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AERONAUTICAL ENGINEERING

A Special Bibliography

Supplement 7

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 .June 197 1 in Scientific and Technical Aerospace Reports (STAR) international Aerospace Abstracts IIAAI.

Srieirrific aird Terhiriral Irrjoritroliorr OJJire OFFICE OF INDUSTRY AFFAIRS AND TECHNOLOGY UTILIZATION 197 I NATIONAL AERONAUTICS AND SPACE ADMINISTRATION INTRODUCTION

Under the terms of an interagency agreement with the Federal Aviation Admin- istration 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. This supplement to Aeroriaufical &iigirieeririg-A Special Bibliography (NASA SP-7037)

Ii,[\ ~OOi-cpt)rl\. p~tiriial;ir~icIc\. ;ii,cl oihL,r Ll(,ciiiiicI (4 oi-i;iii;ill! ;i~ii~o~i~~cc~lIII .Iiriic 197 1 in Scietifific arid Technical Aerospace Reports (STAR/ or in liiferiiafiorial Aerospace Ahsfracfs (IAA). For previous bibliographies in this series, see inside of front cover. 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 by an abstract. The listing of the entries is arranged in two major sections, IAA Erirries and STAR Etitri~in that crdcr. The cita!ioiis and absiracts are reproduced exactly as they appeared originally in IAA or STAR, including the original accession numbers from the respective announcement iournals. This procedure, which saves time and money, accounts for the slight variation in citation appearances. Three indexes- +ubjrct, personal author, and contract number-are included. An annual cumulative index will be published.

... 111 AVAILABILITY OF CITED PUBLICATIONS

IAA ENTRIES (A71-10000 Series)

All publications abstracted in this Section are available from the Technical Information Serv- ice American Institute of Aeronautics and Astronautics Inc (AIAA). as follows Paper copies are available at $5 00 per document up to a maximum of 20 pages The charge for each additional page is 25 cents Microfiche‘” are available at the rate of $1 00 per microfiche for documents identified by the # symbol following the accession number A number of publications, because of their special CtiaracIerisiiLs. die ava;!ab!e ~n!yfor reference in the AIAA Technical Information Service Library Minimum airmail postage to foreign countries is $1 00

Please refer to the accession number e g , A71 -10613. when requesting publications

STAR ENTRIES (N71-10000 Series)

A source from which a publication abstracted in this Section is available to the public is ordinarily given on the last line of the citation, e,g., Avail: NTIS. The following are the most commonly indicated soiirces (full addresses of these organizations are listed at the end of this introduction): Avail. NTIS. Sold by the National Technical Information Service at a standard price of $3.00 for hard copy (printed, facsimile, or reproduced from microcopy) of 300 pages or less. Documents in the 301 to 600 page range are sold for $6.00 in hard COPY. and those in the 601 to 900 page range are sold at $9.00 Documents exceeding 900 pages are priced by NTlS on an individual basis. These prices apply retro- actively to all documents in the NTlS collection, but in addition, documents of 300 pages or less that are over two years old (from date of announcement in Govern- ment Reports Announcements, or STAR for those items announced only in STAR) will have a surcharge of $3.00 added for a total price of $6.00. No additional surcharge will be added for documents over 300 pages. Microfiche is available from NTlS at a standard price of 95 cents (regardless of age) for those documents identified by the # sign following the accession number (e.%. N7 1-10411#) and having an NTlS availability shown in the citation. Avail: SOD (or GPO). Sold by the Superintendent of Documents, U.S. Government Printing Office, in hard copy. The price is given following the availability line. (An order received by NTlS for one of these documents will be filled at the SOD price if hard copy is requested. NTlS will also fill microfiche requests, at the standard 65 cent price, for those documents identified by a # symbol. SOD does not sell microfiche.) Avail. NASA Scientific and Technical Information Office. Documents with this availability are usually news releases or informational brochures available without charge in paper copy. Avail: AEC Depository Libraries. Organizations in U.S. cities and abroad that maintain collections of U.S. Atomic Energy Commission reports, usually in microfiche form. are listed in Nuclear Science Abstracts. Services bvailable from the USAEC and its depositories are described in a booklet, Science Information Available from the Atomic Energy Commission (TID-4550). which may be obtained without charge from the USAEC Division of Technical Information, Avail: Univ. Microfilms. Documents so indicated are dissertations selected from Disserta- tion Abstracts. and are sold by University Microfilms, Inc. as xerographic COPY (HC). microfilm. or microfiche at the prices shown. Microfiche are available only for those dissertations published since January 1, 1970. ~llrequests should cite the author and the Order Number as they appear in the citation.

(1) A microfiche is a transparent sheet of film. 105 x 148 mm in size. contaming up to 72 pages of Information reduced to micro images (not to exceed 20 1 reduction)

iv Avail: HMSO. Publications of Her Majesty’s Stationery Office are sold in the U.S. by British Information Services (BIS). New York City. The U.S. price (including a service charge) is given, or a conversion table may be obtained from BIS. Avail: National Lending Library. Boston Spa. England. Sold by this organization at the price shown. (If none is given, an inquiry should be addressed to NLL.) Avail: ZLDI. Sold by the Zentralstelle fur Luftfahrtdokumentation und -Information. Munich, Federal Republic of Germany. at the price shown in deutschmarks (DM). Avail: Issuing Activity, or Corporate Author. or no indication of availability: Inquiries as to the availability of these documents should be addressed to the organization shown in the citation as the corporate author of the document. Avail: U.S. Patent Office. Sold by Commissioner of Patents, U.S. Patent Office, at the standard price of $.SO each, postage free. Other availabilities: If the publication is available from a source other than the above, the publisher and his address will be displayed entirely on the availability line or in combination with the corporate author line.

GENERAL AVAl LAB I LlTY

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 !nca! !ihrar:es ?:io; to oideiiny any pubiication 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.

SU BSCRlPTI ON AVAl LAB1 LlTY

This publicat~on,s abailable on subscription from the National Technical Information Service (NTIS) The annual subscription rate for the monthly supplements. excluding the annual cumulative index, is $18 00 All questions relating to subscriptions should be referred to the NTI S

V ADDRESSES OF 0 R G ANI ZATlO N S

American Institute of Aeronautics National Aeronautics and Space and Astronautics Administration Technical Information Service Scientific and Technical Information 750 Third Ave. Office (KSI) New York, N.Y. 10017 Washington. D C 20546

National Lending Library for Science British Information Service and Technology 845 Third Ave Boston Spa, Yorkshire, England New York. N Y 10022 National Technical Information Service Springfield, Virginia 22 151 Commissioner of Patents U.S. Patent Office Superintendent of Documents Washington, D.C. 20231 U S Government Printing Office Washington, D C 20402 Defense Documentation Center Cameron Station University Microfilms, Inc. Alexandria. Virginia 2231 4 A Xerox Company 300 North Zeeb Road ESRO/ELDO Space Documentation Service Ann Arbor, Michigan 48106 European Space Research Organization 114, av de Neuilly University Microfilms. Inc. 92-Neuillv-sur-Seine. France Tylers Green London, England Her Majesty’s Stationery Office P.O. Box 569, S.E. 1 U S Atomic Energy Commission London, England Division of Technical Information PO Box62 NASA Scientific and Technical Information Oak Ridge. Tennessee 37830 Facility PO Box33 Zentralstelle fur Luftfahrtdoku College Park, Maryland 20740 mentation und-Information 8 Munchen 86 Postfach 880 Federal Republic of Germany

vi TABLE OF CONTENTS

Page

IAAEntries ...... 339 STAREntries ...... 37 1

Subjectlndex ...... A- 1 Personal Author Index ...... B-I Contract Number Index ...... c-1

TYPICAL CITATION AND ABSTRACT FROM STAR

NASA SPONSORED AVAILABLE ON DOCUMENT

ACCESSlON NUMBER- N71-12035*# Pratt and Whitney Aircraft East Hartford Conn CORPORATE DEVELOPMENT OF MAINSHAFT SEALS FOR ADVANCED c7 SOURCE AIR BREATHING PROPULSION SYSTEMS, PHASE 2 Final TITLE 2Report PUBUCATION V P Povinelli and A H McKibbin 23 Jun5970 122 p refs DATE (Contract NAS3-7609)

COUU gas-turbine engines were designed fabricated and tested The seal COO€ CONTRACT concepts incorporated lift geometries which used the relattve motion OR GRANT between the primary seal surfaces to provide positive separation (film lubrication) One design (self acting) with shrouded Rayleigh step lift pads operated with a gas film separating the sealing faces AVAILABILITY REPORT SOURCE NUMBER The other desrgn (hvdrodpsm8d wcrh a sptral groove geometry operated with oil film separation Tests of the gas-film seal demonshatea the ieasiDility of operation at gas temperatures to 1200 F pressure differentials to 250 psi and sliding speeds to 450 ft/sec Excellent correlations with analytically predicted performance parameters were obtained Face wear was less than 0 1 mil after 320 hours at an air temperature of 1000 F a pressure differential of 200 psi and a sliding speed of 400 ft/sec Average air leakage during that test was 14 scfm These operating conditions exceed the capability of conventional contact seals and the air leakage IS 1/10 that of a labyrinth seal Testing of the oil-film seal revealed an inadequate seal force balance Author

TYPICAL CITATION AND ABSTRACT FROM IAA

NASA SPONSORED AVAILABLE ON DOCUMENT MICROFICHE

ACCESSlON-A71-10969 # Sphere drag in near-freemolecule hypersonic TITLE NUMBER flow. M. I. Kussoy, D. A. Stewart, and C. C. Horstman (NASA. Ames Research Cezer, Moffett Field, Calif.). AlAA Journal, vol. 8, Nov. AUTHORS 1970, p. 2104, 2105. 9 refs. AUTHORS” Investigation of the drag coefficient of spheres at hypersonic AFFILIATION Mach numbers for near-free-molecule flow conditions. Sphere drag data in the near-free-molecular regime for flow conditions close to earth satellite conditions, obtained by using a free-flight technique in PUBLICATION the Ames 42-in. shock tunnel are tabulated, shown graphically, and DATE discussed. O.H.

vii i i AERONAUTICAL ENGINEERING

A Special Bibliography (Suppl. 7) JULY 1971

characteristics are known either from experimental data or from analysis. The order of accuracy is one higher than that of existing methods, and boundary distortion and pressure distribution shift can be taken into account. The procedure has been tested against existing test data and in the particular case of elliptic cylinders in a subsonic IAA ENTRIES stream and agreement found to be very good. (Author) A7125161 Lift and hinge moments of a delta control surface in a blunt-nosed canard configuration. J. Reichenthal and J. Rom (Technion - Israel Institute of Technology, Haifa, Israel). (Israel Annual Conference on Aviation and Astronautics, 13th. Tel Aviv and Haifa, Israel. Mar. 3, 4. 1971.) Israel Journal of Technology, vol. 9. no. 1-2. 1971.p. 165-175.9refs. A71-25144 _” On two dimensional sound sources and sound The aerodynamic forces and the hinge moments of a delta wing yaws. Kaan Edis (Istanbul. Technical University, Istanbul. Turkey). ..A:^..,,,,h is reifsce of a iikfoirn ioilii-irl aii-angemen: installed istanbui Teknrk Univemitesi Bulteni, vol. 23. no. 1. 1970, p. 13-26. 5 one behind a blunt nose are investigated. In order to obtain effective refs. aerodynamic control the delta wings used here are of moderate A solution of the two-dimensional wave equation is obtained in aspect ratio. The measurements of the forces and the moments acting terms of the time-retarded argument, using asymptotic expansions of on the control surface, which is installed on the cylindrical model Bessel functions and the far field boundary condition. For the behind the blunt nose, are obtained in subsonic, transonic and acoustic intensity and acoustic power of aeroacoustic noise sources, supersonic flows in the appropriate wind tunnels. These measure- simple analytical expressions are derived, and a short analysis for the ments are obtained over a wide range of angles of attack and control two-dimensional simple source is given. M.V.E. deflections. The results of these measurements are compared with the vgrinijs thporetical qalq!il3fiOnc for lift oq PI?:! wing< It ic found A71-25145 Israel Annual Conference on Aviation and that the experimental data can be described by using the nonlinear ktronautics, 13th. Tel Aviv and Haifa, Israel, March 3, 4, 1971. delta wing analyses, including the effects of the wing-body inter- Proceedings. Conference supported by the Israel Ministry of Trans- ference parameters and the leading edge vortex coiitributions to the port; the Israel Ministry of Defence, Armament Development wing lift forces and moments. It is shown that the aerodynamic Authority; the Israel Ministry of Commerce and Industry: the coefficients for the present configuration follow qualitatively those Technion . Israel Institute of Technology; Tel Aviv University; the found for a delta wing alone, although in this case the nonlinear lift University of Negev; Aviation Services, Ltd.; and El-AI, Israel is significantly larger in the subsonic speed range. (Author) Airlines. Israel Journal of Technology, vol. 9. no. 1-2. 1971. 199 p. The principal topics discussed are: the temperature distribution A71 -25164 Aircraft power-on polars corrected for propel- in a rotating sphere and in the ambient flow field; propagation and ler slipstream deflection. Y. Elirar (Israel Aircraft Industries, Ltd.. scattering of sound waves in moving media; application of flush- Lod, Israel). (Israel Annual Conference on Aviation and Astro- mounted electrostatic probes to flow diagnostics; compressibility nautics, 13th, Tel Aviv and Haifa. Israel, Mar. 3, 4, 1971.1 Israel correction for subsonic flows; methods and solutions in coupled Journalof Technology, vol. 9. no. 1-2, 1971, p. 195.199. thermoelasticity; laminar-turbulent transition in pipe flows; inter- A method for evaluating propeller power effect on lift and drag action between an axisymmetric jet and a coaxial oscillating stream; coefficients of a twin engine STOL aircraft is presented. This method measurement of heat transfer coefficients between metal strips in is based on a theoretical approach which deals simultaneously with contact; influence of in-plane boundary conditions on the buckling slipstream effect on lift and drag considering slipstream deflection by of clamped conical shells; mixing of homogeneous coaxial streams; the wing flaps. This approach is applied to test flight data of the flowfield analysis of plumes of underexpanded jets; lift and hinge Arava STOL aircraft, yielding a unique polar based on corrected lift moments of a delta control surface in a blunt-nosed canard and drag coefficients (for each flap setting) valid for the whole configuration; and stable limit cycles and triggering limits of the first available positive thrust levels at lift coefficients below the power-on radial mode in unstable liquid rockets. stall. It is shown that this method can reduce the number of test V.P. flights required to cover the whole range of thrust and lift coefficients. (Author)

A71-25149 Compressibility correction for subsonic flows. M. J. Cohen (Technion . !srael Institute of Technology, Haifa, Israel). (Israel Annual Conference on Aviation and Astronautics, 13th. Tel A71-25180 Performance of exhaust silencer components. Aviv and Haifa, Israel, Mar. 3, 4, 1971.) Israel Journal of Tech- R. J. Alfredson (NASA. Langley Research Center, Harnpton, Va.) nology, vol. 9. no. 1-2, 1971, p. 29-36. and P 0. A L. Davies (Southampton. University, Southampton, Tables are presented which enable aerodynamics designers to England). Journal of Soundand Vibration, vol. 15, Mar. 22. 1971. p. estimate the effect of compressibility in flows whose incompressible 175-196. 18 refs. Research supported by the Ministry of Defence.

339 A71-25188

This paper describes part of a systematic investigation aimed at carried out on a sample aircraft in order to establish numerical producing more accurate theoretical models for internal combustion evaluations of their relative merits. Among the three systems engine exhaust silencers. The performance of a number of silencer proposed, the split control system is simplest in its mechanization components, e.g, area discontinuities, branched systems, was mea- and is quite close to the optimal system in its alleviation capabilitv. sured in a very noisy exhaust system. These results were then It is therefore concluded that the split control system is the most compared with those predicted by the one-dimensional linearized desirable one for inclusion in a futcre aircraft A.B.K. theory with mean gas flow. It was found that this one-dimensional theory was sufficiently accurate for silencer design purposes. (Author) A71-25231 NAMC C-1A . Japan's tactical transpart (NAMC C-1A - Japanischer Kampfzonen-Transporter). Hans Brenner. Flugrevue/Flugwelt International, Apr. 1971, p. 23-25. In German. A71-25188 # A note on the T-tail flutter. Kyuichiro The technical specifications of a medium-weight tactical trans- Washizu, Teruo Ichikawa. and Takeshi Adachi. Japan Society for port aircraft intended to replace the present Curtiss C-46 fleet are Aeronautical and Space Sciences, Journal, vol. 18. Sept. 1970, p. presented. The plane is powered by two Pratt & Whitney JP 8 D-9 327-333. 17 refs. In Japanese, with abstract in English. turbofan engines with a takeoff thrust of 6575 kgf each. The span is Demonstration that the dihedral effect of the horizontal tail has 31.00 m. the length 29.00 m, the height 10.06 m, the wing area a significant effect on T-tail flutter and that the flutter speed is 120.70 sq m, the payload 11,800 kg, the takeoff weight 38,600 kg. appreciably dependent on the angle of attack of the horizontal tail the maximum speed 815 km at 7600 m, the cruising speed 704 km at surface The flutter characteristics of a simplified T-tail are analyzed. 10,700 m, and the takeoff distance 671 m. The plane carries a crew A quasi-steady aerodynamic force is used to represent the dihedral of five. V.P. effect of the horizontal tail. Some references are made to experimental data on T-tail flutter which show a tendency similar to that observed by the authors. A.B.K. A71-25232 The SST and air traffic control (SST und Flugsicherung). Frank W. Fischer. flugrevue/flugwelt lnrernational, Apr. 1971, p. 27-29. In German. A71-25189 # Some effects of systematically varied location ATC considerations concerning the introduction of the of one concentrated mass on transonic flutter characteristics of Concorde to passenger transport service are presented. A review of sweptback thin cantilever wing. II. Eiichi Nakai, Toshiyuki Morita, the takeoff and landing characteristics of the Concorde shows that and Toshiro Takagi. Japan Society for Aeronaurical and Space the present ATC regulations should be applicable also to this craft. It Sciences, Journal, vol. 18, Sept. 1970, p. 333-340. 5 refs. In is suggested that priority treatments of the Concorde be reduced tu i Japanese, with abstract in English. minimum. Srraight-line acceleration paths from 100 to 170 n mi. Experimental investigation of the effects of longitudinal and starting as close as possible to the airport, are proposed together with vertical variation of the location of an engine-pod shaped con- flight sectors above FL 430 (to ensure longitudinal separation!. centrated mass on the transonic flutter characteristics of thin Computerized ATC control over the entire flight path and rectilinew cantilever wrngs wirh a sweepback angle of 20 deg and a panel aspect descent paths are suggested. v P. ratio and taper ratio of 4.0 and 0.4, respectively. The investigation was carried out in a transonic blowdown wind tunnel for flutter testing at Mach numbers between 0.759 and 0.964. The results A71-25233 The Viggen landing system (Das Viggen- obtained are presented in the form of a comparison of the limits of Landesystem). Roland Ziegler f lugrevue/Flugwelt International, flutter density and the flutter-velocity coefficients of the respective Apr. 1971, p. 36-38. In German. wing-pod configuration as a function of Mach number. Comparisons The technical aspects of a tactical (all-weather) instrument are also made with calculated results obtained by the matrix iteration landing system developed by Cutler-Hammer (USA) for the Swedish method employing two-dimensional incompressible unsteady flow multipurpose STOL military aircraft Saab 37 Viggen are discussed theory as the required oscillaton/ aerodynamic forces. A.B.K. This microwave scanning-beam system consists essentially of a ground station located close to the landing runway and of an airborne receiver-encoder. The coverage of the system and the angle A71-25194 # The effect of wind-gradient on the landing data transmission and scan cycle and encoding systems are approach of an aeroplane. Nird Hira, Masao Inoue, and Ei Iti diagrammed and discussed. V.P. Takizawa. Japan Society for Aeronautical and Space Sciences, Journal, vol. 18, June 1970, p. 208-214. 6 refs. In Japanese, with abstract in English. A71-25256 # Experience gained in the operational prepara- Consideration of the effect of a wind gradient on the flight tion and putting into service of the IL-62 long-haul jet aircraft characteristics of an aircraft during the final approach to landing. It (Erfahrungen bei der Einsatzvorbereitung und lndienststellung des is shown by numerical calculations that a wind gradient causes a Langstrecken-Strahlflugzeuges IL-62). Klaus Ape1 (Interflug Gesell- considerable amount ot path deviation of an aircraft du:iiig schaft fur Internationalen Flugverkehr mbH, Berlin, East Germany). particular flight regimes. It is concluded thar an aircraft d5ring Technisch-okonomische lnformationen der zivilen Luftfahrt, vol. 6, landing. being accelerated by the wind gradient, may touclt thv no. 9, 1970, p. 445-451. In German. ground earlier than expected, A.ri . I;. Description of the problems which arose in converting over from the use of the IL-18 and the Tu-134 to the IL-62 long-haul jet A71-25195 # On the most feasible configuration for airp1ar.r aircraft, noting the methods of solution adopted. Problems in gust-alleviation system. Kenji Nakagawa, Yoshisada Mui:~tsu, retraining flight and maintenance personnel in the handling of the Toshihiro Tsumura, and Naofumi Fujiwara. Japan Society for new aircraft in the shortest possible time without upsetting existing Aeronautical and Space Sciences, Journal, vol. 18, June 19511, p. schedules are reviewed, It was decided to retrain all of the flight 214-222. 21 refs. In Japanese, with abstract in English. personnel and a small number of the engineering and technical Consideration of a gust-alleviation system in which in-.] tial personnel at the manufacturer's plant in the Soviet Union. It was also sensors and feedback devices are employed and both wing flap, an0 necessary to give passenger and baggage handling briefing regarding elevators are operated io reduce gust-induced aircraft motions, 1hl-er. the IL-62 to the personnel at airports not familiar with this aircraft. possible configwarions of such a system are proposed: link~gr The more exacting requirements of onboard passenger service are control, noninteracting control, and split control. Chang's (lyjl) noted. A.B.K. frequency domain theory is applied to obtain an optimal control system which minimizes the gust response according to sonic A71-25258 # Formalities involving the Tu-154 at foreign criterion. Calculations of the alleviation capability of each system aic airports in the case of three-man crews (Die Abfertigung der Tu-154

340 ii F A71 -25306

auf audandischen Flughafen bei Einsatz von Drei-Mann- Equipment System Program Office, Wright-Patterson AFB, Ohio). Besatzungen). lngolf Stein (Interflug Gesellxhaft fiir Internationalen American Astronautical Society and American Institute of Aero- Flugverkehr mbH, Berlin. East Germany). Technisch-dkonomische nautics and Astronautics, Variable Geometry and Expandable Struc- lnformationen derzivilen Lufrfahrt, vol. 6, no. 10, 1970, p. 508-514. tures Conference, Anaheim, Calif., Apr. 21-23, 1971, AlAA Paper 532. 15 refs. In German. 71-398. 8 p. Members, $1.50; nonmembers, $2.00. Discussion of the responsibilities of the three crew members of A system of expandable structures has been developed, procured the Tu-154 longhaul jet passenger and cargo aircraft. It is shown that and demonstrated by the USAF, which provides a Tactical Fighter a three-man crew consisting of a commander, a copilot, and a flight Organization with a worldwide rapid air mobile capability. These engineer is the best of the possible three-man variants considered. structures are fabricated of foam and honeycomb sandwich materials This arrangement is shown to be especially useful in the filling out of with aluminum facing and are built to aircraft design criteria with the flight plan by the copilot, the fueling of the aircraft, and the expansion ratios which vary from 3: 1 to 1 1 : 1. Each shelter serves as loading and unloading of the baggage compartments when the an air shipping container and is expanded to perform its ground container system is not employed. A.B.K. function. These functions cover the gamut from a complete aircraft maintenance complex to a housekeeping area of dormitories, A71-25259 ii Jet propulsion systems in helicopters (Ubcr kitchens, and latrines. The use of high strength sandwich materials in these structures coupled with expandability have given the USAF a Reaktionsantriebe bei Hubschraubern). Michael Caspari (InterflJF Gesellschaft fur lnternationalen Flugverkehr mbH, Berlin. Ea.: rapid deployable capability with a minimum of air transport sorties. (Author) Germany). Technisch-okonomische Jnformationen der zivilen Luff- fahrr, vol. 6, no. 10, 1970. p. 515-526. 10 refs. In German. A71-25277 Structural considerations in the development Discussion of various types of blade tip propulsion systems to: 2 of extremely lightweight decelerators. Peter G. Niederer (Astro jet-powered helicopters. The power systems considered include the Research Corp., Santa Barbara. Calif.). use of a turbocompressor or gas generator, turbine air jet propulsior. American Astronautical Society and American Institute of Aeronautics and Astronautics, systems, pulsejet engines, ramjet propulsion systems. and rockr: powered propulsion systems. The possibilities of blade tip propulsion Variable Geometry and Expandable Structures Conference, with the aid of turbogenerators are explored in detail, including Anaheim, Calif.. Apr. 21-23. 1971, AlAA Paper 71-401. 13 p. 7 refs. cold-gas propulsion, hot-gas propulsion, and the hot cyclehotor winil Members. $1.50. nonmembers, $2.00. Current development of the Stokes-flow decelerator is aimed at concept. The use of hot-gas propulsion in a proposed passengel increasing the altitude and improving the quality of atmospheric data helicopter and a proposed crane helicopter is described. A.B.K sampling of rocket-borne radiosondes. This very lightweight Anmln...r-r -.,--,.*..A *^ -..--..-. .--.-..--...-..-- ;-I-:-.. P. . "I_.,.CI.,.","I I.. C",'CCLC" L" 'Yv'tJ"', II,.,I"'IIsII,.L;"II ""cly,tlt,y v.175. A7125260 f First flight and operation experiences with thp kg, and to descend with subsonic velocity from altitudes of 80 to 90 IL-62 long-haul jet aircraft (Ere Flug- und Betnebserfahrungen mil km. Its two distinctive features are: (1) its large flat open mesh dem Langstrecken-Strahlflugzeug IL-62). Gerhard Fries (Interflu.? filament canopy of low surface density and high viscous drag Gesellschaft fur Internationalen Flugverkehr mbH. Berlin, Easr efficiency and (2) its need for structural support members in the Germany). Technisch-iikonomische Informationen der zivilef, canopy. Several parachute configurations are described; aspects of Luftfahrt, vol. 6, no. 11, 1970. p. 557-565. In German. their structural designs are presented and their influence on descent Discussion of some of the special features characterizing the performance is outlined. Characteristics of parachutes for small operation of the tL-62 long-haul jet. The crew configuration to bt payload weights are analyzed. and configurations are compared using employed is described as well as *he oqa?!z?ticr! cf ?he :raining ti critwia of weight ?ark;rhility, and deplyshil;?y rr\mbined. Resu!?s be given to prospective crew members at the training center in the of theoretical structural analyses of braces are checked by experi- Soviet Union. Problems in passenger handling, loading and unloading, ments with subscale model parachutes. (Author) fueling, and centering the aircraft bre noted, and the handliny qualities of the aiicraft during taxiiny, takeoff and ascent, level A71-25278 4 Expandable structures for midair pilot rescue flight, descent, landing approach, and landirlg are reviewed. The device. Richard R. Steere (USAF. Aeronautical Systems Div., functions of the navigation computer. the air data computer, the Wright-Patterson AFB, Ohio) and Fred R. Nebiker (Goodyear course system, and the autopilot are outlined. A.B.K. Aerospace Corp., Aero-Mechanical Systems Div., Akron, Ohio), American Astronautical Society and American Institute of Aero- nautics and Astronautics, Variable Geometry and Expandable Struc- A71-25271 r Variable geometry external fuel tanks. Lowell tures Conference, Anaheim, Calif., Apr. 21-23, 1971. AIAA Paper Conveise, Levelle Mahood (USAF. Flight Dynamics Laboratory. 71-402. 7 p. 6 refs. Members, $1.50; nonmembers, S2.00. WI ight-Patteison AFB. Ohio). and Boris Levenetz (Whittaker Coip.. A rescue device combining a modified personnel parachute, a Sari Diego. Calif 1. AnJeriCaIJ Astronaotical Society and American small-size high-capacity burner system, and a lightweight hot-air Institute of Aeronautics and Astronaiitics, Variable Geometry and BALLUTE is considered. In this system, after the normal ejection Expandable Structures Conference, Anaheih, Calif., Apr. 2 1-23. mode and after the man is at terminal velocity on his parachute, the 1971. AIAA Paper 71-395. 11 p. Members, $1.50. nonmembers, ram-air filled BALLUTE is deployed above his parachute. At a s2.00. predetermined time, a butane burner ignites and, with an initial This paper piescnts the curient and planned effort and progress preheat high burn rate, the system becomes buoyant. The crewman in the development of a variable geometry external fuel tank for use has the capability to ascend or descend by operating a flow control on high perfornidnce aiicraft in operation and development. A valve manually. Development of the system included analyses and unique feature of the tank is that it contracts as fuel is tiansferred, tests necessary to establish the BALLUTE size, shape, and material continuously reducing drag. Positive expulsion of the fuel eliminates requiiements Candidate materials were examined, their strength and potentially explosive ullage. centei of gravity shifting. and sloshing. thermal properties measured, and a final material selected. G.R. The piototype tanks are designed foi the swivel pylons of the F-111 as a test bed aircraft. With a capacity of 600 gallons, they will Contiact from a inaximum diameter of 32 inches to about 12 inches A71-25306 + AFFDL investigations concerning the coupled The stiucture is a combination of rigid and elastomeric panels, wing-fuselagetail flutter phenomenon. W. J. Mykytow. T. E. Noll. L. positively cunstrained and contiolltrd by an activatlon mechanism. J Huttsell, and M. H. Shirk (USAF, Flight Dynamics Laboratory, Fabi icatton of piototype tanks is in proyiess with testing beginning Wright Patterson AFB. Ohio). American Institute of Aeronautics and in ApiiI 1971. (Author) Astronautics and American Society of Mechanical Engineers, Struc- tures, Structural Dynamics and Materials Conference, 12th. A71-25274 Y USAF air mobility via expandable structures. Anaheim, Calif., Apr. 19-21. 1971, AlAA Paper 71-326. 12 p. 35 J. E. Catlin, M. E. Brickson, and R. W. Matzko (USAF, Bare refs. Members, S1.50. nonmembers, $2.00.

341 A71 -25307

Low speed flutter model tests are described which were per- A71-25310 // Optimization of a supersonic panel subject to ' formed to determine such controlling parameters as wing sweep a flutter constraint - A finite element solution. Roy R. Craig. Jr. angle, wing bending to fuselage torsion frequency ratio, wing/ (Texas, University. Austin, Tex.). American Institute of Aeronautics hor4zontal tail longitudinal separation and tail dihedral angle, and and Astronautics and American Society of Mechanical Engineers, their effects on flutter velocities. The results indicate that flutter Structures, Structural Dynamics and Materials Conference, 12th, velocities can be reduced by increasing wind sweep, that wing Anaheim, Calif., Apr. 19-21, 1971, AlAA Paper 71-330. 7 p. 7 refs. bendinq to fuselage torsion frequency ratios between 0.3 and 0.6 Members, $1.50: nonmembers, $2.00. provide minimum flutter speeds, and that interterence effects of The equariori, ui I-I-IOT;G; for ii :emi-!nf!nitp flat sandwich panel wing on tail tend to enhance flutter. V.P. in supersonic flow are expressed in matrix form by use of a finite element model of the panel. The following aeroelastic optimization ~71.25307 /I Analysis of supersonic-hypersonic flutter of problem is posed. Minimize the total weight of the panel while lifting surfaces at angle of attack. E. Carson Yates. Jr.. and Robert M. keeping the dynamic pressure paraineter constant at the value Bennett (NASA, Langley Researcli Center, Hampton. Va.). American corresponding to flutter of a uniform panel. A first.order gradient Institute of Aeronautics and Astronautics and American Society of procedure consisting of a 'weight-minimization mode' and a 'lambda- Mechanical Engineers, Structures, Structural Dynamics and Materials modification mode' is employed. For a panel divided into 5 elements Conference, 12th. Anaheim, Calif., Apr. 19-21. 1971, AlAA Paper and having 80% of the mass structural, a total weight reduction of 71-327. 16 p. 35 refs Members, $1.50, nonmembers, $2.00. 4% is obtained. (Author) The features of supersonic-hypersonic flutter of lifting surfaces at angie of diiaih are studicd ana!ptically by three methods: a A71-25317 7 Development of a torsional-flexirral stability modified strip analysis, incorporating shock-expansion theory; a analysis of stiffened titanium panels for application to the U.S. modified Newtonian-flow theory: and a local-flow piston theory. Supersonic Transport. John G. Tawresey and James E. Lium (Boeing Flutter calculations for two pitching and translating rectangular Co., Seattle, Wash.). American Institute of Aeronautics and Astro- wings with diamond airfoils indicate that a typical degradation of nautics and American Sociery of Mechanical Engineers, Structures, flutter speed index occurs with increasing angle of attack (which is Structural Dynamics and Materials Conference, 1 Zth, Anaheim, most pronounced for thin sections at low angles of attack). For some Calif., Apr. 19-21, 1971, AlAA Paper 71-338. 9 p. 5 refs. Members, airfoil shapes, however, a forward location of the center of gravity $1.50; nonmembers, $2.00. may mitigate the degradation at low to moderate angles of attack A solution for torsional flexural buckling of stiffened skins, and essentially postpone it until shock-detachment conditions are riveted or integral. is obtained by the use of small deflection energy approached. The vicinity of shock detachment is shown to be a methods. The effects of local distortions of the stiffener and skin critical region for supersonic-hypersonic flutter. V.P. cross sections and the effects of thermal gradient are directly accounted for in the buckling deternlinant The order of the A71-25308 ,# Recent contributions to experiments on cy. determinant is dependent on the number of distortion modes lindrical shell panel flutter. W. Horn, G. Barr (Sandia Laboratories, selected. The method is applicable to any open section stiffener Albuquerque. N Mex.), L. Carter (Syracuse University Research attached to a skin. It has demonstrated good correlation with test Corp., Syracuse. N.Y.), and R Stearman (Texas, University. Austin, data over a broad parametei iange and has been extensively applied Tex.), American Institute of Aeronaotics and Astronautics and to the titanium compression panel design of the United States American Society of Mechanica! Engineers, Structures, Structural Supersonic Transport fuselage (Author) Dynamics and Materials Conference. 12th. AfJahe~lll,Calif.. Apr. 19-21, 1971, AIAA Paper 71-328. 16 p. 34 refs. Members, $1.50; nonmembers, $2.00. USAF-supported research. A71-25319 fi Intermediate diagonal tension field shear beam The aeroelastic stability of cylindrical shell configurations was development for the Boeing SST. Raymond M. Mello, Max D. studied experimentally for various internal stress and supersonic flow Musgrove (Boeing Co.. Seattle, Wash.). and Robert E. Sherrer conditions. It was found that the still-air buckling characteristics of (Washington. University, Seattle, Wash.). American lnstitute of the shells were hardly influenced by the supersonic (Mach number Aeronautics and Astronautics and American Society of Mechanical 1.2 to 3.51 air stieam, so that still-air buckling data may be used to Engineers, Srructures, Structural Dynamics and Materials Con- determine the buckling loads of cylindrical shells in a supersonic flow ference, 12th, Anaheim, Calif., Apr. 19-21, 1971, AlAA Paper field. Two basic types of flutter instability were detected - one of a 71-340. 14 p 16 refs. Members, $1.50; nonmembers, $2.00. mild limited amplitude motion, causing no persistent damage to the This paper describes the comprehensive test and analysis shell even after several minutes, and the other of a more explosive program initiated for the development of titanium intermediate nature, which destioyed the shell a few seconds after onset. Both diagonal tension-field shear beam analysis and design methods types of panel flutter instability are found to be closely associated necessary to support the Boeing SST. Existing semiempirical design with the fluid bounddry layer characteristics. V.P. and analysis procedures for aluminum beams have been extended for use with titanium beams. Detailed studies of the test results and A71-25309 # A collocation method for predicting oscilla- current design methods show that major improvements of inter- tory subsonic pressure distributions on interfering parallel lifting mediate shear beam structural efficiency can be obtained through surfaces. A. M. Cunningham, Jr. (General Dynamics Corp., Convair improved analytical procedures. A general theoretical analysis of post Aerospace Dlv.. Fort Worth, Tex.). American Institute of Aero. buckled stiffened plates, adaptable to the analysis of intermediate nalJtiCs and Astronautics and American Society of Mechanical diagonal tension-field shear beams. was developed and is presented EWfIeerS. StructlJres. Structural Dynamics and Materials Con. here. The theoretical formulation of this nonlinear problem was ference, 12th. Atialieitii, Calif., Apr. 19-21, 1971, AlAA Paper solved by the Rayleigh-Ritz method. Improvements available after 71-329. 17 11. 19 refs. Membcrs, $1.50; nonmembers, $2 00. the theoretical program becomes fully operational should constitute A method IS presented which is an exteiisiori of the method a second generation of shear beam designs that will provide improved developed by Hsti for isolated surfaces and improved by A. M. and more efficient structure for the SST and other new vehicles. Cunningham. The integration scheme developed for non-planar Areas for improvements to shear beams that have evolved during the interference effects propeily converges to the Mangler formula as the program are indicated. (Author) surfaces become coldanar. The method and the criteria for choosing downwash point arrays a priori are verificd by comparison with results from expeiiment and other theories on various multiple A71-25321 // Critical analysis of the methods used for predicting the response of large flexible aircraft to continuous surface configuiations The method is also shown to he more econoinical than finite element methods for equivalent accuracy on atmospheric turbulence. Gabriel Coupry (ONERA. Chitillon-sous- Bagneux, Hauts-de-Seine, France). American Institute of Aeronautics identical problems. (Author) and Astronautics and American Society of Mechanical Engineers,

342 A71-25351

Structures, Srructural- Dyrian~ics and Materials Conference, 12th. developing efficient optimization and stress modules are described. A Amdtc,;/ll, C.j//t.,AD/-. 1.921. 7977. AlAA P~OC,/11-34.? 8 p. 12 leis. technique for finding a feasible ('safe') design is described and tts ~l~~~llll~~i5,s1 50: ~lonnlellltl~~lr. $2.00. applicaiion is demonstrated. Examples of the program's influence on l)ciiioiistiatioii of A siiiiple foii+iiilawliiclt irdker it pussiblu t? actual design are presented. User experience and reaction with d<,tc,iiiiiiir tlic :.tnyc of vdidity of twd nieihods toi piedicting optimization in practical applications is discussed. (Author) ic's~Joii~t'to tiit Ixilmce. Thts fiist mt:thod iiivolves the iissuniption of

lanc. This I:~L".L.~G!~is ?her? app!:cr! tz j flexibly scdled model of a supeisonic tiansport configuidtion. A7125350 P Dynamic interactions of high speed tracked air Compdrisolis between wind-tunnel data, the modal appioach, and cushion vehicles with their guideways - A parametric study. S. B. calculations based on stiffness influence coefficients are presented Biggers (Kentucky, University, Lexington, Ky.) and J. F. Wilson over the Mach number iange from M = 0.6 to 2.7. The results of this (Duke University, Durham, N.C.). American Institute of Aeronautics study 'show good agreement foi most cases between analysts and and Astronautics and American Society of Mechanical Engineers. expei iment. (Airtho;) Structures, Structural Dynamics and Materials Conference, 12th, Anaheim, Calif., Apr. 19-21, 1971, AlAA Paper 71-386. 13 p. 18 refs. Members. $1.50: nonmembers. $2.00 A71-25325 5 The structural modeling of aircraft tires. S. K. The vehicle-guideway system is modeled as an arbitrary number Cl,oL, 8.N. Zvciyt iXi'itiyii, uiiiveisity. Ann Aroor. iviicn.i, J. I. of lumped, double-sprung vehicle masses travelling in tandem along Lackey. and G. H. Nybakken. Ainericari Institute of Aeronauticsand simply supported beams. The vehicle load is transmitted to the Astronai/tics arid American Society of Mechanical Engineers, Struc- guideway as a time-varying uniform pressure compatible with vehicle tures, Structural Dynatilics arid Materials Conference, 12th. motian Effects of system parameters on the vehicle heave accelera~ Anaheim, Calif., Xpr. 19-21, 7971, AlAA Paper 77-346. 10 p. tions and on the guideway deflections and bending moments are Members, $1.50. inonniembers. $2.00. Grant No. NsG-344. evaluated for high vehicle speeds. By proper choice of parameters, Attempt to solve the difficulty of obtaining full size aircraft tire the passenger-compartment heave accelerations can be minimized, mt,chaiiical data by generating such data on small models. This has although very stiff and costly guideways, soft vehicle suspension the advantage of allowing the necessary measurements to be made systems, and high damping are required to keep this acceleration much mote quickly and economically. It also allows measurements below 0.1 g for vehicles travelling from 100 to 300 mph. T.M. of diicraft tires under extreme conditions. which cannot be tolerated on full scale experiments for safety reasons. The theory of tire modrlling is discussd in terms of tire mechanical properties, tire A71-25361 # Comparison of two stochastic models for stresses, and tire temperatures. From this, it is shown that certain threshold crossing studies of rotor blade flapping vibrations. G. H. dimensionless variables must be the same for model and prototype. Gaonkar and K. H. Hohenemser (Washington University, St. Louis, Data are presented which indicate that the concept of small scale Mo.). American Institute of Aeronautics and 4stronautics and modelling is both theoretically and practically achievable. F.R.L. American Society of Mechanical Engineers. Structures, Structural Dynamics and Materials Conference, 12th, Anaheim, Calif., Apr. A71-25340 + The impact of automated structural optimiza- 19-21, 1971, AlAA Paper 71-389. 10 p. 8 refs. Members, $1.50; tion on actual design. James L. Tocher (Boeing Computer Services, nonmembers. $2.00. Contract No. NAS 2-4151. Inc., Seattle, Wash.) and Richard N. Karnes (Boeing Co., Seattle, An earlier stochastic model which assumed that the vertical Wash.). American Institute of Aeronautics and Astronautics and turbulence velocity is uniform over the rotor disk is compared with a American Society of Mechanical Engineers, Stritctilres, Structural loss restrictive model which considers the correlation between Dynamics and Materials Conference, 12th. Anaheim. Calif.. Apr. vertical turbulence velocities across the rotor disk in the longitudinal 19-27, 1971, AIAA Paper 71-361. 10 p. 6 refs. Members, 51.50; direction. Both models are limited to low-lift high-advance-ratio nonmembers, $2.00. rotor operation where, however, turbulence excited blade vibrations The organization of a large-scale structural optimization are severe. Comparison for a typical example shows that the earlier Program and its application to practtcal aircraft problems IS and simpler mcdel is adequate down to ratios of turbulence scale described. The program combines the matkix displacement method length over rotor radius of about five - a region covering all Of structural analysis with mathematical programming to automati- foreseeable operational conditions. The analytical data are supple- cally design structures of minimum weight. Techniques used in mented by statistical data from analog studies. T.M.

34 3 A71 -25352

A71-25352 N Techniques for stability analysis and design utilizing a previously developed computer program. Once established, optimization with dynamic constraints of nonconservative linear several verification subcomponents were fabricated and tested. At systems. Richard L Bielawa (United Aircraft Research Laboratories. the conclusion of the tests, production type steel tooling was East Hartford, Conn.). American lnsrirure of Aeronautics and fabricated. Utilizing the mylar lay-up method and titanium inserts Astronautics and American Society of Mechanical Engineers, Srruc- for penetration, the required four B/E skins were molded. Destruc- tures, Srructural Dynamics and Materials Conference, 12rh, tive and nondestructive evaluations of these skins indicated structural I Anaheim, Calif., Apr. 19-27, 1971, AlAA Paper 77-388. 14 p. 15 soundness. Simultaneously with skin manufacture, two honeycornb- refs Members, $1.50. nonmembers, $2 00 beam-rib subassemblies were built. The skins were adhesively bonded The dvnamics and aeroelastics of rotating machinery are tn the substructure and the two stabilizers were available for static characterized as highly nonconservative systems whose matrix and fatigue tests. One stabilizer was successfully tested for all mission dynamic equations are typically linear and nonsymmetrical. Three profiles and taken to destruction at 300 F. Failure occurred at 109% complimentary techniques are presented for improved analysis and of design ultimate load, and the fatigue tests on the other stabilizer design of such systems. The first technique systematizes the more than satisfied the F-14 loading spectrum after two lives (12,000 identification of destabilizing forces, the second analytically eval effective flight hours), F.R.L. uates partial derivatives of complex (flutter) eigenvalues with respect to system parameters; and the third provides a method for A71-25427 Composites development, fabrication and optimiiing designs of such systems constrained by dynamic con- characterization. H. F. Volk and I. C. Lewis (Union Carbide Corp.. siderations These techniques are exemplified in a minimum weight Parma Technical Center, Cleveland, Ohio). In’ Society of the Plastics design of a heicoptei rotor blade constrained by bending-torsion Industry. Annual Technical Conference, 26th. Washington. D.C.. flutter stability and favorahle frequency placements. (Author) February 9-12, 1971, Proceedings. New York. Society of the Plastics Industry. Inc., 1971, p. 20-6.1 to 20-66. A71-25355 8 The deformation and instability of a suddenly Contracts No. AF 33(615)-3113:No. AF 33(615)-68-C-1077. accelerated liquid drop. E Y. Harper, G. W. Grube (Brll Telephone This paper describes two activities which constittite a portion Of Lahoratorieq. Inc., Whippariy, N.J.), and I Dee Chang (Stanford a much larger ARPA sponsored combined Industry/Universitv University. Stanford, Calif.). Arnerlcan Institute of Aeronautics and Research Program: the repair of a representative ’Thornel’ fiber, Asrronaiitics and American Sooery of Mechanical Engineers, Struc- epoxy matrix aircraft fuselage component and the fabrication and tures, Strucrorai D ynam!cs and Materials Conference, 12th. evaluation of ‘Thornel’ flber, polysulfone and polyamide iinide Anaheim, Calif., Apr. 19-27, 7971, AlAA Paper 77-393. 7 p. 16 refs. composites. Defects developed in the fuselage component during the Members, $1.50, nonmembers, $2 00. last stage of fabrication consisted primarily of debonding Of Physical interpretdtion of rndthematical results for the transient longitudinal stringers and circumferential stiffeners from the skin and response of an initially spherical liquid droplet subject to the action were characterized by a variety of nondestructive tests. Experimental of surface tension aiid to sudden acceleration by a flow of extwnal and analytical studies indicated that the defects resulted primarily gas with uniform upstream velocity. The vibration. distortion, from thermal degradation of the adhesive and from thermal stresses instability. and disintrgiation of the droplet are described ‘IS incurred during the final heat cure of attachments to the component. functions of gas velocity aiid the Bond and Wehei numbcis. T.M. Novel repair techniques were estahlished. and the component was successfully repaired. Fabrication techniques for ‘Thornel’ fiber, polysulfone, and polyamide imide composites were estahlished. The A7 1-25400 Boron and graphite fiber market competition. shear strength of these composites was found to be identical to that William M Powers (Generdl Technologies Coip , Reston. Va.) In. of the same yarns in epoxy resins. However, the epoxy and Society of the Pldsticc Industry. Annual Technical Confeience, 26th. polyamide-imide composites failed catastrophically In shear, whereas Washington, D.C.. February 9-12, 1971, Proceedings. the polysulfone composites did not. Polysulfone composites also New Yolk, Society of the Plastics Industry. Inc.. 1971, showed no notch sensitivity. (Author) p 8-G1 to 8-G6. 19refs. Thrie currently exists a demand for boron filament but A71-25428 Design and test of a prototype graphite competition from graphite fiber could begin to affect this market in fiberlplastic fuselage component. Dennis P Hanky and S L Cross the neai futuro Boron was the fitst material to develop an important (Bell Aerospace Co , Buffalo. N.Y.) In- Society of the Plastics place for itself in advanced composites Its first big area of Industry. Annual Technical Conference, 26th. Washington. D.C., application was in aerospace and within a short period of time was February 9-12. 1971, Proceedings. New York, being tested as structural material for selected aircraft components. Society of the Plastics Industry, Inc.. 1971, p. 20-C1 to 20-CB. As a result, there exists a considerable knowledge of design data and Contracts No. AF 33(615).3110; No. AF 33(6151-68-C-1077. information on boron filament for use in military aircraft hardware. Objectives of the effort described in this paper were two-fold: to It will take approxtniately two years to develop comparable design demonstrate performance advantages of graphite fiber composite data on graphite fibers. The degree to which boron will retain its material in a representative subscale airframe fuselage structure and market share will depend on the relative prices of the two fibers to develop and apply advanced structural analysis methods. This Graphite and boron are at present about the same price (approxi- approach consisted of preliminary design studies to select the mately $300!lh but graphite has the potential to approach S25/lh configuration, followed by integrdted studies of material character Boron on the other hand is apparently restricted to a minimum of ization and structural element tests leading to final design of the $50/1b. due to the complex manufacturing process. The near term fuselage section. Discrete element analyses were extensively em markets will he mostly boron. but thereaftcr it is difficcilt to predict ployed. The fuselage structure was fahiicated by Union Carbide the indivitlual matk(3t shares as it will deprwd on the progress of Corporation and tested at Bell Aerospace Co.. Division of Textron. graphite fitlor dt!vt!~OOinl~tltsant1 innovations in boron manufacture. The test program included a series of response tests undei vatious (Author) load conditions and combinations priol to a destiuct test undei bending and shear loads. On a bending stiffness-lo density basis. the A71 -25420 First boron wmposite structural production composite shell outperformed the aluminum design by a factoi of part. G. Lubin and S. Dastin (Grumman Aerospace Corp., Bethpage, almost 3. Stiffness predictions, strains, and deflt,ctions correlated N.Y.) In: Society of the Plastics Industry, Annual Technical reasonably well with measuiements. Failure of the shell in the Conference, 26th. Washington, D.C.. February 9-12. 1971, Pro- destruct test occurred at a load 110% of the design requireinent. Thc ceedings. New York, Society of the Plastics test demonstrated a 27% lighter weight shell thdn an aliiii1iiiuil1 Industry, Inc.. 1971, p. 17-C1 to 17-C10. structure designed for the same ultimdte load Pel folllldnce ptojec Design of boron-epoxy (B/E) skins for the production F-14 full tions for the fuselage indicate a 49% potential weight savings with depth honeycornb horizontal stabilizer. The skins were optimized use of presently available ‘Thoinel’ 50s (Atithoi

344 A7 1-25474

A71-25445 Tensile instability of initially spherical bal- Center, Engineering Physics Div.. Greenbelt, Md.) and Joseph Schetz loons. Harold Alexander (Stevens Institute of Technology. Hoboken, (Virginia Polytechnic Institute. Blacksburg. Va.). AlAA Journal, VOI. N.J.). lnrwnarional Journal of Engineering Science, vol. 9. Jan. 1971, 9, Apr. 1971, p. 666-673. 24 refs. Grant No. AF AFOSR 1228-67. p. 151.162. 14 refs. Contracts No. AF 19(628)-4990; No. AF Experimental and analytical results are presented with the 19(628)-67-C-O241. objective of defining the mechanism Of liquid sheet and jet breakup Using a new elastic constitutive relation for rubber-like materials when subjected to a supersonic gas Sheam. Liquid sheets are studied previously proposed by the author, a large deformation analysis of with photomicrographs and high-speed movies of the activity of a the inflation of rotationally symmetric balloons is developed and liquid layer maintained upon a porous Plate test model in a parallel specialized to the inflation of an initially spherical balloon. An Mach 2.2 freestream. Tests with several different liquids show wave investigation of the pressure vs radius characteristic reveals the motion, with droplet and ligament shedding across the liquid surface. existence of a local maximum indicating the occurrence of a tensile Numerical results from a liquid surface stability analysis are used to instability. Observing the form of the total potential energy function explain these observations. Liquid kts are studied with spark at various equilibrium positions yields much insight into the tensile shadowgraphs, high-speed movies and Photomicrographs of the instability phenomenon. An analogy to snap-through buckling is normal injection of various liquids into a Mach 2.1 freestream. The recognized and discussed in detail. Inflation experiments performed results show that the breakup mechanism is characterized by gross jet with neoprene balloons are found to verify the analytically obtained fracture, as opposed to Surface disintegration. The degree of breakup results. Bifurcations to nonspherical modes in the unstable region, at a given streamwise location and jet spread after injection are found previously investigated by V. 1. Feodos'ev by performing a perturba- to be related to injection diameter anddynamic pressure, and certain tion on the homogeneously deformed nonlinear state, are experi- liquid properties. (Author) mentally observed and verified. (Author)

A71-25472 #f An experimental investigation of the inter- A71-25453 k' Coupled nongray radiating flows about long action between a transverse sonic jet and a hypersonic sheilm. V. blunt bodies. Linwood B. Callis (NASA, Langley Research Center, Zakkay. W. Calarese, and L. Sake11 (New York University. Bronx, Hypersonic Vehicles Div., Hampton, Va.). (American lnsrirure of N.Y.). AlAA Journal, vol. 9. Apr. 1971, p. 674-682. 14 refs. Aeronautics and Asrronautics. Thermophysics Conference, 5th. Los Contract No. AF 33(615)-68C-1184. Angeles, Calif., June 29-July 1, 1970, Paper 70-865.)AIAA Journal, Study of the interaction Of an Underexpanded jet with a vol. 9. Apr. 1971, p. 553-559. 22 refs. hypersonic stream. The investigation includes an experimental study Second-order time asymptotic solutions, extending far down- of a finite-span sonic jet on a 7 deg semivertex angle sharp cone in a stream, are presented for hypervelocity blunt-body flow fields in- Mach number 5.8 stream. A range Of Unit Reynolds numbers of ciuding coupied r~oiit~iayia&a;ion. Sky- censidered are parabolas. 2,000,000 to 40.000.000/ft is covered in the experiments, producing spherecones, and blunted conical shapes with continuous curvature. laminar, transitional. and iuiiy ruilukni bouiidaiy :sye;s on rhe Numerical calculations treat the shock as a discrete surface and it is conical surface. The models are instrumented with 60-surface assumed that the flow is inviscid. nonconducting. and axisyrnrnetric. pressure taps from which data on normal force coefficients are Thermochemical equilibrium is assumed. Radiation is accounted for derived. In addition, the resultant forces are checked with a strain with an eight-step model absorption coefficient including line, band, balance. Shock-wave and streamwise patterns in the plane of and continuum radiation. Results include shock shapes, radiative symmetry of the flowfield are obtained from schlieren photographs. heating distributions, and profiles through the shock layer of perti- The experimental study is primarily intended to provide quantitative nent thermodynamic and Tow quarififiei. Aparametric mrafvsir is data on interaction forces due to the three-dimensional effects of a made sf radia?ing f!c*.:rs over spherecones Comparisons with other finite-span jet. It is observed in these experiments that the crossflow investigators are made, where possible. (Author) can produce a iavorabir liei it'stciX?:39,.*.,::h :he zaizS?'e3m, therebv providing an induced normal force Coefficient equal to or possibly A71-25469 4 Evolution of the laminar wake behind a flat exceeding the two-dimenslonal Values. at the same Mach number and plate and its upstream influence. L. I. Schneider (North American jet mass flux ratio. The experimental data show that a positive Rockwell Corp., Space Div, Downey. Calif.) and V. E. Denny normal force (lift) contribution can be obtained from the flow (California. University, Los Angeles, Calif.). AIAA Journal, vol. 9, downstream of the jet slot. Finite span fences have been tested for Apr. 1971, p. 655-660. 21 refs. comparison with jet controls. It is found that the total normal force Analysis of laminar, two-dimensional, viscous flow of an coefficient produced by the jet for which the Mach disk penetrates incompressible fluid over the trailing edge of a vanishingly thin flat the flowfield to the same height as the fence is much larger than that plate. A coordinate transformation is introduced which admits produced by the fence. (Author) sufficient scaling of the problem to enable detailed study of the separating flow and its interactions with the inviscid stream, as well as with a presumed boundary-layer flow in an intermediate region. Second-order boundary4ayer theory is applied in an iterative manner A71-25474 # A lifting-surface solution for vortex-induced to extract a first approximation to the displacement thickness and airloads. Wayne Johnson (U.S. Army, Aeronautical Research Labora- associated induced pressure distribution. It is found that the tory, Ames Research Center, Moffett Field, Calif.). AlAA Journal, near-wake region is nonisobaric, the classical isobaric result of vol. 9, Apr. 1971, p. 689-695. 13 refs. Grant No. NGR-22-009-303. Blasius-Goldstein for displacement thickness being slightly high just Planar lifting-surface theory IS applied to the problem of the prior to the trailing edCe and about 10% low downstream. Local loads induced on an infinite aspect-ratio wing by a straight infinite, corrections to the velocity and pressure distributions are obtained by free vortex in a subsonic. compressible. freestream; the vortex lies in numerically solving the full Navier-Stokes equations, using the a plane parallel to the plane of the wing, at a given distance below it, second-order boundary-layer results to establish Dirichlet boundary and at an arbitrary angle with the wing centerline. The solution is conditions over a rectangular region enclosing the trailing edge point. obtained in the form of an aerodynamic influence function for an It is found that the physical extent of this region is of order R to the infinite aspect-ratio wing in an obltque, sinusoidal gust. The minus 3/4. Within the region. shear at the plate increases with x and lifting-surface theory kernel function for this wing is presented. This becomes very large at the trailing edge. No significant correction to kernel includes as limits the linear. aeiodynamic kernel functions for the displacement thickness was found on resolving the second-order the problems of steady. three-dimensional flow and unsteady, boundary-layer problem, using the Navier-Stokes results as inner two-dimensional flow, and for the problems of incompressible. boundary conditions. (Author) two-dimensional flow and transonic, three-dimensional flow. An approximate analytic expression is given for the lift influence A71-25471 // Breakup of liquid sheets and jets in a super- function. suitable for practical use in the routine calculation of sonic gas stream. Allan Sherman (NASA. Goddard Space Flight vortex-induced airloads. (Author)

345 A7 1-25475

A71-25475 # Experimental investigation of the stability of VOI. 9, Apr. 1971, p. 733-736. Grant No. DA-HC-04-69C-0084. the laminar supersonic cone wake. Deiinis K. McLaughlin (Oklahoma Investigation of the effects of curvature on the freejet boundary State University. Stillwater, Okla ). AlAA Journal, vol. 9, Apr. 1971, between a curved irrotational flow and a stagnant fluid. It IS shown p. 696-702. 18 refs. Contract No. AF 44(620)-C-O013. that similar solutions are possible in both the laminar and turbulent Investigation of the instability occurring in the wake of a 7 deg cases for certain variations of jet curvature, provided the curvature is half-angle, sharp cone suspended magnetically. Hot-wire fluctuation moderate. In fact, for both the laminar and turbulent cases, the measurements were made in the wake for a range of Reynolds equations of motion can be reduced to a single ordinary differential numbers and at a Mach number 4.3. These measurements indicated a equation, the Solutinn ydhic!: is givcz. The iejiiltj of this j01iii;Gn compieieiy srdbie near wake at a freestream Reynolds number of indicate that the velocity profile within the freejet boundary is. for 51,600 and large amplification of small disturbances at a freestream all practical purposes, independent of the curvature. The effects of Reynolds number of 61,900. The amplified waves were highly the pressure across the freejet boundary on the curvature and on the concentrated with respect to frequency, with a number of pro- entrainment are determined. M.M. nounced harmonics being present. Amplitude and phase measurements of the spectral components indicated that the instability process fits within the framework of linear stability theory as A71-25487 # Lift and drag of a wing-cone configuration in formulated by Gold, with each mode having a wavefront shaped like hypersonic flow. Adolfo Reggiori (New York University. New York. a circular helix. It appears that each succeeding mode has an N.Y ). AlAA Journal, vol. 9, Apr. 1971, p. 744, 745. additional thread in the helical wavefront. However, the measured Measurement of the pressure distribution and total forces on a fundamental oscillation has a lar~jeramplification rate and a much reentry-vehicle configuration consisting of a 20-deg cone with wings lower frequency than predicted by Gold’s theory. In addition, weak located at 60 deg from the plane of iyiiirriatry and a sweep-back nonlinear interactions were observed, which grow stronger with angle of 75 deg. Measurements were taken at Mach 5.8 for several downstream position. (Author) angles of attack between -16 and +20 deg The leading edge of the wing was subsonic. Lift and drag coefficients determined from the pressure distribution and directly from balance measurements are A71-25476 ,# Results of a strong interaction, wake-like compared to those obtained with an isolated cone. A large increase in model of supersonic separated and reattaching turbulent flows. Louis lift is obtained with a negative dihedral configuration, while a G. Hunter, Jr. (Avco Corp., Avco Systems Div.. Wilmington. Mass.) positive dihedral configuration gives orily a srndll increase in lift as and Barry L. Reeves. (American Institute of Aeronautics and compared to the isolated cone. T.M. Astronautics, Aerospace Sciences Meeting, 9th. New York. N.Y., Jan. 25-27, 1971, Paper 71-128.) AlAA Journal, vol. 9. Apr. 1971, p. A7125490 // Inclination of pressure orifices in low-density 703-712. 30 refs. flow. K. Kienappel (Aerodynamische Versuchsanstalt, Gottingen, Results of an interaction theory for supersonic separated and West Germany). AIAA Journal, vol. 9. Apr. 1971, p. 749, 750. 7 reattachinq turbulent boundary layers are presented and compared with recent experimcnts for flow past a compression ramp. Effects of refs. The inclination of the orifice venting a cavity to surface rarefied ramp angle. Mach number. Rt:ynoldc numbei, and upstream pressure gas flow is shown to affect the pressure in the cavity. Experiments qradient are considercid foi situatioiis wheir the critical point is were peiformed with a cooled flat plate model in a hypersonic located upstream of the tidiling edge. When the critical point falls low-density wind tunnel. Holes were drilled perpendicularly to the downstream of the trailing edge the whole region of separated flow is model surface and at angles between 30 and 80 deg to the leading influenced by ramp length. In these ‘short ramp’ flows the peak ramp edge. Graphs show measured pressures (normalized with local pressure attains a maximum at a critical ramp angle and then reference pressures) as a function of the angle of inclination and the decreases with increasing angle. It is shown that this effect is gas density. T.M. responsible for the spanwise pressure distributions measured by Whitehead and Keyes for flow over a delta wing with a trailing edge flap. Results are also presented for a turbulent boundary layer shock A71-25492 18 Safety factors and the probability of failure in wave interaction. (Author) fatigue, M. P. Bieniek (Columbia Univcrsity, New York. N Y.) and J. C. Jodnides (North Ameiican Rockwell Corp.. Downey, Calif ) A71-25477 ir Aerodynamic characteristics of a slender body AlAA Journal, vol 9, Apr. 1971, p. 753, 754. 5 refs. traveling in a tube. Theodoie R. Goodman (Oceanics. Inc.. Plainview, A piobabilistic model of fatigue failure under variable~amplitude N Y.). AlAA Journal, vol. 9. Apr. 1971, p. 712-717. 6refs. Research loading is used to esiablish a relation between the safety factor K and supported by the U S. Department of Commerce. the fatigue failure probability. The relation appears to be of definite lncompiessible inviscid slender-body theory is applied to deter- significance in selecting rational values of the safety factor. It may mine the flow about a slender body of revolution traveling in a tube also be useful in planning the inspection, maintenance, and replace Formulas for all the static and dynamic statiility derivatives are ment for a fleet of aircraft. T.M. derived foi an arbitrary body of revoiution in terms of its cross sectional aiea distribution These formulas are specialized to an A71-25494 * # Laminar incompressible flow past a ellipsoid uf revalution as an illuctrative example and plots of the circulation-controlled circular lifting rotor. Allen Plotkin (Maryland, results are presented as a function of the ratio of the maximum University, College Park, Md.). AlAA Journal, vol. 9. Apr. 1971, p. cross-sectional area of the body to the area of the tube. For the body 756-758. 8 refs. Grants No. NsG-398; No. NGR-21-002-266. whose diamc!tei is a large per cent of the tube diameter, the stability Prandtl‘s first-order boundary layer equations !or two- derivatives becoinc: an order of magnitude greater thm they are for dimensional, laminar, incompressible flow past a circulation- the Sam(> body ir, free air Furtheinrore, a staticdlly unstatile force of controlled circular lifting rotor are solved numerically using the dttractioii to the wall caused by proximity to thr wall is present implicit finite difference scheme of Blottner and Flugge Lot2 (1963). which does not exi5t ‘it all for the body in free air. The inherent The laminar theory shows that the momentum coefficient is an aerodynamic iiistdI?ility of a body in free air without controls is thus appropriate jet parameter for moderate values of h/R, where h is the incrcdscd by the pieseiice of the tube wdlk, and the walls may be slot height and R is the cylinder radius. For large values of h/R, the said to exert a Iaigc effect on the aerodynamic characteristics of the ratio of the speeds of the uniform stream and the jet becomes the body (Author) appropriate parameter. T.M.

