Ring Erur Ineering Aeronautical Engir

Aeronautical NASA SP-7037 (125) Engineering August 1980 A Continuing NASABibliography with Indexes

National Aeronautics and Space Administration CPcopY Ae.Fl.,..,xflaLlhCal Enaineer!ngAei ring Erur ineering Aeronautical Engir :al Engineering Aeronautical I iautical EngineeringAeronau rl Engineering Mr bring Aeronautical Engineerin gineering Aeronautical Engimn al Engineering AeFut autr.al Engineering Ae Ui "X^M^utical Engineering Mn ring Aeronautical Engineerinc ACCESSION NUMBER RANGES

Accession numbers cited in this Supplement fall within the following ranges.

STAR (N-10000 Series) N80-22255 N80-24258

IAA (A-10000 Series) A80-32627 - A80-36306

This bibliography was prepared by the NASA Scientific and Technical Information Facility operated for the National Aeronautics and Space Administration by PRC Data Services Company. NASA SP-1037(125)

AERONAUTICAL ENGINEERING

A Continuing Bibliography

Supplement 125

A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in July 1980 in • Scientific and Technical Aerospace Reports (STAR) • International Aerospace Abstracts (/AA).

Scientific and Technical Information Branch 1980 NASA National Aeronautics and Space Administration Washington, DC This supplement is available as NTISUB/141/093 from the National Technical Information Service (NTIS). Springfield, Virginia 22161 at the price of $5.00 domestic: $10.00 foreign. INTRODUCTION

Under the terms of an interagency agreement with the Federal Aviation Administration this publication has been prepared by the National Aeronautics and. Space Administration for the joint use of both agencies and the scientific and technical community concerned with the field of aeronautical engineering. The first issue of this bibliography was published in September 1970 and the first supplement in January 1971. Since that time, monthly supplements have been issued. This supplement to Aeronautical Engineering -- A Continuing Bibliographi' (NASA SP-7037) lists 407 reports, journal articles, and other documents originally announced in July 1980 in Scientific and Technical Aerospace Reports (STAR) or in International Aerospace Abstracts (IAA). The coverage includes documents on the engineering and theoretical aspects of design, construction, evaluation, testing, operation, and performance of aircraft (including aircraft engines) and associated components, equipment, and systems. It also includes research and development in aerodynamics, aeronautics, and ground support equipment for aeronautical vehicles. Each entry in the bibliography consists of a standard bibliographic citation accompanied in most cases by an abstract. The listing of the entries is arranged in two major sections, IAA Entries and STAR Entries, in that order. The citations, and abstracts when available, are reproduced exactly as they appeared originally in IAA and STAR, including the original accession numbers from the respective announcement journals. This procedure, which saves time and money, accounts for the slight variation in citation appearances. Three indexes -- subject, personal author, and contract number -- are included. An annual cumulative index will be published. AVAILABILITY OF CITED PUBLICATIONS

IAA ENTRIES (A80-10000 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 of accessions are available at $7.00 per document up to a maximum of 40 pages. The charge for each additional page is $0.25. Microfiche 1 1 of documents announced in /AA are available at the rate of $3.00 per microfiche on demand, and at the rate of $1.25 per microfiche for standing orders for all IAA microfiche. The price for the /AA microfiche by category is available at the rate of $1.50 per microfiche plus a $1.00 service charge per category per issue. Microfiche of all the current AIAA Meeting Papers are available on a standing order basis at the rate of $1.50 per microfiche.

Minimum air-mail postage to foreign countries is $1.00 and all foreign orders are shipped on payment of pro-forma invoices.

All inquiries and requests should be addressed to AIAA Technical Information Service. Please refer to the accession number when requesting publications.

STAR ENTRIES (N80-10000 Series)

One or more sources from which a document announced in STAR is available to the public is ordinarily given on the last line of the citation. The most commonly indicated sources and their acronyms or abbreviations are listed below. If the publication is available from a source other than those listed, the publisher and his address will be displayed on the availability line or in combination with the corporate source line.

Avail: NTIS. Sold by the National Technical Information Service. Prices for hard copy (HC) and microfiche (MF) are indicated by a price code followed by the letters HC or MF in the STAR citation. Current values for the price codes are given in the tables on page Viii.

Documents on microfiche are designated by a pound sign (#) following the accession number. The pound sign is used without regard to the source or quality of the microfiche.

Initially distributed microfiche under the NTIS SRIM (Selected Research in Microfiche) is available at greatly reduced unit prices. For this service and for information concerning subscription to NASA printed reports, consult the NTIS Subscription Section, Springfield, Va. 22161.

NOTE ON ORDERING DOCUMENTS: When ordering NASA publications (those followed by the * symbol), use the N accession number. NASA patent applications (only the specifications are offered) should be ordered by the US-Patent-Appl-SN number. Non-NASA publications (no asterisk) should be ordered by the AD, PB, or other report number shown on the last line of the citation, not by the N accession number. It is also advisable to cite the title and other bibliographic identification.

Avail: SOD (or GPO). Sold by the Superintendent of Documents, U.S. Government Printing Office, in hard copy. The current price and order number are given following the availability lipe. (NTIS will fill microfiche requests, at the standard $3.50 price, for those documents identified by a symbol.)

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

lv Avail: NASA Public Document Rooms. Documents so indicated may be examined at or purchased from the National Aeronautics and Space Administration, Public Documents Room (Room 126). 600 Independence Ave.. S.W., Washington, D.C. 20546, or public document rooms located at each of the NASA research centers, the NASA Space Technology Laboratories, and the NASA Pasadena Office at the Jet Propulsion Laboratory.

Avail: DOE Depository Libraries. Organizations in U.S. cities and abroad that maintain collections of Department of Energy reports, usually in microfiche form, are listed in Energy Research Abstracts. Services available from the DOE and its depositories are described in a booklet. DOE Technical Information Center - Its Functions and Services (TID-4660), which may be obtained without charge from the DOE Technical Information Center.

Avail: Univ. Microfilms. Documents so indicated are dissertations selected from Dissertation Abstracts and are sold by University Microfilms as xerographic copy (HC) and microfilm. All requests should cite the author and the Order Number as they appear in the citation.

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

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

Avail: BLL (formerly NLL): British Library Lending Division, Boston Spa, Wetherby, Yorkshire, England. Photocopies available from this organization at the price shown. (If none is given, inquiry should be addressed to the BLL.)

Avail: Fachinformationszentrum, Karlsruhe. Sold by the Fachinformationszentrum Energie. Physik. Mathematik GMBH. Eggenstein Leopoldshafen, Federal Republic of Germany, at the price shown in deutschmarks (DM).

Avail: Issuing Activity, or Corporate Author, or no indication of availability. Inquiries as to the availability of these documents should be addressed to the organization shown in the citation as the corporate author of the document.

Avail: U.S. Patent and Trademark Office. Sold by Commissioner of Patents and Trademarks. U.S. Patent and Trademark Office, at the standard price of 50 cents each, postage free.

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

V GENERAL AVAILABILITY

All publications abstracted in this bibliography are available to the public through the sources as indicated in the STAR Entries and IAA Entries sections. It is suggested that the bibliography user contact his own library or other local libraries prior to ordering any publication inasmuch as many of the documents have been widely distributed by the issuing agencies, especially NASA. A listing of public collections of NASA documents is included on the inside back cover.

SUBSCRIPTION AVAILABILITY

This publication is available on subscription from the National Technical Information Service (NTIS). The annual subscription rate for the monthly supplements is$50.00 domestic; $100.00 foreign. 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 Aeronautics Pendragon House, Inc. and Astronautics 899 Broadway Avenue Technical Information Service Redwood City, California 94063 555 West 57th Street, 12th Floor New York, New York 10019 Superintendent of Documents U.S. Government Printing Office British Library Lending Division, Washington, D.C. 20402 Boston Spa, Wetherby, Yorkshire. England

University Microfilms Commissioner of Patents and A Xerox Company Trademarks 300 North Zeeb Road U.S. Patent and Trademark Office Ann Arbor, Michigan 48106 Washington, D.C. 20231

Department of Energy University Microfilms, Ltd. Technical Information Center Tylers Green P.O. Box 62 London, England Oak Ridge, Tennessee 37830

U.S. Geological Survey ESA-Information Retrieval Service 1033 General Services Administration ESRIN Building Via Galileo Galilei Washington, D.C. 20242 00044 Frascati (Rome) Italy

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

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

National Aeronautics and Space U.S. Geological Survey Administration Bldg. 25, Denver Federal Center Scientific and Technical Information Denver, Colorado 80225 Branch (NST-41) Washington, D.C. 20546 Fachinformationszentrum Energie, Physik, National Technical Information Service Mathematik GMBH 5285 Port Royal Road 7514 Eggenstein Leopoldshafen Springfield, Virginia 22161 Federal Republic of Germany

vii NTIS PRICE SCHEDULES

Schedule A STANDARD PAPER COPY PRICE SCHEDULE

)Effective January 1. 1980)

Pflc. P.. Rans Now Ain..Ices Forelp Price Pño. AOl Microfiche S 3.50 $ 5.25 A02 001- 02 5 500 1000 A03 026-050 6.00 12.00 404 051-075 7.00 14,00 A05 076-100 8.00 1600 A06 101-125 9.00 18.00

Aol 126-150 1000 20,00 A08 151-175 11,00 2200 A09 176-200 12,00 24.00 AlO 201-225 13,00 26.00 All 226-250 14.00 28.00

Al2 251-215 15.00 30.00 A13 276-300 16.00 32.00 A14 301-325 17.00 34,00 A15 326-350 18.00 36.00 A16 351-375 1900 38.00

All 376-400 2000 40,00 A18 401425 21.00 42,00 A19 426-450 22,00 44,00 A20 451-475 ' 23.00 46,00 A21 476-500 24,00 48.00

A22 501-525 25.00 50.00 A23 526-550 26.00 5200 A24 551-575 27.00 54,00 A25 576-600 28.00 56.00 A99 601-up '- 1/ -- 2/

1/ Add $100 for each additional 25 page increment or portion thereof for 601 pages up

2/ Add $2.00 for each additional 25 page increment or portion thereof for 601 pages and more

Schedule E EXCEPTION PRICE SCHEDULE Paper Copy & Microfiche

Is North AmsnIc.n Fo,.ign Cod. Price Price E01 S 5.50 $ 11,50 E02 6.50 13.50 E03 8.50 17.50 604 10,50 21,50 E05 12.50 25.50

E06 14,50 2950 607 16.50 33.50 E08 1850 37,50 609 20.50 41.50 610 22.50 45,50

Eli 24.50 49.50 E12 27.50 55.50 E13 30.50 61.50 614 33.50 67.50 E15 36.50 7350

616 39.50 79,50 E17 42.50 85.50 E18 45.50 91.50 E19 50.50 10050 620 60.50 121.50

E99 - Write for quote NOl 28.00 40.00

VIII

TABLE OF CONTENTS

IAA Entries ...... 319 STAR Entries ...... 345

Subject Index ...... A-i Personal Author Index ...... B-i Contract Number Index ...... C-i

TYPICAL CITATION AND ABSTRACT FROM STAR

NASA SPONSORED DOCUMENT AVAILABLE ON MICROFICHE NASA ACCESSIO j' N8O'10148# Northwestern Univ.. Evanston. Ill. Transportation NUMBER ______Center. FACTORS AFFECTING THE RETIREMENT OF COM- CORPORATE MERCIAL TRANSPORT JET AIRCRAFT SOURCE - Frank A. Spencer Aug. 1979296 p refs TITLE ' (Grant NsG-2149) - Avail NTIS HC A13/MF AOl CSCLO1C .a PUBLICATION The historical background of the technology and economics DATE AUTHOR of aircraft replacement and retirement in the prejet era is reviewed I I in order to determine whether useful insights can be obtained applicable to the jet era. Significant differences between the AVAILABILITY CONTRACT two periods are noted. New factors are identified and examined. SOURCE OR GRANT J Topics discussed include concern over current policies regarding deregulation, regulatory reform, and retroactive noise regulations; financing and compliance legislation; aging; economic environment REPORT and inflation, technological progress; fuel efficiency and cost; COSATI NUMBER and a financial perspective of replacement decisions. A.R.H. CODE

TYPICAL CITATION AND ABSTRACT FROM IAA

AVAILABLE ON V MICROFICHE AIAA ACCESSION A80-10196 /1 Effect of flow swirling on heat transfer in the NUMBER i-.- cylindrical part of the prenozzle volume of a model chamber (Vliianie zakrutki potoka na teplootdachu v tsiliodricheskoi chasti TITLE ______predsoplovogo obema model'noi kamery). F. I. Sharafutdinov, A. I. - AUTHORS Mironov, and V. K. Shchukin (Kazanskii Aviatsionnyi Institut,______Kazan, USSR . /nzhen&no.Fizicheskii Zhurna/, vol. 37, Oct. 1979, AUTHORS TITLE OF p. 595. 601 8 refs, In Russian. AFFILIATION PERIODICAL Experimental results are presented on the hydrodynamics and heat transfer in swirling flow in a short orificed tube with PUBLICATION straight-blade turbilizers. Data are correlated by the local simulation DATE method, employing the maximum axial component of wall gas velocity and the torque momentum/axial momentum ratio at the turbilizer outlet. B.J.

IX AERONAUTICAL

ENGINEERING A Continuing Bibliography (Suppl. 125)

AUGUST 1980

electronic, and radar systems. The technology of system production, IAA ENTRIES assembly, and installment is outlined. V. P.

A80-32860 ,9 Advanced rotorcraft noise. H. Sternfeld, Jr. A80-32682 Predictive guidance for interceptors with time (Boeing Vertol Co.. Philadelphia, Pa.). American Fnstithte of Aero- lag in acceleration. C. Hecht (Aerospace Corp., Guidance and Control nautics and Astronautics, International Meeting and Technical Div., El Segundo, Calif.) and A. Troesch (Southern California, Display on Global Technology 2000, Baltimore, Md., May 6-8, 1980, IEEE Transactions on Automatic University, Los Angeles, Calif.). Paper 80-0857. 9 P. 21 refs. Control, vol. AC-25, Apr. 1980, p. 270-274. 5 refs. Contract No. The paper discusses improving helicopter rotor design to effect F4701-77-C-0078. noise reduction. A review of the types and origins of helicopter rotor Predictive guidance equations for systems with time delays are noise is presented, and the aerodynamic environment of the developed using optimal control theory to obtain interceptor steering helicopter main rotor, fundamental principles of the rotary wing, and gains. The time response of the interceptor is approximated by a broadband noise sources are considered. Emphasis is placed on the linear first-order time lag, and the optimal steering gain is evaluated fact that the main influence on rotor noise is tip speed: slowing the using a quadratic penalty function. The optimal control for rotor would reduce noise, but will require wider chord blades and/or interception is determined to be a linear function of the predicted a larger number of blades per rotor, and, in effect, increased weight position error and the acceleration error. Computer simulations and reduced payload. Attention is given to the multispeed rotor, demonstrate a significant improvement of interceptor performance. rotor blade airfoils, tip shapes, and sweep of the entire blade section (Author) rearward. In addition, tail rotor noise is considered, as is the tilt rotor and the blade-vortex separation of the tandem rotor helicopter. A80-32693 Flight control systems. VII. B. R. A. Burns J.P.B. (British Aerospace, WARTON Div., Preston, Lancs., England). Air International, vol. 18, May 1980, p. 229-232, 260. The article traces the development of flight control systems and A80-32861 Some unique characteristics of supersonic describes the various functions of flight control systems, leading to a cruise vehicles and their effect on airport community noise. C. Driver modern full time fly-by-wire system. Attention is given to the need and D. J. Maglieri (NASA, Langley Research Center, Hampton, Va.). for a fuel system with power controls, as well as the topics of American Institute of Aeronautics and Astronautics, International autostabilization and large authority autostabilization. Also discussed Meeting and Technical Display on Global Technology 2000, Balti- are electric signalling, fly-by-wire, and control configured flight. more, Md., May 6-8, 1980, Paper 80- 0859. lop. 23 refs. Finally, future control systems are examined. M.E.P. The paper examines the differences between the supersonic and subsonic commercial aircraft in terms of their configuration, aero- A80-32759 Minimum sensitivity controllers with applica- dynamic characteristics, propulsion systems, and the manner of tion to VTOL aircraft, V. Gourishankar (Alberta, University, operation. The unique characteristics of supersonic cruise vehicles Edmonton, Canada) and G. V. Zackowski (Department of National should provide improved airport-community noise exposures if the Defence, Ottawa, Canada). IEEE Transactions on Aerospace and vehicle is permitted to operate at its most efficient and effective Electronic Systems, vol. AES-16, Mar. 1980, p. 217-226. 7 refs. flight modes. It is concluded that noise exposure levels for supersonic National Research Council of Canada Grant No. A-3322. cruise vehicles can be comparable to those of its equivalent subsonic A technique is described for the design of a fixed-gain feedback counterpart of that time period. A.T. controller for a vertical takeoff and landing (VTOL) aircraft which minimizes the effect of arbitrary variations in the aircraft dynamics A80-32876 # The future of civil turbo-fan engines. A. G. on aircraft performance over varying flight conditions. The design Newton and J. F. Coplin (Rolls-Royce, Ltd., Aero Div., Derby, method involves the assignment of the eigenvalues of the aircraft England(. American Institute of Aeronautics and Astronautics, model to prescribed locations in the complex plane and the minimization of their sensitivities to model parameter variations. International Meeting and Technical Display on Global Technology 2000, Baltimore, Md., May 6-8, 1980, Paper 80-0893. 11 p. This controller is shown to possess better tracking and regulating The paper describes the methods by which the current perfor- capabilities than another fixed-gain controller designed merely for mance of civil turbo-fan engines has been achieved, with special assignment of eigenvalues using nominal parameter values, without emphasis on the work being undertaken for the future. The any consideration of their sensitivity to plant parameter variations. discussion covers the importance of fuel efficiency; optimization for (Author) low airline costa; the RB 211 3-shaft turbo-fan engine design objectives; the 3-shaft concept; modular development; engine fuel A80-32845 # Aircraft radio equipment adjustment and efficiency; historic trends in specific fuel consumption, specific maintenance technology (Tekhnologiia remonta radiooborudovaniia weight and thrust; new engine designs; cost-effective and energy- letatel'nykh apparatov). lu. N. Kalashnikov and L. M. Fedotov. efficient engine; hollow titanium fan; Kevlar containment; unshroud- Moscow, lzdatel'stvo Mash inostroenie, 1979. 248 p. 50 refs. In ed HP turbine; LP/IP turbine module; core compressor technology; Russian. exhaust mixing; combustion technology; building blocks in the This textbook deals essentially with the major aspects of fuel-efficient engine technology program; low specific thrust for training personnel to operate, maintain, and repair aircraft radio, improved fuel consumption; prop-fan and related problems; small/

319

A80-32882

intermediate engines; and future fuel situation where worthwhile American Institute of Aeronautics and Astronautics, International gains are achievable. S. D. Meeting and Technical Display on Global Technology 2000, Balti- more, Md., May 6-8, 1980, Paper 80- 0935. 13 p. 20 refs. A80-32882 # Long range very large aircraft supply system The technology requirements for designing, manufacturing and for civil/military application with special emphasis on water-based operating any vehicle depend largely on the configuration of that aircraft. C. Dornier. Jr. (Domier GmbH, Friedrichshafen, West vehicle. Under the general heading of Very Large Aircraft (VLA), Germany). American Institute of Aeronautics and Astronautics, configurations are many and varied, so, therefore, are the technology International Meeting and Technical Display on Global Technology requirements. The present work is limited to technology require- 2000, Baltimore, Md., May 6-8, 1980, Paper 80-0903. 11 p. 6 refs. ments of particular interest to VLA. While many are of common Very large transport aircraft appear to be indispensable for both interest, a few technology requirements critical to specific VLA civil and military use in the 1990s. The paper discusses parameters types are also covered. Addressed in turn are common VLA concerns for the design of very large aircraft supply systems (VLASSs), for and how they influence configurations and technology; the method- civil and military markets, concept of a VLASS, and project ology followed in selecting requirements and assessing readiness; the realization. The water-based aircraft has advantages over the land- resultant technology requirements and readiness; and some overall based aircraft because it is, to a large extent, independent of an observations regarding technology areas judged to be particularly infrastructure. The kite configuration seems to be the best solution. critical. Over 50 technology requirements are identified as unique or VLASS with a takeoff weight of the order of 1000 t appear to be a particularly critical to VLA. However, none of the requirements is future necessity, both for civil and military operations. Such a considered to have an excellent state of technology readiness. S. D. system could drastically reduce military deployment times and contribute to the credibility of deterrence. S.D. A80-32898 # Advanced high speed commercial aircraft - 2000. A. L. Maxwell and L. V. Dickinson, Jr. (U.S. Congress, Office A80-32887 • # Aeropropulsion in year 2000. R. J. Weber of Technology Assessment, Washington, D.C.). American Institute of (NASA, Lewis Research Center, Cleveland, Ohio). American Institute Aeronautics and Astronautics, International Meeting and Technical of Aeronautics and Astronautics, International Meeting and Tech- Display on Global Technology 2000, Baltimore, Md., May 6-8, 1980, nical Display on Global Technology 2000, Baltimore, Md., May 6-8, Paper 80-0937. 9 p. 10 refs. 1980, Paper 80-0914, 11 p. 5 refs, The potential of introducing advanced high-speed commercial The paper demonstrates that many advances can be anticipated transports is examined on technological, energy, economics and in propulsion systems for aircraft in the next 20 years. A survey is environmental bases in the 2000 timeframe. Emphasis is placed on presented of probable future engine types, including convertible subsonic and supersonic aircraft for the transoceanic market. The engines for helicopters, turboprops for fuel efficient airliners, and most compelling argument for an advanced supersonic transport variable cycle engines for supersonic transports. Also examined is the (AST( is improved aircraft productivity-seat-miles generated by an use of rotary engines in general aviation aircraft. Finally, a review is aircraft per unit time. Societal concerns about AST are also given of related technology improvements in propellers, materials, discussed. S. D. noise suppression, and digital electronic controls. M.E.P, A80-32899 # Air transportation 2000- A challenge for new A80-32888 # Technology requirements as derived from acci- technology. A. Abraham (Deutsche Lufthansa AG, Frankfurt am dent rate analysis. W. Graham (Questek, Inc., Centerport, N.Y.). Main, West Germany). American Institute of Aeronautics and American Institute of Aeronautics and Astronautics, International Astronautics, International Meeting and Technical Display on Global Meeting and Technical Display on Global Technology 2000, Balti- Technology 2000, Baltimore, Md., May 6-8, 1980, Paper 80- 0945. 12 more, Md., May 6-8, 1980, Paper 80-0918. 11 p. P. The paper deals with air carrier approach and landing accidents, - The next generation of air transportation is discussed in terms of general aviation safety, and near midair collision analysis. The fuel, technology and the air transportation infrastructure. The exposure is unknown because no one attempts to keep track of the development of new fuel and combustion technologies are consid- relevant conditions in uneventful flights in which there were no ered, as well as future progress from engine manufacturers regarding accidents. The accident can be calculated whenever the exposure can higher propulsive efficiency. Attention is given to the potential for be estimated by direct or inferential methods. The estimated aerodynamic improvements in winglets, increased aspect ratios and accident rates suggest many ways in which technological improve- the provision of laminar flow by natural or artificial means. Also ments can contribute to safety. S. D. discussed are advanced flight avionics, the use of composite structures, and the improvements required in ground terminal installations. J.P.B. A80-32890 # Technology to increase airport capacity. R. M. Harris (Mitre Corp., Metrek Div., McLean, Va.). American Institute of Aeronautics and Astronautics, International Meeting and Tech- nical Display on Global Technology 2000, Baltimore, Md., May 6-8, A80-33105 # CLST's wing-in-ground effect vehicles (Ekra- noloty CLST). S. T. Czerniawskij. Technika Lornicza i Asrronau- 1980, Paper 80-0920. 6 p. 15 refs. U.S. Department of Transporta- tion Contract No. FA80WA-4370. tyczna, vol. 35, Mar. 1980, p. 5-12. In Polish. Technological approaches and operational procedures currently Experimental and conceptual designs of domestic and foreign under development by the FAA to increase airport capacities and wing-in-ground effect vehicles are reviewed. Comparisons of power efficiencies are summarized. Consideration is given to runway versus speed and weight are made, and some conclusions are drawn configuration management systems, separate short runways for concerning the future of wing-in-ground effect vehicle technology general aviation, dependent IF runway operations, specialized MLS and its applications. V. P. applications to such areas as missed approach situations, reductions in IFR final approach spacing and integrated flow management. It is A80-33106 # Selective methods of determining the range of concluded that more sophisticated levels of integrated flow manage- engine operation in aircraft crash investigations. I (Wybrane metody ment, starting from the current en route metering programs, will be okreslania zakresow pracy silnika podczas badania wypadkow lotni' required to obtain maximal terminal flow efficiency and system czych. I). S. Andruszkiewicz, J. Borgon, and M. Stukonis. Technika coordination. A.L.W. Lotnicza iAstronautyczna, vol. 35, Mar. 1980, p. 16-18. In Polish. The paper deals with methods of analyzing the state of an A80.32897 • # Technology requirements and readiness for aircraft engine at the moment preceeding a crash. The discussion very large aircraft. D. W. Conner and J. C. Vaughan, Ill (NASA, covers means of analyzing onboard recordings, analyzing the color of Langley Research Center, Systems Analysis Branch, Hampton, Va.(. oxide films at fracture surfaces, analyzing the state of blades and the

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mechanical properties of the metal, etc. Metallographic, X-ray, Vertica, vol. 4, no, 1, 1980, p. 29-41. 17 refs, spectral, and micrometric methods are examined. . V.P. The rough ride a helicopter endures is known to be self- generated. This roughness results in fatiguing blade loads and A80-33107 Al Numerical design and optimization of propel- vibration which can be eliminated or greatly reduced by multicyclic lers. II (Numeryczne projektowanie i optymalizacja smigiel. II). control. Rotor performance may also be improved. Several types of Technika Lotnicza iAstronautyczna, vol. 35, Mar. 1980. p. 25.28. In rotors which have employed multicyclic control are reviewed and Polish. compared. Their differences are highlighted and their potential The computer program under consideration incorporates two advantages and disadvantages are discussed. The flow field these subroutines, one of which defines the propeller characteristics while rotors must operate in is discussed, and it is shown that simultaneous the other uses a gradient technique to optimize these characteristics. elimination of vibration and oscillatory blade loads is not an inherent For illustration, the program is applied to the optimization of NACA solution to the roughness problem. The use of rotor blades and 4 propeller efficiency. V.P. energy absorbers is proposed. Input-output relations are considered and a gain control for ROMULAN, a multicyclic controlling computer program, is introduced. Implications of the introduction of A80-33108 # Problems involved in the detection of aircraft multicyclic systems into helicopters are also discussed. defects (Problemy wykrywania usterek samolotow), A. Kiezelis. (Author) Technika Lotnicza iAstronautyczna, vol. 35, Mar. 1980, p. 29-31. In Polish. A80-33135 Flight simulation techniques - The quest for The paper deals with methods of detecting faulty design realism. J. Rhea. High Technology, May 1980, p. 7-10. features, manufacturing defects, and malfunctions resulting from Computer image generation (CIG) techniques for simulating such defects or from improper operational conditions. Some factors flight situations in real time have been criticized for offering limited leading to defects are examined, and the influence of such factors as pictorial realism, The CIG techniques are reaching beyond flight the number and intervals of inspection, aircraft service time, number simulation into maritime training and commercial animation. Their of flight hours, and number of takeoffs and landings is examined. use has proven too expensive for automobile driver training and V. P. arcade games. Computer-generated images are accused of being too stylized, too cartoonish, too unnatural. Given that effective training A80-33121 Active control of rotor blade pitch for vibra- can be achieved with the real system in the real environment, it tion reduction - A wind tunnel demonstration. J. Shaw and N. follows that a simulation providing 100 percent realism would Albion (Boeing Vertol Co., Philadelphia, Pa). Vertica, vol. 4, no. 1, unquestionably provide effective training. New algorithms and 1980, p. 3-11.8 refs. improved hardware are complementing dynamic realism with tex- A. significant advance in the technology of helicopter rotor tures, contours and shadows. S. D. control has been demonstrated in the Boeing V/STOL Wind Tunnel. An automatic control system suppressed vibratory hub loads using A80-33177 # Navigation for a group of aircraft /Automation only small amounts of oscillatory swashptate motion. The closed of data processing and flight control procedures/ (Mezhsamoletnaia loop control system simultaneously suppressed up to 90% of the navigatsiia /Avtomatizatsiia zadach obrabotki dannykh i upravleniia 4/rev vertical force, pitching moment, and rolling moment of a poletom/). V. G. Tarasov. Moscow, lzdatel'stvo Mash inostroenie, 3.05-rn (10-ft( dia, four-bladed hingeless rotor. The system operated 1980. 184 p. 21 refs. In Russian. successfully in a wide range of flight conditions including transition In this book, the principles of designing group navigation and autorotation. Response time to cancel sudden changes of systems and subsystems are discussed, along with the theory of vibration level was very short, about two rotor revolutions. Thus the system automation. Particular attention is given to the synthesis of system will be able to suppress vibration of a flight vehicle even optimal and suboptimal algorithms for processing statistical data, during maneuvers and gusty conditions. The system, although generated by the information sources of the system, and to demonstrated on a hingeless rotor, is also applicable to articulated algorithms of guidance and control within a formation. The single and tandem rotor configurations. (Author) dynamics of an aircraft formation is examined. V. P.

A80-33122 Future of helicopter rotor control. M. Kretz and M. Larché )Giravions Dorand Industries, Suresnes, Hauts-de- A80.33274 • # Modern fluid dynamics of subsonic and transonic flight P. J. Bobbitt (NASA, Langley Research Center, Seine, France). (Netherlands Association of Aeronautical Engineers Subsonic-Transonic Aerodynamics Div., Hampton, Va.). American and National Lucht- en Ruimtevaartlaboratorium, European Rotor- Institute of Aeronautics and Astronautics, International Meeting and craft and Powered Lift Aircraft Forum, 5th, Amsterdam, Nether- Technical Display on Global Technology 2000, Baltimore, Md., May lands, Sept, 4-7, 1979.) Vertica, vol. 4, no. 1, 1980. 13-22. 7 refs. p. 6-8, 1980, Paper 80-0861. 39 p. 65 refs. The projection into the future of past achievements in the field The paper discusses a number of factors, termed research of rotor control shows an ever increasing use of feedback techniques drivers, which are expected to provide much of the stimulus for to extend the helicopter flight envelope. Limitations of the present research in the subsonic and transonic flight regimes in the coming monocyclic swashplate will have to be overcome by the use of new decade. The research drivers discussed comprise the need for energy types of control. The paper presents experimental and theoretical efficiency, new and improved facilities, better instrumentation, more results of research directed towards the extensive use of active capable and efficient computers, theoretical methodology refine- control. It discusses self-adaptive automatic systems for reducing ments, increased use of optimization techniques, and military vibration and stress levels at high load factors and high speeds. Tests requirements. Illustrations of advances in aircraft aerodynamics at on stall barrier feedback show the effectiveness of sensing the local subsonic and transonic speeds are presented, along with a discussion pressure distribution over the blades of a rotor to remove stall from the norma) working conditions of a rotor. Fast response action is of future research opportunities and trends. Particular attention is used to absorb aerodynamic disturbances and gust effects. Rotor given to airfoil and basic fluids research designed to reduce instabilities can be entirely eliminated. New types of control required skin-friction drag. S. D. by this technique result in the elimination of present swashplate and mechanical controls by the installation of fast-response electro- A80-33275 # Modern fluid dynamics of supersonic and hydraulic actuators on the rotating part of the rotor and by the hypersonic flight. R. L. Trimpi (NASA, Langley Research Center, introduction of electrical transmission of control signals. (Author) High-Speed Aerodynamics Div., Hampton, Va.). American Institute of Aeronautics and Astronautics, International Meeting and Techni- A80-33123 The promise of multicyclic control. J. L. cal Display on Global Technology 2000, Baltimore, Md., May 6-8, McCloud, Ill (NASA, Ames Research Center, Moffett Field, Calif.). 1980, Paper 80-0862. 37 p. 85 refs.

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Many aspects of fluid dynamics impacting supersonic and A80-33293 A matrix method for airport site evaluation. hypersonic flight are examined. Progress, current problem areas, and D. C. Koussios (Greek Air Force Academy, Athens, Greece). Airport prognostications for the future are discussed, with special emphasis Forum, vol. 10, Apr. 1980, p. 53-57. on those fluid dynamics facets which can be more directly tied to a The paper describes a site analysis procedure which can simplify potential end-product vehicle. Numerous illustrative examples are the choice of an airport location. The primary factor of the analysis included. S. D. is an airport location checklist matrix which provides a systematic, mathematical evaluation of proposed sites. V.T. A80-33276 II Theoretical investigation of the aerodynamics of double membrane sailwing airfoil sections. H. Murai (Tohoku University, Sendai, Japan) and S. Maruyama. Journal of Aircraft, vol. A80-33294 The importance of runway capacity . An 17, May 1980, p. 294-299. 11 refs. analytical approach. F. Collet (Service Technique des Bases Aêri- The sailwing has many special characteristics due to its flexible ennes; Ecole Nationale de l'Aviation Civile, Paris, Fiance). Airport structure. In order to estimate the sailwing performance theoretical- Forum, vol. 10, Apr. 1980, p. 63-66. 15 refs. ly, a numerical analysis method is presented for obtaining aero- The concept of runway capacity is discussed with emphasis dynamic characteristics and profile forms of a sailwing with a placed on term definitions. Attention is give to time elements, rounded leading edge and upper and lower individual surface shapes. average service and capacity times, and runway system configuration. The trailing edge is fixed and membranes are not stretched by V .T. tension although they have slackness. Through numerical examples, it is shown that a sallwing of this type has a completely different A80-33825 Gasdynamic analysis of gas-turbine combus- pressure distribution from that of a single membrane sailwing with a tion chambers with graduated air admission. G. N. Liubchik, V. A. leading edge of the circular cylinder or oval type. The latter has Khristich, and V. P. Kuts (Kievskii Politekhnicheskii Institut, Kiev, shape peaks in the pressure distribution which may have undesirable Ukrainian SSR). (Energetika, vol. 21, Mar. 1978, p. 68-74.) Fluid effects on the sailwing performance. These peaks in the pressure Mechanics - Soviet Research, vol. 8, July-Aug. 1979, p. 129-136. 7 distribution can be removed by adopting a 0-spar leading edge of refs. Translation. some kind. )Author) The paper analyzes the effects of heat transfer and mats flowrate on the gas dynamics of air flow in the constant-cross-section A80-33280 # Note on the yawing moment due to side slip chamber of a small gas-turbine power plant. The analysis is based on for swept-back wings. B. N. Pamadi and T. G. Pai (Indian Institute of equations of continuity, state and heat and is valid for low values of Technology, Bombay, lndia). Journal ofAircraft, vol. 17, May 1980, supercharging. B.J. p. 378-380. 6 refs. Babister (1961) has derived an expression for the yawing moment coefficient due to tide slip for sweptback wings having no A80-34154 Air Defense Ground environment - A case for dihedral. The present note points Out that the effect of the relative automation. J. M. Tellez (Hughes Aircraft Co., Fullerton, Calif.). In: change in dynamic pressure over the wings due to side slipping flow Military Electronics Defence Expo '79; Proceedings of the Con- should not be ignored, whereas Babister has disregarded it. This ference, Wiesbaden, West Germany, September 25-27, 1979. effect, demonstrated by a numerical example, can be quite large, Cointrin, Geneva, Switzerland, Interavia, S.A., particularly for highly sweptback wings. It is shown that the terms 1979, p. 34-53. not considered by Babister are important and their contribution to The principal operations in a manual Air Defense Ground wing yawing moment is quite significant. S. D. environment )ADGE) system are described as well as those in an automated ADGE system. The advantages to be obtained by automating the ground environment are summarized. The command and control functions which can derive significant benefits from A80-33282 # Experimental investigation of the two- computer aids are discussed. Trends in ADGE are outlined. V. T. dimensional asymmetrical turbulent wake behind a blade. M. A. Ghazi, K. A. Fathalah (King Abdulaziz University, Jeddah, Saudi A80-34156 Survivable C3. D. Shore (RCA, Government Arabia), M. I. flashed (Cairo, University, Cairo, Egypt), and R. M. Systems Div., Moorestown, N.J.). In: Military Electronics Defence EI .Taher (King Abdulaziz University, Jeddah, Saudi Arabia; Cairo, Expo '79; Proceedings of the Conference, Wiesbaden, West Germany, University, Cairo, Egypt). Journal of Aircraft, vol. 17, May 1980, p. September 25-27, 1979. Cointrin, Geneva, Swit- 382. 384. NSF Grant No. OIP.74-21450. zerland, Interavia, S.A., 1979, p. 81-94. Low-speed wind tunnel (working section 0.4 x 0.4 m( results are The paper discusses the survivability problems of command, presented and discussed for turbulence measurements of the asym- control, and communication )C3) centers. Consideration is given to metric turbulent 'near wake' of the cambered airfoil 10C4/30050. versatile terminals, data processing, interior communications, and Some important characteristics of the asymmetric wake flow behind integration into a system. Sensors are briefly described and afford- a blade are identified. Major conclusions are that (1) the distribution ability and capability/flexibility payoffs are outlined. V.1. of turbulence at any streamwise location is asymmetric and has two peaks at the upper and lower sides of the wake, which tend to be A80-34157 1FF for air defence aircraft. D. G. Stewart smoothed into one peak relatively far from the trailing edge; and (2) (Cossor Electronics, Ltd., Harlow, Essex, England). In: Military the actual turbulence intensity normalized by its maximum falls on Electronics Defence Expo '79; Proceedings of the Conference, two curves for the two regions of the wake having positive and Wiesbaden, West Germany, September 25-27, 1979. negative static pressure gradient S. D. Cointrin, Geneva, Switzerland, Interavia, S.A., 1979, p. 109-124. The operating principles and requirements of an Identification A80-33292 Emergency landings on a carpet of foam. L. Friend or Foe OFF) system are discussed. Consideration is given to Scheichl. Airport Forum, vol. 10, Apr. 1980, p. 35, 36, 39 13 ff.). 5 an airborne 1FF interrogator, primary radar, and secondary radar. refs. Emphasis is placed on target resolution and aircraft system and Emergency landing by aircraft with faulty landing gear on problem areas including a radome effect, radar correlation, and carpets of foam laid out on a runway is studied. The theoretical and feeder cables. Automatic code changing is outlined and flight trials experimental fundamentals of foaming techniques are reviewed with are described. V. T. attention given to the characteristics of the various types of foam. Foam equipment is discussed including runway foaming trailers and A80-34158 The modular survivable radar. M. E. Davis water trailers. V. T. (General Electric Co., Aircraft Equipment Div., Utica, N.Y.). In:

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Military Electronics Defence Expo '79; Proceedings of the Con- clutter is substantial and less energy in clear directions, as well as ference, Wiesbaden, West Germany, September 25-27, 1979. with regard to the permanent control of parasitic radiation. Cointrin, Geneva, Switzerland, lnteravia, S.A., 1979, Attention is given to obtaining the radiation pattern of a given radiating array, and to phase control with or without spurious p. 125-132. A modular survivable radar concept based on LSI circuits and side-lobes. Problems from phase errors resulting from the quantiza- microwave integrated circuits technologies is discussed. To illustrate tion of phase are considered, such as lots in gain, error in angular the applications of standard radar modules, two distinct systems have measurement, and the production of parasitic radiation. A descrip- been examined. One has applications to tactical battlefield surveil- tion of phased-array radar antennas is given, including the problem of lance and includes eight auxiliary channels for ECCM cancellation. coupling between adjacent radiating elements, phase shifters (diode The other is a multimode air-to-air and air-to-ground radar for or ferrite), and connecting the transmitter-receiver to the phased J.P.B. lightweight fighters. V. T. array. A80-34174 Airborne FUR - Experiences from flight tests, A80-34159 Airborne radar coherent transmitters. A. L.-G. Larsson )Telefonaktiebolaget L. M. Ericsson, Molndal, Swe- Hainer )Telefonaktiebolaget L. M. Ericsson, Molndal, Sweden). In: den). In: Military Electronics Defence Expo '79; Proceedings of the Military Electronics Defence Expo '79; Proceedings of the Con- Conference, Wiesbaden, West Germany, September 25-27, 1979. ference, Wiesbaden, West Germany, September 25-27, 1979, Cointrin, Geneva, Switzerland, Interavia, S.A., Cointrin, Geneva, Switzerland, Interavia, S.A., 1979, 1979, p. 479-486. p. 133-145. The paper is a follow-up to the MEDE '77 presentation and The L.M. Ericsson Wiggen radar programs is described. The radar outlines some experiences from flight tests with the Ericsson uses transmitters with coupled cavity traveling wave tubes. Con- second-generation FLIR. The flight test system is briefly described. sideration is given to the transmitter design including functional A FUR system can be used in an attack aircraft for the following description and mechanical layout. High voltage technology em- purposes (besides target detection): low-altitude flying aid, naviga- V.T. ployed and testing and field experience are outlined. tion aid, aid for taxiing, and aid for takeoff and landing in darkness. The FUR penetrates haze, smoke and visual camouflage; this means A80-34163 Experiences of a 50 MBPS video recording and improved performance against ground targets day and night. The processing system for FUR images. B. Olsson (Telefonaktiebolaget flight test experiences as regards field of view, spatial resolution, L. M. Ericsson, Molndal, Sweden). In: Military Electronics Defence thermal resolution, target detector function, and display function are Expo '79; Proceedings of the Conference, Wiesbaden, West Germany, summarized. Also described is the FUR equipment. S. D. September 25-27, 1979. Cointrin, Geneva, A80-34175 VLSI/VHSI device technology. D. D. Buss Switzerland, Interavia, S.A., 1979, p. 220-235. (Texas Instruments, Inc., Dallas, Tex.). In: Military Electronics Operational experience obtained with a high-bit-rate airborne Defence Expo '79; Proceedings of the Conference, Wiesbaden, West data acquisition and recording system and a ground-based data Cointrin, processing and evaluation system for forward-looking infrared radar Germany, September 25-27, 1979. Geneva, Switzerland, Interavia, S.A., 1979, 489-493. (FLIR) data is reported. The airborne system, located on a strike p. Problems associated with the military use of LSI technology are aircraft, is a record-only system consisting of a data acquisition unit, discussed, such as high costs, risk, and time delay inherent in the a digital interface unit, a tape recorder and a remote control unit development of custom ICs, large inventory requirements, and capable of recording a digital video signal, flight data and FLI R tests special high-reliability military qualifications. It is recommended that signals at a total rate of 50 Mbit/sec. The ground system, is one abandon low-volume custom military LSI and develop comprised of a data recorder/reproducer, data recorder, a multi- microprocessor-type Programmable System Components )PSCs( for purpose digital interface unit, FUR and radar data control units, a minicomputer, graphic and video display systems and a digital image military signal processing which will be programmable for a broad spectrum of military missions and will be produced in volume by memory. In the course of about 70 flights, the airborne system V. L. exhibited 47 faults, only 11 of which lead to unsuccessful flights, semiconductor manufacturers. and was found to meet the performance specifications. During the A80-34178 Frequency independent sidelobe suppression period of operation from May 1977 to July 1979, the ground system and lobesharpening using broad beam antennas. A. Torby (Saab- experienced 67 faults, predominantly in the first year of operation, Scania AB, Linkoping. Sweden). In: Military Electronics Defence and has performed well for quick-look and performance evaluations, Expo '79; Proceedings of the Conference, Wiesbaden, West Germany, although slowly in image processor simulations. A.L.W. September 25-27, 1979. Cointrin, Geneva, Swit- zerland, Interavia, S.A., 1979, p. 559-565. A80'34166 A broadband, circularly polarized, phase The performance of ESM and radar warning systems is largely steered array. L. Josefsson )Telefonaktiebolaget L. M. Ericsson, dependent on the antenna subsystem configuration, particularly Molndal, Sweden). In: Military Electronics Defence Expo '79; when localization of received signals is concerned. The paper Proceedings of the Conference, Wiesbaden, West Germany, Septem- discusses how to design an antenna subsystem with appropriate signal Cointrin, Geneva, Switzerland, ber 25-27, 1979. processing to estimate accurate bearing angles to unknown signal 273-284. 5 refs. lnteravia, S.A., 1979, p. sources under some restricted conditions. These conditions take into A broadband phased array antenna capable of + or - 60 deg account the problem of false bearing indications due to strong signals beam steering developed for ECM jamming systems is reported. The outside the sector of interest and how to eliminate these false signals antenna consists of an array of 16 waveguide radiators with linear or at least reduce them to a negligible extent. Good angular accuracy polarization. This is transformed to circular polarization by a wire is important but is of no use unless false bearings are sufficiently grid polarizer positioned in front of the array. V. T. suppressed. S. D. A80-34169 Electronically steered antennas. M. H. Carpen- tier )Thomson-CSF, Paris, France) and S. Drabowitch (Thomson- A80-34179 Advanced digital data processing for onboard CSF, Bagneux, Hauts-de-Seine, France). In: Military Electronics missile guidance and control. F. F. J. Kilger (Messerschmitt-Bdlkow- Defence Expo '79; Proceedings of the Conference, Wiesbaden, West Blohm GmbH, Ottobrunn, West Germany). In: Military Electronics Germany, September 25-27, 1979. Cointrin, Defence Expo '79: Proceedings of the Conference, Wiesbaden, West Geneva, Switzerland, Interavia, S.A., 1979, p. 391-400. Germany, September 25-27, 1979, Cointrin, The use of computer-controlled electronically steered antennas Geneva, Switzerland, lnteravia, S.A., 1979, p. 575-596. is discussed, which are superior to mechanically steered antennas in A digital data processing system MODUS developed for onboard that maximum energy can be sent in directions where jamming or missile guidance and control is described. Consideration is given to

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long lifetime of system architecture, flexibility, reliability, and clear Cointrin, Geneva, Switzerland, Interavia, S.A., functional concept. Bus concept, bus implementation, fault-tolerant 1979, p. 859-866. Research supported by the Forschungsförderungs. structures, and interfaces are outlined. It is noted that the MODUS fonds der gewerblichen Wirtschaft. concept permits direct information transfer from module to module, The methods for measuring cloud base height are reviewed, decentralized processing, and realization of the system with many emphasizing equipment based on the principle of electro-optic (laser autonomous modules (multiprocessing). V.T. pulses) range measurement The equipment consists of two units: the measuring module and the data processing and display module which A80-34180 Midcourse guidance for fire and forget missile. may be installed apart but communicating by telephone line under Modification of present homing missile. H. Kuno, H. Nakajima, and the control of two microprocessors. The block diagrams for the Y. Ueno (Tokyo Shibaura Electric Co., Ltd., Kawasaki, Japan). In: modules are given and the basic scheme for the optical system of the Military Electronics Defence Expo '79; Proceedings of the Confer- transmitting and receiving stages is shown. In addition, the basic ence, Wiesbaden, West Germany, September 25-27, 1979. specifications, including those for the laser diode, optical system, and Cointrin, Geneva, Switzerland, Interavia, S.A., 1979, detector are listed. p. 597-608. 7 refs. 0. L. The flight between firing and the seeker lock-on is termed the A80-34189 Design considerations for an active laser seek- midcourse guidance. The increasing demand for fire-and-forget er. E. S. Fans, R. D. Waltram (USAF, Armament Laboratory, Eglin operation requires the modification of the present inventory to have AFB, Fla.), and N. L. Andrade (McDonnell Douglas Astronautics midcourse guidance. The homing missile is fired after the target is Co., Huntington Beach, Calif.). In: Military Electronics Defence locked on by the seeker, whereas the fire-and-forget missile is fired Expo '79; Proceedings of the Conference, Wiesbaden, West Germany, toward the collision point, and during that flight the seeker locks on September 25-27, 1979. Cointrin, Geneva, the target. Midcourse flight path can have the shape of any curve, but Switzerland, Interavia, S.A., 1979, p. 867-873. the straight line is preferable for it gives the shortest flight time It is noted that in a visual range air-to-air dogfight mission, an before lock-on, thereby minimizing the errors caused by dispersion active laser seeker (ALS) offers many potential advantages. The bias and target maneuver. The paper describes lock-on probability primary design tradeoffs which must be made in synthesizing a and the details of a straight-line autopilot. This autopilot can be workable seeker, are described. An analysis is made which shows that modified from the present inventory by replacing rate gyros with a neodymium:YAG laser is the best available device for a near-term better sta{ic balance and the addition of integrating Circuit to the ALS application. Further, using the performance provided by this rate gyro output. S. D. laser and a silicon avalanche detector, laser parameters for a hypothetical seeker are derived. Finally, it is concluded that the current technology of laser and detector devices provides a capability A80-34185 Aurora /CP-140/ aircraft operational software system. L. D. Christie (Department of National Defence, Ottawa, which is within that needed for a successful ALS design. M.E.P. - Canada). In: Military Electronics Defence Expo '79; Proceedings of A80-34190 A solid state /CCD/ cockpit television system. the Conference, Wiesbaden, West Germany, September 25 .27, 1979. M. Vicars-Harris (Fairchild Camera and Instrument Corp., Syosset, Cointrin, Geneva, Switzerland, Interavia, S.A., N.Y.). In: Military Electronics Defence Expo '79; Proceedings of the 1979, p. 754-767. 7 refs. Conference, Wiesbaden, West Germany, September 25-27, 1979. The Aurora (CP-140) aircraft operational software system is Cointrin, Geneva, Switzerland, Interavia, S.A., presented, discussing in detail acquisition, Costs, reliability, efficiency 1979, p. 882-896. Contract No. F33657-78-C-0484. and testing. The aircraft is intended to gather information of a The performance characteristics and capabilities of the Cockpit military and civilian nature required to support the commitments of Television Sensor (CTVS) system are discussed. The system provides the Government of Canada. This includes ASW, the ability to gather a monochrome videotape record of aircraft and instruments, records evidence on illegal maritime events off a coast of Canada and the cockpit audio data, and offers instant postflight evaluation along ability to locate and help rescue persons or vehicles lost at sea or in with the option of real-time display for two-seat aircraft. Two any other area. The operational system includes separate routines displays, such as HUD and radar, are simultaneously recorded on a operating on airborne and ground-based computers, noting hardware single tape using a CTVS s plit-screen mode. The video sensor head of design avionics (acoustic and non-acoustic sensors), data storage (64 the CCD TV camera witha volume under 100 Cu cm and an f/2.8 K words), interfaces, etc. The aircraft will be operational by 1981. auto-iris lens having a 5,000 to 1 dynamic range, is a candidate for 0. L. many applications besides recording the HUD. The split-screen A80-34187 Laser Target Marker /designator/ and Ranger. control unit is found to effectively double the capability of the S. D. Lazenby )Ferranti, Ltd., Electro-Optics Group Edinburgh, airborne video cassette-tape recorder with a modest tradeoff in Scotland). In: Military Electronics Defence Expo '79; Proceedings of horizontal resolution. L. M. the Conference, Wiesbaden, West Germany, September 25.27, 1979. A80-34216 Big-fan engines . A new US generation, B. Cointrin, Geneva, Switzerland, Interavia, S.A., Sweetman. Interavia, vol. 35, May 1980, p.411-414. 1979, p. 846-858. The latest generation of improved big fan high-bypass-ratio The system is based on the use of a neodymium YAG laser powerplants is surveyed, noting that the market for such engines is capable of firing at pulse repetition frequencies of 10 or 20 pulses dominated by two U.S. manufacturers. It is shown that both the per second. The higher frequencies are especially useful for operation CF-6-80 and JT9D-7R4 engine families offer a combination of better with laser guided weapons. The output of the laser is injected into specific fuel consumption and lower costs per flight cycle compared the combined sighting and transmit telescope. The module is with earlier engines. Attention is also given to the market position of accurately interfaced with the tripod support which is essential if the two manufacturers and their differing approaches to technologi- precise bearing information is to be made available for the artillery cal development such as P&W's more radical process of single-crystal role of the equipment. The complete system, including a spare blade casting. M.E.P. battery, weighs 28 kg and is normally transported by two men, often with vehicle or helicopter support. V. L. A80-34217 New developments in US military fighter engines. D. Boyle. Interavia, vol. 35, May 1980, p.415-417. A80-34188 A microprocessor controlled system for deter- The latest development trends in the U.S. F100 and F101 mining the height of clouds. K. A. Roider (D. Swarovski und Co., military fighter engines are discussed. Attention is given to the high Wattens, Austria) and J. Riegl (Dr. Johannes Riegl, lndustrieunter- performance (7.6 to 1 thrust to weight ratio) of the F100 engine nehmen fur Radartechnik und Elektrooptik, Tralenreith, Austria). which has lead to a number of problems in terms of reliability and In: Military Electronics Defence Expo '79; Proceedings of the durability. It is shown that the F101 engine with a thrust to weight Conference, Wiesbaden, West Germany, September 25-27. 1979. ratio of 7.3 to 1 is being developed with a greater emphasis on

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reliability and long service life at the expense of light weight technology, Kalman filtration, and software of the R.P.A. are construction. However, with an expected thrust of 26-29.000 lb., the considered. J.P.B. 1`101 will still supply a better aircraft thrust to weight ratio than the F100 in spite of its greater weight. Finally, the continuing A80-34234 # New mathematical formula for the cropduster development of the F100 and the Component Improvement Program operational cycle (Nowa formula matematyczna agrolotniczego are examined. M.E.P. cyklu operacyjnego). B. Gajewski and J. Sienkiewicz (Akademia Rolnicza, Szczecin, Poland). Technika Lotnicza i Astronautyczna, A80-34218 The DC-8 reengining program. J. McGowen vol. 35, Jan. 1980, p. 11-13. In Polish. (Cammacorp, El Segundo, Calif.). Interavia, vol. 35, May 1980, p. An improved formula is proposed which takes into account the 419-421. numerous factors that affect the amount and quality of cropduster The new-generation high bypass ratio engine (the CFM56) for operation. The formula permits quantitative analysis of the' amount the DC-8 should not only solve the noise problem but should also and quality of cropduster performance, determination of the provide very significant fuel savings and greatly improved takeoff minimal economically tenable agricultural areas to be serviced by one thrust, range, and other performance characteristics. This paper cropduster, determination of optimal airfield locations and many discusses the DC-8 re-engining program with respect to program other factors pertinent to the efficiency of cropduster operation. organization, contract agreements. DC-8 modifications, c,, t and V. P. performance, increased range, and future CFM56 applications. B.J. A80.34235 # Investigation of the stress distribution in the A80-34223 * Release-rate calorimetry of multilayered surface layer of aircraft engine components (Badania rozkladu materials for aircraft seats. L. L. Fewell, J. A. Parker (NASA, Ames naprezen w warstwie wierzchniej elementow silnikow lotniczych). J. Lunarski and M. Korzynski (Rzeszow, Politechnika, Rzeszow, Research Center, Moffett Field, Calif.), F. Duskin, H. Speith, and E. 35, Jan. 1980, p. Trabold (Douglas Aircraft Co., Long Beach, Calif.). SAMPE Quarter- Poland). Technika Lotnicza i Astronautyczna, vol. 14-16. In Polish. ly, vol. 11, Apr. 1980, p.8-13. Multilayered samples of contemporary and improved fire- A technological procedure is proposed for determining the resistant aircraft seat materials were evaluated for their rates of heat distribution of circumferential and axial stresses in surface layers of release and smoke generation. Top layers with glass-fiber block specimens removed by arc cutting from blades, shafts, and other cushion were evaluated to determine which materials, based on their engine components. The configurations of the test specimens, the minimum contributions to the total heat release of the multilayered etching procedure, the stress measurement circuits, and the formulas assembly, may be added or deleted. The smoke and heat release rates for calculating circumferential and axial stresses are given. V. P. of multilayered seat materials were then measured at heat fluxes of 1.5 and 3.5 W/cm2. Abrasion tests were conducted on the decorative A80-34236 # Fuel consumption per units of transport work fabric covering and slip sheet to ascertain service life and compatibil- in airliner operation (Zuzycie paliwa na jednostki pracy przewozowej ity of layers. (Author) w procesie eksploatacji duzych samolotow pasazerskich). K. Rzemek. Technika Lotnicza iAstronautyczna, vol. 35, Jan. 1980, p. 28, 29. In Polish. A80-34226 The automatization of the detection of colli- A method is proposed for calculating indices of fuel consump- sion risks for French air traffic control (L'automatisation de la tion per ton-kilometer and passenger-kilometer for passenger aircraft, detection des risques de collision pour le contrôle du trafic aérien such as IL 62 and DC 10-30. Mathematical expressions for the mean Francais). A. Printemps (Centre d'Etudes de la Navigation Aérienne, fuel consumption functions are derived for each of the two indices. Orly Aérogare, Val-de-Marne, France). (Socióté des Electricians, des V, P. Electroniciens et des Radioélectriciens and Institut Francais de Navigation, Journée d'Etudes sur l'Anticollision, Gif-sur-Yvette, Essonne, France, Nov. 14, 1979.) Navigation (Paris), vol. 28, Apr. A80-34237 # Combustion-gas temperature sensors for tur- 1980, p. 161-171. In French. bine and turbojet engines (Czujniki do pomiaru temperatury gazow The concept of the safeguarding net is discussed, which warns spalinowych w silnikach turbinowych i turboodrzutowych). A. the air traffic controller of any imminent conflicts. Attention is given Lesiuk. Technika Lotnicza I Astronautyczna, vol. 35, Jan. 1980, p. to studies made to develop the system, its characteristics, actual state 30-33. 9 refs. In Polish. of advancement, and impact on the control of aircraft circulation. Some aspects of the application of thermoelectric sensors to Utilizing radar, the position of aircraft is to be determined two in-flight exhaust-gas temperature measurements for turbojet and minutes in advance. The two principal processes of the system are turbine engines are discussed. The reciprocal action of some considered: the rough sorting stage, wherein every 10 seconds the metrological parameters is examined with particular reference to the entire field of active aircraft over the control center is reviewed, and dynamic properties, reliability, and stability of the sensors. V.P. the fine sorting stage, whereby the movement of any two possibly J.P.B. conflicting aircraft is forecast. A80-34238 # Influence of external conditions on the generation and intensity of vortices at air-intakes (Wplyw warunkow A80-34227 Optimal integrated inertial navigation: An zewnetrznych na powstawanie i natezenie wirow przedwlotowych). actual example . The R.P.A. aircraft carrier reference system (La R. Szczepanik. Technika Lotnicza I Astronautyczna, vol. 35, Jan. navigation inertielle intégrée optimale: Un exemple de réalisation - 1980, p. 34, 35. In Polish. Le système de référence porte-avions R.P.A.). L. Camberlein and M. The paper reviews the results of experiments carried out to de Crémiers )Société d'Applications Générales d'Electricité et de study the influence of the meteorological conditions at the airport Mécanique, Paris, France). (Symposium sur la Localisation en Mar, on generation and dynamics of vortices at air-intakes. The influence Brest, France, Oct. 1979.) Navigation (Paris), vol. 28. Apr. 1980, p. of the wind direction on vortex geometry and parameters is 172-187. 5 refs. In French. examined, along with the range of vortex displacement as a function The principles and objectives of integrated navigation are of the wind parameters, V. P. outlined, and the criteria for selecting navigation sensors are indicated. Particular attention is given to inertial navigation, and the use and advantages of Kalman filters are discussed. In addition, the A80-34298 # Advanced research on helicopter blade airfoils. R.P.A. reference aircraft carrier is described, as is the integrated J.-J. Thibert (ONERA, Chatillon-sous-Bagneux, Hauts-de-Seine, inertial navigation system used in the Alidade method for aligning France) and J. Gallot (Sociétè Nationale Industrielle Aérospatiale, the Super-Etendard inertial system on aircraft carriers. The inertial Marignane, Bouches-du-Rhhne, France). (European Rotorcraft and

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Powered Lift Aircraft Forum, 5th, Amsterdam, Netherlands, Sept geneous medium is proposed. Temperature gradients in a hydro- 4-7, 1979,) ONERA, TPno. 1979-120,1979.11 p. 7refs. statically stable atmosphere are shown to have a very slight effect on ONERA and Aérospatiale have undertaken a joint program for the parameters of a sound field. V. P. defining advanced airfoils for helicopter rotor blades. Three airfoils with a thickness to chord ratio of 7 percent, 9 percent and 12 A80'34396 ft Determining the optimal fan silencer design of percent respectively have been defined to specifications suited to the aircraft engines (Vybc. : optimal'noi konstruktsii glushitelia shuma position of the airfoil along the blade span. The characteristics and ventiliatora silovol ustanovki samoleta). E. G. Maslova and Z. N. performance data determined from wind-tunnel testing are presented Naumenko. In: Aeroacoustics. Moscow, tzda- and compared with those of other known airfoils and with the tel'stvo Nauka, 1980, p. 73-78. 5 refs. In Russian. figures expected from computation methods. Construction of model It is proposed to determine the geometrical parameters of an rotors has been decided for testing this new generation of airfoils; optimal silencer on the basis of models constructed from the given experiments carried out in Si wind tunnel in Modane allowed aeroacoustic characteristics of the source. Knowing the modeling confirmation of the expected gains. These tests were complemented scale, it is then possible to determine the modes of operation of the by in-flight testing of a set of blades with the 0A209 airfoil on model fan stage for use in designing silencer versions. Expressing the Dauphin helicopter. The complete set of results has guided the experimental data in the form of relations between the attenuation optimization of blades intended for use on Dauphin or Ecureuil of the various noise components of the fan and the input impedance series. (Author) of the silencer, the impedance value can be determined at which the reduction of fan noise for a given channel geometry is maximal. V.P. A80-34351 A study of the stress-strain state of shaped hollow blades for radial superchargers. V. A. Pukhlii and V. K. A80-34398 # Experimental study of fan-noise silencers of Borisov (Tsentral'nyi Nauchno . I ssledovatel'skii i Proektno- aircraft turbojet engines (Eksperimental'noe issledovanje glushitelei Eksperimental'nyi Institut Promyshlennykh Zdanii i Sooruzhenii, shuma ventiliatorov aviatsionnykh turboreaktivnykh dvigatelei). A. Moscow, USSR). (Prob/emy Prochnosti, Sept. 1979, p. 93-96.) A. Bezgreshnov, S. B. Bogomolov, M. N. Solov'eva, and lu. D. Strength of Materials, vol. 11, no. 9, May 1980, p. 1040-1045. 6 refs. Khaletskii. In: Aeroacoustics. Moscow, lzdatel'- Translation. stvo Nauka, 1980, p. 93-100. In Russian. The paper examines strength calculations of hollow shaped A compressor test stand with silencing and reverberation blades of radial superchargers. The analytical solution' of the chambers was used to test silencers of fan suction and exhaust noise, boundary value problem for a system of elliptic equations, which of the type used in turbojet engines. The honeycomb fillers of the describe the stress-strain state of a blade, is constructed on the basis silencers differed in their comb depth and the number and diameter of the integral correlation method and the method of successive of the perforations. The results obtained at suction Mach numbers approximations. The calculated results were within 15 to 20% of ranging from 0.3 to 0.7 and exhaust Mach numbers from 0.1 to 0.3 strain gage measurements of an operating supercharger blade. A.T. are diagrammed and discussed. V. P. A80-34399 # Experimental investigation of sound absorp- A80-34386 Aeroacoustics (Aeroakussika). Edited by A. V. tion in a flow-carrying channel with a sound-absorbing lining Rimskii-Korsakov. Moscow, Izdatel'stvo Nauka, 1980. 144 p. In (Eksperimental'noe issledovanie pogloshcheniia zvuka v kanale so Russian. zvukopogloshchaiushchei oblitsovkoi pri nalichii potoka). lu. D. The paper deals with the characteristics of aerodynamic noise Khaletskii and R. A. Shipov. In: Aeroacoustics. and methods of suppressing it. The theoretical and experimental Moscow, lzdatel'stvo Nauka, 1980, p. 101-108. 7 refs. In Russian. investigations described deal with the excitation and propagation of A test facility incorporating a double reverberation chamber is sound in air ducts with sound-absoring liners; nonlinear interactions described, using which the spectral characteristics of sound absorp- between flows and sound waves in air ducts; interactions between air tion in the intake and exhaust ducts of turbomachines can be and fan-generated flows, as sources of turbulent noise; and various determined by means of a strain energy method. The potentialities of means of suppressing oscillations in combustion chambers. Noise the facility are illustrated by analyzing test data obtained with generated by airliners and supersonic transports is examined. V. P. various aircraft silencers. V. P.

A80-34387 # Noise characteristics of supersonic passenger A80-34400 ft Suppression of self-oscillations in combustion planes (Akusticheskie kharakteristiki sverkhzukovykh passazhirskikh chambers by means of resonance sound absorbers (Podavlenie wmoletov). A. G. Munin, G. A. Cheremukhin, and R. A. Shipov. In: avtokolebanii v kamere sgoraniia rezonansnymi zvukopoglotiteliami). Aeroacoustics. Moscow, lzcfatel'stvo Nauka, V. I. Kondrat'ev and A. L. Sushkov. In: Aeroacoustics. 1980, p. 3-12. In Russian. Moscow, Izdatel'stvo Nauka, 1980, p. 109-111. In In the present paper, the noise characteristics of a supersonic Russian. transport are studied as a function of the craft's performance and In the present experiment, resonance sound absorbers were specifications. The results of a parametric analysis of the influence of studied using a jet-engine combustion chamber. It proved possible to noise abatement measures on the parameters of the airplane are develop Helmholtz-resonator absorbers capable of suppressing the examined, showing that the noise-optimal cruising parameters differ lowest longitudinal-tangential mode of pressure fluctuations at appreciably from the fuel-optimal parameters. The noise-generating frequencies of 3.2 kHz. Some effective means of suppressing features of an SST and methods of reducing noise are discussed. It is self-oscillations are pointed out. V. P. shown that substantial noise abatement can be achieved by increasing the LID ratio and by using variable-cycle engines. V.P. A80-34402 # Acoustic effects on the flow and the noise spectrum of supersonic jets (Akusticheskoe vozdeistvie na techenie I A80-34388 # Propagation of acoustic waves in a nonuni- spektr shuma sverkhzvukovykh strui). G. I. Eremin and V. I. formly heated medium (Rasprostranenie akusticheskikh voln v Kondrat'ev. In: Aeroacoustics. Moscow, lzda- neravnomerno nagretoi srede). V. I. Bashmakov, A. I. Maiorov, V. P. tel'stvo Nauka, 1980, p. 119-123. In Russian. Panov, E. L. Spektor, and R. A. Shipov. In: Aeroacoustics. The effect of sound oscillations on supersonic )M 1.2 to 2.5) Moscow, lzdatel'stvo Nauka, 1980, p. 12-18. In lets was studied experimentally at frequencies between 10 and 19.5 Russian. kHz and sound pressures ranging from 170 to 176 dB. The effect of The paper deals with the influence of temperature gradients in sound oscillations is found to depend on the intensity of the external the atmospheric boundary layer on the propagation of aircraft- sound source, the excitation frequency, and the position of the generated sound waves. A numerical method for integrating a excitation zone with respect to the nozzle exit section. It is shown two-dimensional wave equation for an unbounded weakly inhomo- that the acoustic effect on a supersonic jet increases when the

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excitation zone is close to the nozzle and the frequency of the which help determine the acoustic characteristics of a full-scale external sound source is low. V. P. externally-blown-flap system utilizing a quieted, high bypass turbofan engine and a three-element flap STOL wing segment. S. D. A80-34403 ft Model studies of acoustic resonators (Model' nye issledovanhia akusticheskikh rezonatorov). A. L. Sushkov. In: Aeroacoustics. Moscow, lzdatel'stvo Nauka, A80-34595 ft Wake vortex trajectories of low flying spray aircraft. R. H. Wickens (National Research Council, Ottawa, Canada). 1980, p . 124-131. 7 refs. In Russian. The experiments described were carried Out to study means of Canadian Aeronautics and Space Journal, vol. 26, 1st Quarter, 1980, improving the damping capacity of a Helmholtz resonator and of p. 41-45. resonance sound absorbers employing Helmholtz resonators. The experiments were performed under conditions of vibrating combus- A80-34596 ft Reduction of aerodynamic drag of external tion in a narrow tube in the presence of high-frequency longitudinal spray booms and nozzles used on DC-6 aircraft. R. H. Wickens pressure fluctuations, and also in the combustion chamber of a gas (National Research Council, Ottawa, Canada). Canadian Aeronautics generator with low-frequency tangential-longitudinal pressure fluctu- and Space Journal, vol. 26, 1st Quarter, 1980, p. 46-51. ations. The characteristics of an effective high-level noise absorber An investigation into the aerodynamic drag of spray booms used developed on the basis of the experimental data are discussed. V. P. on Conair DC-6 aircraft has shown that when flying at 200 kt an additional force of 1300 lb is exerted on the airframe, with a A80-34404 ft Acoustic characteristics of jets issuing from corresponding expenditure of 800 hp. A new boom profile and wing ring-and-needle nozzles (Akusticheskie kharakteristiki Strul, istekaiu- installation has been designed which reduces the parasite losses by shchikh iz sopel s tsentral'nym teplom). V. P. Zhvalov, L. I. Sorkin, 400 hp. Flight observations of the spray showed satisfactory and M. N. Tolstosheev. In: Aeroacoustics. patterns, and the new installation is now standard equipment on Moscow, Izdatel'stvo Nauka, 1980, p. 131-137. 5 refs. In Russian. Conair's aircraft. Flight performance was also improved using these Empirical relations are derived for calculating the sound energy new profiles; estimates of best climb speed, and maneuver times flux, the spectrum, and the directivity pattern of heated jets issuing during low-level turns indicated improvements of 10-15% over the from ring-and-needle nozzles. It is shown experimentally that lets original boom installation. (Author) produced in such nozzles are less noisy than those generated in converging nozzles. V. P. A80-34631 Aircraft gas turbine materials and processes. B. H. Kear and E. R. Thompson (United Technologies Research Center, East Hartford, Conn.). Science, vol. 208, May 23, 1980, p. 847-856. A80-34588 A pulsed radiography technique for studying ft 26 refs. the internal structure of fuel injection jets (Rentgenoimpul'snyi Materials and processing innovations that have been incorpo- metod izuchenila vnutrennei struktury toplivnogo fakela). V. K. rated into the manufacture of critical components for high- Baev, A. N. Bazhaikin, E. I. Bichenkov, A. A. Buzukov, R. L. performance aircraft gas turbine engines are described. The materials Rabinovich, and B. P. Timoshenko. PMTF - Zhurnal Prikladnoi of interest are the nickel- and cobalt-base superalloys for turbine and Mekhaniki i Tekhnicheskoi Fiziki, Jan-Feb. 1980, p. 105-111. 15 burner sections of the engine, and titanium alloys and composites for refs. In Russian. compressor and fan sections of the engine. Advanced processing The paper deals with the development and design of a portable methods considered include directional solidification, hot isostatic X-ray apparatus and its application to studies of the internal pressing, superplastic forging, directional recrystallization, and diffu- structure of fuel jets injected from a diesel nozzle. The cumulative sion brazing. Future trends in gas turbine technology are discussed in nature of the interaction between the jet head and the medium is terms of materials availability, substitution, and further advances in demonstrated, along with the regular formation of liquid condensa- air-cooled hardware. (Author) tions in the body of the jet, the number of which in these cross sections exceeds by an order of magnitude their number in the A80-34652 Types of Ieeside flow over delta wings (Zur rarefied portions of the jet. This phenomenon, observed only during Systematik der Leese iten-Strömung bei Deltaflugeln). J. Szodruch the stage of increasing pressure in the fuel system, is attributed to the (NASA, Ames Research Center, Moffett Field, Calif.; Berlin, Tech- Onset of hydrodynamic instability in jets with a positive longitudinal nische Universität, Berlin, West Germany). Zeitschrift für F/ugwissen- velocity gradient. V.P. schaften und Weltraumforschung, vol. 4, Mar.-Apr. 1980, p. 72-81. 19 refs. In German. A80-34593 ft Pitot-static system . Errors and calibrations. R. It is noted that so far most systematic investigations on the lee D. Michas (Canadian Armed Forces, Ottawa, Canada). Canadian side flow over delta wings at supersonic speeds are concerned with Aeronautics and Space Journal, vol. 26, 1st Quarter, 1980, p. 20-26. flat upper surfaces. On the basis of these results, the paper makes an Accurate airspeed and altitude are required to inform the pilot attempt to characterize the different types of flow over a wing with a on where he is in the flight envelope and to provide a reliable aid to delta-shaped upper surface by varying a number of parameters. It is air traffic control. The aircraft pitot-static system provides such concluded that the work should be considered a first step toward information by measuring the static (outside ambient) and pitot systematizing the flow over delta-shaped lee sides as well. M.E.P. (static plus impact) pressures. System errors, accuracy requirements, and tolerances and the calibration methods used by the Aerospace A80-34653 Study on the dynamics of small flight vehicles Engineering Test Establishment are discussed. Emphasis is laid on the )Zur Dynamik kleiner Fluggeräte). R. Staufenbiel )Aachen, Tech- importance of good maintenance and proper use of the pitot-static nische Hochschule, Aachen, West Germany). Zeitschrift für Flug- system to ensure that it fulfills its intended function. SD. wissenschaften und We/traumforschung, vol. 4, Mar-Apr. 1980, p. 81-93. 21 refs. In German. A80-34594 ft Jet flap impingement noise from a full-scale It is noted that there is increasing interest in small flight STOL EBF engine-wing system. R. G. Goldman (California, Univer- vehicles, especially the use of RPVs. Attention is given to the sity, Santa Barbara, Calif.). Canadian Aeronautics and Space Journal, influence of vehicle size on stability, loads and disturbances as well as vol. 26, 1st Quarter, 1980, p. 28-40. 7 refs. on performance. Emphasis is placed on gust sensitivity and landing A full-scale section of a three-flap STOL wing was constructed techniques of small vehicles with consideration given only to the in order to evaluate the noise levels generated by STQL aircraft longitudinal motion. M.E.P. under various conditions. The paper summarizes the results of th first full-scale acoustic and performance tests on a quieted, modern, high bypass ratio turbofan engine enclosed in an acoustically treated A80-34655 Possibilities for achieving trimmed minimum nacelle mounted to a section of a STOL wing. Tests are reported drag without sacrificing inherent stability (Realisierungsm6glichkei-

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ten des getrimmten Minimalwiderstands ohne Verzicht auf natürliche (Akadem,ia Nauk SSSR, lzvestiia, Mekhanika Zhidkosti i Gaza, Stabilitat). G. Sachs (Mjjnchen, Hochschule der Bundeswehr, Neubi- Sept.-Oct. 1979, p. 114. 125.) Fluid Dynamics, vol. 14, no. 5, Mar. berg, West Germany). Zeitschrift für Flugwissenschaften und Welt- 1980, p. 726-735. 9 refs. Translation. raumforschung, vol. 4, Mar-Apr. 1980, p. 101-106. 18 refs. In Correspondence of solutions of direct and inverse problems of German. the wing theory for a finite span wing is established in the framework The paper deals with the relation between the inherent stability of the linear theory based on the solution of the Volterra wave boundary and the drag optimum c.g. position which represents the equation for supersonic flow, and she solution of the Laplace c.g. position where trimmed drag is minimum. It is shown which are equation in the form of Green's formula for subsonic flow. For the the factors significantly affecting this relation and which are the direct problem in the supersonic case, a formula is derived for conditions where the drag optimum c.g. position is stable. The paper determining wing loading which most fully considers the wing investigates the effects resulting from the aerodynamic configuration geometry characteristics. For the inverse supersonic and subsonic (wing body combination and tail) as well as from thrust moments. flows, formulas are derived for determining wing geometry by (Author) specified wing loadings and the change in loading along the wing span. The solution of she inverse problem is presented in the form of integral convergence of internal points on the wing surface, with the A80-34664 Lightning damage mechanisms and simulation wing surface representing a vortical surface of mutually orthogonal techniques. E. H. Schulte (McDonnell Aircraft Co., St. Louis, Mo.). vertical lines. A. T. Journal of Environmental Sciences, vol. 23, May-June 1980, p. 13-17. 18 refs. The paper describes the natural lightning phenomenon, showing A80-34765 NDI policy and techniques for advanced com- how it relates to the need for aircraft protection. Laboratory posites. R. M. Collins (Grumman Aerospace Co., Bethpage, N.Y.). In: simulations predicting the response of materials and structures to New horizons - Materials and processes for the eighties; Proceedings lightning and defining protective measures are considered. The tests of the Eleventh National Conference, Boston, Mass., November account for the effect of swept stroke under which an aircraft 13-15, 1979. Azusa, Calif., Society for the becomes a part of the lightning arc. Simulations encompass such Advancement of Material and Process Engineering, 1979, p. 178-191. damage mechanisms as high-voltage ruptures and high-current spikes An NDI policy that has provided the guidance necessary to reaching 200,000 amperes in magnitude, during tens of micro- assure the quality of primary structure is described. Critical defect seconds. The simulation techniques proposed also treat high-charge types for NDI are defined. Designs for NDI standards, applicable to transfer resulting in extreme heating, melting, and erosion of variable attenuative structures, are described. The effect of longitudi- conductive materials and the effect of high-level signals induced in nal ultrasonic waves propagating through she laminate thickness is the electrical wiring systems and avionic circuits. O.L. discussed. The utility of NDI techniques for defect depth determination, per ply thickness measurement, detection of radii or edge defects, and the prediction of ultimate or residual strength of a A80-34708 Stationary flow past she lower surface of a structure are presented. (Author) piecewise planar delta wing with supersonic leading edges, S. M. Ter-Minasiants. (Akademiia 1%/auk SSSR, lzvestiia, Mekhanika Zhid. A80-34766 Airworthiness certification of composite com- kosti i Gaza, Sept.-Oct. 1979, p. 80-90.) Fluid Dynamics, vol. 14, no. ponents for civil aircraft - The role of non-destructive evaluation. P. 5, Mar. 1980, p. 699-708. 18 refs. Translation. R. Teagle (British Aerospace Materials Laboratory, Weybridge, The analysis deals with the supersonic flow over a wing surface composed of arbitrary flat triangular elements connected to each Surrey, England). In: New horizons - Materials and processes for the other at small angles along straight lines that intersect at a point on eighties; Proceedings of the Eleventh National Conference, Boston, Mass., November 13-15, 1979. Azusa, Calif., the leading edge. A three-dimensional shock wave is attached to the Society for the Advancement of Material and Process Engineering, leading edge having the shape of a broken line. The pressure 1979, p. 192-210. 17 refs. distribution over the wing span and the pressure as the center of the The paper describes the application of nondestructive evaluation wing are calculated. V.P. to a first generation carbon fiber reinforced plastic civil airframe component. Attention is given to initial research, the development of A80-34711 Construction of a nonstationary nonlinear production test techniques and quality control procedures. Finally, theory of helicopter rotors. S. M. Belotserkovskii, V. A. Vasin, and consideration is given to developments for applications to more B. E. Loktev. (Akademiia Nauk SSSR, lzvestiia, Mekhanika Zhiot complex components. - M.E.P. kosti i Gaza, Sept.-Oct. 1979, p. 107. 113.) Fluid Dynamics, vol. 14, no. 5, Mar. 1980, 720-725. 8 refs. Translation. p. A80-34787 Large-scale and small-scale flammability tests The paper considers application of the discrete vortex method for airplane cabin materials. J. M. Peterson and E. A. Tustin (Boeing for construction of a nonlinear nonstationary propeller theory in an Commercial Airplane Co., Seattle, Wash.). In: New horizons - incompressible medium. The method allows modelling of propeller Materials and processes for she eighties; Proceedings of the Eleventh transition operations, and of conditions like the 'vortex ring' and National Conference, Boston, Mass., November 13-15, 1979. 'vortex cushion'. The method is based on substitution of actual load Azusa, Calif., Society for the Advancement of Material bearing surfaces (propeller blades) with infinitely thin surfaces and Process Engineering, 1979, p. 531-550. followed by substitution with a vortex sheet. The impermeability Flammability test methodology for passenger cabin materials is boundary condition is satisfied on the blade surfaces; velocity discussed with emphasis on correlation between small-scale test circulations along she closed fluid are .constant with time, so that procedures and large-scale fire phenomena. Current aircraft interior circulations of free vortices are also constant with time. The materials were tested by simulated large-scale fire exposure and by Chap lygin-Zhukovsky hypothesis on finiteness of velocities is real- selected laboratory tests. The laboratory methods investigated for ized during the take-off flow around the blade rear edges and on the measuring toxicant production did not consistently produce results side and front edges. Convergence of free vortices which occurs along which could be related to large-scale fire data. A testing technique is the tangent to the propeller surface is assumed at these edges, being developed, based on the Ohio State University release rate concluding that the proposed method allows determination of apparatus, with a view to obtaining direct correlation of laboratory nonstationary dispersed and combined aerodynamic characteristics, results to the magnitude of the large-scale test heat and smoke data. velocity fields, and vortex structures behind the propeller. A.T. V. L.

