB-73744] S77-31355

CDHIIHGHAB, A. 8.. JB.Prediction of transonic aircraft buffet response

H77-31076CONIRGBAH, F. L.

The profile descent( A I A A PAPEB 77-1251] A77-44339

CWISAB, D. S.Development and verification of real-time, hybrid

computer simulation of F100-PH-100 (3J tnrbofanengine[HASA-TP-1034] N77-31154

CIBOS, J. D.Thrust augmenting ejector technology for Havy

aircraft[AIAA PAPEB 77-1239] A77-44331

DADOBB, L. 0.Comparison o£ dynamic stall phenomena for pitching

and vertical translation motions[UASA-CB-2793] H77-30088

DAISTY, B. B.Gas turbines in the RAF from a maintenance

engineering viewpointA77-46406

DAB48IA. B. B.An investigation of the near-field wake behind a

full-scale test aircraftA77-4H816

DAD, K.Evaluation of vibration levels at the pilot seat

caused by wing flow separationN77-31078

DAVIS, J. B.Accuracy of the Kirchoff. formula in determining

acoustic shielding with the use of a flat plate[HASA-TB-73261] H77-30906

DE1HGELO, L. A.Numerical analyses of soft body impacts on rigid

and deformable targets[AD-A040030] N77-31168

DEARTB, 6. B.ECH methods for aircraft engine manufacture

[SBE PAPEB BB76-705] A77-15871DBLOCIA, B. A.

Botor burst protection program: Experimentationto provide guidelines for the design of turbinerotor burst fragment containment rings[HASA-CB-135166] H77-30119

DEBABCBI, J. H.Flight test of an 8000 psi Lightweight Hydraulic

System (LHS)[AD-A039717] N77-30120

DEN MS, B. B.The aircraft gas turbine - Status and prospects

A77-46403DEB, J., JB.

Jave drag reduction for aircraft fuselage-wingconfigurations. Volume 1: Analyses and results[AD-A040997] H77-32012

lave drag reduction for aircraft fnselage-vingconfigurations. Volume 2: Bannal for computerprograms[AD-4040998] H77-32013

DEBBISHIBE, K.central integrated test system /CITS/ - check

three times[AIAA PAPEB 77-1260] A77-Q5513

DEIOOHG, J.ITonplanar wing load-line and slender wing theory

[HASA-CB-2864] H77-31090,

B-3

DICKIHSOB, D. PBESOB1L JOTBOB IHDBX

DICEIHSOH, D.Monitoring foe preventive maintenance in the snail

fleet477-46411

DIEKBABI, ?. I.Airworthiness and flight characteristics

evaluation C-12A aircraft[AD-A040239] H77-31136

DIETEICB. D. i.Siaulation of flight-type engine fan noise in the

NASA-Lewis 9 z 15 anechoic wind tunnelA77-44456

DOLEI, J. L.Control of rare events by aircraft system design

regulation - Impact on operations[AIAA PAPEB 77-1258] A77-45511

DOLLTHIGB, S. B.Subsonic and supersonic longitudinal stability andcontrol characteristics of an aft-tail fighterconfiguration with cambered and nncambered wingsand cambered fuselage[BASH-TN-D-8II72] H77-31093

OOBIBO, E. J.ASDAB (aircraft to satellite data relay) flighttest report[NASA-TH-73744] H77-31355

DOUGLAS. C. A.Visual range: Concepts, instrumentaldetermination, and aviation applications[NBS-BONO-159] H77-30102

DBEBEB, B. C.Studies of friction and wear characteristics ofvarious wires for wire-brush skids[NASA-TH-D-8517] H77-31134

DHISKELL, C. B.Scanned laser visual system

A77-44814DDBBO, G. A.

An electro-optic airspeed sensorA77-44783

DDGiH, J. F.Advanced turboprop technology development

[AIAA PAPEE 77-1223] A77-44324Advanced turboprop technology development[NASA-TH-737291 H77-31155

DOIH. R. B.Air New Zealand's methods of flying the DC-10

[AIAA PAPEB 77-1255] A77-44343DOBHIAK, J. D.

Development of a small, low cost turbojet enginewith thrust augmentation

A77-47347DVOIAK, F. ».

Investigations of three-dimensional flowseparation on fuselage configurations[AD-A039382] H77-30421

OZEKOV, T. A.Hicrowave holographic imaging of aircraft with

spaceborne illuminating sourceN77-30439

ECEB, 1.Application of finite element method for thesolution of transonic flow

A77-47540EGGOB, G. E.

numerical analyses of soft body impacts on rigidand deformable targets[AD-A010030] H77-31168

EHLEBS, F. E.Application of a finite difference method to theanalysis of transonic flow over oscillatingairfoils and wings

H77-31090EILEBTSOB, 1. B.

Tethered hover flight tests of a vertical attitudetakeoff and landing remotely piloted vehicle

A77-47341ELLIS, D. B.

An in-flight simulation of approach and landing ofa S1OL transport with adverse ground effect[NASA-CB-154875] ' H77-31133

ELLIS, J. B.Advanced Technology Ring /ATR/ selection and design

[AIAA PAPEB 77-1210] A77-45505

ELBOD, I. C.Development of a small, low cost turbojet engine

with thrust augmentationA77-47347

EBBACHEB, H.Composite horizontal stabilizer for the B-1 -

Design, fabrication and testA77-46519

ESLIBGEB, B. C.Microcomputer BPV stabilization and control system

S77-47348EIKIH, B.

A laboratory investigation into flight pathperturbations during steep descents of V/STOLaircraft[AD-A040101] N77-30135

BVABS, J. E.Investigation of landing gear deck obstruction

effects by drop testingA77-46825

PABEB, B.Becognition criterion and production of easily

solvable models for flight mechanicaloptimization problems[IFD-9/76] 1177-31178

PAOLKHEB, A. J.The remotely piloted helicopter

A77-44443FEHBEIKABP, L. G.

Surface finishing[NASA-CASE-HSC-12631-2] H77-31131

FIBCK, H. D.Investigation of flight dynamics during roll

[IFD-8/76] H77-31177FISK, D. E.

F-18 blends advanced fighter conceptsA77-46575

FLIOH, A. H.BHAV control for airborne surveys

A77-46264FOBSTEB, J. D.

Sensitivity of Army helicopter operating andsupport costs to changes in design and logisticparameters[AD-A040353] H77-31139

FOBSITB, P. J. E.Fatigue problems in service - Aircraft structures

A77-47503FOOBHIEB, J.

Outlook for utilization of the North Atlantic airspace in 1978

A77-44572FBBBLEB, B. J.

A digital data acquisition and reduction systemfor flight testing general aviation aircraft[AIAA PAPEB 77-1216] A77-44318

FBIESEH, R. J.Flow characteristics in an expansion tunnel as

inferred froia velocity measurementsA77-47108

FBOLOV, S. P.Soviet aircraft and rockets

[NASA-TT-F-770] N77-30065FBOLOV, V. S.

Soviet aircraft and rockets[NASA-TT-F-770] N77-30065

FBOEHAOF, H.-H.Applicability of axisymmetric analysis in

predicting supersonic flow through annularcascades[ASME PAPER 76-PRB-B] A77-44344

FOKBSBIHA, I.Comparison of dynamic stall phenomena for pitching

and vertical translation motions[NASA-CB-2793] H77-30088

SABBIELSEB, B. E.Accuracy of the Kirchoff formula in determining

acoustic shielding with the use of a flat plate[NASA-TB-73261] H77-30906

GALLIIGTON, B. R.Performance prediction method for a wing-in-ground

effect vehicle with blowing under the wing[AD-A039829] H77-30301

B-4

PEBSOliL AOTHOB IHDEI HBLTOB, D. J.

GABDHBB, 6. F.The 3000-HP roller gear transmission development

proqrai. Volume 6: Reliability andmaintainability report[AD-A039381] B77-30480

GABBEB, H. C.A practical framework for the evaluation ofoscillatory aerodynamic loading on wings insupercritical flov

H77-310896ABHEB. J. E.

ASD advanced program research inlet data analysisreport for 1/5.2-scale model inlet tests[AD-A040707] H77-31108

GEBBAB, J. B.The potential role of technological modifications

and alternative fuels in alleviating Air Forceenergy problems[AD-A039597] H77-30261

6EBKE, B. D.Aircraft gun icing evaluation[AD-A039834] H77-30110

GEBSTBH, A.Seakeeping -characteristics of a preliminary design

for a sea loiter aircraft[AD-A040062] H77-30113

GILSIBB, J. I.Validation of an airport simulation model

A77-45719GIHGEBICH, E. D.