A71-25482 6 Curvature effects in the laminar and turbulent A71-25521 P Disintegration of a supersonic jet impinging freejet bour,dary. James C Williams. Ill, Eddy H. Cheng. and Kun H. normally on a flat plate. T. Nakatogawa. M. Hirata (Tokyo, Kim (Noith Carolina State University, Raleigh, N.C ) AlAA Journal, University. Tokyo, Japan), and Y. Kukita. Journal of Spacecraft and

346 A71 -25802

Rockets, vol. 6. Api 1971, p. 410, 411. Description of the selection and development of recommended Previotrs studies of the structule of a supersonic freejet in system concepts. Tentative requirements are derived from opera- relation to let noise revealed that in the case of a highly tional considerations pertaining to airports, aircraft, approach and undei expanded ft eejet, veiy strong directional sound called screech is landing paths, classes of service. failure protection, weather penetra- generated and that disintegration of the jet occurs at the same time tion, and physical interference. The technique assessment procedures It is proved that, for the case of a supersonic jet of almost correct used in the technical and economic reviewing of proposals and in expansion impinging not nially on a flat surface, similar disintegtation reaching conclusions are outlined, and the description of the selected also occuis with strong screech when the normal shock wa\e in front and proposed concept dwells particularly on the capabilities of the of the flat surface is in a decelerating region of the jet. OH system with respect to rollout, missed approach, departure guidance, obstacle clearance, identification, status dara transmission, modulation techniques, and approach and landing guidance. The provisional ~71.25525 t; Performance of diskqap-band. ringsail. and standard signal formats recommended are covered in great detail. cross parachutes at low earth altitudes. Harold N. Murrow and M.V.E. Clinton V. Eckstrom (NASA, Langley Research Center, Hampton, Va.). (American Institute of Aeronautics and Astronautics, Aero- dynamic Deceleration Systems Conference, Dayton, Ohio, Sept. A71-25555 # A status review of Lewis Research Center 14-16. 1970. Paper 707 164.) Journal of Spacecraft and Rockets, supported protection system development. S. J. Grisaffe, J. P. VOI.8, Apr. 1971, p. 418-420. 6 refs. Merutka (NASA, Lewis Research Center, Cleveland, Ohio), and S. R. Evaluation of the performance of the Attached Inflatable Levine (NASA, Lewis Research Center; U.S. Army. Air Mobility Research and Development Laboratory, Cleveland, NASA and Decelerator (AID) - i.e., a low-mass, ram-air inflatable fabric canopy Ohio). configured to the payload . designed for decelerating interplanetary U.S. Air Force, Refractory Composite Working Group Meting, 18th, vehicles during their entry into low-density atmospheres, such as that Marshall Space Flight Center, Huntsville, Ala.. Mar. 16-18, 1971. of Mars. Wind tunnel data for models 5 ft in diameter attached to a Paper. 12 p. 120 deg conical aeroshell, which utilize mechanically deployed Lewis Research Center - sponsored coating development for ram-air inlets to initiate canopy inflation, are examined. Four models superalloys has produced several promising systems including vapor were successfully deployed at supersonic speeds. The models were deposited CoCrAlY coatings, alumina enriched aluminide coatings very stable throughout the Mach number range 2.0 to 4.75 and at and metallic claddings. Efforts to minimize the interdiffusion of angles of attack through 10 deg and had a high drag coefficient. dispersion strengthened materials and protection systems have shown Calculated canopy inflation rates which account for permeability of only modest success. Fused slurry silicide coatings for columbium the material are shown to be in good agreement with experimental reentry hardware are being optimized while process development and values. A mission study performed demonstrated the advantage of scale-up are underway. Several promising fused slurry silicide the AID as the first stage of a two-stage deceleration system. coatings have been developed fnr :m%!sn resntry hardware. Calculation indicates that The A!!? :elaxes sii ingent deployment (Author) conditions on the terminal parachute. O.H. A71-25652 Aerospace applications. M. A. Denney (British Aircraft Corp., Ltd., Weybridge, Surrey, England). In: Glass re A71-25527 P Ground and flight test results for a decelerator inforced plastics. Edited by Brian Parkyn. towline energy absorber. Ross L. Goble and Earl L. Councill, Jr. London, Iliffe Books, Ltd.. 1970, p. 94-105. (NASA, Langley Research Center, Hampton, Va.). /American Applications of GRP in single-skin, wall, and sandwich radomes, Institute of Aeronautics and Astronautics, Aerodynamic Decelera- dielectric panels, and aircraft ducting are reviewed. Production

tion Systems Conference, Dayton, Ohio, Sept. 14- 16, 1970, Paper techniqiupz *-?r rx!zn-.s >: rai;~~5&,iyns are described with Hycar 70-1202.).^^ Journal of Spacecraftwd Pn~kers,"3;. 8. Apr. 1971, p. sandwich structures, fluted-core radomes of Bristol Aircraft, the ULJ-Y~~.5 refs. Concorde radome, the Avro Shackleton radome, and Vickers A test program was conducted to verify the shock attenuation Vanguard and Valiant radomes referred to as examples. The characteristics of a decelerator towline energy absorber for the secondary structures in which GRP are used are listed as fairings, Supersonic High Altitude Planetary Entry Program (SHAPE). electrical distribution panels, propeller spinners, tank platings, Ground-based drop tests were performed to simulate opening passenger cabin furnishings, and freight bay linings. The less frequent parachute shock load and sustained aerodynamic load subsequent to applications in molding and tooling are also covered. V.Z. opening shock. The absorber, although constrained in size by payload canister packaging volume, was found to be effective in A7125661 Effect of changing wing weep on the limiting shock load through energy dissipation by the damper dynamics of the controlled processes. B. N. Petrov, Zh. S. Ageev. B. constituents. Helicopter drop-test data and actual flightdecelerator V. Viktorov, and I. S. Ukolov. (Akademiia Nauk SSSR, Izvestiia, load time histories with the absorber in the system are provided. Tekhnicheskaia Kihernetika, May-June 1970. p. 190-195.) Engineer- (Author) ing Cybernetics, vol. 8, May-June 1970, p. 604-609. Translation. A71-25528 3 A shielded fine-wire probe for rapid measure- Description of a mathematical model for the dynamics of the ment of total temperature in high-speed flows. Leonard M. Weinstein angular motion of a variable geometry (variable wing sweep) aircraft (NASA. Langley Research Center, Aero-Physics Div., Hampton. Va.). treated as a variable mechanical system w,ith specified relative Journal of Spacecraftand Rockets, vol. 8, Apr. 1971, p. 425-428. 12 motions of its elements. Differential equations of angular motion are refs. derived, and an approximate analysis is made for the influence of A probe developed to satisfy the test requirements for a inertial moments on the dynamic properties of the aircraft as a hypersonic helium facility having a 4 to 6 sec run time is described. control plant. Using a hypothetical aircraft as an example, it is shown The probe can survey across a 1-in. hypersonic boundary layer in that the mechanical aspects of sweep variation have little influence approximately 2 sec, generally gives better than 114% absolute on the transient processes in the course and pitch control channels. accuracy in the reduced data, and is useful for freestream Mach In the roll control channel, the inertial components have a very numbers greater than 1, Knudsen numbers less or equal to 0.3,and strong influence on the damping properties. It is concluded that roll control in these circumstances should be primarily carried out by an for total temperature less than 700 R. O.H. autopilot. T.M.

A71-25534 fi A new guidance system for approach and A7125802 fi Determination of threedimensional density landing. Volume 2. Washington, D.C., Radio Technical Commission fields from holographic interferograms. Robert D. Matulka and for Aeronautics (Document No. DO-148). 1970. 396 p. $20. Daniel J. Collins (U.S. Naval Postgraduate School, Monterey, Calif.).

347 A71 -25847

JourtialofApp/iedPhysics, vol.42,Mar. 1. 1971.p.11091119.12 meridional plane solution using a quasi-orthogonal coordinate refs. Navy-supported research. system. The flow condition on these surfaces of revolution and the The successful application of holographic interferometry, and an result. The agreement appears to be very good. Some preliminary associated mathematical reduction process, to the determination of results are presented for a flow containing an oblique shock and its an asymmetric three-dimensional density field of an aerodynamic reflection. The computed rewlts compare satisfactorily with the phenomenon is reported. An integral inversion method from the field exact solution. (Author) of plasma physics has been extensively evaluated by applying it to the determination of functions, both axisymmetric and asymmetric, A71-25950 # The radiation of sound from an airfoil which simulate aerodynamic density fields. The application of immersed in a laminar flow. L. T. Clark (Boeing Co., Commercial hoiogrdp1,ic inter!eromPtrv has been extended to provide multiple Airplane Group, Seattle, Wash 1. AmericatJ Society of Mechanical holograms about a test region, with sufficient coverage io pio:.ide Engineers, Gas Turbine Conference and Products Show, Houston, interferometric data for the successful solution of the density field. Tex., Mar. 28-Apr. I, i97i, hpei 7! GT-4. 11 p. 7 refs. Members, The analytical and experimental methods developed were applied to $1 00. nonmembers, $2.00, an experimental axisymmetric test field, the supersonic flow from a The results of an experimental and analytical investigation of free jet. and shown to be comparable to a previous solution obtained sound generation by single airfoils are presented. Airfoil sections by the Ahel inversion method. Further, the free jet was tilted to studied were representative of those used in modern axial com- provide a test field which was asymmetric in the plane of solution. pressors, included were modified 65 series and double circular arc Conipaiison of the resulting asymmetric solution was shown to be profiles. The radiation of sound from the airfoil immersed in the consistent with the previously obtained axisymmetric solution. potential core of a free jet discharging through an acoustic chamber (Author) was measured, Acoustic data were obtained for the velocity range 200 through 800 ft/sec. Measurements of wake correlation volumes and turbulence velocity components were used in an analytical A7 1-25847 Application of a hybrid computer to the model to predict the spectrum of the sound radiated by the airfoil development of a pilotless captive helicopter (Einsatz eines Hy- Sound generation was found to be dependent upon the quare of the bridrechners bei der Entwicklung eines unbemannten, gefesselten component of turbulent velocity normal to the airfoil chord. In the Hubschraubers). G Schmidt, R. Swik, W. Dusold, and A. Kuechle velocity range 300 to 800 ft/sec, the overall sound pressure level was (Dornier AG, Friedrichshafen, West Germany). In: Association found to be dependent upon free stream velocity to the sixth power Internationale pour le Calcul Analogique and International Federa- A correlation of the normal component of tu;bulent velocity was tion for Information Processing, Conference on Hybiid Computa- found to exist with the momentum thickness of the wake. (Author) tion, Munich, West Germany, August 31-September 4, 1970, Proceedings. Brussels, Presses Academiques A71-25953 # Shock wave behavior in transonic compressor Europknnes, 1970, p. 280-289. In German. noise generation. M. R Fink. American Society of Mechanical A complex real-time simulator is described which was developed Engineers, Gas Turbine Conference and Products Show, Hoiiston, for solving dynamic problems of a captive two-blade rotor platform Tex.. Mar. 28-Apr. I, 1971, Paper 71.GT-7. 7 p. 12 refs. Members. (termed DO 32.K) intended for reconnaissance purposes. Of $1 00, nonmemhers. $2.00. particular interest was the determination of the influence of the Compressor noise at transoilic tip speeds contains strong tones mooring cable (which also served for fuel supply and data trans- at multiples of shaft rotation frequency as well as harmonics of blade mitsion), the rotor, and the turbine unit on the dynamic charac- passage frequency These multiple pure tones or cornhination tones teristics of the entire system and whethei- satisfactory stabilization are caused by rotor blade nonuniforinities which result in could be accomplished with standard flight control equipment. The pronounced irregulaiities in the shock pattern attached to the rotor. mathematical model, block diagram. and signal flow diagrams of the Nonlinear first order theory, similar to that used in analysis of sonic simulator are presented and discussed. V.P. boom strength, is utilized to determine shock wave decay with upstream distance. In the extreme near field of the rotor, shock strength varies inversely as the square root of upstream distance from A71-25852 An application of hybrid computing to design the blade leading edge as with an isolated airfoil. Somewhat further and training. Frank E. Oldfield and Philip J. Wall (Teledyne Ryan upstream, the expansion region from the neighboring blade in the Aeronautical Co , San Diego, Calif.). In: Association Internationale cascade interacts with the shock so that shock strength varies as the pour le Calcul Analogique and International Federation for Infoima inverse first powrr of distance. These aerodynamic results are used to tion Processing, Conference on Hybrid Computation, Munich, West infer some characteristics of transonic compressoi noise whirh in Germany, August 31 -September 4, 1970, Proceedings. turn are compared with experimental results. (Author) Rrussels, Presses Academiques Europeennes, 1970, p. 628-636. Description of a six-degree-of-freedomdigital computer program A71-25958 # Discrete frequency noise from lifting fans. A. written to evaluate a complex flight control system and associated N. Abdelhamid (Carleton University. Ottawa, Canada). American control mode logic. Air launch separations from the launch aircraft Society of Mechanical Engineers, Gas Turbine Conference and were successful, and ground launch was demonstrated successfully, as Products Show, Houston, Tex, Mar. 28-Apr 1, 1971, Paper well as supersonic flight. All flight control modes were successfully 77-GT-12. 10 p. 10 refs Members, $1 00, nonmembeis, 92.00. engaged and flown. To date, six radio control operators (RCOs) were Research supported by the National Reseaich Council of Canada. trained on the simulator, and all have conducted successful flights. Disciete frequency noise charactei istics of a iesearch lifting fdn ale investigated analytically. Based oil steady aeiodynainic data of F.R.L. the fan, unsteady aerodynamic foices acting on the iotor dnd statoi A71-25948 An analysis of flow through a mixed flow blades were calculated using the resiilts of pievious investigators did impeller. Yasutoshi Senoo and Yoshiyuki Nakase (Kyushu Uni- an analysis which deteimines the effect of fluctuating velocity versity, Fukuoka. Japan). American Society of Mechanical Engineers, disturbance pardllel to blade choid on the unsteady lift of cainbciud Gas Turbine Conference and Products Show, Houston, Tex., Mar. thin airfoils. The calculated unsteady foices weie then ustxl to 28-Apr. 1, 1971, Paper 71-GT-2. 8 p. 9 refs. Members, $1.00; determine the characteristics of disciete fiequc’iicy inoise eiilissioil nonmembers. $2.00. from the fan Foi the fan undei consideratioil 11 is shown thdt thi, In this report, a method of analyzing steady. three-dimensional, iotor intoaction noise dominates the f,in iioistt. Coinp‘ii ison Iietwwii subsonic. nonviscoiis flow through a turbomachine with arbitrary the predicted sound pressuie levels and expci iiii(~iit;iI ol)st~v,itioils hub and shroud shapes and with a finite number of blades is shows good agreeincnt Based on thti c,ilculat(d dvt~iilidcoiiti iliu presented. In order to make the analysis manageable, the stream tioiis of the diffeieiit foicv hai iinoiiics actiiig oil thi, l)lci(li~\IO thii fdii surfaces are assumed to be axisymmetric Position and shape of these noise, possible means of ieduciiig lifting fdn inoisc ‘lit, (iiwtiw>(I surfaces, which depend upon the work of blades, are obtained by a (Autlwi1

348 A71-25966

A71-25959 b’ Performance of compressor blade rows in a In this report a method of analyzing subsonic inviscid flow sloping flowpath. H. A. Harmon, A. A. Mikolajczak, and D. Marchant between blades on a stream surface of revolution of a turbomachine. (United Aircraft Corp., Pratt and Whitney Aircraft Div., East which may be an axial, a radial, or a mixed-flow type, is presented. Hartford, Conn.). American Society of Mechanical Engineers, Gas There may be a change in thickness of stream surface of revolution in Turbine Conference and Products Show, Houston, Tex., Mar. the through fhw direction. The stream surface of revolution is 28-Apr. 1, 1971, Paper 71-GT-13. 8 p. 15 refs. Members. $1.00; mapped onto a plane. In this picture plane the influence of rotation nonmembers, $2.00. Research sponsored by the United Aircraft of the system is not always represented by unifoimly distributed Corp. vorticity. Instead. the distribution of vorticity varies with radius. For In an effort to reduce engine length and weight it is desirable in the calculation of velocity distribution in the picture plane, an some applications, such a5 high bypass ratio turbofan engines, to available rotating annular cascade theory is modified so that the introduce compressor stages into a downward sloping flowpath. In variation of vorticity with respect to radius IS properly considered. this ‘mixed flow’ compressor the airfoil orientation with respect to Numerical examples for a mixed flow type comptessor rotor are included. (Author) the flowpath becomes important to ensure good performance. The performance of cascades and compressor stages with sloping walls is presented. Three methods of introducing blading into the flowpath were evaluated. It is shown that by canting the blading to be normal A71-25963 it Heat transfer to an airfoil in oscillating flow. J. to the flow direction, no penalty in performance is incurred A. Miller and P. F. Pucci (US. Naval Postgraduate School, Monterey, compared to the performance of a typical axial compressor with Calif.). American Society of Mechanical Engineers, Gas Turbine cylindrical flowpath. Test results are compared with predictions Conference and Products Show, Houston, Tex.. Mar. 28-Apr. I, based on intrablade analysis and a wall boundary layer calculation. 1971, Paper 71-GT-18. 8 p. 7 refs. Members, $1.00; nonmembers, Qualitatively pod agreement is obtained except for the case when $2.00. Navy-supported research. the blading is swept with respect to the flow direction. Need for Local heat transfer coefficients to an airfoil in an oscillating further investigation of three dimensional internal viscous flows is stream have been measured for a range of frequencies and oscillation indicated. (Author) amplitudes. Results at moderate angles of attack are in agreement with previously reported findings. However, at large angles of attack, including those associated with stall in steady flow, a strong periodic A71-25960 Y Experimental investigation of methods for starting vortex shed from the leading edge leads to a dramatic improving the dynamic response of a twin-spool turbojet engine. A. reattachment of the flow and consequent increase in local Nusselt J. Fawke (Gas Council, Newcastle, England) and H. I. H. numbers of as much as five-fold. These effects are shown to be Saravanamuttoo (Carleton University. Ottawa, Canada). American amplified by increasing oscillation frequency and amplitude. Society of Mechanical Engineers. Gas Turbine Conference and (Author) P-ciducis Sha.v, HOU$~UII,Tex., Mar. 2E-Apr. i. i9i i, Paper 77-GT-14. 7 p. Members. $1.00; nonmembers, $2.00. Research A71-45964 f/ Analytical and experimental studies of supported by the Science Research Council. two- dimensional flows in a radial bladed impeller. R. S. Benson, W. G. This paper describes experimental tests carried out on a Cartwright, and M. J. Hill (Manchester, University. Manchester, twin-spool turbojet to confirm earlier simulator predictions of England). American Society of Mechanical Engineers, Gas Turbine methods of improving the dynamic response. The engine was controlled by a digital computer, permitting ready changes of control Conference and Products Show, Houston, Tex., Mar. 28-Apr. 7, 1971, Paper 71-GT-20. 12 p. 16 refs. Members, $1.00. nonmembers, schedules. It was verified that dynamic response could be improved s2.00. by trading HP surge margin for LP surge margin by suitable variation Numerical direct solutions are dprived nrl the haciz nf the + :he .,-711c _..”_~~~- n,v~L,u~~,~~ . . .140Lcctur~c~ ’ . wete uui.iiid ut! Loti1 potential theory to determine twodimensional flows in radial compressor characteristics during both accelerations and decelera- turbomachines under both on- and off-design conditions. A rotating tions and excellent agreement with simulator results was obtained. cascade rig with a horizontal rotor mounted in an open circular water (Author) tank is used in experiments to obtain water circulation with radial inflow or outflow by the motion of the rotor at rates up to 300 rpm. A71-25961 it Measured and predicted flow near the exit of a A camera with a 12-channel flash unit is used for flow visualization radial-flow impeller. G. E. McDonald, J. H. G. Howard (Waterloo. by photographic observations of polystyrene particles suspended in University, Waterloo. Ontario, Canada), and E. Lennemann (IBM the flow. The experimental and analytical results for a straight vaned Deutschland, Boblingen, West Germany). American Society of constant-area rotor are compared. V.Z. Mechanical Engineers, Gas Turbine Conference and Products Show, Houston, Tex., Mar. 28-Apr. 1, 1971, Paper 71-GT-15. 6 p. 12 refs. A71-25965 # Design considerations in inertia welding of Members, $1 .OO; nonmembers, $2 00. Defence Research Board of turbocharger and gas turbine components. C. D. Weiss, Moen, Canada Grant No. 9550-19. L. J. and W. M. Hallen (Caterpillar Tractor Peoria, Ill.). American Experimental measurements are presented of the velocity field Co.. Society of Mechanical Engineers, Gas Turbine Conference and near the exit of a radial impeller with backwardcurved blades. The Products Show, Houston, Tex., Mar. 28-Apr. 1. 1971, Paper flow pattern, and its variation with changes in the flow coefficient 71-GT-21. 7 p. Members, $1.00; nonmembers, $2.00. are compared with numerical predictions on a blade-to-blade plane. The welding of low alloy steels and wrought superalloys to cast The theoretical flow prediction method assumes inviscid flow, is superalloys of special relevance to the gas turbine field is discussed. essentially two-dlmensionai and is based on the streamline curvature The inertia welding process is described, and i! is shown that its approach. It does not specifically require the condition of zero applicability extends to many combinations of iron, nickel, and absolute vorticity. The comparison with experiment Indicates that cobalt base superalloys and steels for gas turbine and supercharger the principal feature of the flow not accounted for in the inviscid construction. Weldable combinations are listed, and mathematical model is the region of low velocity near mid-blade height on the formulas are given that make it possible to calculate the parameters suction surface, especially for higher blade loadings. (Author) required for inertia welds. The tensile and stress rupture properties of inertia welds at various temperatures are tabulated, and their A71-25962 $ A blade theory of an impeller with an ar- microstructure is illustrated and discussed. Various prerequisites to bitrary surface of revolution. Yasutoshi Senoo and Yoshiyuki Nakase sound welds are reviewed and precautions to be observed set forth. (Kyushu University. Fukuoka. Japan). American Society of Mechani- M.V.E. cal Engineers, Gas Turbine Conference and Products Show, Houston, Tex., Mar. 28-Apr. 1. 1971, Paper 71-GT-17. 7 p. 14 refs. Members, A71-25966 # A turbine-speed, main-engine furl pump. H. T. $1.00; nonmembers, $2.00. Johnson (Battelle Columbus Laboratories, Columbus, Ohlo).

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American Society of Mechanical Engineers, Gas Turbine Conference Electric Co., Lynn. Mass.). American Society of Mechanical Engi- and Products Show, Houston, Tex., Mar. 28-Apr. 1, 1971, Paper neers, Gas Turbine Conference and Products Show, Houston, Tex., 71-GT-24. 8 p. Members, $1.00; nonmembers, $2.00. Grant No. Mar. 28-Apr. 1, 1971, Paper 71-GT-38. 6 p. Members, $1.00; DA-AJ-02-69-C-0072. nonmembers, $2.00. This paper describes the design and experimental evaluation of a Low pressure drop fuel injectors for jet engine combustors are vane-type fuel pump that has operated successfully at speeds up to currently being considered. In this respect, the general problem 49,500 rpm and outlet pressures up to 900 psig. The objective of the considered in this paper is the flow variables affecting the distribu. research was to produce a main-engine fuel pump for small tion of a low pressure drop, low velocity stream of liquid which is .. gas-turbine engines capabie of operaiiriy di engofie shaft speed in convected by a ~oncen:iic ;;:~;:~~:~qi:nst a coflci?'e hemispheriral order to reduce the bulk and complexity of the required gear drive cap similar to possible fuel injectors designs. Experimental results train. The pump has a design JP-4 turbine-fuel flow rate of 2000 from a plexiglass model of the injection system are presented. The Ib/hr at 650 psig. The successful completion of a 200-hr endurance experimental results indicate that for a centrally located liquid run has verified that the high-speed capabilities have been achieved stream injector (less than 1/16 in. from the true center). the without sacrificing pump endurance life. (Author) momentum ratio between the liquid and airstreams is the predominant factor which influences uniform fuel distributions. More uniform distributions are obteined with higher liquid-to-air momen- A71-25967 Effects of Reynolds number on performance H tum ratios. For larger injector eccentricities. the liquid distributions characteristics of a centrifugal compressor. Toshio Mashimo, lchiro exhibit variable tendencies depending on the range of the momentum Ariga, lchiro Watanabe (Keio University, Tokyo, Japan), and Hiroshi ratio. (Author) Suefusa. American Society of Mechanical Engineers, Gas Turbine Conference and Products Show, Houston. Tex., Mar. 28-Apr. 1, 1971, Paper 71-GT-25. 12 p. 16 refs. Members, $1.00; nonmembers, A71-25973 # Investigation concerning the fluid flow in the $2.00. Research supported by the Mitsui Shipbuilding and Engineer- mixed-flow diffuser. Shinji Honami, Toshimichi Sakai (Tokyo ing Co. Institute of Science, Tokyo, Japan), lchiro Watanabe (Keio Uni- The pressure was varied from 0.25 to 1 atm in the surge tank by versity, Tokyo, Japan), and Keiro Tsukagoshi. American Society of a vacuum pump to vary the Reynolds number in a closed system Mechanical Engineers, Gas Turbine Conference and Products Show, used in a study of the peiformance of a centrifugal compressor with Houston. Tex., Mar. 28-Apr. 1, 7971, Paper 71-GT-40. 9 p. 13 refs. a single-shroud impeller having straight radial blades and a parallel- Members, $1 .OO; nonmembers, $2.00, walled vaneless diffuser. The power losses in the compressor, impeller Velocity profile measurements were performed on the flow in a and diffuser stages of the system were determined and the adiabatic mixed-flow diffuser with walls having equal cone angles. The aim of efficiency of the compressor vs the flow rates was analyzed. The the present study IS to understand the flow behavior and the relation critical Reynolds numbeis were from 0.09M to 0.13M for the between the flow patterns and the diffuser losses. The boundary compressor stage, from 0.09M to 0.12M for the impeller, and from layer flow accompanied by separation on the inner wall and the 0.09M to 0.15M for the diffuser. V.Z. velocity normal to the diffuser walls were measured in detail to examine the three-dimensional flow behavior in the mixed-flow diffuser. Comparing with the radial diffuser, the mixed-flow diffuser A71-25970 // Inertia welded jet engine components. K. W. had a more complicated flow mechanism as it had the pressure Stalker and C P. Jahnke IGE Material and Process Technology gradients of transverse and normal directions. (Author) Laboratories, Cincinnati, Ohio). American Society of Mechanical Engineers, Gas Turbine Conference and Products Show, Houston. Tex., Mar. 28-Apr. 1, 1971. Paper 71-GT-33. 9 p. Members, $1.00; A71-25974 # A study on the flow pattern within the nonmembers, $2.00. centrifugal and mixed-flow impellers. Shinpei Miruki, Toshimichi The inertia welding process is discussed as a technique providing Sakai (Tokyo Institute of Science, Tokyo, Japan), and lchiro both a low weight-cost advantage and completely reproducible Watanabe (Keio University, Tokyo. Japan). American Society of excellent mechanical properties when used for joining simple disk Mechanical Engineers, Gas Turbine Conference and Products Show, and ring shapes in the fabrication of jet engine rotors This process is Houston, Tex., Mar. 28-Apr. 1, 1971, Paper 71-GT.41. 13 p. 10 refs. charactei ized as one of solid state joining which forges the two parts Members, $1 .OO; nonmembers, $2.00. together under automatically controlled conditions. The. inertia An investigation of the flow patterns within the centrifugal and welding parameteis for jet engine nickel and titanium alloys and the mixed-flow impeller channel was performed. The velocity distribu- cost and weight advantages due to the elimination of mechanical tions within the impeller channel and blade surface pressure of the joints and a better utilization of material in this process are analyzed. centrifugal and mixed-flow impellers were closely examined by Several typical applications of the process are described. V.Z experiment and the flow behavior within these impellers were clarified. The incompressible and inviscid flows within the impellers having straight radial blades were also derived analytically. The A71.25971 ii A design method and the performance of present authors assumed an outermost boundary of the relative eddy two-dimensional turbine cascades for high subsonic flow. A. Uenishi at the impeller exit periphery and corrected the analytical results. (Hitachi, Ltd.. Research Laboratory, Ibaraki, Japan). American The corrected analytical results thus obtained showed good coin- Society of Mechanical Engineers, Gas Turbine Conference and cidence with the exoerimental data. (Author) Prodiicts Show, Hoiiston, Tex., Mar. 28-Apr. 1, 1971, Paper 71-GT-34. 12 p. 7 refs. Members, $1.00; nonmembers, $2.00, Desci iptioii of an approximate hodograph method for designing. A71-25975 ,4 A numerical technique for the calculation of turbine cascades for high subsonic flow of compressible fluid whose transonic flows in turbomachinery cascades. S. Gopalarkrishnan and specific heat ratio gamma = -1 and gamma greater than 1. This R. Bozzola (Avco Corp.. Avco Lycoming Div., Stratford, Conn.). method, which was established by Cantrell and Fowler (1959). is American Society of Mechanical Engineers, Gas Turbine Conference suitable for profiles with large deflection angles and thickness. and Products Show, Houston, Tex.. Mar. 28-Apr. 1, 1971, Paper Numerical examples are given, and theoretical and measured pressure 71-GT-42. 10 p. 16 refs. Members, $1 .OO; nonmembers, $2.00. distribution for profiles designed by this method are compared. A A numerical technique is presented for the calculation of steady better design criterion for improving cascade efficiency IS presented. inviscid transonic flows in turbomachinery cascades, wherein both M.M. subsonic and supersonic regions co-exist. The problem is posed in the time-dependent form and the asymptotic solution at large times A71-25972 U Liquid distributions of a low pressure drop provides the solution of the steady physical problems. The solutions injection system . Gas turbine 'vaporizer' design. H. W. Alp~ii(New for a hyperbolic nozzle cascade and two turbine cascades are Hampshire, Universltv. Durham, N.H.) and J. S Hoffman (General compared with other analytical solutions and with an experimental

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result. The agreement appears to be very good. Some preliminary to the volume producibility of the blades. The use of a titanium results are presented for a flow containing an oblique shock and its matrix and B-Sic filaments yields evaluational quantities of com- reflection. The computed results compare satisfactorily with the posite blades, but analysis of the process indicates that substantial exact solution. (Author) progress must be made before cost effect production could be contemplated. Raw materials are expensive, and cost reduction is directly associated with market volume. The hand labor and wastage associated with the formation of filament and foil lamellae were A71-25976 = The jet fuel starter goes operational. R. A. reduced by hot stretch forming of thick packages of foils to lengths Quick and F. D. Miller (USAF. Aeronautical Systems Div., Wright- and widths which more closely approximate the required ultimate Patterson AFB, Ohio). American Society of Mechanical Engineers. size. Further economization of the foil and filament lamellae forming Gas Turbine Conference and Products Show, Houston, Tex.. Mar. procedures is examined, and expected developments in this area are 28-Apr. 1, 1971, Paper 71-GT-43. 10 p. 'Members. $1.00; non- outlined. T.M. members, $2.00. The starter described is a compact, lightweight gas turbine consisting of a gas generator module, a power turbine module, and an A71-25980 ii Manufacturing approaches to resin matrix accessory module. The complete unit IS attached to the engine composite airfoils for gas turbine engines. R. A. Whitaker, W. H. accessory gearbox by means of quick-disconnect coupling. The gas Reinhart, and C. H. Castle (TRW. Inc., Cleveland, Ohio). American generator operates on aircraft fuel to generate a high-temperature gas Society of Mechanical Engineers, Gas Turbine Conference and stream output. The output is directed to the power turbine where Products Show, Houston, Tex., Mar. 28-Apr. 1, 1971. Paw the gas energy is converted to mechanical energy or torque for 71-GT-47. 8 p. Members, $1 .OO; nonmembers. $2.00. rotating the aircraft engine fast enough to start it:The advantages of Performance and cost are considered to assess the prospects of this starting system are reviewed, together with development history the use of resin matrix composites in gas turbine airfoils. Graphite- and early service experience. Z.W. fiber and resin-impregnated-graphite-sheet (prepreg) prices are surveyed to determine their contribution to the total cost of the resin matrix composites used. Anticipated high-volume production A71-25977 A fluidic fuel control valve for turbine engines. methods, such as computerized ply development with graphic R. L. Wilcox (Delavan Manufacturing Co.. Inc., West Des Moines. plotting, broadgoods collimation, impregnation and consolidation, Iowa) and J. H. Shadowen (United Aircraft Florida Research and and computerized multiaxis tape-laying machining, are described. Development Center, West Palm Beach, Fla.). American Society of The highly automated fabrication techniques required for a cost- Mechanical Engineers. Gas Turbine Conference and Products Show, effective composite airfoil production with labor and in-process Houston, Tex., Mar. 28-Apr. 1. 1971, Paper 71-GT-44. 4 p. Members, material waste minimization are expected to yield graphite yarn and $1.00; nonmembers, S2.00. tow at costs of $25 to $40/lb after the mid 70s. V.Z. A fluidic valve, consisting of a swirl chamber with tangential and radial inlets and a single outlet, has been used to provide uniform A71-25981 # Effects of polyurethane foam on fuel system fuel distribution to the nozzles in an annular combustor designed for contamination. T. 0. Reed (USAF. Aeronautical Systems Div.. a small turbine engine. The fuel nozzles were of the air atomizing Wright-Patterson AFB, Ohio). American Society of Mechanical type. with large flow passages for contamination tolerance. Pressure Engineers, Gas Turbine Conference and Products Show, Houston, drop across the nozzles was too small at low fuel flows to overcome Tex., Mar. 28-Apr. 1, 1971, Paper 71-GT-54. 10 p. 14 refs. Members, hydraulic heat effects and uniformly distribute the fuel to the $1 .OO;nonmembers, $2.00. nozzles. A fluidic valve installed in series with each nozzle provided The successful implementation of IC-pore/in. foam for aircraft wfficierit pressure orop to aistriwte tne fuel at IOW flow rates fuel system fire and explosion protection is described with special without requiring exceptionally high fuel pressures at large flow reference to fuel contamination. Cleanliness requirements associated rates. The fluidic valves were fed by a dual manifold fuel system. with the foam installation require that the level of particulate matter Fuel flow was divided between the two manifolds, which were does not exceed 1 mg/gal over that serviced to the aircraft. It was connected separately to the tangential and radial inlets of the fluidic verified that the foam installation has not increased the overall valves, by a pressure relief valve. The flow schedule of the system was system contamination level and, in some uses, may have reduced it. similar to that of a dual orifice pressure atomizing fuel system. Requirements for foam cleanliness were enacted through the Turn-down requirements of the system were 40:l. (Author) manufacturing, fabrication, installation, and testing phases of the modification. Periodic maintenance checks are also recommended in A71-25978 tu Cleaner fuel through nitrogen inerting. W. 0. the service. Z.W. Brookley (USAF. Aeionautical Systems Div., Wright-Patterson AFB, Ohio). American Soc;ety of Mechanical Engineers, Gas Turbine A71-25982 # A new method for the calculations of blade Conference and Products Show, Houston, Tex., Mar. 28-Apr. 1, loadings in a radial flow compressor. M. P. Boyce (Texas A & M 7971, Paper 71 GT-45. 3 p Members, S1.00; nonmembers, $2.00. University, College Station, Tex.) and Y. S. Bale. American Society Additional advantages associated with aircraft fuel tank nitrogen of Mechanical Engineers, Gas Turbine Conference and Products inerting are discussed. In addition to fire and explosion suppression, Show, Houston, Tex.. Mar. 28-Apr. 1. 1971, Paper 71-GT-60. 10 p. nitrogen inerting rrdkes it possible to remove oxygen and water from 10 refs. Members, $1.00; nonmembers. $2.00. aviation fuels, reduce foreign particles in fuel tanks, and possibly The paper outlines a quasi-three-dimensional approach based on reduce sludge and lacquering. Malfunctions of components due to the solution of the entire inviscid momentum and energy equations Contaminates were found to be greatly reduced. If oxygen removal is in the meridional and blade-to-blade plane to calculate the blade found to improve thei-mal stability sufficiently the necessity of using loading in a radial flow turbomachine. The method is outlined in expensive fuels for supersonic aircraft can also be eliminated. Z.W. detail so as to enable the reader to adapt it for use on his computer. The flow in the compressor is considered to be nonhomentropic with A71-25979 # Metal matrix composite fabrication procedures variations of thermodynamic properties at the inlet. A comparison of for gas turbine engine bladcs. J. A. Alexander, E. G. Parks, Jr., and P. various inlet distributions is shown and this illustrates the usefulness Melnyk (TRW, Inc., Cleveland, Ohio). .4merican Society of Me of this method. Calculation of the velocity on the trailing and driving chanical Engineers, Gas Turbine Conference and Products Show, faces of the blades is obtained. Pressure and temperature distribution Houston, Tex., Mar. 28-Apr. 1, 1971. Paper 71-GT-46. 7 p. Members. throughout the flow passage considering an actual process is also $1 .OO;nonmembers, 52.00. outlined. (Author) Application of the diffusion bonding process to the formation of gas turbine engine fan blades from titanium or aluminum matrix A71-25983 ti Advanced regenerative gas turbine designs for composites. Emphasis is placed on the susceptibility of this prowss lightweight and high performance. C. F. McDonald (AiResearch

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Manufactuiing Co., Los Angeles, Calif.) and R. A. Langworthy (US. combustor represented by this model can be maintained when the Army, Aviation Materiel Laboratories, Fort Eustis, Va.). American ratio between natural frequencies in (1) and (2) IS larger than unity. Society of Mechanical Engineers, Gas Turbine Conference and V.Z. Products Show, Houston, Tex.. Mar. 28-Apr. I, 1977, Paper 77.~r-67.25 p. 6 refs. Members, $1.00; nonmembers. $2.00. Two integrated gas-turbine concepts for aircraft applications are A71-25988 f! Holographic characterization of aerospace described in which annular recuperators of tubular construction are components. R. K Erf and J. P. Waters (United Aircraft Research ,.~!r?ppPd erntind the turbomachinerv to qive compact liqhtweiqht Laboratories, East Hartford, Conn.) American Society of Mechanical engine packages. The recuperator is the prime structure, forming the Engineers, Gas Turbine Conterence and Products Siiu w, Hous;oi;, backbone of the assembly. Designed for minimum mechanical Tex., Mar. 28-Apr. I, 7977, Paper 71-GT-74. 75 p. 10 refs. Membets. complexity, the engine assembly can be quickly split by a single tool $1 .OO; nonmembers, S2.00. Contract No. NAS 1-9926. into the three basic modules (gas yenerator, recuperator. and power Several adaptations of the basic holographic process to specific turbine) for routine inspection and maintenance Direct per- aerospace problems are described, including pulsed laser holography. formance, weight, and cost comparisons are made (at the same power interferometric holography, and pulsed schlieren holography. level) wtth a nonrecupeiative engine designed for the same cycle Specific applications of interest to the aerospace engineer include data. Sensitivity curves demonstrate the effects of small changes in studies of fuel nozzle spray characteristtcs, vibration analysts basic parameters on optimum recuperatoi critet ia fot given mission techniques, and helicopter rotor flow visualization methods. Non- times Compressor, turbtne, and combustor details are briefly destructive testing of aerospace components and materials IS il- outlined. T.M lustrated by examples of the inspection of electron beam welds. characterizatcx of bond defects In composite materials and honev- comb panels, and identification of internal structural flaws T.M. A71-25984 Y Low cost short life gas turbine design. D. L Murray and w. E. Kidd (Teledyne, Inc., Toledo, Ohio). American Society of Mechanical Engineers, Gas Turbine Conference and A71-25989 I? Lift jet engine, JR100. Masakatsu Matsuki. Products Show, Houston, Tex., Mar. 28-Apr. 1, 1971, Paper Tadao Torisaki (National Aetospace Laboratory. Tokyo, Japan). 71-GT-69. 7 P. Members. $1 .OO; nonmembers, $2 00. Kaneichtro Imai, and Ktyoto Miyarawa (Ishikawalima-HarimaHeavy Results of low cost gas turbine engine design studies are Industries Co.. Ltd., Tokyo. Japan). American Society of Mechanical presented. System requirements are discussed and their effects on Engineers, Gas Turbine Conference and ProduL ts Show, Houston, engine design and cost are analyzed. Parametric performance data are Tex., Mar. 28Apr. 1, 1977, Paper 71-GT-75. 12 p. Members, $1.00; presented and the use of these data in engine build cost trades IS nonmembers, $2.00. discussed. The evolution of specific component fabrication tech- The development of a vertical straight lift tutbojet engine with a niques on selected components is discussed, and the overall effect on six-stage axial flow compressor, an annular combustoi, atomiztng the engine cost is analyzed and described. The techntque of achieving fuel injectots, and two ball and toller bearings IS d~’rciibed At a total low manufacturing costs by the use of innovative design, keyed to weight of 342 Ibs it delivets 3390 Ibs of thiust The design operational requirements rather than new processes. IS described The emphasizes low cost and ready coinponent t~xchangrabilityfot the accessory problem is discussed and a potentially low cost fuel control sake ot easy maintenance and piompt incot1)oiation 01 fuithei concept described. A cross section drawing of a simple production technology advances Its sultahility tor use as a lttt power plant for turbojet is shown and the use of a technique for a low cost design is Compound-type VTOL aircraft has been demonstrated by the outlined. (Author) preliminary endurance tests the engine has undergone as a main propulsion oi booctpr engine. Engine component materials and A71-25985 /i Designing rotor burst protection. A. A. weights and performance data are tabulated and design details Martino (U.S Naval Air Propulsion Test Center, Trenton, N.J.). illustrated in photographs and diagrdms. M.V.E American Society of Mechanical Engineers. Gas Turbine Conference and Products Show, Houston, Tex., Mar. 28-Apr. 7, 1977, Paper 77-GT-70. 13 p. Members, $1.00; nonmembers. $2.00. A71.25990 ,U The supersonic turbine . A design and cascade Research on optimum-weight protective systems against un study. Irving Fruchtman (General Applied Science Laboratories, Inc.. contained rotor failure where fragments pass radially through the Westbury, N.Y ). American Society of Mechanlcal Engineers, Gas turbine engine casing leading to additional damage. A spin-chamber Turbine Conference and Products Show, Hol1ston. Tex., Mar. test facility was used for high-speed photographic study of the 28-Apr. 1, 7971, Paper 77-GT-76. 12 p. 29 refs. Members, $1.00; fragment impact on protective rings. Expertmental data are given for nonmembers, $2 00. Fundamental concepts are given for the desigri of a turbine Stage such factors as fragment types, blade effects, plastic growth of protective rings, ring restraint, fragment energy distribution. ring with supersonic gas velocities relative to the blading. Mtnimum length cross section, and radial clearance. Ring materials evaluated included nozzles (stators) and free-vortex-type rotor blades are specified and a steel, aluminum, ballistic nylon. and filament wound E-glass. TRIP correlation of their published performance is given. A blade selection (Transformation Induced Plasticity) steels exhibited the highest chart is given to provide a method for obtaining appropriate low-loss ratios of attack energy to ring weight. Transient ring computer codes rotor blade configurations. A series of two-dimensional cascade for predicttng the transient response of fragment impacted con- experiments is described in which the performance of ftlm.cooled, blunted leading-edge rotor blades were measured. Blade Performance tainment systems are described. T.M. is given Over a range of inlet Mach numbers and cooling flows. (Author) A71-25987 U A dynamic model of gas turbine engine main ‘Flying test cell’ evaluation and applications. J combustor instability. F F Ehiich (Genera! Electtic Co., Group A71-25991 # Engineering Div.. West Lynn, Mass.) American Society of Mechani- R. Esser (Emerson Electric Co.. St Louis, Mo.) American Society of cal Engineers, Gas Turbine Conference and Prodocts Show, Hooston, Mechanical Engineers. Gas Turbine Conference and Products Show, Tex., Mar. 28-Apr. 1, 7977, Paper 71-GT-73. 6 p Members, $1.00; Housron, Tex., Mar. 28-Apr. 1, 1971. Paper 71-GT-77.9 p. 14 iefs. nonmemlxis. $2.00. Members, $1 .OO; nonmembers, $2 00. A gas turbine combustoi model compiising a picmixing (01 Study of a flight test completed on an on boaid leal-timc engtnc vapotiring) chdmbet (1) and a comburtton chaml)ci (2). both performance monitoring system thdt demonsti attd thr technicdl designed as Helmholtz resotidtors, is desciillcd. The model IS used to feasibility of the baseline compat ison techiiiqiir of jet engitir derive a stahlity ciiterioii for obtaining the ct iticdl combustol thermodynamic health analysis The decistoii to concciittati. on tht? tempeiatuie ratio as a function of the combustoi geometiy in- thermodynamic analysis technique is a iesiilt of its ability to detcrt corpoiattng the chambet volumes and the effective peiiineters and mabi component deterioration. theteby !educing unschrdule(l areas of the chamber oiifices An analysls suggests thd stdbrlrty of a engine removals and delayed flights. By piovttltng a compiitcv controlled analysis tool (flight line 01 on-boatd) icstilts ‘IIC in1

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mediately available. The basic system can be expanded to include composed of two groups of particles: the very small, which are other useful real-time monitoring techniques as they evolve. F.R.L. primarily responsible for visible obscuration, and larger particles, which may constitute as much as half of the total by weight, but do not appreciably contribute to plume visibility. (Author) A71-25992 #! Holographic analysis of turbine blades. J. P. Waters and H. G. Aas (United Aircraft Research Laboratories, East Hartford, Conn.). American Society of Mechanical Engineers, Gas A7125996 #! The computation of transonic flow through Turbine Conference and Products Show, .Houston, Tex., Mar. two-dimensional gas turbine cascades. P. W. McDonald (United 28-Apr. 1, 1971, Paper 71-GT-84. 11 p. Members, $1.00; non- Aircraft Corp., Pratt and Whitney Aircraft Div., East Hartford, members, $2.00. Contract No. N 00019-69-C-0271. Conn.). American Society of Mechanical Engineers, Gas Turbine The applicability of holographic interferometw to measure- Conference and Products Show, Houston, Tex., Mar. 28-Apr. 1, ments of surface strains in turbine blades is reviewed. It is shown that 1971, Paper 71-GT-89. 7 p. Members. $1.00; nonmembers, $2.00. strains can be measured at the surface of a turbine blade, excited in Steady transonic flow through two-dimensional gas turbine dynamic flexure, using interferometric holographic fringe informa- cascades is efficiently predicted using a time-dependent formulation tion. Interferometric holography offers possibilities in the detection of the equations of motion. An integral representation of the of turbine blade flaws. especially using an internal pressurization equations has been used in which subsonic and supersonic regions of technique. Turbine blade stress analysis can be performed at the flow field receive identical treatment. Mild shock structures are elevated as well as at room temperature, but requires rhe use of permitted to develop naturally without prior knowledge of their pulsed holographic techniques for best results. A review of the exact strength or position. Although the solutions yield a complete resonant modes present in turbine blades and an analysis of both the definition of the flow field, the primary aim is to produce airfoil resulting time-average and double pulsed holographic fringe patterns surface pressure distributions for the design of aerodynamically are made. M.V.E. efficient turbine blade contours. In order to demonstrate the accuracy of this method, computed airfoil pressure distributions have been compared to experimental results. (Author) A71-25993 /f Design and development of a borondass- epoxy lightweight composite gear case. W. N. Holcomb (General Motors Corp.. Detroit Diesel Allison Div., Indianapolis, Ind.). A71-25997 # Development of Borsic-aluminum composite American Society of Mechanical Engineers, Gas Turbine Conference fan blades for supersonic turbofan engines. W. J. Schulz (USAF. and Products Show, Houston, Tex., Mar. 28-Apr. 1, 1971, paper Materials Laboratory, Wright-Patterson AFB, Ohio). J. A. 71-GT-85.9 9. Members, $1 !X; nonmembers, $?.on. Mingiipine, and !-!. Starga:.’ter !L!ci:cd Aircraf: CO:~., PrciZt and The design and development of a composite material front Whitney Aircraft Div.. East Hartford, Conn.). American Society of housing for the reduction gear of the T56 engine are discussed. The Mechanical Engineers, Gas Turbine Conference and Products Show, program was undertaken to advance the state-of-the-art in engine Houston, Tex., Mar. 28-Apr. 1, 1971, Paper 71-GT-90. 13 p. 26 refs. structures by making a material available that is capabk of replacing Members, $1.00; nonmembers. $2.00. Contract No. AF aluminum and magnesium, The selected boron-glass-epoxy material 33(615)-64C-1651. exhibits high strength and specific stiffness. light weight, good The design and fabrication of a new type of fan blades is corrosion resistance, and suitability for molding. The deslgn. mold- described and their performance is evaluated. The blades are over ing, machining, and testing phases of the programs are described. 40% lighter than the titanium blades currently in use. In addition, (Author) the blades can be desianed without oartspan rhroiuds which rewltx in a 1% increase in fan efficiency. A successful aeromechanical rig test is A71-25994 $ Aircraft gas turbine condition analysis in- described which demonstrates that the blades can be designed for a strumentation . Its use for the status diagnosis of naval turbine 430 F application without encountering any severe vibratory stress engnes. H. K. Ziebarth and J. D. Chang (AiResearch Manufacturing problem. The condition of the blades after testing was good with no Co.. Los Angeles, Calif.). American Society of Mechanical Engineers, visible cracks and negligible root distortion. Changes in blade twist Gas Turbine Conference and Products Show, Houston, Tex., Mar. angle after testing were also conbidered insignificant. Mc:eover. the 28-Apr. 1. 1971, Paper 71-GT-86. 12 p. 7 refs. Members, $1.00; test results indicate that extending the operational limits of the nonmembers, $2.00. blades to 600 F is possible. O.H. The feasibility of current verification of the mechanical and Performance status of gas turbines for naval use beyond that realized today in other turbine engine use areas is examined. It IS shown that A71 -26054 Preliminary design and analysis of an advanced direct mechanical status determination of critical components convertible fadshaft engine for V/STOL tactical and transport appears to be feasible today in view of recent developments in the aircraft. J. N. Tulino, P. C. Bosse, and W. H. Wiley (United Aircraft sensor and electronic data interpretation areas. This can be achieved Florida Research and Development Center, West Palm Beach, Fla.). by automatic checkout systems which functionally integrate dif- American Helicopter Society, Journal, vol. 16. Apr. 1971, p. 34-42. ferent diagnostic techniques in a manner addressing specific use- This paper describes the mechanical arrangement and per- mode related engine degradation and malfunction phenomena. O.H. formance of the Pratt & Whitney Aircraft STF/S351 convertible engine concept. The STF/S351 is a combined fadshaft engine which A71-25995 /f Standard measurement of aircraft turbine gas can provide the multimode power required by V/STOL aircraft by engine exhaust smoke. D. L Champagne (USAF, Aero Propulsion delivering shaft power to rotors for vertical takeoff. and fan thrust Laboratory, Wright-Patterson AFB, Ohio). American Society Of for long-range high-speed cruise. Using a single gas generator core, Mechanical Engineers. Gas Turbine Conference and Products Show. fixed-geometry fan and power turbines in series, and a turbine bypass Houston, Tex.. Mar. 28-Apr. 1. 1971, Paper 71-GT-88. 11 p. 19 refs. arrangement, this engine can produce full shaft power, full fan Members, S1.00; nonmembers. $2.00. thrust, or any near-linear combination of the two. By changing the A standard system (equipment and procedures) for measuring fan bypass ratio, fan pressure ratio, and turbine temperature smoke emitted by aircraft turbine engines has been developed. It has scheduling, this engine can be tailored to meet a variety of mission been adopted by several federal government agencies. In this paper. requirements with the same gas generator. Compared to a system the system is explained and Its accuracy defined. An experimentally using separate engines for cruise and takeoff, the STF/S351 offers determined relationship between the system’s parameters and true lower installed weight, lower propulsion system cost, decreased smoke density (weight of solids per unit volume) is presented and complexity. decreased frontal area, and eliminates the need for theoretically examined The definition of smoke plume visibility in in-flight starting and stopping of engines during mode-to-mode terms of the system‘s parameters IS also developed. This work led to transition. (Author) the conclusion that aircraft turbine engine exhaust smoke is

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A71-26192 Y Shock-shock reflection. W. Skews 8. A7126201 f! Classification of flexible runway surfaces by (McMaster University, Hamilton, Ontario, Canada). CAS/ the LCN method (Klasyfikacja podatnych nawierzchni lotniskowych Transactions, vol. 4, Mar. 1971, p. 16-19, 5 refs. Research sponsored metodg LCN). Franciszek Kaimierczyk. Technika Lotnicza i Astro- by the National Research Council. nautyczna, vol. 26, Feb. 1971, p. 21-26. 6 refs. In Polish. This paper examines the trajectory described by the triple point The use of the ICAO-recommended LCN (Load Classification of a Mach reflection when reflected off a plane wall. The incident Number) method of determining the load capacity of flexible and triple point was obtained from the Mach reflection of shock waves, composite runway surfaces is demonstrated. Examples of LCN with Mach numbers of 1.2, 1.5, and 2.0, off wedges of various angles -. calculations are given for Iliushin-14 and Iliushin-18 aircraft. T.M. I ne theorericdi pe:ic?;ons were bascc! en ?he si-p!e three-shock theory, an examination of the interactions in the wave train following the reflection, and Whitham's theory. The three-shock A7 1-26258 The profile couple method for studying the theory and the interaction analysis give similai results for small flow of an ideal fluid around a fixed arbitrary obstacle in the corner angles but differ considerably from the results of Whitham's presence of a rectilinear wall (Sur la methode du couple des profils theory. The experimental values lie between these two predictions pour I'etude de I'ecoulement d'un fluide ideal autour d'un obstacle with the shape of the final curves being similar to those predicted arbitraire fixe, en presence d'une paroi rectiligne). Titus Petrila (cluj. from three-shock theory. The experimental values tend towards the Universitatea, Facultatea de Matematica si Mecanica, Cluj, Rumania). theoretical prediction for the limiting case of zero wall angle. Academie des Sciences (Paris), Comptes Rendus. Serie A - Sciences (Author) Mathematiques, vol. 272, no. 13, Mar. 29, 1971, p. 908-910. 5refs. In French. A7126194 # Reattachment of the supersonic laminar Study of the plane motion of an ideal incompi-essible fluid boundary layer (Recollement de la couche limite laminaire en around a fixed profile in the presence of an infinite rectilinear wall. supersonique). C. Bourque (Universite Laval, Quebec, Canada). CAS/ Petrila's (1971) so-called profile couple method is used for this Transactions, vol. 4, Mar. 1971, p. 25-31. 7 refs. In French, purpose, as well as Jacob's (1968) circular ring theorems. An explicit Measurements of the reattachment angle of a laminar mixed expression is derived for the complex potential in the particular case layer by means of a model of symmetrical revolution for a negligible of a circular profile. This expression is the same as that obtained in initial boundary layer. The important parameters are the Mach the so-called 'dual' problem with a translational term added. A.8.K. number, the Reynolds number, and the angle of the cone upon which the layer reattaches. The reattachment angles obtained are from two to three times larger than are predicted by the Chapman A71-26304 # Laser beam probing of jet exhaust turbulence. criterion, which furthermore does not take Reynolds number into C. 6. Hogge and W. L. Visinsky (USAF, Weapons Laboratory, account. A new criterion is proposed which tncludes the effect of Kirtland AFB, N. Mex.). Applied Optics, vol. 10, Apr. 1971, P. Reynolds number and the geometry of the model. This criterion is in 889-892. 9 refs. ARPA-supported research. quite good agreement with experimental measurements. F.R.L. Description of an experiment in which a He-Ne (6326-A) laser beam was passed through the highly turbulent region in the exhaust of a jet engine (J-57 with afterburner). Estimates of a structure A7126196 9' Predictions of the blowing required to sup- constant that would Characterize the turbulence in the exhaust are press separation from high-lift aerofoils. I. s. Gartshore (British made from the beam spread of focused and collimated beams. The Columbia, University, Vancouver, Canada). /Canadian Aeronautics structure constant obtained in this manner is then compared with and Space /ns?ifote and American Institute of Aeronautics and that determined from scintillation measurements of a (10.6-micron) Astronautics, Joint Meeting, Toronto, Canada, July 9, 10, 1970 ) beam and with the results of hot-wire anemometer readings taken in CAS/ Transactions, vol. 4, Mar. 1971, p. 39-46. 16 refs. National the exhaust. The various methods yield results for the structure Research Council of Canada Grant No. A-4308. constant that are in good agreement (typically a structure (Author)constant This paper gives a review of methods for predicting the of the order of ,00003 per meter to the 1/3 power). streamwise development of boundary layers augmented hy tangential blowing, typical results obtainable by one of these methods are presented and problem which remain to bc solved are outlined. A71-26308 Aircraft maintenance. J. W. Norberg (Air From the restilts it appears possible to predict the development of Canada, Montreal, Canada). Aeronautical Journal, vol. 75, Mar. blown boundaiy layers up to separation with reasonable accuracy, 1971, p. 153-158. provided the boundary layer upstream of the blowing slot is not too The philosophy underlying the achievement and sustaining of latge. Calculations of the minimum power required for blowing to the airworthiness standard throughout the life of aircraft is outlined suppress separation show that significant savings can be made if two and the principal tasks in this field are specified. The respective prime processes involved are discussed. Determinatlon, provisioning. slots are used with correct blowing velocities from each. A simple and utilization of maintenance resources are examined. Basic criterion has been found which suggests when a minimum will persist elements of maintenance which constitute a system through which in the velocity profile downstream of a blowing slot due to incomplete mixing of the upstream boundary layer with the jet fluid. the maintenance task is accomplished are summarized. Finally, future maintenance requirements are briefly considered. O.H. (Author)

A7126197 b Effect of small surface curvature on unsteady A71-26309 A design study for a freight-carrying airship. E. hypersonic flow over an oscillating thin wedge. P. Mandl (Carleton Mowforth (Surrey, University. Guildford, Surrey. England). Aero- University. Ottawa, Canada). CAS/ Transactions, vol 4, Mar. 1971, nauticalJourna1, vol 75, Mar. 1971, p. 166-174. p. 47-57. 12 refs Some areas of the overall transport spectrum which might be Consideration of the effect of curvature on the aerodynamic expected to favor airship operation are discussed, and some of the charactciistics of a thin. slightly curved. two-dimensional aitfoil problems associated with different modes of operation are examined. oscilldtiiig harm(iiiically with small am~ilitutlein a uniform hyper- Particular reference is made to the project that IS underway at sonic flow The method employed is a perturbation of the equations Airfloat Transport, Ltd., which IS a vessel with a gas capacity of 30 of small disturl)aiice theoiy. considei ing relative amplitude of oscilla- million cu ft (849,510 cu m) intended for the carriage of large O.H. tion and atifoil curvature at the leading edge as independent indivisible loads over moderate distances. peiturbdtion paiaineteis It is shown that oscillating convex suifaces are dynamically less stalilc than oscillating wedges for all values of A71-2631 0, Local avoidance of sonic booin from an the relevant paiametei s, concave surfaces have the opposite effect. aircraft. W. F. Hilton. Aeronautical Journal, vol. 75, Mar. 1971, p. F.R.L. 179181,

354 A71 -26409

Acoustic consequences of a curved supersonic flight path are space over their territories. With the future development of space exainiiied. It is shown that such a flight path causes a local focus of travel it will be necessary to establish a universa!ly recognized system shock waves and accentuated boom and, more particularly, produces of jurisprudence. F.R.L. a 'no-boom' zone in other localities closer to the center of curvature of the flight path than the M = 1 radius. Practical aspects of this effect are discussed and rules for curved supersonic flight are A71-26364 Wind shear on the approach. W. W. Melvin outlined. O.H. (Delta Air Lines, Inc., Atlanta, Ga.). Shell Aviation News, no. 393, 1971, p. 1620. 6 refs. Some representative examples of low altitude vertical wind A7126311 Analysis of taxiing induced vibrations in air- shears resulting from variations in wind levels with altitude and their craft by the power spectral density method. C. L.'Kirk (Cranfield general characteristics are presented. The effects of the gradients and Institute of Technology, Cranfield, Beds., England) and P. J. Perry magnitudes of wind shears on aircraft flying on approach are (RAF. London, England). Aeronautical Journal, vol. 75, Mar. 1971. examined. Necessary thrust corrections in the presence of a wind p. 182-194. 22 refs. shear and countercorrections in case the wind shear ceases are A method was developed for determining the response to discussed. Thrust requirements for aircraft flying a glide slope with a stationary random vibrations of a flexible aircraft. taking into tailwind that decreases to a no-wind condition just above the ground account nonlinearities in the oleo-pneumatic landing gear in the form are also considered. Several concealed hazards for the pilot due to of orifice damping and Coulomb friction. Results of a separate wind shears are reviewed Particular attention is given to the situation investigation are also presented in which the response of the aircraft that can occur owing.to the combined effect of a shear and the in the coupled rigid body and first elastic mode was determined using characteristic method of flight control utilized by the approach an analog computer. O.H. coupler - i.e.. control of glide path position by pitch corrections, with resultant excursions in airspeed controlled by th:ust corrections. Finally, several rules are suggested mhich might be helpful in A71-26314 A theory on effect of entrainment. due to jet correcting for wind shears. O.H. flap which hits the gound, for an aerofoil with separation. T. Kida and Y. Miyai (Osaka Prefecture, University, Osaka, Japan). Aero- nauticalJournal. vol. 75. Mar. 1971, p. 199-201. 11 refs. A7126401 # Theory and calculation of aircraft bladed A simple approximate method is presented which is effective in machines (Teoriia i raschet aviatsionnykh lopatochnykh mashin). K. calculating the flow around a jet flapped airfoil irrespective of V. Kholshchevnikov. Moscow, lzdatel'stvo Mashinostroenie. 1970. whether or not the jet entrainment exists. The numerical results 613 p. 67 refs. In Russian. show that the increment in lift coefficient due to iet reaction is more The fundamentals of the theory ot bladed machines are significant than the changes in pressure forces on the airfoil. The explained, with emphasis on the design and principles of operation of effect of jet entrainment on lift coefficient is not large except when bladed machines of various types - namely, axial-flow, centrifugal. the jet sheet is almost touching the ground. O.H. and composite compressors, and axial-flow turbines. The basic equations of the theory of these machines are derived, the thermodynamic processes occurring in the machines are represented A71 -26315, A flight test establishment - Its function and a in p-v. T-s. and i-s diagrams, and the determination of the efficiencies suggested composition. J. M. Lewendon (Hawker Siddeley Aviation, of these machines is demonstrated. Special attention is given to the Ltd., Dunsfold, England). Aeronautical Journal, vol. 75, Mar. 1971, characteristics and control of turbines and compressors, and to the p ~7.272. ;jrz5!2~of rna~ch;~r~~:h; peiaiiiziti. of ihr iurbiiie diii compressor The objectives of flight testing of aircraft are detailed, and the in a gas turbine engine system. A.B.K. major features of the individual but interdependent test programs which have to be carried out to achieve these objectives, are broadly explained. Particular attention is given to the responsibilities and A71-26403 Automation of aircraft and rocket power organization of the Flight Test Establishment which provides the plants (Avtornatika aviatsionnykh i raketnykh siiovykh ustanovok) execution of this operation. O.H. (3rd revised and enlarged edition). A. A. Sheviakov. Moscow, Izdatel'stvo Mashinostroenie, 1970. 670 p. 45 refs. In Russian. This third edition extends the theoretical treatment of auto- A71-26316 The manufacture of glass fibre rotor blades matic aircraft and rocket engine control to include automatic control with pressure tappings. D. Gregory-Smith and H. Marsh G. systems of hybrid and nuclear-powered engines. The theoretical (Cambridge University, Cambridge, England). Aeronautical Journal, considerations are limited to problems associated with the determina- vol. 75, Mar. 1971, p. 213-215. Research supported by Rolls-Royce. tion of the dynamic characteristics of the controlled plants, the Ltd. calculation of system dynamics, and to the study of possible control A set of rotor blades from glass fiber and epoxy resin was and fuel system design. A special chapter is devoted to the dynamics designed and manufactured for a large rotating cascade wind tunnel of heat exchangers employed in power plants. Particular attention is used for research on the flow through turbomachines. Design given to control systems of gas turbine engines, ramjet engines, and characteristics of blade root fixing and a description of blade rocket engines. The reader is assumed to be acquainted with the manufacture are presented. Particular attention is given to a cheap fundamentals of automatic control theory, engine theory, and and simple newly developed method for making 30 pressure channels methods of control-system simulation. The textbook should be also running the full length of the blade surface. O.H. of interest to engineers and scientist dealing with automatic engine control. V.P.