A80-34712 Direct and inverse problems of flow over a A80. 34797 Developments in ultrasonic welding for air- wing of finite span in the linear formulation. N. F. Vorob'ev. craft T. Renshaw, J. Curatola, and A. Sarrantonio (Fairchild

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Republic Co., Farmingdale, N.Y.). In: New horizons Materials and such drills to portable equipment for drilling close tolerance holes in processes for the eighties; Proceedings of the Eleventh National aluminum, graphite/epoxy composites, fiberglass composites and Conference, Boston, Mass., November 13. 15, 1979. combinations of these materials. Hole quality is equal to or superior Azusa, Calif., Society for the Advancement of Material and to all competitive drilling procedures in diameter control and surface Process Engineering, 1979, p. 681-693. 5 refs. finish. Finished holes are completed in one step, eliminating any The development of ultrasonic welding of aluminum for aircraft requirement for piloting, step drilling and reaming. (Author) using a Sonobond fixed reed-wedge-transducer assembly and a hydraulically elevated high-power ultrasonic model is presented. The A80-34810 Costs of graphite composite fabrication and problem of tip sticking was overcome, and it was necessary to use repair. T. J. Bettner (Northrop Corp., Aircraft Group, Hawthorne, large radii power tips for spotwelding alclad materials. Spot strength Calif.). In: New horizons - Materials and processes for the eighties; data were discussed, noting that restrictor blocks coated with Teflon Proceedings of the Eleventh National Conference, Boston,Mass., had to be clamped to specimens to minimize the variables associated November 13-15, 1979. Azusa, Calif., Society with peel action of overlapped pull specimens. Fatigue data were for the Advancement of Material and Process Engineering, 1979, p. presented, and it was also shown that ultrasonic welding produces 857.869. the effects of notch damage and/or section change.which leads to The paper presents a cost estimating methodology used for earlier failures than those of virgin panels. A.T. composite (graphite/epoxy) fabrication. The methodology can also be used for the identification of significant cost drivers encountered in the fabrication and repair of composite structures. V. T. A80-34805 Comparison of surface treatments of aluminium and their influence on long term strength of metal bonds. W. A80-34811 Shock loading on reinforced splice joints of Brockmann and 0. D. Hennmann (Institute für angewandte Material- ultra high modulus graphite/epoxy cone frustum. F. H. Koo (Martin forschung, Bremen, West Germany). In: New horizons - Materials and Marietta Aerospace, Orlando, Fla.) and L. R. Aronin )U.S. Army, processes for the eighties; Proceedings of the Eleventh National Army Materials and Mechanics Research Center, Watertown, Mass.). Conference, Boston, Mass., November 13-15, 1979. In: New horizons Materials and processes for the eighties; Azusa, Calif., Society for the Advancement of Material Proceedings of the Eleventh National Conference, Boston, Mass., and Process Engineering, 1979, p. 804-816.5 refs. November 13-15, 1979. Azusa, Calif., Society The influence of different treatments of two aluminium alloys for the Advancement of Material and Process Engineering, 1979, p. in bare and clad state on the strength and long term behavior of 882-899. bonded joints is described. The alloys are 2024 T 3 bare and clad and An ultra high modulus graphite/epoxy frustum reinforced with 7075 T 6 bare and clad treated by FPL-etch European chromic- titanium shims at the splice joint was tested on the SM-1000 shock sulphuric-etch, phosphoric-acid-anodizing and chromic-acid- machine to determine its capability in absorbing peak shock levels in anodizing. Prior to bonding the surfaces were coated with primer BR a shock spectrum. Test set up and procedures are discussed. The 127, the adhesives were FM 123-5 and FM 73. (Author) shock machine was calibrated to achieve the shock levels in increments. The test results in terms of strain gage data were A80-34808 A hybrid. composite helicopter main rotor evaluated to assess the structural response to the applied shock loads. blade employing pneumatic lift control. F. B. Clark and M. L. White (Author) (Kaman Aerospace Corp., Bloomfield, Conn.(. In: New horizons - Materials and processes for the eighties; Proceedings of the Eleventh A80-34819 Evaluation of coatings for wear and corrosion- National Conference, Boston, Mass., November 13-15, 1979. Protection in air/fluid accumulators. D. L. Behmke (U.S. Navy, Naval Azusa, Calif., Society for the Advancement of Material Air Engineering ,Center, Lakehurst, N.J.) and R. D. Brown (South- and Process Engineering, 1979, p. 840-849.8 refs. west Research Institute, San Antonio, Tex.). In: New horizons - A hybrid composite blade, utilizing interleaved S-glass/epoxy Materials and processes for the eighties; Proceedings of the Eleventh and graphite/epoxy laminae, has been developed as part of a program National Conference, Boston, Mass., November 13-15, 1979. to study helicopter flight performance characteristics attainable with Azusa, Calif., Society for the Advancement of Material circulation control aerodynamics. Lift control of a Circulation and Process Engineering, 1979, p. 993-1004. Control Rotor )CCR( blade is accomplished by varying the flow of An evaluation of coatings for wear and corrosion protection in compressed air through a full-span trailing edge slot, rather than by cylinders of catapult accumulators on Navy aircraft carriers is pitch change. In addition to improved and simplified flight control, presented. Wear and corrosion damage of the inner surfaces is this concept promises lower maintenance, reduced vibration levels experienced particularly in the air space region and at the air fluid and enhanced aerodynamic efficiency versus conventional rotors. interface where the piston is at rest. The tests indicated that the However, the CCR concept also introduces new blade design Tribaloy 800 plasma-sprayed and sealed with epoxy and a Nedox constraints arising from the internal air ducting requirements and coating consisting of electrodeposited porous nickel alloy infused trailing edge slot opening, and from compressor heating of the with polytetrafluoroethylene were more corrosion resistant than the control air. Additionally, unique dynamic stability requirements other coatings tested. It is concluded that the Tribaloy 800 coating dictate an unusually high blade torsional stiffness coupled with will provide the best protection in the accumulator application. A.T. conventional bending mode natural frequencies. The great freedom, afforded by hybrid composite construction to tailor elastic, strength A80-34840 * # Current and projected use of carbon compos- and thermal expansion properties contributed greatly to a successful ites in United States aircraft. A. W. Leonard (NASA, Langley design solution. Details of the design, fabrication and development Research Center, Hampton, Va.) and D. R. Mulville (U.S. Navy, testing of the blade are reported. (Author) Naval Air Systems Command, Washington, D.C.). NATO, AGARD, Specialists Meeting on Electromagnetic Effects of Carbon Composite A80-34809 Drilling composites with gun drills. R. T. Beall Materials upon Avionics Systems, Lisbon, Portugal, June 16-19, (Lockheed Engineering Structural and Materials Laboratory, Mari- 1980, Paper. 31 p. 19 refs. etta, Ga.). In: New horizons - Materials and processes for the eighties; It is noted that carbon composite materials are beginning to be Proceedings of the Eleventh National Conference, Boston, Mass., used in commercial transports, general aviation aircraft, military November 13-15, 1979. Azusa, Calif., Society fighter aircraft and helicopters due to demonstrated weight savings for the Advancement of Material and Process Engineering, 1979, p. and potential manufacturing Cost savings. Attention is given to 850-856. current production applications of carbon composites which range Gun drills have the ability to drill deep precision holes due to from the secondary structures of new commercial transports to wing the provision for introducing a coolant to the drill tip which both primary structures of fighters. Current development efforts are cools and aids in removing chips and shavings. Lockheed has adapted discussed that will lead to their future application to fuselages, as

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well as whole airframes. Finally, laminate constructions which vary pitching moments. Certain penalties in pitch-link loads and perfor- widely, and may be relevant to avionics system design, are examined. mance were predicted using higher-harmonic blade feathering. The M.E.P. penalties seem to be more serious for a two-bladed teetering rotor than those for a four-bladed hingeless rotor. Analyses were also A80-34974 Development of a structural overload warning performed to demonstrate that optimal HHC inputs for the system for modern high performance aircraft. G. W. Venorsky multiple-input case are not simply a linear combination of optimal (McDonnell Aircraft Co., St. Louis, Mo.). Society of Flight Test inputs for the respective single-input cases due to interharmonic Engineers, Journal, vol. 2, May 1980, p. 10-26. coupling. Analytical results indicate that both amplitude and phase The development of an overload warning system (OWS), to of HHC vary significantly with airspeed for the four-bladed hingeless provide F-15 pilots with a warning as allowable load factor limits are rotor. For the two-bladed teetering rotor, the required pitch approached, is described. It is shown that the OWS microprocessor amplitude increases as airspeed increases with nearly invariant phase computes allowable load factor using inputs of fuel quantity, stores angle. (Author) configuration, and control stick forces. The warning function is derived by comparing allowable load factor with actual load factor which is also a system input. In this manner, the prototype A80-34997 # Multicyclic control for helicopters - Research implementation accounts for changing fuel loads, some external store in progress at Ames Research Center. J. L. McCloud, Ill (NASA, weights, and maneuver asymmetry, including rapidly increasing roll Ames Research Center, Moffett Field, Calif.). In: Structures, rate. Finally, it is noted that basic design concepts have been Structural Dynamics, and Materials Conference, 21st, Seattle, Wash., demonstrated and system development continues in active flight May 12-14, 1980, Technical Papers. Part 1. New testing. M.E.P. York, American Institute of Aeronautics and Astronautics, Inc., 1980, p. 77-81. 19 refs. (AIAA 80-0671; AHS Paper 80-70) The term multicyclic control describes a blade pitch control A80-34975 Measurement and correlation of structural technique used by helicopter designers to alleviate vibration in response to inlet hamershock phenomena on an F-14 airplane. J. rotorcraft. Because rotor-induced vibrations are periodic, a multi- Auzins (Grumman Aerospace Corp., Calverton, N.Y.). Society of cyclic system, synchronized to the main rotor's azimuth position, is Flight Test Engineers, Journal, vol. 2, May 1980, p. 27.36. suitable. Many types of rotors - ranging from the jet-flap and Engine stalls in high speed jet aircraft can result in hammershock circulation-control rotors to the conventional full-blade feathering and inlet buzz. When these phenomena do occur, they can ihipose rotors - have utilized multicyclic control. Multicyclic control systems significant air/inertia loads on the inlet structure and external stores. may be designed to reduce blade-bending stresses, to reduce Although hammershock and inlet buzz are part of the design criteria, rotor-induced vibration, and to improve rotor performance. Rotor flight tests are necessary to quantify these effects which result from types are reviewed, primarily to highlight their differences. The the complex interaction of propulsive, aerodynamic, geometric and increased use of composites in blade construction is seen to indicate dynamic store response characteristics of the flight vehicle. This that vibration alleviation will be the prime focus of multicyclic paper describes the tests and analytical methodology developed control. Adaptive feedback control systems, which also incorporate during the F-14A flight test program to assess the structural effects gust alleviation, are considered to be the ultimate application of of engine stalls while maintaining the required structural margins. multicyclic control. (Author) (Author) A80-34998 # Multicyclic control of a helicopter rotor con- A80-34995 # A simple system for helicopter individual- sidering the influence of vibration, loads, and control motion. T. J. blade-control and its application to gust alleviation. N. D. Ham (MIT, Brown and J. L. McCloud, III (NASA, Ames Research Center, Cambridge, Mass.). In: Structures, Structural Dynamics, and Materi- Moffett Field, Calif.). In: Structures, Structural Dynamics, and als Conference, 21st, Seattle, Wash., May 12 . 14, 1980, Technical Materials Conference, 21st, Seattle, Wash., May 12-14, 1980, Papers. Part 1. New York, American Institute of Technical Papers. Part 1. New York, American Institute of Aeronautics and Astronautics, Inc., 1980, 82-100. 7 Aeronautics and Astronautics, Inc., 1980, p. 57. 68. 8 refs. NASA. p. sponsored research. (AIAA 80-0666; AHS Paper 80.65) refs. (AIAA 80-0673; AHS Paper 80-72) A new, advanced type of active control for helicopters and its Weighted multiple linear regression is used to establish a transfer application to gust alleviation is described. Each blade is individually function matrix relationship between higher harmonic control inputs controlled in the rotating frame over a wide range of frequencies up and transducer vibration outputs for a controllable twist rotor. Data to the sixth harmonic of rotor speed. Considerable system simplifica- used in the regression were taken from the test of a KAMAN tion is achieved by means of modal decomposition. It is shown both controllable twist rotor conducted in the Ames Research Center's 40- analytically and experimentally that by utilizing a tip-mounted by 80-Foot Wind Tunnel in June 1977. Optimal controls to minimize accelerometer as a sensor in the feedback path, significant reductions fixed system vibrational levels are calculated using linear quadratic in blade flapping response to a sinusoidal gust can be achieved at the regulatory theory with a control deflection penalty included in the gust excitation frequency as well as at super- and subharmonics of performance criteria. Control sensitivity to changes in control travel, rotor speed. (Author) forward speed, and lift and propulsive forces is examined. It is found that the linear transfer matrix is a strong function of forward speed and a weak function of lift and propulsive force. An open-loop A80-34996 # Vibration reduction with higher harmonic strategy is proposed for systems with limited control travel. (Author) blade feathering for helicopters with two-Waded teetering and four-bladed hingeless rotors. J. G. Yen (Bell Helicopter Textron, Fort Worth, Tex.). In: Structures, Structural Dynamics, and Materials A80-35007 # - On experimental versus theoretical incipient Conference, 21st, Seattle, Wash., May 12-14, 1980, Technical Papers. buckling of narrow graphite/epoxy plates in compression. E. E. Spier Part 1. New York, American Institute of (General Dynamics Corp., Convair Div., San Diego, Calif.). In: Aeronautics and Astronautics, Inc., 1980, p. 69-76. 15 refs. (AIAA Structures, Structural Dynamics, and Materials Conference, 21st, 80-0670; AHS Paper 80-69) Seattle, Wash., May 12-14, 1980, Technical Papers. Part 1. Theoretical investigations have been conducted to compare New York, American Institute of Aeronautics and higher harmonic blade pitch requirements for vibration reduction on Astronautics, Inc., 1980, p. 187-193. 17 refs. (AIAA 80-0686) helicopters with two-bladed teetering and four-bladed hingeless Most stiffeners in aerospace structures are composed of narrow rotors in trimmed level flight. For the two-bladed teetering rotor, plate elements with the unloaded edges usually being either elimination of oscillatory two-per-rev hub vertical shear was studied. simply-supported or free. This paper is concerned with the difficul- For the four-bladed hingeless rotor, higher-harmonic control (HHC) ties encountered in attempting to predict the incipient buckling was used to minimize four-per-rev hub vertical shear, rolling and strength for narrow (low width to thickness ratio) angle-plied

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graphite/epoxy plates in compression. Numerous available test data Research Center, Moffett Field, Calif.). In: Structures, Structural was compared to analytical predictions. The tested plates were of Dynamics, and Materials Conference, 21st, Seattle, Wash., May two types: both unloaded edges supported by steel V-blocks 12-14, 1980, Technical Papers. Part 1. New (no-edge-free); one unloaded edge supported by a steel V-block and York, American Institute of Aeronautics and Astronautics, Inc., the other edge free (one-edge-free). Nondimensional plots for both 1980, p. 417-433. 20 refs. (AIAA 80-0734) types of tests are presented which can be used to predict incipient The unsteady aerodynamics of a conventional and a supercritical buckling strengths for plates with laminate configurations other than airfoil are compared by examining measured chordwise unsteady those tested. For completeness, nondimensional crippling plots are pressure time-histories from four selected flow conditions. Although presented where the incipient (initial) buckling stress is employed in an oscillating supercritical airfoil excites more harmonics, the the nondimensional parameters. This approach is an interesting strength of the airfoil's shock wave is the more important parameter ramification of previously published crippling plots where the governing the complexity of the unsteady flow. Whether they are theoretical buckling stress was employed in the nondimensional conventional or supercritical, airfoils that support weak shock waves parameters. (Author) induce unsteady loads that are qualitatively predictable with classical theories; flows with strong shock waves are Sensitive to details of the shock-wave and boundary-layer interaction and cannot be adequately 480-35031 # The outside has to be bigger than the inside. predicted. (Author) H. W. Smith (Kansas, University, Lawrence, Kan.( and R. Burnham (Boeing Co., Seattle, Wash.). In: Structures, Structural Dynamics, and Materials Conference, 21st, Seattle, Wash., May 12-14, 1980, A80-35044 # Composite wing/fuselage integral concept. A. Technical Papers. Part 1. New York, American Musicman (Rockwell International Corp., North American Aircraft Institute of Aeronautics and Astronautics, Inc., 1980, p . 365-370. Div., Los Angeles, Calif.) and H. Re-inert (USAF, Materials Labora- )AIAA 80-0726) tory, Wright-Patterson AFB, Ohio). In: Structures, Structural Dy- A method for calculating the volume requirements for an namics, and Materials Conference, 21st, Seattle, Wash., May 12.14, airplane, and a design procedure for distributing the volume is 1980, Technical Papers. Part 1. New York, described. A not-too-obvious necessity for providing enough total American Institute of Aeronautics and Astronautics, Inc., 1980, p. volume to contain the payload fuel, structure and systems is 492-497, Contract No. F33615-77-C-5278. (A IAA 80.0744) presented as a logical design procedure. With outside mold lines being The integral composite wing/fuselage concept was evaluated for held at a minimum while the need to maximize internal space for its performance, weight and cost. A full-scale component environ- seats, cargo and fuel capacity, a fundamental designer's dilemma is mentally conditioned and tested met initial strength and weight posed. Se-at pitch, area ruling, fuel volume and structural depth are projections and achieved cost savings up to 33% over aluminum and discussed. Two examples, a short haul transport and a supersonic conventional built-up composite construction. Weight savings of 41% fighter airplane are presented. Method versatility allows its use during over aluminum and 18% over conventional composite constructions preliminary, advanced, or production design phases. (Author) were also achieved. A.T.

A80-35036 # CAD produced aircraft drawings. M. D. 480.35045 # Built-up tow-cost advanced titanium Structures Wehrman (Boeing Commercial Airplane Co., Seattle, Wash.). In: /BLATS/. W. L. Franklin (Rockwell International Corp., North Structures, Structural Dynamics, and Materials Conference, 21st, American Aircraft Div., Los Angeles, Calif.) and C. R. Waitz (USAF, Seattle, Wash., May 12-14, 1980, Technical Papers. Part 1. Wright Aeronautical Laboratories, Wright-Patterson AFB, Ohio). In: New York, American Institute of Aeronautics and Structures, Structural Dynamics, and Materials Conference, 21st, Astronautics, Inc., 1980, 404-408. )AIAA 80-0732) p. Seattle, Wash., May 12-14, 1980, Technical Papers. Part 1. The use of computers to include the preparation of engineering New York, American Institute of Aeronautics and drawings has been expanded. The system utilized is a combination of Astronautics, Inc, 1980, 498-503. )AIAA 80-0745) large host mainframes and minicomputers. This combination is tied p. Through the use of advanced-technology structures, a 50- together with a network called the CAD/CAM Integrated Informa- percent cost and 30-percent weight advantage is projected over tion Network (CIIN( which allows data to be transferred between conventional aircraft structures. Advanced fabrication methods machines and also to be stored and retrieved from a common include superplastic forming )SPF) alone or concurrent with diffu- Geometric Data Base )GDB). Engineering drawings are produced sion bonding (DB) of double- or multiple-sheet expanded sandwich using a combination of general and special batch APT (Automatically panels which are joined together by welding, particularly plasma arc. Programmed Tool) programs on the mainframes and then completed Structural concepts were evaluated and tested from which the design (Author) on she interactive computer graphics (ICG) system. of a full-size aircraft component, including the wing carry-through and a portion of the fuselage of a fighter plane, was developed. A A80-35037 // Unsteady airloads on a harmonically pitching demonstration article will be tested to validate cost, weight, and wing with external store. R. Roos (Nationaal Lucht- en Ruimtevaart- structural integrity. (Author) laboratorium, Amsterdam, Netherlands(. In: Structures, Structural Dynamics, and Materials Conference, 21st, Seattle, Wash., May 12-14, 1980, Technical Papers, Part 1. New A80-35046 # Economic life criteria for metallic airframes. S. York, American Institute of Aeronautics and Astronautics, Inc., D. Manning and V. D. Smith (General Dynamics Corp., Fort Worth, 1980, p. 409-416. 6 refs. Grant No. AF-AFOSR-77-3233. )AIAA Tex.). In: Structures, Structural Dynamics, and Materials Confer- 80-0733) ence, 21st, Seattle, Wash., May 12-14, 1980, Technical Papers. Part Results are presented of a wind-tunnel investigation carried out 1. New York, American Institute of Aeronautics on a harmonically pitching fighter-type wing with and without an and Astronautics, Inc., 1980, p. 504-511. 26 re-ft. Contract No. external store. In this test detailed steady and unsteady pressure F33615-77-C-3123. (AIAA 80-0748) distributions were measured on the wing, while also the aerodynamic Economic life Criteria and guidelines are presented and discussed loads on the store were obtained. The Mach number ranged from Ma for implementing the U.S. Air Force's durability requirements for = 0.6 to 1.35, while frequencies up to 40 Hz were achieved. Three advanced metallic airframes at the design level. Economic life is topics are covered in detail: (1) the influence of the store on the quantified in terms of the probability of crack exceedance and/or unsteady wing loading, (2) the behaviour of the unsteady store loads maintenance cost. The number of structural details requiring repair and (3) comparison with unsteady calculations. (Author) after a specified service period is first determined. Maintenance costs can be estimated using this information. Essential elements of the A80-35038 // Unsteady aerodynamics of conventional and proposed economic life criteria are described and practical applica- supercritical airfoils. S. S. Davis and G. N. Malcolm (NASA, Ames tions are discussed. (Author)

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A80-35047 II A quantitative assessment of the variables May 12-14, 1980, Technical Papers. Part 2. New involved in crack propagation analysis for in-service aircraft, R. L. York, American Institute of Aeronautics and Astronautics, Inc., Circle and F. M. Conley (Lockheed-Georgia Co., Marietta, Ga.). In: 1980, P. 555-564. (AIAA 80-0759) Structures, Structural Dynamics, and Materials Conference, 21st, Multilayered samples of contemporary and improved fire- Seattle, Wash., May 12-14, 1980, Technical Papers. Part 1. resistant aircraft seat materials (foam cushion, decorative fabric, slip New York, American Institute of Aeronautics and sheet, fire-blocking layer, and cushion-reinforcement layer) were Astronautics, Inc., 1980, p. 512-521. 12 refs. (AIAA 80-0752) evaluated for their rates of heat release and smoke generation. Top Results on the damage tolerance characteristics of airframe layers (decorative fabric, slip sheet, fire blocking, and cushion structures are presented. An in-depth assessment was made of the reinforcement) with glass-fiber block cushion were evaluated to structural information required for design of a transport aircraft; determine which materials, based on their minimum contributions to determination of the sensitivity of the final analysis prediction was the total heat release of the multilayered assembly, may be added or made to identify the variables requiring additional accuracy and deleted. To p layers exhibiting desirable burning profiles were attention. The results of this assessment are supported by test vs combined with foam cushion materials. The smoke and heat-release analytical comparisons using flight-by-flight test spectra developed rate of multilayered seat materials were then measured at heat fluxes from measured real-time history data from service aircraft. A. T. of 1.5 and 3.5 W/sq cm. Choices of contact and silicon adhesives for bonding multilayered assemblies were based on flammability, burn A80-35048 # Analysis of cracks at attachment lugs. T. M. and smoke generation, animal toxicity tests, and thermal gravimetric Hsu (Lockheed-Georgia Co., Advanced Structures Dept., Marietta, analysis. (Author) Ga.). In: Structures, Structural Dynamics, and Materials Conference, 21st, Seattle, Wash., May 12-14, 1980, Technical Papers. Part 1. A80-35056 # Investigation of internal control laws for New York, American Institute of Aeronautics wing/store flutter suppression. T. E. Noll, L. J. Huttsell, and D. E. and Astronautics, Inc., 1980, p. 522-528. 22 refs. (AIAA 80-0753) Cooley (USAF, Flight Dynamics Laboratory, Wright-Patterson AFB, An analytical procedure using the finite-element method with Ohio). In: Structures, Structural Dynamics, and Materials Confer- the inclusion of a high-order crack-tip singularity element was used ence, 21st, Seattle, Wash., May 12-14, 1980, Technical Papers. Part to determine the pin-bearing pressure distributions and the stress 2. intensity factors for cracks in both straight and tapered lugs. Other New York, American Institute of Aeronautics and Astronautics, Inc., 1980, parameters evaluated include the crack length, the outer-to-inner p . 585-594. 10 refs. (AIAA 80-0764) radius ratio, and the relative rigidity of the pin and the lug. Based on The design and evaluation of active flutter suppression technolo- this study, it is found that the pin-bearing pressure distribution gy using a common wind tunnel mode is discussed. The paper changes with the change in crack length. In the presence of a crack, emphasizes analytical predictions and presents test data for correla- the pressure distributions change significantly compared with the tion; control laws were evaluated using the FASTOP computer uncracked case, and its associate stress intensity factor is sensitive to program and a modified Nyquist criterion. Although the design and the pin-bearing pressure distributions, especially when the crack tests were performed for a Mach number of 0.8, the analyses were length is large or the Outer-to-inner radius ratio is small. The effect of made at several Mach numbers to determine system effectiveness at the relative rigidity of the pin and the lug on the stress intensity off-design conditions. A discussion of current USAF programs and future means of active flutter suppression are also presented. factor is negligible. (Author) A. T.

A80-35049 # Preliminary design of composite wing-box A80-35057 # Active flutter suppression control law defini- structures for global damage tolerance. J. H. Starnes, Jr. (NASA, tion via least squares synthesis. E. H. Johnson (Northrop Corp., Langley Research Center, Structures and Dynamics Div., Hampton, Aircraft Group, Hawthorne, Calif.(. In: Structures, Structural Dy- Va.) and R. T. Haftka (Illinois Institute of Technology, Chicago, III.). namics, and Materials Conference, 21st, Seattle, Wash., May 12-14, In: Structures, Structural Dynamics, and Materials Conference, 21st, 1980, Technical Papers. Part 2. New York, Seattle, Wash., May 12-14, 1980, Technical Papers. Part 2. American Institute of Aeronautics and Astronautics, Inc., 1980, p. New York, American Institute of Aeronautics and 595-603. 6 refs. Contract No. F33615-78-C-3221. (AIAA 80-0765) A technique is described whereby an arbitrary number of Astronautics, Inc., 1980, p. 529-538. 15 refs. Grant No. NAG1-5. (AIAA 80-0755) transfer functions of sensor outputs to a control surface input can be A procedure is presented that incorporates the influence of blended to form a feedback signal that is suitable for controlling a potential global damage conditions into the design process for flutter mode. An attractive feature of the technique, which couples minimum-mass wing-box structures. The procedure is based on the concepts of the Nyquist Criterion with a least squares fit mathematical-programming optimization techniques. Material- procedure, is that it utilizes data which are readily measurable, strength, minimum-gage, and panel-buckling constraints are intro- thereby allowing for the rapid improvement of the control law once duced by penalty functions, and Newton's method with approximate the empirical results are available. A theoretical description of the second derivatives of the penalty terms is used as the search method is presented and its relationship to alternative methods is algorithm to obtain minimum-mass designs. A potential global discussed. An analytical example is presented which depicts a 70 damage condition is represented by a structural model with the percent improvement in the flutter dynamic pressure of the YF-1 7 damaged components removed. Example minimum-mass designs are flutter model. Further results obtained during an analog simulation obtained that simultaneously satisfy the constraints of the damaged and a wind tunnel test of the same model are also presented. and undamaged configurations of both graphite-epoxy and aluminum (Author) wing-box structural models. These e*amples are designed with and without the influence of potential damage conditions, and results A80-35058 * # Design for active flutter suppression and gust indicate that for equal mass cases the residual strength of a damaged alleviation using state-space aeroelastic modeling. M. Karpel (Stan- structure is higher when the influence of potential damage is ford University, Stanford, Calif.). In: Structures, Structural Dynam- properly included in the design from the outset. Results of these ics, and Materials Conference, 21st, Seattle, Wash., May 12-14,1980, Technical Papers. Part 2. New York, American examples also identify the minimum structural mass increase Institute of Aeronautics and Astronautics, Inc., 1980, required to increase residual strength levels. (Author) p . 604-611. 20 refs. Grant No. NGL-05-020-243. (AIAA 80-0766) An analytical design technique for an active flutter-suppression A80-35052 • # Release-rate calorimetry of multilayered mate- and gust-alleviation control system is presented. It is based on a rials for aircraft seats. L. L. Fewell, J. A. Parker (NASA, Ames rational approximation of the unsteady aerodynamic loads in the Research Center, Moffett Field, Calif.), F. Duskin, H. Spieth, and E. entire Laplace domain, which yields matrix equations of motion with Trabold (Douglas Aircraft, Co., Long Beach, Calif.(. In: Structures, constant coefficients. Some existing rational approximation schemes Structural Dynamics, and Materials Conference, 21st, Seattle, Wash., are reviewed, and a new technique which yields a minimal number of

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augmented states for a desired accuracy is presented. The state-space and low-speed wind tunnel tests of a semispan model. The model aeroelastic model is used to design a constant gain, partial-feedback represents a DC-10 derivative with increased wing span and an active control system, which simultaneously assures stability and optimizes aileron surface, responding to vertical acceleration at the wing tip. A any desired combination of gust response parameters throughout the control law satisfying both flutter and gust load constraints is entire flight envelope. (Author) presented and evaluated. In general, the beneficial effects predicted by analysis are in good agreement with experimental data. (Author) 480-35060 # F-16 flutter suppression system investigation. R. P. Peloubet, Jr., R. L. Hailer, and R. M. Bolding (General 480-35065 ft Advanced composite structure repair guide. C. Dynamics Corp., Fort Worth, Tex.). In: Structures, Structural E. Beck (USAF, Flight Dynamics Laboratory, Wright-Patterson AFB, Dynamics, and Materials Conference, 21st, Seattle, Wash., May Ohio"). In: Structures, Structural Dynamics, and Materials Confer- 12-14, 1980, Technical Papers. Part 2. New ence, 21st, Seattle, Wash., May 12-14, 1980, Technical Papers. Part York, American Institute of Aeronautics and Astronautics, Inc., 2. New York, American Institute of Aeronautics 620-634. 17 refs. Contract No. F33615-77-C-3081. (AIAA 1980. p. and Astronautics, Inc., 1980, p. 674-678. 13 refs. USAF-Navy- 80-0768) sponsored research. (Al AA 80-07 74) A study was conducted to determine the feasibility of employ- A need for composite repair technology is discussed. Considera- ing active controls on the F-16 to suppress wing/store flutter for tion is given to composites used in helicopters, space and missile several external store configurations. It was determined that the systems, and fixed-wing aircraft. The status of a federal government existing flaperons, with modifications to the integrated servoactua- sponsored program which will result in the first edition of a repair tort, were effective in suppressing flutter. A separate analog guide is presented. V.T. computer study was conducted to examine the feasibility of measuring the flutter suppression system open-loop frequency response function (FRF(. It was determined that the function could 480.35066 II Repair of advanced composite structures. S. H. be successfully measured below the unaugmented flutter speed, Myhre and J. D. Labor (Northrop Corp., Hawthorne, Calif.). In: where the feedback loop can be physically opened, and above the Structures, Structural Dynamics, and Materials Conference, 21st, flutter speed, where it cannot. The F-16 flutter model was tested Seattle, Wash., May 12-14, 1980, Technical Papers. Part 2. with active flaperons. Open-loop FREt were successfully measured in New York, American institute of Aeronautics and the wind tunnel environment both with the feedback loop physically Astronautics, Inc., 1980, p. 679-686. 7 refs. Contract No. opened and with the loop closed. These measurements provided F33615-76-C-3017. (AIAA 80-0776) guidance in the selection of sensor locations and feedback control A large-area composite structure program it reviewed. The laws to suppress flutter. Control law variations were made to obtain objective of the program is to develop repair techniques which would the desired FRF characteristics. A 100% increase in dynamic pressure restore as much as possible of the original material strength. Five above the flutter dynamic pressure was demonstrated. (Author) large panels were repaired and subjected to static tests. The repair of a speedbrake damaged in service is described. V. T. 480.35061 ft Recent development of the YF-17 active flutter suppression system. C. Hwang, E. H. Johnson, and W. S. Pi A80-35070 ft Honeycomb sandwich joints for primary struc- (Northrop Corp., Aircraft Group, Hawthorne, Calif.). In: Structures, ture. U. Soudak (Israel Aircraft Industries, Ltd., Lod, Israel) and R. Structural Dynamics, and Materials Conference, 21st, Seattle, Wash., A. Hamm (Boeing Commercial Airplane Co., Seattle, Wash.). In: May 12-14, 1980, Technical Papers. Part 2. New Structures, Structural Dynamics, and Materials Conference, 21st, York, American Institute of Aeronautics and Astronautics, Inc., Seattle, Wash., May 12-14, 1980, Technical Papers. Part 2. 1980, 635-648. 5 refs. Contract No. F33615-78-C-3221. (AIAA p. New York, American Institute of Aeronautics and 80-0769) 706-711. (AIAA 80-0780) Active wing/store flutter suppressing systems were demonstrated Astronautics, Inc., 1980, p. Analysis methods and joint design details developed for adhe- in 1977 in a series of wind tunnel tests on a YF-17 scale model. In sively bonded aluminum honeycomb in aircraft primary structure are order to substantially improve the suppression system performance, described. Joint design details, which were tested for strength, new control laws were developed based on multiple feedback loops, durability and environmental resistance, provide a low cost design multiple control surfaces, or both. For test safety, a flutter sensing that is structurally efficient and durable. Weight and cost savings, unit and a new store, functioning as a flutter stopper, were designed producibility, and durability have been confirmed by five years of and fabricated. Test monitoring programs were organized on a service experience on the YC-14 Empennage primary structure. The Hewlett-Packard 5451C Fourier Analyzer that permitted a real time analysis considers the effect of the core on face sheet stress, the assessment of the control law effectiveness. One of the monitoring effect of face sheet eccentricity and also a failure analysis method for. programs generated the aircraft open loop transfer function and square edge panels; in addition, it allows strength/weight optimiza- Nyquist plots in the supercritical region while the flutter suppression )Author( loop was closed. In the tests performed in late 1979, the new control tion procedures for honeycomb design. laws were applied to suppress a severe flutter condition to 70% above the uncontrolled flutter dynamic pressure. Postanalysis of the test A80-35072 ft Damage tolerant design and test considerations data indicated the potential to increase the dynamic pressure to an in the engine structural integrity program. W. D. Cowie and T. A. even higher level. (Author) Stein (USAF, Aeronautical Systems Div., Wright-Patterson AFB, Ohio). In: Structures, Structural Dynamics, and Materials Confer- ence, 21st, Seattle, Wash., May 12-14, 1980, Technical Papers. Part A80-35062 • ft Wind tunnel investigation of active controls technology applied to a DC-10 derivative. B. A. Winther, W. A. 2. New York, American Institute of Aeronautics Shirley, and R. M. Heimbaugh (Douglas Aircraft Co., Long Beach, and Astronautics, Inc., 1980, p. 723-728. (AIAA 80-0784) Calif.). In: Structures, Structural Dynamics, and Materials Confer- Damage-tolerance philosophy and revised durability require- ence, 21st, Seattle, Wash., May 12-14, 1980, Technical Papers. Part ments incorporated into the engine structural integrity program 2. New York, American Institute of Aeronautics (ENSIP) are discussed. Specific design and test criteria under and Astronautics, Inc., 1980, p. 649-655. Contract No. NAS1-15327- consideration for the next revision of MIL-E-5007D are outlined. V. T. 02. (AIAA8O-0771) Application of active controls technology to reduce aeroelastic response offers a potential for significant payoffs in terms of A80-35073 ft Experimental investigation of flutter in mid- aerodynamic efficiency and structural weight. As part of the NASA stage compressor designs. R. R. Jutras (General Electric Co., Energy Efficient Transport program, the impact upon flutter and Evendale, Ohio) and H. R. Bankhead (USAF, Wright Aeronautical gust load characteristics has been investigated by meant of analysis Laboratories, Wright-Patterson AFB, Ohio). In: Structures, Struc-

333 A80-35074

tural Dynamics, and Materials Conference, 21st, Seattle, Wash., May Technical Papers. Part 2. New York, American 12. 14, 1980, Technical Papers. Part 2. New Institute of Aeronautics and Astronautics, Inc., 1980, p. 761-770. 12 York, American Institute of Aeronautics and Astronautics, Inc., refs. Grant No. AF-AFOSR-77-3423D Contract No. 1980, p. 729-740. (AIAA 80-0786) F33615-79-C-3224. )AIAA 80-0795) Blade instability related to compressor mid-stage-type rotor A set of closed-form solutions to describe the effect of fibrous blades is studied with emphasis placed on negative incidence and composite materials on the static aeroelastic characteristics of swept choke flutter. Consideration is given to experimental data obtained and unswept wings are presented. The aeroelastic characteristics to define blade instability boundaries for a quasi-continuous grid of considered are wing divergence, spanwise center of pressure location blade geometries and aerodynamic environment conditions. V.1. and flexible-to-rigid lift. Examples of the use of these expressions are presented. A simple, but accurate, matrix method for static A80-35074 # An optimization method for the determina- aeroelastic analysis is also discussed, together with examples to tion of the important flutter modes. E. Nissim and I. Lottati illustrate the potential for aeroelastic tailoring of forward swept )Technion - Israel Institute of Technology, Haifa, Israel). In: wings. (Author) Structures, Structural Dynamics, and Materials Conference, 21st, Seattle, Wash., May 12-14, 1980, Technical Papers. Part 2, A80-35078 # A wind tunnel demonstration of the principle New York, American Institute of Aeronautics and of aeroelastic tailoring applied to forward swept wings. V. C. Sherrer, Astronautics, Inc., 1980, p. 741-747. 5 refs. )AIAA 80-0790) T. J. Hertz, and M. H. Shirk )USAF, Flight Dynamics Laboratory, Several methods proposed for the determination of the impor- Wright-Patterson AFB, Ohio). In: Structures, Structural Dynamics, tant aircraft flutter modes are briefly reviewed. A new method is and Materials Conference, 21st, Seattle, Wash., May 12-14, 1980, developed which avoids the need to assume constant values for Technical Papers. Part 2. New York, American modal responses and systematic recomputations of the flutter speeds Institute of Aeronautics and Astronautics, Inc., 1980, p. 771-780. 17 of large arrays of reduced-order systems. V.T. refs. )AIAA 80-0796) The principle of aeroelastic tailoring with advanced composite materials to increase the divergence speed of a forward swept wing A80-35075 • II Wing/store flutter with nonlinear pylon stiff- has been demonstrated through low speed wind tunnel tests. The ness. R. N. Desmarais and W. H. Reed, III (NASA, Langley, Research approach was to perform a low cost, fairly simple wind tunnel test Center, Structures and Dynamics Div., Hampton, Va.). In: Struc- on a variable sweep cantilever wing model. Available analytical tures, Structural Dynamics, and Materials Conference, 21st, Seattle, methods were shown to accurately predict the divergence speed of Wash., May 12-14, 1980, Technical Papers. Part 2. both aluminum and composite plate structures in the subsonic speed New York, American Institute of Aeronautics and Astronautics, range. Methods were evaluated for predicting the onset of divergence Inc., 1980, p. 748-753. 8 refs. )AIAA 80-0792) using subcritical wind tunnel data. Results of the analyses and tests Recent wind tunnel tests and analytical studies show that a store are presented in this report. (Author) mounted on a pylon with 'soft' pitch stiffness provides substantial increase in flutter speed of fighter aircraft and reduces dependency of flutter on mass and inertia of the store. This concept, termed the A80-35086 # Finite element analysis of F-16 aircraft canopy decoupler pylon, utilizes a low-frequency control system to maintain dynamic response to bird impact loading. R. E. McCarty )USAF, pitch alignment of the store during maneuvers and changing flight Flight Dynamics Laboratory, Wright-Patterson AFB, Ohio). In: conditions. Under rapidly changing transient loads, however, the Structures, Structural Dynamics, and Materials Conference, 21st, alignment control system may allow the store to momentarily Seattle, Wash., May 12-14, 1980, Technical Papers. Part 2. bottom against a relatively stiff backup structure in which case the New York, American Institute of Aeronautics and pylon stiffness acts as a hardening nonlinear spring. Such structural Astronautics, Inc., 1980, p. 841-852. 23 refs. (AIAA 80-0804) nonlinearities are known to affect not only the flutter speed but also The finite element analysis of F-16 canopy response to bird the basic behavior of the instability. This paper examines the impact is presented. The general requirements for nonlinear analysis influence of pylon stiffness nonlinearities on the flutter characteris- of transparency bird impact is pointed out, and the results of such analyses for the F-16 canopy are given. The material nonlinearity, tics of wing-mounted external stores. (Author) geometrical nonlinearity, and coupling between the impact loads and the resulting dynamic response are compared in regard to their A80-35076 # Aeroelastic tailoring of a forward swept wing relative importance; it is shown that coupling is the most significant and comparisons with three equivalent aft swept wings. W. E. of these factors. It is concluded that such analyses can be successful Triplett (McDonnell Aircraft Co., St. Louis, Mo.). In: Structures, only if they can realistically simulate the effects of load-response Structural Dynamics, and Materials Conference, 21st, Seattle, Wash., coupling, although the nonlinear finite element computer program May 12-14, 1980, Technical Papers. Part 2. New used here provided accurate and efficient results. A. T. York, American Institute of Aeronautics and Astronautics, Inc., 1980, p. 754-760. 9 refs. )AIAA 80'0794) A80-35092 # Durability and consistency of composite com- The structural feasibility of using aeroelastic tailoring of ponents. A. C. Jackson )Lockheed-California Co., Burbank, Calif.). laminated composite material for a forward swept wing (FSW) on a In: Structures, Structural Dynamics, and Materials Conference, 21st, high performance fighter aircraft has been analytically evaluated. An Seattle, Wash., May 12-14, 1980, Technical Papers. Part 2. optimized design is obtained with zero weight penalty for Static New York, American Institute of Aeronautics and divergence by the use of a matrix dominated unbalanced composite Astronautics, Inc., 1980, p. 896-901. )AIAA8O-0811) ply Iayup. The optimized FSW is compared with three equivalent aft The paper discusses the Advanced Composite Vertical Fin swept wings )ASWs) which are evaluated for the same design program and the advanced manufacturing development of a compos- requirements. The FSW compares favorably with the ASWs in terms ite empennage component for L-101 1 aircraft The tests demonstrate of flutter and aircraft roll rate for aileron deflections, The FSW production qualities and static strength for graphite/epoxy compo- requires more structural weight and has higher induced aerodynamic nents. Accelerated durability testing of coupons and subcomponents drag than the ASWs because of outboard air load buildup during high was made, but the evaluation of the effects of flight environments on load factor maneuvers. (Author) a real-time basis takes many years. A program is underway to test components to demonstrate producibility and static strength of A80-35077 # Aeroelastic tailoring of forward swept compos- graphite/epoxy components; testing of components in a cyclic ite wings. T. A. Weisshaar )Virginia Polytechnic Institute and State environment representative of flight and ground storage is being University, Blacksburg, Va.). In: Structures, Structural Dynamics, made which is expected to take 3-1/2 yrs to represent 20 yrs of and Materials Conference, 21st, Seattle, Wash., May 12-14, 1980, service. A. T.

334 A80-35183

A80-35093 # Elevated temperature structural testing of ad- validity of nonstationary gust models such as the transient gust- vanced missiles. 0. R. Otto and G. J. Inukai (McDonnell Douglas encounters, and answer questions, such as the possible inapplicability Astronautics Co., St. Louis, Mo.). In: Structures, Structural Dynam- of the Taylor-von Karman turbulence theory near hovering modes. ics, and Materials Conference, 21st, Seattle, Wash., May 12-14, 1980, A. T. Technical Papers. Part 2. New York, American Institute of Aeronautics and Astronautics, Inc., 1980, p. 902-907. A80-35098 # Integrated thermal-structural finite element (AIAA 80-0812) analysis. E. A. Thornton, P. Decahaumphai (Old Dominion Univer- Structural tests at room and elevated temperature were conduc- sity, Norfolk, Va.), and A. R. Wieting (NASA, Langley Research ted on a full-scale aft airframe section of the Advanced Strategic Center, Structures and Dynamics Div., Hampton, Va.). In: Struc- Air-Launched Missile (ASALM). Loads applied at room temperature tures, Structural Dynamics, and Materials Conference, 21st, Seattle, represented conditions during captive carry and ejection. Test data Wash., May 12-14, 1980, Technical Papers. Part 2. are shown to agree well with theory. Loads applied at temperatures New York, American Institute of Aeronautics and Astronautics, up to 1200 F represented conditions during ramjet flight. The high Inc., 1980, p. 957-969. 19 refs. )AIAA 80-0717) heating rates and temperature levels produced unanticipated and An integrated thermal- structural finite element approach for invalid response from some instrumentation. These events will be efficient coupling of thermal and structural analysis is presented. An described and guidelines for high temperature testing will be integrated thermal-structural rod element is developed and used in presented. Although limited elevated-temperature test data were four thermal-structural applications; the accuracy of this integrated obtained, structural verification of the airframe was achieved. approach is illustrated by comparisons with the customary approach )Author) of finite difference thermal-finite element structural analyses. Results show that integrated thermal-structural analysis of structures mod- A80-35094 // Structural design loads for future airplanes. P. eledwith rod elements is more accurate than conventional analysis, Milns )Boeing Military Airplane Co., Seattle, Wash.). In: Structures, and that its further development promises significant results. A. T. Structural Dynamics, and Materials Conference, 21st, Seattle, Wash., May 12-14, 1980, Technical Papers. Part 2. New York, American Institute of Aeronautics and Astronautics, Inc., A80-35100 • ft Practical design considerations for a flight- 1980, p. 908-914. 10 refs. )AIAA 80-0813) worthy higher harmonic control system. E. R. Wood and R. W. The paper demonstrates that many difficulties exist at the detail Powers )Hughes Helicopters, Culver City, Calif.). In: Structures, level in the interface between the stress analyst and the loads Structural Dynamics, and Materials Conference, 21st, Seattle, Wash., specialist. Additional work is required concerning the inclusion of May 12-14, 1980, Technical Papers. Part 2. New viscous effects into the design loads and improvement of maneuver York, American Institute of Aeronautics and Astronautics, Inc., design criteria. The present and future static load generation 1980, p. 978-986. 11 refs. Contract No. NAS1-14552. )AIAA techniques are discussed with examples of a tailless bomber and 80-0668; AHS Paper 80-67) supersonic vehicles. A. T. The paper discusses the design of a higher harmonic blade pitch control system for flight testing on an OH-6A helicopter. Alternative A80. 35096 II The Eccentuator . A new concept in actuation. designs for both the mechanical and electronic subsystems are also R. G. Musgrove )Vought Corp., Dallas, Tex.). In: Structures, presented. Among the recommendations set forth are: (1) use Structural Dynamics, and Materials Conference, 21st, Seattle, Wash., electronic analog methods instead of FFT software, delegating May 12. 14, 1980, Technical Papers. Part 2. New spectral analysis and self testing to an Electronic Control Unit; (2) York, American Institute of Aeronautics and Astronautics, Inc., use a digital rather than analog computer for increased flexibility in 1980, p. 933-937. )AIAA 80-0815) solution processing; and (3) locate HHC actuators in the nonrotating The Eccentuator is a bent beam actuator that compensates for system and separate these actuators from the primary control the lateral motion of the beam with an eccentric bearing on the system. It is concluded that a target weight for a prototype control support end of the beam. A unique indexing gear arrangement used system would be less than 1% of design gross weight and the with the bent beam and the eccentric bearing maintains the free end production weight of the future HHC system may be 0.5 of the of the beam in a plane normal to the hinge line; the bent weight of the aircraft. A. T. beam/eccentric bearing combination results in planar, arcuate motion. The arcuate motion is twice that achievable by rotating the A80-35101 II Engine environmental effects on composite bent beam alone. The supercritical contour in the region of the behavior. C. C. Chamis and G. T. Smith (NASA, Lewis Research control surface hinge line is thinner than a conventional airfoil Center, Cleveland, Ohio). In: Structures, Structural Dynamics, and contour; the thin contours and large hinge moments coupled with an Materials Conference, 21st, Seattle, Wash., May 12-14, 1980, aerodynamic requirement to keep the upper and lower surfaces from Technical Papers. Part 2. New York, American protuberances produced a need for an actuation system which did Institute of Aeronautics and Astronautics, Inc., 1980, p. 987-997. 7 not resolve the hinge moments with a force couple parallel to the refs. )AIAA 80-0695) surface reference plane. The actuator can be powered by hydraulic or The effects of turbojet engine environmental saturation mois- mechanical inputs; applications of the Eccentuator are also discussed, ture and temperatures up to 300 F on composites were investigated. including the actuation of variable camber surfaces on supercritical It was found that epoxy resin composites absorbed the most wings. A. T. moisture (2 wt %), while poly imide resin composites absorbed 0.8%. High moisture and 250 F degraded the flexular and interlaminar A80-35097 # Review of nonstationary gust-responses of shear properties, and the environmental and impact conditions flight vehicles, G. H. Gaonkar (Indian Institute of Science, Bangalore, severely damaged epoxy composites. The impact damage of fiber India). In: Structures, Structural Dynamics, and Materials.Confer- composites in moisture-temperature environments can be assessed ence, 21st, Seattle, Wash., May 12-14, 1980, Technical Papers. Part with finite element and composite mechanics analyses. Engine 2. New York, American Institute of Aeronautics operation environmental conditions of 0.8% moisture and 140 F had and Astronautics, Inc., 1980, p. 938-956. 85 refs. (AIAA 80-0703) no discernible effect on the fatigue resistance of composite fan exit The paper reviews nonstationary turbulence and its influence on guide vanes, which can be designed to exceed engine operational aircraft, rotor, and propeller systems. A common nonstationary requirements using composite materials. A. T. analytical approach is used, with emphasis on concepts instead of details. The necessity for this approach and its feasibility for A80-35183 ft Development and application concepts for predicting a complete set of gust and response statistics together with trainer and combat-trainer versions of combat jet aircraft (Koncepcja correlations using limited test data are appraised. It is concluded that rozwoju i zastosowania bojowych wersji odrzutowych samolotow due to extensive analytical background developed to date more szkolno-ereningowych i szkolno-bojowych). E. Cichosz. Technika experimental research is required. The research would verify the Lotnicza iAstronautyczna, vol. 35, Apr. 1980, p. 5-9. In Polish.

335 A80-351 84

A method for classifying trainer and combat-trained jets is Italy). (A/AS, Convegno Nazionale, 7th, Cagliari, Italy, Sept. 1979.) proposed, along with a method for comparing such aircraft. For Ingegneria, Mar-Apr. 1980, p. 80-101. In Italian. illustration, the latter method is applied to a comparison of some The use of advanced composite materials in aeronautical representative British, French, German, and Italian trainer and structures is discussed. Mechanical properties are given, and the combat aircraft. The historical development, specifications, and production of carbon fibers is considered, including the pyrolysis of principal parameters of the foreign combat aircraft are examined. polyacrylonitrile and of rayon. The characteristics and high- V. P. temperature applications of epoxy resins and polyimide resins are examined. Attention is given to the process of polymerization of A80-35184 II Selected methods for defining engine operating ranges in the investigation of aircraft accidents. II (Wybrane composite materials and to the process of realizing a multistrate metody okreslania zakresow pracy silnika podcras badania wypad. laminate. With regard to methods of testing, the determination of the kow lotniczych. II). S. Andruszkiewicz, J. Borgon, and M. Stukonis. tensile strength and of the elastic modulus of a composite is discussed, including compression and bending tests; the determina- Technika Lotnicza i .4stronautyczna, vol. 35, Apr. 1980, p. 10, 11. tion of shear resistance is also considered. In Polish. J.P.B. The determination of engine operating ranges is an important factor in aircraft accident investigations. The three methods exam- A80-35801 # Alkyl derivatives of resorcinol used as antioxi- ined in the present paper are based, respectively, on the use of the dants in jet fuels (Alkilproizvodnye rezortsina v kachestve antiokisli. relationship between the rate of turbine blade cooling on the time tel'nykh prisadok k reaktivnym toplivam). 0. P. Lykov, T. P. elapsed after discontinuation of engine operation, the determination Vishniakova, N. V. Tumar, E. P. Seregin, V. N. Prokudin, and I. A. of the color of oxide films on blade fracture surfaces, and the basis Konishcheva (Moskovskii Institut Neftekhimicheskoi i Gazovoi Pro' of instrument readings. V. P. myshlennosti, Moscow, USSR). Khimiia i Tekhnologiia Top/iv I Masel, no. 5, 1980, P. 18-21. 6 refs. In Russian. A80-35185 II Effects of electric fluctuations in electric Several alkylated resorcinols are examined with reference to power systems of flight vehicles (Skutki drgan elektrycznych w their oxidation inhibiting properties when added, in concentrations wezlach elektroenergetycznych obiektow latajacych). Z. Zmudzinsk i of 0.003-0.01%, to hydrogenated jet fuels. The investigated alkylated (Instytut Techniczny Wojsk Lotniczych, Warsaw, Poland). Technika resorcinols include: 5-methyl resorcinol, mono-tert-butyl résorcinol, Lotnicza iAstronautyczna, vol. 35, Apr. 1980, p. 12-14, In Polish. di-tert-butyl resorcinol, 2.4,4-triethyl-5-methyl resorcinol, and tetra- The reasons for the premature wear of brushes observed in ethyl resorcinol. These compounds are shown to improve antioxida- aircraft electric power systems of the GSR-3000 type are studied and tion stability of the fuels without any detrimental effects on fuel are attributed to electric fluctuations in these power systems, due to performance. V. L. faulty voltage control. Remedies to this situation are proposed. V.P. A80-35802 # Mannich base used as an antioxidant in jet A80-35404 General aviation altimetry errors for collision fuels (Osnovanie Mannikha kak antiokislitel'naia prisadka k reaktiv. avoidance systems. A. D. Mundra (Mitre Corp., McLean, Va.). nym toplivam). T. P. Vishniakova, I. A. Golubeva, L. P. Gutnikova, Navigation, vol. 26, Winter 1979-1980, p. 267-274. 14 refs. E. P. Seregin, V. N. Prokudin, and V. M. Veselianskaia (Moskovskii The present compilation of in-flight test data yields histograms Institut Neftekh imicheskoi i Gazovoi Promyshlennosti, Moscow, of errors in automatically reported altitude and errors in indicated USSR). Khimiia I Tekhno/ogiia Top/iviMasel, no. 5, 1980, p. 39-42. altitude for domestic general aviation aircraft. Two fully automatic In Russian. collision avoidance systems, currently under consideration by the The efficiency of 4- (N,N-dimethylaminomethylene) .2,6.di-tert- Federal Aviation Administration, are examined. These are the butyl phenol (Mannich base) as an oxidation inhibitor for jet fuels is Automatic Traffic Advisory and Resolution Service system and the investigated by successive heating techniques. The results of the Beacon-based Collision Avoidance system. Furthermore, the auto- experiments involving several hydrogenated fuels indicate that this matically reported altitude is being increasingly used in the Air additive, when used in a concentration of 0.003%, provides the same Traffic System, as exemplified by the implementation of Conflict efficiency as ionol at a lower cost V. L. Alert in the en route air space. V. P. A80-35498 • # Noise suppression due to annulus shaping of A80.35898 # The impact of fuels on aircraft technology an inverted-velocity-profile coaxial nozzle. J. Goodykoontz and U. through the year 2000. J. Grobman and G. M. Reck (NASA. Lewis von Glahn (NASA, Lewis Research Center, Cleveland, Ohio). Research Center, Cleveland, Ohio). American Institute of Aeronau- Acoustical Society of America, Meeting, 99th, Atlanta, Ga., Apr. tics and Astronautics. International Meeting and Technical Display 21-25, 1980, Paper. 25 p. 8 refs. on Global Technology 2000, Baltimore, Md., May 6-8, 1980, Paper Previous studies have shown that an inverted-velocity-profile 80-0896. 24 p. 29 refs. coaxial nozzle for use with supersonic cruise aircraft produces less jet In the future, it may be necessary to use jet fuels with a broader noise than an equivalent conical nozzle. Furthermore, decreasing the range of properties in order to insure a more flexible and reliable annulus height (increasing radius ratio with constant flow) results in supply and to minimize energy consumption and processing costs at further noise reduction benefits. In the present model-scale study, the refinery. This paper describes research being conducted to (1) the annulus shape, that is, height, was varied by an eccentric determine the potential range of properties for future jet fuels, (2) mounting of the annular nozzle with respect to a conical core nozzle. establish a data base of fuel property effects on propulsion system Acoustic measurements were made in-the flyover plane below the components, (3) evolve and evaluate advanced component technolo- narrowest portion of the annulus and at 90 deg and 180 deg from gy that would permit the use of broader property fuels and )4) this point. The model-scale spectra are scaled up to engine size (1.07 identify technical and economic trade-offs within the overall fuel m diameter) and the perceived noise levels for the eccentric and production-air transportation system associated with variations in baseline concentric inverted-velocity-profile coaxial nozzles are com- fuel properties. (Author) pared over a range of operating conditions. The implications of the acoustic benefits derived with the eccentric nozzle to practical A80-35906 • # Status of NASA full-scale engine aeroelasticity applications are discussed. (Author) research. J. F. Lubomski (NASA, Lewis Research Center, Cleveland, Ohio). In: Structures, Structural Dynamics, and Materials Confer- A80-35771 # Technology of graphite-resin composite mate- ence, 21st, Seattle, Wash., May 12-14, 1980, Technical Papers. riaIiiid their application in the aeronautical industry (Tecnologia Conference sponsored by AIAA. ASME, ASCE, and AHS. New York, del materiali compositi grafite-resina e loro applicazioni nel- American Institute of Aeronautics and Astronautics, Inc., 1980. 18 l'industria aeronautica). G. Romeo (Torino, Politecnico, Turin, p. 14 refs,

336 A80-35958

The paper presents data relevant to several types of aeroelastic material designed for use in the fan exhaust duct walls of the OCSEE instabilities which have been obtained using several types of turbojet UTW )under-the-wing) engine and to compare it with other means of and turbofan engines. Special attention is given to data relative to acoustic suppression. The paper includes comparison of the acoustic separated flow (stall) flutter, choke flutter, and system mode suppression to the original design for the QCSEE UTW engine fan instabilities. The discussion covers the characteristics of these duct which consisted of phased SDOF (single-degree-of-freedom) instabilities, and a number of correlations are presented that help wall treatment and a splitter and also with the splitter removed. The identify the nature of the phenomena. M.E.P. method of approach consisted of mounting the UTW engine on the test stand of the Lewis Engine Noise Facility with an appropriate A80-35907 8 Progress and trends in propeller/prop-fan noise array of far-field microphones in order to measure the acoustic levels technology. F. B. Metzger (United Technologies Corp., Hamilton of the various configurations. Peak suppression was abáut as Standard Div., Windsor Locks, Conn.). American Institute of predicted with the bulk absorber configuration; however, the Aeronautics and Astronautics, International Meeting and Technical broadband characteristics were not attained. Post-test inspection Display on Global Technology 2000, Baltimore, Md., May 68, 1980, revealed surface oil contamination on the bulk material which could Paper 80-0856. 16 P. 53 refs. have caused the loss in bandwidth suppression. (Author) The major contributions to the understanding and control of propeller noise that have occurred in the past 60 years are described. A80-35953 7 Study and experimental tests of fibrous acous- It is shown that early researchers recognized the propeller noise tic treatment for reduction of fan noise from XF3-1 turbofan engine. problem and attempted to model it mathematically, noting that this R. Sasaki (Japan Defense Agency, Technical Research and Develop- early research was hampered by lack of instrumentation. Attention is ment Institute, Tokyo, Japan), K. Ishizawa, and K. Higashi given to progress made in development of theoretically based noise (lshikawajima-Harima Heavy Industries Co., Ltd., Tokyo, Japan). prediction procedures and in systematically measuring propeller American Institute of Aeronautics and Astronautics, Aeroacoustics noise from 1945 until the dominance of jet propulsion in transport Conference, 6th, Hartford, Conn., June 4-6, 1980, Paper 80 L 0988. 9 aircraft caused a decline of interest. Finally, it is shown that the P. recent interest in fuel efficient propulsion has caused a renewed The characteristics of an acoustic treatment employing fibrous interest in propeller aircraft, and that rapid progress is now being material and its effect on fan noise reduction radiated from a made in control of noise of all classes of propeller aircraft in the far turbofan engine have been studied. The predominant feature of the field at locations around airports as well as in the cabins of transport treatment is that it is composed of a fibrous layer backed with an air aircraft. M.E.P. cavity, which facilitates the control of acoustic impedance of the treatment. This paper presents the design procedures for the treatment developed through this study and results of the tests which A80'35912 /1 Experimental investigations on the vibration were done to investigate its mechanical and acoustic properties. As a of blades due to a rotating stall. K. Ishihara )Kawasaki Heavy result of acoustic tests using an XF3-1 turbofan engine, it is shown Industries, Ltd., Akashi, Japan) and M. Funakawa )Okayama, that not only fan discrete tones but also combination tones can be Science University, Okayama, Japan). JSME, Bulletin, vol. 23, Mar. attenuated effectively by the treatment. (Author) 1980, p. 353-360. The unsteady aerodynamic forces acting on blades due to a rotating stall are studied. Characteristics such as velocity, pressure A80-35957 // Experimental verification of propeller noise fluctuations and blade vibration are measured and relations between prediction. G. P. Succi (MIT, Cambridge, Mass.), D. H. Munro, and J. them are studied by using a single stage compressor. It is found that A. Zimmer. American Institute of Aeronautics and Astronautics, the velocity and the width of the stall cell are significant factors Aeroacoustics Conference, 6th, Hartford, Conn., June 4-6, 1980, governing the aerodynamic force. It is concluded that it is reasonable Paper 80.0994. 14 p. 12 refs. Contract No. NAS1-15154. to regard the square wave of the velocity fluctuation as the Results of experimental measurements of the sound fields of aerodynamic force acting on the blade. M.E.P. 1/4-scale general aviation propellers are presented and experimental wake surveys and pressure signatures obtained are compared with theoretical predictions. Experiments were performed primarily on a A80-35944 • 7 Transmission of high frequency sound waves 1C160 propeller model mounted in front of a symmetric body in an through a slug flow jet. S. P. Parthasarathy and A. Vijayaraghavan anechoic wind tunnel, and measured the thrust and torque produced (California Institute of Technology, Jet Propulsion Laboratory, by propeller at different rotation speeds and tunnel velocities, wakes Pasadena, Calif.). American Institute of Aeronautics and Astronau- at three axial distances, and sound pressure at various azimuths and tics, Aeroacouss'ics Conference, 6th, Hartford, Conn, June 4-6, tip speeds with advance ratio or tunnel velocity constant. Aero- 1980, Paper 80-0969. 12 p. 10 refs. Contract No. NAS7-100. dynamic calculations of blade loading were performed using airfoil An analysis has been performed of sound waves which propagate section characteristics and a modified strip analysis procedure. The in a pipe with gas flow. At the pipe exit these waves are partially propeller was then modeled as an array of point sound sources with reflected and the remainder are diffracted. The analysis is carried out each point characterized by the force and volume of the correspond- by resolving the sound at the exit into its Fourier components and ing propeller section in order to obtain the acoustic characteristics. then continuing the solution, which is a combination of elementary Measurements are found to agree with predictions over a wide range plane waves, beyond the exit. These waves are of two types: of operating conditions, tip speeds and propeller nacelle combina- homogeneous waves which propagate to infinity, and inhomogeneous tions, without the use of adjustable constants. A.L.W. waves with complex wave numbers which decay. The reflected waves are evaluated from the .inhornogeneous waves. At the boundary of A80-35958 " Acoustic measurements of three Prop-Fan the jet, refraction of the elementary plane waves is accounted for and models. B. M. Brooks (United Technologies Corp., Hamilton Stan- the far field sound is evaluated by the method of stationary phase. dard Div., Windsor Locks, Conn.). American Institute of Aeronautics Comparisons of the theoretical calculations are made with experi- and Astronautics, Aeroacoustics Conference, 6th, Hartford, Conn., mental results and with calculations of other theories. (Author) June 4-6, 1980, Paper 80-0995. 13 p. 16 refs. Contract No. NAS3-20614. A80'35952 .7 QCSEE fan exhaust bulk absorber treatment Results of NASA sponsored acoustic tests of three 2 ft. diameter evaluation. H. E. Bloomer and N. E. Samanich (NASA, Lewis models of the Prop-Fan (a small diameter, highly loaded, many- Research Center, Cleveland, Ohio). American Institute of Aero- bladed variable pitch advanced turboprop) are presented. The highly nautics and Astronautics, Aeroacoustics Conference, 6th, Hartford, swept model designed for noise reduction produces substantially less Conn., June 4-6, 1980, Paper 80-0987. 11 p. 8 refs. near field noise as simulated 9.8 Mach number cruise conditions than The purpose of the experimental program reported herein was the unswept or slightly swept models. It also produces less far field to evaluate the acoustic suppression capability of bulk absorber noise at conditions simulating takeoff and landing. The noise

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reduction mechanism is discussed. Correlation between harmonic ments and advanced concepts for the reduction of noise levels in noise measurements and theoretical predictions and between mea- three high-speed aircraft driven by propellers. Noise reductions of 25 sured and predicted acoustic pressure pulses is good. Shadowgraph to 28 dB are required to achieve a goal of an A-weighted sound level measurements which show the location of blade associated wave not greater than 80 dB. It is found that only a double-wall system, Patterns were obtained. Predicted and measured wave locations show with a limp inner wall or trim panel, can achieve the required noise good general agreement. Full scale near and far field noise is reductions. Weight penalties are estimated for the double-wall predicted. (Author) treatments. These penalties are 0.75% to 1.51% of the aircraft takeoff weight for the particular baseline designs selected. (Author) A80-35959 • # A collection of formulas for calculation of rotating blade noise - Compact and noncompact source results. F. A80. 35963 # An analytical model for study of interior noise Farassat (NASA, Langley Research Center, Hampton, Va.). American control for high-speed, propeller-driven aircraft. J. D. Revell, F. J. Institute of Aeronautics and Astronautics, Aeroacoustics Conference, Balena (Lockheed-California Co., Burbank, Calif.), and L. R. Koval 6th, Hartford, Conn., June 4-6, 1980, Paper 80-0996. 14 p. 23 refs. (Missouri- Rolla, University, Rolla, Mo.). American Institute of A unified approach is used to derive many of the current Aeronautics and Astronautics, Aeroacoustics Conference, 6th, Hart- formulations for calculation of discrete frequency noise for helicop- ford, Conn., June 4-6, 1980, Paper 80-1000. 11 p. 13 refs. ter rotors and propellers. Both compact and noncompact source An analytical method is described for prediction of the interior formulations are derived. The compact formulations are obtained as noise levels for propeller-driven aircraft, given the exterior noise the limit of noncompact source results. In particular, the linearized signature and its harmonic spectrum, and a description of the acoustic equations by Hawkingt and Lowson, Farassat, Hanson, fuselage sidewall structure and various candidate 'add-on' noise Woan and Gregorek, Succi, and Jou are derived in this paper. An control elements. The structural response is described by the theory interesting thickness noise formula b y Isom and its recent extension of Koval but simplified to consider the stiffeners as 'smeared' to the near field by Ffowcs Williams are also presented. The paper elements. The incremental transmission loss (TL) due to add- includes some comparisons of measured and calculated acoustic on—noise—control elements is derived from the Beranek and Work pressure signatures and spectra for an advanced propeller. The method. Comparisons between experimental data and the theory are theoretical results are obtained using a computer program developed presented. The method is reasonably accurate below the ring by the author and P. A. Nystrom. '(Author) frequency, but is somewhat conservative at normal incidence angle. This method is, however, expedient computationally, is economical A80-35960 # Propeller light aircraft noise at discrete fre- and permits rapid comparisons of noise-control penalties for various quencies. C. Dahan, L. Avezard, G. Guillien, C. Malarmey, and J. treatment concepts. (Author) Chombard (ON ERA, Châtillon-sous-Bagneux, Hauts-de-Seine, France). American Institute of Aeronautics and Astronautics, Aero- A80-35964 Analytical study of interior noise control by acoustics Conference, 6th, Hartford, Conn., June 4 .6, 1980, Paper /f fuselage design techniques on high-speed propeller- driven aircraft. J. 80-0997. 11 8 refs. p. D. Revell, F. J. Balena (Lockheed-California Co., Burbank, Calif.), To study the acoustic field of propelled light aircraft, a method and L. R. Koval (Missouri- Rolla, University, Rolla, Mo.). of in-flight measurements was implemented. The separation of noise American Institute of Aeronautics and Astronautics, Aeroacoustics Conference, sources is achieved by examination of the influence on the acoustic field of the relative set-up of the propeller and the engine. This shows 6th, Hartford, Conn., June 4-6, 1980, Paper 80-1001. 17 p. 11 refs. This study defines acoustical treatment mass penalties required that at high rotational speed, the propeller is the dominant source. to achieve an interior noise level of 80 dBA for propfan-powered Evaluating then the field due to steady/unsteady loading on the blades, one concludes that the former ones are the most acoustically aircraft at 0.8 Mach number. The method, described in a companion efficient. The analysis fly-over noise measurements, using an original paper combines Koval's theory for cylindrical shell noise trans- signal processing (Doppler effect compensation) makes the results mission loss )TL) with the Beranek and Work methods for 'add-on' obtained more complete. (Author) noise control element performance. Three different fuselage diameters are studied in connection with appropriate aircraft. Add-on A80-35961 * # Prediction of the interior noise levels of mass penalties range from 1.7 to 2.4 percent of aircraft takeoff gross high-speed propeller-driven aircraft. D. C. Rennison, J. F. Wilby, and weight (TOGW). Advanced Noise Reduction Designs which permit E. G. Wilby (Bolt Beranek and Newman, Inc., Canoga Park, Calif.). structural modification reduce these penalties to 1.5 percent of American institute of Aeronautics and Astronautics, Aeroacoustics TOGW for aluminum aircraft and 0.74 to 1.4 percent TOGW for Conference, 6th, Hartford, Conn., June 46, 1980, Paper 80' 0998. 12 fuselages constructed of composite materials. (Author) p. 8 refs. Contract No. NAS1.15426. The theoretical basis for an analytical model developed to A80-35965 • # Acoustic pressures on a prop-fan aircraft fuse- predict the interior noise levels of high-speed propeller.driven lage surface. B. Magliozzi (United Technologies Corp., Hamilton airplanes is presented. Particular emphasis is given to modeling the Standard Div., Windsor Locks, Conn.). American Institute of transmission of discrete tones through a fuselage element into a Aeronautics and Astronautics, Aeroacoustics Conference, 6th, Hart- cavity, estimates for the mean and standard deviation of the acoustic ford, Conn., June 4-6, 1980, Paper 80-1002. 11 p. 9 refs. Contract power flow, the coupling between a non-homogeneous excitation No. NAS3-20614. and the fuselage vibration response, and the prediction of maximum Acoustic pressure amplitude and phase distributions on the interior noise levels. The model allows for convenient examination of surface of a simulated fuselage (a rigid semi-cylinder) installed in an the various roles of the excitation and fuselage structural characteris- acoustically treated wind tunnel near a Prop-Fan model were tics on the fuselage vibration response and the interior noise levels, as measured. The test conditions simulated the relative tip Mach is required for the design of model or prototype noise control number and blade loading of a full scale Prop-Fan at high altitude 0.8 validation tests. (Author) Mach number cruise. Measurements were also made at equivalent microphone locations without the semi-cylinder to establish the A80-35962 • # Noise control prediction for high-speed, effects of the presence of a fuselage on the sound pressure propel ler'driven aircraft. J. F. Wilby, D. C. Rennison, E. G. Wilby amplitudes. These effects were found to be 6 dB at 90 degrees (Bolt Beranek and Newman, Inc., Canoga Park, Calif.), and A. H. incidence, decreasing to no effect at grazing incidence. Comparison Marsh (DyTec Engineering, Inc., Long Beach, Calif.). American of measurements and calculations uitng a Hamilton Standard Institute of Aeronautics and Astronautics, Aeroacoustics Conference, Prop-Fan noise calculation computer program showed good agree- 6th, Hartford, Conn., June 4-6, 1980, Paper 80-0999. 11 p. 14 refs. mentJ peak -level and in phase distribution. Continuous recordings Contract No. NAS1-15426. were also made of a Prop-Fan RPM sweep at constant simulated An analytical study is described which explores add-on treat- flight speed and a simulated flight speed sweep at constant Prop-Fan

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RPM. These showed smooth variations in noise level over the tip Cambridge, Mass.). American Institute of Aeronautics and Astro- Mach number range 0.878 to 1.143. (Author) nautics, Aeroacoustics Conference, 6th, Hartford, Conn., June 46, 1980, Paper 80-1013. 11 p. 10 refs. Grant No. NsG-1583. A80.35967 # A theoretical study of the coherence of jet The results of an experimental investigation of low frequency noise. W. G. Richarz (Toronto, University, Toronto, Canada). broadband noise (LFBN) radiated from model helicopter rotors are American Institute of Aeronautics and Astronautics, Aeroacoustics presented. The results are for a range of tip Mach numbers (Mt) up to Conference, 6th, Hartford, Conn., June 4-6, 1980, Paper 80- 1005. 9 0.50. The effect of rotor blade loading, advance ratio, tip speed, p. 18 refs. Research supported by the Natural Sciences and number of blades and free stream turbulence on the sound pressure Engineering Research Council of Canada and University of Toronto. level (SPL) and the spectrum of LFBN have been investigated. The Two point correlations and cross-spectra of jet noise are new peak SPL of LFBN appears to follow an M(4) law if the effect of rms tools available for jet noise diagnostics. They describe the temporal turbulence velocity is removed. The peak SPL of LFBN seems to as well as the spatial coherence of the radiated sound field. Usually saturate with increases in advance ratio and with blade loading, and is the coherence is limited to a relatively narrow 'beam', indicative of proportional to the square of the turbulence integral scale when the independent radiators. The theoretical description herein is a effect of rms turbulence velocity and Mt are removed. Also, a simple development of Ribner's self and shear noise formalism. Influences peak SPL scaling law for noise from a helicopter rotor in forward of source coherence, source strength distribution, and other param- flight due to convected sinusoidal gust is developed. The trend eters are illustrated with the aid of certain turbulent and mean flow predicted by this scaling law is found to be satisfactory for the models. Comparisons of predictions based on a 'realistic' source variation of the peak SPL of LFBN with tip speed. (Author) model with measurement show the two sets of data to be compatible. (Author) A80-35977 # Fan noise caused by the ingestion of anisotropic turbulence - A model based on axisymmetric turbulence A80-35968 // A unique coannular plug nozzle jet noise theory. E. J. Kerschen (GE Corporate Research and Development prediction procedure. P. K. Bhutiani (General Electric Co., Evendale, Center, Schenectady, N.Y.) and P. R. Gliebe (General Electric Co., Ohio). American Institute of Aeronautics and Astronautics, Aero- Aircraft Engine Business Group, Evendale, Ohio). American Institute acoustics Conference, 6th, Hartford, Coon., June 4-6, 1980, Paper of Aeronautics and Astronautics, Aeroacoustics Conference, 6th, 80-1007.11 p.22 refs. Contract No. NAS3.20619. Hartford, Conn., June 46, 1980, Paper W1021. 13 p. 23 refs. The work presents a method for predicting jet mixing and shock Contract No. NAS2.10002. noise spectra from coannular plug nozzles operated in the inverted An analytical model of fan noise caused by inflow turbulence, a velocity profile mode. It is shown that the jet mixing noise generalization of earlier work by Mani, is presented. Axisyrnmetric prediction method is based on the physics of the flow and its noise turbulence theory is used to develop a statistical representation of radiating characteristics, modeling the source spectrum, eddy con- the inflow turbulence valid for a wide range of turbulence properties. vection, and fluid shrouding in a simplistic fashion. Further, the Both the dipole source due to rotor blade unsteady forces and the shock noise prediction procedure is described, noting that it is an quadrupole source resulting from the interaction of the turbulence extension of the Fisher-Harper- Bourne method for conical nozzles. with the rotor potential field are considered. The effects of variations Finally, it is concluded that the method has the potential of being in turbulence properties and fan operating conditions are evaluated. extended to suppressors of complex geometries. M.E.P. For turbulence axial integral length scales much larger than the blade spacing, the spectrum is shown to consist of sharp peaks as the blade A80-35969 " # Noise from a vibrating propeller. H. L. Runyan passing frequency and its harmonics, with negligible broadband (Joint Institute for Advancement of Flight Sciences, Hampton, Va.). content. The analysis can then be simplified considerably and the American Institute of Aeronautics and Astronautics, Aeroacoustics total sound power contained within each spectrum peak becomes Conference, 6th, Hartford, Conn., June 46, 1980, Paper 80-1011. 8 independent of axial length scale, while the width of the peak is p. Contract No, NAS1.14605.13. inversely proportional to this parameter. Large axial length scales are This paper is concerned with an analytical study of the noise characteristic of static fan teat facilities, where the transverse from a vibrating propeller. The influence of airfoil thickness and of contraction of the inlet flow produces highly anisotropic turbulence. steady loading are also included to provide a basis for comparison. In this situation, the rotor/turbulence interaction noise is mainly The analysis was based on the concept of distributing sources and caused by the transverse component of turbulent velocity. (Author) doublets on the surface of the blade, which were multiplied by their appropriate strength factors. The noise in the plane of the propeller A80.35978 • # Analytical study of the effects of wind tunnel was dominated by the thickness noise. Moving the observer's position turbulence on turbofan rotor noise. P. R. Gliebe (General Electric to the propeller axis, the thickness noise and loading noise were zero, Co., Aircraft Engine Group, Cincinnati, Ohio). American Institute of and a pure sinusoidal noise was found, caused by the vibrations of Aeronautics and Astronautics, Aeroacoustics Conference, 6th, Hart- the propeller. (Author) ford, Conn., June 46, 1980, Paper 80-1022. 13 p. 16 refs. Contract No. NAS2-10002. An analytical study of the effects of wind tunnel turbulence on A80-35970 # Helicopter rotor thickness noise. C. Dahan and turbofan rotor noise was carried out to evaluate the effectiveness of E. Gratieux (ONERA, Châtillon-sous . Bagneux, Hauts.de-Seine, the NASA Ames 40 by 80-foot wind tunnel in simulating flight levels France). American Institute of Aeronautics and Astronautics, Aero. acoustics Conference, 6th, Hartford, Coon., June 4-6, 1980, Paper of fan noise. A previously developed theory for predicting rotor/ turbulence interaction noise, refined and extended to include 80-1012.11 p. 11 refs. The attention is focused on rotor blades thickness noise (flow first-order effects of inlet turbulence anisotropy, was employed to subsonic everywhere). The solution of the wave equation is written carry out a parametric study of the effects of fan size, blade number, in a closed form (frequency domain), which emphasizes the essential and operating line for outdoor test stand, NASA Ames wind tunnel, parameters for this field. On an other side, starting from an and flight inlet turbulence conditions. A major result of this study is estimation of the loads on the rotor disk (lifting line theory), the that although wind tunnel rotor/turbulence noise levels are not as acoustic emission due to loads is estimated in such a way that the low as flight levels, they are substantially lower than the outdoor test acoustic efficiency of blade thickness and loads can be compared. To stand levels and do not mask other sources of fan noise. (Author) compare experimental results and predictions, an original signal A80-35979 # Impact of flight effects on multitube suppres- processing method was designed, which compensates the Doppler sor design. J. P. Duponchel and P. Thomas (SNECMA, Paris, France). (Author) effect due to the helicopter motion. American Institute of Aeronautics and Astronautics, Aeroacoustics A80-35971 # Model rotor low frequency broadband noise at Conference, 6th, Hartford, Conn., June 46, 1980, Paper 80-1029. 16 moderate tip speeds. N. G. Humbad and W. L. Harris (MIT, p. 16 refs.