Stereographic projections in air traffic controlsystems

A7 7-06 26 2GLAZKOV. V. D.

Space experiment simulation using an aircraftlaboratory

A77-47200GLOilBSKI, B.

Transonic flow simulation by the finite elementmethod via optimal control

A77-4754sGOBBLES. D. D.

Cast aluminum structures technologyTAIAA PAPEB 77-1232] A77-l|<»328

GOBSALVES, J. B.Emergency-power benefits to multi-engine helicopters

A77-44515GOOBJIAB. P. H.

Efficient solution of unsteady transonic flowsabout airfoils

N77-31087GOIAL, f. E.

Advanced avionics for the Advanced RemotelyPiloted Vehicle /ABPV/

A77-47350GBABT, A. D.

The effect of boundary layer changes due totransient heat transfer on the performance of anaxial-flow air compressor[SAE PAPEB 770281] A77-44565

GBATKB, S. D.Analysis/theory of controlled configured structures

[AIAA PAPEB 77-1212] A77-44316GBBEB. K. i.

Thrust augmenting ejector technology for Uavyaircraft[AIAA PAPEB 77-1239] A77-44331

GBBEB, B. E.. OB.Ultrasonic detection of fatigue damage in aircraftcomponents[AD-A000009] H77-31516

GBEEBE, B. C.A miniature rotary-wing BPV

A77-47351GBEEB. P. B.

Raster monitor display applications study for theA-7ErAD-A039882] 1177-30118

GBITSBBKO, B. A.Calculation of the aerodynamic characteristics of

a ving aoving at subsonic speed, in the case ofa weak shock-wave effect on the wing

A77-47667GBOESBECK, D.

OTi noise correlation for several nozzle/winggeometries using a 5:1 slot nozzle with externaldeflectors

A77-44U61

GBOZDBV, A. A.Configuration of free vortices trailing off a wing

of finite spanA77-U7669

GOBUZ. A. 6.Aerodynamics of a confined jet with variable density

A77-07248

HAAS, J. E.Cold air performance of a

12.766-centimeter-tip-diameter axial-flow cooledturbine. 2: Effect of air ejection on turbineperformance[BASA-TP-1018 ] B77-30089

BAFEB, X.Some quadrature methods for lifting wing theory[IFD-5/76] H77-30097

HAFEZ, B. B.Application of finite element approach totransonic flow problems

A77-47539flixed finite element models and dual iterative

methods for transonic flowA77-47543

HAIHES, A. B.Computers and wind tunnels - Complementary aids to

aircraft designA77-47879

BALI. 6. B.Results of a feasibility study to add canards and

ADEH nozzle to the YF-17[ A I A A PAPEB 77-1227] A77-45506

HALLIRELL, 0. S.Pan supersonic flutter: Prediction and test

analysis[ABC-B/B-3789] B77-31163

HAHIHG, B. K.Flight test of an 8000 psi Lightweight Hydraulic

System (LUS)[AD-A039717] N77-30120

HANOI,-J. B.Airworthiness and flight characteristics

evaluation C-12A aircraft[AD-AO<!0239] H77-31136

HABBADIIB. P. J.Powered lift - Its impact on YC-14 materials and

structures[AIAA PAPEB 77-1231] A77-44327

HABRIS, 6. L.An alternate recovery system for the Aguila

A77-47346HASBIBOTO, B.

Application of the finite element techniquecombined with the collocation method to subsoniclifting surface problems

A77-47537HAVBESSBB, B. L.

Development of lightweight transformers forairborne high power supplies[AD-A041515] H77-31162

HADPT, 0.Case studies in aircraft design

[ A I A A PAPEB 77-12*11] A77-44335Decision-making and optimization in aircraft design

[AD-A039464] H77-30111HEAP, H. F.

Control of rare events by aircraft system designregulation - Impact on operations[ A I A A PAPEB 77-1258] A77-45511

HEDEBBAI, B. F.An evaluation of very large airplanes and

alternative fuels[AD-A040532] H77-31334

HEFFEBBiB. J. I.Surface finishing

[NASA-CASB-BSC-12631-2] N77-31131BEIDBAIB, H. F.

Hacroscopic study of time unsteady noise of anaircraft engine during static tests

177-40453Simulation of flight-type engine fan noise in the

BASA-Lewis 9 x 15 anechoic wind tunnelA77-44456

HBLIOB. D. J.An experimental investigation of a subscalevariable pressure ratio high thru flow turbine[AD-A039823L] H77-30121

B-5

HBHBE, P. A. PgBSOHAL AOTHOB IBDEI

BEHBB, P. A.ling design by numerical optimization

[AIAA PAPBB 77-1247] A77-44336B8BBIBG, H. J.

Army aviation manufacturing technology programguidance[AD-A040821] S77-30074

HEBfEiSTBIB, J.An alternate recovery system for the Aqnila

A77-47346BESS, B. 6.

Advanced cooled turbine airfoil aerodynamicinvestigationtAD~AOim37] N77-31161

HICKS, B. B.Ring design by numerical optimization

[ A I A A PAPBB 77-1247] A77-44336HIBTOH, P. A.

A description of the software analysis from flightand simulation data of the course cut limiter inthe TCV b-737 area navigation conputer[HA5A-TH-74061] H77-31125

HIBSCB, J-Remote rate control for EPVs

A77-47352BTTCB, B. P. I.

Active control technologyA77-45524

BOFFBABR, B. 3.A digital data acquisition and reduction system

for flight testing general aviation aircraft[AIJA PAPEB 77-1216] A77-44318

HOGSH, W. L., JB.An evaluation of a raster scan display for use in

an aircraft information handling system[AD-A039652] H77-30117

BOB, B. B.Development of an integrated configuration

management/flight director system for pilotedSlot approaches[HASA-CB-2883] N77-30132

HOBHEIX, B. A.Automatic target hand-off using correlation

techniques[AD-A036435] H77-30115

HOBTOH, R. A.Airworthiness and flight characteristicsevaluation C-12A aircraft[AD-A040239] N77-31136

HOBVAIB, B. B.An evaluation of very large airplanes andalternative fuels[AD-A040532] H77-31334

BUFFHAS. J. K.Effect of an integrated scramjet installation on

the subsonic performance of an aircraft designedto Hach 6 cruise[AI»A PAPEB 77-1230] A77-44326

HUGHES. P. C.A laboratory investigation into flight pathperturbations during steep descents of T/STOLaircraft[AD-A040101] H77-30135

HUGOS, P,Position finding using distance measurements

A77-44570HOST, J. L.

Streaatnbe analysis of a hydrogen-burning scramjetexhaust and simulation technique

A77-44817BDBTOISKI, F. J.

Software implementation of a PH spread spectrumreceiver to accommodate dynamics

A77-44738BDSSAIB, A. K. B. F.

Upstream influence on the near field of a planeturbulent jet

A77-47005HIABG. C.

Separated-flow unsteady pressures and forces onelastically responding structures

N77-31075

IKBSABA, B.Application of the finite element techniquecombined with the collocation method to subsoniclifting surface problems

A77-47537

JACOB!, J. L.Advanced high speed roller bearing inspection

techniques[AD-A042121] S77-31529

JBFFBBSOH. F. 8.Air traffic control experimentation and evaluation

mth.the HASA ATS-6 satellite. Volume 2:Demonstration of satellite-supportedcommunications and surveillance for oceanic airtraffic control[FAA-HA-75-64-VOI-2] S77-31124

JOBE, C. L.F-8 oblique mng structural feasibility study

[NASA-CB-1548IH] N77-30107JOHHSOB, C. B.

Beat-transfer and pressure measurements on asimulated elevon deflected 30 deg near flightconditions at Hach 7[NASA-TB-X-3563] N77-314110

JOBSSOU, D. C.Honitoring for preventive maintenance in the small

fleetA77-Q61H1

JOBHSOB, 6. A.Aircraft interior sandwich panel development

A77-47625JOBHSOB, B. A.

Ducted-fan VTOL BPV systemA77-H7353

JOHHSOH. B. 8.Design and fabrication of graphite-epozy bolted

wing skin splice specimens[HASA-CB-1H5216] H77-30180

JOBBSOB, B. A.Development of an integrated configuration

management/flight director system for pilotedST01 approaches[HASA-CB-2883] S77-30132

JOHlStOH, P. 3.Effect of an integrated scramjet installation on

the subsonic performance of an aircraft designedto Bach 6 cruise[AIAA PAPEB 77-1230] A77-41326

JOBDAB, T.The aircraft gas turbine - Status and prospects

A77-46403JODD. B.