A71 -26325 Air and cosmic space common law as the only solution of the problem of determining the boundaries of these A71-26409 Quasi-optimum proportional navigation. Elliot spaces (Le regime juridique commun de I'espace aerien et cosmique I. Axelband and Frederick W. Hardy (Hughes Aircraft Co.. Culver wmme la seule solution du problem de la &limitation de ces City, Calif.). IEEE Transactions on Automatic Control, vol. AC-15, espaces). Michel Smirnoff. Revue Francaise de Droit Adrien, vol. 25, Dec. 1970, p. 620-626. 6 refs. Jan.-Mar. 1971. p. 27-34. 20 refs. In French. The problem of deriving feedback guidance laws for interceptor Study of the problem of air and space boundaries which is type aerodynamically controlled missiles which seek to engage implied in the principle of the freedom of the cosmos and the moving targets is considered. These missiles contain target trackers incapability of states to appropriate parts of the cosmos. However, it which provide angular information about the relative interceptor-to- is recognized that states can and do exercise sovereignty in the air target geometry. The performance criterion for this problem is

355 A71-2641 8

quadratic, but the system equations are nonlinear. Suitable guidance Investigation of the flow in the wakes behind two-dimensional mechanizations are obtained by applying the technique of quasi- perforated plates in the Reynolds number range from 25,000 to optimum control. The efficiency of the resulting guidance system, 90,000. Measurements of drag and shedding frequency were made relative to a linear optimum guidance system and a proportional and a pulsed hot-wire anemometer was used to measure the mean navigation system, is demonstrated by simulations of attack situa- velocity and turbulent intensity variations in the highly turbulent tions in which the interceptor missile launch conditions depart from regions immediately behind the plates. The results indicate the the nominal attack geometry. (Author) existence of two distinct types of flows: one appropriate to high and

-L^LIIC "LIDO1-tL-- ...

A71-26418 Property of the equationerror approach to parameter identification. Jerry M. Mendel (McDonnell Douglas A71-26486 A 'static' evaluation ot the manoeuvring tail Astronautics Co.. West Huntington Beach, Calif.). I€€€ Transactions load for instantaneous unchecked longitudinal manoeuvres of sail- on Automatic Control, vol. AC-15. Dec. 1970, p. 676-678. 7 refs planes. Piero Morelli (Torino, Politecnico, Turin, Italy). (Organlsa- An unusual property associated with the equation-error tion Scientifique et Technique lnternationale du Vol a Voile, approach to parameter identification is demonstrated. This property, Congress, 12th, Alpine, Tex., June 27-July 4, 7970.1 Aero-Revue, which is usually a liability of the equation-error formulation. is Apr. 1971, p. 183.185. shown to be an asset for a specific application involving third-order The sailplane in the equilibiium condition coiresponding to a pitch-plane dynamics for a typical high-performance aerodynamically point on the n-V maneuver envelope is considered. Relations controlled aerospace \vehicle M.V.E. regarding the equilibrium of forces in the vertical direction and of moments about the pitching axis die examined. Thc effects of an instantaneous upward deflection of the elevatoi are investigated, and A71 -26443 Y Calculation of three-dimensional turbulent aerodynamic responses of the aircraft are discussed. Conditions for a boundary layers. P. Bradshaw (Ministry of Technology, National sailplane are considered giving attention to the aperiodic dynamic Physics Laboratory, Teddington, Middx., England). Journal of Fluid response. G.R. Mechanics, vol 46, Apr 13, 1971, p. 41 7-445. 35 refs The two dimcns~onal prediction method of Bradrhaw, Ferrrss A7 1-26487 Elevator-induced manoeuvring loads from the and Atwell (19671. which was based on the empirical conversion of standpoint of airworthiness requirements for sailplanes. Piei o Morelli the tiirhulent energy equation into a 'transport' equation for shear (Torino. Politecnico, Turin, Italy). (Organisation Scientifique et stress, is extended to three~dunenslonal flows satisfying the Technique lnternationale du Vol a Voile, Congress, 12th, Alpine, boundary4ayei approximation (which excludcs flows near bluff Tex.. June 27-July 4, 1970.) Aero-Revue, Apr. 1971, p. 185. obstacles or streamwise corners). Predictions. using exactly the same An expression for the inciemental aerodynamic load on the empirical data as in two-dimensional flow, agree to within the likely horizontal tail, produced by an instantaneous elevator deflection, is experimental error with a vaiiety of expeiiments on 'infinite' swept considered. A proposal to use the incremental tail loads thus wings (Authoi) calculated for a ieplacement of the maneuvei ing incremental loads specified by the OSTIV Airwoithiness Requirements IS examined, and an investigation of the tail loads due to abrupt longitudinal A71 -26447 P Viscous tails in Hele-Shaw flow. C. J. Wood maneuvers is discussed. G.R. (Oxford University, Oxford, England). Journal of Fluid Mechanics, vol 46, Apr 13, 1971, p. 569-576. An experiment has been performed, using pulsed dye injection A? 1-26667 * A facelifting for NASA's reliability require- on an aerofoil in a Hele Shaw cell. The purpose was to observe the ments. David S. Liberman (NASA, Reliability and Quality Assurance form of the trailing-edge flow when the Reynolds number was high Office, Washington, D.C.) In Institute of Electi ical and Electronics enough to permit separation and the initiation of a Kutta condition. Engineers. Annual Symposium on Reliability. Washington, D.C.. The experiment provides a successful confirmation of the existence January 12-14. 1971, Proceedings. Sy mpos i ti m of a 'viscous tail' as predicted by Buckmaster (1970) although there co-sponsored by the liistitute of Environmental Sciences and the is an unexplained quantitative discrepancy (Author) American Society for Quality Control New York. Institute of Electi ical and Electronics Engineeis, Inc. (Annals of Assurance Sciences. Volume 4, No. 1 1, 1971, p 121-128. A71-26448 ff On the scattering of aerodynamic noise. D. G. Crighton and F G. Leppington (Imperial College of Science and Brief review of the evolution process which led to supeisession lechnology, London, England). Journal of Fluid Mechanics, vol. 46, of NPC 250-1 by NHB 5300.4(1A) 'Reliability Progiam Provisions Apr. 13, 1971. p. 577 597. 10 refs. Research supported by the foi Aeronautical and Space System Contractors'. The resulting Ministry of Technology. changes in the requirements are described. Experience with NPC The extent to which scattering bodies situated near Lighthill's 250-1 led to significant evolution in capabilities of NASA and multipoles can convert some of their intense near field energy into contractor reliability organizations. acceptance of the assiirdnce role the form of sound waves (whose intensity is greater than the incident of reliability, and the needs of NASA and its projects. It is field) is analyzed for hard and soft bodies of various shape. The considered that the revision has successfully responded in lai ge reciprocal theorem is used to reduce the problem to finding the field, measure to these changed requirements. F.R.L. near the obstacle. induced by an incident plane wave. For the situation where the scatterer is large compared with the wavelength, A71 -26671 Effects of the Pan American reliability pto- the prototype problem of a wedge of exterior angle (piq1pi IS shown to yield an intensity law I proportional to U to the (4 + 2q/p) power gram on airline maintenance. F. H Moxley, JI. (Pan American WoiId (where I is the far field intenSiTy. and U the turbulence velocity) for Airways. Inc., John F. Kennedy International Airport. N Y.). 111: both hard and soft surfaces. This result is shown to hold for more Institute of Elccti ical and Electronics Engineeis. Anntral Sympostum general wedge like surfaces whose dimensions are large scale and on Reliability, Washington, D.C., Janu;liy 12 14, 1971, Pioccdings. whose edges may be smoothed out on a small scale compdred with Symposium co sponsoicd by the lnstitiitr of the wavelength. V.P. Environmentdl Scienctls and the Americdn Soclcty for Quallty Control. Nr,w Yolk, Institute of EIc%ctiicaland Elwtionics Enginrris, Inc. (Anids of Assuidnc(7 Sciencrs Volumr 4. No. l), 1971. 11. A71-26449 // Wake characteristics of two-dimensional per- 163 166. forated plates normal to an air-stream. I. P Castro (Imperial College Review of the sul~stancrand dpplicatioil ir%ilts of d i~'Iidl)ility of Science and Technology, London, England). Journal of Fluid progi am drsigiwd to reduce inaiilt('ildi1ce cost dnd dowvlltimc foi Mechanics, vol. 46, Apr. 13, 1971, p. 599-609. 15 refs. modein comn1~'icidl [et aiiciaft. A brirf outliilr' of th(' backgiound of

356 A71 -26766

cost~effective maintenance management in commercial aviation is Findings include the observation that the overall noise field is followed by a discussion of the reliability program's aircraft roughly nondirectional for all louver angles. M.V.E. performance report parameters, data collection and analysls techniques. functions, and responsibilities. The results so far show that A71-267 14 Adaptive systems; Moskovskii Aviatsionnyi the program has been very effective in reducing aircidft maintenance downtime and costs. The theoretical reliability techniques have Institut, lubileinaia Nauchno-Tekhnicheskaia Konferentsiia, MOSCOW, USSR, Mar. 26, 27, ' 1970, Transactions (Adaptivnye sistemy; proven to be very useful in practice. M.V.E. Moskovskii Aviatsionnyi Institut, lubileinaia Nauchno- Tekhnicheskaia Konferentsiia, Moscow, USSR, Mar. 26, n,1910. A71 -26679 Helicopter auxiliary power unit cost of owner- Trudy). lnformatsionnye Materialy, no. 7 (44). 1970. 144 p. In ship. B. M. Gallagher and W. H. Knobloch (International Harvester Russian. Co.,San Diego, Calif.). In: Institute of Electrical and Electronics Includes the realization of adaptive control algorithms, elements Engineers, Annual Symposium on Reliability, Washington, D.C., of adaptive control systems, self-adjusting control systems for an January 12-14, 1971, Proceedings. Symposium aeroelastic aircraft, adaptive control of flight vehicle roll, flight co-sponsored by the Institute of Environmental Sciences and the vehicle control during atmospheric reentry. parametrically invariant American Society for Quality Control. New York, Institute of control systems, statistical estimation in monitoring and control Electrical and Electronics Engineers, Inc. (Annals of Assurance problems, choosing the transfer function of a standard model of a Sciences. Volume 4, No. 1). 1971, p. 285-291. self-adjusting control system, the equations of motion of bodies of The methodology used to compute life cycle costs for the variable mass, the synthesis of nonsearching self-adjusting control current model of an auxiliary power unit (APU) is explained, and the systems, the development of a criterion for comparing adaptive costs for four different APU concepts are estimated. The various cost control systems, the structure of a digital self-adjusting system with a factors for the four new concepts are described briefly. Comparisons model, the synthesis of a self-adjusting autopilot, and the special are made between current model costs and anticipated decreases or features of fixed-adjustment control systems. increases in the new concepts. It is shown that for the current APU A.B.K. model, support expenditures far exceed the initial acquisition cost. By incorporating design changes which are aimed at increased A71-26716 ii Prospective automatic flight-control systems reliability, improved maintenance, and the reduction of spare parts (Penpektivnye sistemy avtomaticheskogo upravleniia poletom). A. stocked in the field, it is found that life cycle costs can be reduced D. Aleksandrov. (Moskovskii Aviatsionnyi Institut, lubileinaia even when initial acquisition cost is increased. Z.W. Nauchno-Tekhnicheskaia Konferentsiia, Moscow, USSR, Mar. 26,27, fg?L?.! ~,C~C,TSS~C,Z,Z~.S ?vfateiXjj, In". i (Gjj, isis, p. 20.29. ~n Russian. A71 -26683 Screening for reliability growth. Robert W. Description of nonlinear self-adjusting and variable-structure Fink (General Electric Co.. Utica. N.Y.). In: Institute of Electrical automatic control systems for piloted and pilotless flight vehicles. and Electronics Engineers, Annual Symposium on Reliability, Control problems considered include load stabilization, limitation of Washington, D.C.. January 12-14, 1971, Proceedings. critical regimes, and control of yaw. pitch. and roll angles. Emphasis Symposium co-sponsored by the Institute of Environ- is placed on the extension of stability ranges by appropriate mental Sciences and the American Society for Quality Control. New switching of the controller structure. The additional use of adaptive York, Institute of Electrical and Elecrronicr Engineers, tw. (Annals loops is demonstrated, and oscillations arising from intrinsic non- of Assurance Sciences. Volume 4, No. 1). 1971, p. 316.320. linear charartpricticr nf pl~.c?~ics~;" :;$:err.; ;&;< iviizj .,.j TC I 111 eKrcrivriiess of a screening program from parts procure- lags) are examined. T.M. ment through system test is examined on the basis of experience obtained with the AN-APQ-113 attack radar system for the F-111 aircraft. It is shown how screening at all levels affects both reliability A71-26718 F Self-adjusting automatic control systems for performance and profit levels. A Duane Growth Model, constructed an aeroelastic aircraft (Samonastraivaiushchiesia sistemy avtomati- to relate the impact of screening on system MTBF growth, is cheskogo upravleniia aerouprugogo samoleta). G. I. Fedorenko, V. A. discussed. V.P. Vishnevetskaia. V. I. Glukhov, and L. R. L'vov. IMoskovskii Aviatsionnyi Instirut. lubileinaia Nauchno-Tekhnicheskaia Uon- ferentsiia, Moscow, USSR, Mar. 26, 27, 1970.) lnformatsionnye A71 -26702 Sound radiation from a point force in circular Marerialy, no. 7 (44). 1970, p. 36-43. 7 refs. In Russian. motion. C. L. Morfey and H. K. Tanna (Southampton, University, High-quality control of an aircraft as a rigid body can be Southampton. England). Journal of Sound and Vibration, vol. 15. achieved (with allowance for the nonlinearity and inertia of the Apr. 8. 1971, p. 325-351. 14 refs. actuator) by using appropriate compensating devices and by placing This paper is a theoretical study of sound radiation from a adaptive filters in the angular-velocity sensor circuits to eliminate time-varying point force in accelerative motion, where the accelera- noise caused by high- and low-frequency elastic oscillations. The tion arises from steady rotation in a circle. The study is prompted by primary low-frequency components of flexural vibrations in the the question of whether such effects are significant in fan or wings and fuselage can be damped by special control surfaces on the helicopter rotor noise at subsonic tip speeds. Closed~formexpressions wings and fuselage. This damping should be steered from accelerom- are found for the overall radiation at a point in the far field, and for eter sensors positioned in selected points. The required phase the radiated sound power, showing the acceleration effect as an relationships are obtained with compensating mechanisms and either additive term in each case. The effect of rotation on the broad-band phase-lead or phase-lag filters. Automatic control of optimal gain in far-field spectrum is demonstrated by a series expansion for the stabilization loops is accomplished with the aid of spectrum rotational frequencies small compared with the radiated frequency. analyzers. The synthesis of controller structure and parameters I Au thor) should be based on graph-theory methods.

A7 f -26704 Effects of louvres on the noise of an axial flow A71-26766 # Flutter of clamped skew panels with mid-plane fan. P. E. Doak and D. N. May (Southampton, University, forces in supersonic flow. S. Durvasula (Indian Institute of Science, Southampton. England) Journal of Sound and Vibration, vol 15, Bangalore, India). (Aeronautical Society of India. Annual General Apr. 8, 1971.p.421-424. Meeting, 21st. Indian Institute of Technology, Madras, India, Apr. Experimental investigation of the effect on the sound field of 4-6, 1S9.1 Indian Institute of Science, Journal, vol. 52. Oct. 1970, axial flow fans of louvers positioned across their intakes. performed p. 192.208. 31 refs. wiTh the aid of a rig configuration typical of many practical The flutter problem of uniform, thin, flat, isotropic, skew panels situations (e.g , lift fans for VTOL aircraft and ventilation systems). clamped on all the edges and under the action of mid-plane forces is

357 A71 -26870

formulated on the basis of the classical small deflection thin plate A71-26882 it Concorde structural features. Aircraft Engi- theory. For the aerodynamic loading, the two-dimensional static neering. vel. 43. Apr. 1971.p. 16-19,22. approximation is used. Approximate flutter analysis is made by using Description of the methods of construction and materials used the Galerkin method employing a double series of beam character- in the production of the Anglo French SST. Hiduminium RR 58 istic functions to represent the deflection surface. Results of (AU2GN). a heat- and creep-resistant alloy available in the form of numerical calculation for the critical dynamic pressure for a few sheets, forgings, prestretched plates and extrusions, was chosen as the configurations of rhombic panel under direct stress in the stream- basic structural material. Structural details of many components such wise direction are presented. [Authcr! as :t;c wing !cading wi-g ribs, 2nd many others are given and line drawings of them are presented. F.R.L.

A71-26870 Subsonic and supersonic operations in the A71-26883 # The challenge of the supersonic era. Thomas years ahead (Sir Charles E. Kingsford-Smith Memorial Lecture). G. Foxworthy. Aircraft €ngineering, vol. 43, Apr. 1971, p. 23-26. James Andrew (British Overseas Airways Corp., London Airport, Assessment of some of the problems that face the pilot of the Hounslow, Middx., England). Aeronautical Journal, vol. 75, Apr. SST. Adequate instrumentation is one of the greatest concerns. Pilots 1971, p, 269-279. Consideration of various restraints which hinder aircraft opera- expect to see much more information presented in digital form only tions and which threaten further growth. Community reaction to for reasons of space and duplication. Angle of attack and sideslip noise and pollution causes one set of constraints. but at the same indicators would be extremely useful Aspects of supersonic cruise are discussed. It is considered that the problem of rendering fuel time fdbl and efficient transport is desired. Anothw set nf constraints concerns the adequacy of facilities at airports on certain routes. tanks immune to explosion is of plimary coticern. ~iiceilie fuel is Aspects of radio and other aids needed for safe and regular operation used as a heat sink. Better on-board radar is needed. F.R.L. are extensively discussed Some simulated Concorde flights are described, including a complete London-New York mission. F.R.L. A71-26884 4 Powered flying controls on the VAK 1918. Aircraft Engineering, vol. 43, Apr. 1971, p. 27, 28. A71-26878 # The growth of avionics. L. F. E. Coombs. Description of the development of advanced powei-ed flying Aircraft Engineering, vol. 43, Apr. 1971, p. 4-6, 22. 8 refs. controls for the VFW Fokker V/STOL fighter prototype Five Account of the application of electronics to aircraft systems and duplex input servos are fitted to the aircraft. each one being an of the latest advances in this field. It is considered that the rate of electrically signaled, twin channel, high resolution input servo with. growth for the next decade will be less than previously, since civil manual reversion, hydrdulically powered. Its function is to power the aviation has reached a point in its development where avionic input linkage from the pilot’s contiols to the operating servo vdlves advances are becoming marginal. However, there will be increased use of the surface power control, and also to operate the pneumatically of digital computers, solid state transducers, integrated circuits, stabilizing puff-pipes which function continuously during the VTOL electronic flight instruments, area navigation, and collision avoidance flight mode. F.R.L. systems. F.R.L.

A71-26921 In 18 months . First flight of the European Airbus. Interavia, vol. 26, Apr. 1971, p. 371-376. A71-26879 ii The RNAV thing. Mark Lambert (Elliott The present status of the European Airbus is discussed giving Flight Automation, Ctd , Rochestet. Kent, England). Arcraft Engi- attention to the flight trials of the first prototype of the A.300B high neering, vol. 43, Apr. 1971, p. 8-10. Examination of the various solutions to the problem of capacity transport aircraft which are to begin in about 18 months time. Approximately one year later the first A 3008 aircraft could be providing an area navigation facility. In area navigation, all routes are making their debut in scheduled service at European airports It is defined as beatings from the beacons, not as tracks. In a system developed by Decca Navigator Co. and Ambac there are three control pointed out that the Airbus program has entered a iiew phase since and display units by which the crew operates and receives informa Airbus lndustrie was founded by French and German partners in tion from the navigation computers. Marconi offers a computer December 1970. A standard and a long distance version of the driven projection map display. Some aspects of Aeronautical Radio, aircraft are to be manufactured Questions of development phase Inc. (ARINC) standards for area navigation are discussed F.R.L. financing and expenditure are considered. some design data are presented, and sale prospects of the aircraft ale evaluated G.R

A71-26880 # Airborne communications systems. B. H. L. Blake (Marconi-Elliott Avionic Systems, Ltd., Chelmsford, Essex, A71-26939 An application of the method of dimensional England!. Aircraft Engineering, vol. 43, Apr. 1971, p. 11, 12. perturbations to compressible flow. Stefan Nadir (Northrop Corp., Description of the development of aeronautical radio com- Hawthorne, Calif.). Zeitschrlft fur angewandte Mathematik und munications and the different systems in use. Of the three basic Physik, VOI.22, Mar. 25, 1971, p. 257-266. 6 refs. systems, VHF, HF, and UHF, VHF is the most universal, while the The Taylor-Maccoll problem - i.e., the problem of steady. HF system is used for long range communications. Reliability is supersonic, isoenergetic flow of a thermally and calorically perfect emphasized as the keystone of equipment design. F.R.L. gas past circular cones at zero angle of attack - is investigated using the perturbation series approach developed by Garabedian (1956) for the study of axisymmetiic free jet problems. The solution of the A71-26881 /! The development of terrain following radar. R. problem is obtained by perturbing its counterpart in plane flow - J. Starling and C. M. Stewart (Ferranti, Ltd.. Hollinwood, Lancs., namely, supersonic flow past wedges It is found to agree well with England). Aircraft Engineering, vol. 43, Apr. 1971, p. 13-15. the exact numerical solution by Sims (19641. O.H. Account of thc progrcss made with an airboriie guidance system for low flying military aircraft. The penalty which must be paid for the advantage of low-level attack is the dangct of the aircraft striking A71-26946 High-speed methods for testing reliability and the ground, particularly at night or in bad weather. A radar device is fatigue life of airplane structures, I. V. lakobson (Gosudarstvennyi describc4 which when mounted in the nose of a low flying aircraft Nauchno~lssledovatel’skii lnstitut Grazhdanskoi Aviatsii, MOSCOW, scans the terrain ahead and determines the path in elevation which USSR). (Problemy Prochnosti, vol. 2, Api. 1970, p. 30-35.) Strength the aircraft must follow to clear the ground by the required height. of Materials, Apr. 1970, p. 325-330. 5 refs. Translation. This height. selectable by the pilot, can be anywhere between 200 Examination of the principles underlying methods for planning, and 1000 ft. F.R.L. realization, and evaluation of accelerated tests of passenger aircraft

358 A71 -27100

under operational conditions. Topics discussed include (1) Selection A71-27016 Microwave applications of reinforced plastics. of the number of aircraft subjected to testing under operational con- J. A. G. Thomas. Composites, vol. 2, Mar. 1971, p. 4648. ditions, (2) evaluation of data obtained by means of approximate Brief description of the use of reinforced plastics components in formulas, (3) determination of damage accumulation in the tested radar systems, particularly radomes and antennas. Large numbers of aircraft, and (4) selection of the overhaul time for aircraft under reinforced plastic radomes have been produced for the Thunderbird current operation on the hasis of failures observed in selected air- missile program, and nose radomes for the prototype Concorde SST craft. Z.W. have been developed and produced. The Concorde radomes are constructed by the method of molding between matched metal tools. The plastics molding of an antenna is made to reflect by coating the A71 -26952 = Structural-endurance problems for rotor disks concave side with metal. The surface of the mold is prepared and a in turbine engines (Zagadnienia konstrukcyjno-wytrzymaloiciowe thin coating of resin mix is applied and allowed to almost gel. Zinc or tarcz nosnych wirnikow silnikow turbinowych). Stefan Szczecinski. aluminum is then sprayed onto the mold surface gel coat and allowed ~eClJrJikaLornicza I Astronautyczna, vol. 26, Mai. 1971, p. 7-11,21. to gel. The component is then layed-up by hand in the normal way. 9 refs. In Polish. M.M. Analysis of loads imposed on compressoi, ventllator, and turbine iotoi disks havlng laige central holes (up to 0.7 times the outer diameter of the disk). Formulas are given for stress distribu- A71-27040 Performance testing of fluorosilicone hydraulic fluid in high temperature aircraft piston pumps. George J. Quaal tions in such disks as a function of hole radrus, matelial density, and Harry M. Schiefer (Dow Corning Corp., Midland. Mich.). rotational speed, blade loading, and heatlng uniformity. Permissible (American Sociery of Lubrication Engineers, Annual Meeting, 25rh. pel manent deformations ale defined. T.M. Chicago, //I., May 4-8. 1970.) Lubrication Engineering, vol. 27. Apr. 1971, p. 115122. 6 refs. The properties and functional aircraft hydraulic pump testing of A71-26953 f Determination of the mutual aerodynamic a structurally modified fluorosilicone fluid are described. The effects of SM-1 helicopters during takeoff and landing (Ustalenie fluorosilicone hydraulic fluid, designed primarily for SST and other wzajemnego oddzialywania aerodynamicznego imigiowdw SM-1 future high performance aircraft, was subjected to three aircraft podczas startu i Iqdowania). Mieczyslaw Lekowski and Jozef Petulski. Technika Lotnicza iAstronautyczna, vol. 26, Mar. 1971. p. hydraulic piston pump tests. Included were a 200 hour test with a 12-15. In Polish. 160 F Off-Set Pump, a 170 hour test with a 275 F Hlgh Speed Aerodynamic measurements and calculations were performed on In-Line Pump, and a 1300 hour High Temperature Test with a 400 F SM-1 helicopters to determine minimum runway distances for safe In-Line Pump. Testing was conducted at a maxlmum fluid tempera- simultaneous landing and takeoff operations. Gust velocities in the ture of 460 F. Fluid properties, which were monitored during each rotor wake around the helicopter are given as functions of distance test, showed no significant changes after a combined total time of from the craft both on the ground and at different hover heights. 1470 hours of pumping and no fluid make-up. Inspection of the Rotor blade rigidity was measured, and deflection amplitudes are pumps at the end of the tests indicated that each pump could be given as functions of gust velocities from a combination of wind and operated successfully with the fluid above the design temperatures of the pumps. (Author) adjacent-helicopter effects. T.M.

A71-27051 On the accuracy of Merk’s method for solution laminar boundary-layer equations. G. Abad and W. R. A71-26954 tl Fundamental problems in the prproductbn of of laminated aircraft structures (Podstawowe problemy wytwarzania Schowalter (Princeton University. Princeton, N.J.). Applied Scien- laminatowych konstrukcji lotnicrych). Hleronim Oltarzewski. tific Research, vol. 23, Mar. 1971, p. 426-430. 8 refs. Technika Lotnicza i Astronautyczna, vol. 26, Mar. 1971, p. 16-18. Results for the local drag coefficient, computed by a one- and 21. In Polish. two-term Merk expansion 11959). were compared with drag coef- Discussion of the relative importance of initial material proper- ficients computed for more accurate solutions. From the results, a ties. impregnation, shaping, hardening, and stl uctural design in the simple correction procedure was developed which should permit efficient mass production of reinforced laminates for the aircraft rapid and accurate estimation of drag coefficients from the Merk expansion in regions upstream of the stagnation point of shapes wlth industry. Problems arising from ingrained traditional concepts Of design and production are deflned, and some specific causes are listed surface profiles likely to be of physical interest. O.H. .for the relatively stagnant state of laminate fabrication in Poland. T.M. A71 -27063 ff Aerodynamically induced noise or condenser microphones (Das Windgeriusch von Kondensatormikrophonen). P. Koltzsch (VEB RFT Messelektronik, Dresden, East Germany) and A7126991 Thrust measurement of great accuracy of H.-J. Bauer (Dresden, Technische Universitat. Dresden, East aeronautical propulsion systems giving particular attention to a Germany). Hochfrequenztechnik und Elektroakusrik, vol. 79. Dec. hydraulic device for measuring the force. I (Schubmesrung grosser 1970, p. 225.234, 21 refs. In German. Genauigkeit an Flugtriebwerken unwr besonderer Beriicksichtigung It is pointed out that sound generated aerodynamically deter- einer hydraulischen Kraftmeaeinrichtung. I). Joachim Frubose. mines a lower limit for the measurement of acoustic pressure levels. Archiv fur technisches Messen und industrielle Messtechnik, Apr. The dependence of this limit on the velocity and the turbulence of 1971, p. 69-72. In German. air flow is investigated taking into consideration conditions in a Requirements regarding test installations for measuring the condenser microphone, It is found that the aerodynamic sound thrust of propulsion systems are discussed and approaches for depends on the flow direction and that the energy spectrum of the meeting these requirements are considered. Cost and characteristics flow turbulence determines the aerodynamic sound spectrum. of mechanical, electrical and hydraulic systems for the measurement Aspects of a standardization of aerodynamically induced noise are of force are compared. The hydraulic systems combine accuracy Of discussed, and questions regarding a practical application of the about 0.1% with a superior degree of insensitivity against shock. A obtained results are considered. G.R. device consisting of a cylinder and a piston in which friction effects in the direction of the force are practically eliminated is described. A A71-27100 .* Statistical methods of determining the dimen- change in the force to be measured causes a change in the position of sions and concentrations of various inhomogeneities from satellite the piston. This change in piston position causes a change in the oil and aircraft measurement data (Statisticheskie metody opredeleniia pressure, which is measured, because of changes in the width of the razmerov i kontsentratsii razlichnykh neodnorodnostei PO dannym opening for the passage of the oil due to an.appropriate design. G.R. izmerenii so sputnikov i samoletov). N. I. Vul’bson (Glavnoe

359 A71-27123

Upi.avlenic Gidiometeorologicheskoi Sluzhby SSSR. lnstitut A71-27144 4 Planning of transportation operations at Prikladnoi Geofiziki. Moscow, USSR) AkadeIJliia Nauk SSSR, AEROFLOT (Die Planung der Beforderungsleistungen bei der Izvestiia, fizika Atmosfery i Okeana, vol 7, Feb. 1971, p 151-163. AEROFLOT). 0. Ovchinnikov (Aeroflot, Sovtet State Airlines, In Russian Moscow, USSR). Technisch-okonomische Informationen der zivilen A mrthod is proposed for determining the distribution of circles Luftfahrt, vol. 7. no. 2, 1971, p. 106-111. In German. randomly situated on a plane. or of spheres in space, with respect to A new planning methodology introduced in Sovtet civil aviation thcit diatnetet s The distributions and concentrations are detetmined and adapted to the new system of economic planning IS described. from the distribution of the tat-gest cross sections obtained by Principal objectives of this methodology and new planning criteria intersecting the citcles by an arbitrarily ditected strip or tntetsecting and parameters are discussed. Organizational principles adopted fot the Iiy spheres an albitrarily directed cylindrical tu&. Tables ate pian prepararion and iuiiiiinlerii dte uuiilld. n".rl. I, presented, tising which the distt tbution with respect to dimensions of citcles in ii plane Cdn lie easily determined for vatlous widths of the intersecting sti ip. The tctchnique proposed IS useful for improving the A71-27150 Analogue recursive computer. R. J. Lamden. J inlet pretation accuracy of aerial photographs. cloud characteristics, Archer, and A. Maybanks (Ultra Electronics, Ltd., London, England). Institution of Electrical Engineers, Proceedings, vol. 1 18. dnd simildi appicntions V.P. Mar.-Apr. 1971, p. 486-492. Research supported by the Ministry of Technology. A71-27123 Inherent vibration damping of helicopter Description of a control computer which uses a serial digital blades. Wilftetl E B'ikPi (Southwect Reswrch Institute, San Antonio, program to control an arithmetic unit and storage system working Tex.). Interr~~t~or~alJocirnal of Meclia~~~calSciences, vol 13. Feb entirely in the analog mode. Storage is capacitive, using field-effect- 1971, p 157 170. Contract No. DA 31 124 ARO(D) 356 transistor switches for data selection. Using conventional techniques. Comliarison ot the results of extensive expet ttnents on damping speeds ot 20 microsec per arithmetic opeidtion are readily ab of vtbrations in helicopter main irotor blades with those obtatned by tainable. The first application of this computer is to aircraft-gas- theoretical and semiempirical methods of predicting blade damping. turbine control. A control program, for example, of a Rolls Royce The feasibility of numetical solutioii of blade vibration equdttons Olympus 5938 engine occupies 120 instructions, and the computa- which include complicated darnping effects is also dernonsttated. tion has a recursjon time of 3 msec. An accuracy of within 0.1% is Nonlinear air darnl>ing IS shown to he relatively ttiiimportant for all obtainable. (Author) but the funddnletltal hendtng vibration iiiude Dainliing foi higl1t.i mode5 is essentidlly independent of amplitude but varies stqriiftcdntly with frequency For much of the experimental dat'i. internal A71-27169 ? Theory of an inertial navigation system con- damping of the blade matetlal IS ai)pdtciitly the pritndiy SOUICF of structed on the basis of a gyrohorizon compass (K teorii inertsial'noi damping. (Author) sistemy navigatsii, postroennoi na baze girogorizontkompasa). 0. F. Boichuk and V N. Kalinovich. Maternaticheskaia Fizika, no 8. 1970. p. 46 53 10 refs In Russian. Detailed study of the ertors of an inettial system consisting of a A71-27141 #/ Problems and aspects of elaboration of weath- gyrohoiizon compass, a diirictional gyro. and a computer due to er minimum conditions for INTERFLUG aircraft (Problem und vibiattons of the comp~ss.with dllowancr fot side moments applted Aspekte der Erarbeitung von Wettermindestbedingungen fur die to the compass. drift of the diicctiond gyto. and inaccuratr input of Luftfahrzeugtypen der INTER F LUG 1. Erwin Langi ock (Haupt - the initial conditions into the computer, The vibrations of a compass vewaltung der Ztvtlen Lufttahrt, Berlin, East Germany). Technisch- subjected to the action of side moments ate considered. It is shown okonornische Informattonen der zivilen Loftfahrt, vol. 7, no. 2, that the resulting system of diffeicntial equations has the same foim 1971, p. 76-87. 6 refs In German. as the coriesponding system characteiiriny the vihtations of a The methodology necessary for determining weather minima is gyroinertial platfoini. The errors in determining the posttior1 co discussed. Factors affecting this determination are reviewed and ordinates of an object are calculated. This probleln is also found to qualitatively estimated Requirements are presented which must be be equivalent to the andlogous ptoblem for an ineitial system with a included in the methodology Finally, possible approaches to the gyrostabilized pldtfqtm. although it has cettaiii special feattites methodology preparation are examined O.H. ABK

A71-27142 :! Crane and external load flight with helicopters A71-27174 f Motion of a wing of solid profile near a screen (Kran- und Aussenlastflug mit Hubschraubern). Michael Cacpat I (Dvizhenie kryla telesnogo profilia vblizi ekrana). V. N. Ktdvets Tech~~iscli-oko~~o~i~isch~Infort~iatione~i der ztv//en Luftfalirt, vol. 7, Matematicheskaia Ftzika, no. 8, 1970, p 102 107. 6 tefs. In Russian. no.2. 1971. p 8899 InGeitnan. Solution of the piobleni of the niotioli of a wing of soltd piofile Problems involved in using helicopteis 4s a inatetial handling neat a solitl wdll 01 a free surface by employing the acceleiatton equipment fot tianspott ant1 crane opet'itions ale discussetl. Specific potential method A solution to the sitigulat tntegtal eqtt'ition fot featutes of these operations peifot lied hy helicopteis ate outlined this problem IS found by an approximate method involving the use of Factots foi assessing the apl~licahilityof helicopteis to petfoitnl such a small parameter As a result, a foimula IS obtdincd fot the lift ope I J t ions di e ex mii tied . F i nal I y , the eco ti0in i c ef f ixc t ivenesb of t Iiesr coefficient of the wing ptofile. on the bdsis of which L~ calculation I\ op~'tdtionsis c~il~itl~itt~l 0.H made for a specific case ABK

A71-27143 Examination of operational aspects of motion A71-27217 ,u An asymptotic theory of the jet flap iii three sequences on airways (Betriebnechnologische Untersuchungen von dimensions. Naoyitki Tokuda (Caml,rtdgtx Univetsity, Cambrtdgt' Bewegungsablaufen auf Luftstrassen). Rolf Kuttner. Technisch~ England). Jocinial of Fluid Meclial~lcs,vol. 46. Apt. 27. 1971. p okonornische Informationen der zivilen Luftfahrt, vol. 7, no. 2, 705-726. 18 refs. 1971, p. 100-105. In German. A unifot mly v31id asymptotic solution IS cotlstt itcttxi foi Actual and schedirled motion sequences are described by means three-dirrietision,il jet flapped wings by the mt'thoti of tnciti:hrd of mathematical statistical methods. Equations are derived for asymptotic expmsiotis foi high aspect iattos. The flow is aswnicd to calculating the so-called 'advance times' by means of which, provided be inviscid and inconiptcssihl~~,inti is fotmcil.ttcv1 on the thin milotl that a prescrilied altitude path diagram is observed. flight motions theory in accoidaiice witti the two-dimeii~ioi~~~lSpuici' (1SG1 can he exactly adaptrri to an airway so that the shoitest possible theory. Using this fot t111t~dtiOii. J physicdl picttiii' is i)trsr~iitcdthdl not only illuminates the basic stiuctuie of tlic flow ficltl, but 4x1 flight seqitenct' is achieved O.H. greatly facilitates thc analysts. Thc ,isytii~itotic sol~tttotiolitdtiit'd I\

360 A71-27 3 27

consistent with this picture. After deriving the formula for aero- Fechek (USAF, Materials Laboratory, Wright~PattersonAFB, Ohio) dynamic forces on wings. the result of the analysis is applied to flat American Sociery of Mechanical Engineers, Design Engineering wings of various wing plan forms such as cusped, elliptic, and Conference and Show, New York, N.Y., Apr. 19-22, 1971, Paper rectangular wings. M.V.E. 71-DE-13. 9 p Members, S1.00; nonmembers. S2.00. Review of progress in advanced composites, which in five years have come from a laboratory curiosity to a material used in the A71-27220 8 Vortex shedding from circular cylinders at low production of primary aircraft structures. Graphite composites now Reynolds numbers. M. Gaster (Ministry of Technology, National compete with boron composites on an equal basis. Efforts to Physical Laboratory, Teddington, Middx.. England). Journal of Fluid combine graphite filaments into structures have utilized both organic Mechanics, vol. 46, Apr. 27. 1971, p. 749-756. 6 refs. and inorganic matrix materials, with most of the effort being applied Experiments on slightly tapered models of circular cross-section to the epoxy systems. The costs of graphite composites have been have shown that the vortex wake structure exists in a number of continually decreasing, and weight savings for components such as discrete cells having different shedding frequencies. Within each cell speedbrakes, horizontal stabilizers, and spacer beams range from 18 shedding is regular and periodic, the frequency being somewhat to 60%. F.R.L. lower than that from a parallel cylinder of the same diameter. A similar type of wake behavior has also been observed on a parallel A7127324 Applications of self-organizing and learning model in a nonuniform mean flow. These results suggest that the ff control to aeronautical and industrial systems. R. Barron discontinuities in the shedding law observed by Tritton could arise L. (Adaptronics, Inc.. McLean, Va.) and C. W. Gwinn (USAF, Avionics through nonuniformities in the flow. (Author) Laboratory, Wright-Patterson AFB, Ohio). American Society of Mechanical Engineers, Design Engineering Conference and Show, A71-27247 Let’s do away with fog. William H. Best, Jr. New York, N.Y., Apr. 19-22, 1971. Paper 71-DE-22. 13 p. 16 refs. Defense Management Journal, vol. 7. Spring 1971, p. 41-47. Members, $1 .OO;nonmembers, $2.00. USAF-sponsoredresearch. Discussion of fog dissipation techniques and the cost of fog This paper describes a broad area of development in adaptive dissipation. Both cold and warm fog are considered. The existing fog control systems, emphasizing several recent applications. Two dissipation techniques and their efficiency are briefly described. principal lines along which development has occurred since 1961 are: Particular emphasis is placed on the economic problem of whether those systems that use short-term memory retention, and those fog dissipation can compete in the field of benefits and cost systems that use long-term memory retention. Both employ logic avoidance. By several examples illustrating the problem, it is random searches to find appropriate parameter values within the demonstrated that fog costs resources, and that dissipation of fog can controller. Self-organizing systems, use a probability state variable recover these resources for use in a more productive manner. O.H. algorithm, continually updating internal probability distribution fUnCtiOnS by WniCn Successive coriirui dCiiUi-Ij &e mieiiiad. !?eYd:Zs of two recent applications are presented. Learning control systems A71 -27277 High temperature aerodynamics with electro- use multimodal guided random searches to adjust parameters of the magnetic radiation. John D. Anderson, Jr. and Eva M. Winkler (U.S. system, given only a representative data set as the basis for training. Navy, Naval Ordnance Laboratory. White Oak, Md.). IEEE, Proceed- Two representative applications of stateestimation networks are ings, vol. 59, Apr. 1971, p. 651 -658. 39 refs. discussed to illustrate the power of the learning control system In recent vears, the basic study and concepts of the interaction method. (Author) between radiation and matter have found application in aerodynamic oroblems of engineering interest. This paper discusses three such A71-27325 b’ Controlling structural fatigue through adhesive problems actively being examined at the Naval Ordnance Laboratory bonding. M. A. Melcon and V. D. Moss (Lockheed-California Co., (NOL): (1) thermally radiating high-temperature shock layers, (2) Burbank, Calif.). American Society of Mechanical Engineers, Design electric arc-driven wind tunnels, and (3) gasdynamic lasers. Special Engineering Conference and Show, New York. N. Y., Apr. 19-22. emphasis is given to the area of gasdynamic lasers. New research 1971, Paper 71-DE-27. 17 p. Members, $1 .OO;nonmembers, $2.00. results recently obtained at NOL are presented and discussed. Review of fatigue improvement potential through bonding in Moreover, in the same context, an overview IS made of each subject the Lockheed L-1011 TriStar. utilizing analysis of joint variables and in order to whet the enthusiasm of the reader to look more test data. Bonding in the fuselage is discussed with reference to thoroughly into these interesting areas, whether he be an aero- joints, doublers at cutouts, and fail-safe straps. The integration of the dynamicist, electrical engineer. plasma physicist, or any physical bonding process with the structural arrangement is described, as well scientist or engineer interested in radiation and matter. (Author) as the results of full-scale component development tests. Both fatigue test and fail-safe test data are presented. Structural requirements A71-27312 L Holographic detection of microcracks. C. M. pertinent to metal-to-metal bonding in a relatively large aircraft are Vest (Michigan, University. Ann Arbor, Mich.), E. L. McKague discussed. together with past experience that indicates the necessity (General Dynamics Corp., Fort Worth. Tex.), and A. A. Friesem of these requirements. The usefulness of adhesive peel strength as a (Radiation. Inc.. Advanced Optics Center, Ann Arbor, Mich.). parameter for the design of bonded structures incorporating the American Society of Mechanical Engineers, Paper no. 71 -Met-C. relatively thick elements of large aircraft is shown. F.R.L. 1971 5 P. 10 refs. Memhers. S1.00; nonmembers, $2.00. Research sponsored by the General Dynamics Corp.; Grant No. DA-AG-46-69- ~71.27327 The design and application of the Traversing C-0017 f! Thls paoer desci ihes the application of optical holographic Infrared Inspection System (TIRIS). S. E. Cohen (Lockheed-Georgia interferometry to the detection of microcracks in metals. In Co., Marietta, Ga.). American Sociery of Mechanical Engineem, Design Engineering Conference and Show, New York, N.Y.. Apr. particular, detection of iadial cracks extending from bolt holes in 1971, Paper 71-DE-37. 10 p. 11 refs. Members. $1.00; high strength airciaft steel was studied. The method was found to 19-22, have several advantages over currently used detection methods. The nonmembers. $2.00. Description of a Traversing Infrared Inspection System designed result5 of the holographic study compared favorably with indepen- primarily for high-volume production inspection Of c-5 aircraft dent retults ohtained hy magnaflux. eddy current, and X-ray fail-safe strap panels. These panels are bonded laminates of 0.020 in. inwection Some evidence of a possihle ability to detect untempered thick titanium and 0.125 in. thick aluminum. The System is flexible martwxitc rl(:iicisitc was also noted. (Author) enough to be used for the development of specla1 techniques such as the detection of entrapped water in aluminum honeycomb and the A71-27323 fi Advanced composites efforts - A status report inspection of advanced structural composites. The system injects of Air Force programs with graphite reinforced composites. F. J heat into the panels by means of hot air guns. Imperfections as small A71 -27330 as 0.30 in. in diam are displayed on an 8 x 10 in. cathode ray tube in tion between experimental variable geometry test data arid calculated real time. The inspection scanning rate is 4.3 sq fthin. A Polaroid value based on the present program is also included. Results have camera is used to produce thermograms which define the size and shown that a wing pivot system can indeed be designed with much shape of voids, disbonds, and delaminations which are located greater efficiency and speed. O.H. directly on the panels with a unique marking device. Principles of operation are explained in detail with the aid of representative A71-27412 Flame-retardant silicone elastomers for air- thermograms made with the system. A blackbody calibration device craft. T. L. Laur and L. B Guy (Dow Corning Corp.. Midland, and special facilities were also designed for the system. It was found Mach 1 SAMPF Jcxtr~a!,svs!. 7, ,Asp: !.!:y 1973, i;. 21-24, 3:. 7 refs. that no emissivity costing is required for the inspection of the A new rubbet technology was developed and new silicone fail-safe panels because of the surface characteristics of titanium, rubber stocks are produced that consistently exceed aircraft flame (Author) specifications. The sensitivity of the new materials to moisture was A71-27330 # Hypersonic flow around a thin three- minimized. and they are also easier to fabricate and significantly lower in cost than the early flame retardant silicone rubbers. The dimensional body (Giperzvukove obtikannia tonkogo prostorovogo new stocks have much improved resiliency over the early high-phenyl tila). L. I. Dzvonik (Kiivs'kii Derzhavnii Universitet, Kiev, Ukrainian content materials because they react better to low cure temperatures. SSR). Akademiia Naiik Ukrains'koi RSR, Dopovidi, Seriia A - The new materials are not subject to heat aging and have excellent Fiziko-Tekhnichni i Matematichni Nauki, vol 33, Mar. 1971, p. weatherabilitv Z.W. 220 223. In Ukrainian. Theoretical analysis of hypersonic inviscid flow around a thtn delta wing at small angles of attack. Equations of motion and A71-27413 Graphite epoxy flight spoiler - Design! boundaty conditions for a general class of disturbances are derived analysis/fabrication. Leo C. Jensen (Hercules, Inc., Magna, Utah). within the framework of the asymptotic hypersonic theory of small SAKPf Jounia!, vo!. 7, Apl. blay i97i. p. 25-26. pertuibations Flow dround the body is divided into an outer region Presented are discussions on the design, analysis and fabrication of uniform flow arid a central region of conical flow. The outer of a commercial aircraft flight spoiler utilizing graphtteiepoxy region is studied in a cross sectional plane, and numerical calculations composite skins. The unit is designed so that the fibers within a given are performed for finite values of the hypersonic siniilarity parameter ply lamina are multidirectional to provide a greater stiffnesdskin and for an infinite freestteam Mach number in the limiting case A weight ratio than available with conventional unidirectional layups. qualitative pattern of streamline behavior is constructed, together The success of this multiangle ply technique is demonstrated by test with the distribution of the transverse velocity component along results and compatison with conventional ply skin designs and these lines. Analysis of the results conftims the presence of a aluminum skins. (Author) singulai ity reyion near the centidl symmetly plane where addttional Studies of the flow air reciuitecl A71-27437 Performance analysis of the modulation cancellation altimeter. Sol Rauch and Howard A. Grant (Canadian A71 -27339 :! Generalized conditions for the absolute invari- Marconi Co.. Montreal, Canada). If€€ Transactions on Aerospace ance of an aircraft's longitudinal-motion coordinates relative to andElectronic Systems, vol. AES~7.Mar. 1971, p. 367-378.6 refs. atmospheric disturbances (Mzagal'neni umovi absoliutnoi invariant- The performance of the modulation cancellatiori altimeter is nosti koordinat pozdovzhn'ogo rukhu litaka vidnosno atmosfernikh investigated. Several sources of errot are considered. specifically: ( 1) zburen'l. V. S. Mechetiiii Avtomatika, vol. 16. Jan-Feb 1971, p. terrain averaging error; (2) output noise fluctuations; (3) errors due 10 15 5 tefs (ti Ukrdiiiian to phase shifts; and (4) acquisition ambiguities. The predominant A pieviously detcribed concept of the physical reducibility of parameters affecting these errors are investigated with a view towards control systems is used to derive genetalired invariaticr conditions optimizing the performance of the altimeter. (Author) for the coordinates of longitudinal motion. Simultaneous thrust variation. ruddet cleflectioti, and flap-deflection control rules are A71-27450 1: Flow of a two-phase medium with solid given for counteracting vrrtical and horirontal wind gusts Cotidi particles around a thin profile (Obtekanie tonkogo profilia dvukhfaz- ttons for longitudinal coordinate invariance relative to verticdl wind not sredoi s tverdymi chastitsami). N A. Mamadaliev and Kh A gusts are also defined for an aircraft without horizontal contiol Rakhmatulin. In Waves in nonelatic mrldia (Volny v nruprugikli surfaces. Various technical considerations associated with piactical sredakh). Eclitrd by N 2 Dmittenko Kishitiev, reali7ation of the theoretical contiol laws are evaluated. T M. Akademita Nauk Moldavskoi SSR, 1970, p 146 152. 7 refs. In Russian. A71-27410 !J Rapid analysis methods for the design and The two dimensionti1 liiiearizetl problem for the flow of a optimization of wing pivot systems for variable geometry aircraft. two ph'ise, supetsonic. bat ot iopic metliiim with solid particles Ken SChWdttz (USAF, Flight Dynamics Laboratoty. Wright Patteison around a thin profile IS studied with allowance foi elastic collisions AFB. Ohio). Stanley Mellin, atid Leonard Ascani (North American of the particles against the profile surface The boundary condition Rockwell Cotp.. Los Angeles. Calif 1 Anier/cari Astronaiitical iinposrcl on the gas velocity is the same as thdt fot the case of a Society a/id An~er/c;rfr lristittitc of Acro/iaotics and Astro~iaiitics, petfect contititious medium. This condition 15 not valid fot the Variabk Gconietry and Expariddhle Striictiires Cof~feretice, paiticlc velocity which has a component tiotrnal to the solid sutface, A/J~7/JC//IJ,ca/!f., Apr 21-23, 1971, AIAA Papcr 77-404. 48 p 11 tefs. Mctnhcis, $1 50, iiotitii~~tnbcts,$2.00 giviny rise to a thitd type of reflected flow. As a result. a tegion of three-velocity flow arises between the shock wave and the solid Thr piolili'in of devclopinq rapid, low-cost analysis tecliniqucs body. This icgion is separated by a tlivitlitig line from the region of to assess thv c*fficiiwcy of advanced 01 exicting varialile gerimetiy two-velocity flow If the position of the solid ptofile is spcxified, the aplilicdt tons to aircr,ift dcsiqti is investigated 111particttl;tt, a progiain location of this dividing line can be obtained by solving the flow is dtscusscd which IC corici't iied witti the (tiuctittal mechanical design ptoblem, antl inversely, the position of the body cat1 be determined of a wiriq pivot systc:in InclLitli~d in the progtaiii titi! all ciittcal va'itablcs existing Iwtwwti the points of basic aitcraft definitioti fot a specified locdtion of the dividing line. The pioblem IS solved for large and small concenttations of solid particles in the flow T.M. thiough tu the final atid coiiil>liiti' dcstgii of the wing pivoting systeni itself. Siich itettis ds Ioitcl andysts. sttcss deterniination, deflected shapes, fattgu~~analysis. thct riiiil stiesws. ht!ai ing wciit aiitl pet A71-27467 9 Review of testing techniques for transonic fot iTiailCe, dnd 5tlllCtllral Olltimildti~tiCOtlslttltte the output of the airfoils. I . Apparatus for commercial tests at S3MA. II - Experi- progiam. Additional area? also included are follow on detailed desigri mental study of wall corrections at R1 Ch. (Critique des techniques methods utilizing refincc! two tlimensional antl expandrd three d'essais de profils transsoniques. I - Dispositif d'essais industriels a dimensinndl finitc Plrmeiit tecliniqitrs. A discussion of the coriela S3MA. II - Etude experimentale des corrections de parois a R1 Ch.).

362 A71 -27475

M Baziti (ONERA, Modane. Savoie. France), J. Ponteziere, and R. Attempt to show that the testing of medium speed airfoils in a Bctn.wd-Guellt. (ONERA, Meudon. Hauts-de-Seine,France). Associa- laminar boundary layer does not permit distinguishing the onset of tioil Fraricaise des Ing6riieiirs et Techniciens de I'Aeronaurique et de transition. A study of airfoils at different levels of speed fluctuation I'Espsce. Colloque d'Aerodynamique Appliquee, 7th. Modane, provides a sufficiently selective transition criterion. The development Savoie arid Ecole Ceritrale L yonnaise, Ecully, RhBne, France, Nov. of the instantaneous signal and the observation of the power spectral 4.6,7970, Paper. 35 p. 10 refs. In French. density make it possible to better understand the concept of Discussion of the testing of transonic airfoils in two-dimensional instability, amplification of perturbations within the laminar bound- flow in the ONERA S3MA and R1 Ch. wind tunnels. The S3MA ary layer, and the appearance of turbulent gusts. An extensive apparatus is directed toward developments of a practical character. It appendix considers the possibility of accurately predicting the makes it possible to carry out tests on large models over a wide range turbulent behavior of a wing at high Reynolds number. F.R.L. of Reynolds numbers. The study of helicopter blade elements with chords identical to those of rotor blades tested in the SlMA wind tunnel makes comparisons possible. The systematic study of wall ~71-27471 # Lateral control of high-speed aircraft with lift interactions, indispensable for understanding of aerodynamic coef- devices (Controle lateral des avions rapides fortement hyper- ficients, is carried out in the R1 Ch. wind tunnel, 'which is sustentes). R. Guiot (Breguet Aviation, Velizy-Villacoublay, particularly well adapted for basic research at high Reynolds Yvelines, France). Association Franpise des Inp3nieurs et numbers. Preliminary results indicated corrections which are ap- Techniciens de l*Aeronautique et de I'Espace, Colloque &Aero- plicable to test conditions in the latter wind tunnel. F.R.L. dynamique AppliquPe, 7th, Modane, Savoie and Ecole Centrale Lyonnaise, Ecully, Rhbne, France, Nov. 4-6, 7970, Paper. 35 p. In French. A71-27468 ,+ Measurement of unsteady aerodynamic forces The criteria for wing design imposed by the requirement of high and propagation of perturbations during rapid variations of'the angle speed for short takeoff aircraft are examined and a relatively thin of attack of an airfoil (Mesure des efforts aCrodynamiques in- sweptback wing with small aspect ratio is considered. The dis- stationnaires et propagation des perturbations lors de variations advantages of such a design are also investigated. An appropriate rapides I'incidence d'un profil). A. Damongeot (Societe Nationale de design for a fuselage is described and the position for the tail lndustrielle Aerospatiale, Chitillon, Hauts-de-Seine, France). Associa- assemblies is shown. It is found that an aircraft of the design tion Francaise Ing6nieurs et Techniciens de I'Aeronautique et de des considered has very bad takeoff characteristics. It is therefore I'Espace, Colloque d'Aerodynamique AppliquPe. 7th, Modane, necessary to employ lift devices, Designs for a flap and a spoiler are Savoie and Ecole Centrale Lyonnaise, Ecully, RhBne. France, Nov. shown. Problems of lateral control are discussed giving attention to 7970, Paper. 64 p. 9 refs. In French. 4-6, the effects of spoiler position and form and to aerodynamic Measurement of the unsteady flow around wing sections, modifications of the wing. The lateral behavior of the aircraft is particularly for the case of helicopter blades. The analytic inter- analyzed taking in?o ccn:ideiaiion problems of side-slipping at low pretation is due to the previous work of Wagner and his successors. and high speeds. Inertia effects are considered, and the particular In this linear theory the viscositv fnrces sf :he %id do not intervene; problems of the approach are investigated. G.R. rh..- tile vortex elements released downstream of the airfoil during a variation of the circulation are activated by a velocity Vo in relation to the airfoil. In order to take account of the essentials of the A7127473 # Study of the effect of the marginal vortex viscosity effects the distribution of vortex elements must be defined. from a helicopter blade on the aerodynamic flow around the Experimental comparison with the theory was made in the St. Cyr following blade (Etude de I'influence du tourbillon margtrol isw No. 2 wind tunnel, using a mounting permitting a rapid variation of d'une pale d'Wicopt&re sw I'&!oulement aerodynamique autour de the angle of attack. Comparisons are also made with results obtained la pale suivante). 6. Monnerie and A Tqgner (ONERA, Chltillon- by Boeing-Vertol and ONERA. In the second part of the paper souz-Bagncux, Hauts-de-Seine, France). Association Francaise des experiments concerning the distribution of ?s::ex elements of the lnghieun et Techniciens de I'Aeronautique et de I'Espace. Colloque W-49 XC described. d'Aerodynarnique AppliquPe, 7th. Modane, Savoie and Ecole Centrale L yonnaise. Ecully, Rhbne, France, Nov. 4-6, 1970, Paper. 20 p. 5 refs. In French. A7127469 Measurement of unsteady pressures on stator The basic characteristics of marginal vortices from wings with blades of the S2.MA compressor (Mesure des pressions instation- limited span are investigated, and the effect which these vortices can naires sur aubes fixes du compresseur S2.MA). G. Fasso and R. have on the aerodynamics of lifting surfaces in their neighborhood is Larguiei-. Associarion Fraricaise des Ing6nieurs et Techniciens de explored. The effects of the presence of a vortex in the flow I'Adronatitique et de /'€space, Colloque d'Aerodyriarnique Appliquee, 7th, Modane, Savoie and Ecole Centrale Lyonnaise, upstream of a blade are discussed, and effects of the blade form are considered. Velocity measurements are described, and a method for fcully, RliBiie, France, Nov. 4-6,7970, Paper. 13 p. 13 refs. In French. calculating the effect of a vortex on a wing is presented. A photograph is provided showing the marginal vortices in a hydro- Demonstration th6t it is posstble to obtain mean periodic values dynamic tunnel. The noise spectrum for a rectangular blade tip and of pressures on flow straightening blades of a large-sized axial compressor, Four contlguous blades located in the lower part of the for a trapezoidal blade tip is shown. G.R. flow stiaightener weie fitted with short response time pressure detectors. The results showed that a preliminary idea of the A71-27475 it Theoretical and experimental study of Made magnitude of the vibration-exciting forces could be obtained, as well camades in supersonic flows (Etude theorique et exp6rimentale de as of the bphavior of wakes of the totattng wheel and their action on profils de grilles en ecoukment wpersonique). A. Papon and G. the flow sti aightening blades. F.R.L. lnglesakis (IMFM, France). Association Frawaise des Ing6nieun et Techniciens de lIA6ronautique et de I'Espace, Colloque &Aero- A71-27470 # influence of a sinusoidal wall perturbation on dynamique Appliquee, 7th. Modane, Savoie and Ecole Centrale transition (Influence d'une perturbation sinusoidale de paroi sur la Lyonnaise, Ecully, Rhbne, France, Nov. 46, 1970, Paper. 34 p. In transition). P. Gougat (CNRS, Laboratoire d'Aerothermique, French. Meudon, Hauts-&-Seine. France) and J. J. Perrin (Societe Nationale Comparison of theoretical and experimental wave configurations lndustrielle Aerospatiale. Chltillon, Hauts-de-Seine, France). Associa upstream from a simple initial blade cascade contour in a supersonic tion Francaise des lngenieurs et Techniciens de I'Adronautique et de flow. An attempt is made to obtain a blade cascade with an entropy I'Espace, Colloque dlA6rodynamique AppliquPe, 7th. Modane, which is as uniform as possible in the flow downstream from the Savoie and Ecole Centrale L yonnaise, Ecully, RhBne, France, Nov. cascade and to determine the range of variation of the counter- 4-6, 1970, Paper. 38 p. 10 refs. In French. pressure for which this uniformity can be maintained. A.B.K.

363 A71 -27476

~~1.274~6# The high-lift wing. Remarks on the prediction A71-27493 # Thermal behavior of aircraft structural ele- of characteristics (L'aile aux portances elevees . Remarques sur la ments under conditions of aerodynamic heating (Temperaturnyi prevision des caracteristiques). Y. Semezis and J. Gombert. Associa- rezhim elementov konstruktsii letatel'nykh apparatov v usloviiakh tion Francaise des Ingenieurs et Techniciens de I'ACronautique et de aerodinamicheskogo nagreva). V. V. Salomatov. Aviatsionnaia I'Espace, Colloque d'A6rodynamique Applique'e. 7th, Modane, Tekhnika, vol. 13, no. 4, 1970, p. 22-30. 6 refs. In Russian. Savoie and Ecole Centrale L yonnaise, Ecully, RhBne, France, Nov. An approximate analytical method of solving the aerodynamic 4-6, 1970, Paper. 82 p 42 refs. In French. heating problem in general formulation IS proposed. The method is Examination of some problems encountered in predicting the used to determine temperature-field characteristics which can be charx?erirtics of high-lift wings with or without additional high-lift used in engineering calculations of the thermal behavior of aircraft devices. Compromises must be made be?v-;een the qualities desired at elements. It is shown that the heat transfer problem can be reduced high speeds and those desired at takeoff speeds. Attention is given to to the soiuiiuii of a functional eguation containing a term for the existing means of controlling lift or distributing the load on a wing surface temperature. Good convergence of the method of rucces;i:.e by detachment. Particular emphasis is placed on the processes of approximations for this equation is established. This equation yields prediction of maximum lift coefficient and its increase by means of a Volterra integral equation of the second kind for the temperature high-lift devices; these are compared for the case of a moderately in an arbitrary cross section of a structural element. An analysis of long and moderately swept-back wing equipped with conventional the integral equation reveals a linear dependence of the temperature high lift devices. It is considered that improvement in prediction is field on the initial temperature, which can be used as a basis for related to a better understanding of detachment phenomena. Results plotting engineering nomograms. V.P. of current studies are briefly reviewed. aqd various procedures to increase lift by blowing are described. F.R.L.