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The paper presents the acoustical variation obtained from static signatures, or influence vectors, were used for (1) determining and simulated flight tests with a multitube suppressor. A quantitative analytically optimum synchrophase angles and (2) diagnosing the Interpretation of these flight effects on multitube noise characteris- specific paths - airborne and structure-borne - of the noise into the tics and a prediction method are proposed. V. T. cabin. A number of significant conclusions are drawn from flight experiments in a Navy P-3C patrol aircraft. The results and A80-35980 # Simulation of high bypass ratio engine jet techniques from this work are applicable to improving the passenger noise flight effects by model jet wind tunnel test. H. Y. Lu and S. K. and crew comfort as well as equipment life in propeller-powered Lanter (Boeing Commercial Airplane Co.. Seattle, Wash.). American aircraft. (Author) Institute of Aeronautics and Astronautics, Aeroacoustics Conference, 6th, Hartford, Conn., June 4-6, 1980, Paper 80-1030. 7 p. 5 refs. A80-35984 /1 Noise transmission and control for a light, A wind tunnel model test was conducted to simulate the twin-engine aircraft, C. K. Barton and J. S. Mixson (NASA, Langley in-flight noise of high bypass ratio jets. Model nozzles representative Research Center, Hampton, Va.). American Institute of Aeronautics of JT9D and RB.21 1 engines were tested in a 9 by 9 foot wind and Astronautics, Aeroacoustics Conference, 6th, Hartford, Conn., tunnel where noise measurements were made on a two-foot sideline. June 4-6, 1980, Paper 80-1036. 8 p. 8 refs. These measurements were scaled and extrapolated to full scale One of the dominant source-path combinations for cabin noise flyover conditions using the multiple sideline technique based on in light, twin-engine aircraft is propeller noise being transmitted static measurements. Good agreement was obtained with 747 flyover through the fuselage sidewall. This source-path was investigated and results in terms of absolute levels and static-to-flight effects where jet candidate sidewall add-on treatment were installed and tested using noise is dominant. The agreement is seen as a validation of this both an external sound source and the propeller in a ground static simulation technique for the in-flight jet noise of high bypass ratio runup. Results indicate that adding either mass or stiffness to the jets. . ' (Author) fuselage skin would improve sidewall attenuation and that the honeycomb stiffness treatment used generally provided more im- A80-35981 # Prediction of flyover noise from single and provement than an equal amount of added mass. It is proposed that soannular jets. A. Michalke (Berlin, Technische Universitat, Berlin, double-wall Construction in conjunction with skin stiffening should West Germany) and U. Michel. American Institute of Aeronautics provide a good weight efficient combination for the aircraft studied. and Astronautics, Aeroacoustics Conference, 6th, Hartford, Conn., (Author) June 4-6, 1980, Paper 80-1031. 9 p. 24 refs. A recently derived scaling law for predicting flyover jet noise A80-35991 Static tests at model scale indicating rear- from static experiments is presented and extended to the prediction fuselage installation effects on engine exhaust noise. R. C. K. Stevens of the noise from coannular jets in flight The main differences from (National Gas Turbine Establishment, Farnborough, Hants., En- existing theories are the avoidance of a special turbulence model, the gland). American Institute of Aeronautics and Astronautics, Aero- inclusion of the density terms of the source function and the acoustics Conference, 6th, Hartford, Conn., June 4-6, 1980, Paper consideration of a stretching of both the axial source and coherence 80-1046. 11 p. 11 refs. length scales in flight The flyover case at a specific jet and flight To investigate the increases in exhaust noise brought about by velocity proves to be related to that of a static jet The corresponding the rear-fuselage engine installation in an HS125 aircraft, tests have static velocity depends on the emission angle and is lower in the rear been conducted on a 1/9-scale model using a heated single-stream jet arc and higher in the forward arc. The resulting equations are derived to simulate the engine exhaust flow and also a loudspeaker to for low flight Mach numbers and for emission angles not too close to generate internal noise simulating, to a limited extent, the engine the jet axis. The influence of the boundary layer about the outside of core noise. Increases in the jet noise are observed particularly at low the nozzle is neglected. The impressive agreement of the prediction frequencies in the forward arc and these effects, attributed to with experimental results suggests that this might be valid for jet tail-plane reflection, are not strongly dependent on the jet velocity. engines mounted in nacelles. (Author) On the other hand, jet convection is shown to play a major role in determining the more complex installation effects observed with A80-35982 # Noise transmission and attenuation by stiff- internally-generated noise. (Author) ened panels. R. Vaicaitis, M. Slazak (Columbia University, New York, N.Y.), and M. T. Chang. American Institute of Aeronautics A80.35992 ft Model tests demonstrating under-wing installa- and Astronautics, Aeroacoustics Conference, 6th, Hartford, Conn., tion effects on engine exhaust noise. D. J. Way and B. A. Turner June 4-6, 1980, Paper 80. 1034. 12 p. 27 refs. Grant No. NsG-1450. (National Gas Turbine Establishment, Farnborough, Hants., En- An analytical study of noise transmission into semi-cylindrical gland). American Institute of Aeronautics and Astronautics, Aero- and rectangular acoustic enclosures due to turbulent boundary layer acoustics Conference, 6th, Hartford, Conn., June 46, 1980, Paper pressure and propeller noise (prop-fan) is presented. The structural 80-1048. 15 p. 23 refs. noise transmission models include a single panel, discretely stiffened To investigate the increases in exhaust noise brought about by elastic panel and stiffened viscoelastic sandwich panel. Response installing a turbo-fan engine under an aircraft wing, a short characteristics of the stiffened panels are evaluated using a transfer programme of experimental work has been conducted using a matrix procedure. The interior noise field is determined by a one-tenth scale co-axial nozzle positioned adjacent to a model wing. Galerkin-like method. The effect on interior noise due to aerodynam- Although designed to represent the Tristar aircraft, results relevant to ic surface flow, cavity back-up pressure, pressurization, mass, other similar aircraft designs have been obtained by repositioning the stiffness, and damping addition to the structure is investigated. It is Jet exhaust relative to the wing. Increases in the jet noise at both shown that stiffened viscoelastic sandwich panels, while providing engine approach and take-off conditions are observed in the flyover the same stiffening benefits as an equivalent elastic panel, could plane and are attributed to wing reflection and jet-wing and let-flap significantly reduce vibration levels and subsequently give similar interactions. Tentative correlations of these effects have been made benefits for interior noise control. (Author) and the application of this work to project prediction is discussed. (Author) A80-35983 # Propeller signatures and their use. J. F. John- ston, R. E. Donham, and W. A. Guinn (Lockheed-California Co., A80-35996 II Prediction of noise constrained optimum take-- Burbank, Calif.). American Institute of Aeronautics and Astronau- off procedures, S. L. Padula (NASA, Langley Research Center, tics, Aeroacoustics Conference, 6th, Hartford, Conn., June 4-6, Hampton, Va.). American Institute of Aeronautics and Astronautics, 1980, Paper 80-1035. 9 P. Aeroacoustics Conference, 6th, Hartford, Conn., June 4-6, 1980, The identification and use of the noise and vibration signatures Paper 80-1055. 12 p. 10 refs. of individual propellers, described herein, has provided a basis for An optimization method is used to predict safe, maximum- rational advances in propeller-noise analysis and control. These performance takeoff procedures which satisfy noise constraints at

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multiple observer locations. The takeoff flight is represented by airframe noise at approach can be accurately evaluated from the sum two-degree-of-freedom dynamical equations with aircraft angle-of- of the component noise levels and that, when corrected to attack and engine power setting as control functions. The engine certification conditions, this corresponds to a value of about 6 EPN thrust mass flow and noise source parameters are assumed to be dB below the certificated level for the aircraft. (Author) given functions of the engine power setting and aircraft Mach number. Effective Perceived Noise Levels at the observers are treated A80-36001 # Acoustic characteristics of the external upper as functionals of the control functions. The method is demonstrated surface blowing propulsive-lift configuration. M. Maita and T. by applying is to an Advanced Supersonic Transport aircraft design. Torisaki (National Aerospace Laboratory, Tokyo, Japan). American The results indicate that automated takeoff procedures (continu- Institute of Aeronautics and Astronautics, Aeroacoustics Conference, ously varying controls) can be used to significantly reduce commun- 6th, Hartford, Conn., June 46, 1980, Paper 80-1063. 10 p. 19 refs, ity and certification noise without jeopardizing safety or degrading Acoustic characteristics of the external upper surface blowing performance. (Author) (USB) concept of propulsive-lift configuration were studied by full-scale model static experiment. Test components include FJR710 A80-35997 // Current problems and the future in advanced Turbo fan engine with acoustically treated nacelle and USB wing/flap supersonic transport noise. J. V. O'Keefe, R. A. Mangiarotty, and N. assembly utilized in conjunction with ground verification testing of Pickup (Boeing Commercial Airplane Co., Seattle, Wash.). American NAL Quiet STOL Research Aircraft's propulsive system. Results Institute of A eronau tics and Astronautics, Aeroacoustics Conference, were compared with the previous 8%-scale cold flow model data. 6th, Hartford, Conn., June 4-6, 1980, Paper 80- 1056. 9 p. 9 refs. Aft-radiated turbofan engine noise shielding effect by wing/flap Noise control technology developed during the past decade may surface was also discussed and some attempts were made to reduce enable the United States to resume development of an advanced USB noise. (Author) supersonic transport (SST) that will give improved levels of noise. Such developments include coannular and nonconcentric nozzles, thermal acoustic shields, and mechanical suppressors to control Jet A80-36002 • II Upper surface blowing noise of the NASA- noise, the primary source of SST noise. Advanced operational Ames quiet short-haul research aircraft. A. J. Bohn (Boeing Commer- procedures during takeoff and landing will reduce SST community cial Airplane Co., Seattle, Wash.) and M. D. Shovlin (NASA, Ames noise. However, because the success of noise suppression devices Research Center, Moffett Field, Calif.). American Institute of cannot be predicted with certainty, more noise-control technology Aeronautics and Astronautics, Aeroacoustics Conference, 6th, Hart- must be developed and flight tested to ensure that SST jet and ford, Conn., June 4-6, 1980, Paper 80- 1064. 8 p. 7 refs. turbomachinery noise can meet community-noise standards of the An experimental study of the propulsive-lift noise of the (Author) future. NASA-Ames quiet short-haul research aircraft (QSRA) is described. Comparisons are made of measured QSRA flyover noise and model A80-35998 # Comparison of aircraft noise-contour predic- propulsive-lift noise data available in references. Developmental tests tion programs. R. L. Chapkis, G. L. Blankenship, and A. H. Marsh of trailing-edge treatments were conducted using sawtooth-shaped (Dytec Engineering, Inc., Long Beach, Calif.). American Institute of and porous USB flap trailing-edge extensions. Small scale parametric Aeronautics and Astronautics, Aeroacoustics Conference, 6th, Hart- tests were conducted to determine noise reduction/design relation- ford, Conn., June 4-6, 1980, Paper 80- 1057. 10 p. 17 refs. Research ships. Full-scale static tests were conducted with the OSRA sponsored by the U.S. Environmental Protection Agency. preparatory to the selection of edge treatment designs for flight A comparison was made of the FAA Integrated Noise Model testing. OSRA flight and published model propulsive-lift noise data (INM( and the USAF/NOISEMAP computer programs. Those pro- have similar characteristics. Noise reductions of 2 to 3 dB were grams are widely used to predict the location of aircraft noise achieved over a wide range of frequency and directivity angles in contours around airports. Large differences between the programs static tests of the QSRA. These noise reductions are expected to be were found in the noise data bases. There were also differences in the achieved or surpassed in flight tests planned by NASA in 1980. flight profile data bases, the ground attenuation factor, and in the (Author) way the change in noise duration is handled for curved flight paths. The two programs were used to calculate single-event noise level A80-36019 New commutated Doppler microwave landing contours for various air-carrier and general aviation jets. The system. F. R. Connor (Cranfield Institute of Technology, Cranfield, programs were also used to calculate contours of cumulative noise Beds., England). Electronics Letters, vol. 16, May 9, 1980, p. exposure level around a hypothetical average major intercontinental 365-366. airport (AVPORT). Large differences in contour areas and shapes A new design for a double sideband commutated Doppler were found, (Author) system for landing aircraft is proposed. It is capable of providing angular information in elevation and azimuth by the measurement of A80-36000 # Airframe self-noise studies on the Lockheed L a Doppler frequency. Furthermore, it offers the possibility of 1011 TriStar aircraft P. Fethney and A. H. Jelly (Royal Aircraft detecting and correcting any multipath error present in the Doppler Establishment, Aerodynamics Dept., Farnborough, Hants., England). signal. (Author) American Institute of Aeronautics and Astronautics, Aeroacoustics Conference, 6th, Hartford, Conn., June 4-6, 1980, Paper 80-1061. 14 36076 Effect of some aircraft loading program modi- p. 21 refs. A80. An experimental investigation into the level of airframe self- fications on the fatigue life of open hole specimens. A. Buch noise generated by the Lockheed L 1011 TriStar is reported. The (Technion - Israel Institute of Technology, Haifa, Israel). Engineering aircraft was flown in several configurations, with its engines set at Fracture Mechanics, vol. 13, no. 2, 1980, p. 237-256. 23 refs. flight idle, over an extensive array of microphones arranged to Flight simulation and program tests were carried out on measure the noise beneath the aircraft and at a number of sideline different 2024-T3 sheet specimens containing a central hole. The positions. Experimental techniques were employed to obviate ground effect of the peak-load frequency on the damage sum and flight reflection effects and increase the statistical accuracy of the data. number was investigated, and gust spectrum tests were compared The level, spectrum, and polar distribution of the noise generated by with those of other authors. In the case of truncation levels Smax = individual airframe components have been deduced from the flight 1.84 sigma(m) and Smax = 1.685 sigma(m) the investigated change measurements and are compared with the corresponding values of the frequency of stress cycles at the highest loading level had a obtained using Fink's prediction method. Moderate agreement has weak effect on the damage sum, while the effect of decrease of the been demonstrated in terms of spectral content and amplitude of the frequency of the lowest stress amplitude sigma(a) = 0.222 sigma(m) noise at certain angles of propagation, but poor agreement with (MiniTWIST instead of TWIST) was considerable in some cases. It respect to source directivity. It has also been shown that the total was found that in some cases rare load peaks may have not only a

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beneficial but also a detrimental effect on the number of simulated New York, American Society of Mechanical Engineers, 1980, p. flights. B.J. 165-176, 11 refs, A laser anomometer system employing an efficient data acquisi- A80-36137 A' Laser-optical blade tip clearance measurement tion technique has been used to make measurements upstream, system. J. P. Barranger (NASA. Lewis Research Center, Cleveland, within, and downstream of the compressor rotor. A fluorescent dye Ohio) and M. J. Ford (United Technologies Corp., Pratt and Whitney technique allowed measurements within endwall boundary layers. Aircraft Group, West Palm Beach, Fla.). In: Measurement methods in Adjustable laser beam orientation minimized shadowed regions and rotating components of turbomachinery; Proceedings of the Joint enabled radial velocity measurements outside of the blade row. The Fluids Engineering Gas Turbine Conference and Products Show, New flow phenomena investigated include flow variations from passage to Orleans, La., March 10-13, 1980. New York, passage, the rotor shock system, three-dimensional flows in the blade American Society of Mechanical Engineers, 1980, p. 127-131. wake, and the development of the outer endwall boundary layer. The need for blade tip clearance instrumentation has been Laser anemometer measurements are compared to a numerical intensified recently by advances in technology of gas turbine engines. solution of the streamfunction equations and to measurements made A new laser-optical measurement system has been developed to with conventional instrumentation. (Author) measure single blade tip clearances and average blade tip clearances between a rotor and its gas path seal in rotating component rigs and A80-36142 A' Unsteady aerodynamic measurement tech- complete engines. The system is applicable to fan, compressor and niques for turbomachinery research. F. 0. Carta and R. L. O'Brien turbine blade tip clearance measurements. The engine mounted (United Technologies Research Center, East Hartford, Conn.). In: probe is particularly suitable for operation in the extreme turbine Measurement methods in rotating components of turbomachinery; environment. The measurement system consists of an optical Proceedings of the Joint Fluids Engineering Gas Turbine Conference subsystem, an electronic subsystem and a computing and graphic and Products Show, New Orleans, La., March 10-13, 1980. terminal. Bench tests and environmental tests were conducted to New York, American Society of Mechanical Engineers, confirm operation at temperatures, pressures, and vibration levels 1980, p. 177-185. 18 refs. typically encountered in an operating gas turbine engine. (Author) The present paper deals with the application of digital data acquisition and FF1 techniques to the reduction of on-rotor data A80-36138 A' A laser-two-focus /L2F/ velocimeter for auto- and the study of rotating stall. Quick-response transducers, used in matic flow vector measurements in the rotating components of connection with digital data acquisition and reduction equipment, turbomachines. R. Schodl (Deutsche Forschungs . und Versuchs- are shown to provide a powerful tool for studying unsteady processes anstalt für Luft- und Raumfahrt, Institut für Antriebstechnik, in compressors, while On-rotor transducers are well suited for Cologne, West Germany). In: Measurement methods in rotating studying the dynamic response of the flow over the rotor blades. To components of turbomachinery; Proceedings of the Joint Fluids obtain the dynamic changes in force on the rotor blade, extensive Engineering Gas Turbine Conference and Products Show, New data averaging and calculations are required. Individual pressure Orleans, La., March 10-13, 1980. New York, readings on the rotor blade must be combined with an appropriate American Society of Mechanical Engineers, 1980, p. 139-147. 11 curve-fitting expression, and an integrating program must be used to refs. obtain instantaneous force values for an entire rotor rotation. Digital Measurement of blade wakes and shock wave systems in blade computers, directly linked to the high-speed data acquisition passages by means of the L2F velocimeter are time consuming; it equipment, are essential for such work. V. P. takes about one hour to obtain 10 to 15 vector measurements. The technique described in the present paper reduces the measuring time A80-36143 A' Unsteady pressure measurements and data by a factor of 10. Mathematical considerations of the L2F signal analysis techniques in axial-flow compressors. W. F. O'Brien, Jr., W. statistics have resulted in a modified computational model and a new T. Cousins (Virginia Polytechnic Institute and State University, measuring procedure. The optics, operational procedures, and elec- Blacksburg, Va.), and M. R. Sexton (Virginia, University, Charlottes- tronics of the advanced flow measurement technique are discussed, ville, Va.). In: Measurement methods in rotating components of and some experimental data are examined. V. P. turbomachinery; Proceedings of the Joint Fluids Engineering Gas Turbine Conference and Products Show, New Orleans, La., March A80-36139 # Optical advances in laser transit anemometry, 10-13, 1980. New York, American Society of A. E. Smart, W. T. Mayo, Jr. (Spectron Development Laboratories, Mechanical Engineers, 1980, p . 195-201. 12 refs. Project SQUID. Inc., Costa Mesa, Calif.), and D. C. Wisler (General Electric Co.. Methods for the collection and interpretation of unsteady Aircraft Engine Group, Cincinnati, Ohio). In: Measurement methods pressure measurements in axial-flow compressors are described. in rotating components of turbomachinery; Proceedings of the Joint Examples discussed include on-rotor data reduction and analysis for Fluids Engineering Gas Turbine Conference and Products Show, New study of distorted inflow response, and rotating stall detection and Orleans, La., March 10-13, 1980. New York, measurement. Signals from high-response transducers were recorded American Society of Mechanical Engineers, 1980, p. 149-156. 16 and digitized. Data analysis techniques include signal averaging, curve refs. fitting and integration for on-rotor pressure profiles, and application The laser transit anemometer system described in the present of FF1 techniques. (Author) paper will measure the velocity, flow angle, and turbulence in rotating machines. A novel design of the image rotator has resulted in a compact backscatter optical system, whose optimal alignment is A80-36144 # System to measure the pressure distribution not affected by rotation of the sensitive direction. Some unique on fan aerofoil surfaces during flutter conditions. J. W. H. Chivers features of the optical system are discussed, and flowfield measure- (Rolls-Royce, Ltd.. Electronics and Instrumentation Research ments within the rotating blade row of a low-speed axial-flow Group, Derby, England). In: Measurement methods in rotating compressor, made with the laser transit anemometer system, are components of turbomachinery; Proceedings of the Joint Fluids examined. V. P. Engineering Gas Turbine Conference and Products Show, New Orleans, La., March 10-13, 1980. New York, American Society of Mechanical Engineers, 1980, p. 203-207. In order to assist in the understanding of high speed flutter, a A80-36141 A' Laser anemometer measurements in a tran- series0 f tests have been conducted on a research fan in which the sonic axial flow compressor rotor. A. J. Strazisar and J. A. Powell blade srface pressures have been measured by means of miniature (NASA, Lewis Research Center, Cleveland, Ohio). In: Measurement silicon diaphragm pressure transducers embedded in selected fan methods in rotating components of turbomachinery; Proceedings of blades. Prior to this investigation a programme of rig tests was the Joint Fluids Engineering Gas Turbine Conference and Products conducted to examine the effects of centrifugal force and vibration Show, New Orleans, La., March 10-13, 1980. on the transducer performance and a transducer mounting technique

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was developed to minimize blade induced stress in the tranducer. 2048-point time-deflection history for each of the three measure- Instantaneous measurements of the tip stagger angles of the pressure ment locations on each blade is described. V. T. instrumented fan blades have enabled a cross correlation to be performed on the blade surface pressure data and the blade tip A80-36152 * # Preliminary measurements of aerodynamic angles. Some typical test results are shown. . (Author) damping of a transonic compressor rotor. E. F. Crawley, J. L. Kerrebrock, and J. Dugundji (MIT, Cambridge, Mass.). In: Measure- A80-36145 # Fluid and structural measurements to advance ment methods in rotating components of turbomachinery; Proceed- gas turbine technology. M. J. Hartmann (NASA, Lewis Research ings of the Joint Fluids Engineering Gas Turbine Conference and Center, Cleveland, Ohio). In: Measurement methods in rotating Products Show, New Orleans, La., March 10-13, 1980. components of turbomachinery; Proceedings of the Joint Fluids New York, American Society of Mechanical Engineers, Engineering Gas Turbine Conference and Products Show, New 1980, p . 263-271. 9 refs. Grant No. NsG-3079. Orleans, La., March 10-13, 1980. New York, The aeroelastic behavior of a transonic compressor rotor American Society of Mechanical Engineers, 1980, p. 209-213. operated in the MIT Blowdown Compressor Facility has been In the present paper, the current status of fluid and structural examined by means of piezoelectric motion sensors at the base of measurements is reviewed, and some potential improvements in gas each of the 23 blades. Excitation has been observed due to rotating turbine machinery, directly associated with she new measuring stall, due to an incipient flutter, and due to the facility startup capability are discussed. Some considerations concerning the impact transient. A method has been found for determining the aerodynam- of the new capability on the methods and approaches that will be ic damping force by modal analysis of the blade motion. Application used in the further development of advanced technology, in general, of this technique to the example of excitation b y rotating stall has and to aeropropulsion gas turbine machinery, in particular, are led to the conclusions that the blade loading decreases in the stall presented. V. P. cell, and that the damping force on the blades in the clean flow is in phase with blade velocity but opposite it in sign, leading to a A80-36146 # Vibration measurements on turbomachine ro- logarithmic decrement of 0.2. This method of force derivation has tor blades with optical probes. H. Roth (Brown, Boveri et Cie., AG, quite general applicability as it requires only blade motion data such Baden, Switzerland). In: Measurement methods in rotating compo- as are routinely acquired with strain gages. It is argued that models nents of turbomachinery; Proceedings of the Joint Fluids Engineer- are needed for aerodynamic damping which focus on she effects of ing Gas Turbine Conference and Products Show, New Orleans, La., near neighbors of a given blade, since flutter often results in large March 10-13, 1980. New York, American Soci- response of isolated blades or small groups of blades. (Author) ety of Mechanical Engineers, 1980, p. 215-224. The paper deals with a novel display device that will record A80. 36153 I Low profile strain gage applications teleme- simultaneously the vibrations of each blade in a row. The device is # tered from rotating machinery. R. D. DeRose (USAF, Aero very similar to the Lewis system for detection of flutter (Nieberding, Propulsion Laboratory, Wright-Patterson AFB, Ohio). In: Measure- Pollack, 1977) but differs from it in that bright dots can be resolved ment methods in rotating components of turbomachinery; Proceed- in time. The introduction of this additional degree of freedom ings of the Joint Fluids Engineering Gas Turbine Conference and extends substantially the versatility of the device. Hard copies of Products Show, New Orleans, La., March 10-13, 1980. several measurement records are presented. The derivation of the New York, American Society of Mechanical Engineers, basic relations is given in an appendix. V. P. 1980, p. 273-277. A strain gage lead out application using materials developed for A80-36 149 # Processing and analysis of the data from a two flexible printed circuitry is described. This application technique is spool gas turbine engine. N. K. Verma, K. Venkasaraju, M. L. Abrol, being tested along with axially mounted telemetry electronics and N. R. Raghuprasad (Gas Turbine Research Establishment, transmitting signals from a high speed compressor test vehicle. The Bangalore, India). In: Measurement methods in rotating components integrated system uses small pins and sockets interconnecting various of turbomachinery; Proceedings of the Joint Fluids Engineering Gas electronic components to facilitate vehicle disassembly. The results Turbine Conference and Products Show, New Orleans, La., March from past tests along with a description of the next configuration to 10-13, 1980. New York, American Society of be tested are also given. The objective of this effort is to obtain a Mechanical Engineers, 1980, p. 241-246. very low profile (0.08mm or less) application which will minimize The paper deals with the measurement and analysis of a number aerodynamic disturbance when it is applied to airfoils operating at of parameters essential for the development of a gas turbine engine. temperatures up to 585K (600 F). (Author) The first part of the paper describes a microprocessor based data processing system which has been developed for acquiring data from A80-36154 # The design, development and operation of gas over 256 parameters. The salient features of this system are high turbine radio telemetry systems. J. G. B. Worthy (Rolls-Royce, Ltd., accuracy of measurement, fast acquisition time and an on-line Aero Div., Derby, England). In: Measurement methods in rotating monitoring of a selected number of parameters on a bright CRT components of surbomachinery; Proceedings of the Joint Fluids display. The data is presented in engineering units after suitable Engineering Gas Turbine Conference and Products Show, New averaging. In the second part of the paper the analysis of the Orleans, La., March 10-13, 1980. New York, transients and time varying signals on a real time spectrum analyzer American Society of Mechanical Engineers, 1980, p. 279-287. 8 refs. has been described. An attempt has been made to obtain a The design and operation of gas turbine radio telemetry systems correlation between the mechanical and aerodynamic behavior of are examined. Measurements on the rotating components of aerogas various components of the engine and the spectrum generated by turbines produce difficult instrumentation problems. This paper them during the engine operation. (Author) describes the Rolls-Royce approach to this problem and the design of over 30 radio telemetry systems manufactured by this company. A80-36151 II Digital system for dynamic turbine engine Constraints on the measuring system, block diagrams of the blade displacement measurements. L. J. Kiraly (NASA, Lewis telemetry system and transducer selection integrated circuit are Research Center, Cleveland, Ohio). In: Measurement methods in discussed, and experience using dynamic and strain tests is analyzed. rotating components of turbomachinery; Proceedings of the Joint Finally, possible problems such as generation of spurious rotational Fluids Engineering Gas Turbine Conference and Products Show, New frequency signals due to poor antenna design and the proximity of Orleans, La., March 10-13, 1980. New York, stator metal work are considered. A.T. American Society of Mechanical Engineers, 1980, p. 255-262. The paper presents a technique for measuring blade tip A80-36155 * # Impact of new instrumentation on advanced displacements which employs optical probes and an array of turbine research. R. W. Graham (NASA, Lewis Research Center, microcomputers. A system directly digitizing a minimum of a Cleveland, Ohio). In: Measurement methods in rotating components

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of turbomachinery; Proceedings of the Joint Fluids Engineering Gas Turbine Conference and Products Show, New Orleans, La., March 10-13, 1980. New York, American Society of Mechanical Engineers, 1980, p. 289-302. 23 refs. The progression of experimental programs is discussed from the simplest two-dimensional stationary geometry to the highly complex three-dimensional flow in a rotating blade row. Experimental methods and instrumentation techniques are described. Emphasis is placed on rotating blade row measurements. V. T.

A80-36156 Qualification of cooling systems design for high temperature on a turbine facility. A. E. Cournut, M. Laroche )SNECMA, Moissy-Cramayel, Seine-et-Marne, France), Y. Le Bot, and P. J. Michard (ONERA, Chatillon.sous-Bagneux, Hauts.de-Seine, France). In: Measurement methods in rotating components of turbomachinery; Proceedings of the Joint Fluids Engineering Gas Turbine Conference and Products Show, New Orleans, La., March 10-13, 1980. New York, American Society of Mechanical Engineers, 1980, p.303-317. 23 refs. (ONERA, TP no. 1980-15) An advanced turbine test facility for predicting temperature distribution on airfoils and adjacent components is described. The turbine design program including static test rigs, engine tests, and measuring techniques are examined; aerodynamic properties of steam are characterized, including temperature distortion and aerodynamic turbulence, and measurement of heat exchange on blades and vanes. Finally, thermal characteristics of rotor blades and its application to the investigation of film-cooled blade thermal balance are considered. A. T.

A80-36157 # Temperature and pressure measurement techniques for an advanced turbine test facility. F. G. Pollack and R. P. Cochran (NASA, Lewis Research Center, Cleveland, Ohio). In: Measurement methods in rotatingi components of turbornachinery; Proceedings of the Joint Fluids 1Engineering Gas Turbine Conference and Products Show, New Orleans, La., March 10-13, 1980. New York, American Society of Mechanical Engineers, 1980, p. 319. 326. 13 refs. A high pressure. high-temperature turbine test facility is being constructed at the NASA Lewis Research Center for use in turbine cooling research. Several recently developed temperature and pressure measuring techniques will be used in this facility. This paper describes these measurement techniques, their status, previous applications and some results. Noncontact surface temperature measurements will be made by optical methods. Radiation pyrom- etry principles combined with photoelectric scanning will be used for rotating components and infrared photography for stationary components. Contact (direct) temperature and pressure measurements on rotating components will be handled with an 80-channel rotary data package which mounts on and rotates with the turbine shaft at speeds up to 17,500 rpm. The data channels are time-division multiplexed and converted to digital words in the data package. A rotary transformer couples power and digital data to and from the shaft. (Author)

A80-36291 • Air deployment of satellite-tracked drifters. R. E. Cheney (NASA, Goddard Space Flight Center, Greenbelt, Md.), P. L. Richardson (Woods Hole Oceanographic Institution, Woods Hole, Mass.), and B. P. Blumenthal (U.S. Navy, Naval Oceanographic Office, Bay St. Louis, Mo.). Journal of Geophysical Research, vol. 85, May 20, 1980, p . 2773-2778. 7 refs. Contract No. N00014-74-C-0262. NR Project 083-004. Six free-drifting buoys tracked by the Nimbus 6 satellite were successfully launched by C-130 aircraft in a series of deployments during 1977-1979. The buoys were launched in Gulf Stream rings which had been identified with airborne XBT surveys and satellite infrared images. This is the first operational test of these air- deployable buoys. (Author)

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emissions appear to be the result of acoustic energy radiation which has been converted by the trailing-edge noise mechanism from the dynamic fluid energy of independent streamwise 'strips' of the turbulent boundary layer flow. A.R.H.

N8022265*# National Aeronautics and Space Administration. STAR ENTRIES Langley Research Center, Langley Station, Va. THEORETICAL PREDICTION OF NONLINEAR PROPAGA- TION EFFECTS ON NOISE SIGNATURES GENERATED BY SUBSONIC OR SUPERSONIC PROPELLER OR ROTOR- BLADE TIPS Sikorsky Aircraft, Stratford, Conn. N80-22257# Raymond L. Barger May 1980 18 p refs ANALYSIS OF HELICOPTER MAINTENANCE FAULT (NASA-TP-1660: L-13388( Avail: NTIS HC A02/MF AOl ISOLATION CRITERIA/TECHNIQUES Final Report, Oct. CSCL O1A 1977 - Apr. 1979 The nonlinear propagation equations for sound generated by Thomas N. Cook Oct. 1979 173 p refs a constant speed blade tip are presented. Propagation from a (Contract DAAJ02-77-C-0071: DA Proj. 11-2-62209-AH-76( subsonic tip is treated as well as the various cases that can (AD-A080596: SER-5 10022: USARTL-TR-79-2 1) Avail: NTIS occur at supersonic speeds. Some computed examples indicate HC A08/MF AOl CSCL 01/3 that the nonlinear theory correlates with experimental results The problems associated with fault isolation maintenance in better than linear theory for large amplitude waves. For swept Army aviation were investigated. The investigation included a tips that generate a wave with large amplitude leading expansion, detailed engineering analysis of historical maintenance data on the nonlinear theory predicts a cancellation effect that results in the CH-54 helicopter and surveys of selected Army field a significant reduction of both amplitude and impulse. Author activities throughout the United States. The investigation confirmed that fault isolation maintenance is a significant factor in the cost of operating Army helicopters. The most frequent N8022266*# National Aeronautics and Space Administration. criticism voiced by Army personnel in the field concerns the Langley Research Center, Langley Station, Va. generally poor quality of troubleshooting data in current aircraft FULL-SCALE WIND TUNNEL-INVESTIGATION OF THE maintenance publications. In response to this problem, an ADVANCED TECHNOLOGY LIGHT TWIN-ENGINE AIR- improved approach to the development of fault isolation PLANE (ATLIT) maintenance data for complex systems was developed. Called James L. Hassell, Jr., William A. Newsom. Jr. and Long P. Yip FIAT (Fault Isolation Analysis Technique(, the proposed approach May 1980 212 p refs greatly facilitates the identification of symptom/cause relationships (NASA-TP-1591; L-13135( Avail: NTIS HC A10/MF AOl and the collection, processing and organization of data required CSCL O1A for the preparation of maintenance manuals. GRA An investigation was conducted to evaluate the aerodynamic performance, stability, and control characteristics of the Advanced N8022260*# National Aeronautics and Space Administration, Technology Light Twin Engine airplane (ATLIT(. Data were Washington. D. C. measured over an angle of attack range from -4 deg to 20 deg TRANSONIC WING DFVLR-F4 AS EUROPEAN TEST for various angles of sideslip between -5 deg and 15 deg at MODEL Reynolds numbers of 0.0000023 and 0.0000035 for various G. Redeker and Norbert Schmidt Jan. 1980 12 p Transl. settings of power and flap deflection. Measurements were also into ENGLISH from Nachrichten-Tech. Z. (West Germany(. Jun. made by means of special thrust torque balances to determine 1979 p 36-39 Original language document announced as the installed propeller characteristics. Part of the investigation A79-41234 Transl. by Kanner (Leo( Associates. Redwood City, was devoted to drag cleanup of the basic airplane and to the Calif. Original doc. prep. by DFVLR. Brunswick evaluation of the effect of winglets on drag and stability. E.D.K. (Contract NASw-3199( (NASA-TM-75752( Avail. NTIS HC A02/MF AOl CSCL N80-22267# Northrop Corp.. Hawthorne, Calif. Aircraft O1A Group. A transonic wing, the DFVLR-F4 was designed and tested TRANSONIC KERNEL FUNCTION METHOD FOR UN- as a model in European transonic wind tunnels and was found STEADY FLOW CALCULATIONS USING A UNIFIED LINEAR to give performance improvements over conventional wings. One PRESSURE PANEL PROCEDURE Final Report, 1 Mar, reason for the improvement was the reduction of compression 1978 - 30 May 1979 shocks in the transonic region as the result of improved wing D. D. Liu. W. S. Di, and M. T. Landahi Wright-Patterson AFB, design. E.D.K. Ohio AFFDL Oct. 1979 107 p refs (Contract F33615-78-C-3202) N8022264*# North Carolina State Univ. at Raleigh. Center (AD-A080227; NOR-79-52: AFFDL-TR-79-3085) Avail: NTIS for Acoustical Studies. HC A06/MF AOl CSCL 20/4 EXPERIMENTAL STUDY OF AIRFOIL TRAILING EDGE A transonic kernel function method for unsteady flow NOISE: INSTRUMENTATION, METHODOLOGY AND calculations was developed. A unified linear presssure panel INITIAL RESULTS M.S. Thesis procedure is established to solve for two-dimensional problems Mark B. Manley 1980 199 p refs in the subsonic, transonic, and supersonic flow regimes: (Grant NsG-1377( consequently, a TLP2D computer code was developed. Numerical (NASA-CR-163007( Avail: NTIS HC A09/MF AOl CSCL results are presented for pitching or flapping airfoils in' these O1A linear and nonlinear flow regimes. The mixed kernel function The mechanisms of aerodynamic noise generation at the procedure is applied to a pitching Guderley airfoil in sonic flow. trailing edge of an airfoil is investigated. Instrumentation was Comparisons with other results and discussions are given. designed, a miniature semiconductor strain-gauge pressure Additional analytical studies include Landahl's general formulation transducer and associated electronic amplifier circuitry were of the phase correction method and the kernel function formulation designed and tested and digital signal analysis techniques of the Eckhaus-Landahl shock-jump model. Finally, assessments applied to gain insight into the relationship between the dynamic of and recommendations for the present work are given. GRA pressure close to the trailing edge and the sound in the acoustic far-field. Attempts are made to verify some trailing-edge noise N80-22268# Air Force Inst. of Tech.. Wright-Patterson AFB, generation characteristics as theoretically predicted by several Ohio. School of Engineering. contemporary acousticians. It is found that the noise detected EVALUATION OF AN IMPROVED PARACHUTE TEST DATA in the far-field is comprised of the sum of many uncorrelated ACQUISITION SYSTEM M.S. Thesis emissions radiating from the vicinity of the trailing edge. These Gary Alan Richardson Dec. 1979 109 p refs

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)AD-A080240; AFIT/GCS/EE/79- 13) Avail: NTIS BOELSMA experiment. The comparisons show an improvement - HC A06/MF AOl CSCL 14/3 of the prediction over the isotropic calculations. Author (ESA) This project confirms the feasibility of a sixteen channel, self-contained data acquisition system that would be suitable to N80-22274# Office National d'Etudes et de Recherches store data obtained during a parachute perfurmance evaluation Aerospatiales. Paris (France). drop. The overall system is discussed in modular fashion to ACTIVITIES IN AEROSPACE RESEARCH Annual Report, allow generalization to other portable data acquisition systems 1978 that must accept data at high rates but over relatively short 1979 208 p refs Original contains color illustrations time intervals. The storage medium for the proposed system Avail: NTIS HC A10/ME AOl utilizes magnetic bubble memory devices. GRA Aerodynamics, wind tunnel testing, structures, propulsion, physics, and materials science are among the topics discussed. N80-22269# Avco Corp.. Wilmington, Mass. Applications of aerospace research in industry are covered. Patents PROJECTILE/ SABOT DISCARD AERODYNAMICS Final and publications issued during the year are listed. Author (ESA) Report David Siegelnian and Peter Crimi Aberdeen Proving Ground, Md. BRL Dec. 1979 92 p refs N80-22275# Dornier-Werke G.m.b.H., Friedrichshafen )West )Contract DAAK1 1-77-C-0080) Germany). (AD-A080538. AD-E430367; ARBRL-CR-004 10) Avail: NTIS SUPERCRITICAL WING DESIGN STUDIES FOR TRANS- HC A05/MF AOl CSCL 19/1 PORT AIRCRAFT. VOLUME 1: WING DESIGN AND WIND An engineering analysis procedure which describes the sabot TUNNEL MEASUREMENTS Final Report discard process for gun-launched projectiles has been modified Guenter Binder, Hartmut Buers, and Hans-Joerg Proksch Bonn in order to provide an improved tool for investigating the effects Bundesmin. fuer Forsch. u Technol. Jul. 1979 94 p refs In of sabot, projectile and launch parameters upon near field GERMAN: ENGLISH summary Sponsored by Bundesmin. fuer dispersive forces. Experimental test data generated by BRL has Forsch. u. Technol. 2 Vol. been used to formulate an improved engineering model of the )BMFT-FB-W-79-06-Vol-1) Avail: NTIS HC A05/MF AOl Interaction flow field which develops about the projectile/ sabot The design work and wind tunnel measurements for a petal package during the removal process. The experimental data supercritical wing for a transport aircraft to supplement the airbus indicated that individual compression wave intersections and A 300 are described. Author )ESA) reflections are present within the annular flow passage. In order to model this behavior, an integrated flow element approach N80-22276# Dornier-Werke G.m.b.H., Friedrichshafen )West utilizing local shock/expansion procedures has been evolved Germany). Theoretical Aerodynamics. G RA SUPERCRITICAL WING DESIGN STUDIES FOR TRANS- PORT AIRCRAFT. VOLUME 2: THEORETICAL STUDIES Final Report N80-22272# European Space Agency, Paris )France). Willy Fritz, Stefan Leicher, Wolfgang Schmidt, and Hans-Werner CALCULATION OF THE INTERFERENCE EFFECTS BE- Stock Bonn Bundesmin. fuer Forsch. u. Technol. Jul. 1979 TWEEN THE ENGINE WING AND THE BASE WING OF A 148 p refs In GERMAN; ENGLISH summary Sponsored by CIVIL AND MILITARY TRANSPORT AIRCRAFT BY THE Bundesmin. fuer Forsch. u. Technol. 2 Vol. VORTEX LATTICE METHOD )BMFT-FB-W-79-07-Vol-2) Avail: NTIS HC A07/MF AOl W. Schroeder Dec. 1978 101 p refs Transi. into ENGLISH The improvement of currently existing computer methods of "Berechnung der lnterferenzwirkung Zwischen Triebwerks- und for the design of supersonic transport aircraft was studied. This Basisfluegel am Zivil-M ilitaerischen Transporter nach dem was achieved by modifying both equation and boundary conditions. Wirbelleiterverfahren". Rept. D LR-lB- 151-77/19 DFVLR and Wind tunnel wall effects were included as was viscous drag. VFW-Fokker G.m.b.H., Bremen, Dec. 1977 Original report in The detailed comparisons document the present status of the GERMAN previously announced as X79-71705 different methods. Author )ESA) )ESA-TT-493; OLR-lB-1 51-77/19) Avail: NTIS HC A06/MF AOl For incompressible symmetric flow, calculations of the N80-22278# Engineering Sciences Data Unit. London (England). interference between engine and basis wing of the VFW-Fokker A COMPARISON OF VARIOUS NUMERICAL METHODS 614 civil-military transport aircraft model were performed. The FOR CALCULATING SUPERCRITICAL INVISCID ISEN- following parameters were used: angle of attack 0. 3. and 5 deg TROPIC FLOW OVER TWO-DIMENSIONAL AEROFOILS for three different engine wings each with -10%. 10%. 30% or R. H. Blockley Orpington. England Defense Rex. Inform. Centre 50% overlap between engine and basic wing. The results of the 1979 150 p refs linear and nonlinear calculations are discussed. Author )ESA) (Contract K/A72c/259/CB/A72c) )S/T-Memo-4/75; BR47382) Avail: NTIS HC A07/MF AOl Numerical solutions of full potential flow equations are N80-22273# European Space Agency. Paris (France). mutually compared with particular reference to the method of CALCULATION OF THE TURBULENT BOUNDARY LAYER Garabedian and Korn. Comparisons of pressure distributions and ON AN INFINITE SWEPT WING USING A THREE- aerodynamic force and moment coefficients for a small range of DIMENSIONAL MIXING LENGTH MODEL airfoils at Mach numbers for near-critical or supercritical flow are presented. Procedures for using the Garabedian and Korn Gert Reinhard Schneider Jul. 1979 70 p refs Transl. into ENGLISH of "Die Berechnung der Turbulenten Grenzscfticht am program are recommended. An approximate method (transonic Schiebenden Fluegel Unendlicher Spannweite Mittels eines small perturbation method based on Krupp and Murman) is Dreidimensionalen Mischungswegmodells", Rept. D LR-FB-77-73 similarly compared with that of Garabedian and Korn. The airfoils DFVLR. Goettingen. West Germany. May 1978 Original report studied are described. Author )ESA) in GERMAN previously announced as X79-72041 (ESA-TT-534. DLR-FB-77-73) Avail NTIS HC A04/MF AOl. N80-22280# Royal Aircraft Establishment, Farnborough DFVLR, Cologne OM 28,60 (England). Experimental observations of three-dimensional turbulent A COMMENT ON THE ORIGIN OF ENDWALL INTERFER- boundary layers show that the direction of the shear stress is in ENCE IN WIND TUNNEL TESTS OF AEROFOILS general not parallel to the direction of the mean velocity gradient. K. G. Winter and J. H. B. Smith London HMSO 20 Aug. Following this observation for the Reynolds shear stresses, a 1979 20 p refs generalized mixing length model is developed based on a (RAE-TM-Aero-1 816; BR701 72) Avail: NTIS non-isotropically distributed eddy viscosity. The isotropic mixing HC A02/MF AOl length model currently used for three-dimensional flows is included The interference effects of an airfoil spanning the working as a special case. Calculations are carried out for the infinite section of a wind tunnel due to the presence of boundary layers swept wing situation of the VAN DEN BERG, ELSENAR and on the walls are discussed. Tests reveal behavior different from

346 N80-22305 that predicted by theory. A qualitative assessment of the problem STRAPPED DOWN INERTIAL SENSORS FOR NAVIGATION is made and it is suggested that the interference be explained AND FLIGHT CONTROL Ph.D. Thesis in terms of changes in the displacement thickness of the boundary Jackie Wayne Bell 1979 213 p layers on the tunnel walls rather than in terms of induced effects Avail: Univ. Microfilms Order No. 8008430 from trailing vorticity. Author (ESA) The capability of various algorithms for improved estimation of the sensor true outputs from a strapped down inertial reference assembly is examined. A secondary factor is the optimum N80-22281 Royal Aircraft Establishment. Farnborough combination of the estimated outputs from a set of redundant (England). inertial sensors to form an orthogonal triad inertial reference. AERODYNAMIC CHARACTERISTICS OF MOVING TRAIL- The algorithms are based upon various levels of sensor model- ING-EDGE CONTROLS AT SUBSONIC AND TRANSONIC ing in Kalman or fixed-gain optimal filters. The algorithms range SPEEDS from a second-order to a fourth-order filter for each sensor. The D. G. Mabey. D. M. McOwat. and B. L. Welsh London HMSO redundant sensor estimated outputs are combined through a 25 Jun. 1979 27 p refs Presented at AGARO Fluid Dyn. weighted least squares estimator which provides a statistical Panel Meeting on the Aerodyn. Characteristics of Controls. May average of the estimated sensor outputs transformed into body 1979 coordinates. Dissert. Abstr. (RAE-TM-Struc-947; BR69932) Avail: NTIS HG A03/MF AOl Oscillatory pressures calculated and measured at high N80-222975# National Aeronautics and Space Administration. subsonic speeds for a swept back wing of aspect ratio 6 with a Ames Research Center, Moffett Field, Calif. part span trailing-edge flap are compared. The flap was driven A NEW ALGORITHM FOR HORIZONTAL CAPTURE at frequencies of 1 Hz (quasi-steady) and 90 Hz at Mach numbers TRAJECTORIES from 040 to 0.95 with both fixed and free transition over a John D. McLean Mar. 1980 21 p refs range of Reynolds numbers from one to four million. The measured (NASA-TM-81186, A-8111) Avail: NTIS HG A02/MF AOl oscillatory pressures which depend strongly on the boundary layer GSGL 17G displacement thickness at the hinge line, are presented. Tests An algorithm which transfers an aircraft from an initial position with the flaps driven simultaneously at two frequencies (90 Hz and heading to a final position and heading was developed for and 131 Hz) at subsonic and transonic speeds are discussed. onboard synthesis of horizontal flight paths. The algorithm finds Author (ESA) all solutions possible, and selects the one with minimum path length. Degenerate conditions in which one or more of the basic N80-22282# Aeronautical Research Inst. of Sweden. Stockholm. segments is missing are handled without difficulty. The solution Aerodynamics Dept. to this problem is derived, and a FORTRAN listing of the algorithm MEASUREMENT OF LOCAL SKIN FRICTION AND STATIC is provided. E.D.K. PRESSURE ON A SWEPT WING IN FLIGHT Final Report A. Bertelrud Jul. 1979 77 p refs Prepared in cooperation with Swedish Air Force. Stockholm N80-22303# National Aerospace Lab.. Amsterdam (Netherlands). (Contracts FMV-F-K-82223-76-001 -21-001: Flight Div. FM V- F-K-82223-77-OO1 -21-001: COMPARISON OF THE MINILIR LOCATION SYSTEM AND FMV-F-K-82223-77-1 16-21-001: THE NLR INERTIA MEASURING SYSTEM STALINS FMV-F-K-82223-78-003-2 1-001) A. J. L. Willekens 28 Jun. 1978 17 p )FFA-AU-1370) Avail: NTIS HG A05/MF AOl (NLR-MP-78026-U) Avail: NTIS HG A02/MF AOl A series of flight tests have been performed to explore the Aircraft trajectories were determined using the optical location possibility of using multiple total head/static probes (modified system )MINILIR) and the inertial measuring system (STALINS). Preston tubes) for the measurement of local skin friction and The optical tracking was controlled with a movie camera mounted static pressure distribution in flight. The aircraft used in the on the MINILIR tracker. A known position in flight was obtained experiment was a SAAB 32 A Lansen. which is a swept wing with a high precision fan marker system RASP. The accuracy of attack fighter. It is shown that the results obtained are reproducible the position and velocity data obtained using both systems is and agree reasonably well with computations. Thin films discussed. Author (ESA) (McGroskey gauges) mounted on the leading edge showed no deviations in resistance after 19 flights. This indicates that the N8022304*# National Aeronautics and Space Administration. gauges can be used for qualitative, and probably also quantita- Langley Research Center, Langley Station. Va. tive measurements in flight. Author )ESA) PRELIMINARY INVESTIGATION OF MOTION REQUIRE- MENTS FOR THE SIMULATION OF HELICOPTER HOVER Army Safety Center. Fort Rucker. Ala. TASKS N80-22294# Russell V. Parrish Apr. 1980 31 p refs SURVEY OF FORCED AND PRECAUTIONARY LANDING )NASA-TM-81801) Avail: NTIS HG A03/MF AOl GSGL COSTS 01C Emil Spezia. G. D. Kimel, and Thomas Neese Jul. 1979 24 p Data from a preliminary experiment are presented which (AD-A0801 10: USASG-TR-79-4) Avail: NTIS attempted to define a helicopter hover task that would allow HG A02/MF AOl CSGL 01/2 the detection of objectively - measured differences in fixed A questionnaire survey was conducted to learn the costs of base/moving base simulator performance. The addition of forced landings (F/La) and precautionary landings )P/Ls). The heave, pitch, and roll movement of a ship at sea to the hover questionnaire elicited cost data in respect to (1) the effect each task, by means of an adaption of a simulator g-seat, potentially mishap had on the mission assigned the mishap aircraft: fulfills the desired definition. The feasibility of g-seat substitution (2) man-hours lost by the crew and passengers; (3) man-hours for platform motion can be investigated utilizing this task.Author required to recover the crew, passengers, and aircraft; (4) time the mishap aircraft was unavailable for flight; (5) man-hours required to make the aircraft flyable; and (6) the components N80,22305*# Science Applications, Inc.. Los Angeles. Calif. that malfunctioned to cause these mishaps. The broad and obscure Economic Analysis Div. costs revealed by the survey are sufficient to justify the initiation PARAMETRIC STUDY OF HELICOPTER AIRCRAFT of a concerted effort to prevent the causes of these mishaps. SYSTEMS COSTS AND WEIGHTS Prevention of the causes of these mishaps will allow aviation Michael N. Beltramo Jan. 1980 179 p refs Units to operate more efficiently, i.e.. allow them to maintain a (Contract NAS2-8703) higher state of combat readiness. GRA (NASA-GR-152315( Avail: NTIS HG A09/MF AOl CSGL O1G Weight estimating relationships )WERs) and recurring N80-22295 Dayton Univ., Ohio. production cost estimating relationships )GERs( were developed OPTIMAL ESTIMATION APPLIED TO REDUNDANT for helicopters at the system level. The WER5 estimate system

347 N80-22306

level weight based on performance or design characteristics which The Maneuver Criteria Evaluation Program )MCEP) is a digital are available during concept formulation or the preliminary design computer program that solves the flight path equation of motion phase. The CER (or CERs in some cases) for each system utilize for a helicopter without auxiliary propulsion. The use of basic weight (either actual or estimated using the appropriate WER) work, energy, and power relationships makes possible accurate and production quantity as the key parameters. R.E.S. representation of flight path trajectories. MCEP can be used to aid in the development of maneuver requirements that provide N8022306*# National Aeronautics and Space Administration, the necessary maneuver capability to perform the desired mission. Washington, D. C. The desired mission is simulated in MCEP by using individual AERODYNAMICS OF THE NEW GENERATION OF COMBAT flight controllers to 'fly' the helicopter through the mission profile. AIRCRAFT WITH DELTA WINGS Key maneuver parameters are monitored throughout the flight M. P. Bohn Mar. 1980 26 p Transl. into ENGLISH of profile to provide insight into the performance of the helicopter "Aerodynamique de la Nouvelle Generation d'Avions de Combat in achieving the desired flight trajectory. Three maneuvers have a Aile Delta", Rept. AGARD-CP-241 AGARD, Paris, Jun. 1978 been modified to allow rotor rpm to be bled to use some of p 11 . 1-11-13 Presented at the Multi-Panel Symp. on Fighter the rotor's stored energy. These maneuvers are a constant altitude Aircraft Design, Florence, 3-6 Oct. 1977 Translation was acceleration maneuver, a collective pop-up maneuver, and a announced as N78-30106 Transl. by Scientific Translation sideward acceleration maneuver. Correlation with flight test data Service, Santa Barbara. Calif. is established to validate the bleed rpm maneuvers. The appendix (Contract NASw-3 198) to the report, the User's Guide, contains the detailed information (NASA-TM-75793; AGARD-CP-241) Avail: NTIS necessary for setting up an input data deck for MCEP. GRA HC A03/MF AOl CSCL 01C The use of delta wing aerodynamic design for modern fighter N80-22311# Textron Bell Helicopter, Fort Worth. Tex. aircraft is discussed. Various current French fighter airplanes are AH-1S HIGH-SURVIVABLE TRANSMISSION SYSTEM Final utilized for comparisons. E.D.K. Report, Oct. 1977 - Dec. 1978 Gary A. Cope Oct. 1979 89 p ref N80-22308# Naval Air Development Center, Warminster, Pa. (Contract DAAJ02-76-C-0006; DA Proj. 1F2.63208-DB-52( Aircraft and Crew Systems Technology Directorate. )AD-A080568; USAAVRADCOM-TR-79-43) Avail: NTIS STATISTICAL REVIEW OF COUNTING ACCELEROMETER HC A05/MF AOl CSCL 01/3 DATA FOR NAVY AND MARINE FLEET AIRCRAFT The objective of the work performed on this program was Semiannual Summary Report, 1 Jan. 1962 - 30 Jun. 1979 to demonstrate that the AH-1S main transmission system, Warren J. Williams 1 Nov. 1979 159 p refs Revised modified with internal component improvements but without an )AD-A080580; NADC- 13920-2) Avail: NTIS emergency lubrication system, could operate for 30 minutes HC A08/MF AOl CSCL 01/3 following the loss of lubrication. The internal component This report is a specialized summary of normal acceleration improvements were based upon work done under this program data recorded by counting accelerometers. Data are separated and work done under a previous Eustis Directorate contract, by calendar time and mission category. Only data reported in both conducted by Bell Helicopter Textron. Six different modified the counting accelerometer program are included. This is a versions of the AH-1S transmission configuration were tested semi-annual progress report, and it presents a specialized summary under this program. Four of the six transmission configurations of the data in the counting accelerometer program. Statistics had been run to failure previously and the results reported in describing Navy and Marine aircraft cumulative g-count exceed- USAAMRDL-TR-77-30. The loss-of-lube testing for the final two ances are calculated and tabulated. These tabulations are transmission configurations was conducted at 680 input separated by calendar time and into four major categories of horsepower (60 percent of maximum continuous power rating fleet experience: Navy Training. Navy Combat, Marine Training. of the A H-i S) and 6600 input rpm. The first transmission and Marine Combat. These data show that the load rate configuration tested ran 25 minutes under loss-of-lube conditions distributions (counts at 1000 hours) for most models and most before failure of the lower planetary stage. The second transmis- g-levels have a non-normal. distribution. Within a model (F-4N. sion configuration ran 54 minutes before failure of the lower F-8J, etc.) differences in the average load rates exist when data planetary stage. Thus. the 30-minute loss-of-lube capability has are separated by calendar time or mission category. GRA been demonstrated for all transmission components. GRA N80-22309# Aeronautical Research Labs.. Melbourne (Australia). N80-22312// Textron Bell Helicopter, Fort Worth, Tex. GENERATION OF A REPRESENTATIVE LOAD SEQUENCE ROTORCRAFT FLIGHT SIMULATION, COMPUTER PRO- FOR THE FATIGUE TESTING OF MACCHI MB 326H SPAR GRAM C81. VOLUME 1: ENGINEERS MANUAL Final BOOMS Report, Nov. 1976 - Aug. 1977 L. A. Gratzer Jan. 1979 26 p refs James R. VanGaasbeek. T. T. McLarty. and S. G. Sadler Oct. (AD-A074155; ARL/Struc-Note-450) Avail: NTIS 1979 394 p refs Supersedes USAAMRDL-TR-76-41A HC A03/MF AOl CSCL 01/3 3 Vol. Testing techniques have been developed to allow more (Contract DAAJ02-77-C-0003. DA Proj. 1 L2-622O9-AH-76) realistic load sequences. To take advantage of this, the design (AD-A079631; BHT-699-O99-O62-Vol- 1: USARTL-TR-77-54A; of such test sequences must also be improved and for several U5SAMRDL-TR . 76-41A) Avail: NTIS HC A17/MF AOl CSCL years large scale tests at ARL have relied on loads obtained 01/3 from flight histories transformed as little as possible. In this This report consists of three volumes and documents the way the probability structure of flight sequences can be restored. current version in the C81 family of rotorcraft flight simulation Until now however, the design of test histories has been almost programs developed by Bell Helicopter Textron. This current entirely manual. This note describes the generation of histories version of the digital computer program is referred to as AGAJ77. by use of automatic data processing techniques and linear The accompanying program for calculating fully coupled rotor programming. The example used in this note is the Macchi center blade mode shapes is called DNAM05. and the rotor wake section spar boom which is being tested under the design load program is called AR9 102. The first volume, the Engineer's history to supplement earlier data obtained under less realistic Manual, presents an overview of the computer program capabilities load sequences. GRA plus discussions for the background and development of the principal mathematical models in the program. The models N80-22310# Textron Bell Helicopter, Fort Worth, Tex. discussed include all those currently in the program. GRA IMPROVED MANEUVER CRITERIA EVALUATION PRO- GRAM Final report. Sep. 1976 - Jul 1979 N80-22313# Textron Bell Helicopter, Fort Worth, Tex. T. Wood and T. Waak Nov. 1979 79 p refs ROTORCRAFT FLIGHT SIMULATION, COMPUTER PRO- (Contract DAAJ02-76-C-0064; DA Proj. 1 F2-6321 1 -D- 157) GRAM C81. VOLUME 2: USERS MANUAL Final Report, )AD-A080408; USARTL-TR-79-20) Avail: NTIS Nov. 1976 - Aug. 1977 HC A05/MF AOl CSCL 01/2 James R. VanGaasbeek Oct. 1979 511 o refs 3 Vol.

348 N80-22319

(Contract DAAJ02-77-C-0003; DA Proj. 112-62209-AH-76) of a number of working charts for flow parameters and includes IAD-A079632: BHT-699-099-062-Vol-2: USARTL-TR-77-54B: charts for the drag increments due to different types of roughness. USAAMRDL-TR-76-41B1 Avail: NTIS HC A22/MF AOl CSCL In the introductory part, the flow around wings is described 01/3 with emphasis on the variation of flow characteristics with flight This report Consists of three volumes and documents the conditions. Author (ESA( current version in the C81 family of rotorcraft flight simulation programs developed by Bell Helicopter Textron. This current N80-22317# European Space Agency. Paris (France). version of the digital computer program is referred to as AGAJ77. CIVIL COMPONENT PROGRAM WING SECTION. PREDI- The accompanying program for calculating fully coupled rotor MENSIONING OF A SUPERCRITICAL WING blade mode shapes is called DNAM05. and the rotor wake Reinhard Arndt Jul. 1979 226 p refs Transl. into ENGLISH program is called AR9 102. Volume 2. the User's Manual, contains of "Ziviles Kommponentenprogramm 'Flugelsektion' - Vordimen- the detailed information necessary for setting up an input data sionierung eines Flugels mit Ueberkritischem Profil", Rept. deck and interpreting the computed data. Volume 3. the BMFT-FB-W-77-38 DFVLR. Cologne and MBR G.m.b.H., Programmer's Manual, includes a catalog of subroutines and a Hamburg. Nov. 1977 Original report in GERMAN previously discussion of programming considerations. The source tapes announced as X79-72062 and related software for the computer programs documented in (ESA-TT-542. B M FT- F B -W- 77-38) Avail: NTIS this report are unpublished data on file at the Applied Technology HC Al 1/MF AOl: ZLDI. Munich DM 47,45 Laboratory. U.S. Army Research and Technology Laboratories To achieve an optimal wing structure with respect to stringer IAVRADCOMI, Fort Eustis, Virginia. GRA and rib pitch and their cross-sectional shape. an estimated dimensioning of 700 mm rib pitch based upon the structure optimization program 'Dascha' for rigid load cases was written. N80-22314# Naval Ship Research and Development Center, The coordinates are calculates from the contour program 'Geolan', Bethesda. Md. based on the wing profile MBB A1-725-146 and using the THE EFFECT OF SHAFT ANGLE ON PERFORMANCE OF wing geometry of the ZKP basic design 3 IA 300 B 10 X-21. A CIRCULATION CONTROL HIGH-SPEED ROTOR AT AN The dimensioning estimate was made in relation to rigid load ADVANCE RATIO OF 0.7 cases. To obtain a minimum of structure, this estimation should Kenneth R. Reader Feb. 1980 42 p refs be repeated with other pitches and cross-sectional shapes. The IAD-A080953: AERO-1262: DTNSRDC-80/015l Avail: NTIS elastic load cases which result in greater sectional sizes can HC A03/MF AOl CSCL 20/4 Author (ESA) The performance of a high speed rotor model, designated then be taken into consideration. the reverse blowing circulation control rotor IRBCCRI, evaluated in a wind tunnel in the forward flight mode is discussed. The N80-22318# Defence Research Information Centre, Orpington effects of rotor shaft angle of attack on rotor performance at (England). the transition advance ratio of mu = 0.7 are specifically examined. TRIALS TO COMPARE THE STOPPING PERFORMANCE OF The test variables include rotor thrust, blade collective pitch THREE ANTI-SKID SYSTEMS AND TO DEMONSTRATE angle, tip Mach number, and rotor shaft angle. The RBCCR model METHODS OF DETERMINING AIRCRAFT STOP DIS- demonstrates both the lift and trim capabilities required in the TANCES ON THE STANDARD MILITARY REFERENCE WET transitional flight regime. The model also shows that rotor SURFACE efficiency and power sharing between shaft power and compressor I. Beaty (Mech. Eng. Res. and Develop.) and R. W. Sugg (Mech. power can be controlled by rotor shaft angle at an advance Eng. Res. and Develop.) London HMSO Oct. 1979 64 p ratio of 07. M.G. refs (S/T-Memo-3/79: BR70264( Avail: NTIS HC A04/MF AOl N80-22315// European Space Agency. Paris (France). Tests were conducted to determine if there was any difference INVESTIGATIONS INTO AN ACTIVE VIBRATION ISOLA- in the stop distance of a BAC 1-11 aircraft under wet runway TION SYSTEM FOR HELICOPTERS WITH RIGID AND conditions when fitted with three different modern anti-skid ELASTIC AIRFRAME MODELING systems. By comparing the aircraft stop distances at the mu-meter Jean Skudridakis 1979 73 p refs Trarisl. into ENGLISH of reading of .6 it was concluded that although the two more "Untersichung zu Einen Aktiven Schwingungsisolationssystem fuer modern systems appeared to give the shorter distance, the Hubschrauber bei Starrer und Elasticher Zellenomodellierung". difference was small and based on insufficient data points to Rept. DLR-IB-552-78-6 DFVLR, Brunswick, Jun. 1978 give a high degree of confidence. The aircraft Braking Force (ESA-TT-531; DLR-IB-552/78-6) Avail: NTIS Coefficient versus speed and mu-meter reading from one of the NC A04/MF AOl runs was used to demonstrate the use a method to determine A system for active rotor isolation was investigated to the stop distance on the standard military reference wet surface compensate for blade number harmonic excitation of the rotor at the weight at which the aircraft was tested. A method of and limit the static relative movement of the rotor drive unit. deciding on the suitability of a test runway for aircraft/mu-meter Several sensor configurations were studied for the first completed braking trials using National and NATO standards are presented regulator design of a single rigid function model with a modified as well as recommendations on how to conduct the trials and Riccati design. This single axis computer model was reviewed how to determine mu-meter speed/friction curves for the test and extended for the elastic helicopter airframe modeling (by surface. Author (ESA) means of a modified Riccati design). Computer results show that the active rotor isolation is superior in design to all known N80-22319# Deutsche Forschungs- und Versuchsanstalt fuer passive rotor isolation systems. The regulators designed for the Luft- und Raumfahrt. Brunswick (West Germany). Inst. fuer single axis computer model show very good isolation of vibration Flugmechanik. at the 4- and 8- fold rotation frequencies of the rotor, in conjunction IN-FLIGHT HANDLING QUALITIES INVESTIGATION OF with rapid swinging. In addition, the separation between the AIRBUS A 310 DLC. CONFIGURATIONS ON LANDING rotor drive unit and the airframe was reduced with an additional APPROACH USING THE DFVLR-HFB 320 VARIABLE load factor. Author (ESA) STABILITY AIRCRAFT Dietrich Hanke Feb. 1979 87 p refs In GERMAN: ENGLISH N80-22316# Aeronautical Research Inst. of Sweden, Stockholm. summary Report will also be announced as translation Aerodynamics Dept. (ESA-TT-630) A PRACTICAL METHOD FOR PREDICTING ROUGHNESS (DFVLR-FB-79-18( Avail: NTIS HC AOS/MF AOl: DFVLR. EFFECTS ON AIRCRAFT Cologne DM 17.30 A. Bertelrud Nov. 1978 54 p refs In-flight simulation of the longitudinal and lateral/ directional (Contract SWEDBTD-7 1 348-U-253( dynamics of the Airbus A 310 aircraft using the DFVLR-HFB 320 (FFA .AU-1413) Avail: NTIS HC A04/MF AOl variable stability aircraft was studied. The evaluation of different A method for prediction of the extra drag due to surface spoiler direct lift controls IDLCI concepts for longitudinal control roughness on aircraft is described. The method is based on use was stressed. The influence of these concepts handling qualities

349 N80-22320

and pilot-vehicle performance under real instrument landing Modifications to the analysis/ computation procedure were systems (I LS) approach environmental conditions was determined. developed to alleviate restrictions. Sixty-three ILS approaches were flown by two pilots evaluating E. D. K four aircraft/D LC configurations, The main handling quality N8022324*# Pratt and Whitney Aircraft Group, East Hartford. parameter for DLC enhanced longitudinal control is the flight Conn. path to pitch attitude phase. A new general applicable flight PERFORMANCE DETERIORATION BASED ON EXISTING path to pitch attitude phase criteria is proposed. Author (ESA) (HISTORICAL) DATA; JT9D JET ENGINE DIAGNOSTICS PROGRAM N80-22320# Aeronautical Research Inst. of Sweden. Stockholm. G. Phil Sallee 20 Apr. 1978 228 p refs Aerodynamics Dept. (Contract NAS3-20632( ROUGHNESS EFFECTS ON FUEL CONSUMPTION FOR (NASA-CR- 135448: PWA-551 2-21) Avail: NTIS TWO COMMERCIAL AIRCRAFT: MCDONNELL DOUGLAS HC A11/MF AOl CSCL 21E DC-9 AND DC-10 Final Report The results of the collection and analysis of historical data A. Bertelrud Oct. 1979 48 p refs pertaining to the deterioration of JT9D engine performance are (Contracts SWEDBTD-77-4869: SWEDBTD-78-5543( presented. The results of analyses of prerepair and postrepair (FFA-AU-1456( Avail: NTIS HC A03/MF AOl engine test stand performance data from a number of airlines The effects of surface roughness on the fuel consumption to establish the individual as well as average losses in engine of two typical passenger aircraft. McDonnell Douglas DC-9 and performance with respect to service use are included. Analysis DC-b. are estimated. Typical cruise conditions and flights for of the changes in mechanical condition of parts, obtained by the two aircraft types are considered. The roughness effects are inspection of used gas-path parts of varying age, allowed estimated at two levels of sophistication: comprehensive and preliminary assessments of component performance deterioration simplified. In the detailed approach the inviscid flow field around levels and identification of the causitive factors. These component the wings is analyzed by means of a transonic, small perturbation performance estimates, refined by data from special engine code. The boundary layer is calculated with Bradshaw a back-to-back testing related to module performance restoration, straight-tapered swept wing code (with provision for distributed permitted the development of preliminary models of engine roughness). The simplified approach is basically a flat-plate component/ module performance deterioration with respect to analysis, which in many cases gave nearly the same results as usage. The preliminary assessment of the causes of module the more sophisticated approach. Author,(ESA( performance deterioration and the trends with usage are explained. along with the role each module plays in overall engine N80-22321*# National Aeronautics and Space Administration. performance deterioration. Preliminary recommendations with Langley Research Center. Langley Station, Va. respect to operating and maintenance practices which could be PILOT ASSESSMENT OF TWO COMPUTER-GENERATED adopted to control the level of performance deterioration are DISPLAY FORMATS FOR HELICOPTER INSTRUMENT presented. The needs for additional component sensitivity testing APPROACH as well as outstanding issues are discussed J M. S. Frank R. Niesseri, Perry L. Deal, and James M. Patton, Jr. May 1980 40 p refs N8022326*# Teledyne Continental Motors. Muskegon. Mich. (NASA-TM-80151; L-13136) Avail: NTIS HC A03/MF AOl DESIGN STUDY: A 186 kW LIGHTWEIGHT DIESEL CSCL OlD AIRCRAFT ENGINE Final Report Two computer generated display formats were evaluated as Alex P. Brouwers Apr. 1980 24 p primary displays by six research pilots in a fixed base simulator. (Contract NAS3-20830( One of the computer generated display formats was an electronic (NASA-CR-3261( Avail: NTIS HC A02/MF AOl CSCL 21E attitude director indicator (EADI) which featured three cue flight The design of an aircraft engine capable of developing director, command information, superimposed on true perspective 186 kW shaft power at a 7620 m altitude is described. The runway symbology. The other computer generated display format 186 kW design takes into account expected new developments featured separate horizontal and vertical situation information in aircraft designs resulting in a reassessment of the power with vector predictors. A baseline display, consisting of an requirements at the cruise mode operation. Based on the electromechanical attitude director indicator (ADI( with a three results of this analysis a three phase technology development cue flight director and a moving map, was used as a reference program is projected resulting in production dates of 1985, 1992, for the pilot evaluations. Author and 2000. R.E.S. N80-22327 t# National Aeronautics and Space Administration N8022323*# Massachusetts Inst. of Tech.. Cambridge. Lewis Research Center, Cleveland, Ohio. Aeroelastic and Structures Research Lab. GENERAL AVIATION PROPULSION TWO-DIMENSIONAL FINITE-ELEMENT ANALYSES OF Mar. 1980 437 p refs Conf. held in Cleveland. 28-29 Nov. SIMULATED ROTOR-FRAGMENT IMPACTS AGAINST 1979 RINGS AND BEAMS COMPARED WITH EXPERIMENTS (NASA-Cp-2126: E-310) Avail: NTIS HC A19/MF AOl CSCL Thomas R. Stagliano. Emmett A. Witmer, and Jose J. A. Rodal 21E Dec. 1979 363 p refs Programs exploring and demonstrating new technologies in (Grant NGR-22-009-339) general aviation propulsion are considered. These programs are (NASA-CR- 159645: ASRL-TR- 154-13) Avail: NTIS the quiet, clean, general aviation turbofan (QCGAT) program: HC A16/MF AOl CSCL 21E the general aviation turbine engine (GATE) study program: the Finite element modeling alternatives as well as the utility general aviation propeller technology program: and the ad- and limitations of the two dimensional structural response vanced rotary, diesel, and reciprocating engine programs. computer code CIVM-JET 4B for predicting the transient, large deflection, elastic plastic, structural responses of two dimensional beam and/or ring structures which are subjected to rigid N8022328*# AiResearch Mfg. Co.. Phoenix. Ariz. fragment impact were investigated. The applicability of the AIRESEARCH QCGAT ENGINE, AIRPLANE, AND NACELLE CIVM-JET 48 analysis and code for the prediction of steel DESIGN FEATURES containment ring response to impact by complex deformable Roger W. Heldenbrand In NASA. Lewis Rex. Center Gen. fragments from a trihub burst of a T58 turbine rotor was studied. Aviation Propulsion Mar. 1980 11-43 Dimensional analysis considerations were used in a parametric p examination of data from engine rotor burst containment Avail: NTIS HC A19/MF AOl CSCL 21E experiments and data from sphere beam impact experiments. The quiet, clean, general aviation turbofan engine and nacelle The use of the CIVM-JET 4B computer code for making parametric system was designed and tested. The engine utilized the core structural response studies on both fragment-containment of the AiResearch model TFE731-3 engine and incorporated structure and fragment -deflector structure was illustrated. several unique noise- and emissions-reduction features. Compo-

350 N80-22337 nents that were successfully adapted to this core include the nacelle incorporating full length fan ducting with Sound treatment fan, gearbox. combustor, low-pressure turbine, and associated in both the inlet and fan discharge flow paths. Design goals of structure. A highly versatile workhorse nacelle incorporating components and results of component tests are presented together interchangeable acoustic and hardwall duct liners, showed that with full engine test results. The rationale behind the combustor large-engine attenuation technology could be applied to small design selected for the engine is presented as well as the emissions propulsion engines The application of the mixer compound nozzle test results. Total system (engine and nacelle) test results are demonstrated both performance and noise advantages on the included. A.A.H. engine. Major performance. emissions, and noise goals were demonstrated. A.R.H. N8022333*# Avco Lycoming Div., Stratford. Conn. AVCO LYCOMING QUIET CLEAN GENERAL AVIATION N8022329* # AiResearch Mfg. Co.. Phoenix. Ariz. TURBOFAN ENGINE AIRESEARCH QCGAT ENGINE PERFORMANCE AND Craig A. Wilson In NASA. Lewis Res. Center Gen. Aviation EMISSIONS TESTS Propulsion Mar. 1980 p 155-187 refs William M Norgren In NASA. Lewis Res, Center Gen. Aviation Propulsion Mar. 1980 p 45-64 Avail: NTIS NC A19/MF AOl CSCL 21E A fan module was developed using an existing turboshaft Avail. NTIS HC A19/MF AOl CSCL 21E engine. The fan was designed using the latest in large engine Results of aerodynamic performance and emission tests, noise control technology. A mixer was added to reduce the conducted on a specially designed QCGAT engine in the 17.793-N already low exhaust gas velocity. A nacelle incorporating sound (4.000 lb) thrust class, are presented. Performance of the treatment was provided for the test engine. A noise prediction AiResearch QCGAT engine was excellent throughout all testing. model was used through the design process to evaluate the No serious mechanical malfunctions were encountered, and no various design alternatives. Acoustic tests were then made to significant test time was lost due to engine-related problems. verify the prediction and identify the noise characteristics of the Emissions were drastically reduced over similar engines, and the fan, core, jet, and sound treatment. Analysis of the recorded engine exhibited good smoke performance. A.R.H. data yielded close agreement with the expected results. Core noise, as was expected, was the predominant source of noise N8022330*# AiResearch Mfg. Co.. Phoenix, Ariz. for the quiet clean general aviation turbofan (QCGAT) engine. AIRESEARCH QCGAT ENGINE: ACOUSTIC TEST RE- Flyover noise predictions were made which indicated that the SULTS Avco Lycoming QCGAT engine would meet the goals set for Larry S. Kisner In NASA. Lewis Rex. Center Gen. Aviation the QCGAT program. R.E.S. Propulsion Mar. 1980 p 65-100 refs N8022335*# National Aeronautics and Space Administration. Avail: NTIS NC A19/MF AOl CSCL 21E Lewis Research Center, Cleveland, Ohio. The noise levels of the quiet, general aviation turbofan NEW OPPORTUNITIES FOR FUTURE, SMALL GENERAL- (QCGAT) engine were measured in ground static noise tests. AVIATION TURBINE ENGINES (GATE) The static noise levels were found to be markedly lower than William C. Strack In its Gen. Aviation Propulsion Mar. 1980 the demonstrably quiet AiResearch model TFE731 engine. The p 195-219 refs measured QCGAT noise levels were correlated with analytical Avail: NTIS HC A19/MF AOl CSCL 21E noise source predictions to derive free-field component noise The results of four independent contracted studies to explore predictions. These component noise sources were used to predict the opportunities for future small turbine engines are summarized the QCGAT flyover noise levels at FAR Part 36 conditions. The in a composite overview. Candidate advanced technologies are predicted flyover noise levels are about 10 decibels lower than screened, various cycles and staging arrangements are para- the current quietest business jets. Author metrically evaluated, and optimum conceptual engines are identified for a range of 300 to 600 horsepower applications. N8022331 * # Avco Lycoming Div.. Stratford, Conn. Engine improvements of 20 percent in specific fuel consumption QCGAT AIRCRAFT/ENGINE DESIGN FOR REDUCED and 40 percent in engine cost were forecast using high risk NOISE AND EMISSIONS technologies that could be technically demonstrated by 1988. Leonard Lanson and Kenneth M. Terrill In NASA. Lewis Res. The ensuing economic benefits are in the neighborhood of 20 to Center Gen Aviation Propulsion Mar. 1980 p 101-133 30 percent for twin-engine aircraft currently powered by piston engines. Author Avail: NTIS NC A19/MF AOl CSCL 21E The high bypass ratio QCGAT engine played an important N8022336*# National Aeronautics and Space Administration. role in shaping the aircraft design. The aircraft which evolved is Lewis Research Center, Cleveland, Ohio. a sleek, advanced design, six-place aircraft with 3538 kg AN OVERVIEW OF NASA RESEARCH ON POSITIVE (7.800 lb( maximum gross weight. It offers a 2778 kilometer DISPLACEMENT GENERAL-AVIATION ENGINES (1500 nautical mile) range with cruise speed of 0.5 Mach number Erwin E. Kempke, Jr. In its Gen. Aviation Propulsion Mar. and will take-off and land on the vast majority of general aviation 1980 p 227-229 airfields. Advanced features include broad application of composite Avail: NTIS HC A19/MF AOl CSCL 21E materials and a supercritical wing design with winglets. Full- The research and technology program related to improved span fowler flaps were introduced to improve landing capability. and advanced general aviation engines is described. Current Engines are fuselage-mounted with inlets over the wing to provide research is directed at the near-term improvement of conventional shielding of fan noise by the wing surfaces. The design objectives, air-cooled spark-ignition piston engines and at future alternative noise, and emission considerations, engine cycle and engine engine systems based on all-new spark-ignition piston engines, description are discussed as well as specific design features. lightweight diesels, and rotary combustion engines that show A R. H. potential for meeting program goals in the midterm and long-term future. The conventional piston engine activities involve efforts N8022332* # Avco Lycoming Div., Stratford. Conn. on applying existing technology to improve fuel economy, AVCO LYCOMING QCGAT PROGRAM DESIGN CYCLE. investigation of key processes to permit leaner operation and DEMONSTRATED PERFORMANCE AND EMISSIONS reduce drag, and the development of cost effective technology Phil Fogel and Angelo Koschier In NASA. Lewis Rex. Center to permit flight at high-altitudes where fuel economy and safety Gen. Aviation Propulsion Mar. 1980 p 135-154 refs are improved. The advanced engine concepts activities include engine conceptual design studies and enabling technology efforts Avail: NTIS HC A19/MF AOl CSCL 21E on the critical or key technology items. R.E.S. A high bypass ratio, twin spool turbofan engine of modular design which incorporates a front fan module driven by a modified N80-22337# Teledyne Continental Motors, Muskegon, Mich. LTS101 core engine was tested. The engine is housed in a Aircraft Products Div.

351 N80-22338

THE SPARK-IGNITION AIRCRAFT PISTON ENGINE OF THE N8022342*# Cessna Aircraft Co.. Wichita. Kans. Accessory FUTURE Div. Kenneth J. Stuckas In NASA. Lewis Res. Center Gen. Aviatior LOW SPEED PROPELLERS: IMPACT OF ADVANCED Propulsion Mar. 1980 p 231-245 TECHNOLOGIES Ira D. Keiter In NASA. Lewis Res. Center Gen. Aviation (Contract NAS3-2 1272) Propulsion Mar. 1980 p 327-343 refs Avail: NTIS HC A19/MF AOl CSCL 21E Areas of advanced technology appropriate to the design of Avail: NTIS HC A19/MF AOl CSCL 21E a spark-ignition aircraft piston engine for the late 1980 time Sensitivity studies performed to evaluate the potential of period were investigated and defined. Results of the study show several advanced technological elements on propeller performance, that significant improvements in fuel economy, weight and size, noise, weight, and cost for general aviation aircraft are discussed. safety, reliability, durability and performance may be achieved Studies indicate that the application of advanced technologies with a hiah degree of success, oredicated on the continued to general aviation propellers can reduce fuel consumption in development of advances in combustion systems, electronics, future aircraft an average often percent. meeting Current regulatory materials and control systems. R.E.S. noise limits. Through the use of composite blade Construction, up to 25 percent propeller weight reduction can be achieved. N8022338*# Teledyne Continental Motors, Muskegon, Mich. This weight reduction in addition to seven percent propeller General Products Div. efficiency improvements through application of advanced LIGHTWEIGHT DIESEL AIRCRAFT ENGINES FOR GENERAL technologies result in four percent reduction in direct operating AVIATION costs, ten percent reduction in aircraft acquisition cost, and seven Steven G. Berenyi and Alex P. Brouwers In NASA. Lewis percent lower gross weight for general aviation aircraft. M.G. Res. Center Gen. Aviation Propulsion Mar. 1980 p 247-285

Avail: NTIS HC A19/MF AOl CSCL 21E N8O22343*# Hamilton Standard, Windsor Locks, Conn. A methodical design study was conducted to arrive at new ADVANCED TURBOPROP POTENTIAL FOR HIGH SPEED diesel engine configurations and applicable advanced technologies. Bernard S. Gatzen In NASA. Lewis Res. Center Gen. Aviation Two engines are discussed and the description of each engine Propulsion Mar. 1980 p 345-359 includes concept drawings; A performance analysis, stress and weight prediction, and a cost study were also conducted. This Avail: NTIS HC A19/MF AOl CSCL 21E information was then applied to two airplane concepts, a six-place A turboprop propulsion system for general aviation aircraft, twin and a four-place single engine aircraft. The aircraft study allowing high speed flight Ito 0.8 Mach) is discussed. Design consisted of installation drawings, computer generated perfor- methodologies for aerodynamic and acoustic considerations and mance data, aircraft operating costs and drawings of the resulting the performance and cost advantages of a prop-fan aircraft are airplanes. The performance data shows a vast improvement over presented. M.G. current gasoline-powered aircraft. At the completion of this basic study, the program was expanded to evaluate a third engine N8022344*# National Aeronautics and Space Administration. configuration. This third engine incorporates the best features of Lewis Research Center, Cleveland, Ohio. the original two, and its design is currently in progress. Preliminary HIGH-SPEED-PROPELLER WIND-TUNNEL AEROACOUSTIC information on this engine is presented. R.E.S. RESULTS Robert J. Jeracki and James H. Dittmar In its Gen. Aviation N8O22339* # Curtiss-Wright Corp., Wood-Ridge, N.J. Propulsion Mar. 1980 p 361-374 refs ADVANCED ROTARY ENGINE STUDIES Charles Jones In NASA. Lewis Res. Center Gen. Aviation Avail: NTIS HC A19/MF AOl CSCL 21E Propulsion Mar. 1980 p 287-311 refs Some aerodynamic concepts are presented together with an explanation of how these concepts are applied to advanced Avail: NTIS HC A19/MF AOl CSCL 21E propeller design. The unique features of this propulsion system A review of rotary engine developments relevant to a stratified are addressed with emphasis on the design concepts being charge rotary aircraft engine is presented. Advantages in module considered for the high speed turboprop. More particular size and weight, fuel efficiency, reliability, and multi-fuel capability emphasis is given to the blade sweep, long blade chords, and are discussed along with developments in turbocharging, increased the large number of blades. R.C.T. mean effective pressure, improved apex seal/trochoid wear surfacing materials, and high strength and temperature aluminum N80-22345# National Aeronautics and Space Administration. casting alloys. A carbureted prototype aircraft engine is also Lewis Research Center. Cleveland, Ohio. described. M.G. ADVANCED PROPELLER AERODYNAMIC ANALYSIS Lawrence J. Bober In its Gen. Aviation Propulsion Mar. 1980 N8O22340*# National Aeronautics and Space Administration. p 375-385 refs Lewis Research Center, Cleveland, Ohio. Avail: NTIS HC A19/MF AOl CSCL 21E POSITIVE DISPLACEMENT TYPE GENERAL-AVIATION The analytical approaches as well as the capabilities of three ENGINES: SUMMARY AND CONCLUDING REMARKS advanced analyses for predicting propeller aerodynamic perfor- Erwin E. Kempke, Jr. In its Gen. Aviation Propulsion Mar. mance are presented. It is shown that two of these analyses 1980 p 313-314 use a lifting line representation for the propeller blades, and the Avail: NTIS HC A19/MF AOl CSCL 21E third uses a lifting surface representation. R.C.T. The activities of programs investigating various aspects of aircraft internal combustion engines are briefly described including N8022346*# Ohio State Univ., Columbus. Aeronautical and developments in fuel injection technology, cooling systems and Astronautical Research Lab. drag reduction, turbocharger technology, and stratified-charge PROPELLER AEROACOUSTIC METHODOLOGIES rotary engines. M.G. Kenneth D. Korkan and Gerald M. Gregorek In NASA. Lewis Res. Center Gen. Aviation Propulsion Mar. 1980 p 387-404 N8022341*// National Aeronautics and Space Administration. refs Lewis Research Center, Cleveland, Ohio. (Grant N5G-3247l NASA PROPELLER TECHNOLOGY PROGRAM Avail: NTIS HC A19/MF AOl CSCL 21E Daniel C. Mikkelson In its Gen. Aviation Propulsion Mar. 1980 The aspects related to propeller performance by means of a p 315-325 refs review of propeller methodologies are addressed. Preliminary Avail: NTIS HC A19/MF AOl CSCL 21E wind tunnel propeller performance data are presented and the A program on propeller technology applicable to both low predominent (imitations of existing propeller performance and high speed general aviation aircraft is summarized, and the methodologies are discussed. Airfoil developments appropriate overall program objectives and approach are outlined. M.G. for propeller applications are also reviewed. R.C.T.

352 N80-22356

N8O22347*# National Aeronautics and Space Administration. (Contract F33615-78-C-2022: AF Proj. 3066) Langley Research Center. Langley Station, Va. (AD-A080620; PWA-FR- 11867; AFAPL-TA-79-2087) Avail: NASA PROPELLER NOISE RESEARCH NTIS HC A07/MF AOl CSCL 2115 George C. Greene In NASA. Lewis Res. Center Gen. Aviation The program objective was to evaluate active clearance Propulsion Mar. 1980 p 405-420 controls (ACC) for future military fighter and transport aircraft/ engines, rank the candidate schemes, and recommend a future Avail: NTIS HC A19/MF AOl CSCL 21E course of action. Fifty-one potential ACC concepts were reduced The research in propeller noise prediction, noise/ performance to twelve: five mechanical, two pneumatic, and five thermal. optimization, and interior reduction is described. Selected results The fighter and transport missions selected were the Advanced are presented to illustrate the status of the technology and the Tactical Fighter )ATF), and the C141X strategic aircraft. Three direction of future research. R.C.T. levels of controls for ACC were considered: simple on/off two-position; open loop infinitely variable: and feedback (requiring N80-22348t // Pennsylvania State Univ., University Park. a clearance sensor). On/off systems were selected for study PROPELLER DYNAMIC AND AEROELASTIC EFFECTS because the majority of the benefit is obtained during cruise/dash Barnes W. McCormick In NASA. Lewis Res. Center Gen. and the open and feedback systems have positioning and reliability Aviation Propulsion Mar. 1980 p 421-432 refs uncertainties. The criteria selected to evaluate the different schemes were net Life Cycle Cost benefits, to the fleet over the (Grants NsG-1308: N5G-3304) life of the weapons system. These criteria were based on a Avail: NTIS HC A19/MF AOl CSCL 21E new-engine/new-aircraft application where efficiency improve- Various aspects of propeller blade dynamics are considered ments due to ACC were used to reduce aircraft and engine size including those factors which are exciting the blades and the for a fixed mission (range, payload, etc.). The detailed operation dynamic response of the blades to the excitations. Methods for and impact (cost, weight, reliability, maintainability) of the twelve treating this dynamic system are described and problems are final schemes were evaluated by adopting each of the candidate discussed which may arise with advanced turboprop designs schemes to selected stages in the base engines. ACC showed a employing thin, swept blades. Author significant net benefit in the transport high pressure turbine. On the low pressure turbine some schemes showed a net savings, N80.22350*# National Aeronautics and Space Administration. but the amount was small. For the fighter application, ACC showed Lewis Research Center, Cleveland, Ohio. a significant net benefit in the high pressure turbine only. GRA PRELIMINARY STUDY OF ADVANCED TURBOPROP AND TURBOSHAFT ENGINES FOR LIGHT AIRCRAFT N80-22353# Deutsche Forschungs- und Versuchsanstalt fuer G. Knip, R. M. Plencner, and J. D. Eisenberg Apr. 1980 62 p Luft- und Raumfahrt. Cologne (West Germany). Inst. fuer refs Antriebstechnik. (NASA-TM-81467; E-397) Avail: NTIS HC A04/MF AOl CSCL DESIGN AND INVESTIGATION OF STATIC PRESSURE 21E COMPRESSOR CASCADES BEHIND IMPULSE-ROTORS The effects of engine configuration, advanced component Ph.D. Thesis - Technische Hochschule technology, compressor pressure ratio and turbine rotor-inlet Reinhold Fuchs Mar. 1979 119 p refs In GERMAN; ENGLISH temperature on such figures of merit as vehicle gross weight. summary Report will be also announced as translation mission fuel, aircraft acquisition cost, operating, cost and life )ESA-TT-629) cycle cost are determined for three fixed- and two rotary-wing )DFVLR-1`8-79-17( Avail: NTIS HC A06/MF AOl; DFVLR, aircraft. Compared with a current production turboprop, an Cologne DM 21.30 advanced technology (1988) engine results in a 23 percent The design, optimization, and wind tunnel testing for two decrease in specific fuel consumption. Depending on the figure dimensional cascades are described. The cascades decelerate the of merit and the mission, turbine engine cost reductions required rotor outlet velocity of about M = 2 to subsonic stator outlet to achieve aircraft cost parity with a Current spark ignition velocity by a multiple shock system realizing a high static pressure reciprocating (SIR) engine vary from 0 to 60 percent and from ratio. The multiple shock cascades with turning and without were 6 to 74 percent with a hypothetical advanced SIR engine. tested in a cascade wind tunnel and compared with results of Compared with a hypothetical turboshaft using currently available computations. Author (ESA) technology (1978), an advanced technology (1988) engine installed in a light twin-engine helicopter results in a 16 percent reduction in mission fuel and about 11 percent in most of the N8O-22355 Dayton Univ., Ohio. other figures of merit. A.R.H. DESIGN OF AN INTEGRATED FLIGHT/FIRE CONTROL SYSTEM INCLUDING MOVABLE GUN AND GIMBALED LINE OF SIGHT TRACKER Ph.D. Thesis N80-22351# Naval Air Propulsion Test Center, Trenton, N.J. John Hazen Blakelock 1979 354 p Propulsion Technology and Project Engineering Dept. Avail: Univ. Microfilms Order No. 8008431 INVESTIGATION OF LUBRICANT CONCEPTS APPLICABLE The design, analysis, and hybrid simulation of an integrated TO FUTURE NAVY AIRCRAFT PROPULSION SYSTEMS flight/fire control system )IFFC) including a movable gun and Final Report gimbaled line of sight tracker for the F-15 are discussed. The A. J. Porazio, E. F. Pierce. and P. A. Karpovich Nov. 1979 analysis includes a linear root locus analysis of the various control 51 p refs systems and a detailed discrete analysis of the sampled-data (ZF54594001; WF54543300( control system resulting from closing the outer control loops )AD-A079410: NAPC-PE-29) Avail: NTIS HC A04/MF AOl through the digital computer used to compute the prediction CSCL 11/8 angle and to generate the inputs to the flight control systems. Future lubrication requirements for Navy aircraft engines were The capability of the IFFC system was tested against various estimated. Viable areas were evaluated to determine relative target scenarios using a hybrid simulation. The results show strengths and weaknesses of several systems. Among those areas that the IFFC with the movable gun is able to track a wide investigated were ester lubricants, inserted ester lubricant variety of target scenarios, including inverted flight to track an systems, polyphenyl ethers and gas lubricated compliant aircraft performing a split S. with the gun on track for a major bearings. GRA portion of each run. Dissert. Abstr.