An analysis of helicopter rotor response due togusts and turbulence

A77-44440

KALEBABIS, S. G.Effects of technology level on V/STOL aircraft

[ A I A A PAPEB 77-1238] A77-45501KABE, G. B.

Automatic target hand-off using correlationtechniques[AD-A036435] H77-30115

KABISS, A. H.Statistical review of counting accelerometer data

for Havy and Marine fleet aircraft[AD-A041266] H77-311UO

KABCBBBB, A.Core noise source diagnostics on a tnrbofan engine

using correlation and coherence techniques477-44457

KABBAZIB, 8. B.BPV applications of Tomahawk cruise missile

A77-47336KAST, B. B.

Digital shaft encoder[AD-A040706] H77-31172

KATSUBOTO, It. I.GATOB/AV-8A environmental captive flight vibration

response tests[AD-A036198 ] H77-30114

B-6

P3BSOHAL ADTBOH IBDEX IBIHEB, D. K.

KATZ. 1.F-8 oblique ving structnral feasibility study

rHASA-CB-154841] 877-30107KEBKEBIHG. K. J.

Altitude warning signal system evaluationUD-A039365] H77-31147

KEOHES. F.Experimental investigation concerning theredaction of wave draq of pointed symmetricalwings of equal volume with sabsonic leading edgeand bell-shaped planforn for different thicknessdistributions in the spanwise and chordvisedirectionstDLB-FB-75-62] S77-30087

KBZB, J. E.Operational concept for a battlefield surveillance

BPV system /Canadair ci-227/A77-47335

KBAH, T.Thermal stability of transition metal monocarbide

fibers in refractory composites prepared byunidirectional solidification[OHEBA, TP HO. 1977-62] 477-47136

KIB, D. G.An electro-optic airspeed sensor

A77-44783KIHG, E. i.

Emergency-power benefits to multi-engine helicopters477-44515

KIHZ1BB, J. 4.Surface finishing[HASA-CASE-MSC-12631-2] N77-31131

KUPPBOTT, C.F-8 oblique wing structnral feasibility study

f HASA-CB-15481(1 ] H77-30107KLEIB, B. B.

A method for determining the point of lift-off andmodified trajectory of a ground-based heatedturbulent planar jet m a co-flowing wind[AD-A040704] H77-31722

KLEIH, B. B.Development of an integrated configuration

management/flight director system for pilotedSTOL approachesrFASA-CB-2883] H77-30132

KBOX, C. E.A description of the software analysis from flight

and simulation data of the course cut limiter inthe TCV b-737 area navigation computerrNASA-TH-74061] H77-31125

KOBAItSHI, 6. S.Process development for fabricating sculptured

decorative interior aircraft panels using sheetmolding compounds

A77-16508KOEBIG, B. J.

Air transport noise reduction477-44550

KOFSKBT, B. G.Cold air performance of a

12.766-centimeter-tip-diameter axial-flow cooledturbine. 2: Effect of air ejection on turbineperformance[NASA-TP-10181 H77-30089

ftOHLBAH, D. I.Flight test results for an advanced technology

light airplane[AIAA PAPEB 77-1217] • A77-44319

KOLTKO, E.F-8 oblique wing structural feasibility studyfNASA-CB-151841] F77-30107

KOLBET, B. G.Summary of helicopter airfrane testing in the

shipboard environment[AD-4039748] H77-311I»1»

KOBECBAK. G. J.The development and simulation of an automatic

gunnery system for advanced fighter aircraftA77-47257

KBACBBAB, B. B.An alternate recovery system for the Aguila

477-47346KBaflSEfA. A. I.

Increasing jet-engine thrust by water-augmentation477-46984

KBEIB, I. J.Bacroscopic study of time unsteady noise of anaircraft engine during static tests

A77-44453

KBBBZ, G.airframe response to separated flow on the short

haul aircraft VPS 614H77-31081

KBBIBIHA6BI. K. B. «Hnmencal analyses of soft body impacts on rigid

and deformable targetsIAD-A040030] H77-31168

EBOBIB. C. B.Ku-band integrated circuit receiver

477-473511KBUCZY8SKI, L. B.

Aircraft navigation with the limited operationalphase of the HA7STAB Global Positioning System

A77-44436KDBAB, B. T.

Helicopter offshore operationsA77-44437

EOBBALE, B.A study of the charge and current induced on an

aircraft in an E8P simulator facility. Part 1:The formulation. Part 2: The singularityeipansion method. Part 3: The numerical resultsCAD-A039507] H77-31384

LACET. D. B.Bind tunnel results of a 10-percent scale powered

SCAT VIOL aircraftCAD-A040313] H77-31109

LACKHAH. L.Advanced composites and advanced metallics meet

the challenge of design-to-cost[ A I A A PAPEB 77-123M] A77-44329

LABAR, J. E.Yortei-lift roll-control device

[HASA-CASE-LAB-11868-2 ] H77-31176LAHDES, B. E.

Composite tanks for aerospace vehicle application477-46516

LAIGB. B. B.Parametric study of advanced long range

military/commercial cargo transportsC A I A A P4PEB 77-1221] A77-i|«322

1APOBTE, T.Interactions of technology and society: Impacts

of improved airtransport. A study of airportsat the grass roots[HASA-CB-2871] H77-31005

LA ROE, G. 0.Software implementation "of a PH spread spectrum

receiver to accommodate dynamicsA77-44738

LAOBIDIA. B.F-8 oblique wing structural feasibility study

[HASA-CB-154841] H77-30107LAB, H. I. B.

Single-rotor helicopter design and performanceestimation programs. Volume 1: Hethodology[AD-4040803J H77-31138

LABBEBCE. D. L.Aerodynamics of horizontally-opposed aircraft

engine installationsC A I A A PAPEB 77-1249] 477-45508

LEAKE, B. 3.Computational methods to obtain time optimal jet

engine controlA77-46614

LEE, D. G.Hind tunnel results of a 10-percent scale powered

SCAT VIOL aircraft[AD-4040313] H77-31109

LEE, K. B.Interactions of technology and society: Impacts

of improved airtransport. A study of airportsat the grass roots[H4S4-CB-2871 ] H77-31005

LEE, B. S.Surface finishing

CHASA-CASE-BSC-12631-2] B77-31131LEHBAH. L.

Flutter-suppression studies on an activelycontrolled variable-geometry wind-tunnel model

477-46805LSIBBB. D. K.

Software implementation of a PR spread spectrumreceiver to accommodate dynamics

477-44738

B-7

LEIS. B. t. PEBSOS1L &OTHOB IBDEX

LEIS, B. B.Fatigue life prediction of complex structures

CASBB PIPES 77-DE-46] A77-46915LEITOH, G. C., JE.

Variable geometry air cycle machine[ASBB PAEEB 77-ENAS-7] A77-46848

LEVEBTOB, J. I.Ham rotor wake/tail rotor interaction

A77-44441LEVIB, B. 1.

Soviet aircraft and rocketsFBASA-TT-F-nO] S77-3006S

LEVIBE, E.Interactions of technology and society: Impacts

of improved airtransport. A study of airportsat the grass roots[HASA-CB-2871] N77-31005

LEBIS, C. H.The 3-D stress analysis of a turbine blades[AD-A039176] N77-30481

LEZBIAK, J.HAPTC Facility modifications required for altitudetesting of current V/STOI engine[AD-A041608] H77-31184

LIKHOPBBSKII, ». I.Bearrangement of vortex structures in the wake

behind a body and in a jetA77-47674

LILLET, B. B.Interactive LOBAN-C to geographic and

geographic-to-LOBAH-C computation[UASA-CB-153985] H77-30101

LIPCBIB, L. IS.The design of complex navigation systems

A77-46494LID. B. B.

Sensor for measuring instantaneous angle of attackof helicopter blades[BASA-CB-154808] N77-30444

LOCKIOOO, D. L.Development of lightweight transformers for

airborne high power supplies[AD-A041515] N77-31162

LODGE, C. G.Dynamic loading of airframe components

H77-31080LOBG, J.

Flutter-suppression studies on an activelycontrolled variable-geometry wind-tunnel model

A77-46805Wind tunnel experiments on an actively controlled,

variable geometry flutter modelTAD-A039216] H77-30134

LOVELI, D. ».A wind-tunnel investigation of the effects of flap

span and deflection angle, wing planform and abody on the high-lift performance of a 28 degswept winq[ABC-CP-13721 N77-31106

LOVELL, B. B.ASDAB (aircraft to satellite data relay) flight

test reportfBASA-TB-73744] N77-31355

LOBIS, G.Composite horizontal stabilizer for the B-1 -

Design, fabrication and testA77-46519

LDDBIG, B.Composite horizontal stabilizer for the B-1 -

Design, fabrication and testA77-46519

LDEDEES, B. G.An experimental investigation of a snbscale

variable pressure ratio high thru flow turbine[AD-A039823L] H77-30121

LOKIBS, J. B.