A71-27494 a Determination of the optimal dimensions of the fuselage of a supersonic transport in the preliminary design stage A71-27477 Elements of calculation for threedimensional (Opredelenie optimal'nykh razmerov fiuzeliazha sverkhzvukovogo aerodynamics in a perfect fluid (Elements de calcul d'aerodynamique passazhirskogo samoleta na etape predvaritel'nogo proektirovaniia). tridimensionnelle en fluide parfait). P. Perrier and W. Vitte (Avions K. lugov Aviatsionnaia Tekhnika, vol. 13, no. 4. 1970. p. 31-37 Marcel Dassault, Vaucresson, Hauts-de-Seine. France). Association 0. In Russian. Francaise des Ingenieurs et Techniciens de I'Aeronautique et de A formula for calculating the cruising flight range as a function /'€space, Colloque d'Aerodynamique AppliquPe, 7th. Modane, of the geometrical parameters of the fuselage is derived. An Savoie and Ecole Centrale L yonnaise, Ecully, RhBne, France, Nov. expression defining the drag coefficient as a function of the same 4-6, 7970, Paper, 39 p. 5 refs. In French parameters IS also obtained. A procedure, based on these formulas, The problems presented by the calculation of three dimensional flows involving an aircraft are examined giving attention to the for determining the optimal fuselage parameters (for supersonic and subsonic transports) from the prescribed volume of the fuselage is important effect of the vortex field on the flow. The three- proposed V.P. dimensional incompressible flow about a slender foil is investigated making use of a numerical iterative method. Nonlinear effects due to ~~1.2~501# Influence of some design parameters of gas. rolling up at the wing tip appear in the results obtained for the lift turbine-engine combustion chamber on the Circumferential coefficient. Problems of the interaction of the vortex sheet with the nonuniformlty of the gas temperature field (Vliianie nekotorvkh surfaces are investigated. The geometry of the vortex sheet is konstruktivnykh parametrov kamery sgoraniia GTD na okruzhnuiu determined, and the velocity field at the surface is considered. G.R. neravnomernost' temperaturnogo polia gazal. Iu. A Spiridoilov and A. V. Talantov Av/ars/orlnaia Teklmika, VOI. 13. no. 4. 1970. P 80-86 In Ruwan A71-27481 The transient response of a coupled plate- * Appioxiinate expiessioils arc dc.1 ived which desci ibe the gas acoustic system using plate and acoustic finite elements. A. Craggs field nonuniformity as a function of the total atea of the holes in the (Alberta. University. Edmonton, Alberta, Canada). Journal of Sound flame tube, the equivalent diamtytr~r.and the spacing between the and Vibration, vol. 15, Apr. 22, 1971, p. 509-528. 9 refs. Grant No. holes along the tube ciicumferencf' It IS shown thdt to each vdlue of NGR-62-025-003. the total hole area thoie corresponds an optimal value of the Plate and acoustic finite elements are used to simulate the equivalent didmctCi which minimizes the citcumfeiential inonuni behavior of a window-room system. The first part of the paper is formitv of the field. Thr minimum value of this nonunifolmlty concerned with the general formulation of the equations of motion decreases with a decrease in the total hole area. Recommendations and a mixed formulation is used: displacements for the plate and for designing the mixing zone of gas-turbine-engine combustion pressures for the room acoustics. In the final part, the equations are chambers are proposed. V.P. solved for a simple window-room system being excited by a sonic boom. The results show that the room response is dominated by the volume displacing and plane wave depth modes. However, at points A71-27502 #/ Calculation of boundary layer separation from near the window, the effects of nonpropagating cut-off modes are an arbitrary curvilinear rotating plate (K raschetu otryva pogranich- significant. The effect of the room on the window is small except for nogo sloia na proizvol'noi krivolineinoi vrashchaiushcheisia plastine). rooms with a small volume. (Author) I. M. Korshin.Aviatsionnaia Tekhnika, vol. 13, no. 4, 1970, p. 87-92 6 refs. In Russian The laminar boundary layer equations foi a rotating plate with a A71-27491 Calculation of the lifting force of a wing with ti surface of arbitrary curvilinear shape are analyzed. The extelnal-flow a rotating flap (Raschet pod'emnoi sily kryla s vrashchaiushchimsia pressure gradient leading to boundary layer separation IS detei mined zakrylkoml. T. S. Patel'. Aviatsionnaia Tekhnika, vol. 13, no. 4, by a method proposed by Bam-Zelikovich (1954) The paramt!teis 1970. p. 10 15. 6 refs. In Russian. leading to separation at a rotating and a stationary bladc aic Crabtree's (1957) two dimensional theory of wing with rotating calculated as an example. V.P. flap is extended to include an asymmetric Zhukovskii profile with a rotating flap. An equation describing the circulation distribution ovet a slender profile of small curvature is derived within the framework A71-27504 H Determination of the optimal Parameters of an of slender profile theory. Two approaches to the solution of this ejector nozzle under supersonic flight conditions (Opredeleilie equation are proposed. It is shown that, in addition to providing optimal'nykh parametrov ezhektornogo sopla v usloviiakh sverkhzvu supplementary lift at the flap itself, a rotating flap increases the lift kovogo poleta). E D Nc-cteiov and V M Shichkin AVI~I~SIOIIII~II~I of the wing by redistributing the circulation on its surface V.P. Tekhr,,ka, vol 13, no 4, 1970, p 101 110 7 irf5 111 R~iw,iii

364 # A71-27554

The parameters of a propelling nozzle that are optimal for A71 -27542 Economics of propulsion systems for air trans- obtaining a maximum thrust coefficient at Mach numbers between 1 port. I. David Huddie. EmAir World, vol. 23, no. 4, 1971, p. 91-96. and 2.5 are analyzed. Formulas for calculating the optimal parame- Outline of reasons for producing new powerplants and the ters are obtained on the basis of a theory of a cylindrical ejector contributions made by powerplant efficiency and size to alrcraft supersonic propelling nozzle proposed by Pearson et al. (1958). operating economics. The continued growth in aircraft size obliges Problems associated with the control of ejector nozzles are the engine constructor to develop larger engines. At the same time examined. The results of the analysis make it possible to evaluate the the need for lower weight and lower fuel consumption to stave off efficiency of ejector nozzles in the Mach number range under square-cube effects, and social pressures for less nuisance from consideration. V.P. aircraft (noise and air pollution) demand more advanced designs. Provided that the advance in technology continues to allow this A71-27505 # Expansion of a turbulent-jet boundary layer in process to occur with each new generation of aircraft there seems to a slipstream (0 rasshirenii pogranichnogo sloia turbulentnoi strui v be no reason why transport aircraft should not continue to increase spumom potoke). V. K. Temnov. Aviatsionnaia Tekhnika, vol. 13, in size since there is no intrinsic natural limit to the size of no.4, 1970,~.111.115. 6refs. In Russian. turbomachinen/. F.R.L. A formula derived by Abramovich (1960) for the expansion of a boundary layer is checked experimentally, using circular and plane A71-27551 fi Survey of viscous interactions associated with jets. A new formula for calculating the boundaries of the flow core is high Mach number flight. Robert H. Korkegi (USAF, Aerospace proposed which, in combination with the momentum equation, can Research Laboratories, Wright-Patterson AFB, Ohio). (American be used to calculate the bounds of a jet boundary layer at the initial lnstitute of Aeronautics and Asrronaurics, fluid and Plasma Dynam- portion of the jet. An analytical expression describing the behavior ics Conference, 3rd. Los Angeles, Calif., June 2s-July 1, 1970, Paper of the axial velocity of the jet beyond its initial portion is obtained. 70-781.)AlAA Journal, vol. 9, May 1971, p. 771 -784. 76 refs. V.P. Viscous interactions which arise in regions of high compression high Mach number vehicles, can result in severely high local A?1-27531 Effects of temporal and spectral combinations on heating and flow degradation. Regions where such strong interactions on the judged noisiness of aircraft sounds. Karl S. Pearsons and may occur on a cruise vehicle are discussed. In relation to these Ricarda L. Bennett (Bolt Beranek and Newman, Inc., Canoga Park, regions, a brief review is given of advances in our understanding of Calif.). Acoustical Society of America, Journal, vol. 49, Apr. 1971. two-dimensional shock wave-boundary layer interaction and separa- pt. 1. p. 1076-1082. 7 refs. tion in compression corners, and such threedimensional interaction The effects on perceived noisiness of spectral and temporal problems as a blunt fin on a surface, flow in an axial comer, and combinations of stimuli at varying durations were determined by 20 shock impingement. It is concluded that much proyos; has been college students in an anechoic chamber. Several recordings of made in analytical prediction of twodimensional laminar inter- turboprop, turhnkn, txbojel, and helicopter flyovers were also actions and a promising approach advanced for the turbulent included in the list of stimuli. The results indicated that the most case; knowledge of departures from twodimensional flow and three- accurate predictor of the judged noisiness was perceived noise level dimensional interactions is still largely empirical and dominantly with tone and duration corrections as outlined by the Federal qualitative, and wen the inviscid flow field is not well known for Aviation Administration (1968) aircraft certification procedure. To many configurations of practical importance. (Author) illustrate the responsiveness of effective perceived noise level (EPNL) over perceived noise level (PNL) in predicting the noisiness of stimuli, the results of the duration test revealed that. at judged equal A71-27552 * Theoretical analysis of vortex shedding from noisiness. 75% of the data were within 4 dB of the standard signal for bodies of revolution in coning motion. 2. D. %uhn. 5. E. Spangler, EPNL with th? FAA :x: x,d htryldteo auration measure as and J. N. Nielsen (Nielsen Engineering and Research, Inc.. Mountain compared to 11 dB for PNL. (Author) View, Calif.). (American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting, 8rh, New York. N. Y., Jan. 19-21. 1970, Paper 70-52.1AlAA Journal, vol. 9, May 1971, p. 784-790. 11 refs. A? 1-27536 The PT6 after 5 million hours. F. R. Cowley Contract No. NAS 2-4765. (United Aircraft of Canada, Ltd., Montreal, Canada). Society Of A theoretical flow model for the steady asymmetric vortex Automotive Engineen, National Business Aircraft Meeting, Wichita, system shed from a slender body in coning motion is described. The Kan., Mar. 24-26, 1971, Paper 710385. 9 p. Members, $1.00; model was developed using potential flow methods and slender-body nonmembers. $1.50. theory, and provides for the calculation of the strengths and The first PT6A-6 turboprop engine, rated at 500 shp. was positions of two unequal concentrated vortices and the resulting delivered in December 1963 with an initial life of 600 hr between force distribution induced on the body. The vortex motion is overhauls. By early 1971, over 4000 engines had been delivered, the determined in the flow field which consists of a portion described by output had grown to 900 shp, and times between overhaul in excess a velocity potential plus a portion due to rotation. The method of of 5000 hr had been reached. The technology spawned by the PT6 determining the initial conditions for the vortex motions is discussed. has resulted in the development, by UACL, of a host of turboprop, Comparisons are made between predicted and experimental values of turboshaft, and turbofan engines, along with industrial derivatives. In side forces and side moments for slender cones and ogivecylinder over 5 million hr of operation, the PT6 has clearly demonstrated how combinations in lunar coning motion. (Author) sound technology by persistent development can meet the exciting challenges of the 1970s. (Author) A71-27554 t. Supersonic boundary-layer transition - Effects A71-27537 Geodetic control for airports. Willard A. of roughness and freestream disturbances. S. R. Pate (ARO. Inc.. Kuncis (NOAA. Div. of Photogrammetry, Rockville, Md.). In: Arnold Air Force Station, Tenn.). (American lnstitute of Aero- American Congress on Surveying and Mapping, Annual Meeting, nautics and Astronautics, Aerodynamics Tesring Conference, 5th, 31st. Washington, D.C., March 7-12. 1971, Technical Papers. Tullahoma, Tenn.. May 18-20. 1970, Paper 70-586.)AIAA Journal, Washington, D.C., American Congress on Surveying and Mapping, vol. 9, May 1971, p. 797-803. 15 refs. 1971, p 489 493. Boundary-layer transition experiments were conducted in the Approximately 2500 geodetic control stations have been estab- AEDC-VKF 12- and 40-in. supersonic wind tunnels at Mach numbers lished on about 750 airports in the United States and its possessions 3 and 4 on an adiabatic wall, 1Odeg total-angle sharp cone. The in addition to regular networks They were estahllshed In connection effects of spherical roughness elements and free-stream disturbances with an airport obstruction charting program and have been tied, by (radiated aerodynamic noise) on transition we’e investigated. The aPproximatc third-order accuracy methods. to the national network large variation in smooth wall transition locations which exists on of horimntal and vertical geodctic control. O.H. models in supersonic wind tunnels of different sizes is shown to

365 A71 -27555

influence trip performance. These studies have also indicated that the the transition Reynolds number but also on the Mach number. A 'effective point' location proposed by van Driest, et al. is relatively comparison of the deduced spot formation rate with the neutral independent of the smooth wall transition location (or free-stream stability curves indicated that the neutral stability curves can be used disturbance and tunnel size) at supersonic speeds. The correlation as a guide to relate the spot formation rate to the transitional parameters developed by van Driest-Blummer and Potter-Whitfield Reynolds number. Calculations of the transitional heat-transfer rate are examined, and their ability to predict the tripped transition on a sphere in supersonic flow agree well with the experimental location is discussed. (Author) results. (Author)

A71-27555 p Eiecrron-beai,i jtiidie; of vi:co??s !!ow in super- A7i-27559 ,+ Geiieralized ae:~dynamic forcec on a flexible sonic nozzles. Dietmar E. Rothe (Cornell Aeronautical Laboratory, plate undergoing transient motion in a shear flow with an application Inc., Buffalo, N.Y.). (Anierican Institute of Aeronautics and Astro- to panel flutter. E. H. Dowel1 (Princeton University. Princeton. N.J.). nautics, Fluid and Plasma Dynamics Conference, 3rd. Los Angeles, AlAA Journal, vol. 9, May 1971, p. 834-841. 21 refs. Grants No. Calif., June 29-July 1, 1970, Paper 70-810.) AlAA Journal, vol. 9, NGR-31-001.146; NO. NGR 31-001-197. Mav 1971, p. 804-811. 20 refs. Contract No. NASw-1668. Experimental investigation of the internal and external flow for A theoretical solution to the title problem is obtained. Unlike nozzle Reynolds numbers in the general range between 100 and 1000 previous solutions in the literature. the present method allows for with nitrogen as the test gas. Electron-beam techniques are used for finite plate dimensions and continuously varying mean velocity and measuring gas density and rotational temperatures at selected points temperature profiles. A computer program has been developed to throughout the flow, Discharge coefficients are also measured. In calculate the required aerodynamic forces for boundary-layer pro- addition, some effects of ambient pressure on the external flow files. These forces are then employed in a nonlinear flutter analysis structure are studied by flow visualization experiments. At the lower previously developed by the author. The theoretical flutter results Reynolds numbers studied, experimentally determined temperatures are compared with the experimental data of Muhlstein, Gaspers. and Riddle and generally good agreement is indicate the existence of a supersonic bubble inside the nozzle obtained. Other physical problems to which the present aerodynamic analysis is relevant expansion-cone, with a subsequent shock-free viscous transition to subsonic flow. These results substantiate the theoretical prediction of include: (1) stabilization of viscous boundary layers by flexible walls, (2) sound wave propagation through shear layers. and (3) shear layer this phenomenon, first made by Rae (1969) in an earlier phase of this program. (Author) effects on control surface aerodynamics at supersonic speeds. (Author)

A71-27556 # Some numerical results on viscous low-density Am-27560 * id Jet aircraft air pollutant production and dis- nozzle flows in the slender-channel approximation. William J. Rae persion. John 8. Heywood, James A. Fay (MIT, Cambridge. Mass ), (Cornell Aeronautical Laboratory. Inc.. Buffalo, N.Y.). (American and Lawrence H. Linden. (American Institute of Aeronautics and lnsritiite of Aeronautics and Astronautics, Fluid and Plasma Dynain- Astronautics, Aerospace Sciences Meeting, 8th. New Yo&, N. Y., Jan. ics Conference, San Francisco, Calif., June 16-18, 1969, Paper 19-21, 1970, Paper 70-715.) AlAA Journal, vol. 9, May 1971, p. 69-654.) AIAA Joi~rfial,vol. 9, May 1971, p. 811-820 35 refs. 841-850. 44 refs. Grant No. NGR-22-009-378. Contract No. NASw-1668. In this paper two aspects of pollution from jet engines are Calculated rrsults for converging-diverging nozzle flows in which viscous effects are important across the entire nozzle cross considered in detail. Firstly, it is shown from reported exhaust gas section. The slender-channel cquatlons are used, with slip boundary measurements that the most important air pollutants are nitric oxide conditions at the wdlls. Thr solution is started upstream of the and soot, and the production processes of these two pollutants are throat, using asymptotlc results for slow viscous llow In a converging then discussed. A kinetic analysis shows that nitric oxide is formed cone. An implicit finite-difference scheme is then used to calculate mainly in the combustor primary zone, in regions of the flow where the pressure and profiles of velocity and enthalpy at successive the equivalence ratio is greater than about 0.8, and that freezing stations along the channel. The cases chosen for presentation show occurs as the gas is diluted and cooled in the secondary zone. the effects ol varying the nozzle geometry, the Reynolds number, Calculated results for nitric oxide concentrations in the combustion and the thermal condition of the nozzle wall. The results suggest products are presented and compared with existing experimental that specific impulse is improved by a throat whose longitudinal data. The mechanisms important in the formation of carbon in the radius of curvature is small, and that exit area ratios as low as 10 fuel-rich regions of the primary zone are reviewed. The oxidation of can be used without serious of performance. It IS shown that, loss this carbon in the remainder of the combustor is then considered, at sufficiently low Reynolds numbers and low exit-cone angles, and the oxidation rates attainable within the combustor are there is no solution of thr slender-channel equations in which the flow can expand to supersonic conditions. Instead, the boundary computed from existing rate data. Secondly, the dispersion of the in the atmosphere is analyzed, the two effects layer closes, and the solution resembles a viscous subsonic pipe exhaust plume flow. The imphcations of this finding on the upstream influence of considered being the entrainment of surrounding air due to turbulent thc exit-planr conditions and on the limits of validlty 01 the slender- motion of the jet and the motion induced by the buoyancy of the channel equations are discusscd. (Author) trail, For short times, mixing proceeds as in ordinary wakes; for longer times, mixing is dominated by motion induced by buoyancy. Typical pollutant dilutions behind the aircraft are presented. A71-27557 fi Extension of Emmons' spot theory to flows (Author) on blunt bodies. Karl K. Chen and Noel A. Thyson (Avco Corp.. Avco Systems Div , Wilmington. Mass.). AIAA Journal, vol. 9. May A71-27561 # Experimental stability studies in wakes of 1971, p. 821 -825 27 refs Contract No. AF 04(701)-69-C-0117. twodimensional slender bodies at hypersonic speeds. Wilhelm The transitioii region is considered to be characterired by the Behrens (California Institute of Technology. Pasadena, Calif.) and intermittent appearance of turbulent spots, which grow as they move Denny R. S. KO (TRW Systems Group, Redondo Beach, Calif.). downstieam until they finally merge into one another to form the AlAA Journal, vol. 9, May 1971, p. 851-857. 25 refs. Contract No. turbulent Lmunddiy layel The inteimittency factoi for arbitiaiy DA~31.124-ARO(D)-33. axisymmi-!ric body with zeto angle oi attack hds been derived in an Experimental study of the stability in the transition region from expression which can be reduced to the form of universal inter- laminar to turbulent flow in wakes of slender wedges and a flat plate mittency distiibution of Dhdwan and Ndrdslmha in the case of at Mach number 6. As in low-speed flat plate wakes, transition from straight tube or flat plate A key factor to control flow conditions in laminar to turbulent flow may be divided into a linear and a the transition zone appears to be the spot formation rate, which has nonlinear instability region. Inviscid linear stability theory predicts been deduced from the available data of the extent of transition well the growth of fluctuations and amplitude distribution in the zone. It was found that the spot foimation rate deprnds not only on linear region. In the nonlinear region similarities with low-speed

366 A71 -27602 wakes exist Chaiacteristic persisting peaks in the power spectra are as tabular functions of Mach number. Advantages of the proposed obseived Based on these peak frequencies a nearly universal Strouhal algorithm are pointed out as well as potential pitfalls which may be ntimbei is found for both incompressible and hypersonic wake flows encountered in its implementation. M.M. A theoietical approach to predict the development of mean flow and flow fluctuations in the nonlinear region as employed KO, Kubota. and Lees (1970) in slender body low-speed wakes appears A7127598 # Shock interaction effect on a flapped delta equally applicable for hypersonic wakes (Author) wing at M = 8.2. Dhanvada Madhava Rao (NASA, Langley Research Center, Hypersonic Vehicles Div.. Hampton, Va.). AlAA Journal, vol. 9, May 1971, p. 985, 986. 8 refs. Research supported by the A7127577 * Connection between lift and particle displace- Ministry of Technology. ment. Kenji lnouye (National Aerospace Laboratory, Tokyo, Japan). Description of a simple method for estimating the impingement AIAA Journal, vol. 9, May 1971. p. 945, 946. boundary of the reflected expansion arising from shock interaction Demonstration that Corrsin's (1968) conjecture between the lift on a flapped delta wing. The resulting hypersonic aerodynamic and particle displacement around a lifting body can be proved coefficients are presented. The method uses a simple flow model. It without his assumption. The assumption was that the changes of is suggested that, as a consequence of the three-dimensional shock y-coordinates of the fluid particles can be neglected. The conjecture interaction, the outboard portions of the trailing-edge flap on a delta can be proved by the use of the stream function as an integral of the wing are relatively less effective since they derive the least benefit equations of motion of the fluid particle. A similar formulation can from the compression field of the wing. M.M. be found in the analyses of drift in the flow with no circulation around a circular cylinder by Darwin (1953) and around a'sphere by A7127599 ,#' A method for predicting the number of near Lighthill (1956. 1957). M.M. mid-air collisions in a defined airspace. G. T. A. May. Institute of Navigation, Journal, vol. 24. Apr. 1971, p. 204-218. A71-27582 # Threedimensional stagnationpoint heat trans- A simple analytical method was developed for the solution of fer in equilibrium air flows. Andrzej Wortman (Northrop Corp.. some main air traffic control problems in connection with a Hawthorne, Calif.), (American Institute of Aeronautics and Astro- proposed integration of civil and military air traffic control services nautics, Fluid and Plasma Dynamics Conference, 3rd. Los Angeles, in Sweden. Assumptions and principles underlying the method are presented. The method was used practically for determining the Calif., June 29July 1. 1970, Paper 70809.) AlAA Journal, vol. 9. May 1971, p. 955-957. 8 refs. amount of control required for a particular off-airways area and to help determine the optimum control procedures for air traffic A parametric study was made of equilibrium air boundary-layer p!anning In :h3: xsa. Pie:im;iisiy resuiis indicare that when flows at enera! 3h:ec dimensional 5Qgiiialion points, ranging in shape developed further, it may provide a useful guide for studying from spheres, through cylinders, to saddle points with equal en-route traffic structures. O.H. magnitudes of adverse and favorable pressure gradients. The gas properties used in the computations corresponded to free-stream speeds ranging up to 29,OOO ft/sec in the earth's atmosphere. The parameter of wall-to-total enthalpy ratio was varied between 0.01 A71-27600 # The simple logic of radar avoidance action. J. and 0.9, with the higher value used at lower airspeeds. The rapidity V. Inglesby. lnstitu&? of Navigation, Journd, vol. 24, Apr. 1971, p. and ease of the present calculations are shown to be due to the use of 21 9232. a semi-analyticalmethodfor exact solutions of boundary-layerflows. Basic principles of avoidanoe action are developed. It is shown Characteristics of the flow are discud in detai!, and explanations That a miquc, compkiely iogicai set of rules exists which will are given in terms of the known behavior of twodimensional flows. guarantee the safe passage of converging aircraft. When two aircraft It is shown that real-gas heat transfer parameters can be correlated are involved, if either, or both simultaneously, act according to these with highly idealized gas data over the full range of shapes. Several rules, it is impossible to have an accident whatever the situation. The engineering relations are obtained for rapid estimates of heat transfer proposed rules are consistent with the Rules of the Air. Past attempts to formulate rules are compared. O.H. to general stagnation points. (Author)

A7127584 # Flutter of a buckled plate exposed to a static A71-27601 # The promise of aeronautics. Leonard Roberts pressure differential. C. S. Ventres (Princeton University, Princeton, (NASA. Ames Research Center, Moffett Field, Calk). Asrronautics N.J.). AlAA Journal, vol. 9, May 1971, p. 958-960. 8 refs. Grant No. andAeronaurics, YOI.9, May 1971. p. 24-31. 12 refs. NG R-31-001-146. Socioeconomic changes to be expected for the future are Experimental results on the stability boundary for a panel examined. It is pointed out that the industrially developed nations exposed simultaneously to a static pressure differential and to a will have a greater and ever-increasing proportion of the public streamwise applied in-plane load, obtained by Hess (1970). are educated to the use of ai: travel and that this proportion will compared with author's own theoretical stability boundary calcula- increasingly have the means to use it. The need for the development tions. Flutter boundaries for plates with both zero and complete of faster long-range aircraft for travel to the developing continents of in-plane edge restraint were calculated. The experimental data lie Asia, Africa, and South America and transportation requirements closest to the stability boundary for zero restraint. The calculated within these areas are considered. Factors mitigating against the full flutter frequencies are not in as good agreement with the experi- realization of potential growth are reviewed, including concern about undesirable side effects of air transportation, problems of airport mental results as are the flutter boundaries. O.H. access, and lack of profitability for new technological advances. Joint industry and government action of a few clearly defined goals IS A71-27592 -U Computation of Chebycheff optimal control. recommended, giving attention to problems of short-haul transporta- Gerald J. Michael (United Aircraft Research Laboratories, East tion and to vastly improved international longhaul transportation. Hartford, Conn.). AlAA Journal, vol. 9, May 1971, p. 973-975. 6 G.R. refs. Demonstration of a general method for the efficient computation of Chebyshev optimal control for nonlinear systems. The A7127602 8 Turbofan STOL research at NASA. Bradford Chebyshev algorithm is used to determine a Chebyshev optimal H. Wick (NASA. Ames Research Center, Full-Scale and Systems controller for the minirnim flight path angle climb to station of an Research Div.. Moffett Field, Calif.) and Richard E. Kuhn (NASA, airbreathing vehicle whose thrust and fuel flow rate are characterized Langley Research Center, LowSpeed Aircraft Div., Hampton. Va.). by a thrust coefficient and a specific impulse both of which are given Astronauticsand Aeronautics, vol. 9. May 1971, p. 32-50. 10 refs.

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Problems of congestion in the present air-transportation system (1970). Expressions are derived for determining the coordinates of are discussed. The problems are mainly the result of a shortage of particle incidence on the wedge surface and the collision frequency runways and airways. The role of STOL technology in significantly as a function of initial conditions. The local increase in pressure at changing the magnitude of these problems is considered, and the the moment of impact is also estimated. It is found that during a principal requirements of STOL transport to provide the required two-phase flow past a wedge with rebounding particles, there exists a service are examined. The principal factors conditioning landing-field surface which limits the escape of rebounded particles into the length are explored, and navigational and control problems are external flow. Z.W. investigated. Hesearcn on turbofan-powered STgL iiciiirpoi: k reported, focusing attention mainly on two promising jet-flap concepts: the externally blown flap and the augmentor wing. Planned cooperative efforts on STOL transports and avionics systems A71-27676 How to get there from here with new materials are discussed, and a brief outline of limited exploratory investiga- - A designer’s viewpoint. W. T. Shuler (Lockheed-Georgia Co., tions of other STOL aircraft concepts and avionic.system com- Marietta, Ga.). SAMPE Quarterly, vol. 2, Apr. 1971, p. 12-14. ponents is presented G.R. The possibility of application of advanced materials to aircraft design is discussed. In particular, titanium, and boron and graphite fiber composites are considered. Their outstanding mechanical A7 1-27608 Methods utilized in tests of the flying qualities properties are outlined and the problem of making them competitive of the Concorde (Methodes utilisees dans les essais de qualites de vol with current materials in terms of manufacturing efficiency. in- de Concorde). Jean Pinet (Societe Nationale lndustrielle Aero creased performance, lower cost, improved schedules, or a combina- spatiales; Centre de Documentation de I‘Armement, Paris, France). tion, is examined. Sevelai examples of successful applicatinns are L’Aeronautique et I’Astronautique, no. 27. 1971, p. 37-42. In Dresented. O.H. French. Pragmatic use of numerous methods and combinations of methods used to study the flying qualities of the Concorde. This A7 1-27677 Materials for Air Force - 1980: An industry procedure gives great flexibility in testing, and greatly reduces flying commentary. William J. Harris, Jr. (Association of American Rail- time. Simulation is intensively used, notably in the Elagnac flight roads, Washington, D.C.). (Air Force Materials Symposium, Miami simulator, which features a mobile cabin with a visualization scheme, Beach, Fla., May 18-22,1970.) SAMPE Quarterly, vol. 2, Apr. 1971, a monitoring post, a pllot’s post, an analog computer, a color p. 22-26. television terrain model, and recording apparatus. The data proces A brief review is presented of the development in the past years ing is automated F.R.L. in the field of new metals and alloys, compohs, and ceramic materials which were of primary importance to weapon systems. The various problems involved in using advanced materials in aircraft A71-27609 Unsteady stall of an airfoil (Le decrochage industry as replacements for more traditional materials and, in instationnaire d‘un profil). Jean-Jacques Philippe (ONERA, particular. the problem of reluctance in their acceptance, are Chatillon-sous-Bagneux, Hauts-de-Seine, France). (Association examined. Innovations necessary in management of governmental Francaise des Ingenieun et Techniciens de I’Adronautique et de programs, in procurement specifications, and in the contracting /‘€space, Colloque d‘Aerodynarnique Appliquk, 7th, Modane, procedures of the Department of Defense are discussed. O.H. Savoie and Ecole Centrale L yonnaise, Ecully, Rhdne, France, Nov. 4-6, 1970.) L’Aeronautique et I‘Astronautique, no. 27, 1971, p. 51-57.8 refs. In French. Investigation of the unsteady stall of airfoils by testing a A71-27688 # Equipment UIT-1200/50 for determining the two-dimensional model in harmonic pitching oscillation. The pro- heat resistance of sealing materials (Ustanovka UIT-1200/50 dlia opredelenia termostoikosti uplotnitel’nykh materialov). N. L. cesses involved in such a stall are reviewed, followed by examination Golego, M. E. Eelitskii, E. I. Kuznetsov, G. A. Volosovich. and A. P. of its effects on unsteady pi-essure. overall performance, and Voidenov (Kievskii lnstitut lnzhenerov Grazhdanskoi Aviatsii, Kiev. aerodynamic stability as functions of mean incidence, Mach nurribei, Ukrainian SSR; Gosudarstvennyi Trest Predpriiatii PO lzgotovleniiu I and reduced frequency. The unsteady qualities which must be Izmeritel’nykh Priborov, Leningrad, USSR) Problemy Prochnosti, possessed by airfoils intended for helicopter blades are described. In vol. 3, Mar. 1971, p. 92-96. 6 refs. In Russian. this field knowledge of unsteady aerodynamics is basic. F.R.L. The requirements posed to sealing materials of modern aiict-aft power plants are reviewed, with particular reference to the heat A71-27662 Effect of the deoxygenation of jet fuels on resistance of porous metal ceramic seals under thermal cyclic loads. their antiwear properties (Vliianie obeskislorozhivaniia reaktivnykh An automatic equipment that will study the thermal behavior of topliv na ikh protivoiznosnye svoistva). A. F. Aksenov, A. A. materials at temperatures ranging from 200 to 1200 C in such media Litvinov. A. E. Eorodin. V P. Eelianskii. V. P. Logviniuk, and V. V. as nitrogen, argon, air, and exhaust gases, and will record simul- Malyshev. Khimiia I Tekhnologiia Topliv i Masel, vol. 16, no. 2. taneously the changes in the mass of the materials, is described. V.P. 1971, p. 42-44. 5 refs. In Russian. Samples of the ShKh~l5steel were subjected to vibrational and gliding friction in industrial T-7 fuel at temperatutes of 20 and 60 C. A71-27697 #! Method for determining unsteady flow down- A series of tests was carried out in a fuel from which oxygen was wash behind a finite-span wing during a supersonic motion (Metod removed by means of argon oi CO2 sciubbing. It IS shown that the opredeleniia nestatsionarnogo skosa potoka za krylom konechnogo wear of steel in a Co2 sciubbed fuel decreased about three times and razmakha pri sverkhzvukovom dvizhenii). R. A. Mezhlumi,w and R. the criticdl load incrr-dsed about twice with iespect to iestilts Sh. Solomonian (Erevanskii Politekhnichcskii II1stitut. Kiiovdkaii. obtained in the tinscrubbed fuel. For an argon-sciubbed fuel these Armenian SSR). AkadenJiia /%ilk Aritrinllsko/ SSR, IZveStiki, values ate 1.5 and 2. respectively. 2.W Mekhanika, vol 23. no. 6, 1970. p. 50-63. 10 ids. In Russiai?. A procedure is given for solving the piolileni of unstr!atly flow A71-27665 il Interaction of particles with a wedge surface in downwash at finite Strouhal niinllwrs in a Iii1mi f(iimulatioi1. a supersonic two-phase flow (Vzaimodeistvie chastlts s Essential in this procedure is the rcpiesenlation of thc prltui L1,it!oi1 poverkhnost’iu klina v sverkhzvukovom dvukhfaznom potoke). G A. potential through the coefficients of downwdsh iot,itiondl dt?iiv.itivcs Saltanov. Akademiia Nauk SSSR, lrvestiia, Energetika i Transuort, according to Belotserkovskii (1955) and Kisli,iglil (1961). The Jan.-Feb. 1971, p 141-149. 5rcfs. In Russian. supersonic motion of a slendw slightly cuivrd wiry in ai1 idrcil fluid The analysis is carried out by means of equatioiis of mottoil foi at a small angle of attack in the hscncv of rxttviidl foices is a drop behind an oblique shockwdvc derived by Saltdnov et al. discussed. v7

368 A71-27738

A71-27714 fi Structure of vortex flows in axial-flow turbo- inexpensive accelerometers each of which is provided with its own machines (Sur la structure des ecoulements tourbillonnaires dans les electronic circuit. Several hundreds of these devices have been turbomachines axiales). Jean-Pierre Guiraud and Radyadour Kh. successfully applied to individual rockets on the ground for modal Zeytounian. La Recherche Aerospatiale, Mar.-Apr. 1971, p. 65-87. measurements over the 5 to 500 Hz range. M.V.E. 12 refs. In French. The axial flow in a turbomachine is analyzed by means of an asymptotic method assuming infinite mutual blade proximity and A71 -27738 Experimental determination of the momen- ideal incompressible flow. A twofold structure is observed: a turn thickness of a circular cylinder in a cross flow (Experimentelk quasi-axisymmetric mean flow and a thereon superposed fine, Bestimmung der Impulsvedustdicke beim queranptrhten Kreis- fluctuating structure. The latter makes it possible to take into zylinder). E. Achenbach (Kernforschungsnlaw Julich GmbH. Julich, account the effect, outside the blade rows, of the vortex sheets ‘West Germany). Warm- undStoffubertragung, vol. 4, no. 1. 1971, p. issuing from the trailing edges of the blades. The equations governing 18-24. 14 refs. In German. the mean flow and the fluctuations inside and outside the blade rows Measurement of the local static pressure and skin friction are obtained. M.V.E. distribution around circular cylinders in a cross flow in the range of Reynolds numbers from 15,000 to 260.000. The experimental data have been used to determine the momentum thickness of the A71-27715 # Calculation of the mean flow in an axial-flow boundary layer as a function of the angle of circumference. If the turbomachine (Calcul de I’Bcoulement moyen dans une turbo- results are presented in a suitable dimensionless form, it can be machine axiale). Jean-Pierre Veuillot. La Recherche Aerospatiale, shown that the experimental results fit the theoretical curve with a Mar.-Apr. 1971, p. 89-97. 9 refs. In French. scattering of about plus or minus 5%. (Author) A determination is attempted of the velocity field induced by a wheel in an axial-flow turbomachine for the flow of an incompressible ideal fluid uniform at infinity upstream by way of solving an inverse problem under abandonment of the classical hypothesis of absence of any radial velocity component but retaining some simplifying assumptions. An iterative numerical algorithm permits solving this nonlinear limit problem for various values of rotation velocity and circulation. Some calculation results are presented. M.V.E.

1 Ail-27716 # Influence of a given conical fuselage on the problem of optimizing a delta wing in supersonic flow (L’influence d‘un fuselage conique donne sur le probldme de I’optimisation d‘une 1 aile delta en courant suprsonique). Adriana Nastase (Academia RomBni, lnstitutul de Mecanica Fluidelor, Bucharest, Rumania). La Recherche Aerospatiale, Mar.-Apr. 1971, p. 99-107. 7 refs. In French. The surface shape is determined of a thidc detta wing integtated with a conical fuselage and generating minimum drag for a given a jpaed. Un&i the linearized theory applied, it is possible to separate the load-carrying effect from the thickness effect, as well as from the effect of the symmetrical axial flow around the circular cone at zero angle of incidence. The expressions for the axial velocities of the perturbations are determined, and solutions are obtained for the variational problems pertaining to the optimization of either a thin delta wing attached to a conlcal fuselage at some angle of incidence, or a delta wing of symmetrical thickness attached to a conical fuselage at zero angle of incidence. M.V.E.

A71 -27717 # Wind tunnel visualization arrangements for fixed or rotating annular cascades (Dispositifs de visualisation pour souffleries de grilles annulaires fixes ou tournantes). Michel Philbert and Guy Fertin. La Recherche Aerospatiale, Mar.-Apr. 1971, p. 109-118. In French. Review of the nature and work of two experimental installations using schlieren techniques: (1) a supersonic annular fixed cascade wind tunnel, and (2)a supersonic freon compressor. In both of these installations, the gas flow test section is confined to an annular space of slight thickness which imparts a largely two-dimensional character to the flow. This makes for superior schlieren pictures in terms of afforded interpretation thoroughness. However, the presence of vane holding cylinders creates certain problems that are met by an application of techniques and devices described in detail. M.V.E.

A71-27719 li Accelerometric circuits for the measurement of modal characteristics (Chaines accelCrom6triques pour la mesure des caracteristiques modales). Jean-Francois Boisseau and Andre I Duchene. La Recherche AProspatiale, Mar.-Apr. 1971. p. 121-124. In I French. Description of a modal-characteristic pick-up system for vibration tcsts of rockets or aircraft on the ground using small-size

369 N71-21927

UNTERSCHALLWINDKANALEN TElLZ] G Schulz Oct 1970 37 p refs Trans1 into ENGLISH of German report DLR-FB-69-86 (RAE-Lib-Trans-1465. DLR-FB-69-86) Avail NTlS The construction. effects. and evaluation of sound damping elements are discussed Measurements were made on the spatial STAR ENTRIES distribution of the sound in the measuring jet as well as its dependence on the speed of rotation of the fan and on the blowing speed By a suitable theoretical procedure it is possible to separate the characteristic noise of the tunnel into its two parts. the fan noise and the free jet noise Author

"71-21855 Pennsylvania Univ.. Philadelphia. N71-21898 Colorado Univ.. Boulder. A STUDY OF MULTIPLE ACCESS COMMUNICATION SYSTEM THEORY OF THE SOLID ROTOR INDUCTION MACHINE James Clayton Wilson (Ph.D. Thesis) 1969 429 p Edmond Yu-shang Ho (Ph.D. Thesis) 1969 89 p Avail: Univ. Microfilms: HC $19,35/Microfilm $5.50 Order No. Avail: Univ. Microfilms: HC $4.6O/Microfilm $3.00 Order NO. 70-7807 70-5907 Extremely high-speed polyphase induction motors f6r aerospace A digital communication system to be used among low-flying applications must be designed with solid rotors because windings aircraft which, individually, require the transmission channel cannot withstand rotation stresses. The high performance expected infrequently is analyzed. To make more efficient use of the calls for an analysis that takes into account the nonlinearity of the transmission medium without the need for intervening switching rotor iron and the finite length of the motor. complexities not centers. a form of random access is planned. Transmission is considered in an acceptable form by former researchers. This largely along line-of-sight; multipath propagation is assumed to be tvpe involved. Dissert. Abstr. of analysis is applied to predetermine the characteristic of a 5 h.p.. 145 volt. 3200 M.three-phase. wye-connected solid mtor induction motor. After a historical review. a developed mathematical model is described. The partial differential equation and the boundary N71-21874# Speas (R Dixon) Associates. Palo Alto. Calif conditions, considering fully the motion of the rotor. am developed NORCALSTOL: A REPORT ON THE NORCALSTOL from Maxwell's equations. The relationshiD of the terminal volts@ DEMONSTRATION. 13 15 MAY 1970 and of a current sheet representing the stator slot currents is 1970 80 p Prepared in cooperation with Chamber of Commerce developed. The torque of the induction motor as a function of the San Francisco slip is developed from Poynting's theorem. Dissen. Abstr. Avail NTlS Demonstration flights of several short takeoff aircraft were conducted at San Francisco California The purpose of the fllghts was N71-21915# Tennessee Univ , Knoxville to promote the use of such aircraft as commercial transportation SIMPLIFIED GUIDANCE AND CONTROL J Bailey 1 Apr 1970 73 p refs system to improve access to the citv Aircraft wlwh parttctpated M (Contract DAAHOl 69-C-1264) in the demonstration were (1) Britten - Norman Islander. (2) Helio :AC-7:7567) Avaii NTiS CSCii717 H-550A Stallion. 13) Hell0 H-295 Super Courier (4) De Havilland While formulating the optmum trajectory one must at the Twin Otter (5) Fairchild Hiller Heliporter. and (6) Cessna Super same time synthesize some form of corrective control action along Skymaster PNF the way Economic considerations also dictate that this control scheme be as simple as possible commensurate with the desired system accuracy One approach to such a requirement IS to design N71-21882* North American Aviation. Inc.. Downey. Calif. a linear controller that attempts to keep deviations of some or all OPTICAL PROJECTOR SYSTEM Patent Robert A. Beam. inventor (to NASA) Issued 26 Dec. 1967 (Filed the state variables from a standard trajectory small Directional Control which acts to keep the steady state normal velocity due to 9 Sep. 1966) 10 p CI. 88-24 Sponsored by NASA cross winds essentially zero is such a scheme This report (NASA-Case-XNP-03853; US-Patent-3,359,855; summarizesthe statusof investigations into such simplified schemes US-Patent-Appl-SN-578931) Avail. US Patent Office CSCL 20F at the University of Tennessee under the contract GRA The device comprises an optical projector system which projects an image for each eye. and which may take into consideration N71-21922# Honeywell. Inc Minneapolis Minn Systems and peripheral vision. as well as color, symbol and word recognition. . Research Div The projector system also includes provisions to simulate vertical OPTIMAL FUEL SYSTEM ESTIMATION and horizontal eye movement, together with vertical, horizontal and Nelson R Zagalsky 30 Oct 1970 39 p refs angular head movement. The system does not require the (Contract NO0014-69-C-0101) cooperation of an actual observer. The image projector system (AD-717640. Rept-12591-TR-1ElI Avail NTlS CSCL21/4 includes the ability to provide for particular visual characteristics of The application of Kalman (Linear Least Squares Recursive) individual observers For instance, an instrument display may be filtering to the estimation of fuel quantity and fuel rate for fighter arranged which provides for reductions and changes in normal visual aircraft is discussed Error analyses are presented for the resultant limits from such factors as pressure unit visor restrictions. lack Of filter The blending of quantity and rate information IS shown to sufficient oxygen. G forces. light versus dark adapted eyes. and offer a tradeoff between required system accuracies and individual moving the eyes farther away or near to the display panel. Official Gazette of the U.S Patent Office sensor accuracies Author (GRA)

N71-21927# National Research Council of Canada. Ottawa N71-21885% Royal Aircraft Establishment. Famborough (England) (Ontario). Div. of Mechanical Engineering. ON THE MEASUREMENT OF THE NOISE IN THE ENGINE SNOW INGESTION IN THE BELL 206A JET NEIGHBOURHOOD OF BODIES IN SUBSONIC WIND RANGER HELICOPTER TUNNELS, PARTS [UEBER DIE GERAEUSCHMESSUNG AN J. R. Stallabrass Jan. 1971 20 p I UMSTROEMTEN OERPERN IN (NRC-11893; MET-513) Avail: NTlS

37 1 N71-21961

To investigate reported cases of engine flameout occurring AVIATION STATISTICS AIRPORTS, AIR CARRIER FLEET, during flight in snow tests were made on a ground-running AIRCRAFT PRODUCTION, AND AIRMEN helicopter using a device for generating artificial snow The tests Sep 1970 23 p showed that operation in snow could result in engine flameout. Avail NTlS largely as a result of accumulations of ice being formed in the A summary of the statistics pertaining to various aspects engine inlet plenum chamber It is concluded that flight in any of civil aviation is presented Subjects discussed are (1) number condition of snow is unsafe with the existing engine inlet of joint-use landing facilities (21 size of United States civil air fleet c~fifiguiai~onof ihij helaioptei Authoi (3)general aviaiion utiIization i4j difiiiw opeiataoi;;. (5)c.,:! a:rc,z!t production and (6) trends in pilot training and licensing P N F

N71-21961*# National Aeronautics and Space Administration Langley Research Center Langley Station Va N71-21978# Federal Aviation Administration Washington D A WIND-TUNNEL INVESTIGATION OF SONIC-BOOM C Bureau of National Capital Airports PRESSURE DISTRIBUTIONS OF BODIES OF REVOLUTION ANALYSIS OF BOEING 727-200 OPERATIONS AT AT MACH 2 96,3 83, AND 4 63 WASHINGTON NATIONAL AIRPORT Barrett L Shrout Robert J Mack and Samuel M Dollyhlgh Feb 1971 25 p Washington Apr 1971 33 p refs Avail NTlS (NASA TN D 6195 L 7398) Avail NTlS CSCLOlA During the period April through October 1970 the Bureau Sonic boom pressure signature measurements were made of National Cdpital Airports conducted an analytical study of the for a series of bodies of revolution at Mach numbers of 2 96 3 83 operations of the Boeing 727-200 aircraft at Washington National and 4 63 Maximum overpressure and signature impulse tend to Airport The 727 200 is identical (same basic power plant and increase with increasing Mach number as predicted by a near-field wing/flap geometry) to the 727-100 except for an extra 20 foot modified linear theory applicable to smooth bodies However the fuselage section which provides additional seating capacity The measured signatures agree only qualitatively with near-field theory 727-100 has operated at Washington National since it was opened at the high Mach numbers Inclusion in the theory of the effects to let aircraft in 1966 The study included close observation for of oblique plane surface forces and model boundary layer improved impact on environment air and surface traffic management he correlation between theory and experiment A nonsmooth body passenger processing passenger boarding trends and scheduled and theory produced better agreement for the trailing shock but with total operation trends The effect of the current nationwide decline some reduction of the signature impulse Author in airline business evident at all three area airports was also taken into account Analysis of the data collected during the study period N71-21973*# National Aeronautics and Space Administration indicates that the 727-200 had no adverse impact on conditions Langley Research Center Langley Station Va at Washington National or on the growth and utilization of Dulles CHARTS FOR PREDICTING THE SUBSONIC VORTEX-LIFT International Airport Author CHARACTERISTICS OF ARROW. DELTA, AND DIAMOND WINGS Edward C Polhamus Washington Apr 1971 11 p refs (NASA TN D-6243 L 7558) Avail NTlS CSCLOlA N71-21979# Federal Aviation Administration. Washington. D C The leading edge suction analogy method of predicting the Office of Aviation Economics aerodynamic characteristtcs of slender delta wings was extended WASHINGTON NATIONAL AND DULLES to cover arrow and diamond wing planforms Charts for use in INTERNATIONAL AIRPORT FORECASTS, FISCAL YEARS calculating the potential and vortex flow terms for the lift and drag 1971 1982 are presented and a subsonic compressibility correction procedure Nov 1970 51 p based on the Prandtl Glauert transformation IS outlined Author Avail NTlS Forecasts for eight malor traffic categories at both Washington National Airport and Dulles International Airport for fiscal years N71-21976# Federal Aviation Administration Washington. D C 197 1 through 1982 are presented These categories are passengers SECOND MEETING OF THE SONIC BOOM PANEL. REPORT (air carrier and all others) cargo (express. freight and ma:l). and OF THE US DELEGATION aircraft operations (air carrier general aviation. and military) The 19 Nov 1970 112 p Conf held at Montreal 12 21 Oct 1970 study is a basis for planning the intermediate needs of the Bureau IIGIA 17/48) Avail NTlS of National Capital Airports It also supplies guidance for other The second meeting of the ICAO Sonic Boom Panel convened Offices and Services of the Federal Aviation Administration which at ICAO headquarters Montreal on October 12. 1970 On have a direct interest in the dav-to-day operation of these two major October 21, 1970 the panel concluded its meeting in Montreal by commercial airports These forecasts indicate probable aviation submitting to the Air Navigation Commission a report entitled demand for the Washington Metropolitan Area They do not imply Report on the Sonic Boom Phenomenon the Ranges of Sonic Boom that physical capacity to fully meet this demand is available and Values Likely to be Produced by Planned SSTS and the Effects of in being today These projections provide a foundation on which Sonic Boom on Humans Property Animals and Terrain This report airport engineers and regional airport planning officials can make had initially been developed at the Panel s First Meeting and has their'own specialized studies and recornmendations on how best since been amended and expanded upon both by correspondence to meet this demand Author between members and at an ad hoc meeting of panel members held in Paris during February 1970 Specific recommendations were made and it was considered that sufficient progress had been made by the panel within its initial terms of reference with N71-21980# Federal Aviation Administration. Washington. D C reference to Stdqes 1 and 2 to allow transition to Stage 3 of the Office of Environmental Quality Council s Staqed Plan of Action of Steps to be Taken to Facilitate JET ENGINE NOISE DATA FROM SUBSONIC AIRCRAFT, Compliance witti Resolution A16 4 Author MARCH APRIL 1971 1971 42 p Presented at the Intern Short Course on Aircraft Noise Theory and Appl , Knoxville. Tenn , 15 20 Mar 1971 and N71-21977# Federal Aviation Administration. Washington. D C at Aachen. 29 Mar 3 Apr 197 1 Office of Management Systems Avail NTlS

372 N71-22070

The acoustic considerations of aircraft noise have led to The report describes briefly the construction and principles the development of several basic descriptors of that noise The first of operation of aviation gas turbine engines their assemblies and descriptor of an aircraft sound is its representation as a sound level friction points and also the oil systems Operating conditions of spectrum A sound level spectrum presents the intensity of the lubricants in these engines are discussed as are the functions of sound in decibels as a function of the frequency in hertz Sound oils as lubricating materials the functions of operating liquids and level spectra may be developed by the use of weighting functions cooling agents technical specifications required of lubricants are to give perceived noisiness and then factored for discrete frequency discussed Ouestions are discussed related to the assortment and and duration The final descriptor for the description of noise in quality of oils currently employed for aviation gas turbine engines the vicinity of an airport is called the noise exposure forecast The and the requirements for oils of the near future Methods are noise exposure forecast considers the daily operations in the airport described for obtaining from petroleum and synthetics high-quality environment It uses the effective perceived noise level which is oils which possess high anti-oxidation viscosity-temperature combined ultimately with the number of operations weighted for anti wear and other properties Information is presented concerning the type of aircraft. including the flight profile of each aircraft with additives which improve the operational properties of oils for additional weighting factors for the night and daytime operations aviation gas turbine engines Domestic and foreign methods of Author Investigating and testing oils under laboratov conditions and also In special stands and devices are systematized and described N71-21995*# Pratt and Whitney Aircraft West Palm Beach Fla GRA Research and Development Center SINGLE STAGE EXPERIMENTAL EVALUATION OF COMPRESSOR BLADING WITH SLOTS AND WALL FLOW N71-22068*# National Aeronautics and Space Administration. FENCES Langley Research Center, Langley Station. Va. R W Rockenbach and J A Brent 1 Apr 1971 174 p refs ANALYSIS OF EFFECTS OF SPANWISE VARIATIONS OF (Contract NAS3-10481) GUST VELOCITY ON A VANE-CONTROLLED (NASA CR-72635 PWA FR-3597) Avail NTlS CSCL20D GUST- A LLEVIAll ON SYSTEM A highly loaded 08 hub-tip ratio single stage axial flow L Keith Barker and Gene W. Sparrow Washington Apr. 1971 compressor was tested with two rows of slots in both the rotor 20 p refs and stator blades and with wall mounted intrablade row flow (NASA-TN-D-6126: L-7442) Avail NTlS CSCLOlA fences These devices were intended to reduce the rnigraticn of wall An analysis was made of the effects of spanwise variations boundary layer flow onto the blade surfaces and to prevent flow of gust velocity in isotropic turbulence on a gust-alleviation system SeDaration on the hlade sI?ctic" SU-~ECBS The devices 'ireii found which empioys an angle-ot-attack vane mounted ahead of the wing to be ineffective in achieving this goal and the poor performance to sense the vertical gust velocity. The wing flaps were moved in of the stage was largely a result of stall in the wall region It was response to the vane deflection by a linear second-order concluded that the latter mechanism is limiting the permissible servosystem to produce a lift opposite to that produced by the gust. loading and therefore that future means of increasing permissible Consideration of spanwise variation of gusts has indicated design loading be concentrated on the wall stall problem Author parameters (gain and natural frequency of flap servosystem and vane location) that give substantial reduction of the lift due to gusts. Author N71-21996*# National Aef-tics and Space Administration. Manned Spacecraft Center. Houston. Tex. SELECTION OF LANDING AIRFIELDS FOR SHUTTLE N71-22069*# National Aeronautics and Space Administration ORBITERS WITH VARIOUS CROSSRANGES Landing and Langley Research Center Langley Station Va Recovery Division Internal Note FLIGHT INVESTIGATION OF A V/STOL TRANSPORT Jonny E. Ferguson 25 Sep. 1970 112 p refs MODEL HAVING SIX WING-MOUNTED LIFT FANS (NASA-TM-X-67080. MSC-026661 Avail. NTlS CSCL 01E William A Newsom Jr and Sue B Grafton Washington Apr The findings and recommendations resulting from a study 1971 29 p refs designed to select specific airfields to support landings of example (NASA-TN D 6198 L-7560) Avail NTlS CSCLOlC space shuttle orbiters with various hypersonic crossranges are The investigation consisted of free-flight model tests in reported The orbiter is a single unit vehicle similar to a large jet hovering and forward flight through the transition speed range up transport in size, appearance, and landing characteristics. The to the speed where conversion would be made to wing-borne flight airfields were selected from those currently available in the free Dynamic lateral-directional stability characteristics of the model world. Based upon the analysis of all the generated data associated were also calculated to explain the flight-test results The model with these airtield selections. it is recommended that the shuttle was flyable without artificial stabilization but in general angular orbiter should be designed for a hypersonic crossrange not lass rate damping was required to make the flight characteristics than 200 n. mi. to optimize the number of support airfields required satisfactory Author and the duration of in-orbit waits required. It is also recommended that the orbiter be designed to land on runways of not more than 10.000 feet in length and with support capability for loQpsi tire N71-22070# Deutsche Foschungs- und Versuchsanstalt fuer Luft- pressure and an equivalent single-wheel load of about 50.000 Ib. und Raumfahrt. Berlin (West Germany) Abteilung Aeroakustik Consideration should be given to the cost of the number of airfields und lnstabilitaet required. the cost of modifying the airfields as required, the in-orbit A WAVE MODEL FOR SOUND GENERATION IN CIRCULAR waits required. and the hypersonic crossrange desired in all shuttle JETS program design efforts. Author Alfons Michalke Nov 1970 33 p refs (DLR-FB-70-57) Avail NTIS. ZLDl Munich 9.30 DM A wave model is used for the investigation of sound generatton N71-2201l# Air Force Systems Command, Wright-Patterson in circular pts The source term of the Lighthill equation is expressed AFB. Ohio Foreign Technology Div by a Fourier series in the azimuthal angle, is Fourier-transformed LUBRICATING OILS FOR JET ENGINES [SMAZOCHNYE with respect to time, and each component is assumed to be of MASLA DLYA REAKTIVNYKH DVIGATALEI] wave-type in jet direction A far-field solution for the sound E N Kalaitan 23 Dec 1970 237 p refs Trans1 into ENGLISH pressure is derived for single azimuth-frequency components It is from the Russian found that the sound field depends strongly on a convection (AD-717835 FTD-HC-23-1296-68) Avail NTlS CSCL 1 l/8 parameter and on a jet thickness parameter The influence of

373 N71-22072

axisymmetric and azimuthal source components is discussed For a RELATIONS (MIR) TO TRANSONIC AIRFOIL PROBLEMS special source term with arbitrarily chosen amplitude distributions PART 1. INVISCID SUPERCRITICAL FLOW OVER the convection factor and the let thickness factor of sound intensity SYMMETRIC AIRFOILSAT ZERO ANGLE OF ATTACK are calculated and discussed The influence of the amplitude Tsze C Tal Sep 1970 42 p re% distribution of the source components IS found to be of minor (AD-717339 NSRDC 3424. Aero-1 1761 Avail NTlS CSCL20/4 importance Author (ESRO) The feasibility of applying the method of integral relations (MIR) to transonic flows over symmetric airfoils was studied In oidei :O take acccunt of :he ce:le:e tra"st!ers?I flnw variation and N71-22072# Deutsche Forschungs und Versuchsanstalt fuer still retain simplicity in computation the method is modified so that Luft und Raumfahrt Brunswick (West Germany) Abteilung the number of strips used may be considerably higher than the Heterogene Stroemungen order of the polynomial which approximates the integrand An MASS TRANSFER INVESTIGATIONS AT A FLAT STATIC important feature of this modification however is its capability to LlQUlO SURFACE IN PARALLEL AIR FLOW FORMING A extend the free stream boundary to infinity Using one-strip and LAMINAR BOUNDARY LAYER [UNTERSUCHUNG DES two strip approximations flow equations are reduced to a set of STOFFUEBERGANGS AN ElNER EBENEN RUHENDEN ordinary differential equations in a Cartesian coordinate system FLUESSIGKEITSOBERFLAECHE BE1 PARALLELER Numerical procedures including the treatment of thesonic point and ANSTROEMUNG UND LAMINARER GRENZSCHICHT~ the determination of shock location are also formulated The Klaus Juergen Schultz Jul 1970 46 p refs In GERMAN fourth order Runge Kutta method was used in numerical computation ENbLlSH summary Sponsored by Dcut Forschungqpmeinschaft The advantaqe of small computer capaci'y and time required by the (DLR FB 70 58) Avail NTlS ZLDl Munich 12 30 DM method is evidenced by exploratory Cal-ulations for a symmetric Some results of the current experimental work which IS circular arc airfoil and an NACA OC12 airfoil traveling at being done for the determination of the velocity of evaporation of supercritical speeds It is also found that in transonic airfoil problems a flat hydrocarbon film in parallel flow whereby a laminar boundary using a Cartesian coordinate system the oroer of polynomial layer is formed over the liquid surface are reported The test layout approximating the integrand in the method of integral relations and performance are described The dependence of the evaporating should be at least second order or higher Author (GRA) mass per unit time and area averaged over the liquid surface from the velocity and temperature of the flow is presented by means of diagrams for the hydrocarbon benzol and compared with the N71-22129# Deutsche Forschungs und Versuchsanstalt fuer Luft- und Raumfahrt Porz (West Germany1 Abteilung Trans- und results of two simplified computation methods Author (ESROI Ueberschallwindkanaele EXPERIMENTAL INVESTIGATIONS ON SUPERSONIC N71-22076*# National Aeronautics and Space Administration COMBUSTION IN THE FLOW FIELDS OF BODIES OF Langley Research Center Langley Station Va REVOLUTION AND NEAR A FLAT PLATE IN TANGENTIAL FATIGUE OF FOUR STAINLESS STEELS, FOUR TlTANlUM FLOW [EXPERIMENTELLE UNTERSUCHUNGEN ZUR ALLOYS, AND TWO ALUMINUM ALLOYS BEFORE AND WAERMEZUFUHR IM UEBERSCHALL-STROEMUNGSFELD AFTER EXPOSURE TO ELEVATED TEMPERATURES FOR AN ROTATIONSKOERPERN UND AN DER TANGENTIAL UP TO THREE YEARS ANGESTROEMTEN PLATTE] Walter lllg and L A lmig Washington Apr 1971 66 p refs Franz Maurer Franz Joachim Niezgodka and Helmut Post Dec (NASA TN-D 6145 L-7613) Avail NTlS CSCL 11F 1970 77 p refs In GERMAN ENGLISH summary Sponsored Tensile specimens and unnotched notched spotwelded by Bundesmin fuer Verteidigung and fusion welded fatigue specimens from sheets of four stainless (DLR-FB 70-64) Avail NTlS ZLDl Munich 19 70 DM steels four titanium alloys and two aluminum alloys were Supersonic combustion of hydrogen in the flow field of tested at room temperature before and after exposure to elevated a flat plate in tangential flow and near bodies of revolution was temperatures for up to 3 years The steels and titanium alloys were studied in the Mach number range from 1 B to 3 2 In the flat plate exposed at 560 K (550 F) and the aluminum alloys were exposed experiments a secondary air let from a crosswise slot was used at 390 K and 420 K (250 F and 300 F) Fatigue data covering to stabilize the flame Hydrogen was injected upstream of the slot a range of fatigue lives from 1,000 to 10 to the 7th power cycles Flame stabilization on bodies of revolution was obtained due to a were obtained before and after 3 years of exposure The fatigue small annular cavity near the thickness maximum In all cases strengths after exposure were essentially the same as those before spark ignition was used The changes of pressure distribution near exposure Author the flat plate as well as changes of drag of the bodies of revolution due to heat addition were considerable Author (ESRO) N71-220871 Politecnico di Torino (Italy) lstituto di Meccanica Applicata Aerodinamica e Gasdinamica N71-22135*# Lockheed Missiles and Space Co, Palo Alto. Calif LOW PRANDTL NUMBER STAGNATION HEAT FLUX Research Lab CALCULATIONS FOR A BLUNT AXISYMMETRIC BODY IN SIX CHANNEL PHOTOMETRIC OBSERVATIONS FROM HYPERSONIC FLOW THE CV990 AIRCRAFT Final Report Aldo Muggia Jul 1970 10 p refs S B Mende and R H Eather 26 Jun 1970 36 p refs (CoritraLt EOOAR 0049 68) (Contract NASw-1997) (A0 717418 AFOSR 70 3009TR TN 63 SR 9) Avail NTlS (NASA-CR-1 17466 LMSC/N-AR-70-1) Avail NTlS CSCL 14E CSCL 2014 An investigation of the spatial extent of aurorae was Cdlculation\ are performed of the enthalpy behaviour and undertaken from College, Alaska, by the ground based television two of this wall heat flux in the staqnation region past a blunt channel (5577A and 4278A) image intensifier system and with a dxi\ymmetric body in hypersonic axial flow The case of multichannel boresighted tilting filter photometer The measurements hqll fri~strdin Ma( h niimber and consequently high temperature indicate that even on clear nights the extinction due to scattering arid low Praiidtl rluriiber in the stdqnation reqion IS considered By in the 4278A is significant unless the measurements are taken at wv[)o\iiiy eqili~ltJrlliil1flow two numerical examples are presented small zenith angles To confirm the results and to avoid the low for P6 1 If t llllnl~JC?l Author (GRA) altitude scattering problem. measurements were made on a quite arc with the 6 channel tilting filter zenith photometer during the ~71220981 Naval Ship Research and Development Center NASA CV 990 expedition These results show that in the cases Washinqton D C Dept of Aerodynamic5 observed there was no significant difference between the latitude APPLICATION OF THE METHOD OF INTEGRAL profiles of O(55771 and N2(4278) emissions Author