N8O22356*# Joint Inst. for Advancement of Flight Sciences, N80-22352# Pratt and Whitney Aircraft Group, West Palm Hampton, Va. Beach, Fla. Government Products Div. EFFECT OF A FLEXIBLY MOUNTED STORE ON THE THERMAL RESPONSE TURBINE SHROUD STUDY Final FLUTTER SPEED OF A WING Final Report Report, Aug. 1978 - May 1979 Harry L. Runyan NASA. Langley Res. Center. Apr. 1980 E. J. Kawecki Wright-Patterson AFB, Ohio AFAPL Jul. 1979 25 p refs 135 p (Grant NsG-1438(

353 N80-22357

)NASA-CR-159245) Avail: NTIS HC A02/MF AOl CSCL is attached. The device allows the flutter speed of an aircraft 011C flying with an attached store to be increased while reducing the A passive system proposed for increasing the flutter speed sensitivity of flutter to changes in the pitch inertia and center of a wing with heavy concentrated weights involves the concept of gravity location of the store. NASA of mounting the store on a pitch pivot having a very low pitch stiffness relative to the wing stiffness. This concept was N80-22360# Air Force Inst. of Tech.. Wright-Patterson AFB, investigated utilizing a two dimensional approach involving Ohio. School of Engineering. 4 degrees of freedom, namely. wing bending, wing torsion. Store USING VERTICAL GUST ALLEVIATION TO IMPROVE THE pitch and store vertical translation. This preliminary analysis was TARGET TRACKING CAPABILITY OF THE CONTROL very encouraging and the results demonstrate that, if the uncoupled CONFIGURED YF-16 M.S. Thesis store pitch frequency was below the wing bending frequency, Eric R. Molner Aug. 1979 278 p refs the flutter speed was greatly increased. A second more )AO-A080520; AFIT/GGC/ EE/79-5( Avail: NTIS complete analysis was developed utilizing a three dimensional HC A13/MF AOl CSCL 01/3 structure, but retaining the two dimensional, incompressible This thesis investigates the use of multiple aerodynamic unsteady airforces of Theodorsen. The details of the analysis control surfaces as a part of a flight control system configured are included. A.R.H. to reduce aircraft pitch response to atmospheric disturbances. Coordinated deflection of two surfaces provides the desired N8022357*# Massachusetts Inst. of Tech.. Cambridge. gust alleviation with no decrease in system damping. At the Aeroelastic and Structures Research Lab. same time, the commanded aircraft performance is improved THE DESIGN, TESTING AND EVALUATION OF THE MIT relative to the performance of the baseline flight control system INDIVIDUAL-BLADE-CONTROL SYSTEM AS APPLIED TO using a single control surface. The aircraft chosen for this analysis GUST ALLEVIATION FOR HELICOPTERS Final Report is the General Dynamics YF-16. This particular aircraft has a Robert Miller McKillip, Jr. Feb. 1980 92 p refs fly-by-wire electronic flight control system - an arrangement that (Grant NsG-2266) permits the control surfaces to be electronically activated. A (NASA-CR- 152352: ASRL-TR-1 96-1) Avail: NTIS means of applying discrete vertical gusting to a modeled system HC A05/MF AOl CSCLO1C is presented to permit evaluation of system performance. Using A type of active control for helicopters was designed and a simulation computer program, the YF-16 with baseline flight tested on a four foot diameter model rotor. A single blade was control system and Maneuver Enhancement augmentation are individually controlled in pitch in the rotating frame over a wide examined to determine gust response and pilot response range of frequencies by electromechanical means. By utilizing a characteristics. GRA tip mounted accelerometer as a sensor in the feedback path, significant reductions in blade flapping response to gust were N80-22361# Air Force Inst. of Tech., Wright-Patterson AFB, achieved at the gust excitation frequency as well as at super Ohio. School of Engineering. and subharmonics of rotor speed. E D. K. THE APPLICATION OF OUTPUT PREDICTIVE DIGITAL CONTROL TO WING FLUTTER SUPPRESSION AND N8022358*# National Aeronautics and Space Administration. Langley Research Center, Langley Station, Va. TERRAIN FOLLOWING PROBLEMS M.S. Thesis David E. Chaffin Dec. 1979 176 p refs DESCRIPTION OF AN EXPERIMENTAL (HYDROGEN (AD-A080419; AFIT/GE/EE/79-9) Avail: NTIS PEROXIDE) ROCKET SYSTEM AND ITS USE IN MEASUR- HC A09/MF AOl CSCL 01/3 ING AILERON AND RUDDER EFFECTIVENESS OF A LIGHT This thesis is a study of a digital control technique known AIRPLANE as Output Predictive Control )OPC) or Model Algorithmic Control Thomas C. OBryan, Maxwell W. Goode, Frederick D. Gregory. (MAC). In OPC, the behavior of the system is predicted using and Mama H. Mayo May 1980 42 p refs its impulse response function and the desired response is (NASA-TP-1647; L-12494) Avail: NTIS HC A03/MF AOl characterized by a reference trajectory. Controls are computed CSCL O1C iteratively to drive the system output along the desired trajectory. A hydrogen peroxide fueled rocket system, which is to be In an earlier study, the system was made to follow the reference used as a research tool in flight studies of stall and spin maneuvers, trajectory exactly, but only at the control application time; there was installed on a light, four place general aviation airplane. were large oscillations of the output between control changes. The pilot controlled rocket system produces moments about either In this study, the control calculation is reformulated as a least the roll or the yaw body axis to augment or oppose the squares curve fit problem, allowing some deviation from the aerodynamic forces and inertial moments acting on the airplane desired trajectory. This approach is applied as a regulator for a during various flight maneuvers, including the spin. These very lightly damped fourth-order single-input/single-output system controlled moments of a known magnitude can be used in various and as a pitch axis autopilot in a simplified terrain following ways to help analyze and interpret the importance of the various problem. A qualitative discussion of the robustness properties is factors which influence airplane maneuvers. The rocket system included. The design of the controller is difficult due to the and its installation in the airplane are described, and the results interrelationships of the internal parameters. however, the results of flight rests used to measure rudder and aileron effectiveness of the terrain following example indicate that this is a viable at airspeeds above the stall are presented. These tests also serve approach for this problem. GRA to demonstrate the operational readiness of the rocket system for future research operations. E.D.K. N80-22362# Air Force Inst. of Tech., Wright-Patterson AFB, Ohio. School of Engineering. N80.22359*# National Aeronautics and Space Administration. ANALYSIS OF THE EFFECTS OF HIGHER ORDER CONTROL Langley Research Center, Langley Station, Va. SYSTEMS ON AIRCRAFT APPROACH AND LANDING DECOUPLER PYLON: WING/STORE FLUTTER SUPPRES- LONGITUDINAL HANDLING QUALITIES M.S. Thesis SOR Patent Application Muhammad Anwar Pasha Dec. 1979 236 p refs Wilmer A. Reed, Ill, inventor (to NASA) Filed 28 Mar. 1980 )AD-A0805 19; AFIT/GE/EE/79-27) Avail: NTIS 18 p HC A11/MF AOl CSCLO5/8 (NASA-Case-LAR- 12468-1; US-Patent-Appl-SN- 135057) Avail: The approach and landing longitudinal flying qualities data NTIS HC A02/MF AOl CSCL 01C generated by Caispan using variable stability NT-33 aircraft A device for suspending a store from a support such as an combined with significant control system dynamics was analyzed. aircraft wing is described. It comprises soft-spring means whereby Three different approaches were used to determine the re- the store pitch mode is decoupled from support modes and a lationship between pilot ratings and the pilot workload, system low frequency active control mechanism which maintains store sensitivity, and the system performance. An open-loop frequency alignment. In the described embodiment, a pneumatic suspension response analysis showed that for a particular crossover frequency system both isolates the store in pitch and, under conditions of and phase margin (fixed performance), the phase angle (pilot changing mean load, aligns the store with the wing to which it workload) and slope of the phase curve )system sensitivity) at

354 N80-22372 the crossover frequency correlated well with the pilot ratings. Wind tunnel investigations were conducted on a 1/8.5 scale An optimum pilot lead time for pitch tracking, flight path angle model of the A-6/circulation control wing flight demonstrator tracking, and both pitch and flight path angle tracking tasks is aircraft in order to confirm the high lift capability of the concept, determined by a closed-loop analog simulation using integral to improve lifting and control surfaces and to provide supporting error squared as a performance measure. A correlation is found data to assure safety of flight and adequate handling of the between pilot ratings and performance. An attempt is made to full-scale aircraft. The best configuration developed during these explain the landing task as a closed-loop pitch and flight path investigations produced a 2.2 fold increase in maximum coefficient angle tracking task. The open-loop impulse response of the pitch of lift over the conventional A-6A high lift configuration. This attitude showed that the initial delay and the transient behavior circulation control wing configuration was compromised to simplify of the pitch response have a direct impact on the pilot ratings, testbed aircraft modifications, reduce construction costs, and pilot induced oscillations, and comments. GRA provide a larger range of parameters obtainable during flight testing, yet in the final configuration, still provided trimmed N80-22363# European Space Agency. Paris (France). aerodynamic maximum coefficient of lift double that of the CONTROL SYSTEM DESIGN USING VECTOR-VALUED standard A . 6A. A.R.H PERFORMANCE CRITERIA WITH APPLICATION TO THE CONTROL RATE REDUCTION IN PARAMETER INSENSI- N8O22367*# Jet Propulsion Lab., California Inst. of Tech.. TIVE CONTROL SYSTEMS Pasadena. Gerhard Kreisselmeier Dec. 1978 39 p refs Transl. into HIGH VOLTAGE SPARK CARBON FIBER DETECTION ENGLISH of "Reglerentwurf mit Vektoriellen Guetekriterien und SYSTEM Seine Praktische Anwendung zur Stellgeschwindigkeitsreduktion Lien C. Yang 15 Apr. 1980 96 p refs bei Parameterunempfindlichen Reglern", Rept. DLR-FB-77-55 (Contract NAS7-100( DFVLR, Oberpfaffenhofen. Nov. 1977 Original report in GERMAN Avail: previously announced as X79-71 736 (NASA-CR- 162995; JPL-Pub-80-30( NTIS (ESA-TT-512-Rev: DLR-FB-77-55-Rev( Avail: NTIS HC A05/MF AOl CSCL 14B HC A03/MF AOl; DFVLR, Cologne OM 17 The pulse discharge technique was used to determine the A design strategy is suggested which uses for the optimization length and density of carbon fibers released from fiber composite of the control system, a vector-valued performance-criterion such materials during a fire or aircraft accident. Specifications are that a systematic step-by-step improvement of the performance given for the system which uses the ability of a carbon fiber to vector is achieved. i.e.. at each stage the performance of some initiate spark discharge across a high voltage biased grid to components is improved without impairing that of the others, achieve accurate counting and sizing of fibers. The design of so that finally the optimal design is obtained. This technique is the system was optimized, and prototype hardware proved used to design a parameter-insensitive flight-path controller which, satisfactory in ' laboratory and field tests. A.R.H. compared with earlier designs, has both a larger reduction in sensitivity and a considerable reduction in the maximal control N8022368*# National Aeronautics and Space Administration. rate. The design shows that a controller can have considerably Langley Research Center, Langley Station, Va. reduced sensitivity without increasing the demands on the actuator MAGNETIC SUSPENSION AND BALANCE SYSTEM: , A system. This result is due primarily to the control rate being SELECTIVE ANNOTATED BIBLIOGRAPHY directly considered in the design. The controller-synthesis Marie H. Tuttle, Robert A. Kilgore. and Richmond P. Boyden technique based on vector-valued performance-criteria as here Apr. 1980 47 p suggested is feasible even when the number of design aspects (NASA-TM-80225; L-13196) Avail: NTIS HC A03/MF AOl is large. Author (ESA) CSCL 14E This bibliography, with abstracts, consists of 188 citations N80-22364# Office National d'Etudes et de Recherches arranged in chronological order by dates of publication. Selection Aerospatiales. Paris (France). of the citations was made for their relevance to the problems DEFINITION OF A TWO LEVEL CONTROL SYSTEM FOR involved in understanding, designing, and constructing magnetic NONLINEAR AIRCRAFT MOTION suspension and balance systems for use in wind tunnels. Author Albert Kirszenblat 1979 34 p refs In FRENCH; ENGLISH summary Report will also be announced as translation N80-22371# Defence Research Information Centre. Orpington (ESA-TT-614) (England). (ONERA-NT- 1979-7; ISSN-O078-3781) Avail: NTIS A MEANS OF SPECIFYING A STANDARD REFERENCE WET HC A03/MF AOl SURFACE FOR MILITARY AIRCRAFT The utilization of fly by wire control systems is discussed in R W. Sugg (Mech. Eng. Res. and Develop.) London HMSO terms of the improvement of aircraft handling qualities. An Oct. 1979 15 p refs approach to the problem of defining a control law well adapted (5/T-Memo-1/79; BR70262) Avail: NTIS HC A02/MF AOl to the whole flight envelope is presented. This system has a The British civil aircraft requirements (BCAIR) method of two level structure allowing a task oriented control and an aircraft certification under wet conditions and the correction of augmentation of the aircraft stability. A nonlinear model of the stopping distances to a standard using a friction trailer is studied. aircraft dynamics is described incorporating the inertial coupling The method is also examined for military aircraft. The use of term, and the nonlinear aerodynamic effects. The model generates the standard to •accident investigation procedures and NATO a trajectory, a reference control law vector, and an output vector standards is discussed. A standard military reference wet surface which tracks a vector. This vector represents the maneuvering and a way to correct aircraft performance to the standard are objectives assigned by the pilot at any time. A servo compensation examined. Author (ESA( which subordinates the aircraft motion to the model is also given. The control law is obtained by application of the optimal N80-22372# Defence Research Information Centre. Orpington linear control theory to local linear models of the aircraft. Direct (England). force control surfaces were easily incorporated in the computation AN INVESTIGATION INTO MEASURING RUNWAY SUR- of the control system. Author (ESA) FACE TEXTURE BY THE GREASE PATCH AND OUTFLOW METER METHODS N80-22365// Naval Ship Research and Development Center. A. W. Sugg (Mech. Eng. Res. and Develop.) London HMSO Bethesda, Md. Aviation and Surface Effects Dept. Oct. 1979 33 p refs DEVELOPMENT OF THE A-6/CIRCULATION CONTROL (S/T-Memo-2/79; BR70263) Avail: NTIS HC A03/MF AOl WING FLIGHT DEMONSTRATOR CONFIGURATION Final A measurement of surface texture was used by some Report, Sep. 1975 - Jul. 1978 organizations as a means of specifying runway friction for stop Robert J. Englar Jan. 1979 158 p refs distance calculations and certification purposes in spite of the (AD-A081241 ' DTNSRDC/ASED-79-01) Avail: NTIS conclusion by the American Society for Testing and Materials HC A08/MF AOl CSCL 14/2 (ASTM) that it should be discontinued. A method of using surface

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texture to predict friction of ground vehicles at high speed was operate the engine ultralean. A 17 percent improvement in fuel studied and it is concluded that within the limits found on economy was demonstrated in flight with the Beechcraft Duke runways it has only a very small effect on the prediction. It is B60 by simply leaning the engine at constant cruiser power recommended that where high speed prediction is necessary a and adjusting the ignition for best timing. No detonation was more accurate method is to use equations based on test data. encountered, and a 25.000 ft ceiling was available. Engine The difficulty in arriving at a single figure for surface texture roughness was shown to be the limiting factor in the leanout. was demonstrated by showing the variation that can occur along R.C.T. a runway and the large difference in readings between operators. Author (ESA) N8022432*# Little (Arthur D.(. Inc.. Cambridge, Mass. ANALYSIS OF NASA JP-4 FIRE TESTS DATA AND N80-22374# Deutsche Forschungs- und Versuchsanstalt fuer DEVELOPMENT OF A SIMPLE FIRE MODEL Luft- und Raumfahrt. Brunswick (West Germany). Inst. fuer Phani Raj Apr. 1980 58 p refs Entwurfs-Aerodynamik. (Contract NAS1 -15380) GRAVIMETRIC INVESTIGATION OF THE PARTICLE (NASA-CR- 159209: Rept-8 1857-6) Avail: NTIS NUMBER DENSITY DISTRIBUTION FUNCTION IN THE HC A04/MF AOl CSCL 216 HIGH SPEED CASCADE WIND TUNNEL FOR LASER- The temperature, velocity and species concentration data ANEMOMETRY MEASUREMENTS obtained during the NASA fire tests (3m. 7.5m and 1 5m diameter Harro Bessling and Torsten Hinz (Bundesforschungsanstalt fuer JP-4 fires) were analyzed. Utilizing the data analysis, a sample Landwirtsch.( Jan. 1979 39 p refs In GERMAN; ENGLISH theoretical model was formulated to predict the temperature and summary Report will also be announced as translation velocity profiles in JP-4 fires. The theoretical model, which does )ESA-TT-625) not take into account the detailed chemistry of combustion, is (DFVLR-FB-79-12) Avail: NTIS HC A03/MF AOl: DFVLR, capable of predicting the extent of necking of the fire near its Cologne OM 8.50 base. Author The conditions in high speed cascade wind tunnels were investigated to determine for the use of laser anemometers in N80-22492# Solar Turbines International, San Diego, Calif. measuring flow velocities. The natural particle number density DEVELOPMENT OF FIRE-RESISTANT, LOW SMOKE present in the cascade wind tunnel was found insufficient for GENERATING, THERMALLY STABLE END ITEMS FOR the application of the laser method. The effect of adding aerosols COMMERCIAL AIRCRAFT AND SPACECRAFT USING A to increase the number of particles in the wind tunnel is BASIC POLYIMIDE RESIN Final Report, 15 Dec. 1977 - discussed. Author (ESA) 15 Apr. 1980 J. Gagliani. R. Lee. U. A. K. Sorathia. and A L. Wilcoxson N80-22412H National Aeronautics and Space Administration, 15 Apr. 1980 176 p refs Washington, D. C. (Contract NAS9-1 5484) ECONOMICAL PROCESSING OF FIBER-REINFORCED (NASA-CR- 160576: SR79-R-4674-38( Avail: NTIS COMPONENTS WITH THERMAL EXPANSION MOLDING HC A09/MF AOl CSCL 07C K. Schneider Dec. 1979 34 p Transl. into ENGLISH of conf. A terpolyimide precursor was developed which can be foamed Paper-79-011 from OG LR Presented at the Symp. uber by microwave methods and yields foams possessing the best Wirtschaftliche Herstelltechniken, Cologne, 28 Mar. 1979 Original seating properties. A Continuous process, based on spray drying language document was announced as A79-32307 Transl. by techniques, permits production of polyimide powder precursors Kanner (Leo) Associates. Redwood City. Calif. in large quantities. The constrained rise foaming process permits (Contract NASw-3198( fabrication of rigid foam panels with improved mechanical (NASA-TM-75738; Paper-79-01 1) Avail: NTIS properties and almost unlimited density characteristics. Polyimide HC A03/MF AOl CSCL 11 foam core rigid panels were produced by this technique with The concept of economical fabrication of fiber-reinforced woven fiberglass fabric bonded to each Side of the panel in a structural components is illustrated with an example of a typical one step microwave process. The fire resistance of polyimide control surface (aileron). The concept provides for fabricating foams was significantly improved by the addition of ceramic struts, ribs, and a cover plate as an integral structure in a hardening fibers to the powder precursors. Foams produced from these device and then joining the closure cover plate mechanically. compositions are flexible, possess good acoustical attenuation Fabrication of the integral structure is achieved by the 'thermal and meet the minimum burnthrough requirements when impinged expansion molding technique. The hardening pressure is produced by high flux flame sources. A.R.H. by silicone rubber cores which expand under the influence of temperature. Test results are presented for several rubber materials as well as for various structural pieces. The technique N80-22723 Engineering Sciences Data Unit, London (England). is demonstrated extensively for an aileron, consisting of five ribs, ENDURANCE OF RIVETED LAP JOINTS (ALUMINUM struts, and a cover plate. Economically, for a large scale technical ALLOY SHEET AND RIVETS) production of an aileron, cost savings of twenty-five percent 1979 21 p can be realized compared to those for a sheet metal structure. (ESDU-79031: ISBN-0-85679-279-0: ISSN-0141-3996( For J.M.S. information on availability of series, sub-series, and other individual data items, write NTIS. Attn: ESDU, Springfield, Va. 22161 NC $578.50 N80-22430t # Jet Propulsion Lab.. California inst. of Tech.. Fatigue endurance data is provided for riveted lap joints in Pasadena. - aluminum alloy sheet. Life estimations of lightweight structures ULTRALEAN COMBUSTION IN GENERAL AVIATION for aircraft. lightweight surface vessels, and other vehicles can PISTON ENGINES be made from the data. The range of applicability is for J. E. Chirivelia 1 Dec. 1979 246 p refs aluminum alloy sheets and rivets where the geometrical ratios (Contract NA S7- 100) are in the ranges d/t 1.9 to 4.4. p/I (NASA-CR- 163001; JPL-Pub-79-75( Avail: NTIS 0.5 to 2.3 and p/d HC A11/MF AOl CSCL21B = 3.1 to 12.9. ESDU (GRA( The role of ultralean combustion in achieving fuel economy in general aviation piston engines was investigated. The aircraft N80-22734t # National Aeronautics and Space Administration. internal combustion engine was reviewed with regard to general Lewis Research Center, Cleveland. Ohio. aviation requirements, engine thermodynamics and systems. NONLINEAR. THREE-DIMENSIONAL FINITE-ELEMENT Factors affecting fuel economy such as those connected with ANALYSIS OF AIR-COOLED GAS TURBINE BLADES an ideal leanout to near the gasoline lean flammability limit Albert Kaufman and Raymond E. Gaugler Apr. 1980 22 p (ultralean operation) were analyzed. A Lycoming T10-541E engine refs was tested in that program (both in the test cell and in flight). (NASA-TP-1669; E-074( Avail: NTIS NC A02/MF AOl CSCL Test results indicate that hydrogen addition is not necessary to 21E

356 N80-23100

Cyclic stress-strain states in cooled turbine blades were A. E. Dwyer and R. H. Godin (NOAA. Washington. D. C.) Wallops calculated for a simulated mission of an advanced-technology Island, Va. NASA Wallops Flight Center. Mar. 1980 49 p commercial aircraft engine. The MARC. nonlinear, finite-element refs computer program was used for the analysis of Impingement- )NASA-CR-156862) Avail: NTIS HC A03/MF AOl CSCL cooled airfoils, with and without leading-edge film cooling. Creep 08L was the predominant damage mode (ignoring hot Corrosion), The GEOS-3 satellite and radar altimeter instrumentation particularly artund film-cooling holes. Radially angled holes are described, detailing the ice boundary discrimination technique exhibited less creep than holes with axes normal to the surface. utilized and presenting an analyses of the GEOS-3 data with Beam-theory analyses of all-impingement-cooled airfoils gave fair respect to satellite visual and IA imagery. A brief description of agreement with MARC results for initial creep. Author the GEOS-3 real time data system is also given. E.D.K.

N80-22737 t # National Aeronautics and Space Administration. N8022778*# AiResearch Mfg. Co.. Phoenix, Ariz. Langley Research Center. Langley Station. Va. CONCEPT DEFINITION STUDY OF SMALL BRAYTON CYCLE APPLICATION OF TWO DESIGN METHODS FOR ACTIVE ENGINES FOR DISPERSED SOLAR ELECTRIC POWER FLUTTER SUPPRESSION AND WIND-TUNNEL TEST SYSTEMS Final Report, Sep. 1978 - Jun. 1979 RESULTS - Lyle D. Six, Thomas L. Ashe, Frank X. Dobler. and Ron T. Elkins Jerry R. Newsom, Irving Abel, and H. J. Dunn May 1980 Jan. 1980 135 p refs 84p refs (Contracts DEN3-69; EX-76-A-29-1060) )NASA-TP-1653: L-13177) Avail: NTIS HC A05/MF AOl (NASA-CR- 159592: DOE/ NASA/0069-79/ 1, CSCL 20L AiResearch-31-3328) Avail: NTIS HC A07/MF AOl CSCL The synthesis, implementation, and wind tunnel test of two lOB flutter suppression control laws for an aeroelastic model equipped Three first-generation Brayton cycle engine types were studied with a trailing edge control surface are presented. One control for solar application: a near-term open cycle (configuration M. a law is based on the aerodynamic energy method, and the other near-term closed cycle (configuration B), and a longer-term open is based on results of optimal control theory. Analytical methods cycle (configuration Q. A parametric performance analysis was used to design the control laws and evaluate their performance carried Out to select engine designs for the three configurations. are described. At Mach 0.6, 0.8. and 0.9, increases in flutter The interface requirements for the Brayton cycle engine/generator dynamic pressure were obtained but the full 44 percent increase and solar receivers were determined. A technology assessment was not achieved. However at Mach 095. the 44 percent increase was then carried Out to define production costs, durability, and was achieved with both control laws. Experimental results indicate growth potential for the selected engine types. R.E.S. that the performance of the systems is not so effective as that predicted by analysis, and that wind tunnel turbulence plays an important role in both control law synthesis and demonstration of system performance. - E.D.K. N8023008*# National Aeronautics and Space Administration. Langley Research Center. Langley Station, Va. VALIDATION METHODS RESEARCH FOR FAULT- N80-22749# National Aerospace Lab., Amsterdam (Netherlands). TOLERANT AVIONICS AND CONTROL SYSTEMS: WORK- Structures and Materials Div. ING GROUP MEETING. 2 FATIGUE CRACK PROPAGATION IN ALUMINUM ALLOY James W. Gault. ed , Kushor S. Trivedi, ed.. and James B. Clary, SHEET MATERIALS UNDER MANEUVER SPECTRUM AND ed. 1980 105 p Meeting held at Hampton. Va. 3-4 Oct. CONSTANT AMPLITUDE LOADING 1979 - R. J. H. Wanhill Jun. 1978 25 p refs Submitted for publication )NASA-CP-2130; L-13716) Avail: NTIS HC A06/MF AOl Sponsored in part by Royal Netherlands Air Force Directorate CSCL 12A of Material The validation process comprises the activities required to )NLR-MP-78025-U) Avail NTIS HC A02/MF AOl insure the agreement of system realization with system specifica- Aluminum alloy sheets were compared for fatigue crack tion. A preliminary validation methodology for fault tolerant propagation resistance under maneuver conditions and constant systems documented. A general framework for a validation amplitude loading. Results of stress levels, crack growth rate, methodology is presented along with a set of specific tasks delta k value, and fracture toughness for each alloy are intended for the validation of two specimen system. SIFT and presented. Author (ESA) PIMP. Two major areas of research are identified. First, are those activities required to support the ongoing development of the validation process itself, and second, are those activities N80-22753# National Aerospace Lab.. Amsterdam (Netherlands). required to support the design, development, and understanding Structures and Materials Div. of fault tolerant systems. E.D.K. THE INFLUENCE OF BENDING-TORSIONAL COUPLING ON THE BUCKLING LOAD OF GENERAL ORTHOTROPIC, MIDPLANE SYMMETRIC AND ELASTIC PLATES N8O23100*# National Aeronautics and Space Administration. J. F. M. Wiggenraad 1977 75 p refs Lewis Research Center, Cleveland, Ohio. (Contract NIVR-1808) )NLR-TR-77 126-U) Avail: NTIS HC A04/MF AOl FORWARD ACOUSTIC PERFORMANCE OF A SHOCK- The influence of bending-torsional coupling on the buckling SWALLOWING HIGH-TIP-SPEED FAN (QF-13) load of general orthotropic, midplane symmetric and elastic plates James G. Lucas, Richard P. Woodward, and Michael J. MacKinnon May 1980 20 p refs was studied. This effect was analyzed for the case of infinitely )NASA-TP-1668: E-202( Avail: NTIS HC A02/MF AOl CSCL long plate strips, resulting in approximate analytical solutions, 20A which can be presented graphically for the entire range of the Forward noise and overall aerodynamic performance data elastic constants. These solutions were obtained with the are presented for a high-tip-speed fan having rotor blade airfoils approximate method as applied by Thielemann. The results were designed to alter the conventional leading-edge bow shocks to compared with results for finite length panels as derived with weak, oblique shocks which are swallowed within the interblade the finite element method. The conclusion is drawn that buckling channels. It was anticipated that the swallowed shocks would loads for plates with aspect ratio over 2 or 3, which demonstrate minimize the generation of multiple-pure-tone noise. In the the bending-torsional coupling effect, can be estimated fairly well speed range where the shocks presumably were swallowed, the from the results for the infinitely long plate strip. Author (ESA) multiple-tone noise was lowered only about 3 decibels. Compar- ison with several high-speed fans on a thrust-corrected basis N8022758*# Computer Sciences Corp., Wallops Island, Va. indicates that the present fan was the quietest in total forward DETERMINING SEA-ICE BOUNDARIES AND ICE ROUGH- noise at low speeds but offered no advantage at high speeds. NESS USING GEOS-3 ALTIMETER DATA Author

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N80-23104// European Space Agency. Paris (France). N80-23196 George Washington Univ.. Washington, D. C. NOISE GENERATION BY JET-ENGINE EXHAUST DEFLEC- SYNTHESIS OF A THEORETICAL APPROACH FOR TION EMPLOYING ADAPTIVE CONFIGURATION MANAGEMENT Burkhard Gehlar. Werner Dobrzynski. and Bernhard Fuhrken Jul. IN AERONAUTICAL WEAPON SYSTEM PROGRAMS 1979 50 p refs Transl into ENGLISH of "Schallerzung durch Ph.D. Thesis Triebwerksstrahl- Deflexion", Rept. DFVLR-FB-78-2 1, DFVLR, Angelo John DiMascio 1979 426 p Brunswick, Sep. 1978 Original report in GERMAN previously Avail: Univ. Microfilms Order No. 8008364 announced as X79-76750 A unified systems approach for managing aeronautical weapon (ESA-TT-553; DFVLR-FB-78-21) Avail: NTIS HC A03/MF AOl; system acquisition and life cycle support is discussed. The DFVLR. Cologne DM 23.30 proposed holistic model provides a structured framework for Noise radiation by jet engine exhaust-flow-interaction with integration of all of the technical and administrative elements blast deflectors is investigated by means of model-experiments associated with effective life cycle management. The primary of scale 0.1. The investigations pertain to a specific deflector integrative mechanism, which is used as the foundation module, configuration. Noise spectra and directivity characteristics for is an expanded configuration management discipline. An adaptive various power-settings and configuration changes are determined configuration baseline management concept, when logically and used for the prediction of noise generation by the full-scale combined with basic integrated logistics management and research configuration. The investigation shows that the particular and development processes by a tailored system engineering deflector gives rise to higher noise levels than those of the methodology, is required to mitigrate the acquisition and support corresponding engine noise alone when the distance between problems attendant to technology turnover. The adaptive exhaust nozzle and deflector is less than 10 nozzle-diameters. characteristics and the tailoring emphasis are required not only Author (ESA) to deal with the volatile state of technology but also to accommodate the continuously decreasing influence of the military markets on the components industries. N80-23106# National Aerospace Lab.. Amsterdam (Netherlands). Dissert. Abstr. Fluid Dynamics Div. ON THE SOUND FIELD GENERATED BY A FAN IN A N8023249* HARD-WALLED BAFFLED DUCT WITH UNIFORM FLOW National Aeronautics and Space Administration. J. N. Laan and J. B. H. M. Schulten 22 Feb. 1978 67 p Ames Research Center, Moffett Field, Calif. refs CONCEPTUAL STUDIES OF A LONG-RANGE TRANSPORT (Contracts NIVR'1773; NIVR-1821( WITH AN UPPER SURFACE BLOWING PROPULSIVE LIFT (NLR-TR-78024-U) Avail: NTIS HC A04/MF AOl SYSTEM A method to calculate the generation, transmission and John A. Cochrane May 1980 24 p radiation of fan noise is described. A steady uniform flow is (NASA-TM-81196: A-8169( Avail: NASA. Ames Res. Center, assumed in the whole field. A hard walled circular duct is Moffett Field, Calif. 94035 CSCL 01C considered which is terminated at the open end by an infinite The application of propulsive lift technology to the long baffle. It is shown that the source mechanism is the impingement range, heavy lift transport mission was studied. The level of of wakes from an upstream row giving rise to fluctuating blade propulsive lift technology studied was that which is represented forces: this force field drives the sound field. Author (ESA( by the Quiet Short-Haul Research Aircraft (QSRA). This technology uses the upper surface blowing technique )USB) to develop high lift coefficients. Results indicate that field lengths of less than N80-23142// Human Engineering Labs., Aberdeen Proving 3000 ft are feasible at landing gross weights and that even at Ground, Md. maximum takeoff gross weight, a reduction in field length is THE VERIFICATION OF A COMPUTER MODEL OF INTER- available as compared to a conventional aircraft. Further study NAL LIGHT REFLECTIONS FOR HELICOPTER CANOPY of the concept is recommended. J.M.S. DESIGN Final Report Christopher C. Smyth and Harry R. Stowell Oct. 1979 58 p N8023250*# National Aeronautics and Space Administration. refs Ames Research Center, Moffett Field, Calif. )AD-A080473; HEL-TM-2 1-79) Avail: NTIS LEEWARD FLOW OVER DELTA WINGS AT SUPERSONIC HC A04/MF AOl CSCL 01/3 SPEEDS The U.S. Army Human Engineering Laboratory (USAHEL( Joachim G. Szodruch Apr. 1980 49 p refs has experimentally verified a computer model for internal light (NASA-TM-81187; A-8117) Avail: NTIS HC A03/MF AOl reflections on the transparent surfaces of helicopter canopies. CSCL O1A The model was verified using a mockup of the Model 209 AH-1S A survey was made of the parameters affecting the Helicopter with the flat plate canopy design. The transmittance development of the leeward symmetric separated flow over slender and coordinates of the light images on the canopy surfaces delta wings immersed in a supersonic stream. The parameters were measured at various light source positions. A matched included Mach number, Reynolds number, angle of attack, sample was computed for the source positions using the computer leading-edge sweep angle, and body cross-sectional shape, such model. Pearson's correlation coefficients for a linear regression that subsonic and supersonic leading-edge flows are encountered. analysis of the matched measured and computed values are It was seen that the boundaries between the various flow regimes greater than 0.98, and the results are statistically significant at existing about the leeward surface may conveniently be repre- the .01 level. GRA sented on a diagram with the components of angle of attack and Mach number normal to the leading edge as governing parameters. R.E.S. N80-23146# Naval Ocean Systems Center, San Diego, Calif. EMP HARDENING OF AIRBORNE SYSTEMS THROUGH N8023251*# National Aeronautics and Space Administration. ELECTRO-OPTICAL TECHNIQUES DESIGN GUIDELINES Langley Research Center, Langley Station, Va. Technical Report. Apr. - Aug. 1979 A STUDY OF PANEL LOADS AND CENTERS OF PRESSURE R. A. Greenwell 15 Dec. 1979 55 p refs Sponsored by OF THREE DIFFERENT CRUCIFORM AFT-TAIL CONTROL Defense Nuclear Agency SURFACES OF A WINGLESS MISSILE FROM MACH 1.60 (AD-A080650; NOSC/TR-469) Avail: NTIS TO 3-70 HC A04/MF AOl CSCL 18/6 Milton Lamb and Charles D. Trescot. Jr. May 1980 112 p This report examines the utilization of fiber optics technology refs as an alternative to system EMP hardening and provides design (NASA-TM-81787; L-13501) Avail: NTIS HC A06/MF AOl guidelines for airborne system applications. It also examines CSCL O1A potential EMP vulnerabilities of the overall fiber optic data An investigation was made of the forces and moments on subsystems, defines and quantifies methods of protection against the cruciform aft-tail control surfaces of a wingless missile model the EMP threat, and compares vulnerabilities with those of to determine the variation of panel load and center of pressure hard-wired data systems. GRA with angle of attack, tail deflection, model roll angle. and Mach

358 N80-23259 number. Also, a limited force-moment and surface-pressure 125 p refs Investigation was made on a noncircular aft end. These investiga- (Contract F33165-77-C-3003; AF Proj. 2404) tions were made in a unitary plan wind tunnel at Mach numbers (AD-A08147 1; AFFDL-TR-79-3 128-Vol-1) Avail: NTIS of 1.60. 2.36. and 3.70 and at a Reynolds number per meter HC A06/MF AOl CSCL 20/4 of 6.600.000. The cruciform aft-tail results indicate very little This report documents a study to modify an existing computer variation in the center of pressure for the highly loaded windward program which provides an economical and easy to use analytic tail. The noncircular aft-end test results indicate no significant tool for aerodynamic heating to a wide variety of 3 dimensional effect of the fin unporting on the fin loads. R.E.S. vehicle configurations. This report also serves as a user's manual for the computer program plus two auxiliary programs written to analyze vehicle geometry, and presents program capabilities, input/output characteristics, and example problems. Core N8023252*# Georgia Inst. of Tech., Atlanta. School of requirements have been minimized by the use of overlays. User Aerospace Engineering. oriented features of the program include minimized input SURFACE PRESSURE MEASUREMENTS AT TWO TIPS OF requirements and various options for application flexibility. GRA A MODEL HELICOPTER ROTOR IN HOVER Final Report R. B Gray, H. M. McMahon, K. R. Shenoy, and M. L. Hammer May 1980 46 p refs N80-23256# Kaman Avidyne, Burlington. Mass. (Contract NAS1-15158; DA Proj. iLl -61 102-AH-45A( THE VIBRA-8 SUBSONIC AERODYNAMIC NUCLEAR GUST (NASA-CR-3281( Avail NTIS HC A03/MF AOl CSCL O1A VULNERABILITY CODE Final Report, Jul. 1978 - Feb. Surface pressures were measured near the tip of a hovering 1979 single-bladed model helicopter rotor with two tip shapes. The Garabed Zartarian 1 May 1979 23 p refs rotor had a constant-chord, untwisted blade with a square, flat (Contract DNA001-78-C-0317) tip which could be modified to a body-of-revolution tip. Pressure (AD-A081722: AD-E300674; KA-TR-164; DNA-4966F) Avail: measurements were made on the blade surface along the NTIS HC A02/MF AOl CSCL 20/4 chordwise direction at six radial stations outboard of the This report describes certain modifications to the subsonic 94 percent blade radius. Data for each blade tip configuration aerodynamic subroutine in the earlier versions of VI BRA to extend were taken at blade collective pitch angles of 0. 6.18 and the applicability of the nuclear vulnerability code over broader 11.4 degrees at a Reynolds number of 736,000 and a Mach ranges of Mach number, aspect ratio, and sweep angles. This number of 0.25 both based on tip speed. Chordwise pressure modified version, designated as VIBRA-8, was developed in distributions and constant surface pressure contours are presented conjunction with a study of the nuclear vulnerability of an and discussed. Author aeronautical system. A separate classified report has been issued to cover that study. GRA N8023253*# National Aeronautics and Space Administration, N80-23257# Avco Systems Div., Wilmington, Mass. Washington. D. C. HYPERSONIC HEAT TRANSFER TEST PROGRAM IN THE LEE SIDE FLOW FOR SLENDER DELTA WINGS OF FINITE VKI LONGSHOT FACILITY Final Report, 1 Dec. 1978 - THICKNESS 30 Nov. 1979 Joachim G. Szodruch Mar. 1980 161 p refs Trarisl. into Victor Dicristina 18 Dec. 1979 26 p ENGLISH of "Leeseiten-Stroemung Bel Schlanken DeltaFluegeln (Contract F49620-79-C-0013; AF Proj. 2307) eridlicher Dicke" Rept. ILR-23 Tech. Univ., Berlin, Inst. fuer (AD-AO81467: AVSD-0335-79-CR; K500-79-VD-32; Luft und Raumfahrt, 1977 150 p Trans. by Scientific Translation AFOSR-80-0124TR) Avail: NTIS HC A03/MF AOl CSCL Service. Santa Barbara. Calif. 20/13 (Contract NASw-3198) A summary of test results is presented for local pressure (NASA-TM-75753: ILR-23) Avail: NTIS HC A08/MF AOl and heat transfer distributions on a biconic body for a range of CSCL O1A hypersonic Mach numbers, Reynolds number, and angle-of-attack. An experimental and theoretical investigation carried out to The model configuration approximated nosetip contours typical determine the lee side flow field over delta wings at supersonic of low altitude turbulent ablated shapes. Instrumentation included speeds is presented. A theoretical method to described the flow a longitudinal row of ten pressure taps and, 180 degrees apart, field is described, where boundary conditions as a result of the a row of eleven smooth calorimeter discs. The tests were experimental study are needed. The computed flow field with performed in the Longshot Facility of the von Karman Institute shock induced separation is satisfactory. M.G. for Fluid Dynamics. GRA N80-23254# Nielsen Engineering and Research, Inc.. Mountain N80-23258# Boeing Military Airplane Development, Seattle. View, Calif. Wash. ACTIVE CONTROL OF ASYMMETRIC VORTEX EFFECTS EASY-AdS DYNAMIC ANALYSIS. USERS MANUAL Final Final Technical Report. 20 Apr. 1978 - 20 Dec. 1979 Report, 15 Apr. 1977 - 1 Jun. 1979 John E. Fiddler Dec. 1979 55 p refs M. K. Wahi, G. S. Duleba. and P. R. Perkins Wright-Patterson (Contract N60921-78-C-0073; WR02303003) AFB, Ohio AFFDL Sep. 1979 291 p refs (AD-A081648; NEAR .TR-212) Avail: NTIS HC A04/MF AOl (Contract F33615-77-C-3054; AF Proj. 2402) CSCL 20/4 )AD-A081160; AFFDL-TR-79-3106( Avail: NTIS Active control of asymmetric vortex effects on a pointed, HC A13/MF AOl CSCL 09/2 slender body at high angles of attack has been achieved by This report contains a summary description of the command rotating portions of the body about the axis. The lee side language used in the EASY dynamic analysis program. In addition, asymmetric vortex patterns and their associated yaw-plane forces a description of the inputs and outputs for each standard and moments have been varied in cyclic, repeatable fashion at component in the ACLS library is given. GRA rates up to 100 cycles per second. The variations occurred to rapidly that the average yaw-plane quantities were brought to N80-23259# Calspan Advanced Technology Center, Buffalo, small, steady values, or nulled out. The effect was obtained by N.Y. Aerodynamic Research Dept. rotating the nose, the nosetip and a band of the body surface ANALYSIS OF EXPERIMENTS ON THE EFFECTS OF JET just aft of the nose. GRA PLUMES ON PRESSURE DISTRIBUTION OVER A CYLIN- DRICAL AFTERBODY AT TRANSONIC SPEEDS Final N80-23255# McDonnell-Douglas Astronautics Co.. St. Louis, Report Mo. Joseph P. Nenni Feb. 1980 51 p refs NUMERICAL FLOW FIELD PROGRAM FOR AERODYNAMIC (Grant DAAG29-77-C-0008) HEATING ANALYSIS. VOLUME 1: EQUATIONS AND (AD-AO81 647; CALSPAN-AA-4017-W-16: ARO-13797.1-E) RESULTS Final Technical Report, Jun. 1977 - Sep. 1979 Avail: NTIS HC A04/MF AOl CSCL 21/8 H. J. Fivel Wright-Patterson AFB, Ohio AFFDL Dec. 1979 The objective of the present investigation was to obtain

359 N8O-23260 experimentally, the effects of various jet plume parameters on to an oscillating movement, is found to be particularly effective afterbody pressure distributions and to partially validate the Korst in minimizing the effects of the horizontal walls. Agreement modeling procedure. Analysis of the experimental results and between the theoretical and experimental results is comparable supplemental calculations made by the method of characteristics to that obtained from a wing or an aircraft model between the show that the approximate theory used by Korst gives a good results of flutter calculations and flutter measurements in a estimate of the plume shape for nozzle exit Mach number of wind tunnel. However, although phases coincide well, the test 2.0 and below. For nozzle exit Mach numbers much in excess amplitude are approximately 20 percent lower overall than the of 2.0, it appears desirable to include the effect of the nozzle theoretical amplitudes. Author (ESA) wall boundary layer on plume shape. In addition, afterbody pressure distributions produced by a series of nozzles designed to produce the same plume shape, but with different values of the plume N80-23267# European Space Agency. Paris (France). pliability parameter, have been compared with results from a PRESSURE DISTRIBUTION MEASUREMENTS ON WEDGES solid plume simulator. In general, the solid plume simulator AT SUBSONIC AND TRANSONIC VELOCITIES produces results that agree with the nozzles with the higher Mauri Tanner Nov. 1979 44 p refs Transl. into ENGLISH of values of the plume pliability parameter at zero degrees angle "Druckverteilungsmessungen an Keilen bei Unterschall- und of attack. The correlation deteriorates significantly, however, at Transschallgeschwindigkeiten". Rept. DFVLR-FB-78-22 DFVLR, five degrees angle of attack. Also, afterbody pressure distributions Cologne, Oct. 1978 Original report in GERMAN previously from model tests on the ZAP rocket motor are presented for announced as N79-30156 future correlation with prototype results. GRA (ESA-TT-554: DFVLR-FB-78-22( Avail: NTIS HC A03/MF AOl: ZLDI. Munich 19.70 N80-23260# McDonnell-Douglas Astronautics Co.. St. Louis, Measurements were performed in a wind tunnel on three Mo. wedges (apex angle of 8. 15. and 30 deg). Formulas are given NUMERICAL FLOW FIELD PROGRAM FOR AERODYNAMIC for calculating pressure distributions and other characteristics HEATING ANALYSIS. VOLUME 2: USER'S MANUAL Final associated with the wedge. Some comparisons are made with Technical Report, Jun. 1977 - Sep. 1979 theoretically expected results. The pressure distribution on the H. J. Fivel Wright-Patterson AFB. Ohio AFFDL Dec. 1979 wedge flank, the base pressure and the pressure drag vary 113 p refs Supersedes AFFDL-TR-79-3025 2 Vol. considerably with Mach number and wedge angle. Author )ESA) (Contract F33615-77-C-3003: AF Proj. 2404) (AD-A081472; AFFDL-TR-79-3 1 28-Vol-2; AFFDL-TR-79-3025) Avail: NTIS HC A06/MF AOl CSCL 20/4 N80-23268# European Space Agency, Paris (France). This report documents a study to modify an existing computer AFTERBODY DRAG AND BASE PRESSURE MEASURE- program which provides an economical and easy to use analytic MENTS ON A BODY OF REVOLUTION AT ANGLES OF tool for aerodynamic heating to a wide variety of 3 dimensional INCIDENCE UP TO ALPHA = 25 DEG AT SUBSONIC AND vehicle configurations. This report also serves as a user's manual TRANSONIC MACH NUMBERS for the computer program plus two auxiliary programs written Mauri Tanner Nov. 1979 70 p refs Transl. into ENGLISH of to analyze vehicle geometry, and presents program capabilities, Heckwiderstands- und Basisdruckmessungen an einem fluckoerp- input/output characteristics, and example problems. Core errumpf bei Anstellwinkeln bis Alphas = 25 deg im Unterschallund requirements have been minimized by the use of overlays. User Transschallbereicht", Rept. DFVLR-FB-78-14 DFVLR, Goettingen, oriented features of the program include minimized input West Germany, Jun. 1978 Original report in GERMAN previously requirements and various options for application flexibility. GRA announced as N79-30157 (ESA-TT-569. DFVLR-FB-78-14) Avail: NTIS HC A04/MF AOl: ZLDI, Munich DM 26,90 N80-23265# Deutsche Forschungs- und Versuchsanstalt fuer Base pressure and afterbody drag measurements were Luft- und Raumfahrt. Goettingen (West Germany). Inst. fuer performed in a wind tunnel. The Mach number had values from Theoretische Stroemungsmechanik. 0.5 to 1.0. the Reynolds number based on the model diameter LIFT. DRAG AND PITCHING MOMENT MEASUREMENTS was 340,000. Results show the influence of the boattail angle, ON A MISSILE BODY HAVING VARIOUS BOATTAILS AT the boattail length, and the relative base diameter on the base suBSoNic AND TRANSONIC VELOCITIES pressure and the afterbody drag at various angles of incidence. Mauri Tanner Mar. 1979 86 p refs In GERMAN: ENGLISH summary Report will also be announced as translation Author )ESA) (ESA-TT-628) (DFVLR-FB-79-15) Avail: NTIS HC A05/MF AOl; DFVLR, N80-23269// European Space Agency. Paris (France). Cologne DM 13.60 ON DISTURBANCE FIELDS OF MOVING SINGULARITIES The lift, drag, and pitching moment of a missile body with IN AERODYNAMICS AND AEROACOUSTICS boattailing were measured at Mach numbers from 0.5 to 1.0 at Arabino Das Dec. 1979 90 p refs Transl. into ENGLISH of a fleynolds number of 340.000 in a transonic wind tunnel. Lift, "Ueber Stoerfelder Bewegter Singularitaeten in der Aerodynam- sche und Aeroakustik", Rept. DFVLR-FB-78-16 DFVLR, drag, and longitudinal stability of the body was "found to decrease Brunswick, May 1978 Original report in GERMAN previously when the relative base diameter decreased. Author (ESA) announced as N79-301 58 (ESA-TT-570: DFVLR-FB-78-16( Avail: NTIS HC A05/MF AOl: ZLDI, Munich DM 38.10 N80-23266# Rolls-Royce Ltd.. Derby (England). A unified method is presented in which arbitrary translatory UNSTEADY AERODYNAMIC FORCES ON A SUBSONIC motions of the disturbance sources. of the medium, and of the RECTILINEAR CASCADE OF BLADES field point are admitted. The influence factors which arise from H. Loiseau and J. Nicolas 1979 28 p refs Transl. into the kinematics of the disturbance field are derived and the physical ENGLISH of conf. paper "Forces Aerodynamiques Instationnaires processes involved are elucidated. The significance of the Lorentz en Grille Rectiligne d'Aubes Subsonique" ONERA, Paris, Oct. transformation in problems of disturbance propagation from 1976 In ENGLISH and FRENCH Presented at the RFM Symp., moving singularities is discussed. An evaluation of energy Paris, Oct. 1976 p 105-114 density and energy flux in disturbance fields is presented. (PNR-90007: Trans-14737( Avail: NTIS HC A03/MF AOl Author (ESA) Tests performed on Pfenniger- Sulzer airfoils and NACA 65 A 006 airfoils, singly and in cascades in a subsonic wind tunnel to investigate aeroelastic phenomena in gas turbines N80-23270# European Space Aency. Paris (France). are discussed. The simultaneous use of two measurement methods THE HARMONICALLY OSCILLATING BODY IN SUBSONIC (forces extended from the variation in natural frequency and the FLOW: EFFECT OF COMPRESSIBILITY damping of the rotating blade, and from pressures) is a certain Wolfgang Geissler Nov. 1979 42 p refs Transl. into ENGLISH means of checking the quality of the measurements. The choice of "Der Harmonisch Schwingende Rumpf in Unterschallstroemung: of a vibrating configuration, where only one blade is subjected Einfluss der Kompressibilitaet", Rept. DFVLR-FB-78-24 DFVLR.

360 N80-23282

Goettingen, West Germany, Nov. 1978 Original report in to assess the forces likely to be encountered on the canopy GERMAN previously announced as N79-30160 hatches are reported. Author )ESA) (ESA-TT-584; DFVLRFB-78-24) Avail: NTIS NC A03/MF AOl: ZLDI, Munich DM 2020 N80-23278# Crew Systems Consultants, Yellow Springs, Ohio. The calculation of steady and unsteady airloads on harmonic- CARBURETOR ICE: A REVIEW ally oscillation bodies can be done by means of source and sink Richard L Newman 1980 97 p refs Backup document for distributions on the real body surface. It is useful to do the AIAA Synoptic. 'Carburetor ice flight testing: The use of an calculation in a body fixed frame of reference. Pressures and anti-icing fuel additive', scheduled for publication in Journal of forces on oscillating bodies were obtained for incompressible Aircraft in Oct. or Nov. 1980 flow. The extension of this method to compressible subsonic Avail: NTIS HC A05/MF AOl flow is discussed. Numerical results are compared with other Carburetor ice formation, a cause of engine failure and available methods for steady and unsteady flow about bodies. resultant aircraft accidents, is investigated. Prevention techniques Author (ESA) include antiicing fuel additives, such as ethylene glycol monomethyl ether, deicing procedures, pilot education, and engine N80-23273// National Aerospace Lab.. Amsterdam (Netherlands). design. Fluid Dynamics Div. SUMMARY OF DATA REQUIRED FOR THE AGARD SMP ACTIVITY STANDARD AEROELASTIC CONFIGURA- N80-23279# Crew Systems Consultants. Yellow Springs. Ohio. TIONS - TWO-DIMENSIONAL. CONFIGURATIONS CARBURETOR ICE: A REVIEW R. J. Zwaan 30 Apr. 1979 26 p refs Richard L Newman In its Carburetor Ice 1980 56 p refs (NLR-MP-79015-U) Avail: NTIS NC A03/MF AOl For the current AGARD structures and material panel (SMP) (TR-79-9) Avail: NTIS HC A05/MF AOl activity Standard Aeroelastic Configurations two airfoils were The effectiveness of 0.15 percent by volume of ethylene proposed for use in comparative calculations, one of which is glycol monomethyl ether as an antiicing fuel additive was the NLR 7301 airfoil. To facilitate reference to definitions of investigated in-flight using a PA-23 airplane equipped with airfoil geometry and aerodynamic conditions and to experimental 0-320-A engines. Topics addressed include establishment of values, all relevant data are presented. Author )ESA) environmental conditions over which the carburetor is likely to form ice, rate of ice formation, and effectiveness of procedures for deicing a carburetor. The maximum amount of icing that N80-23274# Bristol Univ. (England). can be safely tolerated was estimated. AN AEROELASTIC ANALYSIS OF THE SHERIFF WING E.D.K. B.S. Thesis N80-23280# Crew Systems Consultants, Yellow Springs, Ohio. A. K. Fuan Jun. 1979 40 p refs CARBURETOR ICE: A REVIEW (BU-234( Avail: NTIS HC A03/MF AOl Richard L Newman In its The aeroelastic behavior of the Sheriff wing, particularly the Carburetor Ice 1980 41 p refs aileron dependent flutter characteristics was analyzed with the (TR-77-19) Avail: NTIS HC A05/MF AOl intention of minimizing the mass balance weight. Results are Records of aviation accidents due to carburetor icing are presented for wind divergence speed and control surface reversal. reviewed. Carburetor ice research, including formation and The mass and stiffness matrices and the associated eigenvalues prevention techniques, is discussed. Possible solutions are and eigenvectors are discussed. Author (ESA) presented with emphasis on fuel additives and a pilot education program. E.D.K. N80-23276# Bristol Univ. (England). Dept. of Aeronautical Engineering. N80-23281# Mitre Corp.. Mclean, Va. AN ASSESSMENT OF THE STABILITY AND OPENING OPPORTUNITIES ANALYSIS OF POTENTIAL ADVANCED CHARACTERISTICS OF CRUCIFORM PARACHUTES VORTEX SYSTEMS SEPARATION STANDARDS B.S. Thesis Dana L Hall and Frank A. Amodeo Jul. 1979 73 p refs M. D. Copcutt and P. L. Denner Jun. 1979 53 p ref (Contract DOT-FA79WA-4 184) (BU-238( Avail: NTIS NC A04/MF AOl (AD-AO81479; MTR-79W00073; FAA-EM-79-17) Avail: NTIS The stability of cruciform parachutes and the measurement HC A04/MF AOl CSCL 01/2 of the forces which occurred during the inflationary phase were The benefits associated with conceptual Advanced Vortex investigated. A number of cruciform parachutes, with arm ratios Systems (AVS) are quantified from a delay reduction viewpoint. varying from 2 : 1 to 5 : 1, were constructed. Stability tests The findings are equally applicable to airborne vortex alleviation were performed by attaching the parachutes to a fixed point technology or to ground or air-based vortex avoidance systems. and observing their behavior in a wind tunnel. Force measurements The delay consequences of three sets of successively closer were obtained by the horizontal deployment of the parachutes interarrival standards are compared against the option of on a restraining cable. Cruciform parachutes were found to be maintaining today's rules or a combination of today's and 3 nmi more laterally stable than flat circular parachutes but they exhibit separations. The analysis was performed for only IFR weather a spinning instability. Results indicate that the most promising conditions, since minimum required separation standards were arm ratios for parachute design are between two and a half to selected as representative of possible AVS capabilities. Substantial one and four to one. Author (ESA) delay savings are shown to be possible even with demand growth below that projected to occur across the 1985 through 1995 analysis time period. The benefits are sufficiently large as N80-23277# Bristol Univ. (England). Dept. of Aeronautical to warrant a substantial research and development investment Engineering. into an AVS program. A.R.H. WIND TUNNEL TESTS ON THE SHERIFF TWIN-ENGINED LIGHT AIRCRAFT B.S. Thesis N80.23282*# National Aeronautics and Space Administration. K. M. R. Walsh and S. Watkins Jun. 1979 76 p refs Langley Research Center. Langley Station, Va. )BU-241) Avail: NTIS HC A05/MF AOl STORM HAZARDS '79: 0-10613 OPERATIONS SUMMARY The aerodynamics of the Sheriff twin-engined light aircraft Bruce D. Fisher, Gerald L. Keyser, Jr., Perry L. Deal, Mitchel E. were examined. Flow visualization experiments which gave Thomas, and Felix L. Pitts Mar. 1980 64 p refs evidence of a premature stall arising on the wing section between )NASA-TM-81779) Avail: NTIS HC A04/MF AOl CSCL the nacelle and fuselage are described. A search for improvement 01C was made using various high lift leading edge devices, fillets, Preliminary flight tests with a F-106B aircraft were made and changes of nacelle geometry. Improved aerodynamic on the periphery of isolated thunder cells using weather radar performance in the Sheriff by adopting pointed tail nacelles, leading support. In addition to storm hazards correlation research, a edge cusps on the wing inboard of the nacelles, and fairings on direct-strike lightning measurement experiment and an atmo- the wing/fuselage junctions is discussed. Pressure readings taken spheric chemistry experiment were conducted. Two flights were

361 N80-23283 made to close proximity to lightning generating cumulonimbus described. The replacement of the IBM 9020 computer with an clouds; however, no direct lightning strikes were experienced. instruction-compatible computer system is also discussed. The Although no discernible lightning transients were recorded, many required changes and predicted central processing unit and operational techniques were identified and established. R.E.S. intersystem channel loading for each functional split are presented and implementation cost estimates provided. M.G. N8O23283*# National Aeronautics and Space Administration. N80-23287# Mitre Corp., McLean, Va. Metrek Div. Langley Research Center, Langley Station, Va. PROCEDURAL FEASIBILITY OF REDUCED SPACING OUTLOOK FOR ADVANCED CONCEPTS IN TRANSPORT UNDER WVAS OPERATION WITH APPLICATIONS TO AIRCRAFT ATLANTA AND OHARE D. William Conner Apr. 1980 21 p refs Presented at the 1980 Intern. Air Transportation Meeting, Cincinnati, 20-22 May Ronald G. Gados and Frank A. Amodeo Washington, D.C. FAA 1980 Aug. 1979 64 p refs (NASA-TM-81810: SAE-TP-800744) Avail: NTIS (Contract DOT-FA79WA-4 184) HC A02/MF AOl CSCLO1C )AD-A081480; MTR-79W00243; FAA-EM-79-18( Avail: NTIS Air transportation demand trends, air transportation system HC A04/MF AOl CSCL 01/2 goats, and air transportation system trends well into the 21st A Wake Vortex Avoidance System )WVAS) may provide century were examined in detail. The outlook is for continued increased airport capacity by allowing for reduced aircraft growth in both air passenger travel and air freight movements. separation standards on final approach under certain meteorologi- The present system, with some improvements, is expected to cal conditions. Three sets of reduced separation standards were continue to the turn of the century and to utilize technologically hypothesized in order to describe the operational characteristics upgraded, derivative versions of today's aircraft, plus possibly of potential WVAS systems. The analyses developed several some new aircraft for supersonic long haul, short haul, and high operational schemes which allow aircraft to transition to density commuter service. Severe constraints of the system, reduced separation standards when under WVAS coverage, while expected by early in the 21st century, should lead to innovations maintaining larger terminal area standards prior to intercepting at the airport, away from the airport, and in the air. The innovations that coverage. Specific applications of these schemes to Atlanta are illustrated by descriptions of three candidate systems involving Hartsfield and Chicago O'Hare International Airports are described. advanced aircraft concepts. Advanced technologies and vehicles Procedures for and dynamics of transitioning between different expected to impact the airport are illustrated by descriptions of sets of separation standards were investigated. Capacity laminar flow control aircraft, very large air freighters and benefits corresponding to the utilization of the different sets of R.E.S. separation standards under various operational procedures are cryogenically fueled transports. estimated for Chicago and Atlanta. R.E.S. HBO-23284# National Aerospace Lab.. Amsterdam (Netherlands). N80-23288# National Aviation Facilities Experimental Center. Structures Materials Dept. Atlantic City, N. J. FAILURE ANALYSIS IN AVIATION A FLIGHT INVESTIGATION OF SYSTEM ACCURACIES AND E. A. B. deGraaf 14 Aug. 1978 48 p refs In DUTCH; OPERATIONAL CAPABILITIES OF A GENERAL AVIATION! ENGLISH summary AIR TRANSPORT AREA NAVIGATION SYSTEM (RR3AV) (NLR-MP-78028-U) Avail: NTIS HC A03/MF AOl Final Report, Nov. 1977 - Mar. 1979 The role of service failure analysis in defining new inspection Jack Edmonds, John Gallagher. and Robert Pursel Feb. 1980 procedures and the adoption of existing ones is illustrated. 104 p Examples include failures detected during inspections prescribed (FAA Proj. 975.310-001) by the manufacturer, failures discovered after having learned of (AD-A08 1646; FAA-NA-79-25) Avail: NTIS problems experienced by other operators of the same type of HC A06/MF AOl CSCL 17/7 aircraft, and those found after an accident or by chance. Flight tests were conducted using a general aviation/air Author (ESA) transport type area navigation system (RNAV( to investigation area navigation system accuracies and resultant airspace N80-23285# National Aerospace Lab.. Amsterdam (Netherlands). requirements. The system used very high frequency omni- Structures and Materials Dept. directional radio/distance measuring equipment )VOR/ DM El radio THE FAILURE OF AIRCRAFT STRUCTURES data for position determination. Data and operational capabilities E. A. B. deGraaf 6 Dec. 1978 36 p refs In DUTCH; ENGLISH were also investigated, and graphical data are presented for parallel summary Presented at Bondsdag-Bond van Materialenkennis. offsets, delay fans, and turn anticipation. Author Wageningen, Netherlands, 10 Nov. 1978 (NLR-MP-78040-U) Avail: NTIS HC A03/MF AOl N80-23293# Air Force Packaging Evaluation Agency, Wright- A general discussion of aircraft structural failures and the Patterson AFB, Ohio. design measures taken to prevent them are presented. Methods IMPROVED PACKAGING FOR THE LN-31 INERTIAL for determining static strength and stiffness, loads, and fatigue MEASUREMENT UNIT IF-15 AIRCRAFT) strength are surveyed. Modern design philosophies which take Frank C. Jarvis Mar. 1980 14 p into account the possibility of initial defects, from which fatigue (AD-AO81745; PTPT-80-2) Avail; NTIS HC A02/MF AOl damage could originate are considered. Examples of structural CSCL 17/7 failure are given and discussed. Author (ESA) The investigation of the current packaging for the F-15 Inertial Measurement Unit ( LN-3 1 IMU) revealed that the pack will provide N80-23288# Logicon, Inc., San Pedro, Calif. adequate shock and vibration protection for the item; however, SOFTWARE IMPACT OF SELECTED EN ROUTE ATC it was anticipated that a less expensive pack could be developed COMPUTER REPLACEMENT STRATEGIES Final Report at a cost savings of approximately 25% (PTPT Report 79-3, W. D. Kandler. D. Weeton, and W. B. Cushing Dec. 1979 Packaging and Handling Analysis of the LN-31, 683420-14. 98 p refs Inertial Measurement Unit). A new improved pack was developed (Contract DOT-FA79WA-4313) and evaluated. The estimated cost savings is 20% and the potential )AD-A081478; FAA-EM-79-15: .Rept-7941 -03) Avail: NTIS implementation date is scheduled for June 1980. GRA HC A05/MF AOl CSCL 17/7 The impacts and software constraints associated with N80-232955 National Aeronautics and Space Administration. transitioning to an en route air traffic control system are examined. Ames Research Center, Moffett Field, Calif. The functional splitting of existing major system functions (flight OPERATIONS MANUAL: VERTICAL MOTION SIMULATOR data processing and radar data processing) and the implementation (VMS) S.08 of system enhancements (en route minimum safe altitude warning A. David Jones May 1980 70 p and flight plan conflict probe) in a new computer system attached (NASA-TM-81180: A-8095) Avail: Issuing Activity CSCI. to the existing IBM 9020 system via a selector channel are 14B

362 N80-23303

The Ames Research Center Vertical Motion Simulator (VMS) GERMAN; ENGLISH summary Report will also be announced is described in terms useful to the researcher who intends to as translation (ESA-TT-631) use it. A description of the VMS and its performance are presented (DFVLR-FB-79-20( Avail: NTIS HC A04/MF AOl; DFVLR, together with the administrative policies governing its operation. Cologne DM 11.50 The management controls over its use are detailed, including The effects of wind shear on the arrested landing of data requirements, user responsibilities, and scheduling proce- conventional and short take off aircraft were calculated. The dures. This information is given in a form that should facilitate aircraft trajectory during the landing maneuver is given in communication with the NASA operations group during initial analytical form as a function of wind speed and pilot aircraft simulator use. J.M.S. controls. Various examples are used to illustrate the effect, resulting in specific recommendations for pilot control during N80-23296 Stanford Univ., Calif. the aircraft landing. Author (ESA) ESTIMATION OF WIND SHEAR AND THRUST LOSS DURING STOL AIRCRAFT LANDING APPROACH N80-23300# European Space Agency. Paris (France). Ph.D. Thesis INVESTIGATIONS OF THE DESIGN OF ACTIVE VIBRATION Joseph Andrew Bossi 1980 125 p ISOLATION SYSTEMS FOR HELICOPTERS WITH RIGID Avail: Univ. Microfilms Order No. 8011611 AND ELASTIC MODELING OF THE FUSELAGE Techniques for designing constant gain estimators when Gerd Schulz Nov. 1979 66 p refs Transl. into ENGLISH of uncertainties are present in the dynamic model were investigated. "Untersuchungen zur Auslegung von Vollaktiven Schwingungsisol- Modification of the steady state Kalman filter are described which ationssystemen fuer Hubschrauber bei Starrer und Elastischer provides a satisfactory estimator in such cases. Also, methods Zellenmodellierung". Rept. DFVLR-FB-78-04 DFVLR, Oberpfaf- for predicting the performance sensitivity of estimator designs fenhofen, West Germany Original report in GERMAN previously are described. The results of applying these techniques to the announced as N79-30183 design of an estimator for wind shear and thrust loss on a (ESA-U-556; DFVLR-FB-78-04) Avail: NTIS HC A04/MF AOl; STOL aircraft are presented. Estimator performance was verified ZLDI, Munich DM 25,70 . -- using a digital flight simulation of the aircraft on final approach. Different methods for the design of controllers for active Dissert. Abstr. vibration isolation on helicopters are investigated. Based on the special structure of the controller, compensation for the rotor N80-23297 Princeton Univ., N. J. blade harmonic disturbance vibrations is achieved, guaranteeing AN ANALYTICAL STUDY OF TILT PROPROTOR AIRCRAFT good trim behavior during maneuvers. For the first controller DYNAMICS IN AIRPLANE CRUISE CONFIGURATION design, done for a rigid helicopter fuselage with a modified Riccati INCLUDING THE EFFECTS OF FUSELAGE LONGITUDINAL design, different sensor configurations are investigated. A RIGID BODY MOTION Ph.D. Thesis possibility for sensitivity reduction for rotor speed variations is Tatsuo Komatsuzaki 1980 430 p shown. For the second ccntroller design for an elastic helicopter Avail: Univ. Microfilms Order No. 8011032 fuselage the modified Riccati design, the design by means of The dynamics of tilt proprotor aircraft in symmetric motion Nyquist plots and pole assignment are investigated, especially in airplane cruise configuration were examined with the effects with respect to the applicability for higher order systems. of the fuselage longitudinal rigid body motion included. The Author (ESA) reference values of the physical parameters were mainly based on those of the Bell XV-15, a tilt rotor research aircraft. The N80-23301# Office National d'Etudes et de Recherches influence of the fuselage motion on the aeroelastic stability of Aerospatiales. Paris (France). the proprotor/wing system was investigated, as well as the FLIGHT SAFETY OF ROGALLO HANG GLIDERS. THEORETI- influence of the proprotor/wing system dynamics on the stability CAL AND EXPERIMENTAL STUDY OF THE FLIGHT and control characteristics of the vehicle. In addition, the effects ENVELOPE of various feedbacks were examined with particular emphasis Claudius LaBurthe and Simone Walden 1979 227 p refs In placed upon the feasibility of using relatively simple feedbacks FRENCH; ENGLISH summary Report will also be announced to improve the dynamic stability characteristics of the proprotor/ as translation (ESA-TT-634) wing system. Prior to investigating the dynamics of the com- (ONERA-NT-1979-8) Avail: NTIS HC Al 1/MF AOl plete system, the dynamics of simplified models with reduced Two series of full scale wind tunnel tests were completed number of motion degrees of freedom was examined in some on 15 hang gliders. The results were used to calculate the basic detail in order to obtain physical insights into the dynamics of performance and stability characteristics and to analyze the critical the more complex system. Dissert. Abstr. limitations. The problem of pitching stability is highlighted in the analysis. Implications of the results in areas such as take N80-23298# Decisions and Designs. Inc.. McLean. Va. off, stall, dives, and settings are discussed. Author (ESA) DECISION ANALYSIS OF ADVANCED SCOUT HELICOPTER CANDIDATES Final Technical Report N80-23302# Bristol Univ. (England). Dept. of Aeronautical Michael L. Donnell and Jacob W. Ulvila Jan. 1980 98 p ref Engineering. Contract DAAK50-79-C-0035) INVESTIGATION OF A FOAM SUPPORTED GLASS FIBER. (AD-A081483; PR-80-1-307) Avail: NTIS HC A05/MF AOl D-BOX FOR A RIGID WING HANG GLIDER B.S. Thesis CSCL 01/3 N. A. Ruddick Jun. 1979 22 p refs An analysis is described for thirteen Advanced Scout (BU-240( Avail: NTIS HC A02/MF AOl Helicopter (ASH) candidates and mixtures of those candidates. A proposed design for a foam supported, glass fiber covered The analysis evaluates the candidates on the basis of their military D-box for use as a wing primary structure in a rigid wing hang worth; life cycle costs; attainability; force structure personnel glider is investigated. An arrangement for bracing the wing was impact; and rationalization. standardization and interoperability analyzed and the performance of the structure in bending was impact. The major portion of the report describes and explains verified. The stability of the D-box walls in torsion was investig- the methodology used to evaluate the candidates, presents the Author (ESA) results of the analysis, and illustrates several of the sensitivity ated. analyses that were performed. Detailed assessments used in the analysis are reported in the appendices. GRA N80-23303# Advisory Group for Aerospace Research and Development, Neuilly- Sur- Seine (France). THE IMPACT OF GLOBAL POSITIONING SYSTEM ON N80-23299# Deutsche Forschungs- und Versuchsanstalt fuer GUIDANCE AND CONTROLS SYSTEMS DESIGN OF Luft- und Raumfahrt, Brunswick (West Germany). Inst. fuer MILITARY AIRCRAFT. VOLUME 2A: SPECIFIC APPLICA- Flugmechanik. TION STUDY NO. 1. CLOSE AIR SUPPORT INVESTIGATION OF LANDING FLARE IN PRESENCE OF Louis J. Urban, ed. (ASD( Feb. 1980 70 p WIND SHEAR (AGARD-AR- 1 47-VoI-2A: ISBN-92-835-1349-5) Avail: NTIS Knut Wilhelm and Martin Marchand Jun. 1979 55 p refs In HC A04/MF AOl

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The application of NAVSTAR/Global Positioning System to Ph.D. Thesis Close Air Support is described. A currently available model Edgar Perrin Bruce 1979 250 p was selected, namely the F-4E aircraft equipped with the Avail: Univ. Microfilms Order No. 8010028 ARN-101 weapon delivery system. This was selected since it An existing two dimensional, nonviscous theory which represents the current state-of-the-art for externally aided (LORAN) employed a simplified vortex model in conjunction with the digital avionics system integrated into a reasonably modern fighter assumptions of thin airfoil theory to define cascade unsteady lift aircraft which is currently in the operational inventory of several was modified and extended to include an expression for unsteady NATO countries. R.E.S. pitching moment. Computed theoretical results were compared with measured values of unsteady lift force and pitching moment N80.23304*# National Aeronautics and Space Administration. coefficients and their phase angles and with the unsteady Hugh L. Dryden Flight Research Center. Edwards, Calif. center-Of-pressure position. In a large axial flow fan test facility. WIND TUNNEL INVESTIGATION OF AN ALL FLUSH specially designed screens were employed to produce a variety ORIFICE AIR DATA SYSTEM FOR A LARGE SUBSONIC of rotor inlet flows having a sinusoidally varying axial velocity AIRCRAFT component. Uncambered rotor response during operation in these Terry J. Larson, Stuart G. Flechner. and Paul M. Siemers. Ill harmonically varying inflows was determined by employing a May 1980 97 p refs strain-gaged sensing element on one rotor blade. The results (NASA-TP-1642; H-1085) Avail: NTIS HC A05/MF AOl CSCL show that, in general, the theory tends to overpredict the 01D magnitude of the force and moment coefficients, that good The results of a wind tunnel investigation on an all flush agreement exists between the majority of the measured and orifice air data system for use on a KC- 1 35A aircraft are presented. predicted phase angle data, and that the validity of the theory The investigation was performed to determine the applicability in its present form should be restricted to values of reduced of fixed all flush orifice air data systems that use Only aircraft frequency greater than 0.8. Dissert. Abstr. surfaces for orifices on the nose of the model (in a configuration similar to that of the shuttle entry air data system) provided N8023309*# General Electric Co.. Cincinnati, Ohio. the measurements required for the determination of stagnation CF6 JET ENGINE PERFORMANCE IMPROVEMENT: NEW pressure, angle of attack, and angle of sideslip. For the FAN measurement of static pressure, additional flush orifices in W. A. Fasching May 1980 202 p positions on the sides of the fuselage corresponding to those in (Contract NAS3-20629) a standard pitot-static system were required. An acceptable but (NASA-CR . 159699: R79AEG41 3) Avail: NTIS less accurate system, consisting of orifices only on the nose of HC A10/MF AOl CSCL 21E the model, is defined and discussed. R.E.S. As part of the NASA sponsored engine component improvement program, and fan package was developed to reduce fuel consumption in current CF6 turbofan aircraft engine. The new N80-23305// Douglas Aircraft Co.. Inc.. Long Beach, Calif. fan package consist of an improved fan blade, reduced fan tip FLIGHTTEST EVALUATION OF AIRBORNE TIRE PRESSURE clearance due to a fan case stiffener, and a smooth fan casing INDICATING SYSTEMS Final Report, Oct. 1978 - Aug. tip shroud. CF6 engine performance and acoustic tests demon- 1979 strated the predicted 1.8% improvement in cruise sfc without Ronald L. Suiter and Wilson W. Kwong Sep. 1979 114 p an increase in engine noise. Power management thrust/fan speed (Contract DOT-FA77WA-4070) characteristics were defined. Mechanical and structural integrity (AD-A081598: FAA-RD-78-134-2) Avail: NTIS was demonstrated in model fan rotor photoelastic stress tests, HC A06/MF AOl full-size fan blade bench fatigue tests, and CF6 engine bird Six different cockpit tire pressure indicating systems were ingestion, crosswind, and cyclic endurance tests. The fan was flight tested on two DC-10 aircraft: a seventh was tested on a certified in the CF6-500c2/E2 engines and is in commerical DC-9. The systems evaluated include three analog tire pressure service on the Boeing 747-200, Douglas DC-10-30. and Atrbus system concepts displaying actual tire pressure in the cockpit, industrie A300B aircraft. A.R.H. two weight and balance systems measuring tire pressure indirectly via tire load and axle tilt, a go-no-go discrete pressure sensing N8023311*# Hamilton Standard, Windsor Locks, Conn. system, and a wheel speed system that uses change in rolling ACOUSTIC TEST AND ANALYSES OF THREE ADVANCED radius to detect a low tire. A test evaluation for each of the TURBOPROP MODELS Final Report systems and comments on the general merits of each system Bennett M. Brooks and F. B. Metzger Jan. 1980 245 p refs type are included. A recommendation is made that each system (Contract NAS3-2061411 be subjected to airline service tests before entering fleet (NASA-CR-159667) Avail: NTIS HC A11/MF AOl CSCL service. . A.R.H. 21E Results of acoustic tests of theree 62.2 cm (24.5 inch) N80-23306# McDonnell-Douglas Electronics Co.. St. Charles, diameter models of the prop-fan (a small diameter, highly loaded. Mo. Multi-bladed variable pitch advanced turboprop) are presented. VISUALLY COUPLED SYSTEM: COMPUTER GENERATED Results show that there is little difference in the noise produced IMAGERY (VCS-CGI) ENGINEERING INTERFACE Final by unswept and slightly swept designs. However, the model Report. Aug. 1977 - Mar. 1979 designed for noise reduction produces substantially less noise at Shelton MacLeod and David B. Coblitz Wright-Patterson AFB, test conditions simulating 0.8 Mach number cruise speed or at conditions simulating takeoff and landing. In the near field at Ohio AMRL Nov. 1979 71 p refs (Contract F33615-77-C-0524; AF Proj. 7184) cruise conditions the acoustically designed. In the far field at (AD-A080931; AMRL-TR-79-32) Avail: NTIS takeoff and landing conditions the acoustically designed model HC A04/MF AOl CSCL 14/2 is 5 db quieter than unswept or slightly swept designs. Correlation The Visually-Coupled System Computer-Generated Imagery between noise measurement and theoretical predictions as well (VCS-CGI( Interface program had two main phases. The objective as comparisons between measured and predicted acoustic for the first phase was to successfully interface the various pressure pulses generated by the prop-fan blades are discussed. subcomponents (helmet-mounted sight, helmet-mounted displays, The general characteristics of the pulses are predicted. Shadow- and advanced computer-generated image system) and demon- graph measurements were obtained which showed the location strate their compatibility and feasibility for use in wide field of of bow and trailing waves. R.C.T. view, air-to-ground visual simulation. The objective for the second phase was to conduct a systematic exploration and evaluation N8023312*# Pratt and Whitney Aircraft Group, East Hartford, of various system parameters that could affect display quality. Conn. G RA CORE COMPRESSOR EXIT STAGE STUDY, 2 Final Report R. F. Behlke, E. A. Burdsall, E. Canal. Jr., and N. D. Korn Oct. N80-23308 Pennsylvania State Univ., University Park. 1979 90 p refs AXIAL FLOW ROTOR UNSTEADY PERFORMANCE (Contract NAS3-20578)

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(NASA-CR- 159812; PWA-556 1 -66( Avail: NTIS Studies conducted as part of the NASA-Lewis CF6 jet NC A05/MF AOl CSCL 21E engine diagnostics program are summarized. An 82-engine sample A total of two three-stage compressors were designed and of DC-10-10 aircraft engine checkout data that were gathered tested to determine the effects of aspect ratio on compressor to define the extent and magnitude of CF6-6D short term performance. The first compressor was designed with an aspect performance deterioration were analyzed. These data are ratio of 081; the other, with an aspect ratio of 1.22. Both substantiated by the performance testing and analytical teardown compressors had a hub-tip ratio of 0.915, representative of the of CF6-6D short term deterioration engine serial number (ESN( rear stages of a core compressor, and both were designed to 451507. R.C.T. achieve a 15.0% surge margin at design pressure ratios of 1.357 and 1.324. respectively, at a mean wheel speed of N8O23317*// National Aeronautics and Space Administration. 167 rn/sec. At design speed the 0.81 aspect ratio compressor Ames Research Center, Moffett Field. Calif. achieved a pressure ratio of 1.346 at a corrected flow of STATIC CALIBRATION OF A TWO-DIMENSIONAL WEDGE 4.28 kg/sec and an adiabatic efficiency of 86.1%. The 1.22 NOZZLE WITH THRUST VECTORING AND SPANWISE aspect ratio design achieved a pressure ratio of 1.314 at 4.35 BLOWING kg/sec flow and 87.0% adiabatic efficiency. Surge margin to Michael J. Harris (Naval Ship Research and Development Center, peak efficiency was 24.0% with the lower aspect ratio blading, Bethesda. Md.) and Michael D. Falarski Apr. 1980 38 p refs compared with 12.4% with the higher aspect ratio blading. (NA5A-TM-81161; A-8043) Avail: NTIS HC A03/MF AOl ACT. CSCL 21E The results of a static calibration of the two dimensional N8023313*# National Aeronautics and Space Administration. Lewis Research Center, Cleveland, Ohio. wedge nozzles on a STOL configuration of a large-scale fighter DEVELOPMENT OF IMPROVED-DURABILITY PLASMA model are reported. These nozzles internally turn the efflux SPRAYED CERAMIC COATINGS FOR GAS TURBINE produced by two turbojets down 25 degrees and exhaust it ENGINES over the deflected trailing edge of the wing. This arrangement Irving E. Sumner and Duane L. Ruckle (Pratt and Whitney Aircraft, provides direct thrust lift, enhances wing lift by producting supercirculation, and provides thrust vectoring by varying the East Hartford, Conn.) 1980 25 p refs Proposed for presentation at the 16th Joint Propulsion Conf., Hartford, 30 Jun. - 2 Jul. deflection of the wing's trailing edge. The thrust is vectored 1980: sponsored by AIAA. ASME and SAE from 10 deg to 38 deg. This system was calibrated with spanwise (NASA-TM-81512; E-451) Avail: NTIS HC A02/MF AOl CSCL blowing for augmentation of the leading-edge vortex. When 16% 21E - of the turbojet efflux is blown spanwise. the thrust recovered is As part of a NASA program to reduce fuel consumption of 92% of the thrust produced when the total efflux is exhausted current commercial aircraft engines, methods were investigated longitudinally. E.D.K. for improving the durability of plasma sprayed ceramic coatings for use on vane platforms in the JT9D turbofan engine. Increased N80-23319# Naval Postgraduate School, Monterey, Calif. durability concepts under evaluation include use of improved A PRIMITIVE VARIABLE COMPUTER MODEL FOR strain tolerant microstructures and control of the substrate COMBUSTION WITHIN SOLID FUEL RAMJETS Final temperature during coating application. Initial burner rig tests Report conducted at temperatures of 1010 C (1850 F( indicate that Charles A. Stevenson and David W. Netzer Oct. 1979 45 p improvements in cyclic life greater than 20:1 over previous refs Prepared for Naval Weapons Center, China Lake, Calif. ceramic coating systems were achieved. Three plasma sprayed (AD-AO8 1081; NPS67-79.01 0) Avail: NTIS coating systems applied to first stage vane platforms in the HC A03/MF AOl CSCL 21/5 high pressure turbine were subjected to a 100-cycle JT9D engine An adaptation of a primitive variable, finite-difference endurance test with only minor damage occurring to the computer program was accomplished in order to predict the coatings. A.R.H. reacting flow field in a solid fuel ramjet. The study compares the predictions of the primitive variable computer model with an earlier computer model and empirical data. It was found that the new model reasonably predicted the flow field and N8023314*# National Aeronautics and Space Administration. permitted calculations within the aft mixing chamber. GRA Lewis Research Center. Cleveland, Ohio. OSCEE FAN EXHAUST BULK ABSORBER TREATMENT EVALUATION N80-23320// Solar Turbines , International, San Diego, Calif. H. E. Bloomer and Nick E. Samanich 1980 20 p refs Presented APPLICATION OF CERAMIC NOZZLES TO 10 KW ENGINE at 6th Aeroacoustics Conf., 4-6 June 1980; sponsored by Final Report AIAA James C. Napier and A. G. Metcalfe Dec. 1978 263 p refs (NASA-TM-81498; E-435( Avail: NTIS NC A02/MF AOl CSCL (Contract DAAK02-75-C-01 38) 21E (AD-A081184; SR80-R-4375-43: SO-6-4375-7) Avail: NTIS The acoustic suppression capability of bulk absorber ma- NC Al2/MF AOl CSCL 21/5 terial designed for use in the fan exhaust duct walls of the Work on application of ceramics to the nozzle section of quiet clean short haul experiment engine (OCSEE UTW( was the small radial MERADCOM 10 KW gas turbine engine for evaluated. The acoustic suppression to the original design for meeting the two separate goals of improved erosion resistance the engine fan duct which consisted of phased single degree-of- and increased turbine inlet temperature is reported. Engine freedom wall treatment was tested with a Splitter and also with demonstrations of each of the two ceramic nozzle designs were the splitter removed. Peak suppression was about as predicted completed. Efforts leading to engine demonstrations are document- with the bulk absorber configuration, however, the broadband ed and included; ceramic materials properties studies; design characteristics were not attained. Post test inspection revealed studies; engine simulator experiments for high temperature surface oil contamination on the bulk material which could have erosion, corrosion and thermal shock; and development of caused the loss in bandwidth suppression. R. C.T. specialized relaxing glass adhesives for joining of ceramics. It was demonstrated that ceramics can offer from 10 to 100 times the erosion resistance at 1700 F to superalloys and have excellent N80.23316*# General Electric Co., Cincinnati, Ohio. Aircraft corrosion and thermal shock properties. GRA Engine Group. CF6-6D ENGINE SHORT-TERM PERFORMANCE DETE- RIORATION N80-23321# Naval Postgraduate School, Monterey, Calif. W. H. Kramer, J. E. Paas, J. J. Smith. and R. H. Wulf Apr. ATMOSPHERIC DISPERSION OF HIGH VELOCITY JETS 1980 154 p Final Report (Contract NAS3-20631) Jack V. Brendmoen and David W. Netzer Nov. 1979 84 p (NASA-CR-159830; R80AEG374( Avail: NTIS refs HC A08/MF AOl (ZF57572002(

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(AD-A08161 2; NPS67-76-01 2) Avail: NTIS concepts may be required to provide an acceptable solution. HC A05/MF AOl CSCL 21/5 G RA A neutrally stable atmospheric surface layer was simulated in a low speed wind tunnel by tripping the boundary layer with N80-23324# Motoren- und Turbinen-Union Muenchen G.m.b.H. a fence and letting the turbulent flow develop over a length of (West Germany). roughness elements. Turbojet exhaust dispersion characteristics, DEVELOPMENT OF HIGH TEMPERATURE RESISTANT simulated by a burner/nozzle system, were investigated by CERAMIC PARTS FOR GAS TURBINES Final Report measuring the horizontal and vertical temperature profiles at axial Wolfgang Krueger, Bernd Kugenbuch. Walter-Hans Peschel. and stations downwind from the nozzle exit. Dispersion sensitivity to Wilhelm Siebmanris Bonn Bundesmin. fuer Forsch. u. Technol. different nozzle exit conditions, angles of incidence to the wind, Jul. 1979 54 p refs In GERMAN; ENGLISH summary and nozzle surface blockage were investigated. The results were (Contract BMFT-NTS-19( compared to dispersion methods used in the Air Quality (BMFT-FB-T-79-09( Avail: NTIS HC A04/MF AOl; Fachinfor- Assessment Model (ADAM). It was found that (1) the experimental mationszentrum Energie, Phys.. Math., Eggenstein-Leopoldshafen, jet penetration length was much shorter than that assumed in West Germany DM 10,90 AQAM; (2) the horizontal jet exhibited plume rise; (3) the initial Ceramic materials were used to produce an automobile gas dispersion coefficients were a function of wind direction; and turbine engine which is capable of operating at temperatures of 141 the plume spreading rate was more rapid than for the low up to 1400 C. The flame tube, turbine inlet cone, and turbine velocity, elevated sources in neutrally stable atmospheric nozzle assembly were fabricated entirely of ceramics. The turbine conditions. GRA rotor consisted of ceramic blades and a metal disc. Extensive tests were performed under conditions similar to those expected N80-23322# lIT Research Inst., Chicago, Ill. in automobile applications. Author (ESA) PROPERTY SCREENING AND EVALUATION OF CERAMIC TURBINE ENGINE MATERIALS Final Report, 1 Jul. 1975 - N80-23325# Office National d'Etudes et de Recherches 1 Aug. 1979 Aerospatiales, Paris (France). D. C. Larsen Wright-Patterson AFB, Ohio AFML Oct. 1979 THREE DIMENSIONAL FLOW INVESTIGATION WITH A 152 p refs METHOD OF CHARACTERISTICS IN THE INLET REGION (Contract F33615-75-C-519616( AND THE BLADE-TO-BLADE CHANNELS OF SUPERSONIC IAD-A080963; AFML-TR-79-41881 Avail: . NTIS AXIAL COMPRESSORS Thesis - Paris VI Univ. HC A08/MF AOl CSCL 11/2 Jean Martinon 1979 205 p refs In FRENCH; ENGLISH An overview is presented of the pertinent thermal and summary Report will also be announced as translation mechanical properties of 26 structural silicon-base non-oxide (ESA-TT-637( ceramics that are candidates for advanced heat engine applica- (ONERA-NT- 1979-1; ISSN-0078-379X) Avail: NTIS tions. Included are hot pressed, sintered and reaction sintered HC A10/MF AOl Si3N4 and SiC, and Sialon. Data are presented for flexure A three dimensional method of characteristics was developed strength, elastic properties, strength degradation at long times for the calculation of the supersonic flow in the inlet region and due to subcritical crack growth, long term oxidation effects, creep the blade to blade channels of blade cascades and high transonic resistance, fracture toughness, thermal expansion, thermal axial flow compressors with subsonic or supersonic axial velocity. diffusivity, and thermal shock resistance. All materials are The numerical scheme is described and example calculations on evaluated using the same test equipment so that valid comparisons several linear or annular cascades and rotating blade rows are can be made between materials. Emphasis is placed on presented. Author (ESA) predominant behavioral trends as related to material microstruc- ture and purity, as determined by processing method. Structure- N8023326*# National Aeronautics and Space Administration. property relations are developed. GRA Langley Research Center. Langley Station, Va. NAVIGATION. GUIDANCE, AND CONTROL FOR HELICOP- TER AUTOMATIC LANDINGS N80-23323# Air Force Aero Propulsion Lab., Wright-Patterson James A. Kelly and Frank A. Niessen May 1980 58 p refs AFB, Ohio. Turbine Engine Div. (NASA-TP-1649; L-13454) HCA04/MF AOl CSCL01C TURBOPROPULSION COMBUSTION TECHNOLOGY A navigation, guidance and control concept was developed ASSESSMENT Technology Summary Report, Mar. 1978 - for helicopter automatic approach and landings. The algorithms Oct. 1979 employed were implemented in an airborne digital computer Robert E. Henderson, ed. and A. M. Mellor, ed. (Purdue Univ.( installed on a CH-47B research helicopter. Data are presented Dec. 1979 31 p refs to illustrate system performance during fully automatic approach (AF Proj. 3066) and landings in a variety of wind conditions. A.W.H. (AD-AO80748; AFAPL-TR-79-21 15) Avail: NTIS HC A03/MF AOl CSCL 21/2 This report summarizes the finding of an assessment. Section N8023327*// National Aeronautics and Space Administration. 1 provides a general introductory overview of the state-of- Hugh L. Dryden Flight Research Center, Edwards, Calif. combustion-technology today and highlights some general PRECISION CONTROLLABILITY OF THE YF-17 AIRPLANE projections and trends for the future. Section 2 gives a Thomas A. Sisk and Neil W. Mataeny May 1980 34 p refs state-of-the-art review of the five special topic areas of interest (NASA-TP-1677; H-1089) Avail: NTIS HC A03/MF AOl CSCL covered during the assessment - main burners, afterburners, 01C combustion modeling, structural and mechanical design, and A flying qualities evaluation conducted on the VF-17 airplane alternative fuels. Sections 3 and 4 examine the advanced permitted assessment of its precision controllability in the transonic technology trends and projected technology needs, respectively, flight regime over the allowable angle of attack range. The precision as related to each of the topic areas cited above. A five-year controllability (taitchase tracking) study was conducted in technology plan is outlined in Section 5. Future aircraft propul- constant-g and windup turn tracking maneuvers with the command sion requirements call for combustion systems capable of augmentation system (CAS) on, automatic maneuver flaps, and (1) accepting greater variations in compressor discharge pressure the caged pipper gunsight depressed 70 mils. This study showed temperature and airflow; (2) producing heat release rates and that the YF-17 airplane tracks essentially as well at 7 g's to temperature rises which will ultimately approach stoichiometric 8 g's as earlier fighters did at 4 g's to 5 g's before they levels; and 131 providing high operational reliability and improved encountered wing rock. The pilots considered the YF-17 airplane component durability, maintainability and repairability. In addition, one of the best tracking airplanes they had flown. Wing rock at the new requirements associated with exhaust emissions and the higher angles of attack degraded tracking precision, and lack fuel flexibility must be addressed. Consequently, as the combustor of control harmony made precision controllability more difficult. designer is confroneted with the new requirements of the future, The revised automatic maneuver flap schedule incorporated in especially exhaust emissions and fuel flexibility, new design the airplane at the time of the tests did not appear to be optimum.