Bole of future automated flight deck displays inimproving operating costs[AIAA PAEEB 77-1252] A77-44340

LUKSCH, B.Satellite communications for the mobile service

[AAS 76-045] A77-46630LIBCB, B. A.

BPV applications of Tomahawk cruise missileA77-47336

MHABEI, D. C.

Beasurements of buffeting on two 65 deg deltawings of different materials

H77-31079BACCALLOB, B. B. L.

The effect of boundary layer changes due totransient heat transfer on the performance of anaxial-flow air compressor[SAB PAPER 770284] A77-44565

BACLAOGBLIB, B. C.Hon-integrated gas turbine engine diagnostics

tradeoff analysis[AD-A039494] H77-30125

BADEL01G, 5. 0.Characteristics of fighter aircraft

C A I A A PAPER 77-1219] A77-44321BAGHOS, B.

The transonic oscillating flap: A comparison ofcalculations with experiments

N77-31086BAILHIOT, B. J.

Innovative Aircraft Design Study (IADS) task 2,volume 1[AD-A041234] H77-31141

BALL, J. F.Durability testing of the A-7D composite

outer-wing panelA77-46808

BAHGAHO, G. J.Botor burst protection program: Experimentation

to provide guidelines for the design of turbinerotor burst fragment containment rings[MASA-CB-135166] H77-30119

BABB, C. C.ASD advanced program research inlet data analysis

report for 1/5.2-scale model inlet tests[AD-A040707] N77-31108

BABCEAD, J, A.Exploratory of development of durability of

adhesive bonded joints[AD-A039864] H77-30249

BABIS. J. L.Advanced Technology Wing /ATB/ selection and design

[ A I A A PAPER 77-1210] A77-45505BABKI, F. A.

Ku-band integrated circuit receiverA77-47354

BABSB, C. L.Software implementation of a PH spread spectrum

receiver to accommodate dynamicsA77-44738

BABTIB, D. A.A miniature rotary-wing RPV

A77-47351BASKEW. B.

Investigations of three-dimensional flowseparation on fuselage configurations[AD-A039382] H77-30421

BC KEEL, G. J.An evaluation of future BPV automatic navigation

systemsA77-47349

BCCABTI, J. E.Design and fabrication of graphite-epoxy bolted

wing skin splice specimens[HASA-CB-145216] H77-30180

BCCOBKBY. E. D.Terminal area charting for area navigation

operationsA77-44433

BCCDLLOCB, G. ?.Onited's experience with computer generated visual

systems, April 1977A77-44431

BCBILLAB, J. C.Exploratory of development of durability of

adhesive bonded joints[AD-A039864] N77-30249

BCBALL. B. I., JB.

Development of lightweight transformers forairborne high power supplies[AD-A041515] N77-31162

BCPHEHSOB. B. L.IC-14 flight test results

[ A I A A PAPER 77-1259] A77-45512

B-8

PEBSOHAL 10IHOB IBDEI OKIISHI, T. B.

HCBiE, D. S.Bumerical solution of the conically symmetricSavier-Stokes equations for hypersonic flov atangle of attack

877-30079BEAGBEB, T. F, V.

An evaluation of boundary layer forces andneasnreient lethods[4D-4010917] F77-31218

BEADS, J. L.Single-rotor helicopter design and performanceestimation programs. Volume 1: Rethodoloqy[AD-A040803] F77-31138

BEEB, S. A.A digital goniometer for YOB

177-116 263BBLLOB, A. H.

Characteristic time emissions correlations - TheT-63 helicopter gas turbine combustor

477-118211HEBKOLOV, I. «.

Soviet aircraft and rockets[N4S4-TT-F-7701 F77-30065

BBBT40GB, I. J.An investigation of the near-field vake behind afull-scale test aircraft

A77-11816BIKOLOBSKY. I. 1.

The military utility of very large airplanes andalternative fuels

S77-17271The potential role of technological modifications

and alternative fuels in alleviating Air Porceenergy problems[AD-A039597] H77-30261

An evaluation of very large airplanes andalternative fuels[AD-A010532] F77-31334

BILES. J. B.Effects of forward velocity on noise for a J85

turbojet engine vith multitabe suppressor frommnd tunnel and flight tests

A77-11160BILEY, S. 3.

Aerodynamics of horizontally-opposed aircraftengine installations[AIAA PAPEB 77-1219] A77-15508

BILLEB, C. G.Plow characteristics in an expansion tunnel as

inferred from velocity measurementsA77-17108

BILLS, J. P.Calculation of side line noxse levels during takeoff

[AD-A01062I1] S77-31170BOBLBJI, S. C.

Fuel conservation for high performance aircraft inthe terminal area

477-44431BOOIJ, B. A.

Handling quality criteria development fortransport aircraft with fly-by-wire primarycontrol systemsfHLH-TR-70111-0] F77-31179

The need of stick force stability forattitude-stabilized aircraft, part 1tNLB-TB-76125-0] F77-31180

BOBISSBT, J.The Hirage-2000

A77-16975BOBBIS, E. E.

Composite tanks for aerospace vehicle applicationA77-16516

BOSS, G. P.The dynamic response of wings in torsion at high

subsonic speedsH77-31077

HOLDEB, J. 4.The measurement of performance, stability and

control characteristics of a high subsonic jetaircraft in non-steady flight conditionsemploying high accuracy instrumentation techniques

A77-45525BULLET, B. G.

Feasibility demonstration of the earth referencedmaneuvering flight path displayf A I A A PAPEB 77-1111] A77-15171

BOBBAB, B. B.Application of finite element approach to

transonic flow problems477-47539

Study of design and analysis methods for transonicflowCHASA-CB-152011] H77-30086

BOBPBI, L. E., JB.BPV applications of Tomahawk cruise Missile

477-17336BOBBAI, L.

Seakeeping characteristics of a preliminary designfor a sea loiter aircraft[AD-4040062] H77-30113

BOBTBT, T. B.Vibration analysis of rotor blades with an

attached concentrated mass[BASA-CB-154987] N77-31537

BIKTTOI. I. J.A brief overview of transonic flutter problems

N77-3108U

BATKE, B. G.Experience gained in adjusting the mathematical

model of the VF8 614 short-haul aircraft by useof measured eigenfreguencies

477-45391BAUHOV. T. I.

Soviet aircraft and rockets[NASA-TT-F-770] S77-30065

BEBHAB. S. J.An analysis of helicopter rotor response due to

gusts and turbulenceA77-44440

HEITOB, D. I.An integrated approach to the problem of aircraft

icing[AIAA PAPEB 77-1218] 477-44320

HICKBLL, J. C.An evaluation of boundary layer forces and

measurement methods[AD-A040917] F77-31218

1I1SOB, E. H.Interactive graphics in aircraft gas turbine

engine design177-15491

SISHT, B. I.Calculation of the aerodynamic characteristics of

a ving moving at snbsonic speed, in the case ofa weak shock-wave effect on the wing

A77-17667BOGGLE, L. I.

Preliminary design and analysis of advancedmilitary transports[4144 PAPSB 77-1221] A77-45502

The military utility of very large airplanes andalternative fuels

A77-47271An evaluation of very large airplanes and

alternative fuelsCAD-A040532] H77-31334

HOBGBBB, I. H.Development of an ultra-low-cost gas turbine

477-47344I01LAB, F. S.

Control of rare events by aircraft system designregulation - Impact on operationsCAI44 P4PBB 77-1258] 477-45511

OBBIAB, D. J.D.S./F.B.G. advanced tactical BPV requirements as

analyzed by Boeing and Dormer477-47339

OBBIEB, J. B.Bead-up display in conmercial aviation

[4144 P4PBB 77-1241] 477-44333ODELL, 4. B.

Problems in predicting aircraft noise exposure477-47561

OKIISBI. T. H.Bultistage axial-flow tnrbomachinery wake

production, transport, and interaction[40-4041108] B77-31173

B-9

OBEIl, i. J. PBBSOHAL 1DTHOB IHDEX

OHBIL. f. J.An overview of Viking navigation

A77-(|4427OBBSBEE, A. I.

Optimum acoustic design of free-ranning lov speedpropellersTA1AA PiPEB 77-12118] A77-44337

Propeller study. Part 1: Introduction and overviewCHASi-CB-155002] N77-31156

Propeller study. Part 2: The design ofpropellers for ami in a noise[HASA-CB-155005] ' H77-31157

Propeller stady. Part 3: Ezperiaentaldetermination of thrust and torque on the YO-3Aaircraft[HASA-CB-155003] H77-31158

OBB. I. P.F-8 oblique wing structural feasibility study

CHASA-CB-1518111] K77-30107OBSZAG. S. A.