374 N71-22160

N71-22136# Naval Postgraduate School, Monterey Calif vicinity the boundary layer builds up faster An analysis of the INTERFACE OF MATERIALS AND STRUCTURES ON results shows that the effect of bluntness increases with the Mach AIRFRAMES. PART 2: OUTLINE OF DECISION PROCESS number Author (GRA) IN STRUCTURALDESIGN Ulrich Haupt Dec 1970 57 p refs (AD-717576. NPS-57HP0121A-Pt-2) Avail NTlS CSCL 1/3 N71-22158# Cornell Aeronautical Lab Inc Buffalo N Y The decision process in structural design becomes increasingly Aerodynamic Research Dept important with the introduction of new materials Starting from a RESEARCH ON ADVANCED GASDYNAMIC TEST consideration of present problems in structural design. an outline FACILITIES. PART 1’ STUDIES OF THE ISENTROPIC is developed for the decision process with particular emphasis on COMPRESSION TUBE AS A MEANS FOR PRODUCING interaction between materials. structures. and design This outline HYPERVELOCITY TEST FLOWS Final Technical Report. 1 however, still lacks the details which are required for an analytical Jul. 1966 - 30Jun. 1970 model of the decision process These missing details are FrankJ Stoddard Jan 1970 77 p refs identified and a practical approach toward their solution is shown (Contract AF 33(615)-5389) Author (GRA) (AD-7 17727 CAL-AD-2297-A-3-Pt-1. ARL-70-0235-Pt-1) Avail NTlS CSCL 1412 The report summarizes research conducted on the use of N71-22147# National Aerospace Lab., Tokyo (Japan). isentropic-compression techniques for producing hypervelocity test MODEL TEST ON DEFLECTED JET PIPES OF THE NAL flows The results of experiments in the pilot isentropic-compression FLYING TEST BED tube are reported and compared with theoretical predictions It IS Yoshikazu Tanabe Oct. 1970 10 p refs In JAPANESE: shown that the experimental results are, in general, in agreement with ENGLISH summary the theoretical performance predictions for both the isentropic-flow (NAL-TR-209) Avail: NTlS and the free-piston shock-tube mode of operation Theoretical Problems associated with VTOL operations of a lift-type estimates of the performance of a large-scale high-pressure facility aircraft are evaluated in order to improve flight safety. Deflecting are given which indicate that such a facility would be extremely jet pipes with different deflecting angles are tested to obtain the versatile and capable of performance far exceeding that of existing relationships between the real deflection angle and the geometrical short-duration high-speed test facilities The report provides a deflection angle, the jet pipe thrust coefficient, etc. for suppression complete documentation of the research conducted including of pitching moment caused by one engine failure. It is concluded previously unpublished work recently completed Author (GRA) that the real deflection angle is nearly 90% of the geometrical deflection angle and that the thrust coefficient of the deflecting jet N71-221598 pipes is ?st !ecs ?hac 96% :ega:d!ess c! the gecnetxa! de!!sctis:: Nannna! Aerospace hh.,Tskys (Japac). angle. Author CYLINDRICAL BOUNDARY INTERFERENCE ON VIRTUAL MASS OF A SPHERE Nagamasa Kono Nov. 1970 17 p refs In JAPANESE: ENGLISH N71-22149# McGill Univ Montreal (Quebec) Dept of summary Mechanical Engineering (NAL-TR-223) Avail. NTlS COMPUTER GRAPHICS ONJOUKOWSKI AIRFOILS In order to clarify the virtual mass increment by cylindrical J H T Wu and P P Ostrowski [1970] 11 p refs wall interference the flow field induced by a single doublet located (TN-71-2) Avail NTlS at an arbitrary point in a cylinder and having its axis oriented parallel Steady incompressible flow about a Joukowski airfoil section to the axial and radial direction and nnrmal Tn both dkections was is simulated using an IBM 360 75 digital computer and a Calcomp solved. and closed surfaces were sought by transforming the field plotter The effect of various transformation parameters as well as to an uniformly translating system. The virtual mass was calculated the Streamline pattern and pressure distribution about the airfoil is from the kinetic energy and results were compared with the case illustrated The values of the Simulation technique as a teaching of a free field. When a body is placed on the cylinder axis, tool are demonstrated The method is shown to be particularly useful boundary interference appears both as surface distortion and virtual for flow visualization as all the basic features of the Joukowski mass increase: the former is not serious unless the radius ratio of transformation and the potential flow streamline patterns are clearly the body to the clyinder does not exceed 05.but the latter is depicted Author remarkable. Results when the body is off-centered at 0.3 radius from the cylinder axis showed complex behavior depending on the N71-22156# Air Force Systems Command Wright-Patterson orientation of motion. Author AFE Ohio Foreign Technology Div THE EFFECT OF EDGE BLUNTNESS OF A FLAT PLATE N71-22160# National Aerospace Lab., Tokyo (Japan). ON HEATTRANSFER IN A SUPERSONIC FLOW AERODYNAMIC CHARACTERISTICS OF A FLARED BODY L V Kozlov 2 Dec 1970 15 p refs Trans1 into ENGLISH WITH BLUNT NOSE from the book “lssled Teploobmena v Potokakh Zhidkosti I Gaza Takashi Tani. lwao Kawamoto. Seizo Sakakibara. Junichi Noda. and Moscow, Izd-Vo Mashinostr , 1965 p 103 109 Hiroshi Higuchi Oct. 1970 17 p refs In JAPANESE. ENGLISH (AD-717825. FTD-MT-24 274-70) Avail NTlS CSCL2014 summary The effect of edge bluntness of a flat plate on heat transfer (NAL-TR-221) Avail: NTlS is experimentally investigated in the region where anisotropic The aerodynamic characteristics of a flared body with blunt conditions do not exist on the limit of the boundary layer The nose were investigated theoretically and compared with the result experiments were carried out by means of a wind tunnel having a of experiments conducted in a supersonic wind tunnel at Mach 110 x 110 mm test section with nozzle velocities in the Mach numbers 2 and 3. Measurements of the static pressure. as well as range from 2 to 4 M Heat transfer was evaluated on a flat plate the total pressure. around the blunt nosed body immediately with cylindrical bluntness in a range of a given relative bluntness revealed that the blunt nose caused a strong shear flow field in the The dependence of the nondimensional heat-transfer coefficient on vicinity of the body surface and that the pressure distribution the Reynolds number is illustrated in a graph The data obtained measured on the flare of the blunt body was markedly different from with a blunt-edged flat plate are compared with those obtained on that of a similar body with sharp nose. Analysis based on the a sharp-edged flat plate The distribution of local heat fluxes on concept of two parallel layers which approximated the shear both plates is presented in graphical form and shows that at given region showed the pressure distribution to be quite acceptable in large ratios the local value of the heat flux on a blunt-edged plate simulating the experimental distribution for the flare due to a blunt is always smaller than on a sharp edged plate but in a given nosed bodv. Author

375 N-71-22166

N71-22166p Cornell Univ lthaca N Y Lab of Plasma Studies types of color CRTs are not suitable for cockpit displays and the LABORATORY STUDY OF HIGH-BETA PLASMA SHOCK Penetron and other non-patterned screens could be used in low WAVES ambient light areas Author (GRA) David L Morseand William W Destler Jul 1970 34 p refs (Contract NO0014 67 A 0077 0002) (AD 717397 LPS 531 Avail NTlS CSCL20/9 N71-22186# Deutsche Gesellschaft fuer Luft und Raumfahrt A plasma wind tunnel has been used to generate shock Cologne (West Germany) waves at rest in the laboratory reference frame The upstream FUTURE COMMERCIAL FLIGHT TECHNIQUES pressure ratio beta is in the range 1 to 3 and the Mach number [VERKEHRSFLUGTECHNIK DER ZUKUNFT] basea on tne fast magnerosonic wave speeu 13 3 10 5 ilie siiu~k ivov 1970 239 p refs in GERiviAiv Proc of rhe DGiR Syr~~p wave is formed by lettinq the plasma wind impinge on the field Hamburg 29Jan 1970 of a magnetic obstacle The resulting shock is primarily transverse (DLR MITT 70 15) Avail NTlS ZLDl Munich 50 DM and exhibits a thickness of 1 to 1 1 /2 times the ion inertial length (c/omega sub pi) The shock thickness decreases with increasing CONTENTS Mach number and increases as the ion mass is increased Magnetic 1 THE VTOL JET FOR A FUTURE V/STOL TRANSPORT fluctuations in the shock front are observed with frequencies near SYSTEM B Huinink (Dornier Werke Friedrichshafen) and K B the ion gyral frequency Comparisons of these results with those Brink (Dornier Werke Friedrichshafen West Ger p 7 32 refs of other experiments and with the earths bow shock are made Author (GRAI 2 MARKET SITUATION FOR V/STOL AIRCRAFT H Hoeppner (Ver Fluqtech Werke Fokker Munich West Ger I N71.2216811 Air Force Svstems Command ,Wright-Patterson p 33 52 AFB Ohio Foreign Technology Div 3 AIR SPACE CONGESTION AND THE COMPOUND INVESTIGATIONS OF STRAINS AND STRESSES BY MEANS HELICOPTER S I Sikorsky (United Aircraft Intern) p 53 66 OF MOIRE PATTERNS [ISSLEDOVANIYA DEFORMATSII I NAPR YAZHENII METODOM MUAROVYKH POLOSl 4 COMMERCIAL INTERPRETATION OF VTOL AIR LINERS I P Sukharev et al 9 Dec 1970 182 p refs Trans1 into H G Klug (Hamburger Flugzeugbaul p 67 92 ENGLISH from the Russian FTD HC 23 6 I4 70) Avail NTlS CSCL 20/11 (AD 7 17826 5 PROPELLER DRIVEN VTOL AIRCRAFT U Dornseifer The report contains a discussion of the theoretical principles (Messerschmitt Boelkow Blohm Munich) p 93 104 experimental procedure and the application of a new experimental method for studyinq strains and stresses of machine parts and 6 APPLICATION ANALYSIS OF VTOL AIRCRAFT FOR structural elements in which the moire effect is used The method FUTURE INTEGRATED INTERCITY TRAFFIC SYSTEM H R permits experimental solution of a broad class of problems It has Buschhorn (Ver Flugtech Werke Fokker Bremen) p 105 120 a number of advantages over other techniques and IS distinguished by simplicity of the experimental procedure and equipment 7 VARIABLES INFLUENCING THE DIRECT OPERATIONAL Application of the method for stiidymg plate5 and membraiices IS COSTS OF A V/STOL PASSENGER AIRCRAFT K A Wendt (Ver discussed in qreatest detail Examples are presented from machine Flugtech Werke Fokker Munich) p 121 132 and aircraft buildinq and construction practiLe Author (GRAI 8 LIFT FANS AND A FLEXIBLE SOLUTION FOR THE DEVELOPMENT OF VTOL PASSENGER AIRCRAFT A Hartmann N71-22169# Catholic Univ of America Washington D C lnst (Motoren und Turbinen Union) p 153 170 refs of Ocean Science and Engineering WIND INDUCED VIBRATIONS OF SKEWED CIRCULAR 9 INLET FLOW AND OUTLET JET INFLUENCE ON THE FLOW CYLINDERS AROUND THE WINGS OF TWO LIFT FAN CONFIGURATIONS Gary H Koopmann Sep 1970 26 p refs H Neppert (Hamburger Fluqzeugbaul p 170 218 refs (Contrdct NO0014 68 A 0506 0001) (AD 717739 Rept 70 11) Avail NTlS CSCL20/4 10 CONSIDERATIONS REGARDING THE DESIGN OF THE A general discussion of the various technique.. used to COCKPIT FOR A V/STOL AIRCRAFT J Lindemann (Hamburger measure the oscillating lift coefficients of wind induced vibrations Flugzeugbaul p 219 228 of circular cylinders is presented The discussion is summarized 11 AIR TRAFFIC SECURITY TODAY AND TOMORROW with a brief outline of the various categories of research efforts being H Herb (DFVLR Brunswick) p 229 237 refs conducted on fluid induced vibrations Each category is referenced to an appropriate group of papers which exist in the literature A simple method for determining the oscillating lift coefficient for the N71-22187# Dornier-Werke G m b H , Friedrichshafen (West wind induced vibration of a circular cylinder is developed and Germany) applied to a typical problem where the longitudinal axis of the THE VTOL JET FOR A FUTURE V/STOL TRANSPORT cylinder IS skewed relative to the direction of the oncoming flow SYSTEM [ DAS SEN K RE CHTSTA RTE N DE Author (GRA) STRAHLF LUGZE UG IM RAHMEN El NES ZU KUENFTIGE N VSTOL-TRANSPORTSYSTEMS~ N71-22174# Aeroiiautical Systems Div Wright Patterson AFB B Huinink and K B Brink ln DGLR Future Com Flight Tech Ohio Nov 1970 p 7 32 refs InGERMAN THE FEASIBILITY OF UTILIZING COLOR CATHODE Avail NTIS. ZLDl Munich. 50 DM RAY TUBES FOR AIRCRAFT CREW STATION DISPLAYS In view of the future demand in civil VTOL aircraft the Technical Report. Feb May 1970 advantages offered by the development of the DO-31 aircraft Ronald S Vokits Nov 1970 47 p refs provide a basis for further development An analysis of the (AD 717655 ASD TR 70 33) Avail NTlS CSCL 1/4 aerodynamic characteristics. the aircraft safety. and operating costs The report compiles the characteristics of various leads to the conclusion that the German aerospace industry has state-of the art color cathode ray tubes (CRTs) The structures high chances in this field ESRO theory of operation and technical advantages and disadvantages of the various color CRTs for use in aircraft display instruments are N71-22188# Vereinigte Flugtechnische Werke . Fokker G m b H , evaluated The results Of the study were that presently available Munich (West Germany)

376 N71-22197

MARKET SITUATION FOR V/STOL AIRCRAFT N71-22193# Vereinigte Flugtechnische Werke - Fokker G m b H IMARKTSITUATION FUER V/STOL-FLUGZEUGE] Munich (West Germany) H Hoeppner In DLGR Future Corn Flight Tech Nov 1970 VARIABLES INFLUENCING THE DIRECT OPERATIONAL p 33-52 InGERMAN COSTS OF A V/STOL PASSENGER AIRCRAFT Avail NTlS ZLDl Munich 50 DM [EIIYFLUSSGROESSEN AUF DIE DIREKTEN The market situation for V/STOL aircraft IS assessed for BETRI E ESK OSTE N El NE S both the military and civil aviation fields The design and testing of V/STOL-PASSAOIERFLUGZEUGES] prototypes. taking into account the special operational requirements K-A Wendt In DGLR Future Corn Flight Tech Nov 1970 IS discussed and a specific design is proposed, a tilt wing aircraft p 121 132 InGERMAN with propeller drive in a tandem configuration ESRO Avail NTIS. ZLDl Munich 50 DM The aircraft under consideration is a tilt wing. propeller driven tandem aircraft with a flight range of 800 km The different N71-22189# United Aircraft International Inc . Cologne (West sources of operational costs are described and the influence of Germany) changes in the parameters are discussed Finally. the tradeoff AIR SPACE CONGESTION AND THE COMPOUND between increased cost versus overall travel time IS mentioned HELICOPTER [DIE LUFTRAUM-UEBERFUELLUNG UND DER ESRO VEREUND-HUBSCHRAUBER] S I Sikorsky In DLGR Future Corn Flight Tech Nov 1970 N71-22lw# Motoren- und Turbinen-Union Muenchen G m b H P 53- 66 In GERMAN (West Germany) Avail NTlS ZLDl Munich 50 DM As the majority of civil air transport is over short haul LIFT FANS AND A FLEXIBLE SOLUTION FOR THE distances and in view of air traffic control problems a VTOL DEVELOPMENT OF VTOL PASSENGER AIRCRAFT solution to these problems is proposed In particular a compound [GEELAESEANTRIEBE UND ElNE IN JEDER WEIS FLEXIBLE and a normal helicopter design are described meeting the LOESUNG FUER DIE ENTWICKLUNG VON requirements derrved from the above conditions The use of advanced VTOL-VERKEHRSFLUGZEUGEN] composite materials and retractable rotors is briefly discussed A Hartmann In DGLR Future Com Flight Tech Nov 1970 ESRO p 153 - 170 refs In GERMAN Avail NTIS. ZLDl Munich 50 DM The various design alternatrves in VTOL aircraft thrust N71-22190# Hamburger Flugzeugbau G m b H (West Germany) generation are compared, and a design with separate gas generator COMMERCIAL INTERPRETATION OF VTOL AIR LINERS and thrust generator is discussed The reauirements imwsed on iMARKTGERECHT€ AUSLEGUNG VON the connecting tube. the gas generator. the fans. and their VTOL-VERKEHRSFLUGZEUGEN] combination into a propulsion aggregate Finally. the integration of H-G Klug In DGLR Future Corn Flight Tech Nov 1970 the propulsion system into the aircraft body is discussed ESRO p 67-92 In GERMAN I Avail NTIS ZLDl Munich 50DM The reliability and operational requirements of short haul N71-22196# Hamburger Flugzeugbau G m b H (West Germany) VTOL aircraft are discussed A particular design is presented INLET FLOW AND OUTLET JET INFLUENCE ON TH€ featuring lift- and liftjcruise fans, using a conventional jet engine FLOW AROUND THE WINGS OF TWO LIFT FAN as a gas generator The advantages of this design are outlined. in CONFIGURATIONS [ZULAUF- UND STRAHLEtNFLUE8SE partecular low nose generation and a spacious compartment ZWEIER HUEGEELAESEKONFiGURAllONEN AUF DIE ESRO FLUEGELSTROEMUNG] H Neppert In DGLR Future Corn Flrght Tech Nov 1970 N71-22191# Messerschmitt-Boelkow-BIohm G m b H , Munich p 170-218 refs InGERMAN (West Germany) Avail NTIS, ZLDl Munich 50 DM PROPELLER- DRI VE N VTOL AI RCR AFT Two configurations of lift fans were investigated as to the [PROPELLERGETRAGENE VTOL-FLUGZEUGE] influence of the inlet and outlet flow on the aerodynamic forces U Dornseifer In DGLR Future Corn Flight Tech Nov 1970 and moments A half-model was placed into a wind tunnel to p 93- 104 In GERMAN measure the pressure distributron over Several airfotl SeCtlOns The two Avail NTIS. ZLDl Munich 50 DM configuratlons under test were compared concernmg longitudinal The advantages of propeller-drwen tilt-wing aircraft for intercity stability. cruising flight drag, and tilting moments ESRO transport are outlined The advantages are in particular a lower noise generation as compared to both conventional and V/STOL)et engine powered aircraft. and the excellent STOL properties N71-22196# Hamburger Flugzeugbau G m b H (West Germany) ESRO CONSIDERATIONS REGARDING THE DESl6N OF THE COCKPIT FOR A V/STOL AIRCRAFT [UEBERLEQUNGEN N71-22192# Vereinigte Flugtechnische Werke - Fokker G m b H ZUR GESTALTUNG DES COCKPITS ElWS eremen (West Germany) V/ STOL-TR A N SPORTE R APPLICATION ANALYSIS OF VTOL AIRCRAFT FOR SI J Lindemann In DGLR Future Corn Flight Tech Nov 1970 FUTURE INTEGRATED INTERCITY TRAFFIC SYSTEM p 219 228 InGERMAN [EINSATZANALYTISCHE UNTERSUCHUNGEN EINES Avail NTIS. ZLDl Munich 50 DM ZUKUENFTIGEN INTERCITY-VERKEHRS-VERBUND-SYS- A mockup of a V/STOL aircraft cockpit is presented The TEMS MITVTOL-FLUGZEUGEN] requirements imposed on such a cockpit are outlined. and the H -21 Buschhorn In DGLR Future Corn Flight Tech Nov 1970 resulting design is described ESRO p 105 -120 InGERMAN Avail NTIS, ZLDl Munich 50 DM The operational problems of future integrated intercity VTOL N71-22197# Deutsche Forschungs- und Versuchsanstalt fuer traffic are discussed A model is developed taking into account Luft- und Raumfahrt. Brunswick (West Germany) InSt her conventional ground transfer traffic to derive the optimum condi- Flugrnechanik tions for integrating different means of transport to minimize travel AIR TRAFFIC SECURITY. TODAY AND TOMORROW IDIE time ESRO SICHERHEIT IM LUFTVERKEHR. HEUTE UNO MORGEN~

377 N71-22198

H Herb In DGLR Future Corn Flbght Tech Nov 1970 Maryland. conforms to the latest NavFac design criteria except that p 229 237 refs InGERMAN a surge suppressor was not specified or provided The objectives Avail NTIS. ZLDI Munich 50 DM of the study were to examine the effect of hose diameter and The development of accident figures m air traffic IS discussed, length on the level of charge on fuel entering a refueler and to the factors influencing them, human errors. technical failures. clear determine the effectiveness of the relaxation and bottom-loading air turbulence and cosmic radiation are described ESRO facility in reducing the electrostatic hazard during refueler loading Author (GRA)

N71-22198# National Research Council of Canada. Ottawa (Ontario) N71-22241# Cornell Univ lthaca N Y Graduate School of QUARTERLY BULLETIN OF THE DIVISION OF Aerospace Engineering MECHANICAL ENGINEERING AND THE NATIONAL BOUNDARY LAYER SEPARATION AERONAUTICAL EStABLISHMENT, 1 OCTOBER -31 Demetrios Pyrros Telionis (Ph D Thesis) Sep 1970 147 p refs DECEMBER 1970 (Contract F44620-69 C-0063) 31 Dec 1970 84 p refs (AD-717772 AFOSR-70-2404TR) Avail NTlS CSCL 20/4 (DME/NAE-l970/4/) Avail NTlS The phenomenon of separation is one of the most critical features of the flow of viscous fluids about rigid bodies In the CONTENTS. two-dimensional steady-state case Prandtls criterion (vanishing of 1 PRESENT STATUS OF ELECTRIC AUTOMOBILES skin friction) appears to be successful in predicting separation J J Gottlieb p 1 38 refs Numerical integrations have indicated that the boundary-layer 2 THE DEVELOPMENT AND TESTING OF A PYROTECHNIC equations behave singularly at separation and Goldstein has SEEDING SYSTEM ON A MODIFIED T-33 G K Mather suggested analytical formulas describing this situation Prandtls p 39 54 refs criterion fails to predict meaningful separation for unsteady problems and this seems to have been mostly unnoticed A general and formal definition of boundary layer separation IS given based on the concept of Goldsteins singularity It is demonstrated how from this N71-22200# National Aeronautical Establishment Ottawa definition one can deduce meaningful criteria for the unsteady (Ontario) Flight Resedrch Lab problem as well as other complicated cases such as THE DEVELOPMENT AND TESTING OF A PYROTECHNIC three-dimensional or compressible separation flow A simple formula SEEDING SYSTEM ON'A MODIFIED 1-33 is suggested for the component of the velocity in the direction G K Mather NRC of Can Quart Bull of the Div of Mech In parallel to the wall and it is demonstrated that this is in agreement Eng and the Natl Aeron Estab Oct Dec 1970 31 Dec 1970 with Goldsteins results for small distance from separation along the p 39 54 refs wall A differential equation is derived from the momentum equation Avail NTlS which contains the velocity profile at separation A few applications A T-33 aircraft was modified and instrumented to meet are included demonstrating solutions of this equation which in the requirements for a seeding aircraft in hail suppression the unsteady case contains the velocity of the phenomenon of experiments All systems including radar flare fire control. and separation too GRA instrumentation proved extremely reliable during field tests The design of the flares proved optimum for the Alberta storms The chaff flare was useful in gaining confidence in targetting accuracy N71-22294# Cambridge Univ. (England). Dept. of Engineering. Author THE OFF DESIGN ANALYSIS OF FLOW IN AXIAL COMPRESSORS N71-22221# Joint Publications Research Service. Washington. H. Daneshyar 1970 56 p refs DC (CUED/A-Turbo/TR-l9) Avail: NTlS EXPERIMENTAL INVESTIGATION OF FLUID FLOW ALONG The existence and uniqueness of the solutions obtained A TRAVELING WAVE from the streamline curvature method of calculating flow through V I Merkulov et al In I~SHydrodyn Probl of Bionics 12 Mar turbomachines are examined for several operating points of a 1971 p 153-157 Rolls-Royce compressor, It is shown that under certain conditions Avail NrlS the truncation errors in the numerical solution can become large Mathematical investigations of flow of a viscous fluid along and hence give rise to the violation of the uniqueness conditions. a traveling wave utilize a system of coordinates linked with the The computer program may then give wrong answers to the wave crest In such a system the region boundary becomes a physical problem. The conditions for existence and uniqueness may constant undulating surface each point on which slips along the be violated when the meridional velocities are small (e.g. near stall) tangent toward the fundamental stream Since the forces to which or when there are regions of choked flow. Flow for an operating the body is subjected are independent of selection of inertial point in the stall region is computed by suitable modifications to system of coordinates a coordinate system linked to the wave crest minimize the truncation errors and hence to obtain a unique was used in this investigation The construction of the model, solution. This is compared with the results of the actuator disc layout of measuring devices and method of measurement are theory and other experiments. Author described AL

N71-22300# ARO. Inc ,Arnold Air Force Station Tenn N71-22232# Naval Research Lab Washington D C INVESTIGATION OF BLUNT FIN-INDUCED FLOW STATIC ELECTRICITY MEASUREMENTS DURING SEPARATION REGION ON A FLAT PLATE AT MACH REFUELER LOADING Interim Report NUMBERS 2.5 TO 4.0 Final Report Joscph T Leonard and Homer W Carhart 5 Jan 1971 26 p ErnestJ Lucas AEDC Jan 1971 25 p refs refs (Contract F40600 7 1 -C-0002) (AD 717347 NRL 7203) Avall NTlS CSCL21/4 (AD-717717. AEDC TR-70-265) Avail NTlS CSCL 2014 The generation of electrostatic charge by JP-5 type jet Tests were conducted at Mach numbers 2 5 to 40 to fuel wa5 examined at a truck fill stand which has both a 30 second investigate the effects of cylindrically blunted fins on the flow over relaxation chamber and bottom loadinq capability The installation a flat plate at zero angle of attack The free-stream Reynolds whirti 15 located at Patuxent Naval Air Station in Patuxent number, based on the distance from the blunt fin to the flat plate

378 N71-22379

leading edge, ranged from 2.800.000 to 4.700 000 Pitot pressure detection and false alarm rates due to thermal noise and crosstalk. profiles were obtained in the fin induced flow separation region biphase coding. ground multipath. satellite LIT antenna optimaation. Increasing the thickness of the fin was found to increase the size computation of satellite transmitter linear range requirements for of the three dimensional separation area Pressure distributions as LIT. alternate design approaches for the LIT. aircraft antenna well as examples of the oil flow and schlieren photographic pattern measurements. a multiple tap surface wave delay line. and coverage are presented Author (GRA) a LIT surveillance computer program JM

N71-22331# National Aeronautical Lab. Bangalore (India). ANNUAL REPORT OF THE NATIONAL AERONAUTICAL N71-22345# Michigan Univ Ann Arbor Dept of Naval LABORATORY. 1969 -1970 Architecture and Marine Engineering 1970 91 p refs THEORY OF HIGH ASPECT RATIO PLANING SURFACES Avail: NTlS Technical Report. 1 May 1969 30 Apr 1970 Summaries of research activities are presented The laboratory's Young-Tsun Shen Nov 1970 135 p refs major project was the design. fabrication. commissioning. and (Contract N00014-67-A-0181-0019) calibration of a 4-R trisonic wind tunnel. Other projects reported (AD-7 17667 Rept 102) Avail NTlS CSCL 13/ 10 include the following areas of research. (1) aerodynamics. (2) A high-aspect-ratio planing surface gliding on a stream structural sciences, (3) materials science. (4) propulsion. (5) of an infinitely deep. incompressible inviscid and gravity-free fluid electronics. (6) instrumentation, (7) mathematical sciences. (8)pilot IS treated This complicated problem is decomposed into two plants. and (9) technical aid and assistance D.L.G. relatively simpler boundary-value problems (1) The near-field boundary-value problem is valid only in the neighborhood of the planing surface The problem is solved by the classical hodograph method The second-order inner problem is also shown to be a N71-22339*# TRW Systems Group, Redondo Beach. Calif THE APPLICATIONS OF SATELLITES TO plane irrotational flow and the solution is obtained by following the same procedure as in the first-order inner solution (2) The far-field COMMUNICATIONS, NAVIGATION AND SURVEILLANCE boundary-value problem is valid only far away from the planing FOR AIRCRAFT OPERATING OVER THE CONTIGUOUS surface The first-order outer solution is shown to be a trivial UNITED STATES. VOLUME 1 : Technical Report uniform flow The outer velocity potential is defined in the whqle J. H. Craigie. A. Garabedian. D. D. Morrison. I. Zipper et a1 Dec. space by harmonic continuation The second-order solution is then 1970 314 p refs ;hodvz be stiiniiag d iiiiirig-iirie soiurion Tne unxnown strength icuiiiraci NA35-ii 535) it iu (NASA-CR-117760; TRW-14671-6007-RO-00-Vol-1) Avail: NTlS of singularities is obtained by matching of the velocity potential Then a matching of the free-surface deflection provides a height HCSG.OO/MFS0.95 CSCL 17G reference for the planing surface The location of the planing Satellite applications to communications, navigation, and surface with respect to the undisturbed free surface is uniquely surveillance requirements are discussed for aircraft operating beyond defined In order to obtain a unique second-order solution, it IS 1975 over the contiguous United States and adjacent oceanic necessary to solve the third-order outer solution The detail of this transition regions. The highest priority satellite applications are solution is presented A numerical solution for a planing plate of surveillance and rapid collision warning communicattons and it is arbitrary angle of attack is presented A downwash correction IS concluded that the necessary technology is available A system also *~J~(iedit shov.n ;r.xhcma:oca!!q :ha: thc pre5ent Theory zcncepi based on ihe tecnrioiugy was synthesized. k sareliite-based can be applied to V shape or general-shape planing surfaces with air traffic control concept is described which consists of satellites. curvature in the spanwise direction Author (GRA) ground stations. and electronic hardware, and provides support for a wide range of aircraft. All users have a Location/ldentification Transmitter (LIT) and antenna for surveillance which permits N71-22374# Cambridge Univ (England) Dept of Engineering identification and three-dimensional location of all airborne aircraft EXPERIMENTAL PRESSURE DISTRIBUTIOfUS ON approximately every second; and most of these aircraft are also AEROFOILS INTRANSVERSE AND STREAMWISE OUSTS equipped with LIT backlink receivers providing short access time D W Holmes 1970 38 p refs mid-air collision warning. In addition. higher cost aircraft can have (CUED/A-Turbo/TR-Zl) Avail NTlS an option of satellite navigation equipment which can provide Experiments are described tn which measurements were highly accurate three-dimensional position and velocity information. made of the force and pressure fluctuations on an aerofoil in an The use of satellites for rapid and reliable data communication unsteady flow Two types of unsteady flow are studied (1) a from any place in the country to an aircraft anywhere over the transverse gust flow and (2; a streamwise gust flow In Both cases country also is discussed. Author the gust was non convective and had a propagation speed that was less than the mean flow velocity All the experiments were parformed with a low reduced frequency. the maximum value reached being 0 2 based upon the half chord The streamwise gust N71-22340*# TRW Systems Group Redondo Beach, Calif results are presented to show separately the responses due to THE APPLICATIONS OF SATELLITES TC incidence and thickness For the transverse gust flow a detailed COMMUNICATIONS, NAVIGATION AND SURVEILLANCE picture is presented of the pressure fluctuation in the trailing edge FOR AIRCRAFT OPERATING OVER THE CONTIGUOUS region and results are also presented demonstrating the effect of UNITED STATES. VOLUME 2 APPENDICES incidence It is further shown for both flows that the form of the A J Ma!linckrodt. C S Miller C S Easley. G E Clark R J Hane lift fluctuation due to a harmonic gust is also harmonic to a small et al Dec 1970 180 p refs approximation Author (Contract NAS5-21535) (NASA-CR-117759 TRW-1467 1-6008-RO-OO-Vol-2-App) Avail

NTlS CSCL 17G N71-22379# Polhemus Navigation Sciences. Inc , Burlington. Appendices of supporting information for the application vt of satellites to aircraft communication navigation. and surveillance VERTICAL NAVIGATION STUDY FOR THE CONCORDE over the contiguous United States are presented including future SST. VOLUME 1 : SUMMARY, SIMULATION. ANALYSIS air traffic control loads and air traffic system organization and AND RECOMMENDATIONS Final Report management Specific equipment studles are summarized including Mar 1970 28 p location/identification transmitter (LIT) pricing quotations. pulse (Contract UKTSD-C-4539)

37 9 N71-22380

N71 2238011 Polhemus Navigation Sciences Inc Burlington M Carmel In Natl Council for Civil Aviation Civil Aviation in the vt 1970's 1969 10 P VERTICAL NAVIGATION STUDY FOR THE CONCORDE Avail NTlS HC$600/MF$095 SST VOLUME 2 TECHNICAL SIMULATION, ANALYSIS Planning and developments in civil aviation are outlined AND RECOMMENDATIONS Final Report Considered are future technological and economic trends, the Mar 1970 217 p operation of new transport aircraft the production of transport (Contra't UKTSD C 4539) aircraft in Israel the planning of modern airports and other related (PNSl TR 70 0301 2 Vol 2) Avail NTlS problems GG IPNbI 1H 700.301 1 VoI 1) Avail NIIS An analysis of vertical navigation for the Concorde aircraft is presented Subjects discussed are 11 computer simulation of N71-22383# Federal Aviation Administration. Washington. D C the Concorde and its interrelated guidance systems (2)evaluation TECHNOLOGICAL TRENDS AND FORECASTS FOR THE of several levels and combinations of guidance system aircraft 1970's performance and meteorological forecast errors on ability to predict Joseph D Blatt In Natl Council for Civil Aviation Civil Aviation and achieve planned profiles over a variety of airline routes (3) in the 1970's 1969 13 p evaluation of the effects of certain air traffic control initiated Avail NTlS HC$600/MF$095 commaiids on crew workload fuel schedule reliability and controlled Traffic generating potentials of air transportation and the time of arrival and (4) synthesis of additimal operational techniques problems that must be solved to insure increasing systems capacity and equipment requirements to assure that dir traffic control and are discussed by analyzing market forecasts of unconstrained ?re\" perform3"ce requirements car: be met 'Author growth for the U S air traffic Large scale changes to employ 747 aircraft and SST aircraft demand sophisticated technology and high speeds Improved air traffic control and navigation systems as well N71-22381# National Council tor Civil Aviatian Tel Aviv (Israei, as passenger handling facilities are proposed that rely on automatic CIVILAVIATION IN THE 1970's Simulators to provide guidance for traffic optimization Volumetric 1969 303 p Presented at the Ann Symp on Current Probl navigation. aided by scanning satellites atomic clocks, ground to in Civil Aviation Tel Aviv Israel 8 9 Oct 1969 air and air to ground synchronization techniques precise time and Avail NTlS HC$600/MF$D95 precise frequency standards provide the required flexibility in the use of air space and meet specific operational needs of air traffic CONTENTS developments GG 1 ADDRESS BY THE MINISTER OF TRANSPORT M Camel (Israel Ministry of Transport and Communications N71-22384# Institute of Transport Aviation Paris (France) Tel-Aviv) 10 p ECONOMIC ASPECTS OF THE EXPECTED DEVELOPMENT 2 TECHNOLOGICAL TRENDS AND FORECASTS FOR IN AIR TRANSPORT IN THE NEXT DECADE THE 1970s J Blatt (FAA Waslungton DC) 13 p D Jean Mercier In Natl Council for Civil Aviation Civil Aviation in the 1970~196913 p 3 ECONOMIC ASPECTS OF THE EXPECTED DEVELOPMENT Avail NTIS HC$600/MF$095 IN AIR TRANSPORT IN THE NEXT DECADE J Mercier (Inst of The main positive and negative economic aspects directly Transport Aviation Paris France) 13 p concerning commercial aviation development in the next decade 4 PROBLEMS OF CIVIL AVIATION IN THE NEXT DECADE are discussed (1)financing appears to be one of the most complex M Ben Ari (EL AL Israel Airlines Ltd) 28 P problems to solve. (2) profitability owing to heavier charges and labor costs, will perhaps not be able to maintain a good level, (3) 5 THE E747 AND DEVELOPMENT OF THE SST vertical integration for extensions of transport activities at the level G Snyder (Boeing Co Seattle Wash 53 p of tourism and customer facilities (4) the uncertainty concerning the size of firms which will have to meet these commitments (5) 6 CONTINUED PROGRESS ON CONCORDE M G Wilde the consequences at the economic and organizational level of (British Aircraft Corp Filton England) 29 p maintaining or increasing the flexibility in traffic. (6) adaptation to the changing market which IS developing rapidly. and (7) the 7 ELALS PLANNING FOR THE INTEGRATION OF increasing importance of the operations preceding and following THE B 747 S Eshel (EL AL Israel Airlines Ltd) 8 p the actual transport process with regard to surface transport media Author 8 THE AIRPLANE AND THE AIRPORT L Achitoff (Port of New York Authority N Y ) 28 p N71-22385# ELALlsrael Airlines Ltd Tel Aviv 9 ACCOMMODATING PASSENGERS AND CARGO D C Ramage (British Airports Authority London England) 27 p PROBLEMS OF CIVIL AVIATION IN THE NEXT DECADE M Ben Ari In Natl Council for Civil Aviation Civil Aviation in 10 DEVELOPMENT OF CIVIL AVIATION IN ISRAEL IN THE the 1970s 1969 28 p 1970s R Hare1 (Israel Ministry of Transctort and Communications Avail NTlS HC$6 OO/MF$O 95 Tel Aviv) 21 p T,he main problems are listed that will become critical with 11 TRtNDS IN SPACE ACTIVITY D Abir (Technion Israel the introduction of giant and supersonic aircraft into international civilian air transport (1) financing (2) economics of airline lnst of Tech Haifa) 4 p 12 FROM APOLLO 11 TO THE SPACE STATIONS OF operations (3) marketing and development of traffic (4) security THE FUTURE H Cohen (NASA Washington D C) 29 p problems (5) overland transportation and ground services and (6) charter fliqhts Considerable emphasis IS placed on expected air traffic developments in Israel GG 13 CONTRIBUTIONS OF THE SPACE PROGRAMME TO AVIATION H Cohen (NASA. Washington. D C) 25 p

N71-22386# Boeing Co , Seattle. Wash THE 8-747 AND DEVELOPMENT OF THE SST N71-22382# Israel Ministry of Transport and Communications G Snyder In Natl Council for Civil Aviation Civil Aviation in the Tel-Aviv 1970's 1969 53 p ADDRESS BYTHE MINISTER OF TRANSPORT Avail NTlS HC$60D/MF$095

380 N71-22428

The 747 and SST airplanes are designed to meet the centers of populatior and iidustry Considered are passenger and challenges of the expanding air travel market of the 1970’s Both cargo travel between the aircraft and the private car, public service airplanes are designed to operate from existing airports and to vehicle, truck railway train. etc . with application to Heathrow minimize noise at the airports The SST will operate so as to airpon and its handling of larger and faster aircraft The aircrah is preclude sonic boom problems en route by operating international considered the starting point of the systems approach followed by routes at supersonic speeds. and domestic routes at transonic airline/airport administration and cooperation with government speeds The 747 status reflects the confidence of the initial design levels as well as a scheduling for concept integration GG Development flight testing has been essentially completed. and the airplane characteristics have been proven to permit initiation of FAA certification demonstration Analysis of flight data indicates the N71-22391# Israel Ministry of Transport and Communications airplane Performance IS equal or better than predicted The only Tel-Aviv remaining developmental area of significance relates to engine DEVELOPMENT OF CIVIL AVIATION IN ISRAEL IN THE performance Author 1970‘s R Hare1 In Natl Council for Civil Aviation Civil Aviation in the 1970s 1969 21 p N71-22387# British Aircraft Corp , Filton (England) Avail NTlS HC$6 OO/MF$O 95 CONTINUED PROGRESS ON CONCORDE Four main points are stressed in the development of civil M G Wilde In Natl Council for Civil Aviation Civil Aviation in aviation in Israel (1) aviation is regarded as a leading branch of the 1970s 1969 29 p the national economy 12) cargo, in terms of extent may take Avail NTlS HC$6 OO/MF $0 95 precedence over passengen, (3) measures to improve the supporting Certification flight development for the Concorde IS outlined. infrastructure in handling expected growth in passenger and reported flight testing on two prototypes included 1500 hours of cargo traffics and (4) emphasis on systems planning in reaching endurance flying and direct application on airline routes important decisions A master-plan presently incorporates electronic Improvements during design progress are described and operating low-approach aids and communications as well as the introduction cost trends are analyzed Revenue yields. costs and load factors of terminal radar equipment to meet the requirements for increased for the Concorde and the remaining subsonic traffic clearly prolect air traffic operations during the 1970s GG a single class operation for the supersonic transport as the best economic choice GG N71-22394*# National Aeronautics and Space Administration. Washington D C CONTRIBUTIONS OF THE SPACE PROGRAMME TO r N71-22388# ELAL Israel Airlines, Ltd , Tel Aviv 1 EL-AL’S PLANNING FOR THE INTEGRATION OF THE A VlATlO N H Cohen In Natl Council for Civil Aviation Civil Aviation in the 0-747 1970s 1969 25 p S Eshel In Natl Council for Civil Aviation Civil Aviation in the r (NASA TM-X-67073) Avail NTlS CSCL22A 1970s 1969 8 p Contributions to air transport safety resulting from Avail NTlS HC /6 OO/MF$O 95 developments conducted by space programs are discussed Subjects The airplane is only one component in a complex system presented are (1) meteorological and navigation satellites. (21 MIIM5tmg of man-mer. equrpment, strumure know-how. methods communications satellites (3)flight recorders (4)structural analysis. and procedures all of which are required to enable the airrrah to r5r ttieitidi gutuance systems (61systems for monitoring physical perform its function flying Described are some planning activities condition of flying personnel and (7) manufacturing processes and preparations for the integration of the 747 aircrah into Israel under conditions of weightlessness and vacuum to produce new airline operations Author materials Author

N71-22426# School of Aerospace Medicine Brooks AFB Tex N71-22389# Pon of New York Authority. N.Y. Aviation Technical COCKPIT NOISE WITHIN TRAINER AIRCRAFT Final Report, Services Div. THE AIRPLANE AND THE AIRPORT Feb Oct 1970 Donald C Gasaway Dec 1970 23 p refs LOUIS Achitoff In Natl. Council for Civil Aviation Civil Aviation (AD-717852 SAM-TA-70 95) Avail NTlS CSCL 2011 in the 1970s 1969 28 p Routine unprotected exposure to acoustic noise within cmkpits Avail. NTlS HC$G.OO/MF$0.95 of many trainer aircraft represents potentially hazardous stress The The parameters that require evaluation in the planning of character of the acoustic noise found within the cockpits of fixed- and an international airport intended to accommodate new generation. ROTARY-winq aircraft used primarily for flying training is described high capacity aircraft are discussed. The infrastructure of and illustrated The effect of various maneuvers commonly airport-airplane requirements includes runway/taxiway dimensional encountered in training flights on cockpit noise is evaluated. and trends. taxiway-to-taxiway separation, holding space, noise reduction. factors of aeromedical significance associated with noise in trainer recovery of disabled aircraft, and fire and rescue operations. aircraft are identifted and descrtbed Author (GRA) Emphasis is placed on the necessity of including the airport operations area as part in a public transportation system. G G

N71-22428# Cambridge Univ (England) Dept of Engineering THE UNSTEADY RESPONSE OF AN AXIAL FLOW N71-22390# British Airports Authority. London (England) COMPRESSOR WITH A DISTORTED INLET FLOW ACCOMMODATING PASSENGERS AND CARGO H Mokelke 1970 37 p refs Presented at the Turbomachinery D C Ramage In Natl Council for Civil Aviation Civil Aviation Subcomm of the ARC Meeting. 2 Oct 1970 in the 1970’s 1969 27 p (CUED/A-Turbo/TR-ZO) Avail NTlS Avail NTlS HC$6OO/MF$O95 A 4-staye axial flow compressor with a hub/tip ratio of Airside and landside parts of the overall planning for supporting 0 8 is first investigated with a circumferential 60 deg-square wat’e structures in expanding civil aviation traffic are discussed The inlet flow distortion at a high and a low flow rate By measuring system is evaluated from the point where the payload leaves the the total pressures static pressures and yaw angle behind each I airport and joins the external ground transport system to the stage, the development of the distortion is followed through the

I 38 1 N71-22431

compressor It is found that some of the experimental results N71-22456# National Bureau of Standards Washington. D C differ considerably from analytical results predicted by quasi-steady Photometry Div theories These discrepencies are likely to be due to the unsteady DEVELOPMENT, TESTING, AND EVALUATION OF VISUAL response of the flow around the rotor blades while these are LANDING AIDS Consolidated Progress Report, 1 Jul -30 passing through a distorted region The compressor was tested using Sep. 1970 two asymmetric inlet distortions which were mirror images of each 12Jan 1971 14 p other For the case of a low flow rate great differences in the INBS-10508) Avail NTlS profiles were recorded It is believed that different types of short Evaluations of several types of aircraft approach and landing duration stall a;e responsible for this result In the case of the higher systems are presented Subjects discussed are (11 aviation ground flow tho discrepancies are somewhat less and might conceivably lighting. (2) development, testing. and evaluation of visual landing be explained by unsteady potential flow theories Author aids. (3) operational tests of Dual-Baseline Transmissometer system. 14) photometric measurements of a deck-landing projector sight. and (5) DCA type lamp for Fresnel Optical Landing System Author

N71-22431# Aeronautical Research lnst of Sweden Stockholm STUDY OF INSPECTION INTERVALS FOR FAIL SAFE STRUCTURES N71-22467 Cornel1 Univ lthaca N Y Sigge Eggwertz and Goeran Lindsjoe Jan 1970 59 p refs AERODYNAMIC SOUND PRODUCTION AND THE METHOD (FFA 120) Avail NTlS OF MATCHED ASYMPTOTIC EXPANSIONS Based on a method of evaluating the reliability of failsafe Roy Keith Amiet (Ph C The;,;) 1969 1 13 p structures a theoretical investigation applicable to an aircraft wing Avail Univ Microfilms HC $5 6O/Microfilm $3 00 Order No has been made of the influence of t5e length of inspection intervals 70-5974 which are both constant and varying An optimum study shows The method of matched asymptotic expansions IS first applied that the least number of regular inspections during the service life to problems of sound generation by a body in an infinite fluid The is obtained by making especially the first interval considerably method is then extended to include a free stream flowing over the longer than the following ones This result presupposes that all sound source If the Mach number is less than one but IS not fatigue cracks occurring may be staristically anticipated Unexpected small slender body theory is assumed and the equations are cracks are likely to appear however during an initial debugging linearized The resulting modified wave equation is transformed to period and have to be considered when determining the first the usual wave equation by using a Lorentz and a Galilean inspection intervals Unscheduled inspections randomly distributed transform and the flow in this transformed plane is divided into an in time decrease the risk of total failure but are shown to be much inner incompressible and an outer acoustic region The effect of less effective than regular inspections Author the shed vortices (for airfoil problems) on the order of the error is considered The sound produced by a pulsating airfoil in a stream and the perturbation of a one dimensional sound wave by a movrng elliptical airfoil are calculated as examples In conclusion the N71-22453# National Bureau of Standards. Washington, D c method of matched asymptotic expansions when applicable PHOTOMETRIC CHARACTE RlSTl CS OF SEMI FLUSH provides a simple method of determining acoustic sound fields AIRPORT LIGHTS Dissert Abstr A C Wall [1970] 57 p (NBS-10121) Avail NTlS N71-22469# National Aerospace Lab Tokyo (Japan) The intensity distribution characteristics of semiflush airport AERODYNAMIC NOISE OF A CIRCULAR DOUBLEJET approach and runway lights are presented As installed these lights Nagamasa Kono Sep 1970 18 p refs In JAPANESE ENGLISH prolect one half or one inch above the pavement surface The lights summary may be separated into two generic groups 11) capsule-type lights (NAL-TR-212) Avail NTlS using tubular halogen cycle lamps with lens-type optical systems The noise characteristics of a ]et issuing from a coaxial and (2) prismatic head lights using PAR type sealed reflector lamps double nozzle of diameters of 3 cm and 6 cm respectively are with their beam axes vertical and with prisms to redirect the compared with those of a single let The far field sound pressure beams to near horizontal directions Intensity distribution data of at levels and spectrum at the mesh points 3 m from the nozzle exit least one light of the principal sub types of each generic group are and at 30. 45 60 and 90 degrees from the jet axis respectively included Author were measured under various conditions of by-pass ratio let pressure and Mach number Atsubsonic speeds the maximum noise reduction was 4 db. corresponding to a mass flow ratio of 1 2 at N71-22455# National Bureau of Standards. Washington. D C 75% thrust increase The reduced sound levels are mainly due to OPERATIONAL TESTS OF DUAL BASELINE high frequency compenents while the Strouhal number remains TRANSMISSOMETER SYSTEMS 0 24 At sonic speeds the maximum noise reduction was about 10 J C Wilkerson J W Simeroth. and James E Davis 15 Sep db which is due to delayed shock turbulence interaction At the 1970 14 p same flow conditions mean velocity profiles and velocity fluctuation (NBS-10339) Avail NTlS in the axial direction are investigated to clarify the mutual relation A Skopograph Duplex dual-baseline transmissometer system was between the reduced noise mean shear rate and the turbulence installed and operated for four months to determine operational characteristics The results were that the maximum velocity performance of the system A system of standard transmissometers fluctuation in the double let wab reduced to 1 /3 of the single let with similar baselines was placed beside the test system to provide which causes considerable noise reduction with alleviation of mean data for comparison The output data from both systems were shear Author recorded photographically by a special photo-pack The Skopograph equipment operated through the test period with no failures The N71-22472# National Aeronautical Lab Bangalore (India) mos! irnporlanl maintenance requirement was rhe need for cleaning SOME REMARKS ON MULTHOPP’S SUBSONIC the windows of the field units approximately twice each week LIFTING-SURFACE THEORY Several features Of the performance and records that could P Ramamoorthy Mar 1970 12 p refs require special treatment in processing the data and evaluating the (NAL-TN 24) Avail NTlS performance are discussed Author Multhopp s subsonic lifting surface theory introducing

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interpolation functions to facilitate the integration in the spanwise (ARL/ME-l27) Avail: NTlS direction. is reviewed The interpolation functions were derived, Some Goblin Mk 35 engines in R.A.A.F. service developed using the least square approximation Author unusual noise and vibration in flight at altitudes above about 17,OOO feet. An investigation showed that the noise and vibration were caused by unstable airflow in the engine. which resulted in pressure pulsations in the combustion system. The instability was National Aeronautical Lab, Bangalore (India) N71-22476# found to originate in the compressor vaneless diffuser space under WIND TUNNELPRESSURE REGULATING SYSTEMS conditions of high internal Mach Number which occurs at high S Balakrishna Feb 1970 27 p refs engine speed and low inlet air temperature. While the cause of the (NAL-TN-22) Avail NTlS instability was not determined precisely. evidence indicated that it The design aSpects of the flow control system are discussed with was probably caused by boundary layer flow separation on the rear reference to wind tunnels at the National Aeronautical Laboratory. wall of the vaneless diffuser space. The compressor modification Bangalore A system model is obtained and the effects of various which gave rise to the instability increased the radial depth of the disturbances and their effects on the regulating accuracy are vaneless space. potentially decreasing the stability of the boundary discussed Author layer flow: the actual occurrence of instability depended upon the air flow distribution around the engine. The disturbance was shown to have no effect upon the mean performance. and to present no N71-22485# California Univ La Jolla Dept of the Aerospace hazard to the safe operation of the engine. Some alleviation of the and Mechanical Engineering Sciences condition was shown to be possible by engine nozzle area A KOITER TYPE METHOD FOR FINITE ELEMENT modification to increase the engine airflow, and by 'modifications ANALYSIS OF NONLINEAR STRUCTURAL BEHAVIOR designed to improve the uniformity of airflow distribution around the VOLUME 1 THE MODIFIED STRUCTURE METHOD Final engine. Author Report, 17 Oct 1969 17 Oct 1970 R T Haftka R H Mallett and W Nachbar Wright-Patterson AFB N71-2251q Toronto Unw (Ontaro) lnst for Aerospace Studs Ohio AFFDL Nov 1970 259 p refs INSTITUTE FOR AEROSPACE STUDIES Annual Progress (Contract F33615 69-C 1899) Report, 1970 (AD-717740 AFFDL-TR-70-130 Vol 1) Avail NTlS CSCL20/11 NOV 1970 225 p refs Koiters method for the asymptotic analysis of post-buckling Avail NTlS behavior is reformulted in finite element notation for application tO Research is summarized on the following topics mechanics structures idealized by finite element models Koiters method is Of galdied gases, piasma oynamics. combustion. explosions. herein adapted to a general class of structures exhibiting the common snap-through (limit point) type of buckling This is hypervelocity and two-phase flows MHD power generation and referred to as the Modified Structure method It is accomplished by earth resource satellites aerodynamic noise subsonic aerody- modification of the actual energy functional to create a hypothetical namics space dynamics materials science and structures rocket modified structure having a strictly linear pre-buckling path along research space Simulation and surface interactions high tempera which buckling must be of the bifurcation type The analysis of the ture gas dynamics and gas physics laser excitation diagnostics and environmental sensing flight and air cushion transportatior actual structure is then accomplished by application of Koiters method through consideratton of the actual structure as an tmperfecl atmospheric trace gas studies. sonic boom. and industrial and version of the modified structure The effects of pre-buckling architectural aerodynamics NEN nonlinearity are approximated asymptotically The use of the Modified Structure method in conlunction with direct methods of nonlinear analysis is examined A highly accurate finite element representation N71-22527*# Battelle Memorial Inst., Columbus. Ohio. is employed in presenting a comprehensive numerical evaluation of ANALYSIS OF BRINELLING FAILURE OF BEARINGS FROM VIBRATION TESTED PLV FANS Summary Report the Modified Structure method of analysis on the basis of a W. A. Glaeser. Batra, and H. Prause 8 Jun. 1970 51 p number of planar frame problems Author (GRAI S. K. R. Sponsored by NASA (NASA-CR-117855) Avail: NTlS CSCL 131 N71-22494# Glasgow Untv (ScotlandJ Dept of Aeronautics Brinelling damage was identified in PLV fan bearings as and Fluid Mechanics the cause for noisy running after exposure to a random-vibration environment. Assuming a maximum Hertz stress of 460.000 psi THE ROLE OF HEAT CONDUCTION IN LEADING EDGE HEATING: THEORY AN0 EXPERIMENT to produce brinelling. the niaximum axial load for the fan bearing T Nonweiler H Y Wong. and S R Aggawal Jun 1969 62 p was calculated as 43 pounds. Dynamic analysis of the refs rotor-bearing-spring system revealed that with one preload spring, (Rept-6901) Avail NTlS the maximum predicted axial load would be 297 pounds. It was The effect of heat conduction of material on the temperature determined that reduction in maximum bearing loads under distribution in the vicinity of a wing leading edge in hypersonic vibration conditions could be achieved by reducing the rotor natural flight IS investigated The theory IS based on a conducting plate frequency and by increasing the damping through using a soft spring system When a system of five springs at each end of the rotor subwed to aerodynamic heating It IS found that the role played by the conductivity of the material and the leading edge thickness was considered. the bearing load predicted was 58 pounds Actual in moderating the nose temperature IS very significant Detailed vibration tests using the 5-spring preload configuration resulted in discussions of the numerical solutions for various shapes of leading reduction of bearing damage. A bearing load-capacity computer edge are given An experimental techntque was developed bb program was written so that. given the bearing parameters, inner which a number of models representing a wmg leading edge can race diameter. ball diameter, diametral clearance, total curvature of be tested and the results thus obtained are compared with those the race groove and number of balls, the limiting axial load can be determined using maximum Hertz stress. Author predicted by the theory Author

N71-22503# Aeronautical Research Labs, Melbourne (Australia). N71-22538*# Goodyear Aerospace Corp.. Akron, Ohio. THE GOBLIN Mk35 ENGINE: INVESTIGATION OF NOISE DESIGN, FABRICATION. AND STATIC TESTING OF AND VIBRATION ATTACHED INFLATABLE DECELERATOR (AID) MODELS J. E. Williams and D. H. Edwards Apr. 1970 87 p refs G. L. Faurote 1 Mar. 1971 95 p refs

383 N71-22568

(Contract NASl -9726) N71-22593# Cornel1 Aeronautical Lab lnc Buffalo N Y (NASA CR-111831 GER-149401 Avail NTlS CSCLOlC Aerodynamic Research Dept Three attached inflatable decelerator models were designed RESEARCH ON ADVANCED GASDYNAMIC TEST and fabricated for supersonic wind tunnel evaluation The models FACILITIES PART 2 LASER FLUID INTERACTION incorporate four quick-release aeroshell inlets to accomplish STUDIES Final Technical Report. 1Jul 1966 3OJun 1970 deployment and four canopy inlets to effect final canopy John W Daiber Ronald G Rehm and Herbert M Thompson pressurization It was demonstrated by a rapid inflation test that the Wright Patterson AFB Ohio ARL Oct 1970 41 p refs model's inlet release system and packaqinq and deDlovment svstem lrgntrart AF 33,5151 5389) are workable EMC (AD 717728 CAL AD 2297 A 3 Pt 2 ARL 70 0236) Avail NTlS CSCL 1412 The report describes experimental and theoretical studies conducted on the application of lasers to aerodynamic facilities N71-22568*# National Aeronautics and Space Administration The experimental program IS concerned with the response of a gas Lewis Research Center, Cleveland Ohio to a high intensity ruby laser beam The primary diagnostic COMPUTER PROGRAM DESCRIBING TURBINE tools are high speed streak cameras and x ray emission monitors AERODYNAMIC REQUIREMENTS, APPROXIMATE Experiments were performed in both a spatially uniform gas and in EXTERNAL BLADE GEOMETRIES. AND COOLANT FLOW a free jet expansion In the latter configuration fast moving fronts REQUIREMENTS FOR A TWO STAGE AXIAL FLOW of bright luminosity are propagated back into the high density TURBINE reservoir by the absorption of the ldser energy The theoretical effort Keith A Furgalus David G Evans and Michael R Vanco was concerned with describing the types of fluid responses to laser Washington Apr 1971 59 p refs energy addition through both analytical and numerical analysis (NASA TM-X-2229 E 6014) Avail NTlS CSCL 2.1 E Author (GRA) A computer code is described which generates aerodynamic and thermodynamic designs for a two-stage cooled or uncooled axial-flow turbine A free vortex flow model is used to generate hub N71-22614*# National Aeronautlcs and Space Administration mean and tip velocity diagrams From these diagrams inner-stage Flight Research Center Edwards Calif temperatures and pressures approximate external blade shapes AN INVESTIGATION OF TWO VARIATIONS OF THE GAS external blade surface areas and turbine blade and wall coolant GENERATOR METHOD TO CALCULATE THE THRUST OF airflow requirements are computed Inner-stage temperatures and THE AFTERBURNING TURBOFAN ENGINES INSTALLED turbine annulus areas are adjusted to include the effects of the mass IN AN F-ll1AAIRPLANE flow and energy addition of the blade cooling air Author Frank W Burcham. Jr Washington Apr 1971 30 p refs (NASA-TN-D-6297. H-643) Avail NTlS CSCL21 E Two variations of the gas generator method for calculating N71-22589*# National Aeronautics and Space Administration the net thrust of the afterburning turbofan engines installed in an F-1 11A airplane are investigated An influence coefficient study Langley Research Center, Langley Station Va and two ground thrust tests were performed It was found that the gas ANALOG ANALYSIS OF THE HEAVE RESPONSE AND generator method can be successfully applied to an afterburning CONTROL OF A PLENUM-TYPE AIR CUSHION VEHICLE turbofan engine At static conditions with two engines operating Jack D Leatherwood Washington Apr 1971 31 p refs or percent accuracy can be achieved for most power (NASA-TN-D-6257 L 7227) Avail NTlS CSCLOlC + 2 settings using either the method based primarily on nozzle total An analytical investigation was conducted to determine pressure and area (PTA) or the method based primarily on nozzle the basic heave response characteristics of a plenum type tracked total temperature and weight flow (TTW) For in-flight conditions air-cushion vehicle as a function of vehicle operating parameters In addition to determining basic characteristics the effect of an the influence coefficient results indicated that the accuracy of the active lip control system on the vehicle dynamic response was TTW method was about + or 3 percent whereas the accuracy investigated Nonlinear equations describing the dynamic and of the PTA method was about or 5 percent for a military thermodynamic state of the air-cushion system were derived and power setting With either calculation method additional errors in calculated thrust of or - 2 percent could result from high inlet the response of the system to sinusoidal perturbations of the + flow distortion If accurate thrust values are required both thrust guideway was obtained with the use of an analog computer Results are presented in terms of vehicle to guideway motions and vehicle calculation methods should be used Author accelerations experienced during fundamental and subharmonic oscillations Author N71-22620*# National Aeronautics and Space Administration N71-22590*# National Aeronautics and Space Administration Langley Research Center. Langley Station Va Langley Research Center Langley Station Va SUMMARY OF CENTER-OF-GRAVITY ACCELERATIONS DEVELOPMENT OF A SIMULATOR FOR STUDYING EXPERIENCED BY COMMERCIAL TRANSPORT AIRPLANES SIMPLIFIED LUNAR ESCAPE SYSTEMS IN LANDING IMPACT AND GROUND OPERATIONS George J Hurt Jr David B Middleton and Marion A Wise Paul A Hunter Washington Apr 1971 66 p refs Washington Apr 1971 46 p refs (NASA TN-D-6124. L-7483) Avall NTlS CSCLOl C (NASA TN D 61 11 L 7364) Avail NTlS CSCL 148 Data are presented on incremental normal accelerations A lunar escape system simulator was designed and fabricated due to landing impacts and to ground operations assoclated with to be used as a research tool to study problems related to lunar taxi. takeoff and landing NASA VGH recorders installed in a total escape and simplified manual guidance and control The design of 38 turbine-powered airplanes of both foreign and domestic involved a two man platform with instruments and controllers airlines were used to obtain the data Limited data on longitudinal mounted on a strain gage base Most of the vehicle characteristics deceleration during landing are also presented Author and control logic were contained in the computer program thus a wide range of vehicles (including the lunar flying vehicles) and guidance and control systems could be studied The computer program wascompared withan independent computer program with N71-22622*# National Aeronautics and Space Administration good agreement During checkout operations the subjects were Langley Research Center, Langley Station. Va able to adapt to the equipment with a minimum of training and SUBSONIC AERODYNAMIC CHARACTERISTICS OF A instruction in the operation of the simulator Author HIGHLY SWEPT FIXE0 WING CONFIGURATION WITH