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The largest tracking errors and greatest pilot workload occurred N80-23331# Advisory Group for Aerospace Research and at high normal load factors at low angles of attack. The pilots Development. Neuilly-Su r- Seine (France). reported that the high-g maneuvers caused some tunnel vision DESIGN. DEVELOPMENT AND IMPLEMENTATION OF AN and that they found it difficult to think clearly after repeated ACTIVE CONTROL SYSTEM FOR LOAD ALLEVIATION FOR maneuvers. Author A COMMERCIAL TRANSPORT AIRPLANE R. F. OConnell (Lockheed-California Co., Burbank) Feb. 1980 21 p refs Presented at the 49th Struct. and Mater. Panel N8023328*# Systems Technology, Inc.. Hawthorne, Calif. Meetings, Porz-Wahnm, West Germany, Oct. 1979 PRACTICAL OPTIMAL FLIGHT CONTROL SYSTEM DESIGN (AGARD-AR-683: 15BN92-835- 1348-7) Avail: NTIS FOR HELICOPTER AIRCRAFT. VOLUME 1: TECHNICAL HC A02/MF AOl REPORT An active control system for load alleviation was developed L. G. Hofmann, Susan A. Riedel, and Duane McRuer May for a long range version of the Lockheed L-101 1. This system 1980 273 p refs which permits the use of an extended wing span for fuel (Contract NAS2-9946) conservation with minimum structural change, will be in- IF4ASA-CR-3275; TR-1 127-1-Il Avail: NTIS troduced into commercial service in early 1980. The system is HC Al2/MF AOl CSCL 01C described and the criteria to which it is of the system installed A method by which modern and classical theory techniques on the flight test data obtained from a prototype version of the may be integrated in a synergistic fashion and used in the design system installed on the flight airplane are presented, and of practical flight control systems is presented. A general procedure comparsions of these results with analytical predictions are shown. is develpoed, and several illustrative examples are included. A basis for certification of such systems is presented, assuring Emphasis is placed not Only on the synthesis of the design, but a level of safety equivalent to that of a conventional design. on the assessment of the results as well. R.C.T. R.E.S. N80-23329# Army Missile and Munitions Center and School, N8023332*# National Aeronautics and Space Administration. Redstone Arsenal, Ala. Guidance and Control Directorate. Langley Research Center, Langley Station. Va. THEORY OF DISTURBANCE-UTILIZING CONTROL WITH TWINTAN: A PROGRAM FOR TRANSONIC WALL APPLICATION TO MISSILE INTERCEPT PROBLEMS INTERFERENCE ASSESSMENT IN TWO-DIMENSIONAL William C. Kelly 12 Dec. 1979 327 p refs WIND TUNNELS IAD-AO81 110: DRSMI/RG-80-1 11 Avail: NTIS William B. Kemp, Jr. May 1980 40 p refs HC A17/MF AOl CSCL 12/1 (NASA-TM-81819( Avail NTIS HC A03/MF AOl CSCL Control problems with disturbances which have waveform 148 structure may be addressed by considering the maximum utilization A method for assessing the wall interference in transonic mode of disturbance-accomodating control theory. It is shown two dimensional wind tunnel test was developed and implemented in this work that the optimal utilization of disturbances can lead in a computer program. The method involves three successive to significantly better performance than that of the 'Optimal' solutions of the transonic small disturbance potential equation linear-quadratic regulator. The conditions for the existence of a to define the wind tunnel flow, the perturbation attriburable to steady-state disturbance-utilizing control law are derived. It is the model, and the equivalent free air flow around the model. shown that the steady-state control gains when they exist, are Input includes pressure distributions on the model and along solutions of certain matric algebraic equations. Steady-state gain the top and bottom tunnel walls which are used as boundary expressions are derived for several first and second order plants. conditions for the wind tunnel flow. The wall induced perturbation Results are presented for the cases of optimal disturbance-utilizing fields is determined as the difference between the perturbation control of an air-defense interceptor missile and of a missile in the tunnel flow solution and the perturbation attributable to homing on a fixed target, which demonstrate performance superior the model. The methodology used in the program is described to that obtained by a conventional 'optimal' linear-quadratic missile and detailed descriptions of the computer program input and controller. GRA output are presented. Input and output for a sample case are given. J.M.S. N80-23330# European Space Agency, Paris (France). DEFINITION OF A TWO-LEVEL CONTROL SYSTEM FOR N8023333*# National Aeronautics and Space Administration. NONLINEAR MOTION OF AN AIRCRAFT Langley Research Center, Langley Station, Va. Albert Kirszenblat (Technion - Israel Inst. of Tech.) Feb. 1980 CRYOGENIC WIND TUNNELS: A SELECTED. ANNOTATED 36 p refs Transl. into ENGLISH of "Calcul dun Systeme de BIBLIOGRAPHY Commande a Deux Niveaux du Movement non Lineaire d'un Marie H. Tuttle and Robert A. Kilgore May 1980 15 p Avion", Rept. ONERA-P-1979-7 ONERA, Paris, 1979 Original (NASA-TM-80168( Avail: NTIS HC A02/MF AOl CSCL report in FRENCH previously announced as N8O-22364 14B (ESA-TT-614; ONERA-P- 1979-7) Avail: NTIS This annotated supplement updates the cryogenic wind tunnel HC A03/MF AOl bibliography. The entries continue the numbering begun in the An approach to the problem of defining a control law well first publication and run from 125 through 167. adapted to the whole flight envelope is presented. This system R.E.S. has a two level structure alloWing a task-oriented control and an augmentation of the aircraft stability. A nonlinear model of the aircraft dynamics incorporating the inertial coupling terms N80-23334# Air Force Human Resources Lab., Brooks AFB, and the nonlinear aerodynamic effects constitute the first control Tex. Flying Training Div. level. The model generates a trajectory, a reference control law PLATFORM MOTION CONTRIBUTIONS TO SIMULATOR vector, and an output vector which follows a vector, representing TRAINING EFFECTIVENESS. STUDY 3: INTERACTION the maneuvering objectives assigned by the pilot at any time. OF MOTION WITH FIELD-OF-VIEW Final Report At the second level, a servo compensation subordinates the Mark Nataupsky, Wayne L. Waag. Douglas C. Weyer, Robert aircraft motion to the model. The control law is obtained by W. McFadden, and Edward McDowell Nov. 1979 31 p refs applying optimal linear control theory to local models of the (AF Proj. 1123) aircraft. Direct force control surfaces may be easily incorporated (AD-A078426; AFHRL-TR-79-25( Avail: NTIS into the computation of the control system. This system ensures HC A03/MF AOl CSCL 05/9 an automatic and smooth coordination of the aircraft motions The objective was to determine the effects of platform motion and of the deflection of the aerodynamic control surfaces along cueing, visual field of view IFOVI, and their interaction upon the pitch, roll and yaw axes, even under extreme flight condi- learning in the simulator and as subsequent transfer of training tions; it is particularly adapted to the case of high-performance to the aircraft for basic contact maneuvers in the T-37 aircraft. fighter aircraft. Author (ESA) A transfer of training study design was used in which student

367 N80-23335 pilots were initially trained in the Advanced Simulator for Pilot d'Aubes", Rept. AGARD-CP . 248 AGARD In ENGLISH and Training (ASPI) and subsequently evaluated on their first sortie FRENCH Presented at AGARD/PEP Symp.: Stresses, Vibration, in the 1-37 aircraft. Each student received training under one of Engine Integration and Engine Integrity, Cleveland. 23-27 Oct. four simulator configurations: (1) full platform motion (six 1978 degrees-of-freedom), full FOV 1300 degrees horizontal by 150 (PNR-9001 1; Trans-14190; AGARD-CP.248) Avail: NTIS degrees vertical: (2) full platform motion, limited FOV (48 degrees HC A02/MF AOl by 36 degrees vertical): 131 no platform motion, full FOV; and The nature of the problems of aeroelastic stability in 141 no platform motion, limited FOV. For the ASPT pretraining compressors is reviewed, and the wind tunnel for rectilinear phase, scores from the automated performance measuring system cascades at ONERA is described. The installation simulates as and overall instructor pilot ratings were used for analysis. For closely as possible the conditions in the actual engines studied: the 1-37 evaluation sorties, the overall instructor pilot ratings, compression ratio (Or incidence). Mach number, and corrected as well as individually recorded flight parameters, were analyzed. frequency. The measurement methods are discussed, and test These data provided no conclusive evidence of differential transfer results presented which show the character of the aeroelastic effects resulting from platform motion cueing, size of the visual instabilities in a subsonic and transonic flow. Author (ESA) FOV, or their interaction. As such, these data provide support for previous findings that platform motion cueing does not significantly enhance the transfer of learning for basic contact N8023370*# National Aeronautics and Space Administration. tasks in the 1-37 aircraft, It would seem that the impact of Lewis Research Center, Cleveland, Ohio. peripheral visual cues for initial acquisition is not critical. ENGINE ENVIRONMENTAL EFFECTS ON COMPOSITE Furthermore, no convincing evidence was found indicating BEHAVIOR increased transfer using platform motion in conjunction with a C. C. Chamis and G. T. Smith 1980 20 p refs Presented at narrow FOV visual scene. GRA the 21st Struct., Structural Dyn. and Mater. Conf., Seattle, 12-14 May 1980; sponsored by AIAA. ASME. ASCE. and AHS (NASA-TM-81508; E-446) Avail: NTIS HC A02/MF AOl CSCL N80-23335# Naval Air Development Center, Warminster, Pa. 11 Software and Computer Directorate. A series of programs were conducted to investigate and NAVAIRDEVCEN DYNAMIC FLIGHT SIMULATOR DESIGN develop the application of composite materials to turbojet engines. AND MULTIPURPOSE CREW STATION CONCEPT DESIGN A significant part of that effort was directed to establishing the AND DEVELOPMENT PLAN Final Report impact resistance and defect growth chracteristics of composite G. Terry Thomas 1 Nov. 1979 68 p refs (AD-A08 1982: NADC-8001 9-50) Avail: NTIS materials over the wide range of environmental conditions found HC A04/MF AOl CSCL 14/2 in commercial turbojet engine operations. Both analytical and Chemical reactions important in molecular lasers were studied empirical efforts were involved. The experimental programs and with a special emphasis on atomic recombinations and on the analytical methodology development as well as an evaluation dissociation of diatomic molecules. The experiments involved flash program for the use of composite materials as fan exit guide photolysis and shock wave techniques. The results were vanes are summarized. R.C.T. explained in terms of 3-D trajectory calculations. GRA N80-23371*# Lockheed-California Co., Burbank. FLIGHT SERVICE EVALUATION OF KEVLAR-49 EPDXY N80-23336# Canyon Research Group, Inc.. Westlake Village, COMPOSITE PANELS IN WIDE-BODIED COMMERCIAL Calif. TRANSPORT AIRCRAFT Annual Flight Service Report. AIR COMBAT MANEUVERING PERFORMANCE MEASURE- Jan. - Dec. 1979 MENT R. H. Stone Mar. 1980 43 p refs Michael J. Kelly, Lee Wooldridge, Robert T. Hennessy, Donald (Contract NAS1-1 1621) Vreula, and Steve F. Barnebey Sep. 1979 140 p refs (NASA-CR-159231; AFSR-6) Avail: NTIS HC A03/MF AOl (Contract F33615-77-C-0079; AF Proj. 1123) CSCL 11 (AD-A077429; NAVTRAEQUIPC-IH-315: AFHRL-TR-79-3( Kevlar-49 fairing panels, installed as flight service components Avail: NTIS HC A07/MF AOl CSCL 05/9 on three L-101 1s, were inspected after 6 years' service. The A study was conducted to define measures of Air Combat Kevlar-49 components were found to be performing satisfactorily Maneuvering (ACM) for one-versus-one (lvI) free engagements in service with no major problems. or any condition requiring on the Simulator for Air-to-Air Combat ISAAC). The study found corrective action. The only defects noted were minor impact a small set of measures which were Ill sensitive to differences damage, and a minor degree of fastener hole fraying and in pilot ACM skill level: 121 diagnostic of performance proficiencies elongation. These are for the most part comparable to damage and deficiencies; 131 usable by instructor pilots and compatible noted on fiberglass fairings. R.C.T. with their judgments; (4) capable of providing results immediately after the end of the engagement; and (5) compatible with current projected training measurement hardware. The study was N80-23433# Naval Air Development Center, Warminster, Pa. conducted in three phases. Phase 1 was an analytical study of Aircraft and Crew Systems Technology Directorate. ACM tasks using information from training material and instructor AIRCRAFT CARRIER EXPOSURE TESTS OF ALUMINUM pilots; 28 measures reflected subject matter experts opinion on ALLOYS Progress Report the important elements of ACM. Pilot control, aircraft performance E. J. Jankowsky. S. J. Ketcham, and V. S. Agarwala 1 Nov. and engagement outcome variables were measured in phase 2 1979 36 p refs during 405 free engagements on the SAAC at Luke AFB using (ZF6 1542001) a total of 30 pilots with three different levels of experience. A (AD-A081060; NADC-7925 1-601 Avail: NTIS computer analysis of the engagement data was conducted in HC A03/MF AOl CSCL 11/6 phase 3 to Ill check methodological assumptions that the three An effort is underway to correlate results of accelerated pilot experience levels represented different ACM skill levels and laboratory corrosion tests with actual shipboard exposure of aircraft 121 develop the smallest comprehensive measure set. GRA materials. This report describes the first of the series in which aluminum alloys with varying susceptibilities to exfoliation and stress corrosion were exposed on the flight deck of an aircraft N80-23337# Rolls-Royce Ltd., Derby (England). carrier. Use of an electrochemical corrosion monitor to measure INVESTIGATION INTO COMPRESSOR AEROELASTIC corrosivity of the environment is also described. GRA INSTABILITIES IN A WIND TUNNEL FOR A RECTILINEAR CASCADE OF BLADES N80-23444# Kloeckner- Humboldt- Deutz AG., Oberursel (West Edmond Szechenyi IONERA, Parisl, Henri Loiseau IONERA. Paris). Germany). and Brigitte Maquennehan IONERA, Paris) 1979 14 p refs FATIGUE AT HIGH TEMPERATURES: EXAMINATION OF Transl. into ENGLISH of conf. paper "Etude des Instabilites THE BEHAVIOR OF GASTURBINE CASTING MATERIALS Aeroelastiques des Compresseurs en Soufflerue de Grille Rectiligne ALSO IN SIMULTANEOUS TEMPERATURE AND STRAIN

368 N80-23514

CYCLES Final Report An emergency in-flight egress system was installed in a Arnold Witt and Manfred Pucher Bonn Bundesmin. fuer Forsch. light general aviation airplane. The airplane had no provision for u. Technol. Jul. 1979 102 p refs In GERMAN: ENGLISH egress on the left side. To avoid a major structural redesign for summary Sponsored by Bundesmin. fuer Forsch. u. Technol. a mechanical door, an add on 11.2 kg (24.6 lb) pyrotechnic- (BMFT-FB-T-79-26) Avail: NTIS HC A06/MF AOl: Fachinfor- actuated system was developed to create an opening in the mationszentrum Energie, Phys., Math., Eggenstein-Leopoldshafen. existing structure. The skin of the airplane was explosively severed West Germany OM 21 around the side window, across a central stringer, and down to Test equipment that allows an examination of the effects of the floor, creating an opening of approximately 76 by 76 cm. low cycle fatigue of nickel based cast alloys is described. It is The severed panel was jettisoned at an initial velocity of possible to simultaneously vary temperature and compression- approximately 13.7 m/sec. System development included , a total tension strain cycles of precision cast alloy samples. A hollow of 68 explosive severance tests on aluminum material using cylindrical sample was investigated in terms of the number of small samples, small and full scale flat panel aircraft structural cracks as a function of temperature, dwell times for tension and mockups, and an actual aircraft fuselage. These tests proved compression, cycle period, strain rate, and alteration of temperature explosive sizing/ severance margins, explosive initiation, explosive and strain. Author (ESA) product containment, and system dynamics. This technology is applicable to any aircraft of similar construction. R.C.T. N80-23449# National Aerospace Lab.. Amsterdam (Netherlands). Structures and Materials Div. N8023512*# National Aeronautics and Space Administration. GUST SEVERITY EFFECTS ON FATIGUE CRACK PROPAGA- Langley Research Center, Langley Station, Va. TION IN ALUMINUM ALLOY SHEET MATERIALS A SPIN-RECOVERY PARACHUTE SYSTEM FOR LIGHT R. J. H. Wanhill Dec. 1978 21 p refs Submitted for publication GENERAL-AVIATION AIRPLANES Sponsored by Netherlands Agency for Aerospace Programs and Charles F. Bradshaw In its Proc, of the 14th Aerospace Mech. Dutch Civil Aviation Board Symp. May 1980 p 195-209 refs )NLR-MP-78041-U) Avail: NTIS HC A02/MF AOl Flight simulation fatigue tests were conducted to investigate Avail: NTIS HC A15/MF AOl CSCL 01C the effect of differing gust load experiences on fatigue crack A tail mounted spin recovery parachute system was designed propagation in 7075-T6 and the effect of gust load alleviation and developed for use on light general aviation airplanes. The on 2024-T3. Two gust spectra were used: the Fokker system was designed for use on typical airplane configurations, F-27 spectrum and the reference spectrum TWIST. A large including low wing, high wing, single engine and twin engine systematic effect of gust severity on crack propagation rates in designs. A mechanically triggered pyrotechnic slug gun is used 7075-T6 was correlated by the stress intensity factor for the to forcibly deploy a pilot parachute which extracts a bag that rms of the gust amplitudes. Author (ESA) deploys a ring slot spin recovery parachute. The total system weighs 8.2 kg. System design factors included airplane wake effects 'on parachute deployment, prevention of premature N8023472*# National Aeronautics and Space Administration. parachute deployment, positive parachute jettison, compact size. Lewis Research Center, Cleveland, Ohio. low weight, system reliability, and pilot and ground crew safety. THE IMPACT OF FUELS ON AIRCRAFT TECHNOLOGY Extensive ground tests were conducted to qualify the system. THROUGH THE YEAR 2000 The recovery parachute was used successfully in flight Jack Grobman and Gregory M. Reck 1980 26 refs Presented p 17 times. R.C.T. at the Intern. Meeting and Tech. Display: Global Technol. 2000, Baltimore, 5-11 May 1980: sponsored by AIAA (NASA-TM-81492: E-429) Avail: NTIS NC A03/MF AOl CSCL 21D N8023513* # Pratt and Whitney Aircraft, East Hartford, Conn. The impact that the supply, quality, and processing costs of Government Products Div. future fuels may have on aircraft technology is assessed. The F100 EXHAUST NOZZLE AREA CONTROL potential range of properties for future jet fuels is discussed Joseph R. Kozlin In NASA. Langley Res. Center Proc. of the along with the establishment of a data base of fuel property 14th Aerospace Mech. Symp. May 1980 p 211-223 effects on propulsion system components. Also, the evolution and evaluation of advanced component technology that would Avail: NTIS HC A15/MF AOl CSCL 21E permit the use of broader property fuels and the identification The details of the F100 nozzle mechanism design are of technical and economic trade-offs within the overall fuel highlighted, placing particular emphasis upon the evolution of production-air transportation system associated with variations design constraints or drivers from initial concept through current in fuel properties are examined. M.G. operational deployment. A kinematic description of the area control mechanism is given, and several environmental Constraints which complicate the normal mechanism design process are dis- N80-23474jl Suntech. Inc Marcus Hook, Pa. cussed. R.C.T. RESEARCH ON DIAMANTANE AND OTHER HIGH DENSITY HYDROCARBON FUELS Final Re,ort. 1 Jun. 1978 - 30 Jun. 1979 Boeing Commercial Airplane Co.. Seattle. Wash. A. Schneider and H. K. Myers Wright-Patterson AFB, Ohio N8023514*# AFAPL Oct. 1979 93 refs AIRPLANE WING LEADING EDGE VARIABLE CAMBER p FLAP (Contract F33615-78-C-2037: AF Proj. 3048) James B. Cole In NASA. Langley Res. Center Proc. of the (AD'A080749: AFAPL-TR-79-2080) Avail: NTIS HC A05/MF AOl CSCL 21/4 14th Aerospace Mech. Symp. May 1980 p 225-235 This report describes the preparation of (a) diamantane. Avail: NTIS HC A15/MF AOl CSCLO1C )b( exo-tetrahydro-tricyclopentadiene. Ic) the hydrogenated The invention and design of an aerodynamic high lift device product of isomerized endo, endo-di(norbornadiene). and (d) some which provided a solution to an aircraft performance problem precursors of polyalkyldiamantanes. G RA are described. The performance oroblem of converting a high speed cruise airfoil into a low speed aerodynamic shape that N8023511*# National Aeronautics and Space Administration. would provide landing and take-off characteristics superior to Langley Research Center, Langley Station, Va. those available with contemporary high lift devices are addressed. EMERGENCY IN-FLIGHT EGRESS OPENING FOR GENERAL The need for an improved wing leading edge device that would AVIATION AIRCRAFT complement the high lift performance of a triple slotted trailing Laurence J. Bement In its Proc. of the 14th Aerospace Mech. edge flap is examined. The mechanical and structural aspects of Symp. May 1980 p 173-194 refs the variable camber flap are discussed and the aerodynamic performance aspects only as they relate to the invention and Avail: NTIS HC A15/MF AOl CSCL 01C design of the device are presented. R.C.T.

369 N80-23530

N80-23530# National Aviation Facilities Experimental Center, stroke are briefly reviewed. Measurements at lightning current Atlantic City, N. J. at ground are discussed, with the airborne survey of lightning MEASUREMENT OF INTERFERENCE-TO-NAVIGATION! fields conducted as part of TRIP-76. Author (ESA) COMMUNICATION AVIONICS FROM CABLE TELEVISION (CATV) SYSTEMS Final Report. Jan. - Sep. 1978 N80-23674# Laboratorium fuer Betriebsfestigkeit. Darmstadt Edward M. Sawtelle and James G. Dong Dec. 1979 52 p (West Germany). refs MATHEMATICAL MODEL FOR THE SEPARATION OF GUST (FAA Proj. 213-662-810) AND MANOEUVRE LOADS OF CIVIL AIRCRAFT (AD-A081430: FAA-NA-79-7; FAA-RD-79-104) Avail: NTIS J. Taylor 1979 28 p refs NC A04/MF AOl CSCL 20/14 (FB-141)1979); ICAF-1135) Avail: NTIS HC A03/MF AOl Airborne measurements of cable television (CATVI leakage, Ignoring the unsteady lift functions, the normal acceleration made at selected cities to compile a representative sampling of response of an aircraft at its centre of gravity to a simplified interference effects are presented and discussed. Different altitudes turbulence spectrum varying as frequency to the power were used in the flight-grid-type pattern. Ground measurements -5/3 were studying. It is shown that the pitching influence usually were also accomplished by the Federal Communications reduces the response at long wavelengths from that produced Commission (FCC) at the sites tested to determine any correlation by heaving alone. This influence was relatively small in piston- between the ground and air measurements. The cities selected engined aircraft but has generally become greater as aircraft for discussion in this report were chosen to show various CATV have developed. The increased response at long wavelengths in effects detected by the data collection systems. A statistical modern aircraft makes the problem of separating maneuvres from analysis was performed on the data upon finding that direct gust response more difficult but it is attenuated somewhat by airborne position correlation to strong ground leak points was the pitching contributions to the response. Experimental studies not possible. The analysis provided the mean for each run of a on a T33, on a Concorde and on a Transall indicate that a grid and a comparison to determine if significant differences band frequency exists where the manoeuvres and turbulence existed between runs. Where no significant differences were found, responses are both small so that a filter within this band should the condition was due to ambient noise exceeding signal level. separate one type of response from the other. Author Laboratory measurements were also made. Recommendations include maximum signal level for CATV leakage that may be N8023678* # National Aeronautics and Space Administration. tolerated in the communication and navigation bands. A.further Lewis Research Center, Cleveland, Ohio. recommendation is made that the CAN industry use frequencies STATUS OF NASA FULL-SCALE ENGINE AEROELASTICITY in the navigation band Which are separated from Federal Aviation RESEARCH Administration navigation frequencies by 25 kilohertz. M.G. Joseph F. Lubomski 1980 21 p refs Presented at the 21st Struct., Structural Dyn.. and Mater. Conf., Seattle, 12-14 May 1980: sponsored by AIAA, ASME. ASCE and AHS N80-23536# Edgerton, Germeshausen and Grier. Inc.. Albuquer- )NASA-TM-81500; E-437) Avail: NTIS NC A02/MF AOl CSCL que, N. Mex. E-3A EMP EVALUATION PROGRAM Final Reporf, Nov. 20K Data relevant to several types of aeroelastic instabilities were 1977 - Feb. 1979 J. R. Anderson Kirtland AFB. N. Mex. AFWL Oct. 1980 obtained using several types of turbojet and turbofan engines. In particular, data relative to separated flow (stall) flutter, choke 104 p (Contract F29601-78-C-0013: AF Proj. 37631 flUtter, and system mode instabilities are presented. The unique (AD-AO81725: AD-E200458; E6/AG-1394; AFWL-TR-79-1 15) characteristics of these instabilities are discussed, and a number of correlations are presented that help identify the nature of the Avail: NTIS HC A06/1VIF AOl CSCL 20/14 This document is the final report of the E-3A EMP Evaluation phenomena. R.E.S. Test Program conducted for the AFWL at Kirtland Air Force Base. The report is divided into four sections: Test Planning, N80-23683# National Aeronautics and Space Administration. Test Procedures, Data Management and Test Activities. The Test Langley Research Center, Langley Station, Va. Planning section emphasizes the importance of pretest activities, MINIMUM MASS SIZING OF A LARGE LOW-ASPECT demonstrates what can happen if critical items (such as RATIO AIRFRAME FOR FLUTTER-FREE PERFORMANCE connectors) are not identified early, and makes recommendations William H. Greene and Jaroslaw Sobieszczanski-Sobieski May for future tests. The Test Procedures section gives a step-by-step 1980 40 p refs Presented at the 21st Struct., Structural detailed explanation for performing an EMP test on a large test Dyn.. and Mater. Conf., Seattle, 12-14 May 1980: sponsored object. A great number of the problems the test crew encountered by AIAA, ASME. ASCE and AHS on this program are pointed out and solutions are recommended. (NASA-TM-81818: AIAA-80-0724CP) Avail: NTIS A brief discussion on power-on testing and breakout box NC A03/MF AOl CSCL 20K qualification tests are included at the end of the section. The A procedure for sizing an airframe for flutter-free performance most detailed section in the report is Section 4, Data Management. is demonstrated on a large, flexible supersonic transport aircraft. Virtually every function of Data Management is covered in this The procedure is based on using a two level reduced basis or section; examples of typical response data. 284 calibration data. modal technique for reducing the computational cost of performing Daset log sheets and Adset log sheets are given and explained. the repetitive flutter analyses. The supersonic transport aircraft The final Section. Test Activities, explains to the reader the exhibits complex dynamic behavior, has a well-known flutter mechanics of performing a test at the HPD facility. GRA problem and requires a large finite element model to predict the vibratory and flutter response. Flutter-free designs were N80-23590# Oxford Univ. (England). Dept. of Engineering produced with small mass increases relative to the wing structural Science. weight and aircraft payload. R.E.S. A SURVEY OF THE HIGH FREQUENCY EFFECTS ASSOCI- ATED WITH THE LIGHTNING DISCHARGE N80-23693# Naval Postgraduate School, Monterey, Calif. N. S. J. Braithwaite and M. -J. -Cooke 1979 47 p refs AN INVESTIGATION OF RESIDUAL STRESSES IN SIMU- (OUEL-1290/79) Avail: NTIS HC A03/MF AOl LATED WING PANELS OF 7075-T6 ALUMINUM The literature on high frequency effects associated with the M.S. Thesis lightning discharge is reviewed, with emphasis on the possible Edward C. Engle Dec. 1979 46 p refs hazards to aircraft from electromagnetic fields. Sources of fast )AD-AO80863) Avail: NTIS HC A03/MF AOl CSCL 11/6 field changes in the cloud discharge and in the discharge to The advent of onboard aircraft microprocessor fatigue ground are considered in detail, from experimental observations monitoring systems will establish the opportunity to fully exploit of the far radiation field. Radiation from the return stroke and residual stresses at stress-critical areas, including their effects from K changes is most important up to 10 MHz, and breakdown on fatigue predictions. An experimental investigation was processes become important at higher frequencies. An overall undertaken to more fully understand them by making photoelastic amplitude frequency spectrum is given. Models of the return measurements of residual stresses at notches in simulated wing

370 N80-24134 panels of 7075-T6 aluminum and to establish the relationships instrumentation, calibration results, and initial test results are between local stresses, residual stresses, and the far-field or reported. Initial testing was with fixed pitch blades having applied stress. The stress concentration factors were found to cross-sections of conventional symmetrical airfoils. Costs of decrease with increased plastic deformation while the strain building the test model are included, as well as cost estimates concentration factors were found to remain constant. The residual for blades constructed with composite materials. These costs Stress levels were found to be immutable despite changes in are compared with those of other types of wind turbines. DOE fatigue loading conditions, notch geometry, or test duration.GRA

N80-23759# Deutsche Forschungs- und Versuchsanstalt fuer N80-23862# Massachusetts Inst. of Tech.. Cambridge. Aeroelas- Luft- und Raumfahrt. Oberpfaffenhofen (West Germany). Inst. tic and Structures Research Lab. fuer Physik der Atmosphaere. DYNAMICS OF A FLEXIBLE ROTOR-TOWER SYSTEM REMOTE SENSING METHODS FOR DETERMINATION OF Lennart S. Hultgren and John Dugundji Stockholm Aeronautical Research Inst. of Sweden Aug. 1979 99 p refs SLANT RANGE VISIBILITY (Contract SWEDBESD-5061.012( Christian Werner Mar. 1979 49 p refs In GERMAN: ENGLISH summary Report will also be announced as translation (ASRL-TR- 194-1: FFA-AU- 1 499( Avail: NTIS (ESA-TT-627) NC A05/MF AOl )DFVLR-FB-79-14) Avail: NTIS HC A03/MF AOl: DFVLR, The dynamics of a horizontal axis wind turbine were Cologne DM 8.70 analyzed. Both the blades and the tower are taken to be flexible. The various known methods for the determination of the The analysis is linear and modal. For a three bladed rotor, numerical slant visual range are reviewed and compared. Emphasis is placed results were obtained for free vibrations and forced oscillations on a discussion of laser radar systems for use in aircraft landing due to static unbalance. Analytical solutions were constructed operations. Based on considerations related to accuracy and for forced vibrations due to gravity and wind shear. technical complexity, a measurement method is proposed for Author (ESA( visibility distances of up to 1500 m and altitudes of 100 m. Author (ESA) N8023874*# Virginia Univ., Charlottesville. Engineering Sceinces Research Labs. N80-23181 National Mechanical Engineering Research Inst.. EVALUATING AND MINIMIZING NOISE IMPACT DUE TO Pretoria (South Africa). Aeromechanics Div. AIRCRAFT FLYOVER Final Report THE AERODYNAMICS OF AXIAL FLOW WIND POWER Ira D. Jacobson May 1980 78 p refs TURBINES (Grant N5G-1509) W. J. VanderElst Jun. 1979 37 p refs (NASA-CR-i 53187: UVA/5281 66/MAE8O/ 102) Avail: NTIS (CSIR-ME- 161 9 ISBN-0-7988-1463-2) Avail: NTIS HC A05/MF AOl NC A03/MF AOl The results of a study on the evaluation and reduction of A general analysis of the aerodynamics of wind power turbines noise impact to a community due to aircraft landing and takeoff of the axial flow type is presented. The design parameters appear operations are presented. The case of multiple aircrafts flying in nondimensional form and are presented graphically. The theory on several trajectories, for either approach/ landings or takeoffs is applicable to any type of wind power generator, including was examined. An extremely realistic model of the flight path slow running windmills normally used for powering water pumps was developed. The annoyance criterion used was the noise as well as fast running machines which are suitable for the impact index (Nil). The algorithm was applied to Patrick Henry generation of electric power. Author International Airport. R.E.S.

N80-23845# West Virginia Univ., Morgantown. Dept. of Aerospace Engineering. N80-23887# Research Inst. for Environmental Hygiene, TNO. VERTICAL AXIS WIND TURBINE DEVELOPMENT: EXECU- Delft (Netherlands). Afdel. Buitenlucht. TIVE SUMMARY Final Report, 1 Mar, 1976 - 30 Jun. PROJECT FILTER HOLDER. TESTS ON 25 mm DUST FILTER 1977 HOLDERS [ONTWERP FILTERHOUDER. ON1WERP VAN R. E. Walters, J. B. Fanucci, P. W. Hill. and P. G. Migliore Jul. NIEUWE FILTERHOUDER 25 mm EN HET TESTEN VAN 1979 26 p DRIE TYPEN FILTERHOUDERS 25 mm) (Contract EY-76-C-05-5135) W. C Duba Apr. 1978 19 p In DUTCH (ORO-5135-77-5-Summ) Avail: NTIS NC A03/MF AOl (IG-TNO-F-1638) Avail: NTIS HC A02/MF AOl Information is presented concerning (1) the numerical solution Designs are presented for dust filter holders suitable for use of the aerodynamics of cross-flow wind turbines: (2) boundary in air pollution monitoring equipment. Design principles were layer considerations for a vertical axis wind turbine (VAWT(: determined which overcome problems such as lateral filtration (3) VAWT outdoor test model: (4)10w solidity blade tests: (5) high and leaks. Interchangeable parts permit different methods of solidity blade design: (6) cost analysis of the VAWT test model: sampling using the same basic equipment. Author (ESA( (7) structural parametric analysis of VAWT blades: and (8) cost study of current wind energy conversion systems. DOE N80-24134# Office National d'Etudes et de Recherches Aerospatiales. Paris (France). N80-23846# West Virginia Univ., Morgantown. Dept. of SPECTRAL ANALYSIS OF NON-STATIONARY RANDOM Aerospace Engineering. PROCESSES. APPLICATION TO NOISE OF FLYOVER TYPE VERTICAL AXIS WIND TURBINE DEVELOPMENT Final Thesis - Paris-Sud Univ. Report..1 Mar, 1976 - 30 Jun. 1977 Max Ernoult 1979 180 p refs In FRENCH: ENGLISH summary A. E. Walters, J. B. Fanucci, P. W. Hill. and P. G. Migliore Jul. Report will also be announced as translation (ESA-TT-639) 1979 243 p refs (ONERA-NT-1979-4( Avail: NTIS NC A09/MF AOl (Contract EY-76-C-05-5135) - Nonstationary noise detected by fixed microphones was (ORO-5135-77-5( Avail: NTIS HC All/ME AOl studied during the passage of a moving acoustic source (e.g.. Theoretical and experimental research accomplished in aircraft flyover noise), with the objectives of measuring the noise evaluating an innovative concept for vertical axis wind turbines radiation pattern and characterizing the spatial distribution of (VAWT) is described. The concept is that of using straight blades the noise. A time frequency representation of the energy of composed of circulation controlled airfoil sections. The theoretical nonstationary random processes and a series of charts which analysis was developed to determine the unsteady lift and moment allows the adaptation of the spectral analysis processes to the characteristics of multiple-blade cross-flow wind turbines. To treatment of nonstationary signals are presented. The characteris- determine the drag data needed as input to the theoretical analysis, tics pertaining to the nonstationarity of an aircraft noise determined an outdoor test model VAWT was constructed: design details. in the far field, are discussed, Author (ESA)

371 N80-24151

N80-24151 t # National Aeronautics and Space Administration. Langley Research Center, Langley Station, Va. GLADSTONE-DALE CONSTANT FOR CF4 Alpheus W. Burner. Jr. and William K. Goad May 1980 18 p refs (NASA-TM-80228: L-13551) Avail: NTIS HG A02/MF AOl CSCL 20F The Gladstone-Dale constant, which relates the refractive index to density, was measured for CF4 by counting fringes of a two-beam interferometer, one beam of which passes through a cell containing the test gas. The experimental approach and sources of systematic and imprecision errors are discussed. The constant for CF4 was measured at several wavelengths in the visible region of the spectrum. A value of 0.122 cu cm/g with an uncertainty of plus or minus 0.001 cu cm/g was determined for use in the visible region. A procedure for noting the departure of the gas density from the ideal-gas law is discussed. A.R.H.

N80-24210# Committee on Commerce. Science, and Transporta- tion (U. S. Senate). NATIONAL AERONAUTICS AND SPACE ADMINISTRATION AUTHORIZATION ACT, 1981 15 May 1980 20 p A bill referred to the Comm. on Corn., Sci.. and Transportation. 96th Congr., 2nd Sess.. 30 Jan. 1980 (S-96-719) Avail: US Capitol, Senate Document Room An ammendment is presented to the text of a bill authorizing appropriations to the National Aeronautics and Space Administra- tion for research and development, construction of facilities, and research and program development. A.R.H.

N80-24211# Committee on Science and Technology (U. S. House). NASA AUTHORIZATION, 1981 Washington, D.C. GPO 1980 316 p refs Hearings before the Subcomm. on Transportation. Aviation and Commun. of the Comm. on Sci. and Technol.. 96th Congr., 2nd Sess.. no. 95. v. 3, 6-7 Feb. 1980 (GPO-59-528) Avail: Subcommittee on Transportation. Aviation and Communications Specifics of NASA'S proposed aeronautics program are discussed with emphasis on research and technology development in aerodynamics, materials and structures propulsion, avionics, and human factors engineering. Benefits accrued from the ACEE program are examined and activities related to the defense program are summarized. A.R.H.

372 SUBJECT INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Suppl. 125) AUGUST 1980 Typical Subject Index Listing

TITLE _____J{ING EXTENSION f-] Forward acoustic performance of a shock-swallowing Thee analysis of wing-body combinations at moderate high-tip-speed fan (QF-13) r angles of attack --- missile bodies (NASA-TP-1668] U80-23100 I [AD-A07428] ACOUSTIC NOZZLES Acoustic characteristics of jets issuing from ring-and-needle nozzles A80-34404 LJ7LfEPORT ACOUSTIC PROPERTIES NUMBER Aeroacoustj cs --- Russian book L-C C. -S. S-^' 0-11-H, A80-34386 Boise characteristics of supersonic passenger planes A80-34387 The title is used to provide a description of the subject matter. When the title is Acoustic characteristics of jets issuing from insufficiently descriptive of the document content, a title extension is added. ring-and-needle nozzles separated from the title by three hyphens. The NASA or AIAA accession number A80-34404 Acoustic characteristics of the external upper is included in each entry to assist the user in locating the abstract in the abstract surface blowing propulsive-lift configuration section of this supplement. If applicable, a report number is also included as an [AIAA PAPER 80-1063] A80-36001 aid in identifying the document, ACOUSTIC RETROFITTING The DC-8 re-engining program A80-314218 ACOUSTIC STREAMING Acoustic effects on the flow and the noise A spectrum of supersonic jets 1-6 AIRCRAFT A80-34402 Development of the A-6/circulation control wing ACTUATORS flight demonstrator configuration The Eccentuator - A new concept in actuation [AD-A081241] N80-22365 for aerospace mechanisms A-300 AIRCRAFT [AIAA 80-0815] A80-35096 In-flight handling qualities investigation of ADDITIVES Airbus A 310 DLC. Configurations on landing Alkyl derivatives of resorcinol used as approach using the DFVLB-HFB 320 variable antioxidants in jet fuels stability aircraft A80-35801 (DFVLR-PB-79-18] N80-22319 Hannich base used as an antioxidant in jet fuels ABSORBERS (MATERIALS) A80-35802 Suppression of self-oscillations in combustion ADHESIVE BONDING chambers by leans of resonance sound absorbers Honeycomb sandwich joints for primary structure A80-34400 ofaircraft QCSEE fan exhaust bulk absorber treatment evaluation CAI AS 80-0780] A80-35070 [AIAA PAPER 80-0987] A80-35952 AEROACOUSTICS ACCELERATION Aeroacoustics --- Russian book Statistical review of counting accelerometer data A80-34386 for Navy and Marine fleet aircraft Determining the optimal fan silencer design of (AD-A080580] N80-22308 aircraft engines ACCELERATION (PHYSICS) A80-34396 Predictive guidance for interceptors with time lag Acoustic effects on the flow and the noise in acceleration spectrum of supersonic jets A80-32682 A80-34402 ACCUMULATORS Acoustic characteristics of jets issuing from Evaluation of coatings for wear and corrosion - ring-and-needle nozzles Protection in air/fluid accumulators --- for A80-34404 Navy aircraft carriers Helicopter rotor thickness noise A80-34819 [AlAS PAPER 80-1012] A80-35970 ACOUSTIC ATTENUATION Model rotor low frequency broadband noise at Determining the optimal fan silencer design of moderate tip speeds aircraft engines [AIAA PAPER 80-1013] A80-35971 A80-34396 Impact of flight effects on aultitube suppressor Experimental investigation of sound absorption in design a flow-carrying channel with a sound-absorbing [AXAA PAPER 80-1029] A80-35979 lining Acoustic characteristics of the external upper A80-34399 surface blowing propulsive-lift configuration Model studies of acoustic resonators (AIAA PAPER 80-1063] A80-36001 A80-34403 Upper surface blowing noise of the NASA-Ames quiet ACOUSTIC DUCTS short-haul research aircraft Impact of flight effects on multitube suppressor [AIAA PAPER 80-1064] A80-36002 design High-speed-propeller wind-tunnel aeroacoostic [AIAA PAPER 80-1029] A80-35979 results ACOUSTIC EMISSION N80-22344 Experimental study of airfoil trailing edge noise: Propeller aeroacoustic methodologies Instrumentation, methodology and initial results N80-22346 [NASA-CB-163007] N80-22264 Noise generation by jet-engine exhaust deflection ACOUSTIC MEASUREMENTS (ESA-TT-553] N80-23104 Acoustic measurements of three Prop-Fan models On the sound field generated by a fan in a [AIAA PAPER 80-0995] A80-35958 hard-walled baffled duct with uniform flow [NLR-TE-78024-U] N80-23106

A-i

AERODYNAMIC CHARACTERISTICS SUBJECT INDEX

On disturbance fields of moving singularities in AERODYNAMIC FORCES aerodynamics and aeroacoustics Experimental investigations on the vibration of [ESA-TT-570] N80-23269 blades due to a rotating stall AERODYNAMIC CHARACTERISTICS A80-35912 Theoretical investigation of the aerodynamics of Preliminary measurements of aerodynamic damping of double membrane sailwing airfoil sections a transonic compressor rotor A80-33276 A80-36152 Advanced research on helicopter blade airfoils Projectile/sabot discard aerodynamics [ONERA, TP NO. 1979-120] A80-34298 [AD-A080538 ] N80-222 69 Types of leeside flow over delta wings Effect of a flexibly mounted store on the flutter A80-34652 speed of a wing Study on the dynamics of small flight vehicles [NASA-CR-159245) N80-223 56 under gust loading AERODYNAMIC HEATING A80-34653 Numerical flow field program for aerodynamic Unsteady aerodynamic measurement techniques for heating analysis. Volume 1: Equations and turbomachinery research results A80-36142 [AD-A081471] N80-232 55 Processing and analysis of the data from a two Numerical flow field program for aerodynamic spool gas turbine engine heating analysis. Volume 2: Users manual A80-36149 (AD-A081472] 1180-232 60 Aerodynamic characteristics of moving AERODYNAMIC INTERFERENCE trailing-edge controls at subsonic and transonic Calculation of the interference effects between speeds the engine wing and the base wing of a civil and [EAE-TM-STRUC-947] N80-22281 military transport aircraft by the vortex Advanced propeller aerodynamic analysis lattice method N80-22345 I ESA-TT-493 J N80-222 72 Forward acoustic performance of a shock-swallowing TWINTAN: A program for transonic wall high-tip-speed fan (QF-13) interference assessment in two-dimensional wind [NASA-TP-1668] N80-23100 tunnels A study of panel loads and centers of pressure of [NASA-TM-81819] N80-233 32 three different cruciform aft-tail control AERODYNAMIC LOADS surfaces of a wingless missile from Mach 1.60 to Development of a structural overload warning 3.70 system for modern high performance aircraft [NASA-TM-81787] N80-23251 A80-34974 Lift, drag and pitching moment measurements on a Multicyclic control of a helicopter rotor missile body having various boattails at considering the influence of vibration, loads, subsonic and transonic velocities --- in a and control motion transonic wind tunnel test [AIAA 80-0673] A80-34998 [DFVLR-FB-79-15] N80-23265 Unsteady airloads on a harmonically pitching wing Pressure distribution measurements on wedges at with external store subsonic and transonic velocities --- in a [AIAA 80-0733] A80-35037 transonic wind tunnel Unsteady aerodynamics of conventional and [ESA-TT-554] N80-23267 supercritical airfoils Afterbody drag and base pressure measurements on a [AIAA 80-0734] A80-35038 body of revolution at angles of incidence up to Noise from a vibrating propeller alpha = 25 deg at subsonic and transonic Mach [AIAA PAPER 80-1011] A80-35969 numbers --- transonic wind tunnel measurements AERODYNAMIC NOISE [ESA-TT-569] N80-23268 Some unique characteristics of supersonic cruise Summary of data required for the AGARD SMP vehicles and their effect on airport community activity standard aeroelastic configurations - noise two-dimensional configurations [AIAA PAPER 80-0859] A80-32861 [NLR-MP-79015-U] N80-23273 Model rotor low frequency broadband noise at Wind tunnel tests on the Sheriff twin-engined moderate tip speeds light aircraft (AIRA PAPER 80-1013] A80-35971 (BU-241] N80-23277 Experimental study of airfoil trailing edge noise: The aerodynamics of axial flow wind power turbines Instrumentation, methodology and initial results [CSIN-ME-1619] N80-23781 (NASA-CE-163007] N80-22264 AERODYNAMIC COEFFICIENTS AERODYNAMIC STABILITY Note on the yawing moment due to side slip for Possibilities for achieving trimmed minimum drag swept-back wings without sacrificing inherent stability A80-33280 A80-3L$655 Leeward flow over delta wings at supersonic speeds Full-scale wind tunnel-investigation of the [NASA-TM-81187] N80-23250 Advanced Technology Light Twin-Engine airplane AERODYNAMIC CONFIGURATIONS (ATLIT) --- Langley full scale tunnel Calculation of the interference effects between (NASA-TP-1591] N80-22266 the engine wing and the base wing of a civil and AERODYNAMICS military transport aircraft by the vortex Modern fluid dynamics of subsonic and transonic lattice method flight (ESA-TT-493] N80-22272 [AIRA PAPER 80-0861] A80-33274 High-speed-propeller wind-tunnel aeroacoustic Modern fluid dynamics of supersonic and hypersonic results flight N80-22344 [A.IAA PAPER 80-08621 A80-33275 Development of the A-6/circulation control wing Wake vortex trajectories of low flying spray flight demonstrator configuration aircraft [AD-A08 1241] N80-22365 A80-34595 An analytical study of tilt proprotor aircraft Direct and inverse problems of flow over a wing of dynamics in airplane cruise configuration finite span in the linear formulation including the effects of fuselage longitudinal A80-34712 rigid body motion Unsteady aerodynamics of conventional and 980-23297 supercritical airfoils Airplane wing leading edge variable camber flap (AIAA 80-07343 A80-35038 N80-23514 Activities in aerospace research AERODYNAMIC DRAG N80-22274 Reduction of aerodynamic drag of external spray Aerodynamics of the new generation of combat booms and nozzles used on DC-6 aircraft aircraft with delta wings A80-34596 [NASA-TM-75793] 1180-22306 Application of two design methods for active flutter suppression and wind-tunnel test results [NASA-TP-1653] N80-22737

A-2 SUBJECT INDEX AIR TRANSPORTATION

Active control of asymmetric vortex effects AILERONS [AD-A081648] N80-23254 Description of an experimental (hydrogen peroxide) On disturbance fields of moving singularities in rocket system and its use in measuring aileron aerodynamics and aeroacoustics and rudder effectiveness of a light airplane [ESA-TT-570] N80-23269 NASA-TP-1647] 880-22358 AEROELASTICIT! Economical processing of fiber-reinforced Design for active flutter suppression and gust components with thermal expansion molding alleviation using state-space aeroelastic modeling (NASA-TN-75738] 880-22412 [AIAA 80-0766] A80-35058 AIR CARGO Aeroelastic tailoring of a forward swept wing and Air .deployment of satellite-tracked drifters comparisons with three equivalent aft swept wings A80-36291 [AIAA 80-0794] A80-35076 AIR COOLING Aeroelastic tailoring of forward swept composite Nonlinear, three-dimensional finite-element wings analysis of air-cooled gas turbine blades [ALAA 80-0795] A80-35077 [NASA-TP-1669] 880-22734 A wind tunnel demonstration of the principle of AIR DEFENSE aeroelastic tailoring applied to forward swept Air Defense Ground environment - A case for wings automation [AIAA 80-0796] A80-35078 A80-34154 Status of NASA full-scale engine aeroelasticity IF? for air defence aircraft --- Identification research Friend or Foe A80-35906 A80-34157 Propeller dynamic and aeroelastic effects Laser Target Marker /designator/ and Ranger 880-22348 A80-34187 Unsteady aerodynamic forces on a subsonic Design considerations for an active laser seeker rectilinear cascade of blades A80-34189 [P88-90007] 880-23266 The impact of global positioning system on An aeroelastic analysis of the Sheriff wing guidance and controls systems design of military [BU-2314] 880-23274 aircraft. Volume 2A: Specific application Investigation into compressor aeroelastic study no. 1, close air support instabilities in a wind tunnel for a rectilinear [AGARD-AE-147-VOL-25] N80-23303 cascade of blades AIR INTAKES [PNR-90011] 880-23337 Gasdynawic analysis of gas-turbine combustion Status of NASA full-scale engine aeroelasticity chambers with graduated air admission research A80-33825 [NASA-TM-81500] 880-23678 Influence of external conditions on the generation AERONAUTICAL ENGINEERING and intensity of vortices at air-intakes Transonic wing DFVLR-F4 as European test model A80-34238 [NASA-TM-75752] 880-22260 AIR NAVIGATION Synthesis of a theoretical approach for employing Navigation for a group of aircraft /Automation of adaptive configuration management in data processing and flight control procedures/ aeronautical weapon system programs Russian book 880-23196 A80-33177 The impact of fuels on aircraft technology through Optimal estimation applied to redundant strapped the year 2000 down inertial sensors for navigation and flight [NASA-TM-81492] 880-23472 control National Aeronautics and Space Administration N80-22295 Authorization Act, 1981 Measurement of [S-96-719] 880-24210 interference-to-navigation/communication NASA authorization, 1981 avionics from cable television (CATV) systems (GPO-59-528] 880-24211 [AD-A081430] 880-23530 AERONAUTICS AIR POLLUTION On disturbance fields of moving singularities in Atmospheric dispersion of high velocity jets aerodynamics and aeroacoustics [AD-A081612] 880-23321 [ESA-TT-570] 880-23269 AIR SAMPLING AEROSPACE ENGINEERING Project filter holder. Tests on 25 mm dust filter Activities in aerospace research holders N80-22274 [IG-TNO-P-1638] 880-23887 AEROSPACE INDUSTRY AIR TRAFFIC CONTROL Air transportation 2000 - A challenge for new Technology to increase airport capacity technology [RIAR PAPER 80-0920] 180-32890 (AIAA PAPER 80-0945] A80-32899 The automatization of the detection of collision AEROSPACE TECHNOLOGY TRANSFER risks for French air traffic control Activities in aerospace research A80-34226 N80-22274 Pitot-static system - Errors and calibrations AFTERBODIES A80-34593 Analysis of experiments on the effects of jet Opportunities analysis of potential advanced pluses on pressure distribution over a vortex systems separation standards cylindrical afterbody at transonic speeds [AD-A081479] N80-23281 [AD-A081647] 880-23259 Software impact of selected en route ATC computer Afterbody drag and base pressure measurements on a replacement strategies body of revolution at angles of incidence up to [AD-A081478] N80-23286 alpha = 25 deg at subsonic and transonic Each Procedural feasibility of reduced spacing under numbers --- transonic wind tunnel measurements WVAS operation with applications to Atlanta and [BSA-TT-569] 880-23268 C Rare AGRICULTURAL AIRCRAFT (AD-A081480] 880-23287 New mathematical formula for the cropduster A flight investigation of system accuracies and operational cycle operational capabilities of a general A80-342314 aviation/air transport area navigation . system Wake vortex trajectories of low flying spray (B NA V) aircraft [AD-A081646] 880-23288 A80-34 595 AIR TRANSPORTATION Reduction of aerodynamic drag of external spray Air transportation 2000 - A challenge for new booms and nozzles used on DC-6 aircraft technology A80-34596 [AIAA PAPER 80-0945] A80-32899 All-ic HELICOPTER Outlook for advanced concepts in transport aircraft AN-is high-survivable transmission system [NASA-TM-81810] 880-23283 [AD-A080568] 880-22311

A-3

AIRBORNE EQUIPMENT SUBJECT INDEX

AIRBORNE EQUIPMENT Large-scale and small-scale flammability tests for 1FF for air defence aircraft --- Identification airplane cabin materials Friend or Foe A80-34787 A80-34157 Costs of graphite composite fabrication and repair Airborne radar coherent transmitters of aircraft structures A80-34159 A80-34810 Airborne PLIR - Experiences from flight tests Current and projected use of carbon composites in A80-34174 United States aircraft Validation Methods Research for Fault-Tolerant A80-34840 Avionics and Control Systems: Working Group Built-up low-cost advanced titanium structures Meeting, 2 /BL AT S/ (NASA-CP-2130] 880-23008 [AIAA 80-0745] A80-35045 AIRBORNE/SPACEROREB COMPUTERS Advanced composite structure repair guide Experiences of a 50 MBPS video recording and (AIAA 80-0774) A80-35065 processing system for FLIR images Repair of advanced composite structures --- in A80-34 163 damaged aircraft Advanced digital data processing for onboard [AIAA 80-0776] A80-35066 missile guidance and control Damage tolerant design and test considerations in A80-34179 the engine structural integrity program --- for Aurora /CP-1 140/ aircraft operational software system aircraft turbines A80-34165 [AIAR 80-0784] A80-35072 A microprocessor controlled system for determining Aeroelastic tailoring of a forward swept wing and the height of clouds comparisons with three equivalent aft swept wings A80-34188 [AIAA 80-0794] A80-35076 AIRCRAFT ACCIDENT INVESTIGATION Aeroelastic tailoring of forward swept composite Technology requirements as derived from accident wings rate analysis [AIAA 80-0795] A80-35077 (AIAA PAPER 80-0918) A80-32888 A wind tunnel demonstration of the principle of Selective methods of determining the range of aeroelastic tailoring applied to forward swept engine operation in aircraft crash wings investigations. I (AIAA 80-0796) A80-35078 A80-33106 AIRCRAFT CONTROL Selected methods for defining engine operating Flight control systems. VII ranges in the investigation of aircraft A80-32693 accidents. II Minimum sensitivity controllers with application A80-35184 to VTOL aircraft Survey of forced and precautionary landing costs A80-32759 [AD-A080110] N80-22294 Navigation for a group of aircraft /Automation of Carburetor ice: A review data processing and flight control procedures/ [TR-77-19] N80-23280 Russian book AIRCRAFT ACCIDENTS A80-33177 Emergency landings on a carpet of foam Investigation of internal control laws for A80-33292 wing/store flutter suppression AIRCRAFT APPROACH SPACING [AIAA 80-0764] A80-35056 Opportunities analysis of potential advanced Design for active flutter suppression and gust vortex systems separation standards alleviation using state-space aeroelastic modeling [AD-A081479] 880-23281 [AIAA 80-0166] A80-35058 Procedural feasibility of reduced spacing under F-16 flutter suppression system investigation WVAS operation with applications to Atlanta and [AIAA 80-0768] A80-35060 O'Hare Recent development of the TF-17 active flutter (AD-A081480] 880-23287 suppression system AIRCRAFT CARRIERS [AIAA 80-0769] A80-35061 Optimal integrated inertial navigation: An actual Wind tunnel investigation of active controls example - The R.P.A. aircraft carrier reference technology applied to a DC-10 derivative system [AIAA 80-0771] A80-35062 A80-34227 Toll-scale wind tunnel-investigation of the Aircraft carrier exposure tests of aluminum alloys Advanced Technology Light Twin-Engine airplane [AD-A081060] 880-23433 (ATLIT) --- Langley full scale tunnel AIRCRAFT COMMUNICATION [NASA-TP-1591] N80-22266 Measurement of The application of output predictive digital interference-to-navigation/communication control to wing flutter suppression and terrain avionics from cable television (CATV) systems following problems [AD-6081430] 880-23530 (AD-A080419) 1180-22361 AIRCRAFT COMPARTMENTS Definition of a two level control system for Large-scale and small-scale flammability tests for nonlinear aircraft motion airplane cabin materials [ONEBA-NT-1979-7] 1180-22364 A80-34787 Static calibration of a two-dimensional wedge AIRCRAFT CONFIGURATIONS nozzle with thrust vectoring and spanwise blowing CLST' s wing-in-ground effect vehicles (NASA-TM-81161] 880-23317 amphibious aircraft design Definition of a two-level control system for A80-33105 nonlinear motion of an aircraft In-flight handling qualities investigation of [ESA-TT-614] 1180-23330 Airbus A 310 DLC. Configurations on landing Design, development and implementation of an approach using the DFVLR-HFB 320 variable active control system for load alleviation for a stability aircraft commercial transport airplane (DFVLB-FB-79-18) 880-22319 (AGARI-AR-683] 1180-23331 NASA authorization, 1981 AIRCRAFT DESIGN (GPO-59-528] 880-24211 Long range very large aircraft supply system for AIRCRAFT CONSTRUCTION MATERIALS civil/military application with special emphasis Release-rate calorimetry of multilayered materials on water-based aircraft for aircraft seats [AIAA PAPER 80-0903J A80-32882 A 80-34 223 Technology requirements and readiness for very 801 policy and techniques for advanced composites large aircraft nondestructive inspection (AIAA PAPER 80-0935) A80-32897 A80-34 765 Advanced high speed commercial aircraft - 2000 Airworthiness certification of composite [AIAA PAPER 80-0937] A80-32898 components for civil aircraft - The role of Air transportation 2000 - A challenge for new non-destructive evaluation technology AS 0-34766 [AIAA PAPER 80-0945] A80-32899

A-4

SUBJECT INDEX AIRCRAFT HAZARDS

CLSTs wing-in-ground effect vehicles Experimental investigation of flutter in Did-stage amphibious aircraft design compressor designs --- for aircraft axial flow A80-33105 gas turbine engines Modern fluid dynamics of supersonic and hypersonic [lilA 80-0786) 180-35073 flight Selected methods for defining engine operating [AAA PAPER 80-0862] 180-33275 ranges in the investigation of aircraft Possibilities for achieving trimmed minimum drag accidents. II without sacrificing inherent stability 180-35184 180-34655 The design, development and operation of gas The outside has to be bigger than the inside turbine radio telemetry systems volume requirements calculation and optimal 18 0-36 154 design of supersonic aircraft Impact of new instrumentation on advanced turbine [lIlA 80-0726] 180-35031 research CAD produced aircraft drawings A80-36155 [lIlA 80-0732] 180-35036 Calculation of the interference effects between Preliminary design of composite wing-box the engine wing and the base wing of a civil and structures for global damage tolerance military transport aircraft by the vortex (lIlA 80-0755] 180-35049 lattice method Investigation of internal control laws for [ESA-TT-493] 1180-22272 wing/store flutter suppression Two-dimensional finite-element analyses of (hIll 80-0764) 180-35056 simulated rotor-fragment impacts against rings Design for active flutter suppression and gust and beams compared with experiments alleviation using state-space aeroelastic modeling [NASA-CE-159645] 1180-22323 [lilA 80-0766] 180-35058 Performance deterioration based on existing Aeroelastic tailoring of a forward swept wing and (historical) data; JT9D jet engine diagnostics comparisons with three equivalent aft swept wings program [1111 80-0794] 180-35016 (NASA-CE-135448) 1180-22324 Aeroelastic tailoring of forward swept composite Design study: A 186 kV lightweight diesel wings aircraft engine (lIlA 80-0795] 180-35077 [NASA-CR-3261] 1180-22326 Structural design loads for future airplanes General Aviation Propulsion [lilA 60-0813] 180-35094 (NASA-cP-2 126) 1180-22327 Integrated thermal-structural finite element An overview of NASA research on positive analysis --- for applications to hypersonic displacement general-aviation engines transport design N80-22336 [AIAA 80-0717] 180-35098 The spark-ignition aircraft piston engine of the Analytical study of interior noise control by future fuselage design techniques on high-speed N80-22337 propeller-driven aircraft Lightweight diesel aircraft engines for general [1111 PAPER 80-1001] 180-35964 aviation The design, development and operation of gas 1180-22338 turbine radio telemetry systems Advanced rotary engine studies A80-36154 N80-22339 Transonic wing DPVLR-F4 as European test model Positive displacement type general-aviation [NASA-T11-75752] 1180-22260 engines: Summary and concluding remarks Supercritical wing design studies for transport N80-22340 aircraft. Volume 2: Theoretical studies Preliminary study of advanced turboprop and [BNT-FB-w-79-07-VOL-2] 1180-22276 turboshaft engines for light aircraft --- cost Parametric study of helicopter aircraft systems effectiveness costs and weights [NASA-T11-81467] 1180-22350 (NASA-CR-152315] 1180-22305 Investigation of lubricant concepts applicable to Aerodynamics of the new generation of combat future Navy aircraft propulsion systems aircraft with delta wings [AD-A079410] 1180-22351 [NASA-TM-75793] 1180-22306 Development of improved-durability plasma sprayed Civil component program wing section. ceramic coatings for gas turbine engines Predimensioning of a supercritical wing [NASA-TN-81512] 1180-23313 (ESA-TT-542] 1180-22317 Turbopropulsion combustion technology assessment AiResearch QCGAT engine, airplane, and nacelle [ID-A080748] N80-23323 design features AIRCRAFT EQUIPEENT 1180-22328 Aircraft radio equipment adjustment and QCGAT aircraft/engine design for reduced noise and maintenance technology --- Russian book emissions A80-32845 N80-22331 Release-rate calorimetry of multilayered materials minimum mass sizing of a large low-aspect ratio for aircraft seats airframe for flutter-free performance A80-34223 [NASA-TN-81818] 1180-23683 Effects of electric fluctuations in electric power AIRCRAFT ENGINES systems of flight vehicles The future of civil turbo-fan engines A80-35185 [1111 PAPER 80-0893] A80-32876 AIRCRAFT FUELS Long range very large aircraft supply system for The impact of fuels on aircraft technology through civil/military application with special emphasis the year 2000 on water-based aircraft [1111 PAPER 80-0896] 180-35898 [1111 PIPER 80-0903] 180-32882 Research on diamantane and other high density Selective methods of determining the range of (AD-A080749] N80-23474 engine operation in aircraft crash AIRCRAFT 0010111CR investigations. I I new algorithm for horizontal capture trajectories A80-33106 [NASA-TE-81186] 1180-22297 Investigation of the stress distribution in the Theory of disturbance-utilizing control with surface layer of aircraft engine components application to missile intercept problems 180-34235 [10-1081110) 1180-23329 Aircraft gas turbine materials and processes AIRCRAFT HAZARDS A80-34631 Lightning damage mechanisms and simulation Damage tolerant design and test considerations in techniques --- for aircraft protection the engine structural integrity program --- for 180-34664 aircraft turbines Storm hazards 1 79: F-106B operations summary (lilA 80-0784] 180-35072 [NASA-TB-81779J 1180-23282

1-5

AIRCRAFT HYDRAULIC SYSTEMS SUBJECT INDEX

AIRCRAFT HYDRAULIC SYSTEMS A collection of formulas for calculation of The Eccentuator - A new concept in actuation rotating blade noise - Compact and noncompact for aerospace mechanisms source results [AIAA 80-0815] A80-35096 (AIAA PAPER 80-0996] A80-35959 AIRCRAFT INDUSTRY Propeller light aircraft noise at discrete Aeropropulsion in year 2000 frequencies [AIAA PAPER 80-0914] A80-32887 (AIAA PAPER 80-09973 A80-35960 AIRCRAFT INSTRUMENTS Prediction of the interior noise levels of A solid state /CCD/ cockpit television system high-speed propeller-driven aircraft A80-34190 [AIAA PAPER 80-0998] A80-35961 General aviation altimetry errors for collision Noise control prediction for high-speed, avoidance systems propeller-driven aircraft A80-35404 [AIAA PAPER 80-0999] A80-35962 AIRCRAFT LARDING An analytical model for study of interior noise Emergency landings on a carpet of foam control for high-speed, propeller-driven aircraft A8 0-33 292 [AIAA PAPER 80-1000] A80-35963 New commutated Doppler microwave landing system Analytical study of interior noise control by A80-36019 fuselage design techniques on high-speed Survey of forced and precautionary landing costs propeller-driven aircraft (AD-A080110) N80-22294 [AIAA PAPER 80-1001) A80-35964 Analysis of the effects of higher order control Noise from a vibrating propeller systems on aircraft approach and landing [AIAA PAPER 80-1011] A80-35969 longitudinal handling qualities Helicopter rotor thickness noise (AD-A080519) 1180-22362 [AIAA PAPER 80-1012] A80-35970 A means of specifying a standard reference vet Fan noise caused by the ingestion of anisotropic surface for military aircraft turbulence - A model based on axisymmetric [S/T-MENO-1/79] 1180-22371 turbulence theory Investigation of landing flare in presence of wind [AIAA PAPER 80-1021) A80-35977 shear Noise transmission and attenuation by stiffened [DFVLR-FB-79-20] 1180-23299 panels lRemote sensing methods for determination of slant [AIAA PAPER 80-1034] A80-35982 range visibility Propeller signatures and their use --- aircraft (DPVLR-FB-79-1 4] N80-23759 noise and vibration measurements and analysis AIRCRAFT NAIRTERANCE [AIAA PAPER 80-1035) A80-35983 Aircraft radio equipment adjustment and Noise transmission and control for a light, maintenance technology --- Russian book twin-engine aircraft A80-32845 [AIAA PAPER 80-1036] A80-35984 Costs of graphite composite fabrication and repair Prediction of noise constrained optimum takeoff of aircraft structures procedures A80-34810 [AflA PAPER 80-1055] A80-35996 Advanced composite structure repair guide Comparison of aircraft noise-contour prediction [AIAA 80-0774] A80-35065 programs Repair of advanced composite structures --- in [AIAA PAPER 80-1057] A80-35998 damaged aircraft Upper surface blowing noise of the NASA-Ames quiet [AIRA 80-0776] A80-35066 short-haul research aircraft Analysis of helicopter maintenance fault isolation [AIAA PAPER 80-1064) A80-36002 criteria/techniques Theoretical prediction of nonlinear propagation [AD-A080596] N80-22257 effects on noise signatures generated by Survey of forced and precautionary landing costs subsonic or supersonic propeller or rotor-blade [AD-A080110] N80-22294 tips AIRCRAFT MANEUVERS [NASA-TP-1660] 1180-22265 Improved maneuver criteria evaluation program General Aviation Propulsion flight path equations of motion for the h-58 and [NASA-CP-2126) 1180-22327 Oh-58a aircraft Evaluating and minimizing noise impact due to [AD-A080408] 1180-22310 aircraft flyover Air combat maneuvering performance measurement [NASA-CE-153187] 1180-23874 [AD-A077429] 1180-23336 Spectral analysis of non-stationary random Mathematical model for the separation of gust and processes. Application to noise of flyover type manoeuvre loads of civil aircraft [ONERA-NT-1979-4) 1180-24134 [P8-141 (1979) ] 1180-23674 AIRCRAFT PARTS AIRCRAFT MODELS Problems involved in the detection of aircraft Simulation of high bypass ratio engine jet noise defects flight effects by model jet wind tunnel test A80-33108 [AIAA PAPER 80-1030] A80-35980 Effect of some aircraft loading program Easy-ACS dynamic analysis. User's manual modifications on the fatigue life of open hole [AD-A081160] 1180-23258 specimens AIRCRAFT NOISE A80-36076 Advanced rotorcraft noise AIRCRAFT PERFORMANCE [AIRA PAPER 80-0857] A80-32860 Minimum sensitivity controllers with application Aeroacoustics --- Russian book to VTOL aircraft A80-34386 A80-32759 Propagation of acoustic waves in a nonuniformly Modern fluid dynamics of subsonic and transonic heated medium flight A80-34388 (AIAA PAPER 80-0861) A80-33274 Determining the optimal fan silencer design of New mathematical formula for the cropduster aircraft engines operational cycle A80-3'4396 A80-34234 Progress and trends in propeller/prop-fan noise Development of a structural overload warning technology system for modern high performance aircraft (AIRA PAPER 80-0856] A80-35907 A80-34974 Study and experimental tests of fibrous acoustic Full-scale wind tunnel-investigation of the treatment for reduction of fan noise from 1F3-1 Advanced Technology Light Twin-Engine airplane turbofan engine (ATLIT) --- Langley full scale tunnel [AIAA PAPER 80-0988) A80-35953 [NASA-TP-1591] 1180-22266 Experimental verification of propeller noise Aerodynamics of the new generation of combat prediction aircraft with delta wings [AIAA PAPER 80-0994] A80-35957 [NASA-TM-75793] 1180-22306

A-6

SUBJECT INDEX AIRFRAMES

A practical method for predicting roughness Development of fire-resistant, low smoke effects on aircraft generating, thermally stable end items for (221-10-1413] 880-22316 commercial aircraft and spacecraft using a basic In-flight handling qualities investigation of polyimide resin Airbus A 310 DLC. Configurations on landing [NASA-CR-160576] 880-22492 approach using the DFVLR-HFB 320 variable Failure analysis in aviation stability aircraft - [NLR-NP-78028-U] 880-23284 (DFVLR-FB-79-18] 880-22319 The failure of aircraft structures Advanced turboprop potential for high speed [NLE-MP-78040-U] 880-23285 V80-22343 Flight service evaluation of Kevlar-49 epoxy AIRCRAFT RELIABILITY composite panels in wide-bodied commercial Problems involved in the detection of aircraft transport aircraft defects [NASA-CR-159231] 880-23371 A80-33108 An investigation of residual stresses in simulated Airworthiness certification of composite wing panels of 7075-T6 aluminum components for civil aircraft - The role of [AD-A080863] 880-23693 non-destructive evaluation AIRCRAFT SURVIVABILITY 180-34766 Economic life criteria for metallic airframes A quantitative assessment of the variables [lilA 80-0748] 180-35046 involved in crack propagation analysis for 18-1s high-survivable transmission system in-service aircraft [AD-A080568) 880-22311 [AIAA 80-0752] 180-35047 AIRCRAFT TIRES AIRCRAFT SAFETY Flight test evaluation of airborne tire pressure Storm hazards 1 79: 2-1068 operations summary indicating systems [NASA-TN-81779] 880-23282 (AD-A081598) 880-23305 AIRCRAFT SPECIFICATIONS AIRCRAFT EARNS Development and application concepts for trainer Wake vortex trajectories of low flying spray and combat-trainer versions of combat jet aircraft aircraft A80-35183 A80-34595 A means of specifying a standard reference wet Procedural feasibility of reduced spacing under surface for military aircraft WVAS operation with applications to Atlanta and [S/1-NENO-1/79] 880-22371 O'Hare AIRCRAFT SPIN [AD-A081480] 880-23287 A spin-recovery parachute system for light AIRFOIL PROFILES general-aviation airplanes Theoretical investigation of the aerodynamics of 880-23512 double membrane sailwing airfoil sections AIRCRAFT STABILITY A80-33276 An optimization method for the determination of Advanced research on helicopter blade airfoils the important flutter modes [CREBA, TP NO. 1979-120) A80-34298 [1111 80-0790] 180-35074 Unsteady aerodynamics of conventional and Review of nonstationary gust-responses of flight supercritical airfoils vehicles (lilA 80-0734] A80-35038 [lilA 80-0703] A80-35097 System to measure the pressure distribution on fan Definition of a two level control system for aerofoil surfaces during flutter conditions nonlinear aircraft motion A80-36144 (ONERA-NT-1979-7] 880-22364 AIRFOILS AIRCRAFT STRUCTURES Numerical design and optimization of propellers. Ii Developments in ultrasonic welding for aircraft 180-33107 A80-34797 Low profile strain gage applications telemetered Comparison of surface treatments of aluminium and from rotating machinery their influence on long term strength of metal A80-36153 bonds Experimental study of airfoil trailing edge noise: A80-34805 Instrumentation, methodology and initial results Current and projected use of carbon composites in [NASA-CB-163007] 880-22264 United States aircraft A comparison of various numerical methods for 180-34 840 calculating supercritical inviscid isentropic On experimental versus theoretical incipient flow over two-dimensional aerofoils buckling of narrow graphite/epoxy plates in [S/T-MENO-4/75] 880-22278 compression A comment on the origin of endwall interference in [AIAA 80-0686] A80-35007 wind tunnel tests of aerofoils Composite wing/fuselage integral concept [RAE-TR-AERO-1816] 880-22280 (AIAA 80-0744] A80-35044 Advanced propeller aerodynamic analysis Built-up low-cost advanced titanium structures 880-22345 / BL AT S/ Propeller aeroacoustic methodologies [AIAA 80-07145] 180-35045 N80-22346 Analysis of cracks at attachment lugs NASA propeller noise research [AIAA 80-0753] A80-35048 N80-22347 Release-rate calorimetry of multilayered materials Propeller dynamic and aeroelastic effects for aircraft seats - 880-22348 [lilA 80-0759) A80-35052 The VIBRA-8 subsonic aerodynamic nuclear gust Honeycomb sandwich joints for primary structure vulnerability Code of aircraft [AD-A081722] 880-23256 (AAA 80-0780] A80-35070 Core compressor exit stage study, 2 Finite element analysis of 2-16 aircraft canopy [NASA-CB-159812] 880-23312 dynamic response to bird impact loading Airplane ring leading edge variable camber flap (AIAA 80-0804] 180-35086 N80-23514 Durability and consistency of composite components AIRFRAME MATERIALS for L-1011 aircraft vertical fins Economic life criteria for metallic airframes [AAA 80-0811] A80-35092 [AIAA 80-0748] A80-35046 Technology of graphite-resin composite materials AIRFRAMES and their application in the aeronautical industry A quantitative assessment of the variables A80-35771 involved in crack propagation analysis for Static tests at model scale indicating in-service aircraft rear-fuselage installation effects on engine [AIAA 80-0752] A80-35047 exhaust noise Elevated temperature structural testing of [AIAA PAPER 80-10146] A80-35991 advanced missiles [hAl 80-0812] 180-35093

A-7

AIRPORT PLANNING SUBJECT INDEX

Airframe self-noise studies on the Lockheed 1 1011 ANTENNA DESIGN TriStar aircraft A broadband, circularly polarized, phase steered [AIAA PAPER 80-1061] A80-36000 array Investigations into an active vibration isolation A80-34166 system for helicopters with rigid and elastic Frequency independent sidelobe suppression and airframe modeling lobesharpening using broad beam antennas (ESA-TT-531) 880-22315 A80-34178 Minimum mass sizing of a large low-aspect ratio ANTENNA RADIATION PATTERNS airframe for flutter-free performance Electronically steered antennas [NASA-T8-81818] 880-23683 A80-34169 AIRPORT PLANNING _ANTIICING ADDITIVES Technology to increase airport capacity Carburetor ice: A review [LIAR PAPER 80-0920] A80-32890 880-23278 A matrix method for airport Site evaluation Carburetor ice: A review A80-33293 [18-79-9] 880-23279 The importance of runway capacity - An analytical Carburetor ice: A review approach [TR-77-19) 880-23280 A80-33294 ANTIOXIDANTS AIRPORTS Alkyl derivatives of resorcinol used as Some unique characteristics of supersonic cruise antioxidants in jet fuels vehicles and their effect on airport community A80-35801 noise Hannich base used as an antioxidant in jet fuels [LIAR PAPER 80-0859] A80-32861 A80-35802 AIRSPACE ANTISKID DEVICES A flight investigation of system accuracies and Trials to compare the stopping performance of operational capabilities of a general three anti-skid systems and to demonstrate aviation/air transport area navigation System methods of determining aircraft stop distances (RNAV) on the standard military reference wet surface [AD-A081646] N80-23288 [S/I-MEMO-3/79] 880-22318 ALGORITHMS APPLICATIONS OF MATHEMATICS A new algorithm for horizontal capture trajectories A matrix method for airport site evaluation [NASA-TN-81186] 880-22297 A80-33293 ALKYL COMPOUNDS APPROACH CONTROL Alkyl derivatives of resorcinol used as Analysis of the effects of higher order control antioxidants in jet fuels systems on aircraft approach and landing longitudinal handling qualities ALTIMETERS [AD-A080519] 880-22362 Pitot-static system - Errors and calibrations APPROPRIATIONS A80-34593 National Aeronautics and Space Administration General aviation altimetry errors for collision Authorization Act, 1981 avoidance systems [5-96-719] 180-24210 A80-35404 ARMED FORCES (UNITED STATES) Determining sea-ice boundaries and ice roughness Analysis of helicopter maintenance fault isolation using GEOS-3 altimeter data criteria/techniques [NASA-CR-156862] 880-22758 [AD-A080596] N80-22257 ALUMINUM ARRESTING GEAR Preliminary design of composite wing-box Investigation of landing flare in presence of wind structures for global damage tolerance shear - [AIAA 80-0755] A80-35049 [DPVLR-FB-79-20] N80-23299 ALUMINUM ALLOYS ASPECT RATIO Comparison of surface treatments of aluminium and Core compressor exit stage study, 2 their influence on long term strength of metal [NASA-CR-159812] 880-23312 bonds ATLIT PROJECT A80-34805 Full-scale wind tunnel-investigation of the Endurance of riveted lap joints (aluminum alloy Advanced Technology Light Twin-Engine airplane sheet and rivets) (ATLIT) --- Langley full scale tunnel [ES 00-79031] N80-22723 [NASA-TP-1591] 880-22266 Fatigue crack propagation in aluminum alloy sheet ATMOSPHERIC BOUNDARY LATER materials under maneuver spectrum and constant Propagation of acoustic waves in a nonuniformly amplitude loading heated medium [NLR-MP-78025-U] 880-22749 A80-34388 Aircraft carrier exposure tests of aluminum alloys ATMOSPHERIC ELECTRICITY [AD-A081060] 880-23433 A survey of the high frequency effects associated Gust severity effects on fatigue crack propagation with the lightning discharge in aluminum alloy sheet materials [OUEL-1290/79] 880-23590 [NLR-NP-78041-U] 880-2311149 ATMOSPHERIC TEMPERATURE - An investigation of residual stresses in simulated Propagation of acoustic waves in a nonuniformly wing panels of 7075-T6 aluminum heated medium (AD-A080863) 880-23693 A80-34388 AMPHIBIOUS AIRCRAFT ATMOSPHERIC TURBULENCE CLST' s wing-in-ground effect vehicles Mathematical model for the separation of gust and amphibious aircraft design manoeuvre loads of civil aircraft &80-33105 [28-141(1979)) N80-236714 ANALOG DATA ATTITUDE INDICATORS Plight test evaluation of airborne tire pressure Pilot assessment of two computer-generated display indicating systems - formats for helicopter instrument approach [AG-A081598] 880-23305 [NASA-TM-80151] N80-22321 ANNULAR NOZZLES AUTOMATIC CONTROL Noise suppression due to annulus shaping of an Navigation for a group of aircraft /Automation of inverted-velocity-profile coaxial nozzle data processing and flight control procedures/ A80-35498 Russian book A unique coannular plug nozzle jet noise A80-33177 prediction procedure Validation Methods Research for Fault-Tolerant [AIRL PAPER 80-1007] A80-35968 Avionics and Control Systems: Working Group Prediction of flyover noise from single and Meeting, 2 coannular jets [NASA-CP-2130] N80-23008 [AIAA PAPER 80-1031] A80-35981 Navigation, guidance, and control for helicopter automatic landings (NASA-TP-1649] 880-23326