Bass flow requirements for LPC wing design[AIAA PAEEB 77-1222] A77-U4323

OBVOS, P. S.Tapered roller bearing development for aircraft

turbine engines[AD-A041317] H77-31507

OTEBSfBEET. C. t.F-8 oblique wing structural feasibility study[NASA-CB-154841] H77-30107

OVBHS, J. K.Aerodynamics of horizontally-opposed aircraftengine installations[AIAA PAPEB 77-12*9] A77-45508

PilllET, F. 1.An investigation of the near-field vake behind afull-scale test aircraft

A77-44816PALCZA, J. L.

Nonaxisymmetric nozzle technology program - Anoverview[AIAA PAPEB 77-1225] A77-1U325

Besults of a feasibility study to add canards andADEH nozzle to the IF-17[AIAA PAPBB 77-1227] A77-45506

PABAiEHTEB, I. «.GATOB/AV-8A environmental captive flight vibration

response tests[AD-A036498] N77-3011I1

PEABSOOH, A. J.Unsteady airloads on an oscillating supercriticalairfoil

H77-31085PECKBAB, V. D.

An evaluation of boundary layer forces andmeasurement methodsfAD-AOl09171 H77-31218

PELTOB, B. B.Process development for fabricating sculptureddecorative interior aircraft panels using sheetmolding compounds

A77-46508PEBDBEAOTILIE. F. J.

Simulation of inertia1 inputs to a strapdownplatform for inertial great circle trajectories[SAHD-76-0620] H77-30104

PEBIJDI, J.Transonic flow simulation by the finite element

method via optimal controlA77-«75<m

PEBBI, J. L.Advanced avionics for the Advanced BemotelyPiloted Vehicle /ABPV/

A77-47350PETEBS, B. G.

Automatic target hand-off using correlationtechniques[AD-A036P35] H77-30115

EHAIEUF. B. J.Bead-up display in commercial aviation

CAIAA PAPBB 77-1201] A77-44333PHIIIIPPE, J.-J.

OHEBA aerodynamic research work on helicopters[OHEBA, TP HO. 1977-42B] A77-44957

PHILLIPS, E. L.An alternate recovery system for the Agnila

A77-47316

PIECDCH, L. B.Interactive LOBAS-C to geographic and

geographic-to-LOBAH-C computation[NASA-CB-153985] F77-30101

PIEBCE, D.The dynamic response of wings in torsion at high

subsonic speedsH77-31077

PIEBSOL, A. 6.Coherence and phase techniques applied to noise

diagnosis in the NASA Ames 7 times 10-foot vindtunnel no. 1[HASA-CB-152039] H77-30905

PIHB. J. B.Durability testing of the A-7D composite

onter-wiag panelA77-H6808

PIBOIBEAO. 0.Transonic f low simulation by the finite element

method via optimal controlA77-a75i(<l

PIIIHAB. J. L.Effect of an integrated scramjet installation on

the subsonic performance of an aircraft designedto Bach 6 cruise[ A I A A PAPEB 77-1230] A77-4U326

PLETT. E. G.Besearch on noise generated by ducted air-fuel

combustion systems[AD-A039957] N77-31169

POLLABD, J. S.Ham rotor wake/tail rotor interaction

A77-P1I441POHD, B. B., SB.

Ultrasonic detection of fatigue damage in aircraftcomponents[AD-A040009] B77-31516

POPISSKI. Z.Numerical solution of complete flows around

external stores[AD-A039213] N77-30122

POPOV, S. 6.Bearrangemeat of vortex structures in the wake

behind a body and in a jetA77-U7671

POSI, T. J.Format practices for documenting time critical,

harzardous procedures[AD-A036369] N77-30100

POTOCKI, B. J.Selection of optimum BPV operational launch and

recovery techniquesA77-17340

POiBIE, S. B.Energy management display for air combat maneuvering

[AD-A040198] N77-30109POZHIDAYEV, O. A.

Soviet aircraft and rockets[NASA-TT-F-770] N77-30065

PRIEDIGKEIT. J. B.Definition of a data collection system for OS Army

tactical microwave landing system evaluation[AD-A041230] S77-31126

PBIHSOH, L. J.Automatic target hand-off using correlation

techniques[AD-A036U35] H77-30115

POBL, G. T.A comparison of ECS controls

[ASHE PAPEB 77-ENAS-8] A77-U68I19

QDIH1, G. B.Helicopter offshore operations

BABIHOVITCH, fl.Thermal staBility of transition metal nonocarbide

fibers in refractory composites prepared byunidirectional solidification[ONEBA, IP HO. 1977-62] A77-17136

BiBSBI, B.Dynamic loading of airframe components

H77-31080

B-10

PEBSOHAL AOTBOB IBDEI SCBBEBLY, F. D.

BASBID, 4.Statistical analysis of OS Navy na~]or aircraft

accident rates, pilot and aircrafttime-dependent variablesf A D - A 0 4 0 0 9 6 ] H77-30099

BBADEB, K. B.Hover evaluation of circulation control high speed

rotorfAD-A040921] H77-31100

BEDD, L. T.A comparison of the results of dynamc wind-tunnel

tests with theoretical predictions for anaeromechanical gast-alleviation systen for lightairplanesCHAS1-TH-D-8521] 877-31072

BBDGATB, C. B.The airline viewpoint

A77-U6405BBID, L. D.

A laboratory investigation into flight pathperturbations daring steep descents of T/STOLaircraft[AD-A040101] H77-30135

BBHTZ. F. E.Coherence a'nd phase techniques applied to noise

diagnosis in the NASA Ales 7 tines 10-foot windtunnel no. 1[NASA-CB-152039] H77-30905

BESHOIKO. B.Core noise source diagnostics on a tarbofan engine

usioq correlation and coherence techniquesA77-114H57

BBTTIE, I. B.Preliuinary design and analysis of advanced

nilltary transportsf A I i A PAPEB 77-1221] 477-H5502

BBTBOLDS, p. B. J.An American Omega navigation evaluation programme

- 1975-1977A77-47815

BICH, P.B N A V waypoint charting effects on pilot

procedures, training and workloadA77-44432

BICHEY. G. E.Nonaxisymmetnc nozzle technology program - An

overviewC A I A A P A P E B 77-1225] &77-<t4325

BIDDIE, 0. w.Separated-flow unsteady pressures and forces on

elastically responding structuresN77-31075

BILET, B. J.Comparative perfornance measurements of two

helicopter blade profiles in hovering flightCABC-B/B-3792] N77-31143

BOBBBTS, P. A.Effects of control laws and relaxed static

stability on vertical ride quality of flexibleaircraft

H77-30128BOSS, E. A., JB.

The mini-BPV, cost effectiveness in a tacticalenvironment

A77-473U.2BOSE, S. E.

Complementary roles for BP?s in support oftactical manned aircraft

A77-47334BOSEBBLATT. B.

Numerical analyses of soft body impacts on rigidand deformable targets[AD-A040030] H77-31168

BOSEBTBil, S.Interactions of technology and society: Impacts

of improved airtransport. A study of airportsat the grass rootsCBASi-CB-2871] S77-31005

BOSIII, E.Bunway utilization coefficients

A77-47950BOSS, S.

Interactions of technology and society: Impactsof improved airtransport. A study of airportsat the grass roots[BASA-CB-2871] N77-31005

BOTH. B.A tryont of a rigid airship under tropical

conditionsA77-45460

BODSSEAO. D. S.Performance prediction method for a wing-in-ground

effect vehicle with blowing under the wing[AD-A039329] H77-30301

BUDD, B. J.An electro-optic airspeed sensor

A77-44783Development of prototype optical convolution

airspeed sensorCAD-A039469) H77-30116

BOSBBOBE, I. L.Bunerical solution of complete flows around

external stores[AD-A039213] H77-30122

SACHS. G.A new concept of static stability and its flight

testing in supersonic flightA77-44815

Investigation of flight dynamics daring roll[IFD-8/761 H77-31177

SALBOB, I. T. J.The presentation of information in combat aircraft

A77-47817SiLTINO, J. T.

Botor burst protection program: Experimentationto provide guidelines for the design of turbinerotor burst fragment containment ringsCBASA-CB-135166] N77-30119

SiBDBL, B. A.The 3-D stress analysis of a turbine blades

[AD-A039176] R77-30981SiHCEB. B. I.