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VARIATION IN WING DIHEDRAL ANGLE p 165-188 refs William P Henderson Washington Apr 1971 45 p refs Copyright Avail Technivtsion. Braywick House Maidenhead Berks (NASA-TM-X-2261 L-7473) Avail NTlS CSCL OlA Engl US Distributor Circa Publications Inc 415 Fifth Ave An investigation to determine the effects of wing-dihedral angle Pelham. New ‘fork 10803 (Ann Mr A L Candido) on the aerodynamic characteristics of a highly swept fixed-wing The recent advances in techniques which have significantly configuration was conducted The tests were conducted at a Mach extended the application of free-flight ranges to the study of high temperature gas-dynamic phenomena are discussed with the number of 0 168. at angles of attack of ~ 5 deg to 22 deg. and at sideslip angles of 0 deg and + or - 5 deg The effects of the improvements in the resolution of information available from addition of vertical tails vertical-tail cant angle, and leading-edge laboratory scale flight investigations Two approaches are followed flap deflection on the aerodynamic characterlstlcs are also included in relating subscale and full scale observations direct scaling and Author evolution of theoretical description In the first approach, classical results of similitude are extended to include modeling of nonequilibrium chemistry The second approach requires a detailed mathematical model that contains the essential physical features N71-22625*# AiResearch Mfg Co , Los Angeles, Calif of interest The model is refined using the expenmental findings AN ANALYTICAL STUDY OF HYDROGEN COOLED PANELS Within the scope of this theoretical system observations of both small FOR APPLICATION TO HYPERSONIC AIRCRAFT and large scale events are predictable Evidently the analytical W G Flieder C E Richard. 0 A Buchmann. and F M Walters approach is the more general of the two Author Washington NASA Apr 1971 201 p refs (Contract NASl-5002.1) (NASA-CR-1650. Rept-68-3667) Avail NTlS CSCL 20M N71-22635 Rolls Royce Ltd Bristol (England) Engine DN Results of an engineering design study of flat. hydrogen-cooled, THE USE OF A GUN TUNNEL FOR HYPERSONIC INTAKE structural panels for heat fluxes up to 500 Btu/sec-sq ft and CALIBRATION pressure loads up to 250 psi are presented Three basic conceptual R Hawkins and E Carlton In AGARD New Exptl Tech in designs. with varying degrees of integration of the thermal protection Propulsion and Energetics Res Oct 1970 p 21 1 240 refs and structural functions of the panel, are evolved, minimum panel weights are obtained. and the ranges of applicability of the various Copyright ..wail Technivision Braywick House Maidenhead, Be&. concepts are established Detailed procedures used to analyze and Engl US Distributor Circa Publications Inc 415 Fifth Ave optimize panel design are included Author Pelham New York 10803 (Attn Mr A L Candid01 The use of a gun tunnel as a low temperature test facility ~71-22626 Advisory Group for Aerospace Research and Devel- for hypersonic intake research was studied with the techniques opment. Paris. France) suitable for calibrating intakes for both supersonic and subsonic NEW EXPERIMENTAL TECHNIQUES IN PROPULSlON AND combustion ramjet engines One of the major advantages of the gun ENERGETICS RESEARCH tunnel is the ability to establish supersonic throat flow within the David Andrews and Jean Surugue. eds Oct 1970 637 P refs intake without recourse to variable geometry This coupled with Conf held at Munich. 1 1 15 Sep 1967 the fact that the flow duration is short (typically 30 to 100 (AGARD-CP-38) Copyright Avait Technfvision. Braywick House. rndfiseconds) has led to great stmptification and economy in intake Maidenhead. Berks Engl US Distributor Circa Publications InC . model construction In the case of an intake for a supersonic 41 5 F,kh Are Peihdnt New Yolk iV863 Attn Mr k L Candioor cornbustion engine where the blockage of multitube rakes would be The experimental techniques developed for diagnosing high unacceptable a high soeed pitot traverse technique was successfully velocity flows include shock tubes, optical methods. enthalpy developed For the more difficult case of the subsonic combustion probes mass spectrometry molecular beams measurements using intake it is necessary to cover a range of back pressures up to ionization. plasma flow measurements and gas chromatography the critical value This has been achieved by fitting a specified volume to the intake in which the rate of pressure rise IS slow enough to permit a transient calibration procedure to be adopted Tests were made in a conventlonal wind tunnel facility to check N71-22630 Sheffield Univ. (England). the validity of the results obtained Author COMBUSTION RESEARCH IN A SHOCK TUNNEL J. Swithenbank and R. J. Parsons In AGARD New Exptl Tech

in Propulsion and Energetics Res. Oct. 1970 p 91 ~ 122 refs N71-22637 Office National d Etudes et de Recherches Sponsored in part by Min. of Technol. Aerospatiales Paris (France) Copyright. Avail: Technivision. Braywick House. Maidenhead. 8erks. VISUALIZATION OF LOW VOLUMETRIC MASS Engl. US Distributor: Circa Publications Inc., 415 Fifth Ave.. [VISUALISATION A FAIBLE MASSE VOLUMIOUE] Pelham. New York 10803 (Attn. Mr. A. L. Candido) Claude Veret In AGARD New Exptl Tech in Propulsion and In addition to conventional pressure and shock speed Energetics RES Oct 1970 p 257 269 refs In FRENCH instrumentation, the feasibility of the measurement of gas velocity ENGLISH summary by electromagnetic induction was studied and found to be a Copyright Avail Technivision Braywick House Maidenhead Berks promising technique at the higher flight speeds Radio frequency Engl US Distributor Circa Publications Inc 415 Fifth Ave probes were used to indicate its magnitude. High speed gas sampling Pelham New York 10803 (Attn Mr A L Candido) valves are used to measure the fuel concentration in the mixing The schlieren and phase contrast methods used for the region, however care must be taken with probe design The proven visualization of supersonic flow are revised Both methods are value of flow visualization techniques are attained by high speed described and their sensitivies are compared Examples af wind tunnel cine photography. Author hypersontc flow visualizatbons are pveii The conditions for the application of these methods to the visualization of flows that are themselves luminous (plasmas and flames) are indicated Author N71-22633 AC Electronics-Defense Research Labs , Santa Barbara. Calif AEROPHYSICS RESEARCH BASED ON FREE FLIGHT N71-22639 Deutsche Versuchsanstalt fur Luft und Ratilrlfallit RANGE MEASUREMENTS Stuttgart (West Germany) A Q Eschenroeder. H H King. and K S Wen In AGARD MEASUREMENTS WITH AERODYNAMIC PROBES IN New Exptl Tech in Propulsion and Energetics Res Oct 1970 PLASMA JETS PRODUCED BY ELECTROTHERMAL AND

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HALL CURRENT ACCELERATORS this method the wing is simulated physically by a system of spars S Krause /n AGARD New Exptl Tech in Propulsion and and ribs that are orthogonal to each other In each case the Energetics Res Oct 1970 p 301 -335 refs natural frequencies and mode shapes of vibration are computed from these influence coefficients by means of a lumped-parameter Copyright Avail Technivision Erawick House Maidenhead Eerks method All of the analytical results obtained in this study correlate Engl US Distributor Circa Publications Inc 415 Fifth Ave very well with experimental works Dissert Abstr Pelham New York 10803 (Attn Mr A L Candido) The measurement of macroscopic aerodynamic quantities in plasma jets which contribute largely in obtaining a better N71-22667 Iowa State Univ of Science and Technology Ames understanding of the phenomena in electric plasma accelerators IS studied A survey is given of early and recent experiments performed APPLICATION OF SELECTED FINITE DIFFERENCE at the lnstitut fur Plasmadynamik D V L Stuttgart with common TECHNIQUES TO THE SOLUTION OF CONICAL FLOW and new types of aerodynamic probes Radial distributions of Pitot PROBLEMS pressure stagnation enthalpy mass and energy fluxes and other Paul Kutler (Ph D Thesis) 1969 213 p quantities in plasma jets emerging from electrothermal and Hall Avail Univ Microfilms HC $9 70/Microfilm $3 00 Order No 70-7713 current accelerators are presented A graphical iteration method IS described for the determination of any thermodynamic values and The inviscid flow fields about a pointed circular cone and the plasma velocity from the measured quamitie5 An interesting ex a flat top or conical wing body configuration both at angle of ample shows the calculation of an unknown quantity by simultane attack are determined by applying first and second order differencing schemes to the gas dynamic equations conservation law form) ous of ae od,,iarnic and nonacrod,ramic experimental ies,l:s (in the axial velocity in a Hall current accelerator is derived from and by utilizing the self similar or conical nature of the flow field aerodynamic yaw probe determination of the swirl angle and A survey and analysis which includes an experimental and spectroscopic Doppler effect measurement of the azimuthal velocity theoretical stability study of these finite difference schemes IS performed The purpose of the cone study is to develop a numerical Author method which will predict the flow field when the angle of attack is increased far enough such that embedded shock waves are N71-22640 Centre National de la Recherche Scientifique formed on the lee side of the cone as a result of the large Meudon (France) Lab d Aerothermique cross flow velocities Dissert Abstr EXPERIMENTAL STUDY OF THE LAMINAR BOUNDARY LAYER WITH CATALYTIC REACTION OF THE WALL [ETUDE EXPERIMENTALE D’UNE COUCHE LlMlTE N71-22672*# Northrop Corp Hawthorne Calif Aircraft Div LAMINAIRE FIGEE AVEC REACTION CATALYTIQUE A LA FLOW FIELDS OVER SHARP EDGED DELTA WINGS WITH PAROI~ ATTACHED SHOCKS G Lassau and E A Erun /n AGARD New Exptl Tech in S A Powers and E R Eeeman Jr Washington NASA Apr Propulsion and Energetics Res Oct 1970 p 337 355 refs 1971 67 p refs In FRENCH ENGLISH summary (Contract NASl-7850) Copyright Avail Technivision Eraywick House Maidenhead Eerks Engl US Distributor Circa Publications Inc 415 Fifth Ave (NASA-CR-1738) Avail NTlS CSCL20D The problem of supersonic and hypersonic flow of an inviscid Pelham New York 10803 (Attn Mr A L Candido) ideal gas over conical wings with sharp leading edges and attached The transformation of air components due to the marked shock waves has been treated using the three-dimensional method of increase in temperature during reentry is studied in the shock characteristics Solutions for both the expansion and compression wave It is assumed that there is an equilibrium flow in the shock side have been developed and provided as highly automated layer but the temperature in the vicinity of the wall is lower computer programs These programs provide for wing cross sections chemical equilibrium no longer exists as the reaction time is too of flat plate modified wedge or general conic shapes Since the long in comparison with the residence time in the boundary layer flow fields on upper and lower surfaces are independent the total and the gas along the wall is in a metastable state Experimental wing shape can be a combination of any two of these three evidence of the catalytic effect of the flat wall parallel to the flow shapes These solutions require from one to three minutes on a CDC on the concentration in the boundary layer is given The theory 6600 computer and provide an accurate description of the flow shows that from the concentration profiles in the layer the wall field between the body and the external boundary (the shock wave concentrationcan be obtained Concentration curves are obtained by on the compression side and the free stream on the expansion three different methods (1) By means of an enthalpy probe giving side) Results from these programs are compared with experimental the activated nitrogen concentration in the boundary layer (2) Ey and theoretical data Author iniecting a carbide in the activated nitrogen and studying the luminosity and 13) By mass spectrometry of cyanhydric acid The three methods give similar results Author N71-22674 New York Unlv NY School of Engineering and Science NUMERICAL SOLUTION OF SEVERAL STEADY WAKE N71-22666 Iowa State Univ of Science and Technology. Ames FLOWS OF THE MIXED SUPERSONIC/SUBSONIC TYPE BY NATURAL FREQUENCIES OF VIBRATION OF A A TIME-DEPENDENT METHOD TRIANGULAR INFLATABLE WING MODEL John lstvan Erdos IPh D Thesis) 1969 79 p Lo Ching Hua (Ph D Thesis) 1969 136 p Avail Univ Microfilms HC $4 20/Microfilm $3 00 Order No Avail Univ Microfilms HC $6 6O/Microfilm $3 00 Order No 70-9772 70 7705 The analysis of steady. mixed supersonic/subsonic flow The influence coefficients natural frequencies and mode fields involved difficulties associated with the elliptic character of shape5 of vibration of a triangular inflatable wing are computed the differential equations governing the subsonic regime and the The influence coefficierits of the wing are computed by two resulting interactions between the subsonic and supersonic regions different methods The first is an iterative method based on the The complexities of a mixed elliptic hyperbolic problem can be linear theory of inflatable plates and engineering beam theory The effectively circumvented by transforming it into a purely hyperbolic wing is treated conceptually as a composite structure made from problem through introduction of an additional. albeit artificial. time an edyeles5 inflatati? plate and two semi circular stiff edges The variable The present investigation considers the near wake of a second approdch is by means of the stiffness matrix method In flat-based slender body at supersonic speeds in the context of this

386 N71-23030 type problem Inviscid solutions are obtained by a finite-difference An analytical investigation of the effect of coupling method known as the two-step Lax-Wendroff technique This study characteristics on the response of axially coupled sets of turborotors demonstrates that an inviscid model of the closed near wake is presented A digital computer program based on transfer matrix exhibits remarkable agreement with the available experimental data techniques and utilizing a coupling fixity matrix was developed at even moderately low Reynolds numbers Dissert Abstr Gyroscopic effects and both shaft as well as coupling orthotropy were included in the program Linear bearings were assumed and the motion was restricted to synchronous precession An illustrative example, utilizing two axially coupled modified Prohl rotors N71-22680*# National Aeronautics and Space Administration demonstrates that the nature of the coupling has a significant effect Lewis Research Center Cleveland Ohio on the response characteristics of the rotor set The coupling must COOLING AIRFLOW THROUGH A STATIONARY TURBINE be considered when writing balancing specifications and during DISK AND BLADE actual balancing of the rotor set It is shown that the axial coupling Frederick C Yeh David J Poferl. Reeves P Cochran. and Hadley of turborotors can result in the unloading of particular beerngs T Richards Washington Apr 1971 44 p refs which may initiate journal instabilities that are known to be (NASA-TM-X-2171 E 6006) Avail NTlS CSCLZOD associated with light loading conditions Dissert Abstr The cooling-air pressure changes through a stationary turbine disk and blade assembly and the airflow distribution within a blade were determined experimentally Tests were conducted with room-temperature air over a range of inlet pressures from 28 to N71-22891 Purdue Univ Lafayette Ind THEORETICALSTUDY OF LANDING MAT BEHAVIOR 100 psia and flow rates from 0 12 to 0 45 Ib/sec Based on John Christopher Rosner (Ph D Thesis) 1969 198 p demonstrated agreement between measured and calculated rotor Avail Univ Microfilms HC $9 OO/Microfilm $3 00 Order No disk and blade pressures an analytical procedure is proposed for 70-8962 predicting the cooling-air pressure changes through the rotor disk Mechanistic models are developed to help predict the behavior and blade during engine operation Author of landing mat systems The first model which is based upon elastic theory is capable of duplicating the action of such systems under static loads The associated assumptions are (1) that an N71-22699*# National Aeronautics and Space Administration infinite beam is the structural equivalent of the mat (2) that the Lewis Research Center, Cleveland. Ohio. subgrade is homogeneous (3) that horizontal displacements within HIGH TEMPERATURE TURBINES the subgrade are negligible and (4) that the mat always remains 10 Jack 8. Esgar and R. A Reynolds (Dept. of Ind.. Trade. and Corn. contact with the subgrade The model parameters are established Ottawa1 Paris AGARD Feh 1971 7 p refs Presented a! from simulations of full scale experimental tests These parameters the 36th Meeting of the Propulsion and Energetics Panel. Florence. are also correlated with prototype test variables Results from 21 -25 Sep. 1970 prototype tests indicate that the model parameter k the subgrade (NASA-TM-X-67123: AGARD-AR-29-71) Avail: NTlS CSCL 21 E modulus decreases as trafficking of the section progresses Contrary State of the art review of high temperature turbine technology to common belief the model behavior is found to be extremely was provided at this conference. The following topics were covered sensitive to the magnitude of the subgrade modulus by papers presented: problems involved in cooling small turbines. Dissert Abstr application of turbine blade cooling to engines. selection of high temperature and cooled turbine materiats. heat transfer measurement techniques. and an evaluation of the technioues of N71-23007' National Aeronautics and Space Administration. film. convection, and transpiration cooling EMC Marshall Space Flight Center. Huntsville. Ala METEOROLOGICAL BALLOON Patent N71-22702 South Carolina Univ Columbia James R. Scoggins. inventor (to NASA) Issued 12 Sep 1967 COMBINED FREE AND FORCED LAMINAR (Filed 7 Jan. 1965) 7 p CI 73-189 NON-NEWTONIAN CONVECTION IN A VERTICALTUBE (NASA-Case-XMF-04163: US-Patent-3,340.732; Wilbur Joseph Marner (Ph D Thesis) 1969 116 p US-Patent-Appl-SN-424156) Avail: US Patent Office CSCL 01C Avail Univ Microfilms HC $5 80/Microfilm $3 00 Order NO A meteorological balloon is described having high aerodynamic 70-9306 stability. The balloon contains uniform conical surface protuberances Heat transfer to a power law fluid flowing in a constant to provide roughness and stable boundary layer separation. E.C. wall temperature vertical tube was studied Except for a linear variation of density with temperature, all properties were assumed to be constants An initially fully developed velocity profile was assumed for the analysis Nondimensionalization of the governing N71-23030* Jet Propulsion Lab., Calif. lnst. of Tech., Pasadena. equations showed the parameters controlling the problem to be MODEL LAUNCHER FOR WIND TUNNELS Patent flow behavior index n. Prandtl number Pr, and the Grashof over Harold P. Holway, inventor (to NASA) Issued 19 Sep. 1967 (Filed Reynolds number ratio Gr/Re The dimensionless groups are defined 2 Apr. 19651 5 p CI. 73-1-7 Sponsored by NASA in the generalized sense for power law fluids The governing (NASA-Case-XNP-03578: US-Patent-3,342,066: equations were solved numerically for a range of the parameters US-Patent-Appl-SN-445292) Avail: US Patent Office CSCL 148 Mean Nusselt numbers dimensionless pressure drop, and typical This invention is employed for studying the performance developing dimensionless velocity and temperature profiles are of a body in a high speed wind tunnel. A model launcher is presented Results show that distortion of the velocity profile due positioned within the wind tunnel adjacent a viewing window. The to free convection effects can increase the heat transfer and model launcher includes a chamber and a piston movable within pressure drop significantly Dissert Abstr said chamber The piston ends in a rod having an end whereupon the body or model can be supported for a launching. The piston is held from moving while gas under pressure is introduced into N71-22712 Pennsylvania Univ Philadelphia the chamber. When the piston is released, the gas moves the THE DYNAMIC RESPONSE OF AXIALLY COUPLED piston and the rod until the piston is snubbed. whereupon the model TURBOROTORS can continue its movement into the wind in the chamber, and its Donald George Lemke (Ph D Thesis) 1969 124 p operation in flight is studied through the window. Avail Univ Microfilms HC $6 OO/Microfilm $3 00 Order No Official Gazette of the U S.Patent Office 70-7821

387 N71-23085

N71-23085* National Aeronautics and Space Administration Aug 197 1 sponsored by SAE Flight Research Center Edwards Cal,f (NASA TM X 67809) Avail NTlS CSCL 106 HEAT FLUX MEASURING SYSTEM Patent Windage tests were conducted on two concentric rotor stator Richard D Baxter inventor (to NASA) Issued 6 Feb 1968 (Filed configurations in ambient air producing Reynolds numbers as high 2Jun 1965) 4 p CI 73-190 as 100 000 A cylindrical 12 in diameter iotor ailC an 8 in (NASA Case XFR 03802 US Patent 3 367 182 diameter Lundell type rotor were operated at speeds up to 36 000 US Patent Appl SN 460877) Avail US Patent Office CSCL 20M rpm Gap to radius ratios of 0 01 to 0 04 were incorporated Tests A heat flux sensor is described which is adaoated for mounting were also conducted with axial slots machinvd on the stator on research aircraft for determining the aerodynamic heat flux surface of the Lundell configuration to simulate electrical winding inflow to the skin of an aircraft or space vehicle The thermally slots The stators were mounted on a reaction torque device SO symmetrical rod shaped sensor IS mounted flush with the that viscous drag from the surface of the rotor would be measured aerodynamic surface and is well insulated from the surrounding Tests were also conducted to determine the pumping characteristics environment The sensor includes a heating circuit that detects of the conical sections of the Lundell rotor The results are thermal differentials between the skin and exposed end of the sensor presented and discussed Author and raises the exposed end temperature to the skin temperature a heating circuit that detects temperature differentials between the insulated and exposed ends of the sensor and a heater power N71-23122*# Massachusetts lnst of Tech Cambridge input monitoring device JM Aerophysics Lab DATA REDUCTION TECHNIQUES FOR USE WITH A N71-23091*# National Aeronautics and Space Administration WIND TUNNEL MAGNETIC SUSPENSION AND BALANCE Langley Research Center Langley Station Va SYSTEM Interim Technical Report, Nov 1968 Jun 1970 FLUTTER SUPPRESSION USING ACTIVE CONTROLS George D Gilliam Jun 1970 70 p refs BASED ON THE CONCEPT OF AERODYNAMIC ENERGY (Contract NASl-8658) E Nissim Washington Mar 1971 115 p refs (NASA CR 11 1844 TR-167) Avail NTlS CSCL 148 (NASA TN D-6199 L-7525) Avail NTlS CSCLOlA The equations relating the forces and moments exerted The problem of flutter suppression is treated from an on a body by the magnetic fields produced by the MIT NASA energy point of view whereby the energy dissipated per cycle of prototype magnetic balance are presented A computer program oscillations is reduced to a quadratic form involving a diagonal which will derive the aerodynamic coefficients for a body using matrix of energy eigenvalues which are of aerodynamic origin these relations is listed along with a sample output A preliminary only A simplified binary bending torsion flutter of a wing strip is procedure for aligning the axis of the magnetic suspension system investigated by several systems leading edge control surface trailing with a reference axis is detailed A procedure for determining edge control surface and combined leading edge trailing edge dynamic-stability derivatives is outlined Author control surfaces In each case the control surfaces are allowed to be driven by a linear sensor a rotational sensor and a combined linear rotational sensor system The results show that the flutter N71-23124*# National Aeronautics and Space Administration of the wing strip can be suppressed a single control law being Langley Research Center. Langley Station Va used over a wide range of reduced frequencies irrespective of the EFFECT OF ENGINE POSITION AND HIGH-LIFT DEVICES mass of the system its stiffness center of gravity location elastic ON AERODYNAMIC CHARACTERISTICS OF AN axis the mode of vibration and the Mach number (in the subsonic EXTERNAL-FLOWJET-FLAP STOL MODEL range) Parameters affecting the implementation of the control law Charles C Smith, Jr Washington Mar 1971 141 p refs such as power requirements phase lags and amplitude gains are (NASA-TN-D-6222 L-7581) Avail NTlS CSCLOl C investigated The extension of the results to three dimensional flow An investigation was conducted to provide some basic cases is discussed and the use of the fluttei suppressor as a gust information on the aerodynamic design parameters of an external alleviator is also considered Author flow let flap configuration Static force tests were included to determine the effects of engine vertical and longitudinal position let eXhdUSt deflectors, flap size and type leading edge slat chord and N71-23115*# National Aeronautics and Space Administration Langley Research Center. Langley Station Va deflection, and gap and overlap of the slats and flaps The force DYNAMIC AND STATIC WIND TUNNEL TESTS OF A tests were made in full-scale tunnel with a model having an FLOW DIRECTION VANE unswept untapered wing and powered by four simulated Norman R Rictardson Washington Apr 1971 22 p refs high-bypass-ratio turbofan engines Author (NASA TN-D-6193 L-7431) Avail NTlS CSCL 148 Dynamic and static wind tunnel tests of a low inertia flow-direction vane are described The vane was designed to provide N71-23125*# National Aeronautics and Space Administration good dynamic response characteristics and was used for the in flight Langley Research Center Langley Station Va measurement of gust velocities Both subsonic and supersonic tests WI ND-TUN NEL I NVESTl GAT1 ON OF SONIC-BOOM were conducted The data indicated that the natural frequency of CHPRACTERISTICS OF TWO SIMPLE WING MODELS AT the vane is about one half times the square root of the dynamic MACH NUMBERS FROM 2 3 TO 4 63 pressure (measured in N/sq m) or about three times the square David S Miller Odell A Morris and Harry W Carlson Washington root of the dynamic pressure (measured in psf) The data alsc Apr 1971 31 p refs indicated that the damping ratio is between 0 80 and 0 65 critical (NASA TN D 6201 L 7178) Avail NTlS CSCLOlA at sea level and varies approximately as the square root of the air A wind tunnel investigation was undertaken to provide density Author experimental data for use in studying lift-induced sonic boom characteristics at high supersonic Mach numbers Pressure signatures below two simple wing models were measured at two separation N71-23116 // National Aeronautics and Space Adrninistratiorl distances for a range of lift Coefficients at Mach numbers of 2 3 Lewis Resedrch Center Cleveland Ohio 2 96 3 83 and 4 63 Comparisons of theoretical and experimental EXPERIMENTAL WINDAGE STUDIES FOR HIGH SPEED pressure signatures showed that the good agreement obtained for ALTERNATORS the lowest Mach number of this investigation does not persist into S H Gorland and E E Kempke (19711 12 p refs Proposed the higher Mach number range particularly for high lift coefficients for Presentation at 1971 lntersoc Energy Eng Conf Boston 3 6 In all instances the overall signature correlation became worse

388 N7 1-23157

with increasing Mach number and with increasing lift coefficient ABOUT CERTAIN CLASSES OF AIRFOILS AND SLENDER Impulse comparisons indicated that even at extremety large distances BODIES experimental and theoretical overpressures could differ by as much J R Spreiter and S S Stahara Washington NASA Apr 1971 as 20 percent Author 144 p refs (Contract NAS2-5410) (NASA-CR-1722) Avail NTlS CSCLOlA N71-23126*# National Aeronautics and Space Administration Procedures based on the method of local linearization and Lewis Research Center Cleveland Ohio transonic equivalence rule were developed for predicting properties FORTRAN PROGRAM FOR QUASI-THREE-DIMENSIONAL of transonic flows about thin airfoils and slender bodies The CALCULATION OF SURFACE VELOCITIES AND CHOKING procedures are applicable to transonic flows with free stream Mach FLOW FOR TURBOMACHINE BLADE ROWS numbers near one, below the lower critical, and above the upper Theodore Katsanis Washington Apr 1971 37 p refs critical Canpansons with experimental surface pressure distributons (NASA-TN D-6177 E-5869) Avail NTlS CSCL 20D exhibit good agreement for all shapes considered. although A quasi three dimensional compressible flow analysis for discrepancies appear near the aft region particularly for the slender axial flow turbines was generalized to allow for mixed or radial bodies Analysis of the discrepancies suggests substantial wind flow and for nonuniform inlet conditions The velocity gradient tunnel wall interference effects are present in the experimental method is used with one velocity gradient equation used for radial results for the three dimensional shapes Effects 0' shock wave equilibrium and another velocity gradient equation fbr blade-to-blade boundan/ layer interaction and vortex induced separation are not variation Author included in the theory Author

N71-23134*# National Aeronautics and Space Administration N71-23127*# National Aeronautics and Space Administration Langley Research Center Langley Station. Va Lewis Research Center. Cleveland Ohio INVESTIGATION OF THE AERODYNAMIC CHARACTER- LOW-SPEED JET NOISE FROM A 1.83 METER (6FT) FAN ISTICS OF A HYPERSONIC TRANSPORT MODEL AT MACH FOR TURBOFAN ENGINES NUMBERSTO 6 Gene L Minner and Charles E Feller Washington Apr 1971 p refs James C Ellison Washington Apr 1971 80 p refs $6 (NASA-TN-D-6191 L-7478) Avail NTlS CSCLOl C (NASA-TN-D-6314 E-6124) Avail NTlS CSCL 20D The jet noise from a large fan model was determined for A wind tunnel investigation was conducted at subsonic. two simulated nacelle configurations These u'pie B hzrd ;*;all riiwrsn"lF, and hyperscnic speeds to de;eimine ihe aaiudyriamic nacelle and one having acoustic liners on the walls and on Inlet characteristics of a blended wing-body configuration Data were splitter rings The let veloctty range of the data was from 137 to obtained for the configuration with a single vertical tail. a 223 meters per second (450 to 730 ftfsec) The data show that flow-through inlet. and elevons deflected from 5 deg to ~ 20 deg internally generated low frequency noise IS effectively removed by At a Mach number of 6 and a Reynolds number of 21 6 x 1 the acoustic liners Data from the lined configurations show the million. the configuration had a maximum lift-drag ratio of 5 0 with classical eighth power dependence on let velocity Data from the no trim penalty Based on the selected center of gravity position hard wall configurations were higher in (NASA-TM-X-67809)and of 56 4 percent of the model length. the configuration was stable had a weaker velocity dependence due to the noise from In all directions over the Mach number range Results of analytical internal sources Several comparisons of the data were -r)+ W+ methods agreed with the data a: zero e'evo- def!e:?.cn !a: :he correlations of let noise data from the literature Author range of angle of attack from 0 deg to 6 deg at all Mach numbers Author N71-23135*# National Aeronautics and Space Administration N71-23131i National Aerospace Lab Amsterdam (Netherlands) Langley Research Center Langley Station Va APPLICATION OF A METHOD FOR ESTIMATING LOW-SUBSONl C LONGI TUDI N A L AE R 0 DYNAMIC PRESSURE DISTRIBUTIONSTO AN OSCILLATING T-TAIL CHARACTERISTICS OF A TWIN-BODY SPACE-SHUTTLE R J Zwaan 1 May 1968 55 p refs BOOSTER CONFIG U RAT1ON (NLR-TR 68048 L) Avail NTlS Bernard Spencer Jr and George M Ware Washington Apr A method proposed to estimate pressure distributions from 1971 60 p theory and from measured distributions for one vibration mode (NASA TM-X 2162 L 7417) Avail NTlS CSCLOlA was applied to a T tail configuration at low speeds The results An investigation was conducted in the low turbulence pressure indicate that the method may be used successfullv Author tunnel with a model representative of a first stage booster space shuttle concept proposed by industn/ The configuration consisted N71-23132*# General Motors Corp , Indianapolis. Ind of twin body elements connected by fore and aft wings with each DESIGN AND EXPERIMENTAL RESULTS OF A HIGHLY body having an outboard horizontal and a vertical stabilizer The LOADED, LOW SDUMNTANDEM ROTOR tests were made at angles of attack from about 4 deg to 20 James L Bettner Washington NASA Apr 1971 68 p refs deg at 0 deg sideslip Tests were made over a range of Reynolds (Contract NAS3-111641 numbers (based on body length) from 4 34 million to 26 million at (NASA-CR-1803 EDR-6627) Avail NTlS CSCL 01A Mach numbers below 0 35 Author The overall performance of a single stage turbine with a low solidity tandem rotor blade assembly was tested over a range ~71-23157t National Aerospace Lab Amsterdam (Netherlands' of equivalent and expansion ratios The rotor blades were speeds DESCRIPTION OF THE EQUIPMENT FOR THE FATIGUE designed with negative hub reaction and a mean line axial chord TEST ON THE WING OF THE FOKKER F28 FELLOWSHlP solidity of 1092 The results of this investigation are compared R Noback Nov 1969 75 P refs with the performance of a modified tandem rotor blade which was (NLR-TR-70008-L) Avail NTlS designed to similar velocity diagrams but with a mean section axial chord soldity of 1852 Both rotors were tested with the same The wing of the Fokker F 28 Fellowship was fatigue tested stator Author Before the actual testing started the equipment was tested on a dummy test rig Different types of networks for stabilizing the N71-23133*# Nielsen Engineering and Research Inc Mountain systems were evaluated Considerations which led to the choice of View. Calif the loading systems are given together with a full description of CALCULATIVE TECHNIQUES FOR TRANSONIC FLOWS the test equipment including the protective system The accuracy

389 N71-23186 of the wing test is discussed An analysis is given of two loading N71-23211# Aeronautical Research Associates of Princeton Inc systems especidlly of the influence of the coupling between these NJ svst em s Author THE ART OF DETERMINING GUST FREQUENCY RESPONSE FU NCTl ON John C Houbolt In AGARD Freq Response Functions and Human N71-23186*/ Massachusetts lnst of Tech Cambridge Pilot Modelling Mar 1971 p 1 20 refs Measurement Systems Lab AN AIRSPACE UTILIZATION MODEL FOR V/STOL Avail NTlS TERMINAL OPERATIONS The art of determining the frequency response function for Dor sn Albert De Maio(M S Thesis) Jan 1971 95 p refs gust response and of deriving the associated structural response (Contract NASl2 2081 Grant NGR-22-009-010 Contract parameters A and N sub o is discussed Measured and computed DOT TSC 5) values are compared to show the degree of success obtained It (NASA CR 117887 TE-45) Avail NTlS CSCLOlE IS brought out that frequency response determination IS a The computer processes inputs describing the terminal area computationally large task and that simplified procedures are needed and accompanying constraints and displays on a cathode ray tube the Emphasis is also given to the fact that there is not a frequency airspare utilization model a three dimensional image representation response function for the airplane but that there are many of the constraints at a given altitude Extensive machine/operator depending on flight conditions A procedure is suggested for helping interaction is provided to select various constraint criteria to plan to establish the appropriate frequency response functions and the approaches and departures and to check the results through A and N sub o values for use in design. Author vieviing ana teletype output The program is general and ma) be aprlied to a number of terminal areas The programs applicability an ' usefulness is demonstrated in the analyses of several proposed N71-23212# Boeing Co Wichita Kans V' SL port sites in the Northeast Corridor Approach and departure THE EFFECT OF ACTIVE CONTROLS ON STRUCTURAL iidths are developed for each site and observations are made RESPONSES r?gcirdingflight path characteristics The computer display leads to Clifford F Newberry. James I Arnold and Gerald J Kass In drastic reductions in time and effort over a comparable manual AGARD Freq Response Functions and Human Pilot Modelling task in terminal area studies Authoi Mar 1971 p 21 44 refs Avail NTiS The use of an active control system on large flexible aircraft to improve flying qualities ride qualities and to alleviate loads N71-231936 Lockheed Missiles and Space Co Palo Alto Calif require a good mathematical model The number of modes to be ASYMPTOTIC SOLUTION OF THE PROBLEM OF included is treated from a standpoint of stabllity and for structural OSCILLATIONS OF A SOLID PROFILE IN TRANSONIC loads evaluation The verification of the model during flight testing GAS FLOW ts discussed Frequency response transient response and random G F Sigalov 1971 5 p refs Trans1 into ENGLISH from response techniques are presented Presented are two examples DopovidiAkad NaukUkr RSR (Kiev) no 1 1971 p 80 84 one dealing with a lower structural mode frequency that affects Avail NTlS National Translations Center John Crerar Library the handling qualities and ride qualities of the aircraft and the other Chciaqo 111 60616 deals with a higher frequency mode that IS a stability problem An asymptotic method of investigating nonlinear problems Consideration for artificial damping of the flutter mode IS also 15 developed on whose basis the problem of the oscillation of a presented Author solid profile in a transonic shockless adiabatic inviscid gas flow is investiqated a1 Mach numbers somewhat less than the critical Complete approximation is based on reflection of the physical space N71-23213# Office National d Etudes et de Recherches into a new auxiliary space the space of the approximations and Aerospatiales Paris (France) is realized by means of a special deformation of the coordinates TRANSFER FUNCTIONS OF FLEXIBLE AIRCRAFT TO which converts the nonlinear differential equation in the physical ATMOSPHERIC TURUBLENCE IFONCTIONS DE space into a linear equation in the space of the approximations TRANSFERT DWN AVION SOUPLE A LA TURBULENCE^ The boundary value problem for a nonlinear differential eqUatiOn G Coupry In AGARD Freq Response Functions and Human Pilot which described the low frequency oscillations of a solid profile in Modelling Mar 1971 p 45 48 refs In FRENCH a transonic gas flow is given Author Avail NTlS computation and measurement of the transfer function of an aircraft flexible to atmospheric turbulence are reported After a N71-23210# Advisory Group for Aerospace Research and survey of the usable turbulence models. the computation ot the Development Paris (France) transfer function for isotropic turbulence is discussed. it is shown FREQUENCY RESPONSE FUNCTIONS AND HUMAN PILOT that it is hardly more complicated than in the case of uniform MODELLING turbulence Finally. the methods for measuring the transfer function Mar 1971 65 p refs Mostly in ENGLISH, partly in FRENCH are described Author (AGARD R-580 71) Avail NTlS

CONTENTS N71-23228# National Research Council of Canada Ottawa 1 THE ART OF DETERMINING GUST FREQUENCY (Ontario) RESPONSE FUNCTIONS J C Houbolt (Aeron Res Associates of INITIAL STUDIES OF LOW TEMPERATURE ABLATION IN Princeton Inc 1 p 1 20 refs A HELIUM HYPERSONIC WIND TUNNEL 2 THE EFFECT OF ACTIVE CONTROLS ON STRUCTURAL L Elias. K Orlik-Ruckemann. and D L Kohlman Albuquerque RESPONSES C F Newberry J I Arnold and G J Kass (Boeing N Mex Sandia Corp Jan 1971 61 p refs Prepared for Sandia Co Wichita Kans) p 21 44 refs Corp 3 TRANSFER FUNCTION OF FLEXIBLE AIRCRAFT TO (SC-CR-69-3215) Avail NTlS AMOSPHERIC TURBULENCE G Coupry (ONERA Paris France) Exploratory experiments were carried out at Mach 164 p 45 58 ref5 and at 600 psi stagnation pressure using (a) metal models at room 4 HUMAN PILOT MODELLING H F Huddleston (RAE temperature, (b) models with copper inserts. cooled to 140 C Farnborough Engl p 59 65 ref5 and IC) models with carbon dioxide inserts Surface temperature

390 N71-23278

surface recession rates and pitot pressure profiles were determined N71-23245# Massachusetts Inst. of Tech., Cambridge Acoustics Suitable model fabrication and experimental techniques were and Vibration Lab. developed A simple theoretical method of predicting recession rates AN INVESTIGATION OF THE NEAR WAKE PROPERTIES and surface temperatures was proposed It was demonstrated that ASSOCIATED WITH PERIODIC VORTEX SHEDDING FROM the ablation of carbon dioxide into an unheated Mach 16 4 helium AIRFOILS flow at 600 psi stagnation pressure is significant enough to result Carl E. Hanson Sep. 1970 82 p refs in measurable flat plate recession rates and measurable changes (Contract Nonr-3963(26)) in pitot pressure profiles In addition it was shown that it is (AD-7 18893; A/V-76234-5) Avail: NTlS CSCL 201 1 possible to distinguish between the effects on pitot pressure of An investigation of the near wake of airfoils with various trailing reduction in surface temperature and of mass addition through edge configurations including splitter plates reveals properties sublimation of carbon dioxide It was also found that the first order which are conducive to wake periodicity. The frequency of the theoretical analysis predicts proper trends and correct approximate shedding process is found to scale with the near wake momentum magnitude of sublimation rates Author thickness and a wake velocity simply related to the base pressure coefficient. Computer results suggest that the frequency and bandwidth of the vortex shedding process can be predicted by a N71-23232# Boeing Co Renton. Wash solution of the complete Orr-Sommerfeld equation. Author (GRA) FLAMMABILITY AND DESIGN CONSIDERATIONS FOR COMMERCIAL AIRPLANE INTERIOR MATERIALS N71-23250*# Honeywell Inc Minneapolis. Minn Systems and W S Perkowski and R G Cheatham [1971] 16 p refs Research Div Avail NTlS HIGH TOTAL TEMPERATURE SENSING PROBE FOR THE Plastic materials and textiles used for the interiors of X-15 HYPERSONIC AIRCRAFT commercial aircraft are discussed from the standpoint of flammability Ronald G Bailey Sep 1968 85 p refs cost, and weight Design considerations which are used in the (Contract NAS4-1211) choice of materials are (1) the materials must meet the FAA certification requirements, (2) the materials must provide a maximum (NASA-CR 116712 Rept-12080 FRI) Avail NTlS CSCLOlD The results are presented of research aimed at applying of weight for functional use (3) the materials must provide the the fluid oscillator concept to the development of a probe for lowest and most realistic cod and (4) the materials must provide measuring free stream total temperatures on hypersonic aircraft of a pleasing and acceptable decor Author the X-15 class The probe generates an oscillating pressure signal in the form of a sonic pressure wave which IS propagated and reflected within the device to cause an oscillation oftht= inrorning flud N71-23233# Department of Transportation. Washington. 0 C The sensor oscillation frequency is dependent on the acoustical Air Traffic Service velocity of the wave within the fluid. and thus a function of the INDEX OF STANDARD INSTRUMENT APPROACH fluid temperature in the probe cavity. The probe utilizes a cooled PROCEDURES sensor concept in which the probe body temperature is maintained 4Feb 1971 151 p below the material melting point with nitrogen gas coolant The Avail NTlS free stream total temperature is arrived at through measurements An index of standard instrument approach procedures IS of the oscillation frequency body temperature and local pitot presented The procedures are current up to and including 4 pressure The frequency is measured wrth two conventional pressure February. 1971 Information is presented for airports in the transducers arranged to operate in push pull with either transducer Continental United States, Alaska and the Caribbean area Author capable of independent operation should the other fail The time response of the instrument is dependent upon the purging time of the fluid within the sensor cavities which is about 10 milliseconds Author

N71-23234# Air Line Pilots Association International N71-23268* National Aeronautics and Space Administration Washington D C Langley Research Center Langley Station Va FACT SHEET ON THE AIR LINE PILOTS ASSOCIATION COMBINED OPTICAL ATTITUDE AND ALTITUDE ANNUAL AIR SAFETY FORUM INDICATING INSTRUMENT Patent 21 Jul 1970 49 p refs Presented at 17th ALPA Air Safety Arthur W Vogeley and Alfred J Meintel Jr inventors (to NASA) Forum San Francisco 20 22 Jul 1970 Issued31 Dec 1968(Filed2Jan 1964) 7 p CI 356 72 Avail NTlS (NASA-Case-XLA-01907 US-Patent-3.41 9 329 The Air Line Pilots Association Air Safety Forum is a meeting US Patent-AppCSN-335441) Avail US Patent Office CSCL 148 of all segments of the aviation community It is devoted solely to air Optical instrumentation to facilitate take off and landing safety and has been sponsored by the Air Line Pilots Association of aircraft or space vehicles on planetary surfaces IS described The in the public interest in every year since 1953 The reasons for system serves as a primary or backup onboard instrumentation the Forum are threefold (1) to stimulate an interest in air safety system to present vehicle altitude and attitude information on a (2) to promote an exchange of safety information between pilots screen located on the vehicle instrument panel and viewable by the and representatives of the aviation industry and government. and pilot or other occupants of the vehicle (3) to develop recommendations to improve the safety of air travel Official Gazette of the U S Patent Office Participants in the ALPA Forums are pilot and flight attendant safety experts from all air lines plus safety representatives from the air line companies aircraft manufacturers government agencies concerned with aviation airport operators the military services and many other segments of the national and international aviation N71-23278*# Scientific Translation Service. Santa Barbara. Calif community Subjects covered are those timely ones concerned with ACCELERATED SUPERSONIC MOTION OF A PLANE AT increasing the efficiency and safety of air line flying They vary from A FINITE ANGLE OF ATTACK [USKORENNOYE SVERKHZVUKOVYE DVlZHENlYE PLASTINY PRI year to year but the stress IS upon those associated with air safety problems considered to be currently the most critical They are KONECHNOM UGLE ATAKl] I covered by various means including panel presentation. technical 0 G Goman Washington NASA Apr 1971 12 p refs Trans1 into ENGLISH from Izv Akad Nauk SSSR. Mekh Zhidk Gaza ~ papers open discussion guest speakers and field trips Author (Moscow). no 4. Jul Aug 1970 p 70 75

39 1 i N71-23283

(Contract NASw 2035) Report. 13 Nov. 1969 9 Nov. 1970 (NASA TT-F 13525) Avail NTlS CSCLOlA David M Jaksa and Jeffrey S Yalowitr Nov 1970 259 p Supersonic noiisteady motion of a plane in an ideal gas refs is considered The plane with the attached shock wave moves at (Contract N62269-70-C-0016) a finite (not infinitel\ small) angle of attack The laws governing (AD-718167 Rept-523-0763421-001 11M) Avail NTlS CSCL the change of velocity and the angle of inclination of the plane 915 are assumed to be arbitraw and the Struhal numbers are small With The objective of the integrated high-frequency antenna system the latter assumption and with Mach numbers in the perturbed (IHFAS) program IS to provide a simultaneous operation (SIMOP) area not too close to unity the motion can be characterized capability for the P 3 hf communication system This capability will sufficiently well by instantaneous values of the nonsteady parameters be provided for the P-3C which will incorporate the higher hf and their derivatives This fact provides the possibility of simplifying transmitter powers and Link 11 data capability of A-NEW A considerably the system of equations describing the perturbed technique was developed to optimize transmit filters This technique nonsteady movement and to obtain its analytical solution Author enables analysis of system parameters to determine detailed requirements for an optimum high level transmit filter A series of tests were performed on the AN/ARC 132(V) hf transceiver to aid N71-23283# ITT Research lnst Chicago 111 in evaluating it as a SIMOP radio General performance tests were PRELIMINARY STUDY OF AN AUGMENTED RAM-WING conducted in accordance with applicable portions of MIL-STD 449C VEHICLE CONCEPT Final Report. 1 Aug 1967 18 May 1968 In addition external intermodulation spurious voltage and spurious lmants Reba Jan 1971 126 P refs impedance measurements were made Author (GRA) (Contract DOT 7 33512) (pe 189425 !!TR~16128 FR) Avail NTlS CSCL 13F N71-23314# Georgia lnst of Tech Atlanta School of Aerospace A wind tunnel study of a ram-wing type vehicle with various Engineering blowing arrangements IS reported Two models were studied One AN EXPERIMENTAL INVESTIGATION OF A TURBULENT model represented a thick vehicle configuration with a blunted rear JET IN A CROSS FLOW end The second had a streamlined chord section Blowing David K Mosher (Ph D Thesis) Dec 1970 182 p refs arrangementsconsisted of two two dimensional Coanda nozzles one placed near the leading edge and one near the midchord Upward (Contract DAHC04 68-C-004 Pro] Themis) (AD-718798 GIT-AER-70 7 15) Avail NTlS CSCL 2014 downward and mixed blowing arrangements were investigated The interference phenomenon occurring when a subsonic The results indicate that the downward blowing near the leading turbulent jet exhausts normally from a large flat plate into a low edge and upward blowing at midspan constitute the most promising speed crossflow was experimentally investigated in the Georgia of those arrangements investigated Author (GRA) Tech nine foot wind tunnel Static pressures were measured on the surface around the jet In the region off the surface including the N71-23296*# National Aeronautics and Space Administration jet plume wake and surrounding areas the average total and static Ames Research Center Moffett Field Calif pressures and the average velocity magnitudes and directions were AN INVESTIGATION OF SONIC BOOM FOR STRAIGHT- determined Three let exit configurations were studied one circular AND DELTA-WING SPACE SHUTTLE ORBITERS and two slot shaped with width to length ratios of 0 3 and 3 4 Raymorid M Hicks Joel P Mendoza and Lionel L Levy Jr Apr All have the same exit area The effective let to cross flow velocity 1971 26 p refs ratio was varied for each of the exit configurations. over the range (NASA TM X 620301 Avail NTlS CSCL 20A 4 0 to 12 0 Analysis of the data indicates that the pressure Wind tunnel tests were conducted to determine the sonic distributions induced on the surface are a combined result of the lets boom characteristics of straight wing and delta wing space shuttle blocking and entraining effects on the cross flow with entrainment orbiters during reentry into the earths atmosphere Two different becoming the more dominant of the two as the effective velocity ratio trajectories were analyzed for the delta wing orbiter while one is increased This relative dominance brings about an attenuation trajectov was considered for the straight wing orbiter 80th tralectov of total interference lift loss (when computed as a fraction of gross and angle of attack were found to have strong effects on the level thrust) primarily by causing a rise in the low pressures in the wake of sonic boom overpressure under the flight path of the vehicle region as the effective velocity ratio increases When the effective Author velocity ratio is held fixed the total interference lift loss increases with increasing width to length ratio of the jet exit N71-23297# Air Force Systems Command Wright Patterson Author (GRA) AF8 Ohio Foreign Technology Div CENTRIFUGAL COMPRESSOR MACHINES N71-23333# Catholic Univ of America Washington. D C F M Chistyakov et at Dec 1970 443 p refs Trans1 into A POSITION PAPER ON VEHICLE SAFETY ENGLISH of the Book Tsentrobezhn Kompressornye Machtny Nicholas Perrone Sep 1970 53 p refs Moscow Izd vo Mashinostr 1969 p 1 327 (AD-718397) Avail NTlS CSCL 13/12 (AD 717878 FTD MT 24 183-70) Avail NTlS HC $6OO/MF The problem of the air bag and its development standards $0 95 CSCL 1317 and their significance is addressed The auto safety standards are The book discusses fundamentals of theory calculation and critica!ly reviewed in detail especially those portions concerned design of centrifugal compressor machines There are examined with crashworthiness Suggestions for specific new additions as well processes of flow and losses in elements of the stage and the effect as modifications of existing standards are made Special attention of separate structural factors of the flow area on efficiency There is focused on the instrument panel area hard internal spots such IS substantiated the rational selection of elements of the flow area as door posts windshield headers and main frame structural rotor wheel diffuser return stator and volute There are provided elements and the front seat (which should be appreciably calculations of compressor machines with cooling calculations of strengthened) The worthfrom a cost/benefitviewpoint of increasing disks for strength and of shaft for critical number of revolutions vehicle safety is examined in some detail The problem of general There are examined systems of automatic control of compressor aviation crashworthiness is also examined in the same context and it machines and also questions of their testing Author (GRA) is suggested there that immediate retrofitting of existing airplanes should take place in a manner comparable to automobiles (in other terms, similar standards should be invoked) The general question of resource allocation is also examined and it is suggested that N71-23306# Collins Radio Co. Cedar Rapids Iowa INTEGRATED HIGH FREQUENCY ANTENNA SYSTEM greater and organized national attention be devoted to this critical Final problem Author (GRA)

392 N71-23414

N71-23356# Royal Aircraft Establishment. Farnborough (England) In order that advances in aviation safety may continue RADIO ENVIRONMENT MONITORING FOR THE to be made without unnecessarily adding to cost, it IS essential CATEGORY 3 INSTRUMENT LANDING SYSTEM to be able to study the effectiveness of current regulations to T R G Lampard May 1970 74 p refs determine whether or not they are acting in the manner expected (RAE-TR-70076) Copyright Avail NTlS Methods which have been developed to abstract and examine data The need for integrity monitoring of the category 3 instrument of safety interest are outlined The fields of operations and landing system when used for automatic landing IS discussed A airworthiness are both considered and the relative places of statistical radio environment monitoring system is proposed. based on early data on the one hand and the more detailed study of isolated experimental work carried out at Farnborough and London Airport events are discussed Examples are given of some of the results The practical results obtained support the theoretical work in such which have been obtained The importance of the close links which a way as to indicate that the method of monitoring is a viable have been developed with the operator IS emphasized Author proposition Author (ESRO)

N71-23412# National Aerospace Lab Amsterdam (Netherlands) N71-23361# Royal Aircraft Establishment. Farnborough (England) OPERATIONAL FLIGHT RECORDING AND ITS IMPACT DETERMINATION OF CPlLS LOCALISER BEAM NOISE ON FLIGHT SAFETY AND AIRCRAFT DESIGN J Benjamin Jul 1970 41 p refs T Van Oosterom In AGARD Lessons with Emphasis on Flight (RAE-TR-70141) Copyright Avail NTlS Mech from Qperating Experience. Incidents and Accidents Mar A method of estimating the magnitude of residual beam 1971 19 p refs noise resulting from reflected interference is given for the CPlLS Avail NTlS HC$6 OO/MF$O 95 localizer configuration Author (ESRO) Flight operational experience and results from incident and accident analyses are important sources of basic information for improving flight safety and aircraft design These sources can be N71-23387# Naval Ordnance Lab White Oak Md effectively explored by in-flight recording of data which define the A NEW APPROACH TO THE DETERMINATION OF THE flight condition the navigational environment and the technical STEADY STATE INFLATED SHAPE AND INCLUDED functioning of the aircraft Present aircraft integrated data systems VOLUME OF SEVERAL PARACHUTE TYPES IN 24 GORE (AIDS) provide an extensive data acquisition capability and allow AND 30 GORE CONFIGURATIONS for automatic data processing The main technical features of thesr William P Ludtke 3 Oct 1970 56 p refs systems and the relevant data processing equipment are reviewed (AD 7 18808 NOLTR-70-178) Avail NTlS CSCL 1/3 from a users point of view A survey is given of present and N73--27898 doLumenied a fiwv me:h=d s! deterr?:nrng puaaibia iuiure dppiiwiiuiir uf AiDS witit arripiiaris uii fiiytri safaiy the steady-state inflated shape and included volume of several and aircraft design data recording Some specific examples are types of parachutes in 12-gore and 16-gore configurations This discussed which illustrate the usefulness of flight recording report uses the methods and technique of N70-27898 to extend Author the data to 24-gore and 30-gore configurations of the flat circular. 10 percent extended skirt 16 percent porous ring slot and 24 percent porous ribbon parachutes The inflated elliptical shapes Of N71-23413# General Dynamics/Fort Worth. Tex the various canopies were obtained from photographic records of PROVING THE OPERATIONAL CAPABILITY OF A HIGH the wind tunnel tests at various velocities from 17 mph to 200 mph PERFORMANCE FLIGHTCONTRDL SYSTEM Ussag pa;ach,?e ;r.x!e!s of ;pp:o~-a?el:r AQ inch 98: diameter The E C Cwqgston Jr In AGARD Lessons with Emohasis on Flight steady state canopy volume includes the volume of the billowed Mech from Operating Experience. Incidents and Accidents Mar gore panel and an air volume ahead of the canopy skirt hem The 1971 12 p resulta of this investigation are particularly applicable to studies of Avail NTlS HC$6 00/MF$095 canopy stress analysis and determination of the volume of air Two generalized approaches to the development and proof which must be collected during canopy inflation process for use in of a high performance flight control system are examined The first the calculation of opening-shock force Author (GRA) approach is conventional in that no more than minimal sirnulation is utilized to confirm the system analysis and design In the second approach extensive use is made of complete closed-loop Advisory Group for Aerospace Research and N71-23410# simulation. including an accurate dynamic model of the airframe. to Development. Paris (France) confirm analysis and design Examples encountered in the utiluation LESSONS WITH EMPHASIS ON FLIGHT MECHANICS of these two approaches are provided in order to illustrate the FROM OPERATING EXPERIENCE, INCIDENTS AND benefits of one approach over the other Experience gained from the ACCIDENTS utilization of both of these approaches has shown the latter to be Mar 1971 301 p refs Presented at the 37th Meeting of the the best The extensive use of flight simulators and an airframe Flight Mech Panel of AGARD. Baden-Baden, 20 -23 Oct 1970 test stand assures that the system will meet requirements after (AGARD-CP-76-71) Avail NTlS HC $6 OO/MF $0 95 nlinimal retrofit and flight test Author Detailed accident and incident investigations. flight control systems developments and operational performance recordings are used to optimize aircraft flight mechanical parameters Considerable Smiths Industries. Ltd , London (England) emphasis is placed on human factors engineering for aircraft N71-234148 safety requirements THE OPERATIONAL PROVING OF AUTOMATIC FLIGHT CONTROL SYSTEMS IN THE APPROACH AND LANDING PHASE R H Ashforth ln AGARD Lessons with Emphasis on Flight Mech from Operating Experience. Incident and Accidents Mar 197 1 N71-23411# Air Registration Board. London (England) 10 P A BRIEF REVIEW OF SOME SAFETY STUDIES BASED ON Avail NTlS HC$6 OO/MF $0 95 OPE RAT1ONA L FLIGHT RE CORD ING The Hawker Siddeley Trident aircraft equipped with a flight J C Chaplin In AGARD Lessons with Emphasis on Flight Mech control system that covers both automatic approaches and from Operating Experience. Incidents and Accidents Mar 1971 automatic landings is studied The flight control system comprises 26 p refs the SEP 5 autopilot which is triplex in the pitch and roll axis and Avail NTlS HC$600/MF$095 duplex in yaw The lessons learnt during the flight trails and also

393 N71-23415 as a result. of the service experience are discussed Changes made N71-23418*# ldational Aeronautics and Space Administration to the original design as a result of this experience applicable to Washington D C the approach and landing phase are described in relation to the AVOIDANCE OF AIRCRAFTTRAILING VORTEX HAZARDS different levels of clearance The second part of the paper covers William A McGowan In AGARD Lessons with Emphasis on the in-service recording and statistical proving of the automatic Flight Mech from Operating Experience Incidents and Accidents landing system Author Mar 1971 23 p refs (NASA TM X 67125) Avail NTlS CSCLOlC Trailinq vortices have been the cause of aircraft accidents N71-23415# Messerschmitt-Boelkow-Blohm G m b H , Munich Results of accident investigations theoretical exercises wind tunnel (West Germany) experiments and flight tests are used to describe the formation OPERATIONAL PROVING OF AUTOMATIC FLIGHT and severity of trailing vortices and the spatial extent of their CONTROL SYSTEMS FOR V/STOL FIGHTER AIRCRAFT influence including factors governing persistence This information G Kissel and H Schmidtlein (Vereinigte Flugtech Werke G m b HI is then used to outline procedures for ready application by pilots Bremen West Germany) In AGARD Lessons with Emphasis on tower operators and those concerned with the flow of traffic Flight Mech from Operating Experience Incidents and Accidents during tactical operations The procedures provide the necessary Mar 1971 26 p refs appreciation of the physical attributes of trailing vortices the potential Avail NTlS HC$600/MF$095 hazards involved when encountering them and how best to avoid the Four different types of automatic flight control systems dangerous portions of the wake during flight operations Schemes for V/STOL fighter aircraft were flight tested within the past years under investigation to monitor remotely both the trailing Vortex The VJ 101 C aircraft makes use of pure jet-thrust modulation location and intensity in the airport area and to prohlbit formation control in the thrust sustained flight regime for rolling and pitching of high intensity vortices through aircraft design are discussed and thrust vector control for yawing The VAK 191 flying bedstead Author uses puff-pipe (bleed air) control with additional thrust augmentation for pitching The main characteristics of the systems are (1) stability augmentation system with high authority superimposed on N71-23419# Mississippi Srare univ State College Dept Of the mechanical flight control system versus fly by wire system. (2) Aerophysics and Aerospace Engineering integrating control system versus proportional system 13) pure THE HANDLING QUALITIES REQUIRED FOR SAFE VTOL versus V/STOL capability (4) pure thrust modulation control OPERATION OF SINGLE ENGINE BOUNDARY LAYER versus puff-pipe control and (5)puff pipe control by means of fly CONTROLLED AIRCRAFTIN THE STOLMODE by wire with mechanical back up With all four systems acceptable S C Roberts In AGAAD Lessons with Emphasis on Flight Mech from Operating Experience Incidents and Accidents Mar handling qualities could be reached but it IS shown that especially 1971 in case of thrust modulation where the aircraft has nonlinear 16 p refs characteristics for large control inputs a nonlinear control system Avail NTlS HC$6 OO/MF$O95 gives higher stability Author Operations of single engine. boundary layer control. STOL aircrafts since 1958 are reported The vehicles have been the high lift super cub L-2 1, the modified Cessna L-19 the XAZ- 1. and the XV 11A with wing loadings ranging from 13 Ib/sq h to 28 Ib/sq N71-23416# Deputy Chef of Naval uperations (Development) ft All of these aircraft had a distributed suction boundary laybr Washington D C control system for lift augmentation and XAZ-1 and the XV-11A DESIGN LESSONS LEARNED FROM THE OV-1OA BRONCO also had shrouded propellers for static thrust augmentation The Hugo G Sheridan Ir AGARD Lessons with Emphasis on Flight performance stability and control and handling qualities of these Mech from Operating Experience Incidents and Accidents Mar aircraft have been evaluated and considerable experience gained in 1971 13 p the operational aspects of such STOL aircraft with regard fo the Avail NTlS HC$6 OO/MF $0 95 handling qualities required for safe operation in the STOL mode The OV 10A Bronco 15 one of the aircraft desiqned spectftcally Author for low level counterinsurgency warfare The original design requirements for the aircraft as well as the engineering changes found necessary during the flight test stage are reviewed Use of N71-23420# Breguet-Aviation Veliry (France) the Bronco in combat operations in Southeast Asia IS summarized ESTABLISHING SAFETY MARGINS FOR THE TAKE OFF including loss and damage rate As a result of these combat AND APPROACH OF THE BREGUET 941 operations conclusions are drawn as to the validity of the original [ESTABLISSEMENT DES MARGES DE SECURITE AU requirements for the OV-lOA Design requirements desirable for the DECOLLAGE ET A L‘ATTERRISSAGE POUR LE BREGUET next counterinsurgency aircraft iri light of the experience in South- 9411 J Bastidon In AGARD Lessons with Emphasis on Flight Mech east Asia are recommended Author from Operating Experience Incidents and Accidents Mar 197 1 9P N71 2341 I# Hawker Stddeley Aviation Ltd Woodford (England) Avail NTlS HC$6 OO/MF$O 95 LESSONS FROM OPERATION AND TRIALS OF TWIN The safety margins to be considered are of the two following TURBO PROP AIRCRAFT ON ROUGH AIRFIELDS types (1) speed margins (takeoff and approach speed). and (2) M J Tdylor lri AGARD Lessons with Emphasis on Flight Mech field length margins These two margins are examined and discussed from Operating Experience Incidents and Accidents Mar 197 1 considering the BR 941 Determination of these margins is based 13 p refs on theoretical considerations flight measurements and opetational Avail NTISHC$600/MF$095 test results Allowance is also made for discussions determinlng Trtdls and opeidlions of a civil twin turboprop airliner and special conditions for civil airworthiness of this airplane Author of it\ milltdry counterpart have taken place over a period of nearly ten vedrs During tht5 time both measured data and operating exprripilce have been accumulated from movements on unprepared N71-23421# Naval Air Systems Command, Washington. D C airfield,, 111 parltcular the investigation into two landing accidents LOW ALTITUDE HIGH SPEED FLIGHT EXPERIENCE irivolvitiy the ~iviltype has led to performance measurements on Ralph C A’Harrah In AGARD Lessons with Emphasis on Flight qras5 aiid hard surfaces Information is given on the following (1) Mech from Operating Experience. Incidents and Accidents Mar uridctc drrtaqf’ load measurements (2) airframe Contamination and 1971 13 p refs wpcrfIcidl danldqe and (3)aeroplane performance Author Avail NTlS HC$6 OO/MF$O 95