A-8 SUBJECT INDEX C-135 AIRCRAFT

AUTOMATIC FLIGHT CONTROL BIRD-AIRCRAFT COLLISIONS Design of an integrated flight/fire control system Finite element analysis of P-16 aircraft canopy including movable gun and gimbaled line of sight dynamic response to bird impact loading tracker [AIAA 80-08014] 880-35086 580-22355 BLADE TIPS Control system design using vector-valued Laser-optical blade tip clearance measurement system performance criteria with application to the A80-36137 control rate reduction in parameter insensitive Forward acoustic performance of a shock-swallowing control systems high-tip-speed fan (QP-13) [ESA-TT-512-REV] 4180-22363 [NASA-TP-1668] 1180-23100 AUTOMATIC LANDING CONTROL Surface pressure measurements at two tips of a Navigation, guidance, and control for helicopter model helicopter rotor in hover automatic landings [NASA-CB-3281] 1180-23252 [NASA-TP-1649] 1180-23326 BLAST DEFLECTORS AUTOMATIC PILOTS Noise generation by jet-engine exhaust deflection Midcourse guidance for fire and forget missile - [ESA-TT-553] H80-23104 Modification of present homing missile BOATTAILS 880-34180 Lift, drag and pitching moment measurements on a AUTOMATIC TEST EQUIPMENT missile body having various boattails at A laser-two-focus /L2F/ velocimeter for automatic subsonic and transonic velocities --- in a flow vector measurements in the rotating transonic wind tunnel test components of turbomachines [DFVLR-PB-79-15] 880-23265 A80-36138 BODIES OF REVOLUTION AUTONATION Afterbody drag and base pressure measurements on a Air Defense Ground environment - A case for body of revolution at angles of incidence up to automation alpha = 25 deg at subsonic and transonic Bach 880-314 154 numbers --- transonic wind tunnel measurements AUTOMOBILE ENGINES [ESA-TT-569] 880-23268 Development of high temperature resistant ceramic BODY-WING CONFIGURATIONS parts for gas turbines Composite wing/fuselage integral concept [BMFT-FB-T-79-09] N80-23324 [AIAA 80-0744] 880-35044 AVIONICS BOEING AIRCRAFT Aircraft radio equipment adjustment and CAD produced aircraft drawings maintenance technology --- Russian book [AAA 80-0732] - 180-35036 880-32845 BOOMS (EQUIPNENT) 1FF for air defence aircraft --- Identification Reduction of aerodynamic drag of external spray Friend or Poe booms and nozzles used on Dc-6 aircraft A80-34157 A80-34596 The modular survivable radar --- LSI and microwave Generation of a representative load sequence for circuit technologies for military avionics the fatigue testing of Macchi MB 3268 spar booms A80-34158 [AD-8074155] 1180-22309 Airborne radar coherent transmitters BOUNDARY LATER CONTROL 880-34159 Development of the 8-6/circulation control wing Aurora /CP-140/ aircraft operational software system flight demonstrator configuration 880-34185 [AD-A081241] 1180-22365 A solid state /CCD/ cockpit television system BOUNDARY LAYER EQUATIONS 880-34190 Calculation of the turbulent boundary layer on an Parametric study of helicopter aircraft systems infinite swept ring using a three-dimensional costs and weights mixing length model [NASA-CE-152315] 4180-22305 (ESA-TT-5314] N80-22273 AXIAL FLOW BOUNDARY LATER TRANSITION Unsteady pressure measurements and data analysis Aerodynamic characteristics of moving techniques in axial-flow compressors trailing-edge controls at subsonic and transonic 880-36 143 speeds Axial flow rotor unsteady performance (RAE-IM-STRUC-9447] 1180-2228 1 1180-23308 BOX BEAMS The aerodynamics of axial flow wind power turbines Civil component program wing section. [cSIR-EE-1619] N80-23781 Predimensioning of a supercritical wing AIISYMMETBIC FLOW [ESA-TT-542) N80-22317 A theoretical study of the coherence of jet noise RRAYTON CYCLE [AIAA PAPER 80-1005] 880-35967 Concept definition study of small Brayton cycle Pan noise caused by the ingestion of anisotropic engines for dispersed solar electric power systems turbulence - A model based on axisymmetric (NASA-CR-159592] N80-22778 turbulence theory BUCKLING [8188 PAPER 80-1021] 880-35977 On experimental versus theoretical incipient buckling of narrow graphite/epoxy plates in compression B [8188 80-0686] 880-35007 BAILOUT The influence of bending-torsional coupling on the Emergency in-flight egress opening for general buckling load of general orthotropic, midplane aviation aircraft --- pilot bailout symmetric and elastic plates 4180-23511 [NLR-TR-77 126-U] 88 0-22753 BALANCE BULK ACOUSTIC WAVE DEVICES Magnetic suspension and balance system: A OSCER fan exhaust bulk absorber treatment evaluation selective annotated bibliography [NASA-TN-811498] 880-23314 [NASA-TM-80225] 4180-22368 BUOYS BEARS (SUPPORTS) Air deployment of satellite-tracked drifters Two-dimensional finite-element analyses of A80-36291 simulated rotor-fragment impacts against rings and beams compared with experiments (NASA-CB-159645) N80-22323 C BIBLIOGRAPHIES C-135 AIRCRAFT Magnetic suspension and balance system: A Wind tunnel investigation of an all flush orifice selective annotated bibliography air data system for a large subsonic aircraft [NASA-TM-80225] 4180-22368 conducted in a Langley 8 foot transonic Cryogenic wind tunnels: A selected, annotated pressure tunnel bibliography [NASA-T2-1642] N80-23304 [NASA-TE-80168-SUPPL] 4180-23333

A-9

C-140 AIRCRAFT SUBJECT INDEX

C-140 AIRCRAFT CIRCULATION CONTROL ROTORS Aurora /CP-140/ aircraft operational software system A hybrid composite helicopter main rotor blade A80-34185 employing pneumatic lift control CALIBRATING A80-34808 Pitot-static system - Errors and calibrations CIVIL AVIATION A80-34593 The future of civil turbo-fan engines CAMBER [AIAA PAPER 80-0893] A80-32876 Airplane wing leading edge variable camber flap Longrange very large aircraft supply system for 880-23514 civil/military application with special emphasis CANOPIES on water-based aircraft Finite element analysis of F-16 aircraft canopy [AIAA PAPER 80-0903] A80-32882 dynamic response to bird impact loading Technology requirements as derived from accident [AIAA 80-0804] A80-35086 rate analysis The verification of a computer model of internal [AIAA PAPER 80-0918] A80-32888 light reflections for helicopter canopy design Fuel consumption per units of transport work in [AD-A080473] 880-23142 airliner operation CARBON FIBER REINFORCED PLASTICS A80-34236 Airworthiness certification of composite Airworthiness, certification of composite components for civil aircraft - The role of components for civil aircraft - The role of non-destructive evaluation non-destructive evaluation A80-34766 A80-34766 CARBON FIBRES Roughness effects on fuel consumption for two Current and projected use of carbon composites in commercial aircraft: McDonnell Douglas DC-9 and United States aircraft DC-la A80-34840 [PFA-AU-1456] 880-22320 High voltage spark carbon fiber detection system Outlook for advanced concepts in transport aircraft (NASA-CB-162995) 880-22367 (NASA-TM-81810] 880-23283 CARBON TETRAPLUOBIDE Mathematical model for the separation of gust and Gladstone-Dale constant for CF4 --- experimental manoeuvre loads of civil aircraft design [FB-141 (1979) 3 N80-23674 [NASA-TM-80228] N80-24151 CLEARANCES CA RB U B NT CBS Laser-optical blade tip clearance measurement system Carburetor ice: A review A80-36137 880-23278 CLOUD HEIGHT INDICATORS Carburetor ice: A review A microprocessor controlled system for determining [TR-79-9] 880-23279 the height of clouds Carburetor ice: A review A80-34188 [TR-77-19) 880-23280 COANDA EFFECT CARGO AIRCRAFT Development of the A-6/circulation control wing Conceptual studies of a long-range transport with flight demonstrator configuration an upper surface blowing propulsive lift system (AD-A081241] 880-22365 (NASA-TN-81196) 880-23249 COAXIAL NOZZLES CASCADE PLOW Noise suppression due to annulus shaping of an Unsteady aerodynamic forces on a subsonic inverted-velocity-profile coaxial nozzle rectilinear cascade of blades A80-35498 [P88-90007] 880-23266 COCKPIT SIMULATORS CASCADE BIND TUNNELS Operations manual: Vertical Notion Simulator Gravimetric investigation of the particle number (VHS) S.08 density distribution function in the high speed [NASA-T8-81180] 880-23295 cascade wind tunnel for laser-anemometry COCKPITS measurements A solid state /CCD/ cockpit television system [DFVLB-FB-79-12] N80-22374 A80-34190 Investigation into compressor aeroelastic COHERENT RADAR instabilities in a wind tunnel for a rectilinear Airborne radar coherent transmitters cascade of blades A80-34159 [P88-90011] 880-23337 COLLISION AVOIDANCE CENTRAL ELECTRONIC MANAGEMENT SISTER The automatization of the detection of collision Air Defense Ground environment - A case for risks for French air traffic control automation A80-34226 A80-34154 General aviation altimetry errors for collision CERAMIC COATINGS avoidance systems Development of improved-durability plasma sprayed A80-35L404 ceramic coatings for gas turbine engines COMBAT [NASA-TN-81512] 880-23313 Air combat maneuvering performance measurement CERAMICS [AD-A077429] 880-23336 Application of ceramic nozzles to 10 KW engine COMBUSTION [AD-A081184] 880-23320 Turbopropulsion combustion technology assessment Property screening and evaluation of ceramic [AD-A080748] 880-23323 turbine engine materials COMBUSTION CHAMBERS [AD-A080963] 880-23322 Gasdynawic analysis of gas-turbine combustion Development of high temperature resistant ceramic chambers with graduated air admission parts for gas turbines A80-33825 [RMFT-FB-T-79-09] 880-233214 Suppression of self-oscillations in combustion CH-54 HELICOPTER chambers by means of resonance sound absorbers Analysis of helicopter maintenance fault isolation A80-34400 criteria/techniques Model studies of acoustic resonators [AD-A080596] N80-22257 A80-34403 CHARGE COUPLED DEVICES COMBUSTION EFFICIENCY A solid state /CCD/ cockpit television system Gasdynawic analysis of gas-turbine combustion AR 0-34 190 chambers with graduated air admission CHEMICAL REACTIONS A80-33825 Research on diamantane and other high density Ultralean combustion in general aviation piston [AD-A0807149] 880-23474 engines CIRCULAR POLARIZATION (NASA-CE-163001] 880-22430 A broadband, circularly polarized, phase steered COMBUSTION PRODUCTS array High voltage spark carbon fiber detection system A80-34166 (NASA-CE-162995) 880-22367

A-b

SUBJECT INDEX CONFERENCES

COMBUSTION TEMPERATURE COMPRESSOR ROTORS Combustion-gas temperature sensors for turbine and turbojet engines Laser anemometer measurements in a transonic axial flow compressor rotor A80-34237 COMMAND AND CONTROL A80-36i41 Air Defense Ground environment - A case for Preliminary measurements of aerodynamic damping of automation a transonic compressor rotor A80-36152 A80-34154 COMPUTER GRAPHICS Survivable C3 --- command, control and Flight simulation techniques - The quest for realism communication centers in military electronics defense A80-33135 CAD produced aircraft drawings A80-34156 COMMERCIAL AIRCRAFT (RIAB 80-0732] A80-35036 COMPUTER PROGRAMS Advanced high speed commercial aircraft - 2000 Comparison of aircraft noise-contour prediction [AIRA PAPER 80-0937] A80-32898 programs Current and projected use of carbon composites in [ElBA PAPER 80-1057] United States aircraft A80-35998 Improved maneuver criteria evaluation program A80-3'4840 flight path equations of motion for the b-58 and Prediction of the interior noise levels of Oh-58a aircraft high-speed propeller-driven aircraft (AD-A080408) (AIAA PAPER 80-0998) A80-35961 880-22310 Design, development and implementation of an Rotorcraft flight simulation, computer program C81. Volume 1: Engineer's manual active control system for load alleviation for a (AD-A079631] commercial transport airplane 880-22312 (AGABD-AR-683] Rotorcraft flight simulation, computer program 880-23331 C 81. Volume 2: User's manual COMMUNICATION CABLES (AD-A079632] Measurement of 880-22313 interference-to-navigation/communication Investigations into an active vibration isolation system for helicopters with rigid and elastic avionics from cable television (CATY) systems airframe modeling [AD-A081430] 880-23530 (ESA-TT-531) COMMUNICATION EQUIPMENT 880-22315 Survivable C3 --- command, control and The verification of a computer model of internal communication centers in military electronics light reflections for helicopter canopy design defense [AD-A080473) B80-23142 Numerical flow field program for aerodynamic A80-34156 heating analysis. Volume 1: Equations and COMPOSITE MATERIALS results NDI policy and techniques for advanced composites (AD-A081471] nondestructive inspection 880-23255 Easy-Ads dynamic analysis. User's manual A80-34 765 [AD-E081160] Release-rate calorimetry of multilayered materials N80-23258 for aircraft seats Numerical flow field program for aerodynamic heating analysis. Volume 2: Users manual (AIAA 80-0759) A80-35052 (AD-A08 1472] 880-23260 Engine environmental effects on composite behavior COMPUTER SYSTEMS DESIGN moisture and temperature effects on Processing and analysis of the data from a two mechanical properties spool gas turbine engine [AIAA 80-0695] A80-35101 Flight service evaluation of Kevlar-49 epoxy A80-36149 Validation Methods Research for Fault-Tolerant composite panels in wide-bodied commercial Avionics and Control Systems: Working Group transport aircraft Meeting, 2 [NASA-CB-159231] 880-23371 (NASA-cP-2130] COMPOSITE STRUCTURES 880-23008 Software impact of selected en route ETC computer Airworthiness certification of composite replacement strategies components for civil aircraft - The role of [AD-B081478] 880-23286 non-destructive evaluation COMPUTER SYSTEMS PROGRAMS A80-34766 Software impact of selected en route ATC computer Costs of graphite composite fabrication and repair replacement strategies of aircraft structures [AD-A081478] N80-23285 A80-34810 COMPUTER TECHNIQUES Composite wing/fuselage integral concept Air Defense Ground environment - B case for (ElBA 80-0744] A80-35( )144 automation Advanced composite structure repair guide [AIAA 80-0774] A80-34154 A80-35( )65 COMPUTERIZED DESIGN Repair of advanced composite structures --- in damaged aircraft Numerical design and optimization of propellers. II (AIAB 80-0776] A80-33107 A80-350 66 CAD produced aircraft drawings COMPRESSIBILITY EFFECTS [AIAA 80-0732] A80-35036 The harmonically oscillating body in subsonic Effect of some aircraft loading program flow: Effect of compressibility modifications on the fatigue life of open hole [ESA-TT-584] N80-23 70 specimens COMPRESSION LOADS A80-36076 On experimental versus theoretical incipient Civil component buckling of narrow graphite/epoxy plates in program wing section. compression Predimensioning of a supercriticaj, wing (ESA-TT-542] N80-22317 [AIBA 80-0686] A80-350 07 COMPUTERIZED SIMULATION COMPRESSOR BLADES Experimental investigation of flutter in mid-stage Flight simulation techniques - The quest for realism compressor designs --- for aircraft axial flow A80-33135 gas turbine engines Pilot assessment of two computer-generated display formats for helicopter instrument approach [ALEA 80-0786] A80-350 73 [NASA-TM-80151] 880-22321 Investigation into compressor aeroelastic Easy-ACIS dynamic analysis. User's manual instabilities in a wind tunnel for a rectilinear (AD-A081160] cascade of blades 880-23258 A primitive variable' computer model for combustion (PRE-90011] 880-233 37 COMPRESSOR EFFICIENCY within solid fuel ramjets [AD-A081081] 880-23319 Core compressor exit stage study, 2 CONFERENCES [NASA-CR-159812] N80-233 12 General Aviation Propulsion (NASA-CP-2126) N80-22327

A-li

CONFIGURATION MANAGEMENT SUBJECT INDEX

CONFIGURATION MANAGEMENT CRACK INITIATION - Technology to increase airport capacity - Analysis of cracks at attachment lugs [AIAA PAPER 80-0920) R80-32890 [AIAA 80-0753] A80-350148 Synthesis of a theoretical approach for employing CRACK PROPAGATION adaptive configuration management in A quantitative assessment of the variables aeronautical weapon system programs involved in crack propagation analysis for N80-23196 in-service aircraft CONGRESSIONAL REPORTS [AIAA 80-0752] A80-35047 National Aeronautics and Space Administration Fatigue crack propagation in aluminum alloy sheet Authorization Act, 1981 materials under maneuver spectrum and constant (5-96-719) 1180-214210 amplitude loading CONSTANTS [NLR-MP-78025-U] 1180-22749 Gladstone-Dale constant for CF4 --- experimental Gust severity effects on fatigue crack propagation design in aluminum alloy sheet materials [NASA-TM-80228) N80-24151 (NLR-MP-78041-U) 1180-23449 CONSTRUCTION MATERIALS CROP DUSTING Aircraft gas turbine materials and processes New mathematical formula for the cropduster A80-34631 operational cycle CONTROL CONFIGURED VEHICLES A80-344234 Air transportation 2000 - A challenge for new CRYOGENIC RIND TUNNELS technology Cryogenic wind tunnels: A selected, annotated [AIAA PAPER 80-0945] A80-32899 bibliography Using vertical gust alleviation to improve the [RASA-TM-80168-SUPPL] N80-23333 target tracking capability of the control CUMULATIVE DAMAGE configured YP-16 A quantitative assessment of the variables [A0-A080520] 1180-22360 involved in crack propagation analysis for CONTROL EQUIPMENT in-service aircraft Control system design using vector-valued [AIAI 80-0752) A80-35047 performance criteria with application to the CYCLIC LOADS control rate reduction in parameter insensitive Fatigue crack propagation in aluminum alloy sheet control systems materials under maneuver spectrum and constant (ESA-TT-512-REV) N80-22363 amplitude loading CONTROL STABILITY [NLR-NP-78025-U] 1180-22749 Minimum sensitivity controllers with application CYLINDRICAL BODIES to VTOL aircraft Analysis of experiments on the effects of jet A80-32759 plumes on pressure distribution over a CONTROL SURFACES cylindrical afterhody at transonic speeds A study of panel loads and centers of pressure of [AD-A081647] N80-23259 three different cruciform aft-tail control surfaces of a wingless missile from Mach 1.60 to 3.70 D (NASA-TM-81787] 1180-23251 DATA ACQUISITION CONTROL THEORY Experiences of a 50 MBPS video recording and The application of output predictive digital processing system for FLIE images control to wing flutter suppression and terrain A80-34163 following problems Unsteady pressure measurements and data analysis (AD-A080419] 1180-22361 techniques in axial-flow compressors Application of two design methods for active A80-36143 flutter suppression aid wind-tunnel test results Processing and analysis of the data from a two [NASA-TP-1653] 1180-22737 spool gas turbine engine Theory of disturbance-utilizing control with A80-36149 application to missile intercept problems Evaluation of an improved parachute test data (AD-A081110) 1180-23329 acquisition system CONTROL UNITS (COMPUTERS) (AD-A080240] 1180-22268 Validation Methods Research for Fault-Tolerant Wind tunnel investigation of an all flush orifice Avionics and Control Systems: Working Group air data system for a large subsonic aircraft Meeting, 2 conducted in a Langley 8 foot transonic (NASA-CP-2130] 1180-23008 pressure tunnel CONTROLLABILITY [NASA-TP-1642] 1180-23304 Precision controllability of the YF-17 airplane DATA MANAGEMENT (NASA-TP-1677] 1180-23327 E-3A REP evaluation program CONTROLLERS (AD-A081725] 1180-23536 Investigations of the design of active vibration DATA PROCESSING isolation systems for helicopters with rigid and Advanced digital data processing for onboard elastic modeling of the fuselage missile guidance and control [ESA-TT-556] N80-23300 A80-34179 COOLING SYSTEMS Processing and analysis of the data from a two Qualification of cooling systems design for high spool gas turbine engine temperature on a turbine facility A80-36149 (ONERA, TP NO. 1980-15] A80-36156 DATA RECORDING CORROSION PREVENTION Experiences of a 50 MBPS video recording and Evaluation of coatings for wear and corrosion - processing system for FLIB images Protection in air/fluid accumulators --- for A80-34163 Navy aircraft carriers DATA REDUCTION A80-34819 Unsteady aerodynamic measurement techniques for CORROSION RESISTANCE turbomachinery research Evaluation of coatings for wear and corrosion - A80-36142 Protection in air/fluid accumulators --- for DATA SYSTEMS Navy aircraft carriers Evaluation of an improved parachute test data A80-34819 acquisition system COST ANALYSIS [AD-A080240] 1180-22268 Costs of graphite composite fabrication and repair DC 8 AIRCRAFT of aircraft structures The Dc-8 re-engining program A80-34810 A80-34218 COST EFFECTIVENESS DC 9 AIRCRAFT Preliminary study of advanced turboprop and Roughness effects on fuel consumption for two turboshaft engines for light aircraft --- cost commercial aircraft: McDonnell Douglas DC-9 and effectiveness DC-10 (NASA-TM-81467] N80-22350 [FFA-AU-1456] 1180-22320

A-12 SUBJECT INDEX ELASTOPLASTICIT!

DC 10 AIRCRAFT DISPLACEMENT MEASUREMENT Wind tunnel investigation of active controls Digital system for dynamic turbine engine blade technology applied to a DC-10 derivative displacement measurements [AIAA 80-0771] A80-35062 A80-36151 Roughness effects on fuel consumption for two DISPLAY DEVICES commercial aircraft: McDonnell Douglas DC-9 and Pilot assessment of two computer-generated display DC-10 formats for helicopter instrument approach [PFA-AU-1456] 1180-22320 [NASA-TN-80151] 1180-22321 DECISION THEORY Plight test evaluation of airborne tire pressure Decision analysis of Advanced Scout Helicopter indicating systems candidates [AD-A081598] 1180-23305 (AD-A081483) 1180-23298 Visually Coupled System: Computer Generated DEFLECTION Imagery (VCS-CGI) engineering interface Two-dimensional finite-element analyses of [AD-A080931] 1180-23306 simulated rotor-fragment impacts against rings tiN VAIRDEVCEN dynamic flight simulator design and and beams compared with experiments multipurpose crew station concept design and (NASA-CE-159645] 1180-22323 development plan DELTA WINGS [AD-A081982] 1180-23335 Types of leeside flow over delta rings DISTANCE MEASURING EQUIPMENT A80-34652 A flight investigation of system accuracies and Stationary flow past the lower surface of a operational capabilities of a general piecewise planar delta wing with supersonic aviation/air transport area navigation system leading edges (RNAV) A80-34708 (AD-A081646] 1180-23288 Aerodynamics of the new generation of combat DOUGLAS AIRCRAFT aircraft with delta wings Reduction of aerodynamic drag of external spray (NASA-TB-75793] 1180-22306 booms and nozzles used on DC-6 aircraft Leeward flow over delta wings at supersonic speeds A80-314596 (RASA-TM-81187) 1180-23250 DRAG REDUCTION Lee side flow for slender delta wings of finite Reduction of aerodynamic drag of external spray thickness booms and nozzles used on DC-6 aircraft [NASA-TM-75753] 1180-23253 A80-34596 DEPLOYMENT Possibilities for achieving trimmed minimum drag Air deployment of satellite-tracked drifters without sacrificing inherent stability A80-36291 A80-34655 DESIGN ANALYSIS DRILLING Economic life criteria for metallic airframes Drilling composites with gun drills (AlAN 80-0748) - A80-35046 A80-34809 Investigations of the design of active vibration DUCTED PAN ENGINES isolation systems for helicopters with rigid and New developsents in US military fighter engines elastic modeling of the fuselage A80-34217 (ESA-TT-556] 1180-23300 DUCTED FANS DESTRUCTIVE TESTS - On the sound field generated by a fan in a Release-rate calorimetry of multilayered materials hard-walled baffled duct with uniform flow for aircraft seats [NLR-IR-78024-U] 1180-23106 A80-34223 DURABILITY DIESEL ENGINES Development of improved-durability plasma strayed Design study: A 186 kW lightweight diesel ceramic coatings for gas turbine engines aircraft engine (NASA-TM-81512J 1180-23313 [NASA-CE-3261] 1180-22326 DUST Lightweight diesel aircraft engines for general Project filter holder. Rests on 25 mm dust filter aviation holders N80-22338 (IG-TN0-P-1638) 1180-23887 DIFFERENTIAL EQUATIONS DYNAMIC CONTROL - Investigations into an active vibration isolation The promise of multicyclic control --- for system for helicopters with rigid and elastic helicopter vibration reduction airframe modeling - A80-33123 (ESA-TT-531] N80-22315 DYNAMIC MODULUS OF ELASTICITY DIGITAL SIMULATION Shock loading on reinforced splice joints of ultra Rotorcraft flight simulation, computer program high modulus graphite/epoxy cone frustum C81. Volume 1: Engineers manual advanced interceptor structures (AD-A079631) 1180-22312 A80-34811 DIGITAL SYSTEMS DYNAMIC RESPONSE Advanced digital data processing for onboard Axial flow rotor unsteady performance missile guidance and control - 1180-23308 180-34179 DYNAMIC STRUCTURAL ANALYSIS Digital system for dynamic turbine engine blade Dynamics of a flexible rotor-tower system displacement measurements (ASRL-TR-194-1) 1180-23862 A80-36151 The application of output predictive digital control to wing flutter suppression and terrain E. following problems E-3A AIRCRAFT (AD-A080419] 1180-22361 E-3A EMP evaluation program DIRECT LIFT CONTROLS [AD-A081725] 1180-23536 In-flight handling qualities investigation of EFFECTS Airbus A 310 DLC. Configurations on landing The VIBRA-8 subsonic aerodynamic nuclear gust approach using the DPVLE-HPB 320 variable vulnerability code stability aircraft (AD-A081722] 1180-23256 (DPVLE-FB-79-18] 1180-22319 EGRESS DIRECTIONAL CONTROL Emergency in-flight egress opening for general Pilot assessment of two computer-generated display aviation aircraft --- pilot bailout formats for helicopter instrument approach N80-23511 [NASA-TM-80151] 1180-22321 ELASTOPLASTICITY DISPERSIONS Two-dimensional finite-element analyses of Atmospheric dispersion of high velocity jets simulated rotor-fragment impacts against rings [AD-A081612] N80-23321 and beams compared with experiments [NASA-CR-159645] 1180-22323

A-13

ELECTRIC CURRENT SUBJECT INDEX

ELECTRIC CURRENT Vertical axis wind turbine development A survey of the high frequency effects associated [ORO-5135-77-5] N80-238136 with the lightning discharge ENGINE DESIGN [OUEL-1290/79] 1180-23590 The future of civil turbo-fan engines ELECTRIC FIELDS [AIAA PAPER 80-0893) A80-32876 A survey of the high frequency effects associated Long range very large aircraft supply system for with the lightning discharge civil/military application with special emphasis [OUEL-1290/79] 1180-23590 on water-based aircraft ELECTRIC POWER PLANTS [AIAA PAPER 80-0903) A80-32882 Concept definition study of small Brayton cycle Big-fan engines - A new US generation engines for dispersed solar electric power systems A80-314216 [NASA-CE-159592] N80-22778 New developments in US military fighter engines ELECTRIC PONER SUPPLIES A80-34217 Effects of electric fluctuations in electric power Damage tolerant design and test considerations in systems of flight vehicles the engine structural integrity program --- for A80-35185 aircraft turbines ELECTRIC SPARKS (AIAA 80-0784] A80-35072 High voltage spark carbon fiber detection system Experimental investigation of flutter in mid-stage (NASA-CE-162995) 1180-22367 compressor designs --- for aircraft axial flow ELECTRICAL FAULTS gas turbine engines Effects of electric fluctuations in electric power (AIAA 80-0786] A80-35073 systems of flight vehicles Processing and analysis of the data from a two A80-35185 spool gas turbine engine ELECTRO-OPTICS A80-36 149 A microprocessor controlled system for determining Qualification of cooling systems design for high the height of clouds temperature on a turbine facility A80-34188 [ONERA, TP NO. 1980-15) A80-36156 REP hardening of airborne systems through Design study: A 186 kW lightweight diesel electro-optical techniques design guidelines aircraft engine [AD-A080650] N80-23146 (NASA-CE-3261] 1180-22326 ELECTROMAGNETIC PULSES General Aviation Propulsion ENE hardening of airborne systems through (NASA-CP-2126) 1180-22327 electro-optical techniques design guidelines AiResearch QCGAT engine, airplane, and nacelle [AD-A080650) 1180-23146 design features E-3A FlIP evaluation program N80-22328 (AD-A081725] N80-23536 QCGAY aircraft/engine design for reduced noise and ELECTRONIC AIRCRAFT emissions 1FF for air defence aircraft --- Identification N80-22331 Friend or Foe AvcO Lycoming QCGAT program design cycle, A80-34157 demonstrated performance and emissions E-3A FlIP evaluation program N80-22332 [AD-A081725) 1180-23536 The spark-ignition aircraft piston engine of the ELECTRONIC CONTROL future Survivable C3 --- command, control and N80-22337 communication centers in military electronics Lightweight diesel aircraft engines for general defense aviation A80-34156 1180-22338 Electronically steered antennas Advanced rotary engine studies A80-34169 N80-22339 Practical design considerations for a flightworthy Positive displacement type general-aviation higher harmonic control system --- for flight engines: Summary and concluding remarks testing on OH-6A helicopter H80-22340 [AIAA 80-0668] A80-35100 Carburetor ice: A review ELECTRONIC EQUIPMENT (TR-77-19] 1180-23280 Aircraft radio equipment adjustment and ENGINE FAILURE maintenance technology --- Russian book Measurement and correlation of structural response A80-32845 to inlet hamershock phenomena on an F-14 airplane Pilot assessment of two computer-generated display A80-34975 formats for helicopter instrument approach Selected methods for defining engine operating [NASA-TN-80151] 1180-22321 ranges in the investigation of aircraft ELECTRONIC EQUIPMENT TESTS accidents. II E-3A EMP evaluation program A80-35184 [AD-A081725] 1180-23536 ENGINE INLETS ELECTRONIC NODULES Measurement and correlation of structural response The modular survivable radar --- LSI and microwave to inlet hanershock phenomena- on an F-14 airplane circuit technologies for military avionics A80-34975 A80-34158 ENGINE MONITORING INSTRUMENTS EMERGENCIES Combustion-gas temperature sensors for turbine and Emergency landings on a carpet of foam turbojet engines A80-33292 A80-34237 ENERGY CONSERVATION ENGINE NOISE CF6 jet engine performance improvement: - New fan Experimental study of fan-noise silencers of (NASA-CE-159699] 1180-23309 aircraft turbojet engines ENERGY CONVERSION A80-34398 The aerodynamics of axial flow wind power turbines Experimental investigation of sound absorption in (CSIR-ME-1619] 1180-23781 a flow-carrying channel with a sound-absorbing Vertical axis wind turbine development: Executive lining summary A80-34399 [ORO-5135-77-5--SUEE] 1180-23845 QCSEE fan exhaust bulk absorber treatment evaluation Vertical axis wind turbine development [AIAA PAPER 80-0987) A80-35952 [ORO-5135-77-5] 1180-23846 Study and experimental tests of fibrous acoustic ENERGY METHODS treatment for reduction of fan noise from XP3-1 Application of two design methods for active turbofan engine flutter suppression and wind-tunnel test results (AIAA PAPER 80-0988) A80-35953 (NASA-TP-1653] N80-22737 Acoustic measurements of three Prop-Fan models ENERGY TECHNOLOGY (AIAA PAPER 80-0995] A80-35958 Vertical axis wind turbine development: Executive Acoustic pressures on a prop-fan aircraft fuselage summary surface [ORO-5135-77-5-SUNE] N80-23845 [AIAA PAPER 80-1002) A80-35965

A-14

SUBJECT INDEX FAILURE ANALYSIS

Static tests at model scale indicating EXHAUST GASES rear-fuselage installation effects on engine Combustion-gas temperature sensors for turbine and exhaust noise turbojet engines (AIAA PAPER 80-1046] A80-35991 A80-34237 Model tests demonstrating under-wing installation Model tests demonstrating under-wing installation effects on engine exhaust noise effects on engine exhaust noise [AIBA PAPER 80-1048] A80-35992 [AIAA PAPER 80-1048] A80-35992 AiResearch QCGAT engine performance and emissions AiResearcb QCGAT engine performance and emissions tests tests N80-22329 N80-22329 AiResearch QCGAT engine: Acoustic test results Avco Lycoming QCGAT program design cycle, N80-22330 demonstrated performance and emissions Avco Lycoming quiet clean general aviation N80-22332 turbofan engine EXHAUST NOZZLES N80-22333 Atmospheric dispersion of high velocity jets Noise generation by jet-engine exhaust deflection [AD-A081612] N80-23321 [ESA-TT-553] N80-23104 P100 exhaust nozzle area control ENGINE PARTS N80-23513 Investigation of the stress distribution in the EXPERIMENTAL DESIGN surface layer of aircraft engine components R-38 REP evaluation program A80-34235 [AD-A081725] N80-23536 Aircraft gas turbine materials and processes Gladstone-Dale constant for CF4 --- experimental A80-34631 design Performance deterioration based on existing [NASA-TM-80228] N80-24151 (historical) data; JT9D jet engine diagnostics EXTERNAL STORES program Measurement and correlation of structural response [NASA-CB-135448] N80-22324 to inlet hanershock phenomena on an F-14 airplane Property screening and evaluation of ceramic A80-34975 turbine engine materials Unsteady airloads on a harmonically pitching wing [AD-A080963] N80-23322 with external store ENGINE TESTS [AIAA 80-0733] A80-35037 Selective methods of determining the range of Wing/store flutter with nonlinear pylon stiffness engine operation in aircraft crash [AIAA 80-0792] A80-35075 investigations. I Effect of a flexibly mounted store on the flutter A80-33106 speed of a wing Damage tolerant design and test considerations in [NASA-CB-159245] N80-22356 the engine structural integrity program --- for Decoupler pylon: Ring/store flutter suppressor aircraft turbines [NASA-CASE-LAR-121468-1) N80-22359 [AIAA 80-0784] A80-35072 Status of NASA full-scale engine aeroelasticity research F A80-35906 F-4 AIRCRAFT Temperature and pressure measurement techniques The impact of global positioning system on for an advanced turbine test facility guidance and controls systems design of military A80-36157 aircraft. Volume 2A: Specific application Thermal response turbine shroud study study no. 1, close air support [AD-A080620] N80-22352 [AGABD-AE-147-VOL-2A] N80-23303 CP6-60 engine short-term performance deterioration F-14 AIRCRAFT [NASA-CR-159830] N80-23316 Measurement and correlation of structural response ENVIRONMENT EFFECTS to inlet hamershock phenomena on an F-14 airplane Engine environmental effects on composite behavior A80-34975 [NASA-TB-81508] N80-23370 P-15 AIRCRAFT Evaluating and minimizing noise impact due to Repair of advanced composite structures --- in aircraft flyover damaged aircraft [NASA-CB-153187] N80-23874 [AIAA 80-0776] A80-35066 ENVIRONMENT SIMULATION Improved packaging for the LN-31 inertial Lightning damage mechanisms and simulation measurement unit (F-15 aircraft) techniques --- for aircraft protection [AD-A081745] N80-23293 A80-34664 F-16 AIRCRAFT ENVIRONMENTAL TESTS F-16 flutter suppression system investigation Engine environmental effects on composite behavior [AIAA 80-0768] A80-35060 moisture and temperature effects on Finite element analysis of F-16 aircraft canopy mechanical properties dynamic response to bird impact loading [AIAA 80-0695] A80-35101 [AIAA 80-0804] A80-35086 Aircraft carrier exposure tests of aluminum alloys F-17 AIRCRAFT [AD-A081060] N80-23433 Recent development of the YF-17 active flutter EPDXY COMPOUNDS suppression system Flight service evaluation of Kevlar-49 epoxy [AIAA 80-0769] AB0-35061 composite panels in wide-bodied commercial Precision controllability of the TF-17 airplane transport aircraft [NASA-TP-1677] N80-23327 (NASA-CR-159231) N80-23371 F-100 AIRCRAFT ERROR ANALYSIS P100 exhaust nozzle area control A flight investigation of system accuracies and N80-23513 operational capabilities of a general F-106 AIRCRAFT aviation/air transport area navigation system Storm hazards 0 79: F-1068 operations summary (BNAV) [NASA-TM-81779] 1180-23282 [AD-A081646] N80-23288 FAIL-SAFE SYSTEMS ERROR DETECTION CODES Damage tolerant design and test considerations in Validation Methods Research for Fault-Tolerant the engine structural integrity program --- for Avionics and Control Systems: Working Group aircraft turbines Meeting, 2 [AIAA 80-07843 A80-35072 [NASA-CE-2130] N80-23008 FAILURE ANALYSIS EXHAUST FLOE SIMULATION Failure analysis in aviation Static tests at model scale indicating [NLR-MP-78028-U] 1180-23284 rear-fuselage installation effects on engine The failure of aircraft structures exhaust noise [NLB-MP-78040-U] 1180-23285 [AIAA PAPER 80-1046] A80-35991

A-iS

FATIGUE (MATERIALS) SUBJECT INDEX

FATIGUE (MATERIALS) Theory of disturbance-utilizing control with An investigation of residual stresses in simulated application to missile intercept problems wing panels of 7075-T6 aluminum [AD-A081110] 880-23329 [AD-A080863] 880-23693 Definition of a two-level control system for FATIGUE LIFE nonlinear motion of an aircraft A quantitative assessment of the variables [ESA-TT-614] 880-23330 involved in crack propagation analysis for FILTERS in-service aircraft Project filter holder. Tests on 25 mm dust filter [AIAA 80-0752] A80-35047 holders Effect of some aircraft loading program (IG-TNO-F-1638] 880-23887 modifications on the fatigue life of open hole FINITE ELEMENT METHOD specimens Analysis of cracks at attachment lugs A80-36076 [AIAA 80-0753] A80-35048 Endurance of riveted lap joints (aluminum alloy Integrated thermal-structural finite element sheet and rivets) analysis --- for applications to hypersonic (ESDU-79031] 880-22723 transport design The failure of aircraft structures (AIAA 80-07171 880-35098 [NLB-NP-78040-9] 880-23285 Two-dimensional finite-element analyses of FATIGUE TESTS simulated rotor-fragment impacts against rings Generation of a representative load sequence for and beams compared with experiments the fatigue testing of Eacchi lID 3268 spar booms (NASA-CB-159645] 880-22323 [AD-A074155] 880-22309 Nonlinear, three-dimensional finite-element Fatigue crack propagation in aluminum alloy sheet analysis of air-cooled gas turbine blades materials under maneuver spectrum and constant (NASA-TP-1669] 880-22734 amplitude loading FINS [NLN-RP-78025-U] 880-22749 Durability and consistency of composite components Gust severity effects on fatigue crack propagation for L-1011 aircraft vertical fins in aluminum alloy sheet materials [AIAA 80-0811] A80-35092 NLB-EP-7804 1-U] 880-23449 FIRE CONTROL FEDERAL BUDGETS Design of an integrated flight/fire control system National Aeronautics and Space Administration including movable gun and gimbaled line of sight Authorization Act, 1981 tracker [S-96-719] 880-24210 N80-22355 NASA authorization, 1981 FIRE PREVENTION [GPO-59-528] 880-24211 Large-scale and small-scale flammability tests for FEEDBACK CONTROL airplane cabin materials Minimum sensitivity controllers with application A80-34787 to VTOL aircraft Release-rate calorimetry of multilayered materials A80-32759 for aircraft seats Future of helicopter rotor control [AIAA 80-0759] 880-35052 A80-33122 FIRES Active flutter suppression control law definition Analysis of NASA JP-4 fire tests data and via least squares synthesis development of a simple fire model [AIAA 80-0765] A80-35057 [NASA-CE-159209] 880-22432 Recent development of the YF-17 active flutter FLAMMABILITY suppression system Large-scale and small-scale flammability tests for [AIAA 80-0769] A80-35061 airplane cabin materials Wind tunnel investigation of active controls 880-34787 technology applied to a DC-10 derivative FLAPS (CONTROL SURFACES) [AIAA 80-0771] A80-35062 Summary of data required for the AGABD SEP FIBER COMPOSITES activity standard aeroelastic configurations - Current and projected use of carbon composites in two-dimensional configurations United States aircraft [NLR-HP-79015-U] N80-23273 A80-34840 FLEXIBILITY Aeroelastic tailoring of forward swept composite Effect of a flexibly mounted store on the flutter wings speed of a wing [AIAA 80-0795] A80-35077 (NASA-CE-159245] 880-22356 Technology of graphite-resin composite materials FLIGHT CHARACTERISTICS and their application in the aeronautical industry Possibilities for achieving trimmed minimum drag A80-35771 without sacrificing inherent stability Engine environmental effects on composite behavior A80-34655 [NASA-TE-81508] 880-23370 A practical method for predicting roughness FIBER OPTICS effects on aircraft SlIP hardening of airborne systems through [FFA-AU-1413] 880-22316 electra-optical techniques design guidelines Flight safety of Bogallo hang gliders. [AD-8080550] 880-23146 Theoretical and experimental study of the flight FIELD THEORY (PHYSICS) envelope On disturbance fields of moving singularities in [ONEBA-NT-1979-8] N80-23301 aerodynamics and aeroacoustics FLIGHT CONDITIONS (ESA-TT-570] 880-23269 Investigation of internal control laws for FIGHTER AIRCRAFT wing/store flutter suppression A solid state /CCD, cockpit television system (AIAA 80-0764] A80-35056 A80-34190 FLIGHT CONTROL New developments in US military fighter engines Plight control systems. VII A80-34217 880-32693 Unsteady airloads on a harmonically pitching wing Navigation for a group of aircraft /Automation of with external store data processing and flight control procedures/ [AIAA 80-0733] A80-35037 Russian book Active flutter suppression control law definition 880-33177 via least squares synthesis Optimal estimation applied to redundant strapped [AIAA 80-0765] A80-35057 down inertial sensors for navigation and flight Wing/store flutter with nonlinear pylon stiffness control [AIRA 80-0792] A80-35075 N80-22295 Development and application concepts for trainer Analysis of the effects of higher order control and combat-trainer versions of combat jet aircraft systems on aircraft approach and landing 880-35183 longitudinal handling qualities Aerodynamics of the new generation of combat [AD-A080519] 880-22362 aircraft with delta wings [NASA-TM-75793) 880-22306

A-i 6

SUBJECT INDEX FLUTTER ANALYSIS

Practical optimal flight control system design for PLOW DISTRIBUTION helicopter aircraft. Volume 1: Technical Report Leeward flow over delta wings at supersonic speeds [NASA-CB-3275] 880-23328 [NASA-TN-81187] 880-23250 PLIGHT OPERATIONS Lee side flow for slender delta wings of finite The importance of runway capacity - An analytical thickness approach [NASA-Tm-75753] 880-23253 A80-33294 Numerical flow field program for aerodynamic PLIGHT PATHS heating analysis. Volume 2: User's manual Improved maneuver criteria evaluation program [AD-1081472] 880-23260 flight path equations of motion for the h-58 and PLOW MEASUREMENT Oh-58a aircraft Laser anemometer measurements in a transonic axial [AD-A080408] 880-22310 flow compressor rotor PLIGHT SAFETY A80-36141 Technology requirements as derived from accident Fluid and structural measurements to advance gas rate analysis turbine technology [AIAA PAPER 80-0918] A80-32888 A80-36145 Flight safety of Rogallo hang gliders. Impact of new instrumentation on advanced turbine Theoretical and experimental study of the flight research envelope - A80-36155 (ONERA-NT-1979-8] 880-23301 An investigation into measuring runway surface FLIGHT SINULATION texture by the grease patch and outflow meter Plight simulation techniques - The quest for realism methods A80-33135 S/T-NEHO-2/79] 880-22372 Impact of flight effects on multitube suppressor FLOW THEORY design Construction of a nonstationary nonlinear theory [LILA PAPER 80-1029] A80-35979 of helicopter rotors Simulation of high bypass ratio engine jet noise A80-34711 flight effects by model jet wind tunnel test PLOW VELOCITY [AIAA PAPER 80-1030] i80-35980 Noise suppression due to annulus shaping of an Effect of some aircraft loading program inverted-velocity-profile coaxial nozzle modifications on the fatigue life of open hole A80-35498 specimens A laser-two-focus /L2F/ velocimeter for automatic A80-36076 flow vector measurements in the rotating Preliminary investigation of motion requirements components of turbomachines for the simulation of helicopter hover tasks [NASA-TM-81801] 880-22304 PLOTTER Rotorcraft flight simulation, computer program Noise from a vibrating propeller C81. Volume 1: Engineer's manual [AIAL PAPER 80-1011] A80-35969 [AD-1019631] 880-22312 Decoupler pylon: Wing/store flutter suppressor Rotorcraft flight simulation, computer program [NASA-CASE-LAR-12468-1] 880-22359 C81. Volume 2: User's manual The application of Output predictive digital [AD-A079632] 880-22313 control to wing flutter suppression and terrain Air combat maneuvering performance measurement following problems [AD-A077429] 880-23336 [AD-A080419] 880-22361 FLIGHT SIMULATORS Application of two design methods for active Pilot assessment of two computer-generated display flutter suppression and wind-tunnel test results formats for helicopter instrument approach [NASA-TP-1653] 880-22737 [NASA-TR-80151] 880-22321 An aeroelastic analysis of the Sheriff wing Operations manual: Vertical Notion Simulator [BU-234] 880-23274 (VHS) S.08 Status of NASA full-scale engine aeroe].asticity [NASA-TH-81180] 880-23295 research NAVAIHDEVcEN dynamic flight simulator design and [NASA-TM-81500] N80-23678 multipurpose crew station concept design and Minimum mass sizing of a large low-aspect ratio development plan airframe for flutter-free performance [AD-A081982] 880-23335 [NASA-TH--81818] 880-23683 FLIGHT TESTS PLOTTER ANALYSIS Airborne FLIR - Experiences from flight tests Investigation of internal control laws for A80-34174 wing/store flutter suppression Practical design considerations for a flightworthy [AIAA 80-0764] A80-35056 higher harmonic control system --- for flight Active flutter suppression control law definition testing on 0H-6A helicopter via least squares synthesis [LILA 80-0668] A80-35100 [LILA 80-0765] A80-35057 Generation of a representative load sequence for Design for active flutter suppression and gust the fatigue testing of Nacchi NB 3268 spar booms alleviation using state-space aeroelastic modeling [AD-A074155] 880-22309 [AIAA 80-0766] A80-35058 Carburetor ice: A review F-16 flutter suppression system investigation [TR-79-9] 880-23279 [LILA 80-0768] A80-35060 A flight investigation of system accuracies and Recent development of the YF-17 active flutter operational capabilities of a general suppression system aviation/air transport area navigation system [LIAR 80-0769] A80-35061 (RN AV) Wind tunnel investigation of active controls [AD-A081646] 880-23288 technology applied to a DC-10 derivative Flight test evaluation of airborne tire pressure [AIRA 80-07711 A80-35062 indicating systems Experimental investigation of flutter in mid-stage [AD-A081598] 880-23305 compressor designs --- for aircraft axial flow FLIGHT TRAINING gas turbine engines Platform motion contributions to simulator [LILA 80-0786] A80-35073 training effectiveness. Study 3: Interaction An optimization method for the determination of of motion with field-on-view the important flutter modes [AD-A078426] 880-23334 [AIAA 80-0790] A80-35074 PLIR DETECTORS Wing/store flutter with nonlinear pylon stiffness Experiences of a 50 8BPS video recording and [AIRA 80-0792] a80-35075 processing system for FLIR images System to measure the pressure distribution on fan A80-34163 aerofoil surfaces during flutter conditions Airborne P118 - Experiences from flight tests A80-36144 A80-34174 Effect of a flexibly mounted store on the flutter FLOW DISTORTION speed of a wing Types of leeside flow over delta wings [RASA-CB-159245] 880-22356 A80-34652

A-li

FL! BY WIRE CONTROL SUBJECT INDEX

FL! BY WIRE CONTROL Flight control systems. VII [ë A80-32693 Definition of a two-level control system for GAS DENSITY nonlinear notion of an aircraft Gladstone-Dale constant for CP4 --- experimental (ESA-TT-614] N80-23330 design FOAMS [NASA-TN-80228] N80-24151 Emergency landings on a carpet of foam GAS DYNAMICS A80-33292 Gasdynamic analysis of gas-turbine combustion Investigation of a foam supported glass fiber chambers with graduated air admission D-box for a rigid wing hang glider A80-33825 [BU-240] N80-23302 GAS PLOW FRACTURE MECHANICS Transmission of high frequency sound waves through Analysis of cracks at attachment legs a slug flow jet [LILA 80-07531 A80-35048 [AIAA PAPER 80-0969] A80-35944 FRACTURE STRENGTH GAS TURBINE ENGINES Preliminary design of composite wing-box Selective methods of determining the range of structures for global damage tolerance engine operation in aircraft crash [LIAR 80-0755] A80-35049 investigations. I FUEL COMBUSTION A80-33106 A pulsed radiography technique for studying the Combustion-gas temperature sensors for turbine and internal structure of fuel injection jets turbojet engines A80-34588 A80-34237 Analysis of NASA JP-4 fire tests data and Aircraft gas turbine materials and processes development of a simple fire model A80-3L1631 (NASA-CR-159209) N80-22432 Laser-optical blade tip clearance measurement system FUEL CONSUMPTION A80-36137 Fuel consumption per units of transport work in Fluid and structural measurements to advance gas airliner operation turbine technology A80-34236 A80-36145 Roughness effects on fuelconsumption for two Vibration measurements on turbomachine rotor commercial aircraft: McDonnell Douglas DC-9 and blades with optical probes DC-10 A80-36146 [FFA-AU-1456] N80-22320 Processing and analysis of the data from a two CF6 jet engine performance improvement: New fan spool gas turbine engine [NASA-CR-159699] N80-23309 A80-36149 FUEL CORROSION Digital system for dynamic turbine engine blade Alkyl derivatives of resorcinol used as displacement measurements antioxidants in jet fuels A80-36151 A80-35801 The design, development and operation of gas Eannich base used as an antioxidant in jet fuels turbine radio telemetry systems A80-35 802 A80-36154 FUEL INJECTION Impact of new instrumentation on advanced turbine A pulsed radiography technique for studying the research internal structure of fuel injection jets A80-36155 A80-34588 Thermal response turbine shroud study FUEL TESTS [AD-A080620] 1180-22352 Carburetor ice: A review Development of improved-durability plasma sprayed [TR-79-9] N80-23279 ceramic coatings for gas turbine engines FUEL-AIR RATIO [NASA-TE-81512] N80-23313 Carburetor ice: A review Application of ceramic nozzles to 10 KW engine [TR-79-9J N80-23279 [AD-A081184] 1180-23320 FULL SCALE TESTS Property screening and evaluation of ceramic Large-scale and small-scale flammability tests for turbine engine materials airplane cabin materials [AD-A080963] 1180-23322 A80-34787 Development of high temperature resistant ceramic Full-scale wind tunnel-investigation of the parts for gas turbines Advanced Technology Light Twin-Engine airplane [BNFT-FB-T-79-09] 1180-23324 (ATLIT) --- Langley full scale tunnel GAS TURBINES [NASA-TP-1591] N80-22266 Gasdynanic analysis of gas-turbine combustion FUSELAGES chambers with graduated air admission Composite wing/fuselage integral concept A80-33825 [AIAA 80-0744) A80-35044 Nonlinear, three-dimensional finite-element Analytical study of interior noise control by analysis of air-cooled gas turbine blades fuselage design techniques on high-speed [NASA-TP-1669] 1180-22734 propeller-driven aircraft Concept definition study of small Brayton cycle [LILA PAPER 80-1001] A80-35964 engines for dispersed solar electric power systems Acoustic pressures on a prop-fan aircraft fuselage [NASA-CE-159592] N80-22778 surface GENERAL AVIATION AIRCRAFT [AILA PAPER 80-1002] A80-35965 General aviation altimetry errors for collision Noise transmission and control for a light, avoidance systems twin-engine aircraft A80-35404 [AIAA PAPER 80-1036] A80-35984 General Aviation Propulsion Static tests at model scale indicating (NASA-CP-2126] N80-22327 rear-fuselage installation effects on engine Aisesearcb QCGAT engine, airplane, and nacelle exhaust noise design features [AIAA PAPER 80-1046] A80-35991 1180-22328 An analytical study of tilt proprotor aircraft AiResearch QCGAT engine performance and emissions dynamics in airplane cruise configuration tests including the effects of fuselage longitudinal 1180-22329 rigid body motion AiResearch QCGAT engine: Acoustic test results N80-23297 N80-22330 Investigations of the design of active vibration QCGAT aircraft/engine design for reduced noise and isolation systems for helicopters with rigid and emissions elastic modeling of the fuselage 1180-22331 [ESA-TT-556] 1180-23300 Avco Lycoining QCGAT program design cycle, demonstrated performance and emissions N80-22332

A-18 SUBJECT INDEX MEAT TRANSFER

Avco Lycoming quiet clean general aviation GUIDANCE (MOTION) turbofan engine Predictive guidance for interceptors with time lag N80-22333 in acceleration New opportunities for future, snail, A80-32682 General-Aviation Turbine Engines (GATE) GULP STREAM N8 0- 22335 Air deployment of satellite-tracked drifters An overview of NASA research on positive A80-36291 displacement general-aviation engines GUN LAUNCHERS N80-22336 Projectile/sabot discard aerodynamics Lightweight diesel aircraft engines for general (AD-A080538] 1180-22269 aviation GUST ALLEVIATORS N80-22338 A simple system for helicopter Low speed propellers: Impact of advanced individual-blade-control and its application to technologies gust alleviation N80-22342 (AIRA 80-0666) A80-34995 NASA propeller noise research Design for active flutter suppression and gust N80-22347 alleviation using state-space aeroelastic modeling Ultralean combustion in general aviation piston [AIAA 80-0766] engines A80-35058 The design, testing and evaluation of the MIT [NASA-CB-163001] N80-22430 individual-blade-control system as applied to Emergency in-flight egress opening for general gust alleviation for helicopters aviation aircraft --- pilot bailout (NASA-CB-152352] 1180-22357 N80-23511 Using vertical gust alleviation to improve the A spin-recovery parachute system for light target tracking capability of the control general-aviation airplanes configured TF-16 N80-23512 [AD-A080520] 1180-22360 Mathematical model for the separation of gust and Design, development and implementation of an manoeuvre loads of civil aircraft active control system for load alleviation for a (PB-141 (1979)] N80-23674 commercial transport airplane GEOS 3 SATELLITE (AGABO-AR-683 J 1180-23331 Determining sea-ice boundaries and ice roughness GUST LOADS using GEOS-3 altimeter data Study on the dynamics of small flight vehicles [NASA-ca-156862] N80-22758 under gust loading GLASS FIBER REINFORCED PLASTICS A80-34653 A hybrid composite helicopter main rotor blade Review of nomstationary gust-responses of flight employing pneumatic lift control vehicles A80-34808 [AIAA 80-0703] A80-35097 GLASS FIBERS Effect of some aircraft loading program Investigation of a foam supported glass fiber modifications on the fatigue life of open hole 0-box for a rigid wing hang glider specimens [BU-240] N80-23302 A80-36076 GLOBAL POSITIONING SYSTEM Gust severity effects on fatigue crack propagation The impact of global positioning system on in aluminum alloy sheet materials guidance and controls systems design of military (NLR-MP--78041-U] 1180-23449 aircraft. Volume 2A: Specific application Mathematical model for the separation of gust and study no. 1, close air support manoeuvre loads of civil aircraft [AGABD-AR-147-VQL-2A] N80-23303 [P8-141 (1979) ] GRAPHITE-EPDXY COMPOSITE MATERIALS N80-23674 A hybrid composite helicopter main rotor tlade employing pneumatic lift control FW A80-34808 8-514 HELICOPTER Drilling composites with gun drills Analysis of helicopter maintenance fault isolation A8 0-34 809 criteria/techniques Costs of graphite composite fabrication and repair (A0-A080596] N80-2225 of aircraft structures HANG GLIDERS A80-34810 Flight safety of Bogallo hang gliders. Shock loading on reinforced splice joints of ultra Theoretical and experimental study of the flight high modulus graphite/epoxy cone frustum envelope advanced interceptor structures [ONEBA-NT-1979-8] 1180-23301 A80-34811 Investigation of a foam supported glass fiber On experimental versus theoretical incipient 0-box for a rigid wing hang glider buckling of narrow graphite/epoxy plates in [811-240] N80-23302 compression HARDENING (SYSTEMS) [AflA 80-0686] A80-35007 EMP hardening of airborne systems through Preliminary design of composite wing-box electro-optical techniques design guidelines structures for global damage tolerance [AD-A080650] 1180-23146 (AIAA 80-0755] 180-35049 HARMONIC OSCILLATION Durability and consistency of composite components Practical design considerations for a flightworthy for L-1011 aircraft vertical fins higher harmonic control system --- for flight [AIAA 80-0811] A80-35092 testing on OH-6A helicopter Technology of graphite-resin composite materials [AIAA 80-0668] A80-35100 and their application in the aeronautical industry The harmonically oscillating body in subsonic A80-35771 flow: Effect of compressibility High voltage spark carbon fiber detection system [ESA-TT-584] 880-23270 (NASA-CB-162995] 1180-22367 HEAT MEASUREMENT GRAYIMETRY Release-rate calorimetry of multilayered materials Gravimetric investigation of the particle number for aircraft seats density distribution function in the high speed A80-34223 cascade wind tunnel for laser-anemometry Release-rate calorinetry of multilayered materials measurements for aircraft seats [DFVLB-FB-79-12] N80-22374 (AIAA 80-0759] 180-35052 GROUND BASED CONTROL HEAT RESISTANT ALLOYS Air Defense Ground environment - A case for Aircraft gas turbine materials and processes automation A80-3463 1 A80-34154 MEAT TRANSFER GROUND EFFECT MACHINES Hypersonic heat transfer test program in the VKI CLST' s wing-in-ground effect vehicles longshot facility amphibious aircraft design [AD-A081467] 1180-23257 A80-33 105

A-19 SUBJECT INDEX HELICOPTER CONTROL

Investigations of the design of active vibration HELICOPTER CONTROL Active control of rotor blade pitch for vibration isolation systems for helicopters with rigid and reduction - A wind tunnel demonstration elastic modeling of the fuselage A80-33121 (ESA-TT-556] N80-23300 Practical optimal flight control system design for Future of helicopter rotor control A80-33122 helicopter aircraft. Volume 1: Technical Report N80-23328 The promise of multicyclic control --- for [NASA-CR-3275] helicopter vibration reduction HFB-320 AIRCRAFT A80-33123 In-flight handling qualities investigation of A hybrid composite helicopter main rotor blade Airbus A 310 DLC. Configurations on landing employing pneumatic lift control approach using the DFVLR-HFB 320 variable 180-34808 stability aircraft N80-22319 A simple system for helicopter [DFVLR-FB-79-18] HIGH ASPECT RATIO individual-blade-control and its application to bypass ratio engine jet noise gust alleviation Simulation of high [lilA 80-0666] 180-34995 flight effects by model jet wind tunnel test Multicyclic control for helicopters - Research in [lIlA PAPER 80-1030] 180-35980 progress at Ames Research Center HIGH TEMPERATURE ENVIRONMENTS [AIAA 80-0671] 180-34997 Qualification of cooling systems design for high temperature on a turbine facility Multicyclic control of a helicopter rotor 180-36156 considering the influence of vibration, loads, (ONERA, T2 NO. 1980-151 and control motion HIGH TEMPERATURE TESTS [AIAA 80-0673] 180-34998 Elevated temperature structural tasting of Practical design considerations for a flightvorthy advanced missiles higher harmonic control system --- for flight [hAl 80-0812] 180-35093 testing on 08-61 helicopter HIGH VOLTAGES (lIlA 80-0668) A80-35100 High voltage spark carbon fiber detection system Pilot assessment of two computer-generated display [NASA-CE-162995] N80-22367 formats for helicopter instrument approach HOLDERS Project filter holder. Tests on 25 mm dust filter [NASA-TM-80151) N80-22321 holders The design, testing and evaluation of the NIT N80-23887 individual-blade-control system as applied to [IG-TNO-F-1638] gust alleviation for helicopters HONEYCOMB STRUCTURES (NA SI-C 8-152352) N80-22357 Honeycomb sandwich joints for primary structure Navigation, guidance, and control for heliccpter of aircraft 180-35070 automatic landings [lIlA 80-0780] [NASA-TP-1649] N80-23326 HORIZONTAL FLIGHT A new algorithm for horizontal capture trajectories HELICOPTER DESIGN N80-22297 Advanced rotorcraft noise [NASA-TN-81186) (AIAA PAPER 80-0857] 180-32860 HOVERING Advanced composite structure repair guide Preliminary investigation of motion requirements A80-35065 for the simulation of helicopter hover tasks [lilA 80-0774] N80-22304 HELICOPTER PERFORMANCE (NASA-TN-81801) Advanced research on helicopter blade airfoils HUMAN FACTORS ENGINEERING 180-34298 NASA authorization, 1981 [ONERA, T8 NO. 1979-120] N80-24211 Model rotor low frequency broadband noise at (GPO-59-528) moderate tip speeds HYDRAULIC EQUIPMENT [lIlA PAPER 80-1013] 180-35971 The Eccentuator - A new concept in actuation Improved maneuver criteria evaluation program for aerospace mechanisms flight path equations of motion for the h-58 and [lIAR 80-0815] 180-35096 Oh-58a aircraft HYDROCARBON FURLS N80-22310 Research on diamantane and other high density [AD-A080408] N80-23474 HELICOPTER TAIL ROTORS (AD-A080749] A simple system for helicopter HYDROGEN PEROXIDE individual-blade-control and its application to Description of an experimental (hydrogen peroxide) gust alleviation - rocket system and its use in measuring aileron 180-34995 and rudder effectiveness of a light airplane [AIAA 80-0666] N80-22358 Vibration reduction with higher harmonic tlade [NASA-TP-1647] feathering for helicopters with two-bladed HYPERSONIC AIRCRAFT teetering and four-bladed hingeless rotors Integrated thermal-structural finite element [lilA 80-0670] 180-34996 analysis --- for applications to hypersonic Hulticyclic control for helicopters - Research in transport design 180-35098 progress at Ames Research Center [AlAR 80-0717) [lIlA 80-0671] 180-34997 HYPERSONIC FLIGHT Modern fluid dynamics of supersonic and hypersonic HELICOPTERS A collection of formulas for calculation of flight rotating blade noise - Compact and noncompact [1111 PAPER 80-0862) 180-33275 source results HYPERSONICS [AIAA PAPER 80-0996] 180-35959 Hypersonic heat transfer test program in the VKI Preliminary investigation of motion requirements longshot facility for the simulation of helicopter hover tasks [AD-A081467] N80-23257 (NASA-TM-81801] N80-22304 Parametric study of helicopter aircraft systems costs and weights (NASA-CR-152315] N80-22305 ICE FORMATION The effect of shaft angle on performance of a Carburetor ice: A review circulation control high-speed rotor at an n80-23278 Carburetor ice: A review advance ratio of 0.7 N80-23280 [10-1080953] N80-22314 [?IR-77-19] Investigations into an active vibration isolation ICE PREVENTION system for helicopters with rigid and elastic Carburetor ice: A review N80-23278 airframe modeling [ESA-TT-531] N80-22315 Carburetor ice: A review The verification of a computer model of internal [TR-79-9] N80-23279 light reflections for helicopter canopy design Carburetor ice: A review N80-23280 [10-1080473) N80-23142 (TR-77-19) Decision analysis of Advanced Scout Helicopter candidates [AD-Ad81483] N80-23298

1-20 SUBJECT INDEX JET AIRCRAFT NOISE

ICE REPORTING Shock loading on reinforced splice joints of Ultra Determining sea-ice boundaries and ice roughness high modulus graphite/epoxy cone frustum -- using GEOS-3 altimeter data advanced interceptor structures (NASA-CB-156862) 880-22758 A80-34811 IF? SYSTEMS (IDENTIFICATION) INTERFERENCE LIFT 1FF for air defence aircraft --- Identification A comment on the origin of endwall interference in Friend or Poe wind tunnel tests of aerofoils [RAE-TM-AERO-1816) 880-22280 IMAGE PROCESSING INTERNAL COMBUSTION ENGINES Experiences of a 50 8BPS video recording and Advanced rotary engine studies processing system for FUR images A80-34163 Positive displacement type general-aviation 88 0-22339 IMAGING TECHNIQUES engines: Summary and concluding remarks Visually Coupled System: Computer Generated 880-22340 Imagery (VCS-CGI) engineering interface INVISCID FLOW (AD-A080931) 880-23306 A comparison of various numerical methods for IMPACT DAMAGE calculating supercritical inviscid isentropic Two-dimensional finite-element analyses of flow over two-dimensional aerofoils simulated rotor-fragment impacts against rings (S/T-MEEO-4/75) and beams compared with experiments 880-22278 [NASA-CB-159645] 880-22323 11-FLIGHT MONITORING J General aviation altimetry errors for Collision JAMMING avoidance systems A broadband, circularly polarized, phase steered A80-35404 array Propeller light aircraft noise at discrete A80-34166 frequencies JET AIRCRAFT [AIAA PAPER 80-0997] A80-35960 Development and application concepts for trainer INERTIAL NAVIGATION and combat-trainer versions of combat jet aircraft Optimal integrated inertial navigation: in actual A80-35183 example - The R.P.A. aircraft carrier reference JET AIRCRAFT NOISE system Some unique characteristics of supersonic cruise A80-34227 vehicles and their effect on airport community Comparison of the ninilir location system and the noise NUB inertia measuring system STALINS [AIAA PAPER 80-0859] A80-32861 (NLR-NP-78026-U) 880-22303 Aeroacoustics --- Russian book INERTIAL PLATFOEMS AS 0-34386 Comparison of the minilir location system and the Noise characteristics of supersonic passenger planes NUN inertia measuring system STAUINS A80-34387 (NLR-HP-78026-9) 880-22303 Experimental study of fan-noise silencers of Improved packaging for the LN-31 inertial aircraft turbojet engines measurement unit (F-15 aircraft) A80-34398 (AD-A081745] 880-23293 Experimental investigation of sound absorption in INERTIAL REFERENCE SYSTEMS a flow-carrying channel with a sound-absorbing Optimal integrated inertial navigation: An actual lining example - The R.P.A. aircraft carrier reference A80-34399 system Suppression of self-oscillations in combustion A80-34227 chambers by means of resonance sound absorbers INFESTATION A80-34400 Reduction of aerodynamic drag of external spray Acoustic effects on the flow and the noise booms and nozzles used on DC-6 aircraft spectrum of supersonic jets - A80-34596 A80-34402 INFRARED TRACKING Acoustic characteristics of jets issuing from Comparison of the minilir location system and the ring-and-needle nozzles NLR inertia measuring system STALINS A80-34404 (NLR-MP-78026-u) 880-22303 Jet flap impingement noise from a full-scale STOL INLET FLOW EBF engine-wing system Fan noise caused by the ingestion of anisotropic A80-34594 turbulence - A model based on axisymmetric Noise suppression due to annulus shaping of an turbulence theory inverted-velocity-profile coaxial nozzle (AIAA PAPER 80-1021) A80-35977 A80-35498 INLET NOZZLES Transmission of high frequency sound waves through Application of ceramic nozzles to 10 KW engine a slug flow jet [AD-A0811814] 880-23320 [AIAA PAPER 80-0969] A80-35944 INSPECTION QCSEE fan exhaust bulk absorber treatment evaluation Failure analysis in aviation [AIAA PAPER 80-0987] A80-35952 (NLB-MP-78028-U) 880-23284 A theoretical study of the coherence of jet noise INSTRUMENT ERRORS (AIAA PAPER 80-1005] A80-35967 Pitot-static system - Errors and calibrations A unique Coannular plug nozzle jet noise A80-314593 prediction procedure General aviation altimetry errors for collision (AIAA PAPER 80-1007) A80-35968 avoidance systems Analytical study of the effects of wind tunnel A80-35404 turbulence on turbofan rotor noise INSTRUMENT LANDING SYSTEMS [AIAA PAPER 80-1022] A80-35978 In-flight handling qualities investigation of Impact of flight effects on multitube suppressor Airbus A 310 DUC. Configurations on landing design approach using the DFVLR-HPB 320 variable [AIAA PAPER 80-1029) stability aircraft A80-35979 Simulation of high bypass ratio engine jet noise (DFVLR-FB-79-183 880-22319 flight effects by model jet wind tunnel test INTEGRATED CIRCUITS [AIAA PAPER 80-1030] A80-35980 VLSI/VHSI device technology --- Very High Speed Prediction of flyover noise from single and Integration for military signal processing coannular jets applications [AIAA PAPER 80-1031] A80-35981 i80-34 175 Static tests at model scale indicating INTERCEPTORS rear-fuselage installation effects on engine Predictive guidance for interceptors with time lag exhaust noise in acceleration [AIAA PAPER 80-1046) A80-35991 A80-32682

A-21 JET ENGINE FUELS SUBJECT INDEX

Model tests demonstrating under-wing installation effects on engine exhaust noise [AIAA PAPER 80-1048] A80-35992 Current problems and the future in advanced KERNEL FUNCTIONS supersonic transport noise Transonic kernel function method for unsteady flow [AIAA PAPER 80-1056] A80-35997 calculations using a unified linear pressure Airframe self-noise studies on the Lockheed L 1011 panel procedure TriStar aircraft (AD-A080227) 580-22267 [AIAA PAPER 80-10611 A80-36000 KEVLAR (TRADEMARK) Acoustic characteristics of the external upper Study and experimental tests of fibrous acoustic surface blowing Fropulsive-lift configuration treatment for reduction of fan noise from XF3-1 [AIAA PAPER 80-1063] A80-36001 turbofan engine AiResearch QCGAT engine performance and emissions [AIAA PAPER 80-0988] 180-35953 tests N80-22329 AiReseatch QCGAT engine: Acoustic test results L N80-22330 1-1011 AIRCRAFT Noise generation by jet-engine exhaust deflection Durability and consistency of composite components [ESA-TT-553] 1180-23104 for L-1011 aircraft vertical fins JET ENGINE FUELS [AIAA 80-0811] A80-35092 A pulsed radiography technique for studying the Airframe self-noise studies on the Lockheed L 1011 internal structure of fuel injection jets TriStar aircraft A80-34588 [AIAA PAPER 80-1061) 180-36000 Alkyl derivatives of resorcinol used as LAMINATES antioxidants in jet fuels NDI policy and techniques for advanced composites A80-35801 nondestructive inspection Mannich base used as an antioxidant in jet fuels 180-34765 A80-35802 A hybrid composite helicopter main rotor blade The impact of fuels on aircraft technology through employing pneumatic lift control the year 2000 180-34808 [AIAA PAPER 80-0896] A80-35898 Release-rate calorimetry of multilayered materials Carburetor ice: A review for aircraft seats 1180-23278 [AIAA 80-0759] A80-35052 Carburetor ice: A review Repair of advanced composite structures --- in [TR-79-9] 1180-23279 damaged aircraft The impact of fuels on aircraft technology through [AXAA 80-0776] 180-35066 the year 2000 Aeroelastic tailoring of a forward swept wing and [NASA-TM-81492] 1180-23472 comparisons with three equivalent aft swept wings JET ENGINES [lilA 80-07941 180-35076 CF6-60 engine short-term performance deterioration Technology of graphite-resin composite materials [NASA-CE-159830] 1180-23316 and their application in the aeronautical industry JET EXHAUST A80-35771 Static tests at model scale indicating The influence of bending-torsional coupling on the rear-fuselage installation effects on engine buckling load of general orthotropic, midplane exhaust noise symmetric and elastic plates (AIAA PAPER 80-1046) A80-35991 (NLR-TR-77126-D) 1180-22753 Noise generation by jet-engine exhaust deflection LANDING [ESA-TT-553] 1180-23104 Estimation of wind shear and thrust loss during Analysis of experiments on the effects of jet STOL aircraft landing approach plumes on pressure distribution over a 1180-23296 cylindrical afterbody at transonic speeds LANDING GEAR - [AD-508 1647] 1180-23259 Emergency landings on a carpet of foam Static calibration of a two-dimensional wedge 180-33292 nozzle with thrust vectoring and spanwise blowing LANDING INSTRUMENTS [NASA-TM-81161) 1180-23317 New commutated Doppler microwave landing system JET FLAPS 180-36019 Jet flap impingement noise from a full-scale STOL LAP JOINTS EBF engine-wing system Endurance of riveted lap joints (aluminum alloy A80-34594 sheet and rivets) JET FLOE [ESDU-79031] 1180-22723 Analysis of experiments on the effects of jet LARGE SCALE INTEGRATION plumes on pressure distribution over a The modular survivable radar --- LSI and microwave cylindrical afterbody at transonic speeds circuit technologies for military avionics (AD-A08 1647] 1180-23259 A80-34158 JET IMPINGEMENT VLSI/VHSI device technology --- Very High Speed Jet flap impingement noise from a full-scale STOL Integration for military signal processing EBP engine-wing system applications A80-34594 A80-34175 Upper surface blowing noise of the NASA-Ames quiet LASER ANENOMETERS short-haul research aircraft A laser-two-focus /L2F/ velocimeter for automatic [AIAA PAPER 80-1064] A80-36002 flow vector measurements in the rotating JET MIXING FLOE components of turbomachines A unique coannular plug nozzle jet noise A80-36138 prediction procedure Optical advances in laser transit anemometry [AIAA PAPER 80-1007] A80-35968 A80-36139 JETTISONING Laser anemometer measurements in a transonic axial A spin-recovery parachute system for light flow compressor rotor general-aviation airplanes A80-36141 1180-23512 Gravimetric investigation of the particle number JOINTS (JUNCTIONS) density distribution function in the high speed Shock loading on reinforced splice joints of ultra cascade wind tunnel for laser-anenometry high modulus graphite/epoxy cone frustum measurements advanced interceptor structures [DFVLR-FB-79-12] 1180-22374 A80-34811 LASER APPLICATIONS JP-4 JET FUEL Laser-optical blade tip clearance measurement system Analysis of NASA JF-4 fire tests data and A80-36137 development of a simple fire model LASER TARGET DESIGNATORS (NASA-CR-159209) 1180-22432 Laser Target Harker /designator/ and Ranger A80-34187

1-22

SUBJECT INDEX MATRIX METHODS

Design considerations for an active laser seeker LOGISTICS MANAGEMENT A80-34189 Synthesis of a theoretical approach for employing LEADING EDGE SLATS adaptive configuration management in Airplane wing leading edge variable camber flap aeronautical weapon system programs 880-23514 880-23 196 LEADING EDGE SWEEP LONGITUDINAL CONTROL Stationary flow past the lover surface of a The design, testing and evaluation of the HIT piecewise planar delta wing with supersonic individual-blade-control system as applied to leading edges gust alleviation for helicopters A80- 34708 (NASA-CE-152352] N80-22357 LEAST SQUARES METHOD LOW ASPECT RATIO Active flutter suppression control law definition Minimum mass sizing of a large low-aspect ratio via least squares synthesis airframe for flutter-free performance [AIAA 80-0765] A80-35057 [NASA-TM-81818] 880-23683 LEE NAVES LOW COST Lee side flow for slender delta wings of finite Built-up low-cost advanced titanium structures thickness /8 LA I 5/ [NASA-TM-75753] N80-23253 [AIAA 80-0745] A80-35045 LIFE (DURABILITY) 1.08 DENSITY MATERIALS Durability and consistency of composite components Development of fire-resistant, low smoke for L-1011 aircraft vertical fins generating, thermally stable end items for (AIAA 80-0811] A80-35092 commercial aircraft and spacecraft using a basic LIFE CYCLE COSTS polyimide resin Advanced composite structure repair guide [NASA-CB-160576] 880-22492 [AINA 80-0774] A80-35065 LUBRICANTS LIFT AUGMENTATION Investigation of lubricant concepts applicable to Development of the A-6/circulation control wing future Navy aircraft propulsion systems flight demonstrator configuration [AD-A079410] 880-22351 [AD-A081241] 880-22365 LUBRICATION SYSTEMS Conceptual studies of a long-range transport with AN-is high-survivable transmission system an upper surface blowing propulsive lift system (AD-A080568] 880-22311 [NASA-Tfl-81196] 880-23249 LOGS LIGHT AIRCRAFT Analysis of cracks at attachment legs Study on the dynamics of small flight vehicles (AIAA 80-0753] A80-35048 under gust loading A80-34653 Propeller light aircraft noise at discrete M frequencies MAGNETIC SUSPENSION [AIAA PAPER 80-0997] A80-35960 Magnetic suspension and balance system: A Noise transmission and control for a light, selective annotated bibliography twin-engine aircraft [NASA-TM-80225] 880-22368 (AIAA PAPER 80-1036] A80-35984 MAINTAINABILITY Preliminary study of advanced turboprop and Performance deterioration based on existing turboshaft engines for light aircraft --- cost (historical) data; JT9D jet engine diagnostics effectiveness program [NASA-TM-81467] N80-22350 (NASA-CB-1354483 880-22324 Description of an experimental (hydrogen peroxide) MAN MACHINE SYSTEMS rocket system and its use in measuring aileron Air Defense Ground environment - A case for and rudder effectiveness of a light airplane automation [NASA-TP-1647] 880-22358 A80-34154 Wind tunnel tests on the Sheriff twin-engined MANEUVERABILITY light aircraft Precision controllability of the YP-17 airplane [BU-241] 880-23277 (NASA-TP-1677] 880-23327 LIGHT TRANSPORT AIRCRAFT MANUALS Design study: A 186 kW lightweight diesel Rotorcraft flight simulation, computer program aircraft engine - C81. Volume 1: Engineer's manual [NASA-CE-3261] 880-22326 [AD-A079631] 880-22312 LIGHTNING MANUFACTURING Lightning damage mechanisms and simulation Aircraft gas turbine materials and processes techniques --- for aircraft protection A80-34631 A80-34664 MATERIALS TESTS LINEAR PROGRAMMING Large-scale and small-scale flammability tests for Generation of a representative load sequence for airplane cabin materials the fatigue testing of Macchi MB 3268 spar booms A80-34787 [AD-A074155] 880-22309 MATHEMATICAL MODELS LOAD DISTRIBUTION (FORCES) Definition of a two level control system for Multicyclic control of a helicopter rotor nonlinear aircraft motion considering the influence of vibration, loads, [ONEBA-NT-1979-7] 880-22364 and' control motion Analysis of NASA .JP-4 fire tests data and [AIAA 80-0673] A80-34998 development of a simple fire model Structural design loads for future airplanes [NASA-CE-159209] 880-22432 (AIAA 80-0813] A80-35094 The verification of a computer model of internal LOAD TESTS light reflections for helicopter canopy design On experimental versus theoretical incipient [A0-A080473] 880-23142 buckling of narrow graphite/epoxy plates in Definition of a two-level control system for compression nonlinear motion of an aircraft [AIAA 80-0686] A80-35007 (ESA-TT-614] 880-23330 Elevated temperature structural testing of Mathematical model for the separation of gust and advanced missiles manoeuvre loads of civil aircraft [AIAA 80-0812] A80-35093 (P8-141 (1979) ] 880-23674 Effect of some aircraft loading program Minimum mass sizing of a large low-aspect ratio modifications on the fatigue life of open hole airframe for flutter-free performance specimens [NASA-TM-81818] 880-23683 A80-36076 MATRIX METHODS LOADS (FORCES) A matrix method for airport site evaluation Generation of a representative load sequence for A80-33293 the fatigue testing of Macchi MB 3268 spar booms (AD-A074155] 880-22309

A-23

MECHANICAL PROPERTIES SUBJECT INDEX

MECHANICAL PROPERTIES Laser Target Marker /designator/ and Ranger Engine environmental effects on composite behavior A80-34187 moisture and temperature effects on Design considerations for an active laser seeker mechanical properties A80-34189 (AIRA 80-0695) A80-35101 MISSILE BODIES Technology of graphite-resin composite materials Lift, drag and pitching moment measurements on a and their application in the aeronautical industry missile body having various boattails at A80-35771 subsonic and transonic velocities --- in a MESH transonic wind tunnel test High voltage spark carbon fiber detection system (DFVLR-FB-79-15] N80-23265 (NASA-CE-162995] N80-22367 MISSILE CONFIGURATIONS METAL BONDING Lift, drag and pitching moment measurements on a Comparison of surface treatments of aluminium and missile body having various boattails at their influence on long term strength of metal subsonic and transonic velocities --- in a bonds transonic wind tunnel test A80-34805 [DFVLR-FB-79-15) N80-23265 METAL COATINGS MISSILE CONTROL Evaluation of coatings for wear and corrosion - Advanced digital data processing for onboard Protection in air/fluid accumulators --- for missile guidance and control Navy aircraft carriers A80-34179 A80-34819 Midcourse guidance for fire and forget missile - METAL JOINTS Modification of present homing missile Honeycomb sandwich joints for primary structure A80-34180 of aircraft Theory of disturbance-utilizing control with [AlAS 80-0780] 580-35070 application to missile intercept problems METAL SHEETS [AD-A081110] N80-23329 Endurance of riveted lap joints (aluminum alloy MISSILE DESIGN sheet and rivets) Midcourse guidance for fire and forget missile - [ESDU-79031] N80-22723 Modification of present homing missile METAL SHELLS 580-34180 A study of the stress-strain state of shaped MISSILE STRUCTURES hollow blades for radial superchargers Shock loading on reinforced splice joints of ultra A80-34351 high modulus graphite/epoxy cone frustum METAL SURFACES advanced interceptor structures Comparison of surface treatments of aluminium and 580-34811 their influence on long term strength of metal Elevated temperature structural testing of bonds advanced missiles A80-34805 (AIAA 80-0812) 580-35093 METALS MISSILE TESTS Economic life criteria for metallic airframes Elevated temperature structural testing of [AlAS 80-0748] A80-35046 advanced missiles METHOD OF CHARACTERISTICS [AIAA 80-0812) A80-35093 Three dimensional flow investigation with a method MISSILES of characteristics in the inlet region and the A study of panel loads and centers of pressure of blade-to-tiade channels of supersonic axial three different cruciform aft-tail control compressors surfaces of a wingless missile from Mach 1.60 to [0NERA-NT-1979-1] N80-23325 3.70 MICRCCOMPUTEBS (NASA-TH-81787] N80-23251 - Digital system for dynamic turbine engine blade MIXING LENGTH PLOW THEORY displacement measurements Calculation of the turbulent boundary layer on an 580-36151 infinite swept wing using a three-dimensional MICROPROCESSORS mixing length model A microprocessor controlled system for determining (ESA-TT-53 44) N80-22273 the height of cicuds MODELS 580-34188 Acoustic test and analyses of three advanced MICROWAVE ANTENNAS turboprop models New commutated Doppler microwave landing system (NASA-CB-159667) N80-23311 A80-36019 MOISTURE CONTENT MICROWAVE CIRCUITS Engine environmental effects on composite behavior The modular survivable radar --- LSI and microwave moisture and temperature effects on circuit technologies for military avionics mechanical properties - 580-34158 (AIRS 80-0695] 580-35101 MICROWAVE LANDING SYSTEMS MOTION New commutated Doppler microwave landing system Platform motion contributions to simulator A80-36019 training effectiveness. Study 3: Interaction MIDCOURSE TRAJECTORIES of motion with field-on-view Midcourse guidance for fire and forget missile - (AD-5078426) N80-23334 Modification of present homing missile MOTION SIMULATORS 580-314 180 Operations manual: Vertical Motion Simulator MILITARY AIRCRAFT (VMS) S.08 Long range very large aircraft supply system for (NASA-TM-81180] N80-23295 civil/military application with special emphasis NAVAIRDEVCEN dynamic flight simulator design and on water-based aircraft multipurpose crew station concept design and [AIAA PAPER 80-0903] 550-32882 development plan IF? for air defence aircraft --- Identification [AD-A081982] N80-23335 Friend or Foe 58 0-34 157 The modular survivable radar --- LSI and microwave circuit technologies for military avionics N AC EL L E S A80-34158 AiResearcb QCGAT engine, airplane, and nacelle Statistical review of counting accelerometer data design features for Navy and Marine fleet aircraft N80-22328 [AD-A080580) N80-22308 NASA PROGRAMS MILITARY TECHNOLOGY Status of NASA full-scale engine aeroelasticity VLSI/VHSI device technology --- Very High Speed research Integration for military signal processing 580-35906 applications NASA propeller technology program 580-34175 N80-22341