Foundation of the magnetic field integral equationcode for the calculation of the electromagneticpulse external interaction with aircraftCAD-A039953] H77-31389

SABDBLL. H. B., JB.Linear regulator design for stochastic systems by

a multiple time scales methodA77-46621

SABDEBLIH, B. B.Baster monitor display applications study for the

A-7E[AD-A039882] N77-30118

SABGBBT. H. B.Effects of forward velocity on noise for a J85

turbojet engine with mnltitnbe suppressor fromwind tunnel and flight tests

177-44460SAZBKO. B. ID.

Aircraft laboratories and experience in using thenfor the developnent of method's and means ofremote sensing of earth resources

A77-47199SCiVOLLO. J. J.

Probing the airborne Omega environmentA77-44H35

SCBiBTOB, T. 0.Coherence and phase technignes applied to noise

diagnosis in the N A S A Ames 7 times 10-foot windtunnel no. 1tNASA-CB-152039] H77-30905

SCHEIZ. J. A.The flow about a slender propeller-driven body in

a temperature stratified fluid[AD-A040847J F77-31099

SCHIPPEBS, P.Unsteady airloads on an oscillating supercritical

airfoilH77-31085

SC8S IDT. D. P.Bultistage axial-flow turbomachinery wake

production, transport, and interaction[AD-AOI11108] H77-31173

SCBBITZ. F. H.Acoustically swept rotor

rHASA-C»SE-ABC-11106-1 ] H77-31130SCBHBBLI, F. 0.

The development of the ZBQB-105 Aquila mini-BPVsystem

A77-47338

B-11

SCHHOBHBB. B. PEBSOBAL iOTHOB IBDEX

SCBBflBBBB. B.Monte Carlo simulations of VOB/DBE holding

procedures. Basic ideas and applicationsfDLB-FB-77-08] N77-30105

SCHB1BTZBBBG, H. 1.Single-rotor helicopter design and performance

estimation programs. Volume 1: Methodology[AD-A040803] N77-31138

SCBBEIZEB. P. B.O.S./F.B-G. advanced tactical BPV regairenents as

analyzed by Boeing and DormerA77-47339

SEBASTIAB. J. D.Application of a finite difference method to theanalysis of transonic flov over oscillatingairfoils and wings

N77-31090SEEHiBB, G. B.

AD alternate recovery system for the AgnilaA77-47346

SELDBZB, K.Development and verification of real-time, hybridcomputer simulation of P100-PH-100(3) turbofanengine[HASA-TP-1034] B77-31154

SELLS, C. C. L.Iterative calculation of flow past a thick

cambered ving near the ground[ABC-CP-1370] B77-31104

Iterative design technigues for thick camberedvings in snbcritical flow[ABC-CP-1371] B77-31105

SEHPIB. B. D.Emergency-power benefits to multi-engine helicopters

A77-44515SBA», B.

Development of a catalytic combustor for aircraftqas turbine enginesCAD-A040135] H77-31171

SIDDIQI, S. A.Propeller study. Part 3: Experimental

determination of thrust and torgne on the TO-3Aaircraft[BASA-CB-155003] B77-31158

SIEGBl, S.Foundation of the magnetic field integral eguationcode for the calculation of the electromagneticpulse external interaction with aircraft[AD-A039953] N77-31389

SIHIBSKI, V. J.Development of a catalytic combnstor for aircraft

gas turbine engines[AD-A040135] N77-31171

SIHOBS, I. &.The remotely piloted helicopter

A77-44443SIBPSOH. A.

Active control technologyA77-45524

SIBPSOI, I. B.The development of primary eguations for the use

of on-board accelerometers in determiningaircraft performance[AD-A039174] H77-30112

SI7TBB, K. B.Propeller study. Part 3: Experimental

determination of thrust and torque on the YO-3Aaircraft[BASA-CB-155003] B77-31158

SKABVAB, C. A.Engine control stabilizing compensation-testing

and optimi2ation177-44514

SBill. B. D.Ducted-fan 7TOL BPV system

A77-47353SHITB, B. 6.

Durability testing of the A-7D compositeouter-wing panel

A77-46808SBITB, H. I.

Aircraft composite primary structures in BrazilA77-46807

SBITB, B. B.Airworthiness and flight characteristics

evaluation C-12A aircraft[AD-A040239] H77-31136

SHITB. B. L.Single-rotor helicopter design and performance

estimation programs. Volume 1: Hethodology[AD-A040803] H77-31138

SHITB, I. D.F-8 obligue wing structural feasibility study

[BASA-CB-154841] N77-30107SBIEGOSKI, E. J.

3uantitative TLC analysis of amine antioxidants inhigh-temperature 3et engine lubricants[AD-A039909] N77-30124

SOiA, D. F.The effect of terrain near airports on significant

low level wind shear[AIAA PAPBB 77-1242] A77-44334

SPBBCBB, I. B.Digital shaft encoder

[AD-A040706] H77-31172SPIBTZIK, J.

O.S./F.B.G. advanced tactical RPY reguirements asanalyzed by Boeing and Dormer

A77-47339SPOOBEB, A. B.

Scanned laser visual systemA77-4481II

SBOK01SKI, 4. J.Bass flow requirements for LFC wing design

[ A I A A PAPEB 77-1222] A77-44323STABLET, V. L.

The military utility of very large airplanes andalternative fuels

A77-47271The potential role of technological modifications

and alternative fuels in alleviating Air Forceenergy problems[AD-A039597] H77-30261

STABK, V. J. S.Comparative flutter calculations for the Viggen

aircraftA77-44818

Leading-edge vortex effect on the flutter speedA77-44819

STEABBAB, B.Flutter-suppression studies on an actively

controlled variable-geometry wind-tunnel modelA77-46805

STECB, E. L.Design and evaluation methods for optimizing

ejection seat cushions for comfort and safetyCAD-A036035] B77-31110

STEIBEB, J. E.Ihe timing of technology - Commercial transport

aircraft[AIAA PAPEB 77-1200] A77-45503

STEIABD, F. B.Aerodynamics of a confined ]et with variable density

A77-47248STEIABT, E. C.

A comparison of the results of dynamic wind-tunneltests with theoretical predictions for anaeromechauical gust-alleviation system for lightairplanes[HASA-TB-D-8521] H77-31072

STOHB, J. F.Thermal stability of transition metal monocarbide

fibers in refractory composites prepared byunidirectional solidification[OHEBA, IP BO. 1977-62] A77-47136

STOLTZ, P. G.Definition of a data collection system for OS Army

tactical microwave landing system evaluation[AD-A041230] B77-31126

STORE, B. 1.Flying, maintenance, and the sale of parts to the

field: Interactive models for AB-1 and CH-47systems[AD-A039193] H77-30073

STOIB, J. B.Effects of forward velocity on noise for a J85

turbojet engine with multitube suppressor fromwind tunnel and flight tests

A77-H4460Flight effects on exhaust noise for turbojet and

turbofan engines - Comparison of experimentaldata with prediction

A77-44162

B-12

PBBSOHAL &OTBOE IIDEI VADSB, C. B.

SfBiDB. B. B.An extended prediction model for airplane brakingdistance and a specification for a total brakingprediction systems, volone 214D-A03 9967] H77-30476

SOBBABAIIA», 1. K.Tbe effect of ambient conditions on carbon

nonoiide emissions from an idling gas turbinecombostor[HASA-CB-151986] H77-31148

SDHREBFIELD, B.Research on noise generated by ducted air-fnel

combustion systemsCAD-A039957] N77-31169

SOHBEBS, G. D.A miniature rotary-wing BPV

A77-f7351SOBBEBS, I. P.

Tbe development and simulation of an automaticgunnery system for advanced fighter aircraft

A77-47257SOTLIFF. J. D.

BPV applications of Tomahavk cruise oissileA77-17336

SOTTOS, B. C. 'Innovative Aircraft Design Study (I4DS) task 2,

volume 1CAD-AOU1234] N77-31111

SBEAB. T. F.. JB.The flow about a slender propeller-driven body in

a temperature stratified fluidCAD-AOU08117] H77-31099

SZOCB, J. B.Development and verification of real-time, hybridcomputer simulation of FIOO-Pi-100(3) turbofanengine[HASi-TP-1031] B77-31151

SZDHAHSKI, K.Numerical modeling of helicopter piloting

A77-U63U8

TAKATA, H.Stall margin improvement by casing treatment - Its

mechanism and effectiveness[ASHE PAPEB 76-GT-A] a77-<|(|3«5

TALBOT, P. D.A failure effects simulation of a lov authorityflight control augmentation system on a UH-1HhelicopterFNASA-TH-732581 N77-31174

A mathematical force and moment model of a DH-1Hhelicopter for flight dynamics simulationsrHASA-TH-732511 H77-31175

TALCOTT, B. ».. JB.Streamtnbe analysis of a hydrogen-burning scranjetexhaust and simulation technigue

A77-<l 11817TAHSEB, B.