394 N7 1-23428

An extensive flight test evaluation of the operational capabilities D R Clifford lo AGARD Lesson+ with Emphasis and Flight Mech of contemporary military aircraft in performing low altitude missions from Operating Experience Incidents and Accidents Mar 1971 is reported The particular test phase being reviewed. namely the 22 p refs visual target acquisition test. involved 8 wcraft and 200 pilots Avail NTlS HC$6OO/MF$O95 making more than 400 low altitude sorties Assisned penetration Final approach control for transport aircraft consists primarily speeds ranged from 175 to 550 Knots Two altitude corridors were in aerodynamic performance during cruise The specific objectives assigned minimum safe altitude to 400 feet and 500 to 900 feet defined for the Boeing 727 and 737 in this respect and the above the terrain Author boundary layer control research with the 707 prototype are outlined. together with results achieved Steep angle decelerating and curving approaches have been considered singly and in combination A simple speed control for decelerating approach on the normal N71-23422# Ecole Nationale Superieure de I’Aeronautique, glidepath angle is under development for the 747 and research Toulouse (France) activities include extending the capability of high quality area INFLUENCE OF SIMPLE AERODYNAMIC MODIFICATIONS navigation equipment to control of flightpath, speed and configuration ON THE PERFORMANCE OF AN AIRCRAFT [INFLUENCE on final approach so as to minimize noise Oescribed are the DE MODIFICATIONS AERODYNAMIQUES SIMPLES SUR operational characteristics of the airborne system for terminal LE COMPORTEMENT D’UN AVlON] path guidance on reduced noise trajectories. including the system J E Forestier In AGARD Lessons with Emphasis on Flight Mech configuration. functlons of key elements redundancy requirements from Operating Experience Incidents and Accidents Mar 1971 control law aspects and cockpit displays Author 12 P Avail NTlS HC$6 OO/MF$O 95 Described are modifications made on prototype Vautour aircrafts N71-23426# National Aeronautics and Space Council during their development phase Principle difficulties encountered Washington D C were lateral control and beyond Mach 093 longitudinal control A REVIEW OF V/STOL AIRCRAFT ACCIDENTS IN THE US characteristics Adjustmentsofthe turbulence generator positions on John H Enders and William E Thurman In AGARD Lessons with the outer airfoils just before the wing tip. and modifications in the Emphasis on Flight Mech from Operating Experience Incidents and chamber of the wing leading edge provided the desired performance Accidents Mar 1971 14 p refs improvements Trans1 by G G Avail NTlS HC$6 OO/MF$O95 V/STOL research and development aircraft accidents have occurred for the same major reasons and over the same operation4 N71-234238 National Aero- and Astronautical Research Inst phasc spcctGZ a; ha-c acc:dcnts tc cc”Ynt:cna! a:rc:5ft Exc!:dmg Amsterdam (Netherlands) hover and transition phases from the operational phases, a pattern MAN/MACHINE COMBINATION IN THE LIGHT OF SAFETY of accident distribution of V/STOL aircraft is similar to that for REQUIREMENTS conventional aircraft - about 55-60% during landing. about 20% F W L Herckenrath. J J P Moelker. and C M Ramsey In in cruise. and about 20% during takeoff The pattern of accidents AGARD Lessons with Emphasis on Flight Mech from Operating suggests no clearly dominant remedial action to reduce these Experience Incidents and Accidents Mar 1971 10 p refs accidents across-the-board but increased attention in each of the cause factor areas will effect an improvement Nearly every accident Avail NTIS HC$600/MFS095 investigation prompted changes in either design methods of A description IS given of a few limiting factors in man ~z~ra:t~nmanagc-evt rtri2lrtiire ?nlqr triipivg mpthodq or and tneir bearing upon aircraft design Examples are given of maintenance procedures Author limitations in attention perception learning memory and intelligence and decision making Present design deficiencies are considered in tbe light of crew training and procedures It is stressed that from N71-23427# Ministry of Defence London (England) the earliest conception of a design close cooperation between V/STOL IN THE ROYAL AIR FORCE SOME LESSONS designers safety organisations and prospective operators is of vital FROM THE FIRST 18 MONTHS importance to assure safety in aerospace operations Author R G Lofting In AGARD Lessons with Emphasis on Flight Mech from Operating Experience Incidents. and Accidents Mar 197 1 4P N71-23424# National Aeronautical Establishment. Ottawa Avail NTlS HC$600/MF$095 (Ontario) Some 18 months of V/STOL operations with the Harrier REVIEW OF SEVERAL FACTORS RELEVANT TO JET ground attack and reconnaissance aircraft have been completed UPSETS and the aircraft s flight safety record during this period IS discussed 8 Caiger In AGARD Lessons with Emphasis on Flight Mech The record has been encouragingly good. taking into consideratisn from Operating Experience Incidents and Accidents Mar 1971 the novel problems of V/STOL operation. and field covered by tile 11 p refs complete Harrier flight safety record is not a large one Selected Avail NTlS HC$600/MF$095 are the following four topics from the Harrier flight safety record Various contributory factors to jet upsets are reviewed covering which lie reasonable close to flight mechanics (1) stability and instrument or control system failures and severe turbulence control (2) exhaust gas reingestion (3) ejection facilities and (4) encounters Related problems of pilot disorientation are discussed control system Author The need for detailed analyses of upsets IS emphasized It is concluded that well designed autopilot systems may provide more N71-23428# Messerschrnitt-Boelkow G m b H Munich (West effective control in severe turbulence encounters than the human Germany) pilot but that suppression of primary structural modes and the use V/STOLACClDENTS OR INCIDENTS of head up displays are still desirable to alleviate the pilot‘ s 0 Richarz In AGARD Lessons with Emphasis on Flight Mech difficulties Author from Operating Experience, Incidents and Accidents Mar 1971 10 P N71-23425# Boeing Co , Seattle. Wash Commercial Airplane Avail NTlS HC$600/MF$095 Group Performance tests on two models of the VJ lOlC VTOL APPROACH PATH CONTROL FOR REDUCED NOISE AND high performance aircraft are reported and observed accidents IMPROVED TRAFFIC CAPACITY connected with flight mechanical aspects are analyzed Four out of

395 N71-23429 the five accidents reported had somethinq to do with hot DETECTOR Summary Report gases and recirculation A great deal of the recirculation problems Charles R Martel Nov. 1970 74 p refs experienced were directly connected to the triangular arrangement (AD-718418: AFAPL-TR-70-63) Avail. NTlS CSCL 14/2 of the aircraft s 6 engines GG The Aqua-Glo Series II free water detector. for use in measuring the quantity of free (undissolved) water in hydrocarbon fuels, was evaluated Two dynamic test loops and a batch-blending N71-23429# Sud-Aviation Toulouse (France) calibration apparatus were used to check the accuracy and ALL WEATHER SUD/LEAR LANDING SYSTEM INSTALLED repeatability of the Aqua-Glo Series II The Aqua-Glos response to OM THE CARAVEL~E iSYSTEfviE D’AEEFiFiiSSireE iree water in iuei was iuuiici iu be aiiecied by the presence of f~e! TEMPS SUD/LEAR INSTALLE SUR CARAVELLE] additives in the fuel and by the degree to which the water was G Payeur In AGARD Lessons with Emphasis on Flight Mech dispersed in the fuel. Corrosion inhibitors such as Santolene C. from Operating Experience Incidents and Accidents Mar 197 1 AFA-1. and Lubrizol 541 were found to decrease the Aqua-Glos 10 P response to free water while the fuel system icing inhibitor was Avail NTlS HC$600/MF$095 found to increase the Aqua-Glos response to free water. A poor Experience with the all weather SUD/LEAR landing system dispersion of the free water in fuel. Le.. one that has a few large confirms its reliability in phase 3a automatic approach and landing drops versus a good dispersion. where there are many small requirements The system encorporates a flash warning signal on drops, resulted in decreased repeatability and a lowered Aqua-Glo the panel in front of the flight captain that combines all essential response In general. the Aqua-Glo Series II free water detector was warnings relating to aircraft flight control and integrates in particular found to be suitable for field use in its present configuration Over the following warnings (1) HZ-4 and MR-4 indicator flags (2) the range of 2 to 40 milligrams per liter of water in the fuel. beam error detector warnings, (3) autopilot warnings and (4) Author (GRA) altitude error warnings transmitted by the radio altimeter AF-and servo-mechanism unit The fact that the warnings are combined in a single flash enables the flight captain to continue outside the N71-23475# Lockheed Georgia Co Marietta aircraft and yet perceive within his immediate field of vision a A THEORETICAL INVESTIGATION OF A CIRCULAR possible malfunction flash signal he can make a decision (down to LIFTING JET IN A CROSS FLOWING MAINSTREAM Final 50 ft) to continue the approach or to initiate go-around Report,Jul 1909 Dec 1970 Trans1 by G G James E Hackett and H Ronald Miller Wright Patterson AFB Ohio AFFDL Jan 1971 59 p refs (Contract F33615 69 C 1753) N71-23430# Army Aviation Systems Command, St Louis Mo (AD 718121 LGR ER 10940 AFFDLTR 70 170) Avail NTlS PROBLEMS ENCOUNTERED IN NAP OF THE EARTH CSCL 1/1 FLYING AND THEIR EFFECT ON AIRCRAFT DESIGN Finite element potential flow modeling theoretical techniques MISSION PERFORMANCE are described which predict from first principles both the rolled up Lawrence R Dewey Jr In AGARD Lessons with Emphasis on geometry and the path of a round lifting let convergent into a Flight Mech trom Operating Experience Incidents and Accidents Mar 1971 5 11 refs cross flowing mainstream as on VTOL or direct lift assisted STOL Avail NTlS HL$6 00/MF$095 aircraft Starting with a straight cylinder geometry point vortex Reviewed are some of the design problems that are elements are perturbed using a pre dictor corrector stepping method accentuated by tactical helicopter maneuvering close to ground to give a first estimate of the bent back shape using assumed Considered are aerodynamic coupling effects that cause the aircraft circulation values A collocation scheme is next used to revise the to roll during climb with sudden forward pitching for a gun run circulation values and after three or four iterations a final exit plane on target and dynamic structural aircraft vibrations durmg low level pressure distribution rnay be calculated The fan induced total high speed terrain avoidance maneuvers Proposed safety measures pressure rise is simulated by injecting vortex rings at a chosen include an automatic information and warning system for the pilot position in th duct which feeds the let Since the scope of the and safety margins that realistically encompass fatigue dynamics method is entirely non viscous separations toward the rear of real inherent iri close to ground operations GG jets and the associated pressure changes are not simulated and base pressure type of pressures cannot be expected Nevertheless for forward speed ratios of 0 1 0 2 0 3 and 0 4 the low pressure N71-23431# Ministry of Technology. London (England) contours at each side of the jet do show an increasing rearward WEATHER AS A FACTOR IN FATAL ACCIDENTS shift just as is found experimentally Somewhat surprisingly the INVOLVING CIVIL TRANSPORT AIRCRAFT simulated plumes were more stable dt higher velocity ratios At J Burnham /n AGARD Lessons with Emphasis on Flight Mech lower forward speeds there was a tendency to flap rather like a from Operating Experience Incidents and Accidents Mar 1971 hose end when freed It is anticipated that if viscous effects were 21 p refs simulated these motions mi-ht damp out Author (GRA) Avail NTlS HC$6 OO/MF$O 95 An analysis is given of the importance of weather in fatal accidents involving civil transport category aircraft during the N71;23480# Ballistic Research Labs Aberdeen Proving Ground period 1946 69 Out of a total of 1 433 accidents involving 25.801 Md fatalities. weather is known to have been a factor in 318 accidents WIND TUNNEL SUPPLY HEADERS involving 6 778 fatalities. and rnay have been involved in others Anders S Platou Dec 1970 45 p refs The average of 13 accidents per year in which weather was (AD-718227. ERL-MR-2085) Avail NTlS CSCL 14/2 low turbulence flow involved comprise about 10 per year in poor visibility. 2 per year It has been found that good quality due to gusts and 1 per year due to icing and other weather in a wind tunnel test section IS dependent on the flow and hazaids The only type of weather accident which has increased in turbulence conditions in the supply header This report indicates how frequency in recent years is that of approach and landing in poor good quality low turbulence flow can be obtained in a supply visibility Author header and presents flow surveys taken in a supply header before and after modification Author (GRA)

396 N71-23591

M L Juncosa Dec 1970 33 p refs N71-23499* Jet Propulsion Lab Calif Inst of Tech Pasadena (Contract F44620-67-C-0045) DECONTAMINATION OF PETROLEUM PRODUCTS Patent (AD-718405 R-515-PR) Avail NTlS CSCL 112 James R Mosier inventor (to NASA) Issued 16 Jul 1968 (Filed A simple analysis of the problem of achieving a soft landing 18 May 1965) 2 p CI 44-77 Sponsored by NASA for airdrop by fitting the payload with retrorockets. and a direct (NASA Case XNP-03835 US Patent 3 393 059 iterative numerical procedure for determining the switch-on point US Patent-Appl-SN 4568741 Avail US Patent Office CSCLO7C ’ for minimal fuel consumption in terms of either time or altitude A description IS given of a means and method of effectively Through appropriate reversals of sign the formulas may also be controlling bacteria growth in petroleum products as well as used for ascent tra:ectories of full-thrust. vertically boosted rockets trapping other impurities such as water and solid panicles which where the assumption of a constant gravity field is acceptable normally settle to the bottom of stored petroleum products by the Since the unretrothrusted portion of the descent is identical with use of a small effective amonJnt of honey free fall. the dynamical equations are integrable in closed forms For Official Gazette of the U S Patent Office a constant atmosphere. closed form analytic solution IS also obtained for the retrothrusted descent For an exponentially varying atmosphere. however, one cannot escape a numerical integration of N71-23528# School of Aerospace Medicine. Brooks AFB. Tex. the dynamical equations Author (GRA) SIX INDICES FOR PREDICTING SPEECH INTERFERENCE WITHIN AIRCRAFT Final Technical Report, 1 Oct. 1968-6 Jul. 1970 N71-23488# Naval Air Engineering Center, Philadelphia. Pa Donald C. Gasaway Dec. 1970 35 p refs Engineering Dept (AD-718098: SAM-TR-70-72) Avail: NTlS CSCL 1712 SHIPBOARD TEST PROCEDURE FRESNEL LENS OPTICAL Acoustic noise within aircraft during flight often causes LANDING SYSTEM MK 6 MOD 2 some degree of interference with aural communication. Several Wesley F Davis 19 Jan 1971 88 p methods have been used over the years to identify and predict (AD-718335. NAEC-ENG-7656) Avail NTlS CSCL 115 degrees of speech interference. Six of these methods are discussed: This procedure is a guide to be used by the Test Engineer. four involve octave-band averaging: two use frequency weighting. Field Service Representative or Test Officer for Shipboard testing The assessment is based on application of each of the six indices after initial the Fresnel Lens Optical Landing System MK 6 MOD 2 to noise levels measured within the cockpits of 191 fixed-wing and installation or the completion of a major change overhaul or 58 rotary-wing aircraft, grouped into 11 categories by engine type extensive repairs These tests are necessary to demonstrate the Equivalent speech interference levels obtained from the use of each integrity of the installation as well as functional readiness for of the Sir indices are prnvirled fnr the acnirstic spectra developed b operation Author (GRA) for the 11 classes of vehicles The operational considerations which influence speech interference values are described. Noise attenuation N71-23497’ National Aeronautics and Space Adminstration provided by headset devices commonly used by Air Force aircrew Langley Research Center Langley Station Va members is shown for different groups of noise spectra. Criteria ’ LEADING EDGE CURVATURE BASED ON CONVECTIVE are given for evaluating protected and unprotected exposures to HEATING Patent noise that compromise communications Author (GRA) Dewey E Wornom inventor (to NASA) Issued 16 Jul 1968 (Filed 1 Sep 1965) 5 p Ct 244-13 (NASA-Case-XLA-01486 US-Patent-3 392 936 N71-235381 Air Force Systems Command Wright-Patterson US-Patent-Appl-SN 484485) Avail US Patent Office CSCL 01A AFB. Ohio Foreign Technology Div A high speed flight vehicle having improved flight efficiently STABILITY AND CONTROLLABILITY OF SUPERSONIC at both subsonic and high speeds IS described All leading edges AIRCRAFT of the vehicle are provided with leading edge curvature while the V Lutskii et al 4 Dec 1970 13 p ref Trans1 into ENGLISH leading edge sweep is maintained along with a corresponding from Aviatsiya I Kosmonavtika (Moscow) no 4. 1970 p 25 - 27 decreasing leading edge radius such that the relationship between (AD-718474. FTD-HC-23-600-70) Avail NTlS CSCL 113 sweep and radius that IS normally associated with aerodynamic A general discussion is presented of various factors which affect heating at high speeds IS not altered the stability and controllability of supersonic aircraft GRA Official Gazette of the U S Patent Office

N71-23498# Aeroplane and Armament Experimental N71-23547# Aiuminum Lab Ltd , Banbury (England) Establishment. Boscombe Down (England). DEVELOPMENT OF SIZE 22 TYPE D.6O.S BEAGLE 8125 BULLDOG G-AXEH (LYCOMING 10-360AlC). SILICON-MAGNESIUM-ALUMINIUM ALLOY AIRCRAFT PART 1 : PREVIEW HANDLING TRIALS CABLES AND TERMINATIONS T. Heffernan. J. J. Lee. and R. Hargreaves 14 Oct. 1970 17 p G W Hunton Aug 1970 67 p (AAEE-963-Pt-1) Avail: NTlS (Contract KJ-D-3908-CB55C) A brief handling assessment has been made of the Beagle (TRC-BR-19785) Avail NTlS Bulldog at a representative training loading. The overall impression The performance of size 22 aircraft cables with conductors of the aircraft was most favorable. and it is well suited to the of type D 50 S silicon-magnesium-aluminum alloy is assessed trainer role. No handling problems were encountered and the together with their associated terminations and these are compared characteristics were even better than those of the Pup 150. The with their copper equivalents Author (ESRO) aircraft was easy to fly while providing scope to achieve precision. Ground handling was excellent, pedal forces being lighter than on N71-23591# Naval Ship Research and Development Center. the Pup. Stability and control were good about all axes. Stalling Washington. D C tests showed that the controls were effective throughout and UNSTEADY HYDRODYNAMIC LOADS ON A TWO recovery was prompt. The aircraft could be made to spin more easily DIMENSIONAL HYDROFOIL Final Report than the Pup and the rate of rotation. though fast. was acceptable John H Pattison Nov 1970 150 p refs in view of the stable nature of the spin. Aerobatics were if anything (AD-717953. NSRDC-3245) Avail NTlS CSCL 13/10 better than on the Pup die to the clear view canopy. constant Unsteady hydrodynamic lift. moment. and drag on a speed propeller, and larger rudder Recommendations are made for two-dimensional NACA 16-209 hydrofoi! are determined improving the cockpit layout. Author (ESRO) experimentally as functions of depth of submergence. forward speed

397 N71-23596

mean angle of attack and frequency of oscillation in pure heave and AIR FORCE MATERIALS SYMPOSIUM 1970. TECHNICAL pure pitch motions Various theoretical and experimental results SPECIALIST SESSIONS. SUMMARY ABSTRACTS are compared with the expenmental steady and unsteady load 22 May 1970 101 p Conf held at Miami Beach. Fla. 18-22 coefficients on the hydrofoil model The comparisons include both May 1970 finite and zero forward speed effects Added-mass coefficients are (AD-718432) Avail NTlS CSCL 11/6 obtained from the zero forward speed case Theoretical and The document contains the 100-word abstracts of all the experimental results do not agree because of limitations in both the papers presented in the Technical Specialist Sessions of the Air theories and exDeriments Author (GRA) Force Materials Symposium 70 held in Miami Beach Florida on 18-22 Mav 1970 Author (GRA)

N71-23596# Deutsche Forschungs und Versuchsanstalt fuer N71-23659*# National Aeronautics and Space Administration Luft und Raumfahrt Berlin (West Germany) lnst fuer Lewis Research Center Cleveland Ohio Turbulenzforschung OVERALL PERFORMANCE IN ARGON OF A 164 SOUND GENERATION BY A DISTURBED SIMPLE LAMINAR CENTIMETER (644 INCH) SWEPT BACK BLADED JET CENTRIFUGAL COMPRESSOR Alfons Michalke Jan 1971 38 p refs Carl Weigel Calvin L Ball and Edward R Tysl Washington Apr NTIS. ZLDl Munich 70 DM (DLR-FB-71-02) Avail 9 1971 21 p refs The sound generation by a part of a circular jet is investigated (NASA TM-X-2269 E-6100) Avail NTlS CSCLZOD theoretically The investigation IS limited to that part of the jet for Overall compressor performance is presented as a function which a linear theory is applicable In this ' linear flow region there equivalent weight flow At the rtpsign pqiiivalent weight flow of exists a laminar let flow approximately parallel with small spatially 0 69 kg/sec (1 52 Ib/sec) and the design equivalent tip speed of growing disturbances The source term of the Lighthill equation and 325 m/sec (1066 ft/sec) the compressor produced an overall the sound far-field IS calculated for this laminar fluctuating jet flow total pressure ratio of 2 28 and an adiabatic efficiency of 0 80 The For the special let flow produced by a cylindrical vortex sheet the peak efficiency at design speed was 0 808 at an equivalent weight directivity of sound is discussed at various Strouhal numbers and flow of 0 65 kg/sec (1 43 Ibm/sec' Author Mach numbers It is found that the directivity depends strongly on the Strouhal number and is quite different for axisymmetric and azimuthal source comDonents Author (ESRO) N71-23660# Martin Marietta Corp Baltimore Md Hesearch lnst for Advanced Studies SPAN LOADING AND WAKE FORMATION N71-23597# Deutsche Forschungs und Versuchsanstalt fuer Peter F Jordan Dec 1970 27 p refs Presented at Luft- und Raumfdhrt Porr (West Germany) Hauptabteilung AF OSA Boeing Symp on Aircraft Wake Turbulence Seattle 1 3 Wissenschaft und Technik Sep 1970 NUMERICAL METHOD FOR EVALUATING AERODYNAMIC (Contract F44620 69 C 0096) COEFFICIENTS OF THIN SUPERSONIC WINGS AT (AD 718024 RlAS TR 70 12C AFOSR 70-2873-TR) Avail NTlS ANGLE OF ATTACK CONDITIONS [NUMERISCHES CSCL 1/1 VERFAHREN ZUR BESTIMMUNG Contrary to the classical assumption of an elliptic span ANSTELLWINKELABHAENGIGER AERODYNAMISCHER loading the actual span loading contains a logarithmic term In BEIWERTE DUENNER UEBERSCHALLFLUEGEL~ consequence there is an infinite upwash directly behind the wing Walter Helmut Diesingsr Jan 1971 68 p refs In GERMAN lust inside the wing tip This explains why the aircraft wake rolls up ENGLISH summary faster than classical analyses predict The downwash distribution (DLR-FB-71 01) Avail NTlS ZLDl Munich 17 50 DM behind the circular wing is calculated in some detail The numerical method makes use of the linearized txm?ntial Author (GRA) flow theory and is limited to wings where Evvards theorem can be applied The method fits especially to preliminary design calculations where influence of warping and thickness of the wing N71-23673# Solar San Diego Calif are not needed The aerodynamic coefficients are evaluated by TUNGSTE N REI N F OR CED 0x1 D AT1 0 N RESISTANT numerical integration of the velocity potential for which the numerical COLUMBIUM ALLOYS Final Report, 1 Nov 1969 1 Nov. accuracy can be determined by a simple additional procedure 1970 M Klein A G Metcalfe and R B Domes Nov 1970 78 p Because of the comparatively small amount of calculations the method may be applied to reduce the running time of existing refs computer programs For the application at desk calculation machines (Contract NO0019 69 C-0137) (AD 717969 RDR-1635-8 SOLAR-R-P-6-31 13-7) Avail NTlS tables are listed and simple examples presented Author (ESRO) CSCL 1 1 /4 lhe approach used in this investigation was to combine N71-23609# Collins Radio Co Cedar Rapids Iowa weak but oxidation resistant matrices with high-strength filaments INTEGRATED HIGH FREQUENCY ANTENNA SYSTEM. to produce a composite with oxidation resistance under loads at APPENDIX D Final Report, 13 Nov 1969 9 Nov 1970 temperatures above 2OOOF These operating temperature and Nov 1970 361 p refs strength goals are needed for gas turbine engines but are beyond the (Contract N62269 70 C 001 6) range of nickel and cobalt base superalloys which have maximum (AD 718054 Rept 523 0763421 OOlllM App D) Avail NTlS temperature capabilities of about 1900F Ideally the composite CSCL 9/5 material could be used uncoated but could also serve as a fail safe The document describes tests to determine the spectral material when coated During the period covered by this report (the chard~teristirsof an AN/ARC 132lV) Radio Set conslsting of the second year) characterization of the mechanical properties oxidation units and niodule5 sp?cified in paragraph 5 2 The subject tests are resistance and filament matrix compatibility of the model system a requirement of the Integrated High Frequency Antenna System was continued Author (GRA) IlHFASl Pha\e 111 Contract IN62269 70 C 0016) and will be performed in accorddnce with MI1 STD 449C Author (GRA) N71-23702*# Scientific Translation Service. Santa Barbara Calif THE EFFECTS OF FLOW CONTAINING DUST ON THE N71-23625# Air Force Systems Command. Wright-Patterson RESULTS OF HYPERSONIC WIND TUNNEL EXPERIMENTS AFB Ohio Material\ Lab IVLlYANlYE ZAPYLENNOSTI POTOKA NA REZUL'TATY

398 N71-23779

ISPYTANIYV GIPERZVUKONUKH AERODINAMICHESKIKH aircraft during the Barbados Oceanographic and Meteorological TRUBAKH) Experiment IBOMEX) July 11 to 28. 1969 are documented with 8 I Bakum et al Washington NASA Apr 1971 7 p refs Trans1 specific information on the character and location of the photography into ENGLISH from ILVAkad Nauk SSSR Mekhan Zhidkosti I The photographic products. the tabulation of cloud photography

Gaza (Moscow). no 4, Jul ~ Aug 1970 p 187 189 data. the procedure used to reconstruct flight tracks and Posltlon (Contract NASw-2035) photographs are described with the availability Of archived data (NASA-TT-F-13529) Avail NTlS CSCLLOD Author The influence of flow containing dust upon aerodynamic experiments in hypersonic wind tunnels is considered It is found that there is an increase in drag for thin profrles and a drag N71-23748# School of Aerospace Medicine. Brooks AFB. Tex decrease for blunt profiles Author NOISE ASSOCIATED WITH AIRBORNE OPERATION OF C-141A AIRCRAFT Final Report, 1 Mar. 1969 28 Feb. 1970 Donald C Gasaway Dec 1970 34 p refs N71-23720# Civil Aeronautics Board. Washington. D.C. (AD-7 18097. SAM-TR-70-74) Avail NTlS CSCL 201 1 CAPTIVES OF INDUSTRY Acoustic noise measurements obtained within several Lockheed Whitney Gillilland 1970 9 p refs Presented at Braniff Intern C- 141A aircraft during various operational missions are reported, Airlines Management Club. Dallas. 16 Nov. 1970 factors of aeromedical significance are identified and described Avail: Issuing Activity and methods with which undesirable effects can be controlled are The role played by the CAB in determining passenger fares. proposed Author (GRA) granting new routes, and encouraging competition among air carriers and among aircraft manufactures is described. It is felt that N71-23764*# National Aeronautics and Space Administration the air transportation system which has evolved is characterized Lewis Research Center Cleveland Ohio by operational efficiency. excellent quality and extent of services. SHUlTLE AIRBREATHING PROPULSION economy. and reasonable fare levels. N.E.N. Warner L Stewart Arthur J Glassman and Stanley M Nosek 119711 15 p Presented at the 7th Propulsion Joint Specialist Conf Salt Lake City 14 18 Jun 197 1 sponsored by AlAA N71-23726* National Aeronautics and Space Administration (NASA TM X 67806) Avail NTlS CSCL2lA Marshall Space Flight Center. Huntsville Ala Airbreathing gas turbine engines are considered to provide ANEMOMETER WITH BRAKING MECHANISM Patent cruise landing go around and ferry capability for space shuttle Robert E Turner and Dennis W Camp inventors (to NASA) vphrClpg The study reported !s bas& 3" the q-csssip; determtnc Issuea 0 Sep 1YbY Ihled 15 Aug 19671 4 p CI 73 189 lnt which engines are most suitable and to examine them for CI GOlw1/02 modifications and technology needed to meet new requirements (NASA Case XMF-05224 US Patent 3 165 584 such as launch, space residence and reentry A review is made of the US Patent-Appl-SN-660842) Avail US Patent Office CSCL 146 requirements imposed on the engine the effect of fuel selection An anemometer having a wind driven member mounted and the studies currently being conducted to assess candidate on a shaft journaled for rotation in a cylindrical base and a braking engine designs Author mechanism positioned on the base for engagement with the shaft to stop movement of the wind driven member is described The braking mechanism includes a housing a brake lever and solenoid N7i-237788 Aatuiidulicdi Rebearch ~db5,Meiouurne tAusrraliar ttwuiiiru un &,ehousing driu d iinnage connecring me soienoio ana brake lever where the brake lever can be pivoted to a position Of STATIC PRESSURE PROBES AT MACH 7.5 engagement with the shih journaled for rotation in the base M J Williams Sep 1970 15 p refs Official Gazette of the U S Patent Office (ARL/A-3271 Avail NTlS Two static pressure probe shapes with pressure holes at varying distance from the nose have been tested at Mach number N71-23738# Boeing Scientific Research Labs.. Seattle, Wash 15 in the Reynolds number range from 3200 to 9600, based on FINITE DIFFERENCE CALCULATIONS OF THE BEHAVIOR probe diameter Self-induced pressures produced by boundary layer OF A DISCONTINUOUS SIGNAL NEAR A CAUSTIC interaction with the external inviscid flow were strongly dependent R. Seebass. E. M. Murman, and J. A. Krupp Jan. 1971 11 p on hole position and could not be correlated by the flat plate refs Presented at the Conf. on Sonic Boom Res., 3d. Washington. viscous interaction parameter The influence of nose shaDe was

D.C.. 29 ~ 30 Oct. 1970 negligible at stations not too close to the shoulder as was the effect (AD-718835; D1-82-1040) Avail. NTlS CSCL20/1 of probe temperature As a result of these tests design and It is important to predict sonic boom overpressure signatures calibration data for probes suitable for detailed exploration of the in the vicinity of a caustic. In particular. one needs to be able to core of the tunnel flow are now available Author calculate the overpressure when the caustic surface intersects, or when it is near the ground. While the analytical formulation of this problem is a simple one. the solution by formal mathematical N71-23779*# National Aeronautics and Space Administration techniques presents great difficulties. Consequently. there is great Ames Research Center Moffett Field Calif impetus for developing numerical techniques that can provide such MEASUREMENTS OF BOUNDARY LAYER TRANSITION, predictions. Here the authors report on the extension to the SEPARATION AND STREAMLINE PIRECTION ON caustic problem of a technique developed by Murman and Cole for ROTATING BLADES transonic flows Author (GRA) William J McCroskey Washington Apr 1971 38 p refs Prepared in cooperation with Army Air Mobility Res and Develop Lab, Moffett Field Calif N71-23746# Environmental Science Services Adminlstration. INASA-TN-D 6321 A-3863) Avail NTlS CSCLLOD Rockville. Md BOMAP Office Laminar separation. transition to turbulence and surface HIGH LEVEL CLOUD PHOTOGRAPHY INVENTORY: BOMEX streamline directions were measured on helicopter rotor blades in PERlOD4.11 28JULY 1969 a variety of rotating and nonrotating configurations The results VanceA Myers Mar 1971 70 p Reprinted indicate that the centrifugal effects of rotation do not significantly alter (ESSA-TM-ERLTM BOMAP-1) Avail NTlS the boundary layer development for most operating conditions The high-level cloud photography missions flown by RB-57F Laminar separation bubbles were observed near the leading edge

399 N71-23796

of the upper surface of the blades at moderate and large angles or control yoke and an arm secured to the internal gear sector of attack and this phenomenon triggered a sudden transition to extends immediately adjacent to the steering wheel so that It IS turbulent flow Surface streamline patterns were found to be the within easy reach of the pilot's thumb Same for both laminar and turbulent flows Author Official Gazette of the U S Patent Office

N71-23796*# Techtran Corp Glen Burnie Md N71-23818# Air Force Systems Command, Wright Patterson LAMINAR BOUNDARY LAYER ON A WING AND A BODY AFB. Ohio Foreign Technology Div OF REVOLUTION IN THE PRESENCE OF BLOWING S?APIL!TY AND COMTROLLAB!L!TY OF SL!PERS@hl!C ILAMINARNYY POGRANICHNYY SLOl NA KRYLE I TELE AIRCRAFT VRASHCHENIYA PRI NALICHII VDUVANIYA~ V Lutskii et al 3 Dec 1970 10 p Transl into ENGLISH from L F Kozlov et al Washington NASA Apr 1971 12 p refs Aviatsiya I Kosmonautika (USSR). no 10. 1969 p 21 -23 Transl into ENGLISH from Samoletostr Tekh Vozdush Flota (AD-718285. FTD-HC-23-596-70) Avail NTlS CSCL 1/3 (USSR) no 17 1970 p 19 25 Controllability and stability are interrelated and determine (Contract NASw 2037) one another The characteristics of the stability and controllability (NASA TT F 13627) Avail NTlS CSCL20D of modern supersonic aircraft in longitudinal and lateral movement A method is developed for calculating the characteristics are analyzed Author (GRA) of a two dimensional axisymmetric incompressible boundary layer on a blown wing using a sixth order polynoniial for approximating the velocity distribution acrocs the boundary layer, An arbitrary N71-23822*# National Aeronautics and Space Administration velocity distribution at the outer boundary of the layer is assumed Lewis Research Center Cleveland Ohio A solution to the problem is obtained with the aid of Karman s NOZZLE PERFORMANCE MEASUREMENT ON UNDERWING integral relation The method can be readily extended to the NACELLES OF AN F 106 UTILIZING CALIBRATED calculation of blown laminar boundary layers on bodies of revolution ENGINES AND LOAD CELLS Author Harold W Groth (19711 21 p refs Presented at 7th Propulsion Joint Specialist Conf, Salt Lake City, 14-18 Jun 1971, sponsored by AlAA N71-23805# Air Force Systems Command Wright-Patterson (NASA TM-X-67816) Avail NTlS CSCLOlC AFB. Ohio Aero Propulsion Lab Installation effects on turbojet engine exhaust nozzles over EFFECTS OF FUEL SLOSH AND VIERATION ON THE a range of flight Mach number from 0 60 to 1 30 are discussed TWO FLAMMABILITY HAZARDS OF HYDROCARBON TURBINE J85-13 afterburning turbojet engines were mounted in underwing FUELS WITHIN AIRCRAFT FUEL TANKS Technical Report, nacelles Exhaust nozzle propulsion efficiency is being measured 1 Sep. 1969 30 Apr. 1970 using load cells, calibrated engines. and flight calibrated nacelle tare Edwin E Ott Nov 1970 63 p refs forces Reference nozzles of known performance were used to (AD-718091, AFAPL-TR-70-65) Avail NTlS CSCL 21/2 determine nacelle tare forces Analysis of flight calibration data The report deals with the effects of liquid fuel motion on shows that the system is capable of determining nozzle efficiency the flammability of hydrocarbon turbine fuels in aircraft fuel tanks to a one-sigma random error + or 1 5 percent Author Three military turbine fuels JP-4. JP-5. and JP-8. were used in the testing The fuels were placed in an explosion proof cylindrical test vessel (80-gallon capacity) and subjected to slosh and vibration An electric arc was formed within the ullage which ignited any N71-23860*# National Aeronautics and Space Administration flammable fuel-air mixture present The pressure rise from combustion Langley Research Center Langley Station Va was measured and correlated with initial conditions The major A WIND TUNNEL INVESTIGATION OF STATIC effect of fuel slosh and vibration was to lower or abolish the lean LONGITUDINAL AND LATERAL CHARACTERISTICS OF A flammabile temperature limit of the fuel The rich flammable FULL-SCALE MOCKUP OF A LIGHT TWIN ENGINE temperature limit was unchanged An analysis was performed on AIRPLANE these results and an explanation proposed based upon the hypothesis Marvin P Fink James P Shivers and Charles C Smith Jr that all the fuel vapor in the ullage burns for combustion below Washington Apr 1971 269 p refs the flash point Author (GRA) (NASA TN D-6238 L 7607) Avail NTlS CSCL 20D The model was a full scale mockup of a light twin engine low wing monoplane Tests were made over an angle of attack N71-23809* National Aeronautics and Space Administration range of 4 deg to 24 deg and over a sideslip range of i or Ames Research Center, Moffett Field. Calif 8 deg at thrust coefficients of 0 0 19. and 0 28 Control CONTROL DEVICE Patent effectiveness and hinge moments were determined for a full range Nozomu lwasaki and Wayne 0 Hadland inventors (to NASA) of deflections on the aileron elevator and rudder Downwash Issued 14 Oct 1969 (Filed 28 Nov 1967) 4 p CI 74-89 19. surveys were made in the region of the horizontal tail Limited tests Int CI F16j15/50 were made with simulated ice on the wing and horizontal tail (NASA-Case-XAC-10019, US-Patent-3,472 086 Author US-Patent-Appl SN-686209) Avail US Patent Office CSCL 131 A potentiometer mounted on a small housing or bracket N71-23861*# National Aeronautics and Space Administration with a driving wheel or disc secured to the shaft IS described A Ames Research Center Moffett Field Calif sector of the disc is provided with gear teeth and another sector LARGE-SCALE WIND TUNNEL INVESTIGATION OF A is provided with a cam profile against which a cam follower acts DUCTED FAN. DEFLECTEDSLIPSTREAM MODEL WITH The cam follower is carried on a slide and is urged to engage with AN AUXILIARY WING the cam profile by a biasing spring or the like which acts against Michael D Falarski and Kennety W Mort Washington Apr 1971 a bearing member The spring acts on the bearing member in a 49 p refs Prepared in cooperation with Army Air Mobility R direction toward the cam profile so as to balance the force and D Lab transmitted to the shaft by the cam follower itself A large internal (NASA TN D 6323 A 3670) Avail NTlS CSCL20D gear sector is pivotly mounted on the frame so that movement The longitudinal aerodynamic charaCteristicS of a semispan through a relatively small arc will produce rotation of the cam wing deflected slipstream configuration with a double slotted flap through its complete profile The frame is adapted to be secured and an auxiliary wing were determined The model was powered to some operating member of aircraft such as the steering wheel by two low-pressure ratio ducted fans A comparison of static test

400 N71-23980

results with results obtained from various propeller-driven N71-23934 National Lending Library for Science and configurations indicates that the turning effectiveness of fan-powered Technology Boston Spa (England) deflected-slipstream configurations can be correlated with DESIGN OF A NONEXPANDING REFLECTOR BALLOON propeller-powered configurations with the same flap-chord to E Reininger 16 Feb 1971 41 p refs Transl into ENGLISH . slipstream-diameter ratio The turning effectiveness of the auxiliary from Meteorol Nationale (France) no 255 wing was essentially the same as would be produced by a (NLL-M 20326-(5828 4F)) Avail Natl Lending Library. Boston conventional slotted flap system with the same flap-chord to Spa Engl 4 NLL photocopy coupons slipstream-diameter ration The auxiliary wing reduced the thrust Theoretical considerations are presented for a nonexpanding required at low speeds as would be expected due to the inorease reflector balloon capable of measuring the fine structure of the high in lifting surface area Aulhor stratosphere after a fast ascent through the troposphere Balloons which expand a great deal (of Neoprene). balloons which expand very little (of natural latex) and balloons of both types inside each N71-23922*# National Aeronautics and Space Administration other are discussed Pressure, volume, weight. ascent rate. and Flight Research Center. Edwards. Calif burst altitude are considered for each case It is shown that the COMPARISON OF WIND TUNNEL AND dual arrangement with the enclosed balloon for the nonexpanding FLIGHT-MEASURED BASE PRESSURES FROM THE material gives the best results To achieve a maximum increase in SHARP-LEADING-EDGE UPPER VERTICAL FIN OF THE X-15 height and mimmum weight excess pressure is permitted to AIRPLANE FOR TURBULENT FLOW AT MACH NUMBERS escape to the atmosphere through a tube with a valve adjusted for FROM 1.5 TO 5.0 very low internal excess pressure The inner balloon is composed Sheryll A. Goecke Washington May 197 1 38 p refs of tetrahedral sections made of metallized polyethylene N E N (NASA-TN-D-6348, H-602) Avail NTlS CSCL 20D Pressures measured at six locations on the base of the sharp-leading-edge upper vertical fin of the X-15 airplane during N71-23953*# National Aeronautics and Space Administration the power-off portion of eight flights are compared with previous Ames Research Center Moffett Field Calif flight data obtained from a blunt-leading-edge fin. theov. and wind SURFACE-FLOW VlSUALlZATlON INVESTIGATION OF A tunnel data The flight and wind tunnel base pressure ratios for the DELTA WING SHUlTLE CONFIGURATION AT A MACH Mach number range from 1 5 to 5.0 are presented as a linearized NUMBER OF 7.4 AND SEVERAL REYNOLDS NUMBERS function of turbulent boundary-layer height and base width by H Lee Seegmiller Jun 1970 56 p refs using a Mach-number-dependent factor derived in the study. The (NASA-TM-X-620361 Avail NTlS CSCL 20D , resiilting r~veseen5 ts proslide ~ncther'criterien for determ:n:og SUrfece-Ro& vijualazainoii phoiogtciphs die preseiired for whether flow is laminar or turbulent. The difference between base a model of a delta wing shuttle concept An oil flow technique was pressure and free-stream pressure for any specific Mach number used to visualize the surface flow at a Mach number of 7 4 and of the study is found to be a linear function of both free-stream several Reynolds numbers between 1 400.000 and 5 700.000 L pressure and dynamic pressure. Data from the sharp-leading-edge Angles of attack from 15 deg to 60 deg were tested at zero upper vertical fin agree with data from the blunt-leading-edge sideslip A sideslip angle of 5 deg was also tested at an angle of upper vertical fin. The flight data show the variation in pressure attack of 15 deg Details of the surface patterns are shown which across the base to be negligible Author illustrate the complexity of the hypersonic flow Author

N71-23927*# National Aeronautics and Space Administration N71-23967*# Techtran Corp Glen Burnie. Md Lewis Research Center Cleveland Ohio ESRO HAS BEGUN THE INITIAL STUDIES FOR A INSTANTANEOUS AND DYNAMIC ANALYSIS OF EUROPEAN SYSTEM OF AIR TRAFFIC CONTROL VIA SUP€ RSONl C INLET-E NGI N E COMPATI BILlTY SATELLITE [ L'ESRO A LANCE LES PREMIERES ETUDES James E Calogeras Paul L Burstadt. and Robert E Coltrin D'UN SYSTEME EUROPEEN DE CONTROLE DU TRAFIC [ 197 11 16 p refs Presented at the 7th Propulsion Joint Specialist AERIEN PAR SATELLITE^ Conf . Salt Lake City. 14 18 Jun 1971 sponsored by AlAA Jacques Morisset Washington NASA May 1971 5 p refs (NASA-TM-X-67821 ) Avail NTlS CSCL 2 1A Transl into ENGLISH from Air et Cosmos (France). no 363. 10 An experimental wind-tunnel investigation was made to Apr 1971 p 15 determine the effects of time-variant distortions produced in a (Contract NASw-2037) supersonic inlet on a J85-GE-13 turbojet engine Results are (NASA-TT-F-13651) Avail NTlS CSCL22A presented principally in terms of instantaneous distortion amplitudes The progress of European development of a UHF air traffic and contours measured through compressor stall They indicate control satellite under the direction of ESRO IS examined in the that although a time-averaged distortion may be far from a light of American decisions regarding cooperation Author stall-inducing value. corresponding instantaneous distortion amplitudes can approach or exceed this value A film made by combining instantaneous distortion contours demonstrates that severe total N71-23980*# National Aeronautics and Space Administration pressure fluctuations at the compressor face can result in an Lewis Research Center Cleveland Ohio instantaneous distortion of a type completely different from the COLD AIR INVESTIGATION OF A TURBINE WITH time-averaged distortion Author TRANSPIRATION COOLED STATOR BLADES 4 STAGE PERFORMANCE WITH WIRE-MESH SHELL STATOR BLADING N71-23931# Aeronautical Hesearch Labs Melbourne (Australia) Frank P Behning. Harold J Schum and Edward M Szanca DEPARTMENT OF SUPPLY, AERONAUTICAL RESEARCH Washington Apr 1971 30 p refs LABORATORIES ANNUAL REPORT. 1969 - 1970 (NASA-TM-X-2176 E-6C28) Avail NTlS CSCL 21E Canberra Australia Australian Govt Publishing Sew 1971 Turbine performance characteristics were obtatned with a 92 p refs Original Contains Color Illustrations single-stage axial-flow turbine which had stator blades employing Avail NTlS transpiration coolant election through a wire mesh shell The turbine Summaries for the research during this period are presented was tested over a range of speed and pressure ratio and with Topics include wind tunnel facilities aerodynamics structural nominal coolant fraction of 0 031 Additional tests were made at analysis atmospheric turbulence and instrumentation F 0 S the design speed in which the coolant flow was varied from 0 to

40 1 N71-24001

0 07 of the primary flow The results were compared to similar the injection system The application and functional reliability of results obtained from turbines using stator trailing edge coolant this fuel preevaporation system in small tip drive ramjet engines is election and discrete hole transpiration-cooled stator A base turbine demonstrated and proved by means of tests The influence Of the with no cooling provisions was used as a standard for comparisons operational parameters, such as velocitv of air flow altitude Author air-fuel ratio fuel flow rate and pressure on the caloric state of the fuel before injection and after expansion was theoretically investigated N71-24001*# National Aeronautics and Space Administration Author Ames Research Center Moffett Field Calif EIIDCAPC CI~M\iiciini 17nrinki munm-w-aamue nc ~ur “.VIII-”L-, LV.. .I“YCILILC.IIVI. I I1VIVUr,~rllQ vr ,nc MSC ORBITER AND A 55 DEG SWEPT DELTA WING N71-24081*# Wayne State Univ Detroit Mich Research lnst MODIFICATION FOR SEVERAL REYNOLDS NUMBERS AT for Engineering Sciences MACH NO 104 STUDY OF CONCEPTUAL AND OPERATIONAL H Lee Seegmiller Apr 1970 110 p refs FEASIBILITY OF LASER DOPPLER DETECTION SYSTEMS (NASA-TM-X-62033) Avail NTlS CSCL 20D Progress Report Surface flow visualization photographs are presented for J Alex Thomson 30 Nov 1970 103 p refs the straight wing orbiter concept Results are also shown for a 55 (Contract NAS8 248 10) deg swept delta wing modification to the configuratron and for the (NASA CR 103105) Avail NTlS CSCL20E fuselage without wings The surface flow streamlines were visualized Continuing research is reported in a program aimed at with an oil flow technique at a Mach number of 104 and length establishing the feasibility and design criteria of a laser doppler Reynolds numbers of 0 5 0 84 and 2 7 x 1 millmn The angles of system for dptpcting and mapping tiirhiilenre IPVPISand wind or attack were 18 deg 40 deg. 50 deg 60 deg. and 70 deg velocity profiles in various applications Current efforts include (1 Author the design of an optical mechanical system for the laser van (2) calculations to obtairi detailed profiles for the system radial and ~71.2400g*#National Aeronautics and Space Administration axial response for various operating conditions and methods and Lewis Research Center Cleveland Ohio aperture apodization functions (3) compilation of a set of specific LOW SPEED JET NOISE FROM A 183 METER (6 FOOT) experiments and experimental oblectives for the laser van system FAN FOR TURBOFAN ENGINES and (4) construction of a source that can be used as a standard Gene L Minner and Charles E Feller [I9711 11 P refs scatterer A summary of completed projects is included D L G Presented at the 4th Fluid and Plasma Dyn COnf Palo Alto Calif 21 23 Jun 1971 Sponsored by AlAA (NASA TM X 67825) Avail NTlS CSCL 21 E N71-24298# National Aeronautical Establishment Ottawa The let noise contribution to the far field sound from a (Ontario) 1 83 meter diameter fan has been determined for two simulated FREE VIBRATIONS AND RANDOM RESPONSE OF AN nacelle configurations One nacelle had hard walls while the other INTEGRALLY STIFFEN ED PANEL has acoustic liners on the wall and on inlet splitter rings The let Mervyn D Olson and Garry M Lindberg Oct 1970 121 p refs velocities typical of high bypass ratio fan engines varied from 137 (LR-544 NRC 118551 Avail NTlS to 223 meters per second The results of the study show that The free vibrations and random response to jet noise of the acoustic liners effectively eliminate low frequency noise from an integrally-stiffened five-bay panel were studied both theoretically internal sourLeS Ddta from the lined configurations were found to and experimeritally A finite element approach was used to represent be in good agreement with the eighth power dependence on let the panel and the predictions were verified by measurements on velocity Data from the hard wall conflgurations because of the a model panel integrally machined from solid aluminum stock The influence of internally generated noise show higher noise levels and comparison between predicted and measured vibration modes and a weaker velocity dependence Author frequencies revealed good correlation of frequencies while the correlation of mode shapes was only fair especially for higher N71-24021*# Lockheed Georgia Co Marietta modes The predicted models and frequencies were used in a modal RESIDUAL TENSILE PROPERTIES OF MATERIAL FROM analysis of the panel s response to jet noise with a consistent finite C-130 CENTER WING SECTION AFTER SERVICE Final element method being introduced to calculate the required Report cross spectral modal force terms Quantitative agreement between L R Kaisand I19701 15 p predicted and measured RMS stresses and displacements was (Contract NAS1-9485) realized whereas only qualitative agreement was obtained for the (NASA-CR-111828) Avail NTlS CSCLOlE associated spectra Author No adverse correlation was found between the residual tensile properties of 7075-T6 material and the associated number of flight hours of the C-130 aircraft from which the specimens were extracted Author

N71-24053’# Scientific Translation Service Santa Barbara Calif PREVAPORIZATION OF LIQUID FUEL IN A SMALL RAMJET ENGINE [DIE VORVERDAMPFUNG VON FLOSSIGKRAFTSTOFF IN ElNEM KLEINEN STAU STRAHLTRIE B WERKI F Gehring (Ph D Thesis Stuttgart Univ) Washington NASA Apr 1971 128 p refs Trans1 into FNGLISH from Deut Luft und Raumfahrt German report DLR FE 69 67 (Contract NASw 2035) (NASA TT F 13605) Avail NTlS CSCL 2 1 E In order to improve the combustion efficiency the liquid fuel is heated up by the dissipated heat of the ramjet engine to such an extent that it evaporates immediately during expansion in

402 SUBJECT INDEX

6 AERONAUTICAL ENGINEERING 1 A Special Bibliography (Suppl. .JULY 1971 I 7)

Typical Subject Index Listing

SUBJECT HEADING Adaptive self-orqanizinq and -1earninq control ACCIDEIT PREVIRTION systems with lonq and short term memory predictor displars for retention, using logic random searches to find control problems parameter values [ SASA-Cp- 1113723 lN71- 11466I [ ASf4E PAPER 71-DE-221 171-27324 ADEESIVE BOBDING Patique life, fail-safe capability and corrosion resistance of commercial aircraft structures NUMBER improved thronqh adhesive metal-metal bonding CONTENT NUMBER [ ASlE PAPER 71-DE-271 A71-27325 ADIABATIC COllDITIONS The subject heading is a key to the subject content of the document The supersonic boundary layer transition on adiabatic Notation of Content (NOC) rather than the title of the document. is used wall. discussinq wind tunnel size, surface ronqhness and freestream disturbances effects to provide a more exact description of the subject maner The report number TAIAA PAPER 70-5861 1171-27554 helps to indicate the type of document cited (e g NASA report translation ADIABATIC moa NASA contractor report) The accession number is located beneath and Reynolds number effects on centrifuqal compressor to the right of the Notation of Content eg N71-11466 under any one performance characteristics, discussing power subject heading the accession numbers are arranged In sequence with losses in compressor, impeller and diffuser the IAA accession numbers appearing first staqes and compressor adiabatic efficiency [ ASIE PAPER 71-GT-251 A71-25967 mx,xin TDFGS I Aerodynamic characteristics of near wakes produced 1 A b9 periodic vortex shedding from airfoils AC GENERATORS [ AD-7188931 N71-23245 aindaqe tests of cylindrical and Lundell-conical AERIAL PEOTD6BAPHT rotors in ambient air produciuq Reynolds numbers statistical diameter size distribution of randon 1 up to 100.0@@ for high speed alternators circles on ulane or spheres in space from [ NASA-Tl-X-67R091 N71-23116 satellite and aircraft measurements for aerial ACCELERATED LIFE TESTS and cloud photoqraphy Passenqer aircraft structures accelerated testinq A71'-27100 for safety and fatique durability under Tabulation of E-57 aerial cloud photoqraphy of operational conditions, describinq tests, tropical convection systems for 11 to 28 July planning and evaluation 196Y with flight path over Barbados Islands A71 -269U6 [ SSSA-TI-ERLTB-BOIEP-11 N71-23746 Theory, calculation, and design of centrifuqal AERODIIAUIC BALANCE ComPressor machines Reentry vehicles confiquratian lift and draq TAD-7178181 N71-23297 coefficients in hypersonic flow from pressure ACCELERATION (PETSICS) distribution and balance measuraments, comparinq Initially spherical liquid droplet transiect with isolated cone data response under surface tension accelerated by A71-25487 external qas flou AERODTIAlIC CEAEACTERISTICS ~AIAA PAPER 71-3931 871-25355 wind tunnel evaluation of analytical method for Sound radiation from tine varying point force in predictinq lonqitudinal stability and accelerative motion, applying to fan or aerodynanic characteristics of large flexible helicopter rotor noise at subsonic tip speeds aircraft applied to supersonic transport 171-26702 configuration Analysis of nornal accelerations thronqh center of [AIAA PAPER 71-3431 A71-25322 gravity of aircraft due to landinq inpacts and Aerodynamic characteristics of slpnder body of qround operations associated with taxi, takeoff, revolution travelinq in long tube with circular and laudinq cross section, deriving static and dynamic i NASA-TR-D-6 124 ] N71-22620 stability derivatives formulas ACCELEBOIETEBS A71-25477 Iodal characteristic pick-up systen for vibration Asymmetric three dimensional aprodynamic density tests of rockets or aircraft on ground, using fields from holoqraphic intmferoqraas, applyinq small size accelerometers with individual to supersonic flow from free jet electronic circuit 1171-25802 1171-271 19 nutual aerodynamic effects of SN-1 helicopters ACOUSTIC BEASOREBENTS durirq simultaneous takeoff and landing, Axial flow €an noise, investigating louvers detersininq minimum distances between effects on sound field helicopters 1171-26704 171-26953 I Identification and control of aeromedical factors Predictinq aerodynamic characteristics of arrow, associated with aircraft noise and acoustic delta. and diamond vinq platforms usinq ~ measurements durinq C-141 operational nissions Prandtl-Glauert transformation [AD-7180971 N71-23748 r NASI-TN-D-62431 N71-21973 I I ACOUSTIC SCATTERIIIG Nose bluntness effect OD aerodvnamic I Aerodynamic noise scattering near Liqhthill cnaracteristics of flared body in supersonic multiples, considering intense near-field enerqy wind tunnel conversion into sound waves [ NAL-TR-221] N71-22160 I A71-26U48 Computer program to qenerate turbine aerodynamic ADAPTIVE COBTROL requirements, approximate external blade Adaptive systems - Conference, Iloscor, Iarch 1970 qeometries, and coolant flow requirements for 171-26714 two staqe axial flow torbine r NASA-Tf4-X-22291 N71-22568

A-1 AERODYNAMIC COEFFICIENTS SUBJECT INDEX

Numerical analysis of dynamic and thermodynamic cruciform control surface in blunt-nosed canard state of plenum-type air-cushion vehicle to configuration for subsonic, transonic and determine heave response and control system supersonic flows operatinq characteristics A71-25 161 [ NASA-TN-D-62571 N71-22589 T tail flutter analysis, considering dihedral, Uind tunnel tests to determine effects of winq angle of attack and aerodynamic force effects dihedral angle on aerodynamic characteristics of A71-25188 hiqhly swept f ired-winq cnnfignrntinn Uin?-fuselage-tail interacting low speeil flettnr; [ NASA-TM-X-226 11 N71-22622 considerinq mechanical tuninq and aerodynamic Numerical analysis of influence coefficients, interference couplinqs natural frequencies, and mode shapes of [AIAA PAPER 71-3261 A71-25306 vibration of trianqular inflatable winq Equation error approach to parameter N71-22666 identification in third order pitch plane Effect of enqine position and hiqh lift devices on dynamics for high performance aerodynamically aerodynamic characteristics of external flow, controlled aerospace vehicle jet flap STOL model - qraphs A71-26418 [ NASA-TN-D-62221 N71-23124 Sailplanes control, derivinq incremental Wind tunnel investiqation of hypersonic transport aerodynamic load on horizontal tail produced by model aerodynamic characteristics at nach instantaneous elevator deflection numbers to 6 - qraphs A71-26487 [ NASA-TN-D-6191] N71-23127 Computer proqram for aerodynamic forces on Low subsonic lonoitudinal aerodynamic flexible plate underqoinq transient motion in characteristics of twin body space shuttle shear flow, applyinq to panel flutter booster confiquratios usinq low turbulence A71-27559 pressure tunnel - qraphs Beasurement of force and pressure fluctuations on I NASA-TM-X-21621 N71-23135 airfoils durinq transverse and streamuise gust Aerodvnamic characteristics affectinq stability flows and controllability of supersonic aircraft [ CUED/A-TUR8O/TR-21] N71-22374 [AD-718474] N71-23538 Data reduction techniques for deriving aerodynamic Aerodynamic performance of sweptback-bladed forces and moments in absence of support centrifuqal compressor in arqon as function of interference equivalent weiqht flow [NASA-CR-1118441 N71-23122 NASA-Tll-X-22691 N71-23659 ABRODYNAIIIC BEAT TRAlSPER Effects of flow containinq dust on results of Heat transfer to airfoil in oscillating flow at hypersonic wind tunnel experiments large anqles of attack, showinq vortex shed [ NASA-TT-F-13529 1 N71-23702 reattachment and Nusselt numbers increase Investiqation of lonqitudinal and lateral [ ISNE PAPER 71-GT-181 1171-25963 stability and controllability of supersonic AERODYNAMIC HEATING aircraft Aircraft structural elements thermal behavior I AD-718285 J N71-238 18 under aerodynamic heating with linear dependence Wind tunnel investiqation of static lonqitudinal on initial temperature and lateral characteristics of full scale mockup A71-27493 oE liqht twin enqine aircraft Heat flux sensor adapted for mountinq on aircraft NASA-'IN-D-62381 N71-23860 or spacecraft to measure aerodynamic heat flux Wind tunnel investiqation of lonqitudinal inflow to aircraft skin N71-23085 aerodynamic characteristics of semispan winq rNASA-CASE-XPR-O3802] deflected-slipstream confiquration with double AERODYNAflIC LOADS slotted flap and auxiliary winq Quasi-three dimensional method €or radial flow INASA-TN-D-63231 N71-23861 compressor blade loadinqs computation, Cold-air tests to determine performance presentinq combined meridional plane and blade characteristics of sinqle-staqe turbine with to blade solutions for adaptation to computer stator blades employing transpiration coolant ASflE PAPER 71-GT-60 3 A71-25982 ejection throuqh wire mesh shell Flutter analysis of clamped thin skew panels with [NASA-Tn-X-21761 N71-23980 midplane forces in supersonic flow, usinq AERODYNAMIC COEFFICIENTS Galerkin method wins flap slipstream deflection correction method A71-26766 for evaluation of propeller power effect on lift Aircraft wake turbulence with downwash loading Of and draq coefficients of Arava twin enqine STOL winq span aircraft [ AD-7183241 N71-23660 A71-25164 AERODYNAMIC NOISE Two dimensional laoinar boundary layer equation Screech noise generation by supersonic

A-2 SUBJECT IIDEI AIR PLOU

tnnnel perf 01mance A71-27473 [ NASA-T!I-X-679731 N71-22394 Proceedinqs and recommendations of conference on AEROSPACE EUGIBEERIIG sonic booms Pulsed laser holoqraphic applications to aerospace I [ IGIA- 17/4.8 J 1171-21976 components nondestructive testinq, inspecting Aerodynamic sound prodnction and method of matched electron beam welds and internal strnctnral asymptotic exoansions flaws N71-22467 r ASNE PAPER 71-6T-741 A71-25988 Aerodynamic characteristics of near wakes prodnced Analrsis of solid rotors used in hiqh speed by periodic vortex sheddinq from airfoils indnction mot9rs for aerospace applications TAD-718893 J A71-23245 971-21898 AERODIBAITIC STABILITT Canadian research on aerospace sciences and Stability analysis and design optimization sith enqineerinq, qas and plasna dynamics, and dynamics and aeroelastics constraints for related topics helicopter rotor blade minimnm weisht with N71-22515 bending torsion flutter and favorable frequency AEROSPACE SCIEBCES placenents Apulication of spacecraft technaloqy to aircraft CAIAA PAPER 71-3881 A71-25352 for improvement in systems. aaterials. and Eypersonic wakes of two dimensional slender wedges oerformance and flat plate, testinq stability in transition [ NASA-TR-X-67373 3 N71-22394 region in vind tunnel AEROSPACE STSTEES 171-27561 NASA reliability program Provisions for Aerodynamically stable meteoroloqical balloon aeronautical and space system contractors, using surface roughness effect reviewing evolution process C NkSA-CASE-XRF-041631 1171-23007 A71-26667 Flaps and leading edge modifications for improved Research and development in aerospace systems aerodynamic control stability of military inclndinq desiqn and fabrication of 4-ft aircraft trisonic vind tunnel 1171-23422 N71-22331 AERODIBAIICS AEROSPACE VERICLBS Cascade and single stage rotating riq data Equation error approach to parameter comparison with aerodynamic predictions based on identification in third order pitch plane intrablade analysis, incladina wall boundary dlnamics for high performance aerodynamically layer model controlled aerospace vehicle 7 * c ,I 0 [ASBE PAPlR 71-GT-131 A71 -25959 r,I -CY- ,> High temperatnre aerodynamics with electromagnetic AEROTEERBODIIABICS radiation, considerinq thermally radiating shock Enthalpy and wall heat €13~calculations for 1 layers, electric arc driven wind tunnels and qas staqnation reqion aft of blnnt axisymmetric dynamic lasers bodies in hypersonic axial flow 1171-27277 [ AD-7174181 N71-22087 Three dimensional incompressible flos about Combined free and forced laminar convective heat slender foil in perfect flnid, stressinq vortex transfer to nonNewtonian flnids flowing in field effect constant wall temperature vertical tnbes and A71-27477 controlling parameter analysis Keasurenent of nacroscopic aerodyeamic quaetities 1371-22702 in plasma jets produced by electrothermal and APTEBBURBIIIG I hall carrmt ?cceleratcrs Tro variations vi gas generator metnoa to mi-22639 calculate thrust of afterbnrninq turbofan AEROELASRCITT enqines installed in F-111A aircraft Uind tnnnel evalnation of analytical method for I NASA-TA-D-62971 N71-22614 predicting longitndinal stability and AILEEOIIS aerodynamic characteristics of larqe flexible Device for controlling rotary potentiometer aircraft applied to supersonic transport mounted on aircraft steerinq wheel or aileron configuration control [AIAA PAPES 71-3433 A71-25322 [ NASA-CASE-XAC-10019] N71-23839 Stability analysis and design optimization with AIR BREATEIIG EBGIIES dynamics and aeroelastics constraints for Requirements analysis of airbreathinq gas turbine helicopter rotor blade minims weight with enqines for shuttle vehicles bending torsion flutter and favorable frequency [NASA-TR-X-67806 J N71-23764 placements AIR CARGO [AIAA PAPEB 71-3881 A71-25352 Cargo airship standazd atmosphere operation modes. Aeroelastic aircraft self adiusting automatic discussing long range qas capacity and short control systems, discussing elimination of range applications for larqe compact loads elastic oscillations cansed noise from angular 171-26 309 velocity sensina circnits Support systems planning for expanded passenger A71-26718 and carqo traffic in civil aviation AEEOIIAUTICAI, EIIGIIEEUIIIS n7i-22390 IASA reliability program provisions for AIR COOLIlG aeronantical and space system contractors, Beasnrement of coolinq air pressure changes revieuing evolution process throngh stationary turbine disk and airflow A71-26667 distribution within a blade at room temperatnre Air transport propulsion systems. discussinq and pressnres from 28 to 100 psia aircraft operating economics with reference to [ NASA-TK-1-2171] 871-22680 weight. size, poverplant efficiency. noise and AIR PLOU air pollution Uake flow behind two dimensional perforated plates A71-27542 normal to air stream, measuring draq, sheddinq. SUmmarY of aeronautical research, and wind tunnels velocity and tnrbnlence at Reynolds nnmber 11-11-23931 25.00 0- 90,O 00 AIIEOIIAUTICS A71-264149 Aviation and astronantics - Conference, Tel Aviv Condenser microphones aerodynamically indnced I and Eaifa. Earch 1971 noise, investiqatinq aconstic pressure lower A7l-25145 limit dependence on air flow velocity and Socioeconomic changes in aeronautics, discussing turbulence faster long range aircraft, airport access &%I-27063 problems. technoloqical advances, short hanl Air flow velocity, altitude, fuel-air ratio, foe1 transportation and indastry/qovernment relations flow velocity, and pressure effects on fuel A71-27601 temperature before and after preraporization in Application of spacecraft technology to aircraft ramjet engines for improvement in systems. materials. and NASA-TT-P-13605 ] N71-24053