A-24

SUBJECT INDEX NOISE REDUCTION

National Aeronautics and Space Administration Noise control prediction for high-speed, Authorization Act, 1981 propeller-driven aircraft (S-96-719) N80-214210 [AIAA PAPER 80-0999) A80-35962 NASA authorization, 1981 An analytical model for study of interior noise [GPO-59-528] N80-214211 control for high-speed, propeller-driven aircraft NAVIGATION [AIAA PAPER 80-1000] A80-35963 Comparison of the minilir location systemand the A unique coannular plug nozzle jet noise NLR inertia measuring system STALINS prediction procedure (NLR-EP-78026-U) N80-22303 [AIAA PAPER 80-1007] A80-35968 NAVIGATION AIDS Model rotor low frequency broadband noise at Navigation for a group of aircraft /Automation of moderate tip speeds data processing and flight control procedures/ [AIAA PAPER 80-1013] A80-35971 Russian book Pan noise caused by the ingestion ofanisotropic A80-33 177 turbulence - A model based on axisymmetric Navigation, guidance, and control for helicopter turbulence theory automatic landings [AIAA PAPER 80-1021] A80-35977 [NASA-TP-1649] N80-23326 Analytical study of the effects of wind tunnel EAVSTAB SATELLITES turbulence on turbofan rotor noise The impact of global positioning system on [AflA PAPER 80-1022] A80-35978 guidance and controls systems design of military Prediction of flyover noise from single and aircraft. Volume 2A: Specific application coannular jets study no. 1, close air support [AIAA PAPER 80-1031] A80-35981 [AGARD-AR-147-VOL-2A] N80-23303 Model tests demonstrating under-wing installation NAVY effects on engine exhaust noise Statistical review of counting accelerometer data [AIAA PAPER 80-1048] A80-35992 for Navy and Marine fleet aircraft Prediction of noise constrained optimum takeoff [A0-A080580] N80-22308 procedures NEAR FIELDS [AIAA PAPER 80-1055] A80-35996 Projectile/sabot discard aerodynamics Comparison of aircraft noise-contour prediction [AD-A080538] N80-22269 programs NEAR WAKES (AIAA PAPER 80-1057) A80-35998 Experimental investigation of the two-dimensional Airframe self-noise studies on the Lockheed L 1011 asymmetrical turbulent wake behind a blade IriStar aircraft A80-33282 [AIAA PAPER 80-1061] A80-36000 NEODYNIUN LASERS Aimesearch QCGAT engine: Acoustic test results Design considerations for an active laser seeker N80-22330 A80-34189 NOISE PROPAGATION NICKEL ALLOYS Noise transmission and attenuation by stiffened Fatigue at high temperatures: Examination of the panels behavior of gasturbine casting materials also in [AjAR PAPER 80-1034) A80-35982 simultaneous temperature and strain cycles Airframe self-noise studies on the Lockheed L 1011 (BRPT-PB-T-79-26) N80-23444 TriStar aircraft NOISE GENERAIORS [AIAA PAPER 80-1061] A80-36000 A collection of formulas for calculation of Theoretical prediction of nonlinear propagation rotating blade noise - Compact and noncompact effects on noise signatures generated by source results subsonic or supersonic propeller or rotor-blade [AIRA PAPER 80-0996] A80-35959 tips NOISE MEASUREMENT [NASA-TP-1660] 1180-22265 Propeller light aircraft noise at discrete NOISE REDUCTION - frequencies Advanced rotorcratt noise [AIAA PAPER 80-0997] - A80-35960 [AIRA PAPER 80-0857] A80-32860 Acoustic pressures on a prop-fan aircraft fuselage Aeroacoustics --- Russian book surface A80-34386 [AIAA PAPER 80-1002] A80-35965 Noise characteristics of supersonic passenger planes Noise from a vibrating propeller A80-34387 (AIAA PAPER 80-1011) A80-35969 Determining the optimal fan silencer design of Simulation of high bypass ratio engine jet noise aircraft engines flight effects by model jet wind tunnel test A80-34396 [AIAA PAPER 80-1030) A80-35980 Experimental study of fan-noise silencers of Upper surface blowing noise of the NASA-Ames quiet aircraft turbojet engines short-haul research aircraft A80-34398 [AIAA PAPER 80-1069] A80-36002 Experimental investigation of sound absorption in Acoustic test and analyses of three advanced a flow-carrying channel with a sound-absorbing turboprop models lining (NASA-CE-159667] N80-23311 A80-34399 Spectral analysis of non-stationary random Noise suppression due to annulus shaping of an processes. Application to noise of flyover type inverted-velocity-profile coaxial nozzle [ONERA-NT-1979-4] N80-24134 - A80-35498 NOISE POLLUTION Progress and trends in propeller/prop-fan noise Some unique characteristics of supersonic cruise technology vehicles and their effect on airport community (ALmA PAPER 80-0856] A80-35907 noise QCSEE fan exhaust bulk absorber treatment evaluation [AIAA PAPER 80-0859] A80-32861 [AIAA PAPER 80-0987] A80-35952 Evaluating and minimizing noise impact due to Study and experimental tests of fibrous acoustic aircraft flyover treatment for reduction of fan noise from XP3-1 [NASA-CE-153187] N80-23874 turbofan engine NOISE PREDICTION (AIRCRAFT) [ALmA PAPER 80-0988] A80-35953 Progress and trends in propeller/prop-fan noise Acoustic measurements of three Prop-Pan models technology (AIAA PAPER 80-0995) A80-35958 [AIAA PAPER 80-0856) A80-35907 Noise control prediction for high-speed, Transmission of high frequency sound waves through propeller-driven aircraft a slug flow jet (AIAA PAPER 80-0999) A80-35962 [AIAA PAPER 80-0969] A80-35944 An analytical model for study of interior noise Experimental verification of propeller noise control for high-speed, propeller-driven aircraft prediction [ALmA PAPER 80-1000) A80-35963 [AIAA PAPER 80-0994] A80-35957 Analytical study of interior noise control by Prediction of the interior noise levels of fuselage design techniques on high-speed high-speed propeller-driven aircraft propeller-driven aircraft [AIAA PAPER 80-0998) A80-35961 [AIAA PAPER 80-1001] A80-35964

A-25

NOISE SPECTRA SUBJECT INDEX

Analytical study of the effects of wind tunnel Noise suppression due to annulus shaping of an turbulence on turbofan rotor noise inverted-velocity-profile coaxial nozzle [ArEA PAPER 80-1022] A80-35978 A80-35498 Impact of flight effects on multitube suppressor NUCLEAR EXPLOSIONS design The VIBRA-8 subsonic aerodynamic nuclear gust (AIEA PAPER 80-1029] A80-35979 vulnerability code Noise transmission and attenuation by stiffened [AD-A081722) 880-23256 panels NUMERICAL ANALYSIS [ArEA PAPER 80-1034] A80-35982 Theoretical investigation of the aerodynamics of Noise transmission and control for a light, double membrane sailwing airfoil sections twin-engine aircraft A80-33276 [AIAA PAPER 80-1036] A80-35984 The outside has to be bigger than the inside Prediction of noise constrained optimum takeoff volume requirements calculation and optimal procedures design of supersonic aircraft [RIAR PAPER 80-1055] A80-35996 [AIEA 80-0726] A80-35031 Current problems and the future in advanced Transonic kernel function method for unsteady flow supersonic transport noise calculations using a unified linear pressure [AIAA PAPER 80-10563 A80-35997 panel procedure Comparison of aircraft noise-contour prediction [AD-A080227] 880-22267 programs A comparison of various numerical methods for [AIAA PAPER 80-1057] A80-35998 calculating supercritical inviscid isentropic Acoustic characteristics of the external upper flow over two-dimensional aerofoils surface blowing propulsive-lift configuration [S/T-MEMO-4/75) 880-22278 [AIEE PAPER 80-1063) A80-36001 NUMERICAL CONTROL QCGAT aircraft/engine design for reduced noise and Electronically steered antennas emissions A80-34169 880-22331 A microprocessor controlled system for determining Avco Lycoming quiet clean general aviation the height of clouds turbofan engine A80-34188 N8 0-22 333 NUMERICAL PLOW VISUALIZATION NASA propeller noise research Numerical flow field program for aerodynamic N80-22347 heating analysis. Volume 1: Equations and Forward acoustic performance of a shock-swallowing results high-tip-speed fan (QP-13) [AD-A081471] 880-23255 [NASA-TP-1668] 880-23100 Numerical flow field program for aerodynamic OSCEE fan exhaust bulk absorber treatment evaluation heating analysis. Volume 2: Users manual (NASA-T8-81498] 880-23314 (AD-A081472) 880-23260 Evaluating and minimizing noise impact due to aircraft flyover [NASA-CE-153187] 880-23874 It NOISE SPECTRA 011-6 HELICOPTER Acoustic effects on the flow and the noise Practical design considerations for a flightworthy spectrum of supersonic jets higher harmonic control system --- for flight A80-34402 testing on 0H-6A helicopter Propeller light aircraft noise at discrete [AflA 80-0668] A80-35100 frequencies 011-58 HELICOPTER [AIEA PAPER 80-0997] A80-35960 Improved maneuver criteria evaluation program A theoretical study of the coherence of jet noise flight path equations of motion for the h-58 and (AIRA PAPER 80-1005) A80-35967 Oh-58a aircraft Propeller signatures and their use --- aircraft [AD-A080408] 880-22310 noise and vibration measurements and analysis OPERATING SYSTEMS (COMPUTERS) [AIEA PAPER 80-1035] A80-35983 Aurora /CP-140/ aircraft operational software system Comparison of aircraft noise-contour prediction A80-34185 programs OPTICAL MEASUREMENT (AIAA PAPER 80-1057] A80-35998 Laser-Optical blade tip clearance measurement system Spectral analysis of non-stationary random A80-36137 processes. Application to noise of flyover type Optical advances in laser transit anemometry (ONERA-NT-1979-4] 880-24 134 A80-36139 NONDESTRUCTIVE TESTS Vibration measurements on turhomachine rotor 801 policy and techniques for advanced composites blades with optical probes nondestructive inspection AN 0-36146 A80-34765 OPTICAL RANGE FINDERS Airworthiness certification of composite A microprocessor controlled system for determining components for civil aircraft - The rcle of the height of clouds non-destructive evaluation A80-34188 A80-34766 OPTICAL REFLECTION NONFLAMMABLE MATERIALS The Verification of a computer model of internal Development of fire-resistant, low smoke light reflections for helicopter canopy design generating, thermally stable end items for [AD-A080473] N80-23142 commercial aircraft and spacecraft using a basic OPTICAL SLANT RANGE polyimide resin lRmote sensing methods for determination of slant [NASA-CB-160576] 180-22492 range Visibility NONLINEAR EQUATIONS DFVLR-PB-79-14] 880-23759 Theoretical prediction of nonlinear propagation OPTIMAL CONTROL effects on noise signatures generated by Predictive guidance for interceptors with time lag subsonic or supersonic propeller or rotor-blade in acceleration tips A80-32682 [NASA-TP-1660] 880-22265 Minimum sensitivity controllers with application NOSE TIPS to VIOL aircraft Active control of asymmetric vortex effects A80-32759 [AD-A081648] N80-23254 Navigation for a group of aircraft /Automation of NOZZLE DESIGN data processing and flight control procedures/ Static calibration of a two-dimensional wedge Russian book nozzle with thrust vectoring and spanwise blowing A80-33177 [NASA-TN-81161] 880-23317 Application of two design methods for active NOZZLE GEOMETRY flutter suppression and wind-tunnel test results Acoustic characteristics of jets issuing from [NASA-TP-1653] 880-22737 ring-and-needle nozzles A80-34404

A-26

SUBJECT INDEX PRESSURE DISTRIBUTION

Definition of a two-level control system for PHASED ARRAYS nonlinear motion of an aircraft A broadband, circularly polarized, phase steered [ESA-TT-6114] 880-23330 array OPTIMIZATION 180-34166 Numerical design and optimization of propellers. II Electronically steered antennas A80-33107 A80-34169 An optimization method for the determination of PHENOLS the important flutter nodes Hannich base used as an antioxidant in jet fuels [lIlA 80-0790] 180-35074 180-35802 Civil component program wing section. PIEZOELECTRIC GAGES Predinensioning of . a supercritical wing Preliminary measurements of aerodynamic damping of [ESA-TT-542) 880-22317 a transonic compressor rotor Control system design, using vector-valued 180-36152 performance criteria with application to the PILOT PERFORMANCE control rate reduction in parameter insensitive control systems Air combat maneuvering performance measurement [AD-A077429] 880-23336 [ESA-TT-512-REV] N80-22363 PILOT TRAINING ORIFICES Flight simulation techniques - The guest for realism Wind tunnel investigation of an all flush orifice A80-33135 air data system for a large subsonic aircraft PIPE FLOW conducted in a Langley 8 foot transonic Transmission of high frequency sound waves through pressure tunnel a slug flow jet (NASA-TP-1642] 880-233014 [1111 PAPER 80-0969] 180-35944 ORTBOTROPIC PLATES PISTON ENGINES The influence of bending-torsional coupling on the The spark-ignition aircraft piston engine of the buckling load of general orthotropic, midplane future symmetric and elastic plates [NLB-TR-77 126-n] S80-22337 880-22753 Ultralean combustion in general aviation piston OSCILLATING CYLINDERS engines The harmonically oscillating body in subsonic [NASA-CB-163001) 880-22430 flow: Effect of compressibility PITCH (INCLINATION) [ESA-TT-584) N80-23210 Unsteady airloads on a harmonically pitching wing OVERPRESSURE with external store Measurement and correlation of structural response [AIAA 80-0733] A80-35037 to inlet hamershock phenomena on an F-14 airplane Practical design considerations for a flightvorthy A80-34975 higher harmonic control system --- for flight testing on 08-61 helicopter [lilA 80-0668] 180-35100 p PITOT TUBES PACKAGING Pitot-static system - Errors and calibrations Improved packaging for the 18-31 inertial 18 0-34 593 measurement Unit (F-15 aircraft) PLATES (STRUCTURAL BERBERS) [AD-A08 1745] N80-23293 PANELS On experimental versus theoretical incipient buckling of narrow graphite/epoxy plates in Noise transmission and attenuation by stiffened compression panels [AAA 80-0686] 180-35007 [AIAA PAPER 80-1034] 180-35982 PLUG NOZZLES PARACHUTES A unique coannular plug nozzle jet noise Evaluation of an improved parachute test data prediction procedure acquisition system [AIAA PAPER 80-10073 A80-35968 [10-1080240] 880-22268 PLUSES An assessment of the stability and opening Analysis of experiments on the effects of jet characteristics of cruciform parachutes plumes cn pressure distribution over a [80-238] 880-23276 cylindrical afterbody at transonic speeds A spin-recovery parachute system for light [10-1081647] 880-23259 general-aviation airplanes PNEUMATIC CONTROL 880-23512 A hybrid composite helicopter main rotor blade PARTICLE DENSITY (CONCENTRATION) employing pneumatic lift control Gravimetric investigation of the particle number A80-34808 density distribution function in the high speed POLLUTION RONITORING cascade wind tunnel for laser-anemometry Project filter holder. Tests on 25 mn dust filter measurements holders (DFVLR-FB-79-12] 880-22374 [IG-TNO-F-1638] 88 0-23887 PASSENGER AIRCRAFT POLYIRIDE RESINS Fuel consumption per Units of transport work in Development of fire-resistant, low smoke airliner operation generating, thermally stable end items for A80-3'4236 commercial aircraft and spacecraft using a basic PERFORRANCE PREDICTION polyinide resin Advanced propeller aerodynamic analysis [NASA-CE-160576] N80-22492 W80-22345 POSITION ERRORS Propeller aeroacoustic methodologies Pitot-static system - Errors and calibrations N80-22346 A80-34593 PEBFORNANCE TESTS POSITION INDICATORS Experimental study of fan-noise silencers of A flight investigation of system accuracies and aircraft turbojet engines operational capabilities of a general A80-34398 aviation/air transport area navigation system Suppression of self-oscillations in combustion (ENAV) chambers by means of resonance sound absorbers [AD-A081646] N80-23288 A80-34400 PRESSURE DISTRIBUTION CF6 jet engine performance improvement: New fan System to measure the pressure distribution on fan (NASA-CR- 159699] 880-23309 aerofoil surfaces during flutter conditions CF6-6D engine short-term performance deterioration A80-36144 [NASA-CB-159830] 180-23316 A study of panel loads and centers of pressure of PERTURBATION THEORY three different cruciform aft-tail control On disturbance fields of moving singularities in surfaces of a wingless missile from Bach 1.60 to aerodynamics and aeroacoustics 3.70 [ESA-TT-570] 880-23269 [NASA-Tfl-81787] 880-23251

1-27 PRESSURE MEASUREMENTS SUBJECT INDEX

Analysis of experiments on the effects of jet Noise control prediction for high-speed, plumes on pressure distribution over a propeller-driven aircraft cylindrical afterbody at transonic speeds [AIAA PAPER 80-09993 A80-35962 [AD-A081647) 1180-23259 An analytical model for study of interior noise Pressure distribution measurements on wedges at control for high-speed, propeller-driven aircraft subsonic and transonic velocities --- in a [AIAA PAPER 80-10001 180-35963 transonic wind tunnel Analytical study of interior noise control by [ESA-TT-554] 1180-23267 fuselage design techniques on high-speed PRESSURE MEASUREMENTS propeller-driven aircraft Pitot-static system - Errors and calibrations (lIAR PAPER 80-1001) 180-35964 A80-34 593 PROPELLER EPPICIENC! Unsteady pressure measurements and data analysis Numerical design and optimization of propellers. II techniques in axial-flow compressors A80-33107 A80-36143 NASA propeller technology program Temperature and pressure measurement techniques N80-22341 for an advanced turbine test facility Low speed propellers: Impact of advanced RH 0-36 157 technologies Surface pressure measurements at two tips of a 1180-22342 model helicopter rotor in hover PROPELLER PANS [NASA-CE-3281] - 1180-23252 Acoustic measurements of three Prop-Pan models Hypersonic beat transfer test program in the VEl [lIAR PAPER 80-0995) A80-35958 longshot facility Acoustic pressures on a prop-fan aircraft fuselage [AD-A081467] N80-23257 surface Afterbody drag and base pressure measurements on a [AIAA PAPER 80-1002] 180-35965 body of revoluticn at angles of incidence up to PROP ELI RE S alpha = 25 deg at subsonic and transonic Each Propeller signatures and their use --- aircraft numbers --- transonic wind tunnel measurements noise and vibration measurements and analysis (ESA-TT-569) 1180-23268 [AIAA PAPER 80-1035) 180-35983 Wind tunnel investigation of an all flush orifice NASA propeller technology program air data system for a large subsonic aircraft 1180-22341 conducted in a Langley 8 foot transonic Low speed propellers: Impact of advanced pressure tunnel technologies [NASA-TP-1642] N80-23304 N80-22342 Flight test evaluation of airborne tire pressure High-speed-propeller wind-tunnel aeroacoustic indicating systems results [AD-A08 1598] N80-23305 B80-22344 PRESSURE OSCILLATIONS Advanced propeller aerodynamic analysis Aerodynamic characteristics of moving NBO-22345 trailing-edge controls at subsonic and transonic Propeller aeroacoustic methodologies speeds N80-22346 [RAE-TN-STRUC-947] N80-22281 NASA propeller noise research PRESSURE SENSORS 1180-22347 System to measure the pressure distribution on fan Propeller dynamic and aeroelastic effects aerofoil surfaces during flutter conditions B80-22348 A80736144 PROPULSION Experimental study of airfoil trailing edge noise: Turbopropulsion combustion technology assessment Instrumentation, methodology and initial results [AD-A080748] N80-23323 [NASA-CE-163007] N80-22264 PROPULSION SYSTEM CONFIGURATIONS PROCUREMENT MANAGEMENT Aeropropulsion in year 2000 Aurora /CP-140/ aircraft operational software system [AIAA PAPER 80-0914] 180-32887 A60-34185 General Aviation Propulsion PRODUCTION ENGINEERING [NASA-cP-2126] 1180-22327 Parametric study of helicopter aircraft systems Investigation of lubricant concepts applicable to costs and weights future Navy aircraft propulsion systems (NASA-CE-152315) N80-22305 [AD-A079410] 118022351 PROPAGATION NODES The impact of fuels on aircraft technology through Theoretical prediction of nonlinear propagation the year 2000 effects on noise signatures generated by [NASA-TM-81492] N80-23472 subsonic or supersonic propeller or rotor-blade PROPULSIVE E.PPICIENCY tips Static calibration of a two-dimensional wedge [NASA-TP-1660] 1180-22265 nozzle with thrust vectoring and spanvise blowing PROPELLANT COMBUSTION [NASA-TE-811613 1180-23317 A primitive variable computer model for combustion PROTECTIVE COATINGS within solid fuel ramjets Evaluation of coatings for wear and corrosion - [AD-A081081] 1180-23319 Protection in air/fluid accumulators --- for PROPELLANT PROPERTIES Navy aircraft carriers The impact of fuels on aircraft technology through 180-34819 the year 2000 PULSED LASERS [AIRA PAPER 80-0896] 180-35898 Laser Target Harker /designator/ and Sanger PROPELLER BLADES A80-34 187 Construction of a nonstationary nonlinear theory PYLON MOUNTING of helicopter rotors Wing/store flutter with nonlinear pylon stiffness A80-34711 [AIAA 80-0792] A80-35075 Noise from a vibrating propeller PYLONS (AIAA PAPER 80-10111 180-35969 Decoupler pylon: Wing/store flutter suppressor PROPELLER DRIVE (NASA-CASE-LAB-12468-1) 1180-22359 Progress and trends in propeller/prop-fan noise technology [AIAA PAPER 80-0856] A80-35907 0 Experimental verification of propeller noise QUALITY CONTROL prediction Problems involved in the detection of aircraft (AIAA PAPER 80-0994) 180-35957 defects Propeller light aircraft noise at discrete A80-33108 frequencies QUANTITATIVE ANALYSIS [AIAA PAPER 80-0997] 180-35960 A quantitative assessment of the variables Prediction of the interior noise levels of involved in crack propagation analysis for high-speed propeller-driven aircraft in-service aircraft [AIAA PAPER 80-0998] A80-35961 (AIAA 80-0752] 180-35047

A-28 SUBJECT INDEX ROTARY STABILITY

QUIET ENGINE PROGRAM An assessment of the stability and opening QCSEE fan exhaust bulk absorber treatment evaluation characteristics of cruciform parachutes (AIBA PAPER 80-0987] A80-35952 [80-238] 880-23276 AiBesearcb QCGAT engine, airplane, and nacelle REMOTE SENSORS design features iBemote sensing methods for determination of slant 880-22328 range visibility AiBesearch QCGAT engine performance and emissions [DFVLR-PB-79-14] 880-23759 tests RESEARCH AND DEVELOPMENT 880-22329 Flight control systems. VII Aiflesearch QCGAT engine: Acoustic test results *80-32693 M80-22330 Aeropropulsion in year 2000 Avco Lycoaing QCGAT program design cycle, [AIAA PAPER 80-0914] *80-32887 demonstrated performance and emissions Technology requirements and readiness for very N80-22332 large aircraft Avco Lycoming quiet clean general aviation (AIAA PAPER 80-0935) turbofan engine *80-32897 Air transportation 2000 - A challenge for new 880-22333 technology OSCEE fan exhaust bulk absorber treatment evaluation [AIAA PAPER 80-09145] (NASA-TB-81498] *80-32899 880-23314 Advanced research on helicopter blade airfoils (ONERA, TP NO. 1979-120] A80-34298 An overview of NASA research on positive RADAR ANTENNAS displacement general-aviation engines 880-22336 A broadband, circularly polarized, phase steered National Aeronautics and Space Administration array Authorization Act, 1981 A80-34166 [S-96-719] 880-24210 Electronically steered antennas NASA authorization, 1981 *80-34169 (GPO-59-528] 880-24211 Frequency independent sidelobe suppression and RESIDUAL STRESS lobesharpening using broad beam antennas An investigation of residual stresses in simulated 180-34178 wing panels of 7075-T6 aluminum RADAR EQUIPMENT [AD-A080863] 880-23693 The modular survivable radar --- LSI and microwave RESONANT FREQUENCIES circuit technologies for military avionics An optimization method for the determination of A80-34158 RADAR INAGERT the important flutter modes [AIAA 80-0790] *80-35074 Experiences of a 50 8BPS video recording and RESONATORS processing system for P118 images model studies of acoustic resonators A80-34163 A80-34403 RADAR TRACKING REVERBERATION Determining sea-ice boundaries and ice roughness Experimental investigation of sound absorption in using GEOS-3 altimeter data a flow-carrying channel with a sound-absorbing [NASA-C8-156862] 880-22758 lining RADAR TRANSMITTERS A80-34399 Airborne radar coherent transmitters RIGID ROTORS A80-34159 Vibration reduction with higher harmonic blade RADIO EQUIPMENT feathering for helicopters with two-bladed Aircraft radio equipment adjustment and teetering and four-bladed hingeless rotors maintenance technology --- Russian book [AIAA 80-0670] *80-34996 A80-32845 An analytical study of tilt proprotor aircraft The design, development and operation of gas dynamics in airplane cruise configuration turbine radio telemetry systems including the effects of fuselage longitudinal *80-36154 rigid body motion RADIO FREQUENCY INTERFERENCE N80-23297 Measurement of RIGID STRUCTURES interference-to-navigation/communication Noise transmission and attenuation by stiffened avionics from cable television (CATY) systems panels [AD-A081430] 880-23530 (AIAA PAPER 80-1034] *80-35982 RADIOGRAPHY RIGID RINGS A pulsed radiography technique for studying the Investigation of a foam supported glass fiber internal structure of fuel injection jets D-box for a rigid wing hang glider A80-34588 [Bu-240) N80-23302 RANJET ENGINES RING STRUCTURES A primitive variable computer model for combustion Two-dimensional finite-element analyses of within solid fuel ramjets simulated rotor-fragment impacts against rings [AD-A081081] N80-23319 and beams compared with experiments REFRACTIVITY [NASA-CH-159645] 880-22323 Gladstone-Dale constant for CP4 --- experimental RIVETED JOINTS design Endurance of riveted lap joints (aluminum alloy [NASA-T8-80228] 880-24151 sheet and rivets) REINFORCEMENT (STRUCTURES) (ESDO-79031) 880-22723 Economical processing of fiber-reinforced ROCKET ENGINES components with thermal expansion molding Description of an experimental (hydrogen peroxide) (NASA-TN-75738] 880-22412 REINFORCING FIBERS rocket system and its use in measuring aileron Economical processing of fiber-reinforced and rudder effectiveness of a light airplane (NASA-TP-1647] 880-22358 components with thermal expansion molding ROCKET NOZZLES [NASA-TN-75738] 880-22412 Analysis of experiments on the effects of jet RELAXATION NETHOD (NATEENATICS) Plumes on pressure distribution over a Supercritical wing design studies for transport cylindrical afterbody at transonic speeds aircraft. Volume 2: Theoretical studies (AD-A081647) 880-23259 [BBPT-FB-W-79-07-V0L-2] 880-22276 ROTARY STABILITY RELIABILITY ANALYSIS Experimental investigation of flutter in mid-stage Survivable C3.--- command, control and compressor designs --- for aircraft axial flow communication centers in military electronics gas turbine engines defense (AIAA 80-0786] A80-34156 A80-35073

A-29 ROTARY WING AIRCRAFT SUBJECT INDEX

ROTARY WING AIRCRAFT Forward acoustic performance of a shock-swallowing Rotorcraft flight simulation, computer program high-tip-speed fan (QP-13) C81. Volume 1: Engineer's manual [NASA-TP-1668] N80-23100 [AD-A079631) N80-22312 Axial flow rotor unsteady performance Rotorcraft flight simulation, computer prcgraa v80-23308 C81. Volume 2: User's manual ROTOR BLADES [AD-A079632] N80-22313 Advanced research on helicopter blade airfoils ROTARY WINGS [ONERA, TP NO. 1979-120] A80-34298 Advanced rotorcraft noise Helicopter rotor thickness noise [AIAA PAPER 80-0857] 180-32860 (1111 PAPER 80-10121 180-35970 Active control of rotor blade pitch for vibration Design and investigation of static pressure reduction - A wind tunnel demonstration compressor cascades behind impulse-rotors 180-33121 [DFVLB-PB-79-17] 580-22353 Future of helicopter rotor control ROTOR BLADES (TUBBONACHIWEET) 180-33122 Experimental investigation of flutter in mid-stage The promise of multicyclic control --- for compressor designs --- for aircraft axial flow helicopter vibration reduction gas turbine engines A80-33123 (lIlA 80-0786] 180-35073 Advanced research on helicopter blade airfoils Experimental investigations on the vibration of [ONERA, TP No. 1979-120] A80-34298 blades due to a rotating stall Construction of a nonstationary nonlinear theory 180-35912 of helicopter rotors Vibration measurements on turbomachine rotor 180-34711 blades with optical probes A hybrid composite helicopter main rotor blade 180-36186 employing pneumatic lift control Axial flow rotor unsteady performance A80-34808 N80-23308 A simple system for helicopter ROTOR SPEED individual-blade-control and its application to C16 jet engine performance improvement: New fan gust alleviation [NASA-CE-159699] N80-23309 [AIAA 80-0666] 180-34995 ROTORS Vibration reduction with higher harmonic blade Dynamics of a flexible rotor-tower system feathering for helicopters with two-bladed [ASRL-TB-194-1] N80-23862 teetering and four-bladed hingeless rotors RUDDERS [lilA 80-0670] 180-34996 Description of an experimental (hydrogen peroxide) Multicyclic control for helicopters - Research in rocket system and its use in measuring aileron progress at Ames Research Center and rudder effectiveness of a light airplane [AIAA 80-0671] A80-34997 [NASA-TP-1647] N80-22358 Nulticyclic control of a helicopter rotor RUNWAY CONDITIONS considering the influence of vibration, loads, Emergency landings on a carpet of foam and control moticn 180-33292 [AIAA 80-0673] A80-34998 The importance of runway capacity - An analytical A collection of formulas for calculation of approach rotating blade noise - Compact and nonconpact 180-33294 source results Influence of external conditions on the generation [AIAA PAPER 80-0996] 180-35959 and intensity of vortices at air-intakes Helicopter rotor thickness noise A80-34238 [AIAA PAPER 80-1012] 180-35970 Trials to compare the stopping performance of Model rotor low frequency broadband noise at three anti-skid systems and to demonstrate moderate tip speeds methods of determining aircraft stop distances [AIRA PAPER 80-1013] 180-35971 on the standard military reference wet surface The effect of shaft angle on performance of a [S/T-MEMO-3/79] 1180-22318 circulation control high-speed rotor at an A means of specifying a standard reference wet advance ratio of 0.7 surface for military aircraft [AD-A080953] N80-22314 [S/T-MEMO- 1/79] 880-22371 The design, testing and evaluation of the MIT An investigation into measuring runway surface individual-blade-control system as applied to texture by the grease patch and outflow meter gust alleviation for helicopters methods [NASA-CE-152352] N80-22357 [S/T-MEMO-2/79] 1180-22372 Surface pressure measurements at two tips of a RUNWAYS model helicopter rotor in hover Technology to increase airport capacity [NASA-CR-3281) N80-23252 [1111 PAPER 80-0920] 180-32890 ROTATING BODIES The design, development and operation of gas turbine radio telemetry systems S A80-36154 SAAB AIRCRAFT ROTATING STALLS Measurement of local skin friction and static Experimental investigations on the vibration of pressure on a swept wing in flight blades due to a rotating stall [FFA-A0-1370] 1180-22282 180-35912 SABOT PROJECTILES ROTOR AERODYNAMICS Projectile/sabot discard aerodynamics Construction of a nonstationary nonlinear theory (AD-1080538] 1180-22269 of helicopter rotors SAFETY FACTORS 180-34711 Technology requirements as derived from accident A simple system for helicopter rate analysis individual-blade-control and its application to [AAA PAPER 80-09181 180-32888 gust alleviation SAIL WINGS [AAA 80-0666] A80-34995 Theoretical investigation of the aerodynamics of Multicyclic control of a helicopter rotor double membrane sailwing airfoil sections considering the influence of vibration, loads, A80-33276 and control motion SANDWICH STRUCTURES [AIAA 80-0673] 180-34998 Honeycomb sandwich joints for primary structure The effect of shaft angle on performance of a of aircraft circulation control high-speed rotor at an [AIAA 80-0780] 180-35070 advance ratio of 0.7 SATELLITE OBSERVATION [AD-A080953] N80-22318 Determining sea-ice boundaries and ice roughness The design, testing and evaluation of the MIT using GEOS-3 altimeter data individual-blade-control system as applied to (NASA-CB-156862] 1180-22758 gust alleviation for helicopters (NASA-CE-152352] 880-22357

A-3D

SUBJECT INDEX SOUND TRANSMISSION

SATELLITE TRACKING SIGNAL ANALYSIS Air deployment of satellite-tracked drifters Experimental study of airfoil trailing edge noise: 180-36291 Instrumentation, methodology and initial results SCALE MODELS (NASA-CE-163007] 880-22264 Acoustic measurements of three Prop-Pan models SIGNAL PROCESSING (lIlA PAPER 80-0995) A80-35958 VLSI/VHSI device technology --- Very High Speed SEA ICE Integration for military signal processing Determining sea-ice boundaries and ice roughness applications using GEOS-3 altimeter data A80-34175 [NASA-CR-156862] 880-22758 Frequency independent sidelobe suppression and SEATS lobesbarpening using broad beam antennas Release-rate calorimetry of multilayered materials A80-34 178 for aircraft seats - SIGNATURE ANALYSIS 180-34223 Propeller signatures and their use --- aircraft Release-rate calorimetry of multilayered materials noise and vibration measurements and analysis for aircraft seats (AIAA PAPER 80-1035] A80-35983 [AIAA 80-0759] 180-35052 SILENCERS SELF OSCILLATION Determining the optimal fan silencer design of Suppression of self-oscillations in combustion aircraft engines chambers by means of resonance sound absorbers 180-34396 180-34'400 Experimental study of fan-noise silencers of SEPARATED FLOW aircraft turbojet engines Leeward flow over delta wings at supersonic speeds 180-34398 [NASA-TM-81187] 880-23250 SINGLE SIDEBAND TRANSMISSION SERVICE LIFE New commutated Doppler microwave landing system Economic life criteria for metallic airframes A80-36019 (AIAA 80-07148) 180-35046 SITES Performance deterioration based on existing A matrix method for airport site evaluation (historical) data; JT9D jet engine diagnostics A80-33293 program SIZE (DIMENSIONS) [NASA-CB-135448] 880-22324 Technology requirements and readiness for very SERVOMECHANISMS large aircraft The design, testing and evaluation of the MIT (AIAA PAPER 80-0935) 180-32897 individual-blade-control system as applied to SKIN FRICTION gust alleviation for helicopters Measurement of local skin friction and static (NASA-CR- 152352] 880-22357 pressure on a swept wing in flight SHOCK LOADS [PFA-AU-1370] N80-22282 Shock loading on reinforced splice joints of ultra SLENDER BODIES high modulus graphite/epoxy cone frustum Active control of asymmetric vortex effects advanced interceptor structures [AD-A081648] 880-23254 180-34811 SOLAR GENERATORS Measurement and correlation of structural response Concept definition study of small Brayton cycle to inlet hamershock phenomena on an F-14 airplane engines for dispersed solar electric power systems 180-314975 RASA-CE-159592] 880-22778 SHOCK TESTS SOLID PROPELLANTS Shock loading on reinforced splice joints of ultra A primitive variable computer model for combustion high modulus graphite/epoxy cone frustum within solid fuel ramjets advanced interceptor structures (AD-A081081] 880-23319 A80-34811 SOUND FIELDS SHOCK WAVE ATTENUATION Experimental verification of propeller noise Forward acoustic performance of a shock-swallowing prediction high-tip-speed fan (QF-13) [hAl PAPER 80-0994] 180-35957 [NASA-TP-1668] 880-23100 A theoretical study of the coherence of jet noise SHOCK WAVE PROFILES [lIlA PAPER 80-1005] 180-35967 Stationary flow past the lower surface of a On the sound field generated by a fan in a piecewise planar delta wing with supersonic hard-walled baffled duct with uniform flow leading edges NLR-TB-78024-U] N80-23106 A80-34708 SOUND GENERATORS SHORT HAUL AIRCRAFT Theoretical prediction of nonlinear propagation Upper surface blowing noise of the NASA-Ames quiet effects on noise signatures generated by short-haul research aircraft subsonic or supersonic propeller or rotor-blade [hAl PAPER 80-1064) 180-36002 tips SHORT TAKEOFF AIRCRAFT [NASA-TP-1660) 880-22265 Jet flap impingement noise from a full-scale STOL SOUND PRESSURE REP engine-wing system Acoustic pressures on a prop-fan aircraft fuselage A80-34594 surface Acoustic characteristics of the external upper [hAl PAPER 80-1002] 180-35965 surface blowing propulsive-lift configuration SOUND PROPAGATION [AIAA PAPER 80-1063] A80-36001 Noise from a vibrating propeller Development of the A-6/circulation control wing [lIlA PAPER 80-1011] A80-35969 flight demonstrator configuration SOUND TRANSMISSION [AD-A081241] 880-22365 Determining the optimal fan silencer design of Estimation of wind shear and thrust loss during aircraft engines STOL aircraft landing approach A80-34396 N80-23296 Experimental investigation of sound absorption in SHROUDED TURBINES a flow-carrying channel with a sound-absorbing Thermal response turbine shroud study lining [AD-A080620] 880-22352 A80-34399 SIDELOBE REDUCTION Suppression of self-oscillations in combustion Frequency independent sidelobe suppression and chambers by means of resonance sound absorbers lobesharpening using broad beam antennas 18 0-34 400 A80-34178 Model studies of acoustic resonators SIDESLIP A80-34403 Note on the yawing moment due to side slip for Transmission of high frequency sound waves through swept-back wings a slug flow jet A80-33280 [1111 PAPER 80-0969] A80-35944 Noise transmission and control for a light, twin-engine aircraft [AIAA PIPER 80-1036] 180-35984

1-31

SOUND WAVES SUBJECT INDEX

SOUND WAVES STRAIN GAGES Propagation of acoustic waves in a nonuniformly Low profile strain gage applications telemetered heated medium from rotating machinery A80-34388 180-36153 Acoustic effects on the flow and the noise STBAPDOWN INERTIAL GUIDANCE spectrum of supersonic jets Optimal estimation applied to redundant strapped A80-34402 down inertial sensors for navigation and flight model studies of acoustic resonators control A80-34403 N80-22295 Transmission of high frequency sound raves through STRESS ANALYSIS a slug flow jet Structural design loads for future airplanes (AIRA PAPER 80-0969) A80-35944 [AIAR 80-0813) 180-35094 SPACECRAFT STRUCTURES STRESS CONCENTRATION Development of fire-resistant, low smoke Investigation of the stress distribution in the generating, thermally stable end items for surface layer of aircraft engine components commercial aircraft and spacecraft using a basic A80-342.35 polyimide resin An investigation of residual stresses in simulated [NASA-C8-160576] 1180-22492 ring panels of 7075-T6 aluminum SPARN IGNITION [AD-A080863] N80-23693 The spark-ignition aircraft piston engine of the STRESS CORROSION future Aircraft carrier exposure tests of aluminum alloys 1180-22337 [AD-A081060] N80-23433 SPATIAL DISTRIBUTION STRESS-STRAIN RELATIONSHIPS A theoretical, study of the coherence of jet noise A study of the stress-strain state of shaped [AIAA PAPER 80-1005] A80-35967 hollow blades for radial superchargers SPECTRAL SIGNATURES A80-34351 Propeller signatures and their use --- aircraft STRUCTURAL ANALYSIS noise and vibration measurements and analysis A study of the stress-strain state of shaped [AIAA PAPER 80-1035] A80-35983 hollow blades for radial superchargers SPECTRUM ANALYSIS A80-34351 Spectral analysis of non-stationary random The outside has to be bigger than the inside processes. Application to noise of flyover type volume requirements calculation and optimal [ONERA-NT-1979-4] 1180-24134 design of supersonic aircraft SPOT WELDS [AIAA 80-0726] A80-35031 Developments in ultrasonic welding for aircraft Fluid and structural measurements to advance gas A80-34797 turbine technology SPRAY NOZZLES A80-36145 Reduction of aerodynamic drag of external spray An aeroelastic analysis of the Sheriff wing booms and nozzles used on DC-6 aircraft (80-234) 1180-23274 A80-34596 Improved packaging for the LN-31 inertial SPRAYED COATINGS measurement unit (P-15 aircraft) Development of improved-durability plasma sprayed [AD-A081745) N80-23293 ceramic coatings for gas turbine engines Decision analysis of Advanced Scout Helicopter [NASA-TB-81512] 1180-23313 candidates SPRAYING [AD-A081483] 1180-23298 Wake vortex trajectories of low flying spray STRUCTURAL DESIGN aircraft Development of a structural overload warning A80-34595 system for modern high performance aircraft STABILITY DERIVATIVES A80-34974 Wind tunnel investigation of active controls CAD produced aircraft drawings technology applied to a DC-10 derivative [AIAR 80-0732] A80-35036 [AIAA 80-0771] A80-35062 Preliminary design of composite wing-box STABILITY TESTS structures for global damage tolerance An assessment of the stability and opening [AIAA 80-0755] A80-35049 characteristics of cruciform parachutes Structural design loads for future airplanes (BU-238] 1180-23276 [AIRA 80-0813] A80-35094 STANDARDS Integrated thermal-structural finite element Opportunities analysis of potential advanced analysis --- for applications to hypersonic vortex systems separation standards transport design (AD-A081479) 1180-23281 [AIAA 80-0717] A80-35098 STATIC PRESSURE Turbopropulsion combustion technology assessment Measurement of local skin friction and static [AD-A080748] N80-23323 pressure on a swept ring in flight STRUCTURAL ENGINEERING [FFA-Au-1370] 1180-22282 Composite wing/fuselage integral concept STATISTICAL DISTRIBUTIONS (AIAA 80-0744] A80-35044 Statistical review of counting accelerometer data Built-up low-cost advanced titanium structures for Wavy and Marine fleet aircraft /BLAIS/ [AD-A080580] 1180-22308 (AIRA 80-0745] 180-35045 STATOR BLADES STRUCTURAL STABILITY Design and investigation of static pressure Active flutter suppression control law definition compressor cascades behind impulse-rotors via least squares synthesis [DFVLR-FB-79-17] N80-22353 [AIRA 80-0765) A80-35057 STEERABLE ANTENNAS F-16 flutter suppression system investigation A broadband, circularly polarized, phase steered [AIAA 80-07681 180-35060 array Elevated temperature structural testing of A80-34166 advanced missiles Electronically steered antennas (AIAA 80-0812] A80-35093 A80-34169 STRUCTURAL STRAIN STEERING Fatigue at high temperatures: Examination of the Predictive guidance for interceptors with time lag behavior of gasturbine casting materials also in in acceleration simultaneous temperature and strain cycles A80-32682 [BMFT-FB-T-79-26] N80-23444 STIFFNESS STRUCTURAL VIBRATION The influence of bending-torsional coupling on the Vibration reduction with higher harmonic blade buckling load of general orthotropic, midplane feathering for helicopters with two-bladed symmetric and elastic plates teetering and four-bladed hingeless rotors [NLR-TR-77 126-U] N80-22753 (AIAA 80-0670] A80-34996

A-32

SUBJECT INDEX SYNTHETIC FUELS

Multicyclic control for helicopters - Research in SUPERSONIC TRANSPORTS progress at Ames Research Center Some unique characteristics of supersonic cruise [AIAA 80-0671] 880-34997 vehicles and their effect on airport community STRUCTURAL WEIGHT noise Analytical study of interior noise control by (AIAA PAPER 80-0859) 880-32861 fuselage design techniques on high-speed Prediction of noise constrained optimum takeoff propeller-driven aircraft procedures [AIAA PAPER 80-1001] 880-35964 [AIAA PAPER 80-1055] 880-35996 SUBROUTINES Current problems and the future in advanced The VIREA-8 subsonic aerodynamic nuclear gust supersonic transport noise vulnerability code [AIAA PAPER 80-1056] A80-35997 (AD-A081722] 880-23256 Minimum mass sizing of a large low-aspect ratio SUBSONIC AIRCRAFT airframe for flutter-free performance Advanced high speed commercial aircraft - 2000 (NASA-TM-81818] 880-23683 [AIAA PAPER 80-0937] 880-32898 SUPPORTS Wind tunnel investigation of an all flush orifice Effect of a flexibly mounted store on the flutter air data system for a large subsonic aircraft speed of a wing conducted in a Langley 8 foot transonic [NASA-CR-159245] 880-22356 pressure tunnel SUPPRESSORS (NASA-TP- 1642] 880-23304 Investigation of internal control laws for SUBSONIC FLOW wing/store flutter suppression The harmonically oscillating body in subsonic [8188 80-0764] 880-35056 flow: Effect of compressibility Impact of flight effects on nultitube suppressor [ESA-TT-584] 880-23270 design SUBSONIC SPEED (AIRA PAPER 80-1029) A80-35979 Modern fluid dynamics of subsonic and transonic SURFACE FINISHING flight Comparison of surface treatments of aluminium and [AIAA PAPER 80-0861) 880-33274 their influence on long term strength of metal SUBSONIC WIND TUNNELS bonds Unsteady aerodynamic forces on a subsonic 180-34805 rectilinear cascade of blades SURFACE LAYERS (P88-90007] 880-23266 Investigation of the stress distribution in the SUPERCRITICAL FLOW surface layer of aircraft engine components Supercritical wing design studies for transport 880-34235 aircraft. Volume 1: Wing design and wind SURFACE PROPERTIES tunnel measurements An investigation into measuring runway surface (BMFT-PB-W-19-06-VOL-1] N80-22275 texture by the grease patch and outflow meter A comparison of various numerical methods for methods calculating supercritical inviscid isentropic [S/T-MEMO-2/19] N80-22372 flow over two-dimensional aerofoils SURFACE ROUGHNESS [S/T-BEMO-4/75] 880-22278 A practical method for predicting roughness SUPEBCBITICAL WINGS effects on aircraft Unsteady aerodynamics of conventional and (FFA-AU-1413) N80-22316 supercritical airfoils Roughness effects on fuel consumption for two [AIAA 80-0734] 880-35038 commercial aircraft: McDonnell Douglas Dc-9 and Supercritical wing design studies for transport DC-10 aircraft. Volume 2: Theoretical studies (PPA-AU-1456] 880-22320 [BNPT-FE-W-79-07-VOL-2] N80-22276 SURFACE WATER Civil component program wing section. Trials to compare the stopping performance of Predimensioning of a supercritical wing three anti-skid systems and to demonstrate [ESA-TT-542] N80-22317 methods of determining, aircraft stop distances Summary of data required for the AGAED SMP on the standard military reference wet surface activity standard aeroelastic configurations - (S/T-MEMO-3/79) 880-22318 two-dimensional configurations SWEPT FORWARD WINGS [NIB-RP-79015-U] N80-23273 Aeroelastic tailoring of a forward swept wing and SUPERSONIC AIRCRAFT comparisons with three equivalent aft swept wings Advanced high speed commercial aircraft - 2000 (AIAA 80-0794) 880-35076 (AIRA PAPER 80-0937) A80-32898 Aeroelastic tailoring of forward swept composite Noise characteristics of supersonic passenger planes wings AS 0-343 8 7 (AIAA 80-0795) 880-35077 The outside has to be bigger than the inside A wind tunnel demonstration oX the principle of volume requirements calculation and optimal aeroelastic tailoring applied to forward swept design of supersonic aircraft wings (AIAA 80-0726] 880-35031 (8188 80-0796) A80-35078 Supercritical wing design studies for transport SWEPT WINGS aircraft. Volume 2: Theoretical studies Calculation of the turbulent boundary layer on an (BMFT-FB-W-79-07-VOL-2] 880-22276 infinite swept wing using a three-dimensional SUPERSONIC AIRFOILS mixing length model Stationary flow past the lower surface of a (ESA-TT-534) 880-22273 piecewise planar delta wing with supersonic Measurement of local skin friction and static leading edges pressure on a swept wing in flight A80-34708 [PFA-Au-1370] N80-22282 SUPERSONIC BOUNDARY LAYERS SWEPTBACK WINGS Supercritical wing design studies for transport Note on the yawing moment due to side slip for aircraft. Volume 2: Theoretical studies swept-back wings [BEFT-F8-W-79-07-VOL-2] 880-22276 A80-33280 SUPERSONIC COMPRESSORS Aeroelastic tailoring of a forward swept wing and Design and investigation of static pressure comparisons with three equivalent aft swept wings compressor cascades behind impulse-rotors (AIRA 80-0794] 180-35076 (DPVLR-FR-79-17) 880-22353 SYNTHESIS SUPERSONIC PLIGHT Research on diamantane and other high density Modern fluid dynamics of supersonic and hypersonic [AD-A080749] 880-23474 flight SYNTHETIC FUELS [AIAA PAPER 80-0862] A80-33275 Research on diamantane and other high density SUPERSONIC JET PLOW [AD-A0807 149] 880-23474 Acoustic effects on the flow and the noise spectrum of supersonic jets A80-34402

8-33

SYSTEM EFFECTIVENESS SUBJECT INDEX

SYSTEM EFFECTIVENESS Optical advances in laser transit anemonetry Description of an experimental (hydrogen peroxide) 180-36139 rocket system and its use in measuring aileron Fluid and structural measurements to advance gas and rudder effectiveness of a light airplane turbine technology [NASA-TP-1647] 880-22358 A80-36145 SYSTEM FAILURES An overview of NASA research on positive Validation Methods Research for Fault-Tolerant displacement general-aviation engines Avionics and Control Systems: Working Group B80-22336 Meeting, 2 Turbopropulsion combustion technology assessment (NASA-CE-2130] 880-23008 [AD-A080748] N80-23323 SYSTEMS ANALYSIS TECHNOLOGY UTILIZATION Easy-ACTS dynamic analysis. Users manual The impact of global positioning system on [AD-A081160] N80-23258 guidance and controls systems design of military SYSTEMS ENGINEERING aircraft. Volume 21: Specific application Development of a structural overload warning study no. 1, close air support system for modern high performance aircraft [AGARD-AR-147-VOL-2A] N80-23303 180-34974 TELEMETRY Synthesis of a theoretical approach for employing Low profile strain gage applications telemetered adaptive configuration management in from rotating machinery aeronautical weapon system programs A80-36153 N80-23196 The design, development and operation of gas Visually Coupled System: Computer Generated turbine radio telemetry systems Imagery (VCS-CGI) engineering interface A80-36154 [AD-A080931] N80-23306 TELEVISION CAMERAS Practical optimal flight control system design for A solid state /CCD/ cockpit television system helicopter aircraft. Volume 1: Technical Report 180-34190 [NASA-CR-3275] N80-23328 TELEVISION SYSTEMS Design, development and implementation of an A solid state /CCD/ cockpit television system active control system for load alleviation for a 180-34190 commercial transport airplane TEMPERATURE EFFECTS [AGARD-A5-683) 880-23331 Engine environmental effects on composite behavior SYSTEMS MANAGEMENT moisture and temperature effects on Technology to increase airport capacity mechanical properties [AIRA PAPER 80-0920] 180-32890 [AIAA 80-0695] 180-35101 TEMPERATURE GRADIENTS Propagation of acoustic waves in a nonuniforaly II heated medium TAIL ASSEMBLIES A80-34388 A study of panel lcads and centers of pressure of TEMPERATURE MEASUREMENT three different cruciform aft-tail control Impact of new instrumentation on advanced turbine surfaces of a wingless missile from Mach 1.60 to research 3.70 180-36155 (NASA-TN-81787] N80-23251 Temperature and pressure measurement techniques TAKEOFF for an advanced turbine test facility Prediction of noise constrained optimum takeoff A80-36157 procedures TEMPERATURE SENSORS [AIAA PAPER 80-1055] 180-35996 Combustion-gas temperature sensors for turbine and TARGET ACQUISITION turbojet engines Design of an integrated flight/fire control system A80-34237 including movable gun and gimbaled line of sight TEST FACILITIES tracker Temperature and pressure measurement techniques 880-22355 for an advanced turbine test facility Using vertical gust alleviation to improve the A80-36157 target tracking capability of the control Cryogenic wind tunnels: A selected, annotated configured YF-16 bibliography [AD-A080520] N80-22360 [NASA-TM-80168-SUPPL] N80-23333 TECHNOLOGICAL FORECASTING THERMAL CONTROL COATINGS Air transportation 2000 - A challenge for new Development of improved-durability plasma sprayed technology ceramic coatings for gas turbine engines [AIAA PAPER 80-0945] A80-32899 [NASA-TM-81512] N80-23313 The impact of fuels on aircraft technology through THERMAL ENVIRONMENTS the year 2000 Integrated thermal-structural finite element [AIAA PAPER 80-0896] 180-35898 analysis --- for applications to hypersonic New opportunities for future, small, transport design General-Aviation Turbine Engines (GATE) [AIAA 80-0717] A80-35098 N80-22335 THERMAL EXPANSION The spark-ignition aircraft piston engine of the Economical processing of fiber-reinforced future components with thermal expansion molding 880-22337 [NASA-TB-75738] 880-22412 Outlook for advanced concepts in transport aircraft THERMAL FATIGUE (NASA-TM-81810] N80-23283 Fatigue at high temperatures: Examination of the Turbopropulsion combustion technology assessment behavior of gasturbine casting materials also in (AD-A080748] 880-23323 simultaneous temperature and strain cycles TECHNOLOGY ASSESSMENT [BMFT-FB-T-79-26] N80-23444 Aeropropulsion in year 2000 THERMAL STABILITY [AIAA PAPER 80-0914] A80-32887 Development of fire-resistant, low smoke Technology to increase airport capacity generating, thermally stable end items for [1111 PAPER 80-0920] 180-32890 commercial aircraft and spacecraft using a basic Technology requirements and readiness for very polyimide resin large aircraft (NASA-CB-160576) N80-22492 [AIAA PAPER 80-09351 180-32897 THERMODYNAMIC CYCLES Big-fan engines - A new US generation Avco Lycoming QCGAT program design cycle, A80-3'4216 demonstrated performance and emissions New developments in US military fighter engines N80-22332 180-34217 THERMODYNAMIC PROPERTIES Development and application concepts for trainer Thermal response turbine shroud study and combat-trainer versions of combat Jet aircraft [AD-A080620] 880-22352 A80-35183

A-311 SUBJECT INDEX TURBINE ENGINES

Property screening and evaluation of ceramic TRANSONIC FLOW turbine engine materials Laser anemometer measurements in a transonic axial - [AD-A080963] N80-23322 flow compressor rotor THREE DIMENSIONAL BOUNDARY LAYER A80-36141 Calculation of the turbulent boundary layer on an Transonic wing DPVLR-F4 as European test model infinite swept wing using a three-dimensional (NASA-TN-75752] 1180-22260 ailing length model Transonic kernel function method for unsteady flow (ESA-TT-534] 1180-22273 calculations using a unified linear pressure THREE DIMENSIONAL FLOW panel procedure Impact of new instrumentation on advanced turbine (AD-A080227] 1180-22267 research Summary of data required for the AGABD SEP A80-36155 activity standard aeroelastic configurations - Numerical flow field program for aerodynamic two-dimensional configurations heating analysis. Volume 1: Equations and (NLR-NP-79015-1J] 1180-23273 results TRANSONIC FLUTTER [AD-A081471] 1180-23255 Preliminary measurements of aerodynamic damping of Three dimensional flow investigation with a method a transonic compressor rotor of characteristics in the inlet region and the 180-36152 blade-to-blade channels of supersonic axial TRANSONIC SPEED compressors Analysis of experiments on the effects of jet [ONERA-NT-1979-1 ] 1180-23325 plumes on pressure distribution over a THRUST cylindrical afterbody at transonic speeds Estimation of wind shear and thrust loss during [AD-A081647] 1180-23259 STOL aircraft landing approach TRANSONIC WIND TUNNELS 1180-23296 Aerodynamic characteristics of moving THRUST VECTOR CONTROL trailing-edge controls at subsonic and transonic Static calibration of a two-dimensional wedge speeds nozzle with thrust vectoring and spanwise blowing [RAE-TM-STRUC-947] - 1180-22281 (NASA-T11-81161] 1180-23317 IWINTAN: A program for transonic wall TH UN D BBS TORN S interference assessment in two-dimensional wind Storm hazards '79: F-106B operations summary tunnels (NASA-TN-81779] 1180-23282 [NASA-TN-81819] 1180-23332 TIRE LAG TRANSPORT AIRCRAFT Predictive guidance for interceptors with time lag Long range very large aircraft supply system for in acceleration civil/military application with special emphasis A80-32682A on water-based aircraft TIP SPEED [AIAA PAPER 80-0903] A80-32882 Model rotor low frequency broadband noise at Noise characteristics of supersonic passenger planes moderate tip speeds A80-34387 [AIAA PAPER 80-1013] A80-35971 Integrated thermal-structural finite element TITANIUM analysis --- for applications to hypersonic Built-up low-cost advanced titanium structures transport design /BL ATS/ [AIAA 80-0717] A80-35098 [AIAA 80-0745] A80-35045 Calculation of the interference effects between TOWERS the engine wing and the base wing of a civil and Dynamics of a flexible rotor-tower system military transport aircraft by the vortex [ASRL-TR-194-1] 1180-23862 lattice method TRACKING (POSITION) (ESA-TT-493] 1180-22272 Precision controllability of the YP-17 airplane Supercritical wing design studies for transport [NASA-TP-1677] 1180-23327 aircraft. Volume 1: wing design and wind TRAILING EDGES tunnel measurements Experimental study of airfoil trailing edge noise: [BEET-FR- W-79-06-VOL-1] N80-22275 Instrumentation, methodology and initial results Conceptual studies of a long-range transport with [NASA-CB-163007] 1180-22264 an upper surface blowing propulsive lift system TRAILING-EDGE FLAPS [NASA-TN-81196] 1180-23249 Aerodynamic characteristics of moving Outlook for advanced concepts in transport aircraft trailing-edge controls at subsonic and transonic [NASA-TE-81810J N80-23283 speeds Design, development and implementation of an fBAE-TE-STEUC-947] 1180-22281 active control system for load alleviation for a TRAINING AIRCRAFT commercial transport airplane Development and application concepts for trainer [AGARD-AR-683] 1180-23331 and combat-trainer versions of combat jet aircraft Flight service evaluation of Kevlar-49 epoxy A80-35183 composite panels in wide-bodied commercial TRAJECTORY ANALYSIS transport aircraft A new algorithm for horizontal capture trajectories (NASA-CE-159231] 1180-23371 [NASA-TH-81186] 1180-22297 TRAVELING NAVE TUBES TRANSFER OF TRAINING Airborne radar coherent transmitters Platform motion contributions to simulator A80-34 159 training effectiveness. Study 3: Interaction TURBINE BLADES of motion with field-on-view System to measure the pressure distribution on fan (AD-A078426] 1180-23334 aerofoil surfaces during flutter conditions TRANSIENT RESPONSE A80-36 144 Two-dimensional finite-element analyses of Digital system for dynamic turbine engine blade simulated rotor-fragment impacts against rings displacement measurements and beans compared with experiments A80-36151 [NASA-CE-159645] 1180-22323 Nonlinear, three-dimensional finite-element TRANSMISSIONS (MACHINE ELEMENTS) analysis of air-cooled gas turbine blades AB-1S high-survivable transmission system [NASA-TP-1669] 1180-227314 [AD-A080568] N80-22311 Unsteady aerodynamic forces on a subsonic TRANSONIC CORPRESSORS rectilinear cascade of blades Preliminary measurements of aerodynamic damping of [PNR-90007] 1180-23266 a transonic compressor rotor TURBINE ENGINES A80-36152 Damage tolerant design and test considerations in TRANSONIC FLIGHT the engine structural integrity program --- for Modern fluid dynamics of subsonic and transonic aircraft turbines flight [AIAA 80-0784] A80-35072 [AIRA PAPER 80-0861] A80-33274 New opportunities for future, small, General-Aviation Turbine Engines (GATE) N80-22335

A-35 TURBINE INSTRUMENTS SUBJECT INDEX

TURBINE INSTBUNENTS Avco Lycoming quiet clean general aviation Laser-optical blade tip clearance measurement system turbofan engine A80-36137 N80-22333 Low profile strain gage applications telemetered cP6 jet engine performance improvement: New fan from rotating machinery (NASA-CB-159699) N80-23309 A80736153 Turbopropulsion combustion technology assessment Impact of new instrumentation on advanced turbine [80-8080748] N80-23323 research FlOG exhaust nozzle area control A80-36155 N80-23513 Temperature and pressure measurement techniques Status of NASA full-scale engine aeroelasticity for an advanced turbine test facility research A80-36157 [NASA-TR-81500] N80-23678 TURBINES TUB 50 FAN S The aerodynamics of axial flow wind power turbines System to measure the pressure distribution on fan [CsIR-BE-1619] N80-23781 aerofoil surfaces during flutter conditions Vertical axis wind turbine development: Executive 880-36 144 summary Forward acoustic performance of a shock-swallowing [ORO-51 35-77-5-SUER] N80-23845 high-tip-speed fan (QP-13) Vertical axis wind turbine development [NASA-TP-1668] N80-23100 [OEO-5135-77-5] N80-23846 cF6 jet engine performance improvement: New fan TO RB OCOR PB B S SOBS [NASA-CE-159699) N80-23309 A laser-two-focus /12?,' velocimeter for automatic TURBOJET ENGINES flow vector measurements in the rotating Engine environmental effects on composite behavior components of turbomachines moisture and temperature effects on 880-36138 mechanical properties Unsteady pressure measurements and data analysis (AIAA 80-0695] 880-35101 techniques in axial-flow compressors Status of NASA full-scale engine aeroelasticity 880-36143 research Three dimensional flow investigation with a method 880-35906 of characteristics in the inlet region and the Qualification of cooling systems design for high blade-to-blade channels of supersonic axial temperature on a turbine facility compressors [ONERA, 12 NO. 1980-15] 880-36156 [ONERA-NT-1979-1 ] N80-23325 Atmospheric dispersion of high velocity jets TURBOFAN AIRCRAFT [80-8081612] N80-23321 Advanced turboprop potential for high speed Engine environmental effects on composite behavior N80-22343 (NASA-TM-81508] N80-23370 TURBOFAN ENGINES Status of NASA full-scale engine aeroelasticity The future of civil turbo-fan engines research [8188 PAPER 80-0893) 880-32876 (NASA-TN-81500) 1180-23678 Big-fan engines - A new US generation TURBONACBINE BLADES 880-34216 A study of the stress-strain state of shaped New developments in US military fighter engines hollow blades for radial superchargers 880-34217 A80-34351 The DC-8 re-engining program TURBORACBINEBI 880-34218 Optical advances in laser transit anemometry Experimental study of fan-noise silencers of A80-36139 aircraft turbojet engines unsteady aerodynamic measurement techniques for A80-34398 turbomachinery research Jet flap impingement noise from a full-scale STOL A80-36142 EB? engine-wing system Low profile strain gage applications telemetered 880-34 594 from rotating machinery Status of NASA full-scale engine aeroelasticity 880-36153 research TURBOPROP AIRCRAFT 880-35906 Acoustic pressures on a prop-fan aircraft fuselage QCSEB fan exhaust bulk absorber treatment evaluation surface [AIAA PAPER 80-0987] 880-35952 [AIAA PAPER 80-1002) 880-35965 Study and experimental tests of fibrous acoustic Noise transmission and attenuation by stiffened treatment for reduction of fan noise from XP3-1 panels turbofan engine [AIAA PAPER 80-1034] 880-35982 [8188 PAPER 80-0988] 880-35953 Advanced turboprop potential for high speed Fan noise caused by the ingestion of anisotropic 1180-22343 turbulence - A model based on axisymoetric Acoustic test and analyses of three advanced turbulence theory turboprop models [8188 PAPER 80-1021] 880-35977 [NASA-CR-159667] 1180-23311 Analytical study of the effects of wind tunnel TURBOPROP ENGINES turbulence on turbofan rotor noise Acoustic measurements of three Prop-Pan models [8188 PAPER 80-1022] 880-35978 [AIAA PAPER 80-0995] A80-35958 Model tests demonstrating under-wing installation Preliminary study of advanced turboprop and effects on engine exhaust noise turboshaft engines for light aircraft --- cost [AIAA PAPER 80-1048] 880-35992 effectiveness Temperature and pressure measurement techniques (NASA-TM-81467] N80-22350 for an advanced turbine test facility TURBO SHAFTS A80-36157 Preliminary study of advanced turboprop and Aisesearch QCGAT engine, airplane, and nacelle turboshaft engines for light aircraft -- cost design features effectiveness N80-22328 [NASA-TN-8 1467] 1180-22350 AiResearch QCGAT engine performance and emissions TURBULENCE tests Analysis of NASA JP-4 fire tests data and N80-22329 development of a simple fire model AiResearch QcGAT engine: Acoustic test results [NASA-cR-159209] N80-22432 N80-22330 TURBULENCE EFFECTS QcGAT aircraft/engine design for reduced noise and Study on the dynamics of small flight vehicles emissions under gust loading N80'-22331 A80-34653 Avco Lycoming QCGAT program design cycle, Review of nonstationary gust-responses of flight demonstrated performance and emissions vehicles B80-22332 [8188 80-0703] 880-35097

A-36 SUBJECT INDEX VOLTAGE REGULATORS

Fan noise caused by the ingestion of anisotropic VERTICAL NOTION turbulence - A mode], based on axisymluetric Operations manual: Vertical Notion Simulator turbulence theory (VMS) S.08 [AIAA PAPER 80-1021] A80-35977 (NASA-TN-81180] 880-23295 Analytical study of the effects of wind tunnel VERTICAL ORIENTATION turbulence on turbofan rotor noise Vertical axis wind turbine development: Executive [AIlA PAPER 80-1022] A80-35978 summary TURBULENT BOUNDARY LAYER (ORO-5135-77-5-SUBN] N80-23845 Calculation of the turbulent boundary layer on an Vertical axis wind turbine development infinite swept wing using a three-dimensional (080-5135-77-5] 880-23846 mixing length model VERTICAL TAKEOPF AIRCRAFT [ESA-TT-534] 880-22273 Minimum sensitivity controllers with application TURBULENT WANES to VIOL aircraft Experimental investigation of the two-dimensional A80-32759 asymmetrical turbulent wake behind a blade VHF ONNIRANGE NAVIGATION A80-33282 A flight investigation of system accuracies and TWO DIMENSIONAL FLOW operational capabilities of a general Experimental investigation of the two-dimensional aviation/air transport area navigation system asymmetrical turbulent wake behind a blade (BNAV) 180-33282 (AD-1081646) 880-23288 VIBRATION DANPING Active control of rotor blade pitch for vibration U reduction - A wind tunnel demonstration ULTRASONIC TESTS NDI policy and techniques for advanced composites The promise of multicyclic control --- for A80-33121 nondestructive inspection helicopter vibration reduction A80-34765 A80-33123 ULTRASONIC WELDING Vibration reduction with higher harmonic blade Developments in ultrasonic welding for aircraft feathering for helicopters with two-bladed A80-34797 teetering and four-bladed hingeless rotors UNSTEADY FLOW [111k 80-0670] 180-34996 Unsteady aerodynamic measurement techniques for Preliminary measurements of aerodynamic damping of turbomachinery research a transonic compressor rotor A80-36142 A80-36152 Transonic kernel function method for unsteady flow VIBRATION EFFECTS calculations using a unified linear pressure Nulticyclic Control of a helicopter rotor panel procedure considering the influence of vibration, loads, [AD-A080227] 880-22267 and control motion Summary of data required for the AGARD SAE (1111 80-0673) 180-314998 activity standard aeroelastic configurations - VIBRATION ISOLATORS two-dimensional configurations Investigations into an active vibration isolation [NLR-RP-79015-U] 880-23273 system for helicopters with rigid and elastic Axial flow rotor unsteady performance airframe modeling N80-23308 (ESA-TT-531] 880-22315 UNSTEADY STATE Decoupler pylon: Wing/store flutter suppressor Unsteady aerodynamics of conventional and [NASA-CASE-LAR-121468-1] 880-22359 supercritical airfoils Investigations of the design of active vibration [AIAA 80-0734] 180-35038 isolation systems for helicopters with rigid and Unsteady pressure measurements and data analysis elastic modeling of the fuselage techniques in axial-flow compressors (ESA-TT-556) 880-23300 180-36143 VIBRATION NEASUBENENT UPPER SURFACE BLOWN FLAPS Vibration measurements on turbomachjne rotor Acoustic characteristics of the external upper blades with optical probes surface blowing propulsive-lift configuration A80-36146 (kIll PAPER 80-1063] A80-36001 Digital system for dynamic turbine engine blade Upper surface blowing noise of the NASA-Ames quiet displacement measurements short-haul research aircraft A80-36151 [AIAA PAPER 80-1064] A80-36002 VIBRATION BODE Conceptual studies of a long-range transport with An optimization method for the determination of an upper surface blowing propulsive lift system the important flutter modes [NASA-TM-81196] N80-23249 (AIAA 80-0790) 180-35074 USER MANUALS (COMPUTER PROGRAMS) VIBRATIONAL SPECTRA Rotorcraft flight simulation, computer program Propeller signatures and their use --- aircraft C81. Volume 2: User's manual noise and vibration measurements and analysis [AD-A079632] 880-22313 [AIAA PAPER 80-1035] 180-35983 Easy-ACIS dynamic analysis. User's manual VIDEO EQUIPMENT [AD-A081160] 880-23258 Experiences of a 50 8BPS video recording and processing system for PLIB images A80-34163 VISIBILITY VARIABLE PITCH PROPELLERS iBenote sensing methods for determination of slant Active control of rotor blade pitch for vibration range visibility reduction - A wind tunnel demonstration [DPVLR-FB-79-14] 880-23759 180-33121 VISUAL PLIGHT VECTORS (MATHEMATICS) Visually Coupled System: Computer Generated Control system design using vector-valued Imagery (VCS-CGI) engineering interface - performance criteria with application to the (AD-A080931] 880-23306 control rate reduction in parameter insensitive VISUAL PERCEPTION control systems Platform motion contributions to simulator [ESA-TT-512-REV] 880-22363 training effectiveness. Study 3: Interaction VELOCITY DISTRIBUTION Of motion with field-on-view Analysis of NASA JP-4 fire tests data and [AD-A078426] 880-233314 development of a simple fire model VOLTAGE REGULATORS [NASA-CR- 159209] 880-22432 Effects of electric fluctuations in electric power VENTILATION PANS systems of flight vehicles A study of the stress-strain state of shaped hollow blades for radial superchargers A80-35185 A 80-3435 1

1-37 VORTEX GENERATORS SUBJECT INDEX

VORTEX GENERATORS A wind tunnel demonstration of the principle of Influence of external conditions on the generation aeroelastic tailoring applied to forward swept and intensity of vortices at air-intakes wings A80-34238 [AThA 80-0796] A80-35078 VORTICES Analytical study of the effects of wind tunnel Construction of a nonstationary nonlinear theory turbulence on turbofan rotor noise of helicopter rotors (AIAA PAPER 80-1022] A80-35978 A80-34711 Simulation of high bypass ratio engine jet noise Active control of asymmetric vortex effects flight effects by model jet wind tunnel test [AD-A081648] N80-23254 [AIAA PAPER 80-1030] A80-35980 Opportunities analysis of potential advanced Transonic wing DFVLR-P4 as European test model vortex systems separation standards [NASA-TB-75752] 1180-22260 [AD-A081479] 1180-23281 Full-scale wind tunnel-investigation of the Procedural feasibility of reduced spacing under Advanced Technology Light Twin-Engine airplane WVAS operation with applications to Atlanta and (ATLIT) --- Langley full scale tunnel 0-Hare [NASA-TP-1591] 1180-22266 [AD-A081480] N80-23287 Supercritical wing design studies for transport VULNERABILITY aircraft. Volume 1: Wing design and wind The VIBRA-8 subsonic aerodynamic nuclear gust tunnel measurements vulnerability code [BBFT-PB-W-79-06-VOL- 1] 1180-22275 [AD-A081722] N80-2325 A comment on the origin of endwall interference in wind tunnel tests of aerofoils [RAE-TN-AERO-1816] N80-22280 High-speed-propeller wind-tunnel aeroacoustic WALL FLOW results Types of leeside flow over delta wings W80-22344 A80-34652 Application of two design methods for active WARNING SYSTEMS flutter suppression and wind-tunnel test results The automatization of the detection of collision [NASA-TP-1653] 1180-22737 risks for French air traffic control Summary of data required for the AGARD SNP A80-34226 activity standard aeroelastic configurations - Development of a structural overload warning two-dimensional configurations system for modern high performance aircraft (NLR-BP-79015-U] 1180-23273 A80-34974 Wind tunnel tests on the Sheriff twin-engined WAVE PROPAGATION light aircraft Propagaticn of acoustic waves in a nonuniformly [80-241] 1180-23277 heated medium Flight safety of Rogallo hang gliders. A80-34388 Theoretical and experimental study of the flight WEAPON SYSTEMS envelope Survivable C3 --- command, control and [ONERA-NT-1979-8) 1180-23301 communication centers in military electronics WIND TUNNEL WALLS defense TWINTAN: A program for transonic wall A80-34156 interference assessment in two-dimensional wind Synthesis of a theoretical approach for employing tunnels adaptive configuration management in [NASA-TN-81819] 1180-23332 aeronautical weapon system programs WIND TUNNELS N80-23196 Magnetic suspension and balance system: A WEAR TESTS selective annotated bibliography Evaluation of coatings for wear and corrosion - [NASA-TB-80225] N80-22368 Protection in air/fluid accumulators --- for WINDMILLS (WINDPOWNRED MACHINES) Navy aircraft carriers Dynamics of a flexible rotor-tower system A80-34819 [ASRL-TR-194-1] 1180-23862 WEDGES WINDPOWERED GENERATORS Pressure distribution measurements on wedges at The aerodynamics of axial flow wind power turbines subsonic and transonic velocities --- in a [cSIE-NE-1619) N80-23781 transonic wind tunnel Vertical axis wind turbine development: Executive [ESA-TT-554] 1180-23267 summary WEIGHT REDUCTION [OBO-5135-77-5-SUNN] 1180-23845 Built-up low-cost advanced titanium structures Vertical axis wind turbine development /BLATS/ [CRO-5135-77-5] 1180-23846 [AIAA 80-0745] A80-35045 WING FLAPS WELD STRENGTH Jet flap impingement noise from a full-scale STOL Developments in ultrasonic welding for aircraft EBF engine-wing system A80-34797 A80-34594 WIND SHEAR WING LOADING Estimation of wind shear and thrust loss during Direct and inverse problems of flow over a wing of STOL aircraft landing approach finite span in the linear formulation V80-23296 A80-34712 Investigation of landing flare in presence of wind WING NACELLE CONFIGURATIONS shear Model tests demonstrating under-wing installation [DFVLR-28-79-20] 1180-23299 effects on engine exhaust noise WIND TUNNEL TESTS [AThA PAPER 80-1048] A80-35992 Active control of rotor blade pitch for vibration WING OSCILLATIONS reduction - A wind tunnel demonstration Active control of rotor blade pitch for vibration A80-33 121 reduction - A wind tunnel demonstration Experimental investigation of the two-dimensional 180-33121 asymmetrical turbulent wake behind a blade Future of helicopter rotor control A80-33282 180-33 122 Unsteady airloads on a harmonically pitching wing The promise of multicyclic control --- for with external Store helicopter vibration reduction [AIAA 80-0733] A80-35037 180-33 123 Wind tunnel investigation of active controls Unsteady airloads on a harmonically pitching wing technology applied to a DC-10 derivative with external store [AIAA 80-0771] A80-35062 [AIAA 80-0733] 180-35037 Wing/store flutter with nonlinear pylon stiffness Investigation of internal control laws for [AIAA 80-0792] A80-35075 wing/store flutter suppression [lilA 80-07641 180-35056

A-38

SUBJECT INDEX TP-16 AIRCRAFT

Active flutter suppression control law definition via least squares synthesis [AIAA 80-0765] A80-35057 The application of output predictive digital control to wing flutter suppression and terrain following problems (AD-A080419] N80-22361 WING PANELS Preliminary design of composite wing-box structures for global damage tolerance [AIAA 80-0755] A80-35049 Repair of advanced composite structures --- in damaged aircraft [AIAA 80-0776] A80-35066 Wing/store flutter with,nonhinear pylon stiffness [AIAA 80-07923 A80-35075 An investigation of residual stresses in simulated wing panels of 7075-16 aluminum [AD-A080863] 1180-23693 WING SPAN Stationary flow past the lower surface of a piecewise planar delta wing with supersonic leading edges A80-34708 Direct and inverse problems of flow over a wing of finite span in the linear formulation A8 0-34 712 WING-FUSELAGE STONES Investigation of internal control laws for wing/store flutter suppression [AIAA 80-0764] A80-35056 F-16 flutter suppression system investigation [AIAA 80-0768] A80-35060 Recent development of the YF-17 active flutter suppression system [AINA 80-0769) A80-35061 WINGS Current and projected use of carbon composites in United States aircraft A80-34 840 Composite wing/fuselage integral concept [AIAA 80-0744] A80-35044 Transonic wing DFVLR-F4 as European test model [NASA-TM-75752] 1180-22260 Calculation of the interference effects between the engine wing and the base wing of a civil and military transport aircraft by the vortex lattice method (ESA-IT-493] 1180-22272 Effect of a flexibly mounted store on the flutter speed of a wing [NASA-CE-159245] 1180-22356 Decoupler pylon: Wing/store flutter suppressor [NASA-CASE-LAB-12468-1) 1180-22359 An aeroelastic analysis of the Sheriff wing [89-234] 1180-23274 X X RAT APPARATUS A pulsed radiography technique for studying the internal structure of fuel injection jets A80-34588 I'd TAG LASERS Design considerations for an active laser seeker A80-34189 TARING NORENTS Note on the yawing moment due to side slip for swept-back wings A8 0-332 80 YC-14 AIRCRAFT Honeycomb sandwich joints for primary structure of aircraft [AIRA 80-0780] A80-35070 TF-16 AIRCRAFT Using vertical gust alleviation to improve the target tracking capability of the control configured YF-16 [AD-A080520] 1180-22360

A-39 PERSONAL AUTHOR INDEX AERONAUTICAL ENGINEERING 1A Continuing Bibliography (Suppl. 125) AUGUST 1980 Typical Personal Author Index Listing

NAUTHOR ARUJI, K K Studiesof the acoustic transmission characteristics of coaxial nozzles with inverted ASBE, T. L. I velocity profiles, volume 1 Concept definition study of small Brayton cycle I (NASA-CR-159698) 880-11870 engines for dispersed solar electric power systems [NASA-CE-159592] 880-22778 AUZINS, J. Measurement and correlation of structural response NASA I to inlet hamershock phenomena on an F-14 airplane NUMBERACCESSION I A80-34975 NUMBER AVEZARD, L. Propeller light aircraft noise at discrete frequencies [AIAA PAPER 80-0997] Listings in this index are arranged alphabetically by personal author. The title A80-35960 of the document provides the user with a brief description of the subject matter. The report number helps to indicate the type of document cited (e.g. NASA B report, translation. NASA contractor report(. The accession number is located BAEV, V. K. beneath and to the right of the title. e.g. N80-1 1870 Under any one author's A pulsed radiography technique for studying the internal structure of fuel injection jets name the accession numbers are arranged in sequence with the /AA accession A80-34588 numbers appearing first. BALENA, P. J. An analytical model for study of interior noise control for high-speed, propeller-driven aircraft [AIAA PAPER 80-1000] A80-35963 Analytical study of interior noise control by ABEL, I. fuselage design techniques on high-speed Application of two design methods for active propeller-driven aircraft flutter suppression and wind-tunnel test results (AIAA PAPER 80-1001] A80-35964 [NASA-TP-1653] 880-22737 BANKBEAD, H. S.. ABRAHAM, B. Experimental investigation of flutter in mid-stage Air transportation 2000 - A challenge for new compressor designs technology (AIAA 80-0786] A80-35073 [AIRS PAPER 80-0945] A80-32899 BANGER, S. L. ABROL, B. L. Theoretical prediction of nonlinear propagation Processing and analysis of the data from a two effects on noise signatures generated by spool gas turbine engine subsonic or supersonic propeller or rotor-blade A80-36149 tips AGARWALA, V. S. [NASA-TP-1660] 880-22265 Aircraft carrier exposure tests of aluminum alloys BASNEBEY, S. P. [AD-A051060] 880-23433 Air combat maneuvering performance measurement ALBION, N. [AD-A077429] 880-23336 Active control of rotor blade pitch for vibration BAREANGER, .3. P. reduction - A wind tunnel demonstration Laser-optical blade tip clearance measurement system A80-36137 ANODEO, P. A. BARTON, C. K. Opportunities analysis of potential advanced Noise transmission and control for a light, vortex systems separation standards twin-engine aircraft [AD-A081479] 880-23281 [AIAA PAPER 80-1036] A80-35954 Procedural feasibility of reduced spacing under BASBBAKOV, V. X. WVAS operation with applications to Atlanta and Propagation of acoustic waves in a nonuniformly 0 , Hare heated medium (AD-A081480] 880-23287 A80-34355 ANDERSON, J. B. BAZBAXRIN, A. N. E-3A EMP evaluation program A pulsed radiography technique for studying the [AD-A081725] 880-23536 internal structure of fuel injection jets ANDRADE, N. L. A80-34588 Design considerations for an active laser seeker BEALL, B. T. A80-34189 Drilling composites with gun drills ANDRDSZKIEWICZ, S. AS 0-34 809 Selective methods of determining the range of BEAT!, I. engine operation in aircraft crash Trials to compare the stopping performance of investigations. I three anti-skid systems and to demonstrate A80-33106 methods of determining aircraft stop distances Selected methods for defining engine operating on the standard military reference wet surface ranges in the investigation of aircraft [ S/T-NERO-3/79] 880-22318 accidents. II BECK, C. B. Advanced composite structure repair guide ANNOy , N. [AIAA 80-0774] A80-35065 Civil component program wing section. BEHLKE, B. P. Predimensioning of a supercritical wing Corecompressor exit stage study, 2 [ESA-TT-542] N80-2231i [NASA-CB-159812] 880-23312 ARONIN, L. S. BEHNKE, D. L. Shock loading on reinforced splice joints of ultra Evaluation of coatings for wear and corrosion - high modulus graphite/epoxy cone frustum Protection in air/fluid accumulators A80-3481 1 A80-34819

B-i BELL, J. N. PERSONAL AUTHOR INDEX

BELL, J. N. BOGOEOLOV, S. B. Optimal estimation applied to redundant strapped Experimental study of fan-noise silencers of down inertial sensors for navigation and flight aircraft turbojet engines control A80-34398 N80-22295 BORN, A. J. BELOTSEBKOVSKII, S. B. Upper surface blowing noise of the NASA-Ames quiet Construction of a nonstationary nonlinear theory short-haul research aircraft of helicopter rotors [AIAA PAPER 80-1064] A80-36002 A80-34711 BORN, H. P. BELTRABO, H. N. Aerodynamics of the new generation of combat Parametric study of helicopter aircraft systems aircraft with delta wings costs and weights [NASA-TM-75793] N80-22306 [NASA-CR-152315) N80-22305 BOLDING, R. B. BBHEIT, L. J. F-16 flutter suppression system investigation Emergency in-flight egress opening for general [AIAA 80-0768] A80-35060 aviation aircraft BURGOS, J. N80-23511 Selective methods of determining the range of BBEENTI, S. G. engine operation in aircraft crash Lightweight diesel aircraft engines for general investigations. I aviation A80-33106 N80-22338 Selected methods for defining engine operating BERTELRIJD, A. ranges in the investigation of aircraft Measurement of local skin friction and static accidents. II pressure on a swept wing in flight A80-35184 [FFA-AU-1370] N80-22282 BOEISOV, V. K. A practical method for predicting roughness A study of the stress-strain state of shaped effects on aircraft hollow blades for radial superchargers [FFA-AU-1413] N80-22316 A80-314351 Roughness effects on fuel consumption for two BOSSI, J. A. commercial aircraft: McDonnell Douglas Dc-9 and Estimation of wind shear and thrust loss during DC-10 STOL aircraft landing approach [FFA-AU-1456] N80-22320 N80-23296 BESSLING, H. BO!DEN, B. P. Gravimetric investigation of the particle number Magnetic suspension and balance system: A density distribution function in the high speed selective annotated bibliography cascade wind tunnel for laser-anemometry [NASA-TN-80225] N80-22368 measurements BOYLE, D. (DFVLR-FB-79-12 3 N80-22374 New developments in US military fighter engines BETTNEB, T. J. A80-34217 Costs of graphite composite fabrication and repair BEADSHAN, C.. F. A80-314810 A spin-recovery parachute system for light BEZGEESHNOV, A. A. general-aviation airplanes Experimental study of fan-noise silencers of 1180-23512 aircraft turbojet engines BEAITHNAITB, N. S. J. A80-34398 A survey of the high frequency effects associated BRUTIANI, P. K. with the lightning discharge A unique coannular plug nozzle jet noise [OUEL-1290/793 N80-23590 prediction procedure BRENDHOEN, J. V. [AIAA PAPER 80-1007] A80-35968 Atmospheric dispersion of high velocity jets BICEENKOY, E. I. [AD-A081612] 1180-23321 A pulsed radiography technique for studying the BROCKHANN, L. internal structure of fuel injection jets Comparison of surface treatments of aluminium and A80-34588 their influence on long term strength of metal BINDER, G. bonds Supercritical wing design studies for transport A80-34805 aircraft. Volume 1: wing design and wind BROOKS, B. B. tunnel measurements Acoustic measurements of three Prop-Fan models (BNFT-FB-W-79-06-VO1-1 3 N80-22275 [AIAA PAPER 80-0995] A80-35958 BLAKELOCK, J. H. Acoustic test and analyses of three advanced Design of an integrated flight/fire control system turboprop models including movable gun and gimbaled line of sight [NASA-CB-159667] N80-23311 tracker BEOUNERS, A. P. N80-22355 Design study: A 186 kW lightweight diesel BLANKENSHIP, G. L. aircraft engine - - Comparison of aircraft noise-contour prediction [NASA-CE-3261] N80-22326 programs Lightweight diesel aircraft engines for general [AIAA PAPER 80-1057] A80-35998 aviation BLOCKLET, B. N. N80-22338 A comparison of various numerical methods for BROWN, B. D. calculating supercritical inviscid isentropic Evaluation of coatings for wear and corrosion - flow over two-dimensional aerofoils Protection in air/fluid accumulators [S/-MEMO-4/75] N80-22278 A80-34819 BLOOHEE, H. H. BROWN, T. J. QCSEE fan exhaust hulk absorber treatment evaluation Multicyclic control of a helicopter rotor - [AIAA PAPER 80-0987) A80-35952 considering the influence of vibration, loads, OSCEE fan exhaust bulk absorber treatment evaluation and control motion [NASA-TM-81498] N80-23314 (AIAA 80-0673] 180-34998 BLUMENTHAL, B. P. BRUCE, E. P. Air deployment of satellite-tracked drifters Axial flow rotor unsteady performance A80-36291 N80-23308 BOBBITT, P. J. BUCH, A. Modern fluid dynamics of subsonic and transonic Effect of some aircraft loading program flight modifications on the fatigue life of open hole [AXAR PAPER 80-0861] A80-33274 specimens BOBER, L. J. A80-36076 Advanced propeller aerodynamic analysis N80-22345

B-2 PERSONAL AUTHOR INDEX CRAWLEY, E. P.