The theoretical determination of the base pressurein supersonic flow

A77-U5388TABHOPOLSKII, T. I.

Space experiment simulation using an aircraftlaboratory

A77-17200TAOSSIS, 8. B.

British Airways: An analysis of efficiency andcost levelsfPB-268060/1 ] H77-31113

TiYLOB, A. B.Beat-transfer and pressure measurements on a

simulated eleven deflected 30 deg near flightconditions at Bach 7[NASA-TH-X-3563] N77-311MO

TAItOB. C. 0.A study of the charge and current induced on an

aircraft in an EBP simulator facility. Part 1:The formulation. Part 2: The singularityexpansion method. Part 3: The numerical results[AD-A039507] B77-3138n

TCHBBG, P.Experiment and analysis on the flow process

dynamics of the NASA-Langley eight foottransonic pressure tunnel[BASi-CB-15Q806] H77-30085

TBIBKBTZIS. D.Linear regulator design for stochastic systems bya multiple time scales method

A77-46621TEHHISSBB, B. 8.

A laboratory investigation into flight pathperturbations during steep descents of V/STOLaircraft[AD-A040101] B77-30135

THOBAS, F. J.General principles of automatic TV trackers

A77-uq812TBOBPSOB, A. 0.

Omega system performance predictionsA77-1H138

THOBESOI, 8.Emergency-power benefits to multi-engine helicopters

A77-10515TIJDBBAB, B.

Unsteady airloads on an oscillating supercriticalairfoil

H77-31085TIBLIBG, B. B.

Estimates of the effectiveness of automaticcontrol in alleviating wake vortex induced rollexcursionsfHASi-TH-73267] H77-30129

TORBSBBD, T. B.AH/PBC-S6 helmet radio set upgrading. Recommendedmodifications reguire minimal resources butpromise considerable improvement in reliabilityoperability, and logistics support[AD-A041190] N77-31368

TBASKOS, B. L.Flight control testing of the VAK-191B aircraft[ AD-A040535] N77-31137

TBBACY, J. J.The use of probability analysis in aircraftcertification and its effects on maintenance andequipment maintenanceTAIAA PAPER 77-12561 A77-45509

IBOSTEE, B.The 3000-BP roller gear transmission development

program. Volume 6: Reliability andmaintainability report[AD-A039381] H77-30180

TSEKA, J.Variable geometry air cycle machine

[AS1JE PAPEB 77-EHAS-7] A77-06848TSITOVICH, V. S.

Aircraft laboratories and experience in using themfor the development of 'methods and means ofremote sensing of earth resources

A77-«7199tSOKODA, i.

StaJ.1 margin improvement by casing treatment - Itsmechanism and effectiveness[ A S B E PAPEB 76-GT-A] A77-01l3a5

TILEB, D. B.Altitude warning signal system evaluation

[AD-A039365] H77-31147

TIB HOITEH, I.On the validity of lifting line concepts in rotor

analysisA77-naaao

TAHDEBPLAATS, S. B.The computer for design and optimization

A77-46136VAB600L, B. F. C.

The need of stick force stability forattitude-stabilized aircraft, part 1[B1R-TB-75125-0] F77-31180

VABIAKOJIS, T.Compliance with amended FAR 25.1309 - DC-10 case

history[ A I A A PAPER 77-1257] A77-05510

VABVATSIS, A. D.Foundation of the magnetic field integral equation

code for the calculation of the electromagneticpulse external interaction with aircraftIAD-A039953] H77-31389

VAOSE, C. B.Acoustically swept rotor

[HASA-CASE-ABC-11106-1 ] H77-31130

B-13

?BITEBGBOBBB. J. I. PEESOHiL AOTBOB IBDBX

VBITEB6BDBEB, J. E.Design criteria for aircraft warning, caution and

advisory alerting systems[AIAA PAPBB 77-1240] A77-44332

VITBB. P. i.Ways of increasing the resources /potential lives/

of gas turbine enginesA77-47472

»OB 6LAHB, 0.OT« noise correlation for several nozzle/wing

geometries asing a 5:1 slot nozzle with externaldeflectors

A77-44461

wVAGBBB. B.

Systematic pressure distribution and forcemeasurements of two yawed slender vings[IFD-2/76/I] H77-30095

A method for calculating flov around a yavedslender ving at snail angle of attackfIFD-4/76] H77-30096

Some quadrature methods for lifting ving theory[IFD-S/76] H77-30097

•AHI, H. K.An extended prediction model for airplane brakingdistance and a specification for a total brakingprediction systems, volnne 2[AD-A039967] N77-30476

BABBEH. S. B.An extended prediction model for airplane braking

distance and a specification for a total brakingprediction systems, volume 2[AD-A039967] B77-30476

BASHIZU, K.Application of the finite element techniquecombined vith the collocation method to subsoniclifting surface problems

A77-4/7537BASSOB. B. B.

Results of a feasibility study to add canards andADEH nozzle to the TF-17[AIAA PAPEB 77-1227] A77-45506

BAILEE, J. F., JB.Feasibility demonstration of the earth referenced

maneuvering flight path display[AIAA PAPEB 77-1111] A77-45171

WATTS. J. C.Airworthiness and flight characteristicsevaluation C-12A aircraft[AD-A040239] H77-31136

WEATBBBILL. S, B.Application of a finite difference method to the

analysis of transonic flov over oscillatingairfoils and vings

B77-31090iEAVBB. J. A.

CB-47 mediam lift helicopter effectivenessevaluation program ran book[AD-A041162] H77-31KI2

BEIBSTEIB. I.Heat-transfer and pressure measurements on a

simulated elevon deflected 30 deg near flightconditions at Bach 7[BASA-TB-X-3563] H77-31440

IELLFOBD, I. C.Application of finite element approach totransonic flov problems

A77-47539BBILFOBD, 1. C.. JB.

Hixed finite element models and dual iterativemethods for transonic flov

A77-47543WEIABT, J. P.

The potential role of technological modificationsand alternative fuels in alleviating Air Forceenergy problems[AD-A039597] B77-30261

BHITTBB, t. D.Vectored-engine-over-ving configaration design[AIAA PAPEB 77-1228] A77-45507

ilLBI, J. F.Coherence and phase technignes applied to noise

diagnosis in the BASA Ames 7 times 10-foot windtunnel no. 1[BASA-CB-152039] H77-30905

BILKIBSOB, 0. B.Development of a small, low cost turbojet engine

with thrust augmentationA77-47347

BILLIABS, J. G.Analysis/theory of controlled configured structures

[ A I A A PAPEB 77-1212] A77-44316BILLIABS, I. 3.

Advanced turboprop technology development[AIAA PAPBB 77-1223] A77-44324

Advanced turboprop technology development[BASA-TH-73729] H77-31155

ilLLIAHS, B. H.Generalized Iheodorsen solution for singular

integral equations of the airfoil classA77-449U6

•ILLS, C. B.Bain rotor wake/tail rotor interaction

•IHELEB, B. B.Bultiple Drone Control development

A77-473158IHSOB. C. A.

General principles of automatic TT trackersA77-44812

BOiB, C. J.Optimum acoustic design of free-running lo» speed

propellers[AIAA PAPEB 77-1248] A77-44337

Propeller study. Part 2: The design ofpropellers for minimum noise[BASA-CB-155005] B77-31157

•OLFE, B. L., JB.Development of a small, lov cost turbojet engine

with thrust augmentationA77-47347

SOLOBICZ. C. B.An improved free ving for an aircraft

[BASA-CASE-FBC-10092-1 ] H77-31135BOODBET, B. «.

Vectored-engine-over-ving configuration design[AIAS PAPEB 77-1228] A77-45507

BOODIABD, F. A.Investigations of three-dimensional flov

separation on fuselage configurations[AD-A039382] H77-30421

100BBB. C.A program for increased flight fidelity in

helicopter simulation[AD-A039234] H77-30108

4BI6BT, B. B.Development of a small, lov cost turbojet engine

vith thrust augmentationA77-47347

BDEST. «.The calculation of flov fields about three

dimensional bodies in high altitude(free-molecular flov of neutral atoms)[DLB-FB-75-45] H77-30922

BIATT, F. G.F-8 oblique wing structural feasibility study

[HASA-CB-154841] H77-30107

IABBBODGH, S. B.A-7 titanium nose gear development

A77-46801IBB. F.