BURRS, H. CIRCLE, R. L. Supercritical wing design studies for transport aircraft. Volume 1: Wing design and wind A quantitative assessment of the variables involved in crack propagation analysis for tunnel measurements in-service aircraft [BHFT-FB-W--79-06-VOL- 1] N80-22275 (AIAA 80-0752) BURDSALL, B. A. CLARK, P. B. 880-35047 Core compressor exit stage study, 2 A hybrid composite helicopter main rotor blade (NASA-CR-159812] N80-23312 BURNER, A. N., JR. employing pneumatic lift control 880-34808 Gladstone-Dale constant for CF4 CLAEY, J. B. (NASA-TM-80228] N80-24151 BURNBAN, B. Validation Methods Research for Fault-Tolerant Avionics and Control Systems: Working Group The outside has to be bigger than the inside Meeting, 2 (8188 80-0726) A80-35031 BURNS, B. (NASA-CP-2130) B. A. COBLITZ, D. R. 1180-23008 Flight control systems. VII Visually Coupled System: Computer Generated A80-32693 BUSS, D. D. Imagery (VCS-CGI) engineering interface [80-8080931] 1180-23306 VLSI/VHSI device technology COCHRAN, B. P. A80-34175 BUZUKOV, A. A. Temperature and pressure measurement techniques for an advanced turbine test facility A pulsed radiography technique for studying the internal structure of fuel injection 880-36157 jets COCHEANE, J. A. A80-34588 Conceptual studies of a long-range transport with n an upper surface blowing propulsive lift system (NASA-TM-81196) 1180-23249 CANBERLEIN, I. COLE, J. B. Optimal integrated inertial navigation: An actual Airplane wing leading edge variable camber flap example - The R.P.A. aircraft carrier reference N80-23514 system COLLET, P. The importance of runway capacity - An analytical 880-34227 CANAL, B., JR. approach Core compressor exit stage study, 2 88 0-33 2 94 COLLINS, B. N. (NASA-CR-159812) N80-23312 CARPENTIER, N. H. 1101 policy and techniques for advanced composites A80-34765 Electronically steered antennas CONLET, P. M. 880-34169 CARTA, F. 0. A quantitative assessment of the variables Unsteady aerodynamic measurement techniques for involved in crack propagation analysis for turbomachinery research in-service aircraft [AIAA 80-0752] 880-35047 880-36142 CONNER, D. V. CHAPPIN, D. B. Technology requirements and readiness for very The application of output predictive digital large aircraft control to wing flutter suppression and terrain following problems [8188 PAPER 80-0935) 880-32897 Outlook for advanced concepts in transport aircraft (AD-A080419) N80-22361 CHANTS, C. C. [NASA-TM-81810) CONNOB, P. R. N80-23283 Engine environmental effects on composite behavior New commutated Doppler microwave landing system (8188 80-0695) 880-35101 A80-36019 Engine environmental effects on composite behavior COOK, T. N. [NASA-TN-81508] N80-23370 CHANG, N. T. Analysis of helicopter maintenance fault isolation criteria/techniques Noise transmission and attenuation by stiffened (80-8080596] 1180-22257 panels COOKE, N. J. [AIAA PAPER 80-1034] A80-35982 CHAPElS, R. I. A survey of the high frequency effects associated with the lightning discharge Comparison of aircraft noise-contour prediction (OUEL-1290/79) 1180-23590 programs COOLEY, D. E. [8188 PAPER 80-1057) 880-35998 CHERRY, R. B. Investigation of internal control laws for wing/store flutter suppression Air deployment of satellite-tracked drifters [8188 80-0764] A80-35056 880-36291 COPCOTT, N. 06 CHERENUKOIN, G. A. Noise characteristics of supersonic passenger planes An assessment of the stability and opening characteristics of cruciform parachutes A80-34387 CHIRIVELLA, [BU-238] 1180-23276 J. B. COPE, G. A. Ultralean combustion in general aviation piston engines AN-is high-survivable transmission system [AD-A080568] N80-22311 [NASA-CR-163001] 1180-22430 COPLIN, J. CHIVERS, J. N. H. P. System to measure the pressure distribution on fan The future of civil turbo-fan engines [1188 PAPER 80-0893] 880-32876 aerofoil surfaces during flutter conditions COURNUT, A. E. A80-36144 CHONBARD, J. Qualification of cooling systems design for high Propeller light aircraft noise at discrete temperature on a turbine facility (ONERA, TP NO. 1980-15] 880-36156 frequencies COUSINS, N.. T. [AIAA PAPER 80-0997] 880-35960 CHRISTIE, L D. Unsteady pressure measurements and data analysis Aurora /CP-140/ aircraft operational software system techniques in axial-flow compressors 880-34185 COVIE, V. D. A80-36143 CICROSZ, B. Development and application concepts for trainer Damage tolerant design and test considerations in and combat-trainer versions of combat jet aircraft the engine structural integrity program [lilA 80-0784] A80-35072 A80-35183 CEAWLET, E. P.. Preliminary measurements of aerodynamic damping of a transonic compressor rotor 880-36152

5-3 CRIBI, P. PERSONAL AUTHOR INDEX

CRIBI, P. DOBRZTNSKI, U. Projectile/sabot discard aerodynamics Noise generation by jet-engine exhaust deflection [AD-A080538) 1180-22269 [ESA-TT-553] 1180-23104 CURATOLA, J. DONG, J. G. Developments in ultrasonic welding for aircraft Measurement of A80-34797 interference-to-navigation/communication CUSHING, N. B. avionics from cable television (CATV) systems Software impact of selected en route ATC computer [AD-A081430] 1180-23530 replacement strategies DONHAB, B. E. (AD-A081478) 1180-23286 Propeller signatures and their use CZERNIAWSKIJ, S. T. [AIAA PAPER 80-1035] A80-35983 CLST's wing-in-ground effect vehicles DONNELL, N. L. A80-33105 Decision analysis of Advanced Scout Helicopter -candidates [AD-A081483] 1180-23298 D DOENIER, C., JR.. DAHAN, C. Long range very large aircraft supply system for Propeller light aircraft noise at discrete civil/military application with special emphasis frequencies on water-based aircraft [&IAA PAPER 80-0997) A80-35960 (AIAA PAPER 80-0903] A80-32882 Helicopter rotor thickness noise DRABONITCH, S. [AIAA PAPER 80-1012] A80-35970 Electronically steered antennas DAS, A. A80-34169 On disturbance fields of moving singularities in DRIVER, C. aerodynamics and aeroacoustics Some unique characteristics of supersonic cruise [ESA-TT-570) 1180-23269 vehicles and their effect on airport community DAVIS, B. B. noise The modular survivable radar AIAA PAPER 80-0859) A80-32861 A80-34158 DORA, U.I C.. DAVIS, S. S. Project filter holder. Tests on 25 mm dust filter Unsteady aerodynamics of conventional and holders supercritical airfoils [IG-TNO-F-1638] 1180-23887 [AIAA 80-0734] A80-35038 D0GDNDJI, J. DR CREBIEBS, M. Preliminary measurements of aerodynamic damping of Optimal integrated inertial navigation: An actual a transonic compressor rotor example - The R.P.A. aircraft carrier reference A80-36152 system Dynamics of a flexible rotor-tower system A80-34 227 [ASRL-TR-194-1] 1180-23862 DEAL, P. L. DULEBA, G. S. Pilot assessment of two computer-generated display Easy-ACS dynamic analysis. User's manual formats for helicopter instrument approach (AD-A081160) 1180-23258 [NASA-TN-80151] 1180-22321 DUNN, H. J. Storm hazards '79: F-106B operations summary Application of two design methods for active [NASA-TM-81779] 1180-23282 flutter suppression and wind-tunnel test results DBCABAUNPHAI, P. [NASA-TP-1653] N80-22737 Integrated thermal-structural finite element DUPONCHEL, J. P. analysis Impact of flight effects on multitube suppressor [AIAA 80-0717] A80-35098 design DEGRAAF, E. A. B. (AIAA PAPER 80-1029) A80-35979 Failure analysis in aviation DUSKIN, F. [NLR-NP-78028-U] 1180-23284 Release-rate calorimetry of multilayered materials The failure of aircraft structures for aircraft seats [NLR-NP-78040-U] 1180-23285 A80-34223 DENREB, P. A. Release-rate calorimetry of multilayered materials An assessment of the stability and opening for aircraft seats characteristics of cruciform parachutes [AIAA 80-0759) A80-35052 [50-238] 1180-23276 DW!EN, B.. S. DEROSE, R. D. Determining sea-ice boundaries and ice roughness Low profile strain gage applications telemetered using GEOS-3 altimeter data from rotating machinery [NASA-CB-156862] 1180-22758 A80-36153 DESNABAIS, B. N. Wing/store flutter with nonlinear pylon stiffness E [AIAA 80-0792] A80-35075 EDNONDS, .3.. DI, U. S. A flight investigation of system accuracies and Transonic kernel function method for unsteady flow operational capabilities of a general calculations using a unified linear pressure aviation/air transport area navigation system panel procedure (RNAV) [AD-A080227] 1180-22267 [AD-A081646] 1180-23288 DICKINSON, L. V., JR. EISENBERG, J. D. Advanced high speed commercial aircraft - 2000 Preliminary study of advanced turboprop and [AIEA PAPER 80-0937] A80-32898 turboshaft engines for light aircraft DICRISTINA, V. [NASA-TN-81467] 1180-22350 Hypersonic heat transfer test program in the VKI EL-TAllER, E. ! longshot facility Experimental investigation of the two-dimensional [AD-A08 1467] 1180-23257 asymmetrical turbulent wake behind a blade DIBASCIO, A. J. A80-33282 Synthesis of a theoretical approach for employing ELKINS, B. T. adaptive configuration management in Concept definition study of small Brayton cycle aeronautical weapon system programs engines for dispersed solar electric power systems N80-23196 [NASA-CB-159592] 1180-22778 DITTNAE, J. H. ENGLAB, R. J. High-speed-propeller wind-tunnel aeroacoustic Development of the A-6/circulation control wing results flight demonstrator configuration H80-22344 (AD-A081241] 1180-22365 DOBLER, F. I. ENGLE, H. C. Concept definition study of small Brayton cycle An investigation of residual stresses in simulated engines for dispersed solar electric power systems wing panels of 7075-T6 aluminum [NASA-CR-159592] 1180-22778 (AD-A080863] N80-23693

B-4 PERSONAL AUTHOR INDEX GOLUBEVA, I. A.

HEREIN, G. I. FUCHS, N. Acoustic effects on the flow and the noise Design and investigation of static pressure spectrum of supersonic jets compressor cascades behind impulse-rotors A80-34402 [DFVLR-PB-79- 17) 880-22353 ERNOULT, N. FUHRKEN, B. Spectral analysis of non-stationary random Noise generation by jet-engine exhaust deflection processes. Application to noise of flyover type [ESA-TT-553] N80-23104 [ONERA-NT-1979-14] 880-24134 FUNAKANA, N. Experimental investigations on the vibration of blades due to a rotating stall FAL.ABSKI, N. D. F A80-35912 Static calibration of a two-dimensional wedge nozzle with thrust vectoring and spanwise blowing [NASA-TH-81161] N80-23317 GADOS, B. G. FANUCCI, J. N. Procedural feasibility of reduced spacing under Vertical axis wind turbine development: Executive WVAS operation with applications to Atlanta and summary O • Hare [ORO-5135-77-5-SUNN) 880-23845 (AD-A081480] 880-23287 Vertical axis wind turbine development GAGLIANI, J. [080-5135-77-5] 880-23846 Development of fire-resistant, low smoke FARASSAT, F. generating, thermally stable end items for A collection of formulas for calculation of commercial aircraft and spacecraft using a basic rotating blade noise - Compact and noncompact polyimide resin source results [NASA-CR-160576] 88 0-22492 [AIAL PAPER 80-0996] A80-35959 GAJENSKI, B.. PARIS, N. S. New mathematical formula for the Cropduster Design considerations for an active laser seeker operational cycle A80-34189 A80-34234 FASCHING, N. A. GALLAGHER, J. CP6 jet engine performance improvement: New fan A flight investigation of system accuracies and [NASA-CB-159699] 880-23309 operational capabilities of a general FATHALAH, K. A. aviation/air transport area navigation system Experimental investigation of the two-dimensional (B NAY) asymmetrical turbulent wake behind a blade [AD-A081646] 880-23288 A80-33282 GALLOT, J. FEDOTOV, L. N. Advanced research on helicopter blade airfoils Aircraft radio equipment adjustment and [ONERA, TN NO. 1979-120] A80-34298 maintenance technology GAONKAR, G. H. A80-32845 Review of nonstationary gust-responses of flight FETHNET, P. vehicles Airframe self-noise studies on the Lockheed 1 1011 [AIAA 80-0703] A80-35097 !triStar aircraft GATZEN, B. S. [AIAA PAPER 80-10611 A80-36000 FEWELL, I. L. Advanced turboprop potential for high speed H80-22343 Release-rate calorimetry of multilayered materials GAUGLEN, B. N. for aircraft seats Nonlinear, three-dimensicjal finite-element A80-34223 analysis of air-cooled gas turbine blades Release-rate calorimetry of multilayered materials [NASA-TP-1669] N80-22734 for aircraft seats GAULT, J. N. [AIRA 80-0759] A80-35052 FIDDLER, J. E. Validation Methods Research for Fault-Tolerant Avioni Control Systems: Working Group Active control of asymmetric vortex effects Neeti [AD-A081648] N80-23254 [NASA- 880-23008 FISHER, B. D. GEHLIR, B. Storm hazards 79: 1-1068 operations summary Noise gene. [NASA-TN-81779] by jet-engine exhaust deflection N80-23282 [ESA-TT-5... 880-23104 PIVEL, H. 3. GEISSLEN, N. Numerical flow field program for aerodynamic The harmonically oscillating body in subsonic heating analysis. volume 1: Equations and flow: Effect of compressibility results - [ESA-TT-584] 88 0-23270 [AD-A081471] 880-23255 GHAZI, N. A. Numerical flow field program for aerodynamic Experimental investigation of the two-dimensional heating analysis. Volume 2: Users manual asymmetrical turbulent wake behind a blade [AD-A081472] 880-23260 A80-33282 PLECENER, S. G. GLIEBE, P. N. Wind tunnel investigation of an all flush orifice Fan noise caused by the ingestion of anisotropic air data system for a large subsonic aircraft turbulence - A model based on axisymmetric [NASA-TP-1642] 880-23304 turbulence theory FOGEL, P. [AIAA PAPER 80-1021] A80-35977 Avco Lycoming QCGAT program design cycle, Analytical study of the effects of wind tunnel demonstrated performance and emissions tdrbulence on turbofan rotor noise N80-22332 [AIAA PAPER 80-1022] A80-35978 FORD, H. J. GOAD , Laser-optical blade tip clearance measurement system Gladstone-Dale constant for CF4 A80-36137 [NASA-TN-80228] 880-24151 FRANKLIN, N. L. GODIN, N. H. Built-up low-cost advanced titanium structures Determining sea-ice boundaries and ice roughness /BLATS/ using GEOS-3 altimeter data [AIAA 80-0745] A80-35045 [NASA-CE-156862] 880-22758 FRITZ, N. GOLDEAN, E. G. Supercritical wing design studies for tiansport Jet flap impingement noise from a full-scale STOL aircraft. Volume 2: Theoretical studies EBF engine-wing system [BNET-FB-W-79-07-VOL-2] N80-22276 A80-34594 FDAN, A. K. GOLUBEVA, I. A. An aeroelastic analysis of the Sheriff wing [85-234] Bannich base used as an antioxidant in jet fuels N80-23274 A80-35802

B-S GOODE, N. V. PERSONAL AUTHOR INDEX

GOODE, N. V. BAR , N. D. Description of anexperimental (hydrogen peroxide) A simple system for helicopter rocket system and its use in measuring aileron individual-blade-control and its application to and rudder effectiveness of a light airplane gust alleviation [NASA-TP-1647] N80-22358 [AIAA 80-0666] 180-34995 GOOD!KOONTZ, J. HARE, B. A. Noise suppression due to annulus shaping of an Honeycomb sandwich joints for primary structure inverted-velocity-profile coaxial nozzle [lilA 80-0780] 180-35070 A80-35498 BANNER, N. L. GOURISHAUAR, V. Surface pressure measurements at two tips of a Minimum sensitivity controllers with application model helicopter rotor in hover to VTOL aircraft [NASA-CE-3281] 1180-23252 A80-32759 HANKE, D. GRAHAM, B. V. In-flight handling qualities investigation of Impact of new instrumentation on advanced turbine Airbus A 310 DLc. Configurations on landing research approach using the DFVLR-HFB 320 variable A80-36155 stability aircraft N80-22319 GRAHAM, I. [DFVLR-FB-79-18] Technology requirements as derived from accident HARRIS, N. J. rate analysis Static calibration of a two-dimensional wedge [AIAA PAPER 80-0918] A80-32888 nozzle with thrust vectoring and spanwise blowing GNATIEUX, E. [NASA-TM-81161] 1180-23317 Helicopter rotor thickness noise HARRIS, 8. N. (AIAA PAPER 80-1012] A80-35970 Technology to increase airport capacity GRATZEN, L. B. [AIAA PAPER 80-0920] 180-32890 Generation of a representative load sequence for HARRIS, U. L. the fatigue testing of flacchi NB 326H spar booms Model rotor low frequency broadband noise at [AD-A074155] 1180-22309 moderate tip speeds GRAY, B. B. (AIAA PAPER 80-1013] A80-35971 Surface pressure measurements at two tips of a HARTNAIN, N.. J. model helicopter rotor in hover Fluid and structural measurements to -advance gas (NASA-CB-3281] N80-23252 turbine technology GREENE, C. C. A80-36145 NASA propeller noise research HASSELL, J. L., JR. 1180-22347 Full-scale wind tunnel-investigation of the GREENE, V. 8. Advanced Technology Light Twin-Engine airplane Minimum mass sizing of a large low-aspect ratio (ATLIT) airframe for flutter-free performance (NASA-TP-1591] 1180-22266 [NASA-TN-81818] 1180-23683 DECRY, C. GBEENWELL, N., A. Predictive guidance for interceptors with time lag REP hardening of airborne systems through in acceleration electro-optical techniques design guidelines A80-32682 [AD-A080650] 1180231146 HEINBAUGH, N. N. GREGOREK, C. H. Wind tunnel investigation of active controls Propeller aeroacoustic methodologies technology applied to a DC-10 derivative N80-223'46 [AIAA 80-0771] A80-35062 GREGORY, F. D. HELDEVBRAND, B. V. Description of an experimental (hydrogen peroxide) Aiflesearch QCGAT engine, airplane, and nacelle rocket system and its use in measuring aileron design features and rudder effectiveness of a light airplane N80-22328 [NASA-TP-1647] N80-22358 HENDERSON, R. N. GROBEAN, J. Turbopropulsion combustion technology assessment The impact of fuels on aircraft technology through [AO-A080748] 1180-23323 the year 2000 NEWNESS!, B. T. (AIAA PAPER 80-0896] A80-35898 Air combat maneuvering performance measurement The impact of fuels on aircraft technology through [AD-1077429] 1180-23336 the year 2000 HEINNANE, 0. D. [NASA-TN-8 1492] 1180-23472 Comparison of surface treatments of aluminium and GUILLIEN, G. their influence on long term strength of metal Propeller light aircraft noise at discrete bonds frequencies A80-34805 [AIAL PAPER 80-0997) A80-35960 HERTZ, T. J. GUINN, V. A. A wind tunnel demonstration of the principle of Propeller signatures and their use aeroelastic tailoring applied to forward swept [AIRA PAPER 80-1035] A80-35983 wings GUTNIKOVA, I. P. [AIAA 80-0796] 180-35078 Nannich base used as an antioxidant in jet fuels BIGASHI, K. A8 0-35 802 Study and experimental tests of fibrous acoustic treatment for reduction of fan noise from 1F3-1 turbofan engine I. [AIAA PAPER 80-09881 A80-35953 HAYTKA, B. T. BILL, P. V. Preliminary design of composite wing-box Vertical axis wind turbine development: Executive structures for global damage tolerance summary [AIAA 80-0755] A80-35049 [ORO-5135-77-5-SUNN] 1180-23845 HAIlER, A.- Vertical axis wind turbine development Airborne radar coherent transmitters [ORO-5135-77-5] 1180-23846 A80-34159 BINZ, T. HALL, D. L. Gravimetric investigation of the particle number opportunities analysis of potential advanced density distribution function in the high speed vortex systems separation standards cascade wind tunnel for laser-anemometry [AD-A081 1479] N80-23281 measurements BILLER, B. L. [DYVLB-PB-79-12] 1180-22374 F-16 flutter suppression system investigation EOPNAII, L. C.. [AIAA 80-0768] 180-35060 Practical optimal flight control system design for helicopter aircraft. Volume 1: Technical Report (NASA-CE-3275] 1180-23328

B-6

PERSONAL AUTHOR INDEX KIBZELIS, A.

1150, T. N. Analysis of cracks at attachment lugs [AIAA 80-0753] A80-35048 HULTGREN, L. S. KALASHNIKOV, ID.. N. Dynamics of a flexible rotor-tower system Aircraft radio equipment adjustment and [ASRL-TR-194-1] 1180-23862 maintenance technology HUMBAD, N. C. 180-32845 Model rotor low frequency broadband noise at KANDLEB, N. D. moderate tip speeds Software impact of selected en route ATC computer [AI.AA PAPER 80-1013] A80-35971 replacement strategies HUITSELL, L. J. [AD-A081478] 880-23286 Investigation of internal control laws for KABPEL, N. wing/store flutter suppression Design for active flutter suppression and gust (AIAA 80-0764] A80-35056 alleviation using state-space aeroelastic modeling HWANG, C. [AIAA 80-0766] A80-35058 Recent development of the YF-17 active flutter KARPOVICB, P. A.. suppression system Investigation of lubricant concepts applicable to [AIAA 80-0769] A80-35061 future Navy aircraft propulsion systems [AD-A079410] N80-22351 KAUPNA!, A. Nonlinear, three-dimensional finite-element INUKAI, G. J. analysis of . air-cooled gas turbine blades Elevated temperature structural testing of [NASA-TP-1669] 880-22734 advanced missiles KAVECKI, B. J. [AIAA 80-0812) A80-35093 Thermal response turbine shroud study ISHIHARA, K. [AD-A080620] 880-22352 Experimental investigations on the vibration of KEAR, B. H. blades due to a rotating stall Aircraft gas turbine materials and processes A80-35912 A80-34631 ISHIZARA, K. KEITEB, I. D. Study and experimental tests of fibrous acoustic Low speed propellers: Impact of advanced treatment for reduction of fan noise from XP3-1 technologies turbofan engine N80-2234 2 [AIAA PAPER 80-0988] A80-35953 KELLY, J. B. Navigation, guidance, and control for helicopter automatic landings j [NASA-TP-1649] 880-23326 .JACKSON, A. C. KELLY, N. 3.. Durability and consistency of composite components Air combat maneuvering performance measurement [AIRA 80-0811] A80-35092 [AD-A077429] N80-23336 JACOBSON, I. D. KELLY, V. C. Evaluating and minimizing noise impact due to Theory of disturbance-utilizing control with aircraft flyover application to missile intercept problems (NASA-C8-153187] 880-23874 [AD-A081110] 880-23329 JANKOWSKY, E. J. KEEP, V. B., Aircraft carrier exposure tests of aluminum alloys 'A program for transonic wall [AD-A081060] 880-231133 interference assessment in two-dimensional wind JARVIS, P. C. tunnels Improved packaging for the LN-31 inertial [NASA-TB-81819] N80-23332 measurement unit (F-15 aircraft) KENPKE, E. B., JR. [AD-A081745] 880-23293 An overview of NASA research on positive JELLY, A. H. displacement general-aviation engines Airframe self-noise studies on the Lockheed L 1011 880-22336 TriStar aircraft Positive displacement type general-aviation [AIAA PAPER 80-1061] A80-36000 engines: Summary and concluding remarks JENACKI, R. J. N80-22340 High-speed-propeller wind-tunnel aeroacoustic KEEREBBOCK, J. 1... results Preliminary measurements of aerodynamic damping of N80-22344 a transonic compressor rotor JOHNSON, E. H. A80-36152 Active flutter suppression control law definition KEBSCBEN, B. J. via least squares synthesis Pan noise caused by the ingestion of anisotropic [AIAA 80-0765] A80-35057 turbulence - A model based on axisymmetric Recent development of the YF-17 active flutter turbulence theory suppression system [AIAA PAPER 80-1021] A80-35977 [AIAA 80-0769] A80-35061 KETCHAN, S. J. JOHNSTON, J. P. Aircraft carrier exposure tests of aluminum alloys Propeller signatures and their use [AD-A081060] N80-23433 [AIAA PAPER 80-1035] A80-35983 KEYSER, G. 1.., JR. JONES, A. D. Storm hazards • 79: F-106B operations summary Operations manual: Vertical Motion Simulator (NASA-TN-81779) N80-23282 (VNS) S.08 KHALBTSKII, ID. D. [NASA-TN-81180] 880-23295 Experimental study of fan-noise silencers of JONES, C. aircraft turbojet engines Advanced rotary engine studies A80-3439 8 N80-22339 Experimental investigation of sound absorption in JOSEPSSON, L. a flow-carrying channel with a sound-absorbing A broadband, circularly polarized, phase steered lining array A80-34399 A80-34166 KBRISTICH, V. A. JUTRAS, B. N. Gasdynamic analysis of gas-turbine combustion Experimental investigation of flutter in mid-stage chambers with graduated air admission compressor designs A80-33825 [AIAA 80-0786) A80-35073 KIEZELIS, A. Problems involved in the detection of aircraft defects A80-33108

B-i KILGER. P. P. J. PERSONAL AUTHOR INDEX

KILGER, P. P. J. KREISSELMEIEE, 0. Advanced digital data processing for onboard Control system design using vector-valued missile guidance and control performance criteria with application to the A80-34179 control rate reduction in parameter insensitive KILGORE, B. A. control systems Magnetic suspension and balance system: A (ESA-TT-5 12-REV) 880-22363 selective annotated bibliography KRETZ, B. [NASA-TM-80225] 880-22368 Future of helicopter rotor control Cryogenic wind tunnels: A selected, annotated 180-33122 bibliography KRUEGER, B. [NASA-TM-80168-SUPPL) 880-23333 Development of high temperature resistant ceramic KIMEL, G. D. parts for gas turbines Survey of forced and precautionary landing costs [BMFI-P8-T-79-09] 880-23324 [A0-A080110] 880-22294 KUGENHUCS, B. KIRAL!, I. J. Development of high temperature resistant ceramic Digital system for dynamic turbine engine blade parts for gas turbines displacement measurements [BMPT-PB-7-79-09] 880-23324 A80-36151 KUNO, H. KIRSZRNDLAT, A. Midcourse guidance for fire and forget missile - Definition of a two level control system for Modification of present homing missile nonlinear aircraft motion A80-34180 [OBERA-NT-1979-7] 880-22364 RUTS, V. P. Definition of a two-level control system for Gasdynamic analysis of gas-turbine combustion nonlinear motion of an aircraft chambers with graduated air admission [ESA-TT-614] 880-23330 A80-33825 KISNER, L. S. KEONG, B. B. AiResearch QCGAT engine: Acoustic test results Plight test evaluation of airborne tire pressure N80-22330 indicating systems KNIP, G. [AD-A081598] 880-23305 Preliminary study of advanced turboprop and turboshaft engines for light aircraft [NASA-TN-81467] 880-22350 L KONATSUZAKI, T. LAAN, J. N. An analytical study of tilt proprotor aircraft On the sound field generated by a fan in a dynamics in airplane cruise configuration hard-walled baffled duct with uniform flow including the effects of fuselage longitudinal [NLR-TR-78024-U] N80-23106 rigid body motion LABOR, J. 0. N80-23297 Repair of advanced composite structures KONDEATET, V. I. [AIRA 80-0776) A80-35066 Suppression of self-oscillations in combustion LABURTHE, C. chambers by means of resonance sound absorbers Flight safety of Rogallo hang gliders. A80-34400 Theoretical and experimental study of the flight Acoustic effects on the flow and the noise envelope spectrum of supersonic jets [ONERA-NT-1979-8) 880-23301 A80-34402 LAMB, N. KOIISBCHEYA, I. A. A study of panel loads and centers of pressure of Alkyl derivatives of resorcinol used as three different cruciform aft-tail control antioxidants in jet fuels surfaces of a wingless missile from Mach 1.60 to 880-35801 3.70 KOO, P. H. [NASA-TN-81787] 880-23251 Shock loading on reinforced splice joints of ultra LANDABL, B. T. high modulus graphite/epoxy cone frustum Transonic kernel function method for unsteady flow A80-34811 calculations using a unified linear pressure KORKAB, K. U. panel procedure Propeller aeroacoustic methodologies [AD-8080227] 880-22261 880-22 346 LANSON, I. KORN, N. D. QCGAT aircraft/engine design for reduced noise and Core compressor exit stage study, 2 emissions (NASA-CE-159812] 880-23312 N80-22331 KORZ!BSKI, B. LANTER, S. K. Investigation of the stress distribution in the Simulation of high bypass ratio engine jet noise surface layer of aircraft engine components flight effects by model jet wind tunnel test A80-34235 (AIAA PAPER 80-1030] 880-35980 KOSCHIBR, A. LABCHE. B. Avco Lycoling QCGAT program design cycle, Future of helicopter rotor control demonstrated performance and emissions 880-33122 N80-22332 LAROCHE, B. KOUSSIOS, D. C. Qualification of cooling systems design for high A matrix method for airport site evaluation temperature on a turbine facility 880-33293 [ONERA, TP NO. 1980-15) A80-36156 ROYAL, L. B. LARSEN, D. C. An analytical model for study of interior noise Property screening and evaluation of ceramic control for high-speed, propeller-driven aircraft turbine engine materials (AIAA PAPER 80-1000) 880-35963 [AD-A080963] 880-23322 Analytical study of interior noise control by LARSON, T. J. fuselage design techniques on high-speed Wind tunnel investigation of an all flush orifice propeller-driven aircraft air data system for a large subsonic aircraft (AIAA PAPER 80-1001) A80-35964 [NASA-TP-1642] N80-23304 KOZLIE, J. B. LARSSON, L.-G. P100 exhaust nozzle area control Airborne PUB - Experiences from flight tests N80-23513 A80-34174 KRAMER, B. H. LAZENBY, S. D. C26-6D engine short-term performance deterioration Laser Target Marker /designator/ and Ranger [NASA-CR-159830] 880-23316 A80-34187 LE ROT, 1. Qualification of cooling systems design for high temperature on a turbine facility [ONERA, TP 80. 1980-15) A80-36156

8-8

PERSONAL AUTHOR INDEX MCCLOUD, J. L., III

LEE, R. NAGLIOZZI, B. Development of fire-resistant, low smoke Acoustic pressures on a prop-fan aircraft fuselage generating, thermally stable end items for surface commercial aircraft and spacecraft using a basic [AIAA PAPER 80-1002] A80-35965 polyimide resin MAIOROV, A. I. [NASA-CB-160576] 880-22492 Propagation of acoustic waves in a nonuniformly LEICHER, S. heated medium Supercritical wing design studies for transport A80-34388 aircraft. Volume 2: Theoretical studies MAlTA, A. [BMFT-FB-W-79-07-VOL-2] 880-22276 Acoustic characteristics of the external upper LEONARD, R. N. surface blowing propulsive-lift configuration Current and projected use of carbon composites in [LILA PAPER 80-1063] A80-36001 United States aircraft MALARME!, C. A8 0-34840 Propeller light aircraft noise at discrete LESIUK, A. frequencies Combustion-gas temperature sensors for turbine and [AIAA PAPER 80-0997] A80-35960 turbojet engines MALCOLM, U. N. A80-34237 Unsteady aerodynamics of conventional and LIU, D. D. supercritical airfoils Transonic kernel function method for unsteady flow [AIAA 80-0734] A80-35038 calculations using a unified linear pressure NANGIAROTT!, R. A. panel procedure Current problems and the future in advanced (AD-A080227] 880-22267 supersonic transport noise LIUBCHIK, G. N. [AIAA PAPER 80-1056] A80-35997 Gasdynamic analysis of gas-turbine combustion MANLEY, M. B. chambers with graduated air admission Experimental study of airfoil trailing edge noise: A80-33825 Instrumentation, methodology and initial results LOISEAU, H. [NASA-CB-163007] 880-22264 Unsteady aerodynamic forces on a subsonic MANNING, S. 0. rectilinear cascade of blades Economic life criteria for metallic airframes (P88-90007] N80-23266 [LILA 80-0748] A80-35046 Investigation into compressor aeroelastic MAQUENNEBAN, B. instabilities in a wind tunnel for a rectilinear Investigation into compressor aeroelastic cascade of blades instabilities in a wind tunnel for a rectilinear [ p 88-90011] 880-23337 cascade of blades LOKTEV, B. N. (PNB-90011] 880-23337 Construction of a nonstationary nonlinear theory MARCHAND, N. of helicopter rotors Investigation of landing flare in presence of wind A80-34711 shear LOTTATI, I. [DYVLE-FB-79-20] 880-23299 An optimization method for the determination of MARSH, A. H. the important flutter modes Noise control prediction for high-speed, [LIAR 80-0790] A80-35074 propeller-driven aircraft LU, H. V. [LILA PAPER 80-0999] A80-35962 Simulation of high bypass ratio engine jet noise Comparison of aircraft noise-contour prediction flight effects by model jet wind tunnel test programs [LIAR PAPER 80-1030] A80-35980 (LIAR PAPER 80-1057] A80-35998 LUBOESKI, J. F. MARTINON, 3.' Status of NASA full-scale engine aeroelasticity Three dimensional flow investigation with a method research of characteristics in the inlet region and the A80-35906 blade-to-blade channels of supersonic axial Status of NASA full-scale engine aeroelasticity compressors research (ONERA-NT-1979-1] N80-23325 (NASA-TM-81500] N80-23678 MARUTAMA, S. LUCAS, J. G. Theoretical investigation of the aerodynamics of Forward acoustic performance of a shock-swallowing double membrane sailwing airfoil sections high-tip-speed fan (QF-13) AS 0-33276 [NASA-TP-1668] 880-23100 MASLOVA, K. U.. LUNANSKI, J. Determining the optimal fan silencer design of Investigation of the stress distribution in the aircraft engines surface layer of aircraft engine components A80-34396 A80-34235 MATAENY, N. N. LYKOV, 0. P. Precision controllability of the !F-17 airplane Alkyl derivatives of resorcinol used as (NASA-TP-1677] 880-23327 antioxidants in jet fuels MAXWELL, R. L. A80-35801 Advanced high speed commercial aircraft - 2000 [AIAA PAPER 80-0937] A80-32898 MAYO, N. H. M Description of an experimental (hydrogen peroxide) MARE!, D. U. rocket system and its use in measuring aileron Aerodynamic characteristics of moving and rudder effectiveness of a light airplane trailing-edge controls at subsonic and transonic [NASA-TP-1647] 880-22358 speeds MAYO, N. T., JR. [RAE-TN-STBUC-947] 880-222 81 Optical advances in laser transit anemometry MACKINNON, I. J. - A80-36 139 Forward acoustic performance of a shock-swallowing MCCARTY, B. B. high-tip-speed fan (QF-13) Finite element analysis of F-16 aircraft canopy (NASA-TP-1668) 880-231 00 dynamic response to bird impact loading MACL ROD, S. (AIAA 80-08041 A80-35086 Visually Coupled System: Computer Generated NCCL000,3. L., III Imagery (VCS-CGI) engineering interface The promise of multicyclic control (AD-A080931) 880-233 06 A80-33123 NAGLIERI, D. J. Multicyclic control for helico pters - Research in Some unique characteristics of supersonic cruise progress at Ames Research Center vehicles and their effect on airport community [LILA 80-0671] 180-34997 noise Multicyclic control of a helicopter rotor (LISA PAPER 80-0859] A80-328 61 considering the influence of vibration, loads, and control motion [AIAA 80-0673] A80-34998

8-9 ECCOBEICK, B. N. PERSONAL AUTHOR INDEX

ECCOBEICK, B. N. NOLNEB E. B.. Propeller dynamic and aeroelastic effects Using vertical gust alleviation to improve the N80-22348 target tracking capability of the control ECDOWELL, B. configured TF-16 Platform motion contributions to simulator [AD-A080520] 1180-22360 training effectiveness. Study 3: Interaction NULVILLE, D. B. of motion with field-on-view Current and projected use of carbon composites in [AD-A078426] 1180-23334 United States aircraft BCFADDEN, B.. V. A80-34840 Platform motion contributions to simulator NUNDRA, A. D. training effectiveness. Study 3: Interaction General aviation altimetry errors for collision of motion with field-on-view avoidance systems [AD-A078426] 1180-23334 A8 0-354 04 !CGOVRN, J. NUBIN, A. G. The DC-8 re-engining program Noise characteristics of supersonic passenger planes A80-34218 A80-34387 ECKILLIP, N. N., JR. BUNBO, D. H. The design, testing and evaluation of the BIT Experimental verification of propeller noise individual-blade-control system as applied to prediction gust alleviation for helicopters [AIAA PAPER 80-0994] A80-35957 [NASA-CB-152352] 1180-22357 NUBAX, 0. BCLABTT, V. V. Theoretical investigation of the aerodynamics of Rotorcraft flight simulation, computer program double membrane sailving airfoil sections C81. Volume 1: Engineers manual A80-33276 [AD-A079631] 1180-22312 NUSGROVE, B. G. ECLEAN, J. U. The Ecceutuator - A new concept in actuation A new algorithm for horizontal capture trajectories (AIAA 80-0815] A80-35096 [NASA-TN-81186] 1180-22297 NUSICEAN, A. NCNABON, B. N. Composite wing/fuselage integral concept Surface pressure measurements at two tips of a (AIAA 80-0744] A80-35044 model helicopter rotor in hover BYERS, B.. K. [NASA-CR-3281] 1180-23252 Research on diamantane and other high density ECOWAT, D. N. (AD-A080749] 1180-23474 Aerodynamic characteristics of moving ETHER, S. B. trailing-edge controls at subsonic and transonic Repair of advanced composite structures speeds [AIAA 80-0776] A80-35066 [RAE-TM-STRUC-947] N8022281 NCBUER, D. Practical optimal flight control system design for helicopter aircraft. Volume 1: Technical Report NAKAJIBA, H. [NASA-CR-3275] 1180-23328 Midcourse guidance for fire and forget missile - NELLOB, A. N. Modification of present homing missile Turbopropulsion combustion technology assessment A80-34180 [AD-A080748] N80-23323 NAPIEB, J. C. BETCALFE, A. G. Application of ceramic nozzles to 10 NW engine Application of ceramic nozzles to 10 KW engine [AD-A081184] 1180-23320 [AD-A081184] 1180-23320 NATAUPSKT, N. EB?ZGER, F. B. Platform motion contributions to simulator Progress and trends in propeller/prop-fan noise training effectiveness. Study 3: Interaction technology of motion with field-on-view [AIRA PAPER 80-0856] A80-35907 [AD-A078426] 1180-23334 Acoustic test and analyses of three advanced NAUNENKO, Z. N.. turboprop models Determining the optimal fan silencer design of [NASA-CE-159667] 1180-23311 aircraft engines BICHALKB, A. A80-34396 Prediction of flyover noise from single and ERRS!, V. coannular jets Survey of forced and precautionary landing costs (AIAA PAPER 80-1031] A80-35981 (AD-A080110] N80-22294 RICHARD, P J. NENNI, J. P.. Qualification of cooling systems design for high Analysis of experiments on the effects of jet temperature on a turbine facility plumes on pressure distribution over a (ONERA, TP NO. 1980-15] A80-36156 cylindrical afterbody at transonic speeds NICHAS, B. D. [An-A081647] 1180-23259 Pitot-static system - Errors and calibrations HETZER, D. V. A80-34593 A primitive variable computer model for combustion NICHEL, 0. within solid fuel ramjets Prediction of flyover noise from single and [AD-A081081] 1180-23319 coannular jets Atmospheric dispersion of high velocity jets [AIAA PAPER 80-1031] A80-35981 [RD-A081612] 1180-23321 BIGLIORE, P. G. NEWNAN, B. L. Vertical axis wind turbine development: Executive Carburetor ice: A review summary N80-23278 [ORO-5135-77-5-SUBM] N80-23845 Carburetor ice: A review Vertical axis wind turbine development (111-79-9] 1180-23279 [080-5135-77-5] 1180-23846 Carburetor ice: A review NIKKELSON, D. C. [TB-77-19] 1180-23280 NASA propeller technology program BENSON, J. B. 1180-22341 Application of two design methods for active NILES, P. flutter suppression and wind-tunnel test results Structural design loads for future airplanes [NASA-TP-1653] 1180-22737 [AIRA 80-0813] A80-35094 BENSON, W. A., .3!. NIlSO!, J. S. Full-scale wind tunnel-investigation of the Noise transmission and control for a light, Advanced Technology Light Twin-Engine airplane twin-engine aircraft (ATLIT) [AIAA PAPER 80-1036] A80-35984 [NASA-TP-1591] N80-22266 NEWTON, A. C. The future of civil turbo-fan engines [AIAA PAPER 80-0893] A80-32876

B-lU PERSONAL AUTHOR INDEX PUKELIX, V. A.

NICOLAS, J. PARTHASARATBT, S. P. Unsteady aerodynamic forces on a subsonic Transmission of high frequency sound waves through rectilinear cascade of blades a slug flow let [PNR-90007] 880-23266 (LIAR PAPER 80-0969] A80-35944 NIESSEN, P. B. PASHA, B. A. Pilot assessment of two computer-generated display formats for helicopter instrument approach Analysis of the effects of higher order control (NASA-TM-80151] systems on aircraft approach and landing 880-22321 longitudinal handling qualities Navigation, guidance, and control for helicopter [AD-A080519] automatic landings 880-22362 PATTON, J. B., JR. [NASA-TP-1649] 880-23326 NISSIB, E. Pilot assessment of two computer-generated display formats for helicopter instrument approach An optimization method for the determination of [NASA-TM-80151] 880-22321 the important flutter modes PELOUBET, R. P., JR. [AIAA 80-0790] A80-35074 ROLL, T. E. F-16 flutter suppression system investigation [AIAA 80-0768] A80-35060 Investigation of internal control laws for PERKINS, P. B. wing/store flutter suppression Easy-ACS dynamic analysis. User's manual [AIAA 80-076(4] A80-35056 [AD-A081160] 880-23258 NORGREN, N. B. PESCHEL, V. H. AiResearch QC43AT engine performance and emissions tests Development of high temperature resistant ceramic parts for gas turbines 880-22329 [BRFT-FB-T-79-09) 880-23324 PETERSON, J. B. 0 Large-scale and small-scale flammability tests for OBRIEN, E. L. airplane cabin materials A80-347R7 Unsteady aerodynamic measurement techniques for P1, N. S. turbomachinery research Recent development of the YF-17 active flutter A80-36142 suppression system OBRIEN, N. P., JR. [LIAR 80-0769] A80-35 061 Unsteady pressure measurements and data analysis PICKUP, N. techniques in axial-flow compressors Current problems and the future in advanced A80-36143 OBRTAN, T. C. supersonic transport noise [LIAR PAPER 80-1056] A80-35 997 Description of an experimental (hydrogen peroxide) PIERCE, E. F. rocket system and its use in measuring aileron Investigation of lubricant concepts applicable to and rudder effectiveness of a light airplane future Navy aircraft propulsion systems [NASA-TF-1647] 880-22358 [AD-A079410] 880-22 351 OCONNELL, R. F. PITTS, F. L. Design, development and implementation of an Storm hazards '79: F-1065 operations summary active control system for load alleviation for a NASA-TR-81779] commercial transport airplane 880-23 282 PLENCNER, R. B. [AGARD-AR-683] 880-23331 OKEEPE, J. V. Preliminary study of advanced turboprop and Current problems and the future in advanced turboshaft engines for light aircraft (NASA-T8-81467] 880-22 350 supersonic transport noise POLLACK, P. G.. [AIAA PAPER 80-1056] A80-35997 OLSSON, B. Temperature and pressure measurement techniques for an advanced turbine test facility Experiences of a 50 BBPS video recording and A80-36 157 processing system for FLII4 images PORAZIO, A. J. A80-34163 OTTO, 0. R. Investigation of lubricant concepts applicable to future Navy aircraft propulsion systems Elevated temperature structural testing of (AD-A079410] 880-22351 advanced missiles POWELL, J. A. [AIAA 80-0812] A80-35093 Laser anemometer measurements in a transonic axial flow compressor rotor A80-36141 P POWERS, R. V. PALS, J. B. Practical design considerations for a flightworthy CF6-6D engine short-term performance deterioration higher harmonic control system (NASA-CB-159830] 880-23316 [LIAR 80-0668] A80-35100 PADULA, S. L. PRINTREPS, A. Prediction of noise constrained optimum takeoff procedures The automatization of the detection of collision risks for French air traffic control [AIAA PAPER 80-1055] A80-35996 PAl, T. G. A80-34226 PROKSCH, B. J. Note on the yawing moment due to side slip for swept-back wings Supercritical wing design studies for transport aircraft. Volume 1: Wing design and wind A80-33280 PABADI, B. N. tunnel measurements BNFT-PB-W-79-06-VOL-1] 880-22275 Note on the yawing moment due to side slip for PROKUDIR, V. N. swept-back wings Alkyl derivatives of resorcinol used as A80- 332 80 PANOV, V. P. antioxidants in jet fuels Propagation of acoustic waves in a nonuniformly A80-35801 heated medium Mannich base used as an antioxidant in jet fuels A80-35802 A80-34388 PUCHER, B. PARKER, J. A. Release-rate calorimetry of multilayered materials Fatigue at high temperatures: Examination of the for aircraft seats behavior of gasturbine casting materials also in simultaneous temperature and strain cycles A80-34223 [BBFT-FB-T-79-26] 880-23444 Release-rate calorimetry of multilayered materials PUKBLII, for aircraft seats V. A. A study of the stress-strain state of shaped [LILA 80-0759) A80-35052 PARRISH, B. V. hollow blades for radial superchargers Preliminary investigation of motion requirements A80-34351 for the simulation of helicopter hover tasks [NLSA-T11-81801] 880-22304

B-il PURSNL, L PERSONAL AUTHOR INDEX

PURSEL, N. RIESKII-KOESAKOT, A. V. A flight investigation of system accuracies and Aeroacoustics operational capabilities of a general A80-34366 aviation/air transport area navigation system. NODAL, J. J. A. (RNAV) Two-dimensional finite-element analyses of [AD-A081646) N80-23288 simulated rotor-fragment impacts against rings and beams compared with experiments [NASA-CH-159645] 1180-22323 R ROIDER, K. A- RABINOVICH, N. L. A microprocessor controlled system for determining A pulsed radiography technique for studying the the height of clouds internal structure of fuel injection jets A80-34188 A80-34588 ROMEO, G. RAGRUPRASAD, N. N. Technology of graphite-resin composite materials Processing and analysis of the data from a two and their application in the aeronautical industry spool gas turbine engine A80-35771 A80-36149 BOOS, B. RAJ, P. Unsteady airloads on a harmonically pitching wing Analysis of NASA .32-4 fire tests data and with external store development of a simple fire model [BIkE 80-0733] A80-35037 [NASA-CB-159209] N80-22432 ROTH, H. BASHED, N. I. Vibration measurements on turbomachine rotor Experimental investigation of the two-dimensional blades with optical probes asymmetrical turbulent wake behind a blade A80-36146 A80-33282 BUCKLE, D. L. READER, K. B. Development of improved-durability plasma sprayed The effect of shaft angle on performance of -a ceramic coatings for gas turbine engines circulation control high-speed rotor at an [NASA-TN-81512] 1180-23313 advance ratio of 0.7 RUDDICK, N. L. (AD-A080953) N80-22314 Investigation of a foam supported glass fiber BECK, G. N. D-box for a rigid wing hang glider The impact of fuels on aircraft technology through [BU-240] 1180-23302 the year 2000 RUNYAN, H., 1. [AIAA PAPER 80-0896.] A80-35898 Noise from a vibrating propeller The impact of fuels on aircraft technology through [AIAA PAPER 80-10111 A80-35969 the year 2000 Effect of a flexibly mounted store on the flutter [NASA-TN-81492] N80-23472 speed of a wing REDEKER, G. (NASA-CH-159245] 1180-22356 Transonic wing DPVLR-P4 as European test model EZNNEA, K. (NASA-TN-75752] N80-22260 Fuel consumption per units of transport work in REED, N. A., III airliner operation Decoupler pylon: Wing/store flutter suppressor A80-34236 [NASA-CASE-LAR-12468-1] N80-22359 REED, N. B., III Wing/store flutter with nonlinear pylon stiffness [AIAA 80-0792] A80-35075 SACHS, G. REINERT, H. Possibilities for achieving trimmed minimum drag Composite wing/fuselage integral concept without sacrificing inherent stability [AIAA 80-0744] A80-35044 A80-34 655 RENNISON, D. C. SADLER, S. G. Prediction of the interior noise levels of Botorcraft flight simulation, computer program high-speed propeller-driven aircraft C81. Volume 1: Engineer's manual [AIAA PAPER 80-0998] A80-35961 [AD-A079631] 1180-22312 Noise control prediction for high-speed, SALLEN, G. P. propeller-driven aircraft Performance deterioration based on existing [AIAA PAPER 80-0999] A80-35962 (historical) data; .JT9D jet engine diagnostics RENSHAN, T. program Developments in ultrasonic welding for aircraft [NASA-CR-135448] 1180-22324 A80-34797 SANANICH, I. E. RETELL, J. D. QCSEE fan exhaust bulk absorber treatment evaluation An analytical model for study of interior noise [EllA PAPER 80-0987] A80-35952 control for high-speed, propeller-driven aircraft OSCEE fan exhaust bulk absorber treatment evaluation [AIAA PAPER 80-1000] A80-35963 [NASA-TN-81498] 1180-23314 Analytical study of interior noise control by SARRAITONXO, I. fuselage design techniques on high-speed Developments in ultrasonic welding for aircraft propeller-driven aircraft A80-34797 [AIAA PAPER 80-1001] A80-35964 SASAKI, B. RHEA, J. Study and experimental tests of fibrous acoustic Flight simulation techniques - The quest for realism treatment for reduction of fan noise from XF3-1 A80-33135 turbofan engine RICHARDSON, G. A. [AIAA PAPER 80-0988] A80-35953 Evaluation of an improved parachute test data SAWTELLE, E. E acquisition system Measurement of (AD-A080240] N80-22268 interference-to-navigation/communication RICHARDSON, P. L. avionics from cable television (CATV) systems Air deployment of satellite-tracked drifters [AD-A081430) 1180-23530 A80-36291 SCHEICHL, L. RICHARZ, N. G. Emergency landings on a carpet of foam A theoretical study of the coherence of jet noise A80-33292 [AIAA PAPER 80-1005] A80-35967 SCHMIDT, N. RIEDEL, S. A. Transonic wing DFVLR-P4 as European test model Practical optimal flight control system design for [NASA-TN-75752] 1180-22260 helicopter aircraft, volume 1: Technical Report SCHNIDT, N. [NASA-CE-3275] N80-23328 Supercritical wing design studies for transport RIEGL, J. aircraft. Volume 2: Theoretical studies A microprocessor controlled system for determining [BMPT-PB-9-79-01-VOL-2] N80-22276 the height of clouds SCHNEIDER, A. A80-34188 Research on diamantane and other high density (AD-A080749] 1180-23474

B-12 PERSONAL AUTHOR INDEX SPIRE, K. B.

SCHNEIDER, G. B. SIEMERS, P. H.., III Calculation of the turbulent boundary layer on an Wind tunnel investigation of an all flush orifice infinite swept wing using a three-dimensional air data system for a large subsonic aircraft mixing length model (NASA-TP-1642) 1480-23304 (ESA-TT-534) 1480-22273 SIENKIEWICZ, J. SCHNEIDER, K. New mathematical formula for the cropduster Economical processing of fiber-reinforced operational cycle components with thermal expansion molding 180-314234 [NASA-TM-75738] 1480-22812 SISK, T. B. SCHOOL, B. Precision controllability of the YP-17 airplane A laser-two-focus /L2F/ velocimeter for automatic [NASA-TP-1677) 1480-23327 flow vector measurements in the rotating SIX, I. D. components of turbomachines Concept definition study of small Brayton cycle 180-36138 engines for dispersed solar electric power systems SCHROEDER, N. [NASA-CE-159592] 1480-22778 Calculation of the interference effects between SKUDRIDAKIS, J. the engine wing and the base wing of a civil and Investigations into an active vibration isolation military transport aircraft by the vortex system for helicopters with rigid and elastic lattice method airframe modeling (ESA-TT-493) 1480-22272 [ESA-TT-531] 1480-22315 SCHULTE, B. H. SLAZAK, H. Lightning damage mechanisms and simulation Noise transmission and attenuation by stiffened techniques panels A80-34664 (LIlA PAPER 80-1034) 180-35982 SCHULTEN, J. B. H. H. SMART, A. E. On the sound field generated by a fan in a Optical advances in laser transit anemometry hard-walled baffled duct with uniform flow A80-36139 NLH-TR-78024-4j] 1480-23106 SMITH, G. I. SCHULZ, C. Engine environmental effects on composite Investigations of the design of active vibration behavior [lilA 80-0695] 180-35101 isolation systems for helicopters with rigid and Engine environmental effects on composite elastic modeling of the fuselage behavior [NASA-TM-8 1508] 1480-23370 [ESA-TT-556] 1480-23300 SMITH, H. N. SEREGIN, E. P. The outside has to be bigger than the inside Alkyl derivatives of resorcinol used as (lILA 80-0726) 180-35031 antioxidants in jet fuels SMITH, J. B. B. 180-35801 A comment on the origin of eudwall interference in Hannich base used as an antioxidant in jet fuels wind tunnel tests of aerofoils A80-35802 [RAE-TH-AERO-1816] N80-22280 SEXTON, N. R. SMITH, J. 3. Unsteady pressure measurements and data analysis CP6-60 engine short-term performance deterioration techniques in axial-flow compressors [NASA-cR-159830] 1480-23316 A80-36143 SMITH, V. D. SHAM, J. Economic life criteria for metallic airframes Active control of rotor blade pitch for vibration [lIlA 80-0748] 180-35046 reduction - A wind tunnel demonstration SMYTH, C. C. A80-33121 The verification of a computer model of internal SHENOT, K. B. light reflections for helicopter canopy design Surface pressure measurements at two tips of a (10-1080473) 1480-23142 model helicopter rotor in hover SOBIESZCZANSKI-SOBIESKI, J. [NASA-CR-3281] 1480-23252 Minimum mass sizing of a large low-aspect ratio SHEBBEE, V. C. airframe for flutter-free performance A wind tunnel demonstration of the principle of [NASA-TH-81818] 1480-23683 aeroelastic tailoring applied to forward swept SOLOVEVA, H.. N. wings Experimental study of fan-noise silencers of [lilA 80-0796] 180-35078 aircraft turbojet engines SHIPOV, B. A. A80-34398 Noise characteristics of supersonic passenger planes SORATHIA, U. A. K. 180-3(4387 Development of fire-resistant, low smoke Propagation of acoustic waves in a nonuniforaly generating, thermally stable end items for heated medium Commercial aircraft and spacecraft using a basic 180-314388 polyimide resin Experimental investigation of sound absorption in [NASA-CE-160576] 1480-221492 a flow-carrying channel with a sound-absorbing SORKIM, L. I. lining Acoustic characteristics of jets issuing from 180-34399 ring-and-needle nozzles SHIRK, H. H. A80-34404 A wind tunnel demonstration of the principle of S000AK, U. aeroelastic tailoring applied to forward swept Honeycomb sandwich joints for primary structure wings (lIlA 80-0780] 180-35070 [AIAA 80-0796] 180-35078 SPRITE, H. SHIRLEY, N. A. Release-rate calorimetry of multilayered materials Wind tunnel investigation of active controls for aircraft seats technology applied to a DC-10 derivative A80-34223 (AIAA 80-0771] 180-35062 SPEKTOB, B. L. SHORE, D. Propagation of acoustic waves in a nonuniforaly Survivable C3 heated medium 180-344 156 A80-34388 SHOVLIN, H. D. SPEZIA, B. Upper surface blowing noise of the NASA-Ames quiet Survey of forced and precautionary landing costs short-haul research aircraft [AD-A0801 10] 1480-22294 [lIlA PAPER 80-1064] 180-36002 SPIER, B. B. SIEBIANNS, N. On experimental versus theoretical incipient Development of high temperature resistant ceramic buckling of narrow graphite/epoxy plates in parts for gas turbines compression (BMPT-?B-T-79-09) 1480-23324 [lILA 80-0686] SIEGELMAN, D. 180-35007 Projectile/sabot discard aerodynamics [AD-A080538] 1480-22269

8-13 SPIETH, U. PERSONAL AUTHOR INDEX

SPIBTE, B. SUITER, B. 1.. - Release-rate calorimetry of multilayered materials Flight test evaluation of airborne tire pressure for aircraft seats indicating systems [AIAA 80-0759] A80-35052 (AD-1081598] 1180-23305 STAGLIABO, T. B. SUMNER, I. E. Two-dimensional finite-element analyses of Development of improved-durability plasma sprayed simulated rotor-fragment impacts against rings ceramic coatings for gas turbine engines and beams compared with experiments [NASA-TM-81512] 1180-23313 [NASA-CB-159645] 1180-22323 SUSHKOY, A. L. STABlES, J. II.. JR.. Suppression of self-oscillations in combustion Preliminary design of composite wing-box chambers by means of resonance sound absorbers structures for global damage tolerance A80-34400 [AIAA 80-0755] A80-35049 Model studies of acoustic resonators STAUPENBIBL, B. A8 0-34 403 Study on the dynamics of small flight vehicles SNEETMAN, B. A80-31&653 Big-fan engines - A new US generation STEIN, T. A.. A80-3l4216 Damage tolerant design and test considerations in SZCZEPANIK, B. the engine structural integrity program Influence of external conditions on the generation [ALAA 80-07814] A80-35072 and intensity of vortices at air-intakes STEENPELD, B., JR. A80-34238 Advanced rotorcraft noise SZECBEIYI, E. [AIAA PAPER 80-0857] A80-32860 Investigation into compressor aeroelastic STEVENS, B. C. K. instabilities in a wind tunnel for a rectilinear Static tests at model scale indicating cascade of blades rear-fuselage installation effects on engine [PNR-9001 1] 1180-23337 exhaust noise SZODBUCH, J. [AIAA PAPER 80-10146] A80-35991 Types of leeside flow over delta wings STEVENSON, C. A. 0-34 652 A primitive variable computer model for combustion SZODBUCH, J. G. within solid fuel ramjets Leeward flow over delta wings at supersonic speeds [AD-A081081] 1180-23319 [NASA-TN-81187] 1480-23250 STEWABT, D. G. Lee side flow for slender delta wings of finite 1FF for air defence aircraft thickness A80-34157 (NASA-TM-75753] 4480-23253 STOCK, B. N. Supercritical wing design studies for transport aircraft. Volume 2: Theoretical studies II [BNFT-PB-W-79-07-V0L-2] 1180-22276 TANNER, B.. STONE, B. B. Lift, drag and pitching moment measurements on a Flight service evaluation of Kevlar-49 epoxy missile body having various boattails at composite panels in wide-bodied commercial subsonic and transonic velocities transport aircraft (OPVLR-PB-79-15] 4480-23265 [NASA-CE-159231] 1180-23371 Pressure distribution measurements on wedges at STOWELL, B. B. subsonic and transonic velocities The verification of a computer model of internal (ESA-TT-5514] 1180-23267 light reflections for helicopter canopy design Afterbody drag and base pressure measurements on a [AD-A080473] 880-231142 body of revolution at angles of incidence up to STRACK, N. C. alpha = 25 deg at subsonic and transonic Bach New opportunities for future, small, numbers General-Aviation Turbine Engines (GATE) [ ESA-TT-569] 1180-23268 1180-22335 TABASOV, V. G., STRAZISAR, A. .3.. Navigation for a group of aircraft /Automation of Laser anemometer measurements in a transonic axial data processing and flight control procedures/ flow compressor rotor A80-33177 A80-36141 TAYLOR, J. STUCKAS, K. J. Mathematical model for the separation of gust and The spark-ignition aircraft piston engine of the manoeuvre loads of civil aircraft future [FB-141 (1979)] 1180-23674 1180-22337 TEAGLE, P. B. STUKOBIS, B. Airworthiness certification of composite Selective methods of determining the range of components for civil aircraft - The role of engine operation in aircraft crash non-destructive evaluation investigations. I A80-34766 A80-33106 TELLER, J. B.. Selected methods for defining engine operating Air Defense Ground environment - A case for ranges in the investigation of aircraft automation accidents. II A80-34 154 A80-35184 TEE-BINASIANTS, S. B. SUCCI, G. P. Stationary flow past the lower surface of a Experimental verification of propeller noise piecewise planar delta wing with supersonic prediction leading edges [AIAA PAPER 80-0994] A80-35957 A80-3'4708 SUGG, B. N. TERRILL, K.. B... Trials to compare the stopping performance of QCGAT aircraft/engine design for reduced noise and three anti-skid systems and to demonstrate emissions methods of determining aircraft stop distances N80-22331 on the standard military reference wet surface THIBERT, J.-J. [S/T-NEM0-3/79] 1180-22318 Advanced research on helicopter blade airfoils A means of specifying a standard reference wet (eNEmA, TP NO. 1979-120] A80-34298 surface for military aircraft THOMAS, G. T. [S/T-NENO-1/79] 1180-22371 NAVAIRDEYCEN dynamic flight simulator design and An investigation into measuring runway surface multipurpose crew station concept design and texture by the grease patch and outflow meter development plan methods (AD-A081982] 1180-23335 [S/T-MEMO-2/79] 1180-22372 THOMAS, B. B. Storm hazards 1 79: F-106B operations summary (NASA-TM-81779] 1180-23282

B-14 PERSONAL AUTHOR INDEX WAlTZ, C. B.

THOMAS, P. URBAN, L. J. Impact of flight effects on multitube suppressor The impact of global positioning system on design guidance and controls systems design of military (8188 PAPER 80-1029) 880-35979 aircraft. Volume 28: Specific application THOMPSON, N. B. study no. 1, close air support Aircraft gas turbine materials and processes (AGARD-AR-147-VQL-28] N80-23303 A80-3l4631 THORNTON, E. A. Integrated thermal-structural finite element OTA analysis VAICAITIS, L. (AIAA 80-0717] 880-35098 Noise transmission and attenuation by stiffened TIMOSHENKO, B. P. panels A pulsed radiography technique for studying the [AIAA PAPER 80-1034] 880-35982 internal structure of fuel injection jets VAWDEBELST, N. J. A80-34588 The aerodynamics of axial flow wind power turbines TOLSTOSHEEV, M. N. [CSIR-ME-1619] 1180-23781 Acoustic characteristics of jets issuing from VANGAASBBEN, 3. ring-and-needle nozzles ;l!;flightht simulation, computer program 880-314404 C81. Volume 1: Engineers manual TORBY, A. [80-8079631] N80-22312 Frequency independent sidelobe suppression and Rotorcraft flight simulation, computer program lobesharpening using broad beam antennas C81. Volume 2: Users manual A80-34178 (AD-A079632) 1180-22313 TORISAKI, T. VASIN. V. A. Acoustic characteristics of the external upper Construction of a nonstationary nonlinear theory surface blowing propulsive-lift configuration of helicopter rotors [AIAA PAPER 80-1063) 880-36001 880-34711 TRABOLD, N. VAUGHAN, 3. C., III Release-rate calorimetry of nultilayered materials Technology requirements and readiness for very for aircraft seats large aircraft A80-34223 (AIAA PAPER 80-0935] 880-32897 Release-rate calorimetry of multilayered materials VENKATANAJO, K. for aircraft seats Processing and analysis of the data from a two [AIAA 80-0759) 880-35052 spool gas turbine engine TRESCOT, C. 0., JR. 88 0-36 149 A study of panel loads and centers of pressure of VNNONSKT, G. N. three different cruciform aft-tail control Development of a structural overload warning surfaces of a wingless missile from Bach 1.60 to system for modern high performance aircraft 3.70 A80-34974 (NASA-TM-81787] N80-23251 VEERA, N. K. TRINPI, B. L. Processing and analysis of the data from a two Modern fluid dynamics of supersonic and hypersonic spool gas turbine engine flight 880-36149 (8188 PAPER 80-0862) 880-33275 VESELIANSKAIA, V. B. TRIPLETT, V. N. Mannich base used as an antioxidant in jet fuels Aeroelastic tailoring of a forward swept wing and 880-35802 comparisons with three equivalent aft swept wings VICARS-HABNIS, B. (AIAA 80-0794) A80-35076 A solid state /CCD/ cockpit television system TRIVEDI, K. S. 880-34190 Validation Methods Research for Fault-Tolerant VIJA!ABAGEAVAN, A. Avionics and Control Systems: Working Group Transmission of high frequency sound waves through Meeting, 2 a slug flow jet [NASA-CP-2130) N80-23008 [AmA PAPER 80-0969] A80-35944 TROESCH, A. VISHNIAKOVA, T. P. Predictive guidance for interceptors with time lag Alkyl derivatives of resorcinol used as in acceleration antioxidants in jet fuels A80-32682 A80-35801 TUNAN, N. V. Mannich base used as an antioxidant in jet fuels Alkyl derivatives of resorcinol used as A80-35802 antioxidants in jet fuels VON GLARE, U. 880- 35 80 1 Noise suppression due to annulus shaping of an TURNER, N. A. inverted-velocity-profile coaxial nozzle Model tests demonstrating under-wing installation A80-35498 effects on engine exhaust noise VOROBEV, N. F,. [8188 PAPER 80-1048] 880-35992 Direct and inverse problems of flow over a wing of TUSTIN, B. A. finite span in the linear formulation Large-scale and small-scale flammability tests for A80-34712 airplane cabin materials VEEULA, D. A80-34787 Air combat maneuvering performance measurement TUTTLE, N. H. (80-8077429] 1180-23336 Magnetic suspension and balance system: A selective annotated bibliography. (NASA-TM-80225] N80-22368 W Cryogenic wind tunnels: A selected, annotated HAG, N. L. bibliography Platform motion Contributions to simulator (NASA-TM-80168-SOPPL) N80-23333 training effectiveness. Study 3: Interaction of notion with field-on-view [AD-A078426] 1180723334 U WAlKI T. UENO, T. Improved maneuver criteria evaluation program Midcourse guidance for fire and forget missile - [AD-A0801408] 1180-22310 Modification of present homing missile WAHI, N. K. 880-34180 Easy-ACIS dynamic analysis. Users manual ULVILA, J. 1. (ID-A081160) 1180-23258 Decision analysis of Advanced Scout Helicopter WAlTZ, C. N.. candidates Built-up low-cost advanced titanium structures [AD-A081483] N80-23298 /BLATS/ [AIAA 80-0745] 180-35045

B-15

WALDEN, S. PERSONAL AUTHOR INDEX

WALDEN, S. WILD!, J. F. Flight safety of Rogallo hang gliders. Prediction of the interior noise levels of Theoretical and experimental study of the flight high-speed propeller-driven aircraft envelope [lIlA PAPER 80-0998] 180-35961 [ONERA-NT-1979-8] 1180-23301 Noise control prediction for high-speed, WALSH, K. H. . propeller-driven aircraft Wind tunnel tests on the Sheriff twin-engined [AIAA PAPER 80-0999] A80-35962 light aircraft WILCOISON, L. L. (BU-241] 1180-23277 Development of fire-resistant, low smoke WALTERS, B. E. generating, thermally stable end items for Vertical axis wind turbine development: Executive commercial aircraft and spacecraft using a basic summary polyimide resin (080-5135-77-5-50MM) 1180-23845 [NASA-CE-160576] 1180-221192 Vertical axis wind turbine development WILHELM, K. (080-5135-77-5] N80-23846 Investigation of landing flare in presence of wind WALTHAM, B. D. shear Design considerations for an active laser seeker (DPVLR-FB-79-20] 1180-23299 A80-34189 WILLEKENS. A. J. L. WANHIU, B. J. H. Comparison of the minilir location system and the Fatigue crack propagation in aluminum alloy sheet NLR inertia measuring system STALINS materials under maneuver spectrum and constant [NLR-MP-78026-U] 1180-22303 amplitude loading WILLIAMS, N. J. [NLB-MP-78025-U] 1180-227119 Statistical review of counting accelerometer data Gust severity effects on fatigue crack propagation for Navy and Marine fleet aircraft in aluminum alloy sheet materials [AD-1080580] 1180-22308 (NLB-MP-78041-U] 1180-23449 WILSON, C. A. WATKINS, S. Avco Lycoming quiet clean general aviation Wind tunnel tests on the Sheriff twin-engined turbofan engine light aircraft [BU-241] 1180-23277 WINTER, K. G. WA!, D. J. A comment on the origin of emdwall interference in Model tests demonstrating under-wing installation wind tunnel tests of aerofoils effects on engine exhaust noise [RAE-TN-AEEO-1816] N80-22280 [AIAA PAPER 80-1048] 180-35992 VINTHEB, B. A. WEBER, B. J. Wind tunnel investigation of active controls Aeropropulsion in year 2000 technology applied to a DC-10 derivative [1111 PAPER 80-0914] A80-32887 [AIAA 80-0771] 180-35062 WEETON, D. WISLEB, D. C.. Software impact of selected en route ATC computer Optical advances in laser transit anemometry replacement strategies A80-36139 [AD-A081478] 1180-23286 WITHER, E. A. WEHBNAN, 11. D. Two-dimensional finite-element analyses of CAD produced aircraft drawings simulated rotor-fragment impacts against rings (AIAA 80-07321 180-35036 and beams compared with experiments WEISSHAAB, T. A. (NASA-CB-159645] 1180-22323 Aeroelastic tailoring of forward swept composite WIT!, A. wings Fatigue at high temperatures: Examination of the [AIAA 80-0795] A80-35077 behavior of gasturbine casting materials also in WELSH, B. L. simultaneous temperature and strain cycles Aerodynamic characteristics of moving [BMFT-FB-T-79-26] N80-234414 trailing-edge controls at subsonic and transonic WOOD, B. B. speeds Practical design considerations for a flightworthy [RAE-TM-STRUC-947] 1180-22281 higher harmonic control system WERNER, C. [lilA 80-0668] 180-35100 iBemote sensing methods for determination of slant WOOD, T range visibility Improved maneuver criteria evaluation program [DFVLR-FB-79-14] N80-23759 [AD-A080408] 1180-22310 WETEB, D. C.. WOODWARD, B. P. Platform motion contributions to simulator Forward acoustic performance of a shock-swallowing training effectiveness. Study 3: Interaction high-tip-speed fan (QF-13) of motion with field-on-view [NASA-TP-1668] 1180-23100 [AD-A078426] 1180-23334 WOOLDBIDGE, L. WHITE, N. L. Air combat maneuvering performance measurement A hybrid composite helicopter main rotor blade [AD-10771429] 1180-23336 employing pneumatic lift control WORTH!, J. G. B. A80-34808 The design, development and operation of gas VICKERS, B. R. turbine radio telemetry systems Wake vortex trajectories of low flying spray A80-36154 aircraft WOLF, B. H. A80-3'4595 CF6-6D engine short-term performance deterioration Reduction of aerodynamic drag of external spray [NASA-CR-159830] 1180-23316 booms and nozzles used on DC-6 aircraft A80-34596 WIETING, A. L Integrated thermal-structural finite element TANG, 1. C. analysis High voltage spark carbon fiber detection system [AIAA 80-0717] A80-35098 (NASA-CE-162995] 1180-22367 WIGGENRAAD, J. P. ft. TEN, J. G. The influence of bending-torsional coupling on the Vibration reduction with higher harmonic blade buckling load of general orthotropic, midplane feathering for helicopters with two-bladed symmetric and elastic plates teetering and four-bladed hingeless rotors (NLS-TR-77126-D] 1180-22753 (lilA 80-0670] 180-311996 WILE!, E. G. TIP, L. P. Prediction of the interior noise levels of Full-scale wind tunnel-investigation of the high-speed propeller-driven aircraft Advanced Technology Light Twin-Engine airplane [AIAA PAPER 80-0998] A80-35961 (ATLIT) Noise control prediction for high-speed, [NASA-TP-1591] 1180-22266 propeller-driven aircraft (AIAA PAPER 80-0999] 180-35962

8-16 PERSOAL AUTHOR INDEX ZVAAN, E. J.

Z ZACKOVSKI, G. V. Minimum sensitivity controllers with application to VTOL aircraft A80-32759 ZABTARIAN, G. The VIBRA-8 subsonic aerodynamic nuclear gust vulnerability code [AD-A081722] N80-23256 ZHVALOV, V. P. Acoustic characteristics of jets issuing from ring-and-needle nozzles A80-314404 ZINHEE, J.. A. Experimental verification of propeller noise prediction [AIAA PAPER 80-0994] A80-35957 ZRUDZINSRI, 2. Effects of electric fluctuations in electric power systems of flight vehicles A80-35185 ZWAAN, N.. J. Summary of data required for the AGARD SEP activity standard aeroelastic configurations - two-dimensional configurations (NLR-NP-79015-U] N80-23273

B-17

CONTRACT NUMBER INDEX AERONAUTICAL ENGINEERING 1A Continuing Bibliography (Suppl. 125) AUGUST 1980

Typical Contract Number Index Listing

P652-9344 P80-11097 NAS1-15158 P80-23252 534-03-23-01 580-22432 PAS1-15327-02 534-04-13-57 P80-23326 I A80-35062 534-13-57 P80-22321 I CONTRACT I 'NASA ACCESSION' PAS1-15380 P80-22432 791-40-19 880-22305 NUMBER NUMBER NAS1-15426 A80-35961 989-10-00 P80-233014 A80-35962 PAS2-8703 P80-22305 NAS2-9946 P80-23328 Listings in this index are arranged alphanumerically by contract number. NAS2-10002 A80-35977 Under each contract number, the accession numbers denoting documents A80-35978 that have been produced as a result of research done under that contract N6S320578 P80-23312 are arranged in ascending order with the /AA accession numbers appearing PAS3-20614 A8035958 first. The accession number denotes the number by which the citation is A80-35965 identified in either the /AA or STARsecticw P80-23311 NAS3-20619 A80-35968 PAS3-20629 P80-23309 PAS3-20631 P80-23316 NAS3-20632 P80-22324 PAS3-20830 P80-22326 'AP PROJ. 1123 ET-76-C-05-5135 PAS3-21272 880-22337 P80-23334 P80-23845 PAS7-100 A80-35944 P80-23336 P80-23846 P80-22367 AF PROJ. 2307 FAA PROJ. 213-662-810 P80-22430 580-23257 580-23530 NAS9-15484 P80-22492 AF PROJ. 2402 FAA PROJ. 975-310-001 PGL-05-020-243 P80-23258 P80-23288 A80-35058 AP PROJ. 2404 FPV-F-K-82223-76-001-21-001 PGR-22-009-339 P80-23255 580-22282 P80-22323 P80-23260 FNV-F-K-82223-77-001-21-001 NIVR-1773 P80-23106 AF PROJ. 3048 P80-22282 PIVR-1808 580-22753 P80-23474 FRV-F-K-82223-77-116-21-001 PIVR-1821 P80-23106 AF PROJ. 3066 P80-22282 PR PROJECT 083-004 P80-22352 FWV-F-K-82223-78-003-2 1-001 A80-36291 P80-23323 P80-22282 NBC A-3322 A80-32759 AF PROJ. 3763 F4701-77-C-0078 NSF OIP-74-21450 P80-23536 A80-32682 A80-33282 AF PROJ. 7184 F29601-78-C-0013 NSG-1308 P80-22348 P80-23306 P80-23536 PSG-1377 P80-22264 AF-AFOSR-77-3233 F33165-77-C-3003 PSG- 1438 P80-22356 A80-35037 P80-23255 PSG-1450 A80-35982 AF-AFOSR-77-3423D F33615-75-C-519616 PSG-1509 P80-23874 A80-35077 P80-23322 PSG-1583 A80-35971 BRPT-PTS-19 P80-23324 F33615-76-C-3017 PSG-2266 P80-22357 DA PROJ. 1P2-63208-DB-52 A80-35066 PSG-3079 A80-36152 P80-22311 F33615-77-C-0079 PSG-3247 P80-22346 DA PROJ. 1F2-63211-D-157 P80-23336 PSG-3304 580-22348 P80-22310 F33615-77-C-0524 B00014-74-C-0262 DA PROJ. 1L1-61102-AH-45A P80-23306 A80-36291 P80-23252 F33615-77-C-3003 P60921-78-C-0073 DA PROJ. 1L2-62209-AH-76 P80-23260 P80-23254 P80-22257 P33615-77-C-3054 PROJECT SQUID P80-22312 P80-23258 A80-36143 P80-22313 F33615-77-C-3081 SWEDBRSD-5061. 012 DAAG29-77-C- 0008 A80-35060 P80-23862 P80-23259 P33615-77-C-3123 SVED8TD-71 .348-0-253 DAAJ 02-76-C-0006 A80-35046 P80-22316 P80-22311 P33615-77-C-5278 SWEDBTD-77-4869 DAAJ02-76-C-0064 A80-35044 580-22320 P80-22310 P33615-78-C-2022 SWEDBTD-78-5543 DAAJ02-77-C-0003 P80-22352 P80-22320 580-22312 F33615-78-C-2037 SF54543300 P80-22351 N80-22313 P80-23474 P802303003 P80-23254 DAAJ02-77-C-0071 F33615-78-C-3202 zF54594001 P80-22351 P80-22257 P80-22267 ZP57572002 P80-23321 DAAK02-75-C-01 38 F33615-78-C-3221 ZF61 542001 P80-23433 P80-23320 A80-35057 505-02 P80-22734 DAAK11-77-C-0080 A80-35061 505-03 P80-23100 P80-22269 F33615-79-C-3224 505-07-11 P80-22297 DAAK50-79-C-0035 A80-35077 505-31-53-01 P80-22368 P80-23298 F33657-78-C-0484 505-31-53-03 P80-23332 DEP3-69 P80-22778' A80-34190 505-33-63-02 P80-22737 DPA001-78-C-0317 F49620-79-C-0013 P80-23683 P80-23256 P80-23257 505-35-3 P80-23295 DOT-PA77WA-4070 K/A72C/259/CB/A72C 505-35-33-01 P80-22304 P80-23305 P80-22278 505-41-13-03 P80-22358 DOT-PA79WA-4 184 NAG1-5 A80-35049 505-43-23-02 P80-23251 P80-23281 PASW-3198 P80-22306 505-44-13 P80-23282 P80-23287 P80-22412 506-51-11 P80-23250 DOT-PA79WA-4313 P80-23253 506-51-23-02 P80-24151 P80-23286 NASW-3199 P80-22260 506-51-34 P80-23327 DOT-PA80WA-4370 PAS1-11621 P80-23371 517-54-01 P80-23317 880-32890 PAS1-14552 A80-35100 530-04-13-01 P80-23283 EI-76-A-29-1060 NAS1-14605-13 532-02-11 P80-23249 P80-22778 A80-35969 533-01-43-03 P80-22265 PAS1-15154 A80-35957 534-02-13-22 P80-23008

C-i 1. Report No. 2. Government Accession No. 3. Recipient's Catalog No. NASA SP-7037 (125)

4. Title and Subtitle 5. Reoort Date August 1980 AERONAUTICAL ENGINEERING Performing Organization Code A Continuing Bibliography (Supplement 125)

7. Author(s) B. Performing Organization Report No.

10. Work Unit No. 9. Performing Organization Name and Address

National Aeronautics and Space Administration ii. Contract or Grant No. Washington, D. C. 205146

13. Type of Report and Period Covered 12. Sponsoring Agency Name and Ad1ress

14. Sponsoring Agency Code

15. Supplementary Notes

16. Abstract

This bibliography lists 1407 reports, articles, and other documents introduced into the NASA scientific and technical information system in July 1980.

17. Key Words (Suggested by Author(s)) 18. Distribution Statement

Aerodynamics Aeronautical Engineering Unclassified - Unlimited Aeronautics Bibliographies

19. Security Classif. (of this report) 20. Security Classif. (of this page) 21. No. of Pages 22. Price Unclassified . Unclassified 126 $5.00 HC

For sale by the National Technical Information Service, Springfield, Virginia 22161 NASA-Langley, 1980 PUBLIC COLLECTIONS OF NASA DOCUMENTS DOMESTIC NASA distributes its technical documents and bibliographic tools to eleven special libraries located in the organizations listed below. Each library is prepared to furnish the public such services as reference assistance, interlibrary loans, photocopy service, and assistance in obtaining copies of NASA documents for retention CALIFORNIA MASSACHUSETTS University of California, Berkeley Massachusetts Institute of Technology, Cambridge COLORADO MISSOURI University of Colorado, Boulder Linda Hall Library, Kansas City DISTRICT OF COLUMBIA NEW YORK Library of Congress Columbia University, New York GEORGIA OKLAHOMA Georgia Institute of Technology, Atlanta University of Oklahoma. Bizzell Library ILLINOIS PENNSYLVANIA The John Crerar Library, Chicago Carnegie Library of Pittsburgh WASHINGTON University of Washington. Seattle NASA publications (those indicated by an "s" foowir,g the accession number) are also received by the following public and free libraries. CALIFORNIA NEW YORK Los Angeles Public Library Brooklyn Public Library San Diego Public Library Buffalo and Erie County Public Library COLORADO Rochester Public Library Denver Public Library New York Public Library CONNECTICUT OHIO Hartford Public Library Akron Public Library MARYLAND Cincinnati Public Library Enoch Pratt Free Library, Baltimore Cleveland Public Library MASSACHUSETTS Dayton Public Library Boston Public Library Toledo Public Library MICHIGAN TENNESSEE Detroit Public Library Memphis Public Library MINNESOTA TEXAS Minneapolis Public Library Dallas Public Library MISSOURI Fort Worth Public Library Kansas City Public Library WASHINGTON St. Louis Public Library Seattle Public Library NEW JERSEY WISCONSIN Trenton Public Library Milwaukee Public Library

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NASA CONTINUING BIBLIOGRAPHY SERIES

NUMBER TITLE FREQUENCY NASA SP-7011 AEROSPACE MEDICINE AND BIOLOGY Monthly Aviation medicine, space medicine, and space biology NASA SP-7037 AERONAUTICAL ENGINEERING Monthly Engineering, design, and operation of aircraft and aircraft components NASA SP-7039 NASA PATENT ABSTRACTS BIBLIOGRAPHY Semiannually NASA patents and applications for parent NASA SP-7041 EARTH RESOURCES Quarterly Remote sensing of earth resources by aircraft and spacecraft NASA SP-7043 ENERGY Quarterly Energy sources, solar energy, energy conversion, transport, and storage NASA SP-7500 MANAGEMENT Annually Program, contract, and personnel management, and management techniques

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