The 3-D stress analysis of a turbine blades[AD-A039176] H77-30481

TEBBOBY, P. A.Gas turbine pover for large hovercraft

A77-46412IOSHIHABA, B.

The transonic oscillating flap: A comparison ofcalculations vith experiments

N77-31086TOST, J. B.

' Emergency-power benefits to multi-engine helicoptersA77-44515

ZKLAZBI, S. I.Bumerical solution of complete flovs around

external stores[AD-A039213] B77-30422

B-14

PEBSOBAL AOIBOB IBDEI ZVAAIEVELD, J.

ZHEBCBOZBIH, B. A.Soviet aircraft and rocketsCHASA-TT-F-770] H77-30065

ZIEGIBB, B.Rave drag redaction for aircraft faselage-winqconfigarations. Volume 1: Analyses and resultsTAD-A011C997] H77-32012

Rave drag reduction for aircraft fuselage-wingconfigarations. Volune 2: flanual for conpnterprograms[AD-AOQC998] H77-32013

ZIBSIG, D. B.Advanced avionics for the Advanced Bemotely

Piloted Vehicle /ABPV/A77-47350

ZIBAB, IA. L.Aircraft laboratories and experience in using then

for the developaent of methods and means ofremote sensing of earth resources

A77-97199Space experiment simulation using an aircraft

laboratoryA77-U7200

ZIBEBAT, B.& special-purpose pocket calculator for aviation

and maritime navigationA77-i( 11571

ZIBBBBBAB, B.

Experience gained in adjusting the mathematicalmodel of the VPi 614 short-haul aircraft by useof measured eigenfreguenco.es

A77-U5391ZIBBEBBAHH, H.

Airframe response to separated flow on the shorthaul aircraft VFH 611

H77-31081ZBAKET, C. A.

Complementary roles for BPVs in support oftactical manned aircraft

A77-4733HZOCHOBICZ. K.

Static electricity in aviation and vays ofaverting its effects

A77-16349ZHA&HEVELD. J.

Aerodynamic data and off-design characteristics ofthe modified quasi-elliptical airfoil sectionSLB 7101[NLB-TB-76012-a} H77-30094

B-15

CONTRACT NUMBER INDEXAERONAUTICAL ENGINEERING IA Special Bibliography (Suppl 90)

Typical Contract Number Index Listing

DECEMBER 1977

SAS2-9177 B77-11064

ICONTRACT NASA ACCESSIONNUMBER NUMBER

Listings in this index are arranged atphanumencally by contract numberUnder each contract number the accession numbers denoting documentsthat have been produced as a result of research done under that contractare arranged in ascending order with the IAA accession numbers appearing•first The accession number denotes the number by which the citation isidentified in either the lAAot STARsec\\on

AF PBOJ. 1987877-30116

AF PBOJ. 3066H77-30121

AF PBOJ. 3145H77-31162

IP PBOJ. 7231H77-31110N77-31922

iP PBOJ. 7381S77-30219

AF PBOJ. 8219H77-30135

AP-APOSB-2916-76H77-31173

AF-AFOSB-2961-76B77-31384

ABPA OBDEB 1910H77-31099

DA PBOJ. 1G1 -62207- JS-72H77-30480

DAAB07-75-00906H77-31126

DAAB07-75-C-1366A77-47354

DAAG46-75-C-0072B77-30481

DAAH01-76-C-0396H77-30115

DAAJ01-75-C-0448877-30074

DAAJ02-69-C-0042B77-30480

DAAJ02-75-C-0036B77-30421

DAAJ02-76-O0039A77-47346

DBA001-75-C-0038H77-31218

DOT-OST-PS-70292N77-31113

E(29-1)-789 B77-30104E<49-18)-2087

A77-16621EPA-B-802650 A77-44824F4460-75-C-0003

B77-30422F08635-76-C-0117

H77-30092P29601-75-C-0067

N77-31389F33615-67-C-1912

H77-31110P33615-72-C-1052

A77-i|<l816F33615-73-C-3013

H77-30135F33615-73-C-5066

A77-16838F33615-711-C-2007

H77-31172F33615-7«-C-3039

A77-U6851P33615-7a-C-5065

B77-302«9

P33615-75-C-20H1P77-31162

F33615-75-C-2033H77-31171

F33615-75-C-5052H77-31168

F33615-75-C-5289N77-31108

F33615-75-D-1125A77-47350

F3361S-76-C-0122B77-311U1

P33615-76-C-05071177-31170S77-31922

F33615-76-C-2009N77-31161

F33615-76-C-2019H77-31507

F33615-76-C-2068H77-30121

F33615-76-C-21»7H77-31529

F33615-76-C-3051B77-30116

F33657-74-C-0129H77-30U76

F33657-75-C-0518A77-17319H77-31116

F36615-74-C-3066A77-11816

FH4620-76-C-0072N77-30131

FU4620-76-C-0081H77-31516

F49620-77-C-0023H77-30261H77-31331

HAS1-I4246 A77-«I7539HAS1-11513 H77-31133HAS1-13500 S77-31091HAS1-13786 A77-U75H2HAS1-11056 H77-30088HAS1-11420I1 H77-31090NAS1-1U327 H77-30180NAS2-6111 B77-30132HAS2-8382 N77-30905HAS2-88147 B77-30086BAS3-20046 B77-31119NAS4-2266 B77-30107BAS7-100 A77-UI11I27NATO PROJECT 823

A77-»7510BG1-22-009-124

A77-l(6621HGB-05-003-471

B77-31005HGB-1U-005-19II

A77-a<l337H77-31156N77-31157877-31158

BGB-17-002-072A77-a»319

SGB-31-001-197A77-4U916

BGB-36-009-017877—3010 1

HIVB-1723 877-30091SIVB-17115 877-31179

877-31180SB PBOJ. 062—481

B77-31099BB PBOJ. 337-076

877-30103SBC A-1942 A77-47218BSP GK-32626 A77-47005BSG-1079 877-30085BSG-1083 A77-45508SSG-1143 877-30444

877-31537HSG-3045 877-311488SG-3048 A77-46614B00014-67-A-01 51-0029

877-31169H00014-68-A-04 02-0008

A77-47005B00014-72-C-0101

877-30100H00014-75-C-0507

B77-31169B00014-75-C-0639

B77-30103J00010-75-C-0763

B77-31099H00014-76-C-1411

477-45506B62269-75-C-0537

877-32012877-32013

U62269-76-C-0198877-30118

H62269-76-C-0254B77-30120

HB-HLI>-1973-1.1877-31179

BB-BLD-1975-1. 1B77-31180

SD-321 877-31139505-04 877-30089505-OU-32 877-31148505-05 H77-31153

877-31154505-08-22 B77-30129505-08-31-01 877-31134505-10-11-02 877-31072505-10-21-01 877-30088505-10-23 S77-31174

S77-31175505-10-41 877-30906505-11-21-03 877-31093505-11-31-02 B77-3M40513-52-01-16 877-31125791-40-08-01 877-31094

C-1

1 Report No

NASA SP-7037 (90)

2 Government Accession No. 3 Recipient's Catalog No

4. Title and Subtitle

AERONAUTICAL ENGINEERINGA Special Bibliography (Supplement 90)

5 Report DateDecember 1977

6 Performing Organization Code

7 Author(s) 8 Performing Organization Report No.

10 Work Unit No

9 Performing Organization Name and Address

National Aeronautics and Space AdministrationWashington, D. C. 205̂ 6

11 Contract or Grant No

13 Type of Report and Period Covered

12 Sponsoring Agency Name and Address

14 Sponsoring Agency Code

IS. Supplementary Notes

16. Abstract

This bibliography lists 351 reports, articles, and other documentsintroduced into the NASA scientific and technical information systemin November 1977.

17. Key Words (Suggested by Author(sl)

AerodynamicsAeronautical EngineeringAeronauticsBibliographies

18 Distribution Statement

Unclassified - Unlimited

19. Security Oassif. (of this report)

Unclass ified20 Security Classif (of this page)

Unclass i f ied21. No of Pages

112

22 Price*

$^.75 HC

For sale by the National Technical Information Service, Springfield, Virginia 22161NASA-Langley, 1978

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An extensive collection of NASA and NASA-sponsored publications is maintained by the British LibraryLending Division. Boston Spa, Wetherby, Yorkshire. England By virtue of arrangements other than withNASA, the British Library Lending Division also has available many of the non-NASA publications citedm STAR European requesters may purchase facsimile copy or microfiche of NASA and NASA-sponsoreddocuments, those identified by both the symbols "ft" and "*". from ESRO/ELDO Space DocumentationService. European Space Research Organization. 114, av Charles de Gaulle. 92-Neuilly-sur-Seme.

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