11-3 AIR NAVIGATION SUBJECT INDEX

AIR NAVIGATION circuits, electronic flight instruments, area Area naviqation facility, discussing control and naviqation and collision avoidance systemsA71-26878 display and naviqation standards 871-2687? Terrain follouinu radar for airborne quidance Of Airport qeodetic control stations, discussinq low flyinq military aircraft obstruction chartinq proqram A71-26881 A71-71537 ITRCRIPT Nonte Carlo qeneral purpose shieldinq computer Operational preparation and commissioninq of IL-62 proqram in FOPTRAN 4 for IBtl 7094 computer long distance jet aircraft, considering fliqht [ PNSI-TR-70-0301-1-VGL-1 1 N71-22379 crew and maintenance personnel traininq at Simulation, analysis, and recommendations for U.S.S.R. plant fliqht profile of Concorde aircraft to predict A71-25256 and achieve improvements in aircraft operation - AIRCRAFT ACCIDERT INVESTIGATION VOl. 2 Accident investiqations, flight control Systems, PNSI-TR-70-0301-2-VGL-21 N71-223RG and operational recordings for improved aircraft AIR POLLUTION flight mechanics Air pollutinq nitric oxide and soot production by r AGARD-CP-76-71] N71-23410 jet aircraft, discussinq mixinq process and Pattern of accident distribution for V/STOL atmospheric dispersion aircraft in United States of America [AIAA PAPER 70-1151 A71-27560 N71-23426 AIR TRAFFIC Fliqht mechanics problems in accident notion sequelitial analysis of airudys utilization, investiqdtions foL VZ-101 diLcLdfi usinq mathematical-statistical methods N71-23428 A71-27 143 Weather factors in fatal civil transport aircraft Proceedinqs and recommendations of conference on accidents sonic booms N71-23431 r IGIA- 17/4.8 1 N7 1-2 1976 AIRCRAFT ANTENNAS AIR TRAPPIC CONTROL Tests for determining spectral siqnatnres of ATC requlations considered for Concorde inteqrated high-frequency antenna systems for introduction to passenqer service. discussinq P-3 aircraft landinq and takeoif characteristics [ AD-7180541 N71-23609 A71-25232 AIRCRAFT CARRIERS Area naviqation facility, discussinq control and Shipboard test procedure of Fresnel lens optical display and naviqation standards landing system NK 6 NOD 2 for carrier landinqs A71-26879 AD-7183351 N71-23488 Airport qeodetic control stations, discussinq AIRCRAFT COFIUUNICATION obstruction chartinq proqram Airborne radio communication systems, Stressing A71-27537 electronic equipment design reliability flidair collisions analysis for civil-military A7146880 inteqrated ATC air space, discussinq near miss Uultiple access diqital communication system for volume, random headinq aircraft density and 1011flyinq aircraft with infrequent users pilots evasive action vs avoidance percentaqes N71-21855 A71-27599 Nethods for predicting speech interference uithin Aircraft safety and aircraft reliability, notinu cockpits of fixed winq and rotary winq aircraft pilot performance. landinq approach and takeoff, [AD-7180981 N71-23528 and clear air turbulence AIRCRAFT CONTROL N71-22197 Variable sweep winq aircraft anqular motion Satellite applications to aircraft communications, mathematical model, analvzinq inertial moments naviqation. and surveillance over US includinq influence on control dynamics synthesized satellite network and aircraft A71-25661 equipment for air traffic control Sailplanes tail load static derivation for NASA-CR-117760 1 N71-22339 instantaneous unchecked lonqitudinal maneuver, Location/identification transmitter and equipment considerinq aperiodic response for use in satellite applications in aircraft A71-26486 communication, naviqation, and surveillance for Sailplanes control, derivinq incremental US air traffic control aerodynamic load on horizontal tail produced by TNASA-CR-1177591 N71-22340 instantaneous elevator deflection Harket forecasts and traffic control technologies A71-26487 of Boeinq 747 aircraft and supersonic aircraft Aeroelastic aircraft self adjusting automatic operations control systems, discussing elimination ok N71-22383 elastic oscillations caused noise from angular US cooperation with ESRO UHF satellite system velocity sensing circuits development for air traffic control in Europe A71-26718 [NASA-TT-F-13651 1 N71-23967 Aircraft longitudinal coordinates invariance AIR TRANSPORTATION relative to atmospheric disturbances, giving Air and cosmic space common law, discussinq simultaneous thrust variation, rudder deflection boundaries, sovereiquty over state territories and flap deflection control rules and iurlsprudence related to travel development A71-27339 A71-26325 Accident investiqations, fliqht control Systems, European airbus, considerinq fliqht trials of and operational recordinqs for improved aircraft first A.3008 hiqh capacity transport aircraft fliqht mechanics N71-23410 A71-26921 r AGARD-CP-76-71] Air transport propulsion systems, discussinq Fliqht simulator and airframe test stand for aircraft oppratinq economics with reference to evaluatina operational performance of aircraft weiuht, size, powerplant efficiency, noise and fliqht control system air pollution N71-23413 A7 1- 2754 2 Flaps and leadinq edqe modifications for improved Turbofan STDL transpoEt application to air aerodynamic control stability of military t r a n s port a t. ion conq ~s t ion, discus s inq aircraft

conditioninq landina field lpnath.~ ~ ~~ N71-23422 naviqationdi/controi problems and' jet flap Device for controllinq rotary potentiometer concttpts mounted on aircraft steering wheel or aileron A71-27602 control Air transportation systpm and Civil Aeronautics [NASA-CASE-XAC-10019] N71-23809 Board decisions AIRCRAFT DESIGN N71-23720 tlediun weiqht NANC C-1A tactical transport AIRBORNE EOUIPUENT aircraft technical specifications Avionics qrowth, discus.sinq use of diqital A71-25231 computers, solid state transducers, inteqrated

A-4 SUBJECT IBDEX AIRCRAFT BAIRTEBARCE

Ti intermediate diaqonal tension field shear heam A71-27542 analysis and desiqn for Boeing SST. nsinq Aircraft power plants sealing materials, Rayleigh-Ritz method emphasizing porous cermet seals heat resistance [AIAA PAPER 71-3401 A71-25319 under thermal cyclic loads Automated optimal weight fully stressed large A71-27688 scale structural desiqn of aircraft, usinq AIRCBAFT EQUIPIIEBT matrix- mathematical proqramming technique Satellite applications to aircraft communications, [AIAA PAPER 71-3611 A71-25340 navigation, and surveillance over US including Prototype graphite fiber/plastic fuselage synthesized satellite network and aircraft component design. test and performance equipment for air traffic control prediction, using structural analysis methods [ NASA-CR -1177601 N71-22339 A71-25428 Location/identification transmitter and equipment Fatigue life, fail-safe capability and corrosion for use in satellite applications in aircraft resistance of commercial aircraft structures communication, navigation, and surveillance for improved throuqh adhesive metal-metal bonding us air traffic control [ASBE PAPER 71-DE-271 171-27325 [BASA-CR-117759] N71-22340 Automated lor cost structural-mechanical design AIRCRAFT FUEL STSTEBS and optimization of winq pivot systems for Polyurethane foam effects on fuel contamination variable geometry aircraft during installation for fuel system fire and [AIAA PAPER 71-4041 A71-27410 explosion protection Yinq design criteria imposed by high speed [ ASBE PAPER 71-GT-54 A71-25981 requirement for short takeoff aircraft, AIBCRAFT FUELS considering thin sweptback ring with small Aircraft fuel tank nitrogen inertinq. fire and aspect ratio for lateral control explosion suppression for foreign particle A71-27471 contamination. sludge and lacquering reduction Ti, B and qraphite fiber composites application to [ASNE PAPER 71-GT-453 A71 -25 978 aircraft design. discussing mechanical AIRCRAFT GUIDABCE properties and market competition Report on qnidauce system for approach and 1171-27676 landing. discussiuq airports. aircraft, approach Aircraft industry materials development, and landinq paths, service classes, failure discussing innovations in governmental proqrams protection and weather penetration manaqement, procurement specifications and A71-25534 Department of Defense contracting procedures Terrain following radar for airborne guidance of A71-27677 low flying military aircraft Performance test of sinsle staqe turbine with low A71-26881 solidity tandem rotor blade assembly AIRCRAFT BAZARDS NASA-CR- 18031 N7!-23?32 :afetf Prasurs io eiiminate aircraft trailing Power spectrum method for determininq gust vortex hazards frequency response functions in dynamic aircraft r NASA-TB-X-67125] N71-23418 desiqn AIRCBAFT ETDBAULIC SYSTEES E71-23211 Hydraulically powered duplex input servos for Accident investigations. fliqht control systems, flight control system of VPY-Pokker V/STOL and operational recordings for improved aircraft fighter aircraft flight mechanics A71-26884 [ AGARD-CP-76-7 1 ] N71-23410 AIRCRAFT IBSTRUEEBTS Onboard data acquisition for improved aircraft SST problems, includinq adequate instruaentation design and operational flight safety and fuel tank immunization to explosion N71-23412 a71-7G.aa3 Dpsiqn nn

A-5 AIRCRAFT MODELS SUBJECT INDEX

AIRCRAFT IIODELS Operational flight data analysis for improved nodel desiqn for Vertical takeoff aircraft cockpit aviation safety levels notinq naviqation aids, visual displays, and N71-23411 console confiquration Onboard data acqnisition for improved aircraft N71-22196 desiqn and operational flight safety AIRCRAFT IIOISE N71-23412 Two dimensional sound wave equation solution in AIRCRAFT STABILITY L,....."LTLI_I cf ti~eretarded arouments, derivinq Wind tunnel evaluation of analytical method for analytical expressions for aircraft noise predictinq longitudinai stabiiiiy and intensity and power aerodynamic characteristics of large flexible A71-25144 aircraft applied to supersonic transport Temporal and spectral stimuli combinations effects confiqnration on judqed noisiness of aircraft sounds by [AIAA PAPER 71-3431 A71-25322 colleqe students Investiqation of longitudinal and lateral A71-27531 stability and controllability of supersonic Routine unprotected exposure to acoustic noise aircraft within cockpits of trainer aircraft presentinq [AD-718285] N71-23818 potential hazardous stress Wind tunnel investiqation of static longitudinal r AD--117852 1 N71-22426 and lateral characteristics of full scale mockup AIRCRAFT PERFORMANCE of liqht twin enqine aircraft Variable geometry external fuel tanks for hiqh INASA-TN-D-62381 N71-23860 performance aircraft with draq reduction upon AIRCRAFT STRUCTURES fuel transfer Glass fiber reinforced plastics aerospace [AIAA PAPER 71-3951 871-25271 applications covering radomes, dielectric Fliqht test completed on onboard real time enqine panels, aircraft ducting, secondary structures, performance monitorinq system. discussinq furnishings, mouldinqs and toolinq thermodynamic analysis technique A71-25652 r ASNE PAPER 71-GT-77 ] A71-25901 Passenqer aircraft structures accelerated testinq .flodal characteristic pick-up system for vibration for safety and fatique durability under tests of rockets or aircraft on qround, usinq operational conditions, describinq tests, small size accelerometers with individual planninq and evaluation electronic circuit A71- 26 946 A71-27715 Naterial properties, impregnation, shapinq, Investiqation of lnnqitudinal and lateral hardening and structural desiqn in mass stability and controllability of supersonic production of reinforced laminates for aircraft aircraft construction r ~~-7182851 N71-23818 1171-26954 AIRCRAFT PRODUCTION Flame retardant silicone elastomers for use as Low cost short life qas turbine desiqn based on aircraft construction materials, describinq parametric performance and component selection. fabrication techniques, mechanical, aging and outlininq turbojet production weatherinq properties TASME PAPER 71-GT-691 A71-25984 A71-27412 Traversinq Infrared Inspection System for C-5 Aircraft structural elements thermal behavior aircraft fail-safe strap panels of bonded Ti-A1 under aerodynanic heatinq with linear dependence laminates, discussinq desiqn and application on initial temperatdre r ASME PRPER 71-DE-371 A71-27327 A71-27493 AIRCRAFT RELIABILITY Solution of problems in structural desiqn with Aircraft safety and aircraft reliability, notinq emphasis on interaction between materials, pilot performance, lacding approach and takeoff, structures, and desiqn requirements and clear air turbulence r AD-7175761 N71-22136 N71-22157 Determination of inspection intervals and nature Determinetion of inspection intervals and nature of inspections for safe and economical operation of inspections for safe and economical operation of aircraft structures of aircraft structures r FFA- 1 263 N71-22431 IFFA-1201 N71-22431 Enqineerinq desiqn analysis of hydrogen cooled AIRCRAFT SAFETY structural panels for application to hypersonic Polyurethane foam effects on fuel contamination aircraft durinq installation for fuel system fire and INASA-CB-16501 N71-22625 explosion protection Heat flux sensor adapted for mounting on aircraft rASnE PAPER 71-GT-541 171-25981 or spacecraft to measure aerodynamic heat flux SST problems, includinq adequate instrumentation inflow to aircraft skin and fuel tank immunization to explosion rNASA-CASF-XFP-O3802] N71-23085 A71-26883 Transfer functions in modellinq human pilot and Passenqer aircraft structures accelerated testins dynamic structural aircraft responses for safety and fatique durability under [ AGAFD-R-580-711 N71-23210 operationa 1 conditions, describin4 tests, Hathematical modellinq of aircraft structural planninq and evaluation response modes to active control system A71-26546 N71-23212 Ueather minimum standards €or civil aircraft, Computation and measurements of dynamic aircraft considerinq cloud ceilings, visibility, wind transfer functions to atmospheric turbulence velocity and direction, onboard and ground-based N71-23213 fliqht control equipment and aircraft Haterial specifications, flammability, safety characteristics considerations, and design criteria for A71-27141 materials used in construction of commercial Aircratt safety and aircraft reliability, notinq aircraft interiors pilot Performance, lar.dinq approach and takeoff, N71-23232 and clear air turbulfrce Abstracts of papers presented at US Air Force N71-22197 materials symposium held at Niami Beach, Florida Determination of inspection intervals and nature in nay, 1970 of inspections for safe and economical operation [ AD-7184321 N71-23625 of aircraft structures AIRCRAFT TIRES [PFA-1201 N71-22431 Aircraft tires mechanical data from small models, Proceedinqs of Air Line Pilots Association annual discussinq mechanical properties, tire stresses safety forum and tire temperatures N71-23234 rAIAA PAPER 71-3461 A71-25325 Accident investiqations, fliqht control systems, AIRCRAFT WAKES and operational recordinqs for improved aircraft Aircraft wake turbulence with downwash loadinq of fliqht mechanics winq span [ AGARD-CP-76-7 11 N71-234 10 [ AD-7180243 N71-23660

A-6 SUBJECT IADEI ALKALIES

AIRPOIL PROPILES 1171-26671 Sound radiation and wake turbulence spectra from Subsonic and supersonic airline operations, axial compressor single airfoils, including restraints, considering noise, air pollution and double circular arc profiles inadequate airport facilities [ASUE PAPER 71-GT-41 A71-25950 1171-26870 Transonic airfoil testinq techniques in two soviet airlines operations planning, aiscussinq dimensional flow. discussing wind tunnel principal objectives, methodology and conditions at various Reynolds numbers organizational principles 171-27467 A71-27144 AIRFOILS Analysis and statistics of airports, air carrier Resin matrix composite airfoils in qas turbine fleet operation, aircraft production. and status engines. considerinq performance, fabrication of civilian pilot personnel for September. 1970 and cost 171-21977 [ASRE PAPER 71-64-473 171-25980 Analysis of Boeinq 727 aircraft impact on Approximation of flou around jet flapped airfoil, environment, passenger processing, passenqer discussing ground effect on lift coefficient boarding trends, an8 scheduled and total increments operation trends A71-26314 N71-21978 Hele-Shaw flou viscous tails from airfoil, Simnlation. analysis, and recommendations for observinq high Reynolds number trailinq edqe fligbt profile of Concorde aircraft to predict flow for separation and initiation of Kutta and achieve improvements in aircraft operation - condition VOl. 2 A71-26447 [PNSI-TR-7C-O301-2-VOL-2] 1171-22380 Airfoils unsteady stall by testing two dimensional Planning for expected civil aviation developments model in harmonic pitching oscillation for caused by change-over to Boeinq 747 aircraft and helicopter rotor blades characteristics supersonic transport A71-27609 871-22381 Application of inteqral relations to inviscid Planning for civil aviation operations including supercritical flow over symmetric airfoils at Boeing 747 aircraft and supersonic aircraft zero angle of attack N71-22382 [AD-7173391 N71-22098 Market forecasts and traffic control technologies Graphical computer simulation of incompressible of Boeinq 747 aircraft and supersonic aircraft flow about airfoil operations [TN-71-21 N7 1- 22 149 N71-22383 neasurement of force and pressure fluctuations on Econonics and operational planning for future airfoils during transverse and streamwise gust civil air transportation flows N71-22384 [CUED/A-TURBO/TR-21] N71-22374 Civilian airline operations with Boeing 747 Procedares for predicting properties of transonic aircrafts and supersonic aircraft flows about thin airfoils and slender bodies N71-22385 [ NASA-CR-1722 J N71-23133 Planning for Eoeinq 747 aircraft integration into Fatigue test equipment for evaluating Focker Israel airline operations aircraft wing N71-22388 [ NLB-TB-70008-L] N71-23157 Support systems planning for expacaad passenger Aerodynamic characteristics of near wakes produced and cargo traffic in civil aviation by periodic vortex sheddinq from airfoils N71-22390 [AD-718893) N71-23245 Inteqrated systems approach for der-lopinr: AIRFBALIE LIATBBIaLS rquiresects of increased civil aviation in Soln+ion of prsbless in structural design with Israel emphasis on interaction between materials, N71-22391 structures, and desiqn requirements Proceedings of Air Line Pilots Association annual [AD-7175761 N71-22136 safety forum Effect of heat conduction of material on N71-23234 temperature distribution in vicinity of winq AIRPORT PLAAAIIIG leading edqe in hypersonic flight Planuinq for expected civil aviation developments r REPT-69011 N71-22494 caused by change-over to Boeing 747 aircraft and AIRPEALIES supersonic transport 8ilitary aircraft flight test establishments, N71-22381 discussinq airframe, engine. fliqbt control and Planning parameters for high capacity weapons delivery systems tests work flow international airport system inteqration requirements N71-22389 A71-26315 AIRPORTS Koiter method for asymptotic analysis of Airport geodetic control stations, discussinq postbucklinq behavior reformulated in finite obstruction charting program element notation A71-27537 [AD-7177401 171-22485 Ten year forecast for eight major traffic AIIBLIIIE OPEBATIOIIS categories at Pashington National and Dulles Operational preparation and commissioning of IL-62 International airports for period 1971 throuqh lonq distance jet aircraft, considering flight 1982 crew and maintenance personnel training at N71-21979 U.S.S.R. plant Development and description of basic aescriptors A71-25256 used to analyze jet engine noise, aircraft TU-154 responsibilities of three-man crews, noise, and noise level of airports considerinq flight plan. refuelinq. carqo N71-21980 loadinq and unloading Tables and maps of selected landing airfields for A71-25258 shuttle orbiters with various crossranges Plight and operation of IL-62 lonq distance jet [ NASA-TU-X-67080] N7 1- 2 1996 aircraft, consideriuq fliqht crew composition AIRSEIPS and training, passenger and cargo handling and Carqo airship standard atmosphere operation nodes. ref aeling discussing lonq ranqe qas capacity and short A71-25260 range applications for lame compact loads Jet aircraft airworthiness standards, discussing A71-26309 airline fleet maintenance resources, inspection AIRSPACE systems and future requirements notion sequential analysis of airways utilization, A71-26308 using mathematical-statistical methods Pan American reliability program effect on airline .A 7 1- 27 14 3 maintenance. considering cost effectiveness, ALKALIES aircraft performance. data collection and Finite difference method for calculating sonic analysis boom overpressure siqnatures in vicinity of

a-7 ALL-WEATHER AIR NAVIGATION SUBJECT INDEX

caustics A71-25534 [ AD-7188351 N71-23738 Aircraft approach and landing under low altitude ALL-WEATHER AIR NAVIGATION wind shear conditions, discussinq flying hazards Technical aspects of tactical all-weather and qlide path correction procedures instrument landing system of Swedish STOL A71-26364 aircraft Saab 37 Viqqen Speed and field lenqth safety factors for approach A71-25233 and lardinq mechanics of Breguet aircraft ALTIBETERS N71-23420 nodulation cancellatiox altimeter error analysis Airborne equipmeiii :or zppr9ach path control on and performance optimization reduced noise trajectories in Boeinq transport A71-27437 aircraft traffic ALTITUDE N71-23425 Combined optical attitude and altitude indicatinq APPROACH INDICATORS instrument for use in aircraft or spacecraft Index of standard instrument approach procedures r NASA-CASE-XLA-01907 1 871-23268 for domestic and foreign airports ALTITUDE TESTS N71-23233 Stokes flow parachute extremely liqhtweiqht Automatic approach and landinq system with flash decelerator for increasinq altitude and rocket- varninq siqnal for caravelle aircraft control borne radiosondes atmosoheric data samplinq N71-23429 quality APPROXIBATION [AIAA PAPER 71-4011 A71-25277 Approximation of flow around jet flapped airfoil, ALUBINUB discussinq qround effect on lift coefficient Desiqn and fabrication of RorSiC aluminum incrcmcnts composite fan blades for supersonic turbofan 471-263 14 enqines, considerinq 430 F application without Asymptotic solution of low frequency winq severe vibratory stress oscillations in transonic shockless adiabatic ASRE PAPER 71-GT-90 1 A71-25997 inviscid qas flow based on complete ALUBINUB ALLOYS approximation El-evated temperature effects on fatique life of N71-23193 tensile stressed titanium alloys, aluminum ARGON alloys, and stainless steels Aerodynamic performance of sweptback-bladed NASA-TN-D-61451 N71-22076 centrifuqal compressor in argon as function of Comparison between silicon-maqnesium-aluminum equivalent weight flow N71-23659 alloy and copper aircraft electric conductors NASA-TE-X-22691 and terminals notinq types of tests ARITEBETIC AND LOGIC UNITS r TfiC-BR-19785 1 N71-23547 Analoq recursive computer with serial digital ANALOG COBPUTERS proqram for arithmetic unit and storage system Analoq recursive computer with serial diqital control proqram for arithmetic unit and storaqe system A71-27150 control ARROW WINGS A71-27150 Predictinq aerodynamic characteristics of arrow, ANEBORETERS delta, and diamond winq platforms using Anemometer with brakinq mechanism to prevent Prdudtl-Glauert transformation rotation of wind driven elements [ NASA-TN-D-62431 N71-21973 [NASA-CASE-XMF-O5224] N71-23726 ASPECT RATIO ANGLE OF ATTACK blinq desiqn criteria imposed by hiqh speed T tail flutter analysis, considerinq dihedral, requirement for short takeoff aircraft, anqle of attack and aerodynamic force effects considerinq thin sweptback winq with small A71-25188 aspect ratio for lateral control Liftinq surfaces supersonic-hypersonic flutter at A71-27471 anqle of attack determined by shock expansion, ASTRONAUTICS Newtoniar, flov and local flow piston theory Aviation and astronautics - Conference. Tel Aviv [AIAA PAPER 71-3271 A71-25307 and Haifa, !larch 1971 A71-25145 Unsteady flow measurement around winq sections durinq rapid anqle of attack variations, ASYIIPTOTIC BETHODS emphasizinq helicopter rotor blades Time asymptotic solutions for hypervelocity blunt A71-27468 body flow field with coupled nonqray radiation, Accelerated supersonic motion of plane at finite treating shock as discrete surface anqle of attack [AIAA PAPER 70-865) A71-25453 [ NASA-TT-F-135251 N71-23278 Three dimensional jet flapped winq matche'a ANGULAR DISTRIBUTION asymptotic expansion solution for hiqh aspect Flow variation effect on velocity and flow anqle ratios based on thin airfoil theory assuminq distribution at exit of shrouded radial flow inviscid and incompressible flow impeller with backward swept blades, usinq A71-27217 streamline curvature method Aerodynamic sound production and method of matched rASME PAPER 71-GT-153 A71-25961 asymptotic expansions ANTENNAS N71-22467 Analysis of inteqrated hiqh frequency antenna Asymptotic solution of low frequency winq system for P-3c aircraft radio communications oscillations in transonic shockless adiabatic [AD-7181671 N71-23306 inviscid qas flow based on complete ANTIFRICTION BEARINGS approximation Rotor-bedrinq system analysis to determine cause N71-23193 of brint.llinq failure of benrinqs from vibrat.ion ATBOSPHERIC CIRCULATION tt,-.ted PLY fans Nonexpandinq reflectinq balloon for radar NASA-CR-117855 1 N71-22527 measurement of stratospheric circulat.ion APPROACA [NLL-R-20326-/5828.4F/I N71-23934 Computer qraphics display proqram for use in ATBOSPEERIC COIPOSITION tvrminal opvrdtions and V/STOL approach and Transtormation in air components due to marked dFpdrturv path synthesis increase in temperature durinq reentry shock NASA-CR-1178H7 1 N71-23186 wave APPROACH CONTROL N71-22640 wind qrndicint effect on fliqht characteristics ATBOSPHERIC DKNSITY durinq aircraft. landinq approach, particularly Parachutes for low density atmospheres, describinq path deviation low and hiqh altitude test results A71-25194 [AIAA PAPER 70-116(11 A71-25525 Report on quidance system for approach and ATIOSPHERIC DIFFUSION landinq, discussinq airports, aircraft, approach Air polluting nitric oxide and soot production by and landinq paths, service classes, failure jet aircraft, discussinq mixinq process and protect ion and wpa thsr penrtra tion atmospheric dispersion

A-8 SUBJECT INDEX BEES

[AIAA PAPER 70-1153 A71-27560 Effects of wave inlet distortion at hiqh and low ATBOSPUERIC TURBULENCE flow rate on performance of axial flow Validity range of response prediction methods for compressor large flexible aircraft to continuous [ CUED/A-TURBO/TR-20 3 1171-22428 atmospheric turbulence, discussing power AXIAL PLOW TURBIEES spectral densities and fatigue life Soviet book on theory of aircraft bladed uachines [AIAA PAPER 71-3421 1171-25321 covering axial flow, centrifugal and composite Aircraft longitudinal coordinates invariance turbines and compressors, thermodynamic relative to atmospheric disturbances, qivinq eff iciency, control turbocompressor matchinq, simultaneous thrust variation, rudder deflection etc and flap deflection control rules 171-26401 671-27339 Quasi-axisynmetric and superposed fine fluctuating Coaputation and measurements of dynamic aircraft structure of ideal incompressible vortex flovs transfer functions to atmospheric turbulence in axial flow turbines, assuuinq infinite mutual N71-23213 blade proximity ATTITUDE IUDXCAMBS A71-277 14 Combined optical attitnde and altitude indicating nonlinear limit rotation velocity and circulation instrument for use in aircraft or spacecraft induced by wheel in axial flow turbomachine for [NASA-CASE-XLA-01907] 871-23268 incompressible ideal fluid, using iterative AUDITORY STIMULI numerical algorithm Temporal and spectral stimuli conbinations effects A71-27715 on judged noisiness of aircraft sounds by Computer proqram to generate turbine aerodynamic college students reguireients, approximate external blade A71-27531 geometries, and coolant flow requirements for AURORAS two stage axial flow turbine Photometric observations of auroral scattering by NASA-TU-X-2229 1 N71-22568 CV 990 aircraft Cold-air tests to determine performance r NASA-CR-1174661 871-22135 characteristics of single-stage turbine with AUTOBATIC COETEOL stator blades employins transpiration coolant Soviet book on aircraft and rocket enqines control ejection throngh wire mesh shell automation, discnssinq nuclear power plant/fuel [NASA-TU-X-2176] N71-23980 systems design and control simulation methods AXIAL LOADS 871-26403 Couplinq characteristic effects on dynamic AUTOMATIC PLIGET COETROL response of axially coupled turborotors with Operational performance of Barker Siddeley digital computer program based on transfer aircraft automatic flight approach and landina matri I techriiqiss control system N71-22712 871-23414 AXISTIEEPBIC PLOW Operational performance of automatic V/STOL flight Steady three dimensional subsonic nonviscous flow control systens using jet thrust or air bleed through turbomachine with arbitrary hub and 871-23415 shroud shapes and finite blade number, using Ruman factors and control system failures in jet iterative blade to blade procedure upsets durinq turbnlence encounters [ISRE PAPER 71-GT-21 A71-25940 871-23424 AUTOEATIC LAUDIEG COETBOL Radio frequency interference monitoring for B instrument landinq system in automatic landing BACTERIA r RAE-TR-700761 N71-23356 --,,,taminationn-?.... of petroleum products with honey Operational oerforaerce of aawker Siddeley IWASA-CASE-XNP-038351 N71-23499 aircraft automatic flight approach and landing BALL001 FLIGHT control system Inflation of initially spherical balloon of n7 1-23414 elastic rubber-like material, discussing tensile Automatic approach and landing system with flash instability warning siqnal for Caravelle aircraft control A71-25445 N71-23429 BALL008 SOUNDIUG AUTOBOBILE EEGIUES Nonexpandinq reflecting balloon for radar Technoloqy review on electric automobiles, and measurement of stratospheric circulation modified T-33 aircraft system for pyrotechnic rNLL-R-20326-/5828.4F/] N71-23934 hail suppression seeding BALLOTES [DUE/NAE-1970/4/] N71-22 198 Expandable structures for midair pilot rescue AUTOMOBILES device with hot air filled BALLUTE, discussinq Safety standards development analysis for BALLUTE material development passenqer vehicles and aircraft [AIAA PAPER 71-4021 A71-25278 [AD-7183973 871-23333 BAROTROPIC PLOW AUXILIARY POWER SOURCES TWOphase supersonic barotropic flow with solid Helicopter auxiliary power unit /APU/ life cycle particles around thin profile with allowance for cost computation elastic particle collisions A71-26679 1171-27450 AVIONICS BASE PRESSURE Avionics growth, discussinq use of digital Pliqht-measured base pressures from sharp leading com~uters,solid state transducers. integrated edae upper vertical fin of X-15 aircraft circuits, electronic flight instruments. area compared with wind tunnel data for turbulent navigation and collision avoidance systems flow at Mach numbers from 1.5 to 5.0 A71-26878 [NASA-TB-D-63481 N71-23922 Airborne radio communication systems, stressing BEAGLE AIRCRAFT electronic equipment desiqn reliability Reaqle B125 training aircraft handling tests A71-26880 [ AAEE/963-PT-l] 171-23498 AXIAL PLOW BEAMS (RADIATIOH) Axial flow fan noise, investiqatinq louvers Gas and fluid response to high intensity ruby effects on sound field laser beam A71-26704 [ AD-7177281 N71-22593 Large axial compressor flow straighteninq stator BEAES (SIIPPORTS) blades unsteady pressure measurements with short High speed tracked air cushion vehicles dynamic response time detectors interactions with guideways, considering model A71-27469 of lumped double-sprung vehicle nasses traveling Enthalpy and wall heat flux calculations for in tandem along simply supported beams staqnation region aft of blunt axisymeetric [AIAA PAPER 71-3861 A71-25350 bodies in hypersonic axial flow BEES [ AD-717418 1 871-22087 Decontamination of petroleum products with honey

A-9 BENZENE

[ NASA-CASE-XNP-038351 N71-23499 Ninimum drag surface shape of thick liftinq delta BENZENE wing inteqrated with conical fuselage for Benzene evaporation rate determined from flat supersonic cruising speed plate film boilinq under hiqh temperature air flow with application to qas turbine air wind tunnel investigation of hypersonic transportA71-27716 I pollution reduction model aerodynamic characteristics at Nach [ DLR-FB-70-581 N71-22072 numbers to 6 - qraphs BLADE TIPS [NASA-TN-D-6191] N71-23127 narqinal vortex effects on aerodynamics of Hind tunnel study of augmented ram-wing vehicle helicopter liftinq surfaces, considerinq blade with various blowinq arrangr.ente form and noise spectrum tested in hydrodynamic [ PB-1894251 N71-23283 tunnel BOEIRG AIRCRAFT A71-27473 -. BLOODOON OIND TUUUELS reduced noise trajectories in Boeinq transport Flow control system desiqn for blowdown wind aircraft traffic tunnels and disturbance effects on regulatinq N71-23425 accuracy BOEING 2707 AIRCRAFT [ NAL-TN-22 1 N71-22476 Ti intermediate diagonal tension field shear beam BLOOING analysis and desiqn for Boeinq SST, usinq optimal blowinq wall jet prediction for Rayleiqh-Ritz method 871-25319 suppressinq separation from hiqh lift aerofoils [AIAA PAPER 71-3403 with incomplete nixing of upstream boundary BOEIUG 727 AIUCRAFT layer Analysis of Boeinq 727 aircraft impact on A71-26196 environment, passenger processinq, passenger Wind tunnel study of auqmented ram-wing vehicle boardinq trends, and scheduled and total with various blowinq arranqements operation trends [ PB-189425 1 N71-23283 N7 1-2 1978 Laminar boundary laver on winq and body of BOEING 747 AIRCRAFT . revolution in-presence of blowinq Planning for expected civil aviation developments TNASA-TT-F-136271 N71-23796 caused by chanqe-over to Boeing 747 aircraft and BLUFF' BODIES supersonic transport Compressibility correction for subsonic flows past N71-22381 bluff bodies, considerinq boundary distortion Planninq for civil aviation operations including and pressure distribution shift Boeinq 747 aircraft and supersonic aircraftN71-22382 A71-25149 BLUNT BODIES Narket forecasts and traffic control technologies Aerodynamic forces and hinqe moments of delta of Boeinq 747 aircraft and supersonic aircraft cruciform control surface in blunt-nosed canard operations coufiquration for subsonic, transonic and N71-22383 supersonic flows Civilian airline operations with Boeinq 747 A71-25161 aircrafts and supersonic aircraft N71-22385 Time asymptotic solutions for hypervelocity blunt body flow field with coupled nonqray radiation, Fliqht tests of Boeing 747 aircraft and treatinq shock as discrete surface operational analysis for supersonic transportN71-22386 [AIAA PAPER 70-8653 1171-25453 Emmons spot theory extension for boundary layer Planninq for Boeinq 747 aircraft inteqration into flow on blunt bodies, deducinq spot formation Israel airline operations rate dependence on transition Reynolds and nach N71-22388 numbers BOLTZIIAUN TRANSPORT EQUATION A71-27557 Three dimensional turbulent boundary layer Enthalpy and wall heat flux calculations for calculations, usinq two dimensional method based staqnation reqion aft of blunt axisymmetric on turbulent enerqy equation empirical bodies in hypersonic axial flow conversion into shear stress transport equation [AD-7174181 N71-22087 171-26443 Nose bluntness effect on aerodynamic BOOSTER ROCKET EUGINES characteristics of flared body in supersonic Low subsonic lonqitudinal aerodynamic wind tunnel characteristics of twin body space shuttle I NAL-TR-2211 N71-22160 booster confiquration usinq low turbulence Separated flow over flat plate with blunted fin at pressure tunnel - qraphs N71-23135 zero anqle of attack [ NASA-Tn-X-21621 l AD-7177171 N71-22300 BORON BODI~S OF REVOLUTION Boron and qraphite fiber market competition, Aerodynamic characteristics of slender body of considerinq aerospace application revolution traveling in lonq tube with circular A71-25400 CKOSS section, derivinq static and dynamic Boron-epoxy structural skius desiqn €or P-14 stability derivatives formulas honeycomb horizontal stabilizer, usinq computer A71-25477 proqrai Flow field model for steady asymmetric vortex A71-25820 system shed from slender body of revolution in Ti, B and qraphite fiber composites application to coninq motion aircraft desiqn, discussing mechanical [AIAA PAPEH 70-521 A71-27552 properties and market competition Neasurements of sonic boom pressure distribution A71-27676 of bodies of revolution at nach 2.96, 3.83. and BOURDARY LATER CONTROL 4.63 in Unitary Plan wind tunnel Operational performance and handling safety [NASA-TN-D-61951 N71-21961 requirements for sinqle enqine boundary layer Supersonic combustion, fuel injection, and controlled aircraft in STOL mode recirculation in hydroqen hypersonic external N71-23419 combustion at flat plates and bodies of BOOUDARY LAYER PLOW revolution Flat plate trailinq edge problem solution [DLR-FB-70-641 N71-22129 consistent with second Order boundary layer Laminar boundary layer on wins and body of theory, establishing laminar wake evolution revolutiou in presence of blowinq nature and upstream influence [NASA-TT-F-13627) N71-23796 A71-25469 BODY-UIUG ARD TAIL CONPIGORATIOUS Interaction theory for supersonic separated and Winq-fuselaqe-tail interactinq low speed flutter, reattachinq turbulent boundary layers, ConpaKing considerinq mechanical tuninq and aerodynanic to real flow past compression ramp interference couplinqs [AIAA PAPER 71-1281 A71-25476 [AIAA PAPER 71-3261 A71-25306 Prandtl first order boundary layer equations for two dimensional laminar incompressible flow past

A-10 SUBJECT IIDEI CEITRIPUGAL COIIPBESSORS

circulation controlled circular lifting rotor BBEGUET AIRCRAFT A7 1-25494 Speed and field length safety factors for approach Three dimensional boundary layer flow and velocity and landing mechanics of Breguet aircraft profiles in mixed diffuser with equal anqle 171-23420 walls BUCKLI.6 FASBE PAPER 71-GT-40 J 871-25973 Cylindrical shells panel flutter analysis €or Hele-Shaw flow viscous tails from airfoil, internal stress and supersonic flow. considerinq observing hiqh 2eynolds number trailinq edqe still air buckling data useful for determininq flow for seDaration and initiation of Kutta buckling loads condition (AIAA PAPER 71-3281 171-25308 A71-26447 Emmons spot theory extension for boundary layer flow on blunt bodies, dedncing spot formation C rate dependence on transition Reynolds and Each C-130 AIRCRAFT numbers Fliqht service effects 'on residnal tensile A71-27557 DroDerties.. of C-130 aircraft center wina_. Dlate Equilibrium air bonndary layer flows at three section dimensional stagnation points, discossinq flow [NASA-CR-l11828] N71-24021 characteristics and real gas heat transfer C-141 AIRCRAFT parameters Identification and control of aeromedical factors [AIAA PAPER 70-8091 A71-27582 associated with aircraft noise and acoustic Surface flow photovisualization of straight wing measurements during C-141 operational missions orbiter and swept delta wing orbiter CAD-7160971 N71-23748 confiqnrations at Each 10.4 and several Reynolds CAM ABD COIFIGUB~TIOIIS numbers Aerodynamic forces and hinge moments of delta [ NASA-TI-1-6 20 3 3 ] N71-24001 cruciform control surface in blunt-nosed canard BOUUDART LAYEE SEPARATIOII configuration for subsonic. transonic and Optimal blowing wall jet prediction for supersonic flows suppressinq separation from hiqh lift aerofoils A71-25161 with incomplete mixinq of upstream boundary CARBOHYDBATES layer Decontamination of petroleum products with honey A71-26196 [NASA-CASE-XNP-03835] N71-23499 Laminar boundary layer equations for rotatinq CABBOI FIBERS plate with surface of arbitrary cnrrilinear Boron and qraphite fiber market competition, shape, determining external flow pressure considering aerospace application qradient leading to separation A71-25400 17:-27505 CARIBBEAI SEA Ryper5Jnic cruise vehicles viscons interactions Tabulation of B-57 aerial cloud photography of areas, examining compression corners, shock tropical convection systems for 11 to 28 July interactions, laminar and turbulent flow, 1969 with fliqht path over Barbados Islands boundary layer separation, etc [ESSA-TB-E8LTB-BOBAP-l] 871-23746 [AIAA PAPER 70-7811 A71-27551 CASCADE FLOW Boundary laver separation in viscous flow around Eigh subsonic flow two dimensional tnrbine cascade riqid bodies desiqn by approximate hodograph method, notinq [AD-7177721 N71-22241 pressure distribution measurements BOUIDABT LATER STABILITY ( ASBE PAPER 71-GT-34 J A71-25971 Laminar boundary layer perturbation by sinusoidal Time dependent asymptotic solution fr)r transonic vall roughness, analyzing effect on transitioq flows ia lryperboiic nozzle and tnrbins cascades nature and Dosition with oblique shock A71-27470 [ASBE PAPES 71-GT-421 A71-25975 BOOIDART LATER TBAISITIOI Supersonic turbine design. presentinq performance Laminar bonndarv laver Derturbation bv sinusoidal data for film cooled blunt leadinq edqe rotor wall ronqhness, analpiing effect on- transition blades measured in two dimensional cascade nature and position experiments A71-27470 [ ASBE PAPER 71-61-76] A71-25990 Supersonic boundary layer transition on adiabatic Torbomachine blade cascades in supersonic flov. wall, discussing wind tunnel size, surface notinq wave configurations, entropy and counter rouqhness and freestream disturbances effects pressure variations [AIAA PAPER 70-5861 A71-27554 1171-27475 Laminar boundary layer transition, separation and CASCADE VIID TUIIIELS streamline direction on rotating helicopter Glass fiber rotor blades desiqn with longitudinal blades pressure tappings for cascade wind tunnel and r IASA-TN-D-63211 871-23779 turbomachinery flow research applications BOOIDART LAYERS A71-26316 Bomentum thickness of boundary layer of circular Schlieren visualization for supersonic annular cylinder in cross flow at high Reynolds numbers fixed cascade and freon compressor wind tnnnels. from static pressure and skin friction using vane holding cylinder- devices measurements A71-277 17 A71-27736 CASCADES BOUIDABT TALOE PROBLEIIS Cascade and single stage rotating rig data Thin delta wins in hypersonic inviscid flow at comparison with aerodynamic predictions based on small anqles of attack, calculating motion intrablade analysis, includinq wali bonndary equations and boundary conditions at small layer model perturbations [ASBE PAPER 71-GT-131 A71-25959 1171-27330 CATHODE RAY TOBBS Asymptotic solution of low frequency wing Feasibility of ntilizinq color cathode ray tubes oscillations in transonic shockless adiabatic for airckaft crew station displays inviscid gas flow based on complete CAD-7176551 N71-22174 approximation CEILIkS (IIETEOEOLO6Y) 871-23193 Development and evaluation of dual baseline BRAKBS (FOB ARBESTIIIG IIOTIOI) transmissometer used to measure and record Design, fabrication and static testing of attached visibilities in ranqe of nine to fifty inflatable decelerator models for supersonic kilometers wind tunnel evaluation rn~s-103391 N7s-22455 [NASA-CR-111831] N71-22538 CEETRIFOEAL COUPRESSOBS BRAKIBG Reynolds number effects on centrifuqal compressor Anemometer with braking mechanism to prevent performance characteristics, discussing power rotation of uind driven elements losses in compressor, impeller and diffuser [NASA-CASE-XBP-O5224] N71-23726 stages and compressor adiabatic efficiency

A-11 CERHETS SUBJECT INDEX

AsXr PAPlR 71-GT-251 A71-25967 Economics and operational planninq for future Soviet book on theory of aircraft bladed machines civil air transportation coverinq axial flow, centrifuqal and composite N71-22384 turbines and compressors, thermodynamic Civilian airline operations with Boeinq 747 efficiency, control turbocompressor matching, aircrafts and supersonic aircraft etc N71-22385 871-26401 Planninq parameters for hiqh capacity Theory, calculation, ail2 iesig?. ~lfcentrifuqal international airport system compressor machines N71-22389 TAD-717878 1 N71-23297 Inteqrated systems approach for developinq Aerodynamic performance of sweptback-bladed requirements of increased civil aviation in centrifuqal compressor in arqon as function of Israel equivalent weiqht flow N71-22391 [NASA-TM-X-2269 3 N71-23659 Ueather factors in fatal civil transport aircraft CERHETS accidents Aircraft power plants sealinq materials, N71-23431 emphasizinq porous cermet seals heat resistance Air transportation system and Civil leronautics under thermal cyclic loads Board decisions A71-27688 N71-23720 CHANNEL FLOW CLASSIFYING Flow patterns within centrifuqal and mixed flow Flexible runuay surfaces classification by LCN impeller channel. examininq velocity method, calculatinq for Ilyushin aircraft distributions, blade surface pressure arid flou A71-26201 behavior CLOUD PHOTOGRAPRY [ ASME PAPER 71-GT-41 ] A71-2597U Statistical diameter size distribution of random Glass fiber rotor blades desiqn with lonqitudinal circles on plane or spheres in space from pressure tappings for cascade wind tunnel and satellite and aircraft measurements for aerial turbonachinery flow research applications and cloud photoqraphy A71-26316 A71-27100 Viscous converqe1.t-diverqent nozzle flow slender Tabulation of 6-57 aerial cloud photography of channel approximation, discussinq nozzle tropical convection systems for 11 to 28 July qeometry, Reynolds number and wall temperat.ure 1969 with fliqht path over Barbados Islands effects [ ESSA-Tfl-ERLTR-BORAP-1 ] N71-23746 [AIAA PAPdR 69-6541 A71-27556 CLOUD SEEDING CEEBYSREV APPROXIlATION Technoloqy revieu on electric automobiles, and Nonlinear systems optimal control comput.dtiona1 modified T-33 aircraft system for pyrotechnic method, usinq Chebyshev alqorithm hail suppression scedinq A71-27592 [ DBE/NAE- 1970/4/ 1 N71-22198 CHEUICAL REACTIONS Rodified T-33 aircraft system for pyrotechnic hail Transformation in air components due to marked suppression secdinq increase in tempprature duririq rticntry shock N71-22200 wave COCKPITS N71-22640 model desiqn for vrrtical takeoff aircraft cockpit CIRCULAR CONES notinq naviqation aids, visual displays, and Steady supersonic isoenergetic flow of thermally console confiquration and calorically perfect qas past circular cones N71-22196 at zero anqle of attack, usinq dimensional Routine unprotected exposure to acoustic noise perturbation method within cockpits of trainer aircraft presentinq A71-26939 potential hazardous stress CIRCULAR CYLINDERS [ AD-7178521 N71-22426 Vortex sheddinq characteristics of circuldr Methods for predictinq speech interference within cylinders at low Reynolds numbers from cockpits of fixed winq and rotary winq aircraft experiment on tapered models wake structure [ AD-718098 J N71-23528 A71-27220 COLLISION AVOIDANCE Romentum thickness of boundary layer of circular midair collisions analysis for civil-military cylinder in cross flow at hiqh Reynolds numbers inteqrated ATC air space, djscussinq near miss from static pressure and skin friction volume, random headinq aircraft density and measurements pilots evasive action vs avoidance percentaqrts A71-27738 A71-27599 CIVIL AVIATION Radar avoidance action loqic for converqinq Ueather minimum standards for civil aircraft, aircraft sdfe passaqe, discussinq near miss and considerinq cloud ceilinqs, visibility, wind collision situations velocity and direction, onboard and qround-based A71-27600 fliqht control equipment and aircraft COLLISION RAZES characteristics Particle interaction with wedge surface in A71-27141 supersonic two phase flow, determininq incidence Soviet airlines operations planninq, discussing coordinates and collision frequency as fuuction principal objectives, methodoloqy and of initial conditions orqanizational principles A71-27665 A71-27144 COLLOCATION Evaluation of short takeoff aircraft for Collocation method predictinq oscillatory subsonic commrrcidl shuttle fliqht applications to reduce pressure distributions on interferinq parallel traffic conqestion in San Francisco, California liftinq surfaces, considerinq approach more area economical than finite element method W7 1-21 874 [AIAA PAPER 71-3291 A71-25309 Analysis and statistics of airports, air carrier COLOR TELEVISION fleet operation, aircraft production, and status Concorde economic fliqht testinq methods, of civilian pilot personnel for September, 1970 discussiua Blaanac flisht sinulator mobile cabin N71-21977 visualization and color TI terrain model Analysir. of Boeinq 727 aircraft impact on A71-27b08 environmpnt, nasspnqer processinq, passenqer Peasibilitv of utilizinq color cathode ray tubes boardinq trends, and scheduled and total for aircraft crew station displays Operation trends [ AD-717655 J N71-22174 N71-21978 COUBUSTIOR CEAUBERS Plarininq for expected civil aviation developments Gas turbine engine combustor stability dynanic caused by chanqe-over to BOeinq 747 aircraft and model, representinq premixinq and combustion super-sonic transport chambers as Helmholtz resonators for stability N71-22381 criteria derivation [ ASRE PAPER 71-GT-731 A71-25987

A-12 SUBJECT ISDEX COEPUTEB PEOGRAUS

Gas field nonuniformity as function of turbine ply design and fabrication engine combustion chamber design parameters, A71-27413 discussing hot tube circumferential holes total COUPOUID EELICOPTBES area effect Normal and compound helicopters to be used as A7 1-2750 1 short hanl aircraft in view of burden on today's Simulation of supersonic ramjet CoBbUStiOn chamber air traffic control in shock tunnel N71-22189 N71-22630 COUPBBSSIBILITY EFFBCl% COIBUSTIOI PRODUCTS Compressibility correction for subsonic flows past Air pollutinq nitric oxide and soot production by bluff bodies, considerinq boundary distortion jet aircraft, discussing mixing process and and pressure distribution shift atmospheric dispersion 1171-25149 [AIAA PAPEB 70-1151 171-27560 COIPBESSIBLB FLOW COUBUSTIO. STABILITY Loads induced on infinite aspect ratio winq by Gas turbine engine combustor stability dynamic straight infinite free vortex in subsonic model. representing premixing and combustion compressible freestream, usinq planar liftinq chambers as Eelmholtz resonators for stability surface theory criteria derivation A71-25474 [ASBE PAPER 71-GT-731 171-25987 Steady supersonic isoenergetic flow of thermally COUIEBCIAL AIBCEAPT and calorically perfect qas past circular cones Pan American reliability program effect on airline at zero angle of attack, usinq dimensional maintenance. considering cost effectiveness, perturbation method aircraft performance. data collection and A71-26939 analysis COIPBESSOB BLADES A71-26671 cascade and single staqe rotating rig data Evaluation of short takeoff aircraft for comparison with aerodynamic predictions based on commercial shuttle fliqht applications to reduce iutrablade analysis, including wall boundary traffic conqestion in san Francisco. California layer model area [ASIE PAPER 71-GT-131 A71-25959 N71-21874 Impeller blade loading vorticity on stream surface Analysis and statistics of airports, air carrier of revolution for nixed flow compressor, usinq fleet operation, aircraft production, and status annular cascade theory of civilian pilot personnel for September, 1970 [ASPIE PAPEB 71-GT-171 A71-25962 1171-21977 Quasi-three dimensional method for radial flow Baterial specifications, flammability, safety compressor blade loadings computation. considerations, and design criteria for presentin_q cxkij1s: meridional plane and blade materials used in construction nf cs==ezCial.- to blade solutions for adaptation to computer aircraft interiors [ ASnE PAPEB 71-GT-601 171-25982 R71-23232 Larqe axial compressor flov straightening stator Safety standards development analysis for blades unsteady pressure measurements'with short passenqer vehicles and aircraft response time detectors r 110-718397') 871-23333 A71-27469 Air transportation system and Civil Aeronautics Additional slot and flow fence effects on Board decisions aerodynamic characteristics of sinqle stage 1171-23720 compressor blading COUPLE1 SYSTBUS [ NASA-CR-72635) N71-21995 Complex real time hybrid computer simulator for COUPBESSOB EPFICIBBCY captive two blade rotor platform dynamic problem 156ditioi;al slot and flow fence effects on solvinq aerodynamic characteristics of single stage A7 1- 258 47 compressor blading COIPOSITE IATEBIALS INASA-CR-726353 871-21995 Representative Thornel fiber aircraft fuselaqe COIPBESSOB BOTOBS component nondestructive testinq and repair, and Loads on compressor, ventilator and turbine rotor Thornel fiber, polysulfone and polyamide-imide disks having large central holes, giving composites fabrication and evaluation formulas for stress distributions A71-25427 A71-26952 Prototype graphite fiber/plastic fuselaqe COIPBESSOBS comporent desiqn, test and performance Isentropic-compression tube techniques producing Prediction. using structural analysis aethods hypersonic flow in wind tunnels including A7 1-25428 isentropic flow and free-piston shock tube modes Resin matrix composite airfoils in gas turbine IAD-7 17727I N71-22158 enqines. considerinq performance, fabrication conPoma GBAPBICS and cost Computer graphics display program for use in [ASME PAPER 71-61-47) 1171-25980 terminal operations and V/STOL approach and Boron-qlass-epoxy lightweight composite qear case departure path synthesis for aircraft engine reduction qearbox, INASA-CR-~~~~~~] N71-23186 describing design, molding, machining and COUPUTER PBOGBAUS testinq Analog recursive computer with serial digital [ ASnE PAPEB 71-GT-851 A71-25993 proqram for arithmetic unit and storaqe systea Air Force development programs with graphite control reinforced composites, discussing matrix A71-27150 materials and cost and weight savings Computer program for aerodynamic forces on [ASBE PAPER 71-DB-13] 871- 27 323 flexible plate undergoing trausient motion in Ti. B and graphite fiber composites application to shear flow, applying to panel flutter aircraft desiqn, discussing mechanical A71-27559 properties and market competition Examining solutions obtained from streamline A71-27676 curvature method of calculating flow through naterial specifications, flammability. safety turbomachines for several operating points of considerations, and design criteria for Rolls-Royce compressor materials used in construction of conmercial [COED/A-TURBO/TR-19] N71-22294 aircraft interiors Computer program to generate turbine aerodynamic N71-23232 requirements, approximate external blade Abstracts of papers presented at US Air Force qeometries, and coolant flow requirements for materials symposium held at niami Beach, Florida two stage axial flow turbine in nay, 1970 [ NASA-TM-X-22291 171-22568 [ AD-7184321 A71-23625 Couplinq characteristic effects on dynamic COIPOSITE STRUCTURES response of axially coupled turborotors with Graphite-epoxy composite skins for commercial digital computer program based on transfer aircraft flight spoiler, discussinq multiangle matrix techniques

A-13 COBPOTER STORAGE DEVICES SUBJECT INDEX I

N71-22712 Conference on hiqh temperature turbines detailinq COBOUTER STORAGE DEVICES effect of film cooling on blade profile loss Adaptive self-orqanizinq and -1earninq control [ NASA-TU-X-67123 ] N71-22699 systems with lonq and short term memory Proceedings of Air Line Pilots Association annual retention, usinq loqic random searches to find safety forum parameter values N71-23234 iilsiiz PAPEP 71-DP-223 A71-27324 Abstract5 of papers presented at Os Air Force COlPUTER TECRNIQOES materials symposium held at Uiami Beach, Florida Twin spool turbojet engine dynamic response, in nay, 1970 discussinq simulator predictions, diqital [AD-718432] N71-23625 computer control, nozzle area variations and CONICAL BODIES operatinq trajectories Numerical analysis of inviscid flow fields about [ ASUE PAPER 71-GT-14 J A71-25960 pointed circular cone and conical wing-body COHPOTERIZED DESIGN confiquration at various angles of attack Automated optimal weight fully stressed large N71-22667 scale structural desiqn of aircraft, usinq windaqe tests of cylindrical and Lundell-conical matrix- mathematical proqramminq technique rotors in ambient air producinq Reynolds numbers IAIAA PAPER 71-3611 1171-25340 up to 100,000 for high speed alternators six deqree of freedom hybrid diqital computer INASA-Tn-X-67809 ] N71-23116 proqram for complex fliqht control and CONICAL PLOP associated mode logic design and traininq Magnetically suspended laminar supersonic cone A71-25852 wake stability from hot wire fluctuation and Automated low cost structural-mechanical design spectral components amplitnde/phase measurements and optimization of wing pivot systems for 1171-25475 variable qeometry aircraft CONSTROCTION BATERIALS IAIAA PAPER 71-4041 A71-27410 Glass fiber reinforced plastics aerospace Computer program to generate turbine aerodynamic applications covering radomes, dielectric requirements, approximate external blade panels, aircraft ductinq, secondary structures, qeometries,’and coolant flow requirements for furnishings, mouldinqs and toolinq two staqe axial flow turbine A71-25652 [ NASA-Ti-X-22291 N71-22568 Concorde aircraft construction methods, materials COBPOTERIZED SIBULATION and design Complex real time hybrid computer simulator for A71-26882 captive two blade rotor platform dynamic problem Baterial properties, impregnation, shapinq, solvi nq hardeninq and structural design in mass 171-25847 production of reinforced laminates for aircraft Graphical computer simulation of incompressible construction flow about airfoil A71-26954 ITN-71-21 N71-22149 Flame retardant silicone elastomers for use as CONCORDE AIRCRAFT aircraft construction materials, describing ATC requlations considered for Concorde fabrication techniques, mechanical, aqing and introduction to passenqer service, discussinq weatherinq properties landinq and takeoff characteristics A71-274 12 A71-25232 Aircraft industry materials development, Concorde aircraft construction methods, materials discussing innovations in qovernmental programs and desiqn manaqement, procurement specifications and A71-26882 Department of Defense contracting procedures Concorde economic flight testinq methods, A71-27677 discussing Rlaqnac fliqht simulator mobile cabin COUTROL DATA (COEOOTERS) visualization and color TV terrain model Analoq recursive computer with serial diqital A71-27608 proqram for arithmetic unit and storage system Uonte Carlo qeneral purpose shielding computer control proqram in FORTRAN 4 for IBB 7094 computer 1171-27150 IPNSI-TR-70-0301-1-VOL-l] N71-22379 CONTROL EQUIPBENT Simulation, analysis, and recommendations for Numerical analysis of dynamic and thermodynamic fliqht profile of Concorde aircraft to predict state of plenum-type air-cushion vehicle to and achieve improvements in aircraft operation - determine heave response and control system VOl. 2 operatinq characteristics I PNSI-TR-70-0301-2-VOL-2 1 N71-22380 INASA-TN-D-62571 N71-22589 Fliqht tests of Concorde prototypes, desiqn Device for controllinq rotary potentiometer modifications, and operational costs of mounted on aircraft steering wheel or aileron supersonic aircraft control N71-22387 [NASA-CASE-xAC-l00191 N71-23809 CONDUCTIVE HEAT TRANSFER CONTROL SIIIULATION Effect of heat conduction of material on Soviet book on aircraft and rocket enqines control temperature distribution in vicinity of winq automation, discussing nuclear power plant/fnel leadinq edoe in hVDerSOniC flight systems desiqn and control simulation methods IRFPT-6901 1 N71-22494 A7 1-26403 CONFERENCES CONTROL STABILITY Aviation and astronautics - Conference, Tel Aviv Variable sweep winq aircraft angular motion and Haifa, Uarch 1971 mathematical model, analyzinq inertial moments A71-25145 influence on control dynamics Adaptive Svstems - Conference, loscow, larch 1970 A71-25661 A7 1-267 14 COUTROL SORPACES Proceedinas and recommendations of conference on Aerodynamic forces and hinqe moments of delta sonic booms cruciform control surface in blunt-nosed canard IIGIA-17/4.8 1 N71-21976 confiquration for subsonic, transonic and Conference proceedinqs on vertical takeoff supersonic flows aircraft technology, notinq tandem winq A71-25161 aircraft. tilt winq aircraft, helicopters, lift Flutter suppression with dissipated enerqy reduced fans, and jet enqines to quadratic form for control surfaces r DLR-UITT-70-15 1 N7 1-22 186 INASA-TN-D-61991 N71-23091 Planninq for expected civil aviation developments CONVECTIVE AEAT TBANSPER caused by chanqe-over to Boeinq 747 aircraft and Combined free and forced laminar convective heat supersonic transport transfer to nonNewtonian fluids flOWinq in N71-22381 constant wall temperature vertical tubes and conference on propulsion and energetics techniques controllinq parameter analysis for diaqnosinq hiqh velocity flows 871-22702 [ AGARD-CP-38 1 N71-22626

A-1U SUBJECT IIDEI DECELERATIOI

COIVEB6EIT-DIIEBGEIT IOZZLES vibrational and gliding friction Viscous flow in supersonic de Lava1 nozzle, A71-27662 measurinq qas density and rotational CROSS PLOY temperatures by electron beam techniques Nomentum thickness of boundary layer of circular rAIAA PAPBR 70-8101 A71-27555 cylinder in cross flow at high Reynolds numbers Viscous convergent-diverqent nozzle flov slender from static pressure and skin friction channel approximation. discussing nozzle measurements geometry, Reynolds number and wall temperature 171-27738 effects Interference phenomenon of subsonic turbulent jet rAIAA PAPEB 69-6541 871-27556 exhausts fror flat plate in low speed cross flow CORBELATIOI DETECTIOI [AD-7187981 171-23314 Landinq systems signal reflection interference on CRUCIPOBl PII6S correlation protected instrument landing systea Aerodynamic forces and binge moments of delta beams crnciform control surface in blunt-nosed canard [BAE-TR-701411 1171-23361 configuration for subsonic, transonic and CORBOSIOI RESISTAICE supersonic flows Fatigue life, fail-safe capability and corrosion A71-25161 resistance of commercial aircraft structures CRUDE OIL improved throuqh adhesive metal-metal bondinq Decontamination of petroleum products with honey [ ASflE PAPER 71-DE-271 A71-27325 r EASA-CASE-X~P-038351 mi-23499 COST AJALTSIS CRUISII6 PLIGHT Resin matrix composite airfoils in qas turbine Cruisinq flight ranqe as function of engines, considering performance, fabrication snpersonic/subsonic transport fuselage and cost geometrical parameters [ASNE PAPER 71-GT-471 A71-25980 A71-27494 Low cost short life gas turbine desiqn based On ainimuo drag surface shape of thick liftinq delta parametric performance and component selection. wing inteqrated with conical fuselage for outlininq turbojet production supersonic cruising speed [ASBE PAPER 71-GT-691 A71-25984 1171-27716 Helicopter auxiliary power unit /APU/ life cycle CURVE PITTIIG cost computation Examining solutions obtained from streamline 1171-26679 curvature method of calcnlatinq flow through Thrust measurement of aircraft and rocket turbomachines for several operatinq points of propulsion systems, comparing cost and Rolls-Royce conpressor characteristics of mechanical, electrical and [CUED/A-TURElO/TR-19] t?7?-22274 hydraulic systems CCEYSS 1171-26991 Supersonic fliqht path curvature effects on local Cost analysis in vertical takeoff aircraft shock rave production. considering no boom zone operation for short haul traffic notinq and ground rules influence of airport operation A71-26310 ~7 1-22193 CV-990 AIRCRAFT Flight tests of Concorde prototypes, design Photometric observations of auroral scattering by modifications, and operational costs of cv 990 aircraft supersonic aircraft [8ASA-CR-117466] N71-22135 N71-22387 CTLIIDRICAL BODIES COST BFPECTIVEIESS Lift coeffieut for wind induced vibration of Pan Awrican reliability program effect on airline skewed cylindrical horly maintenance, considerinq cost effectiveness, r AD-7177391 N71-22169 Eirczaft performance, data collection and windage tests of cylindrical and Lundell-conical analysis rotors in ambient air producing Reynolds numbers A71-26671 up to 100,000 for high speed alternators Cost effectiveness of reliability screeninq [NASA-TB-X-67809] 171-23116 proqram from parts procurement through system CTLIBDBICAL SEELLS test, using experience with attack radar for Cylindrical shells panel flutter analysis for F-111 aircraft internal stress and supersonic flow, considering A71-26683 still air bucklina data useful for determininq COUPLII6 buckling loads Wing-fuselage-tail interacting low speed flutter. [AIAA PAPER 71-3281 A71-25308 considerinq mechanical tuning and aerodynamic interference cowlings [AIAA PAPER 71-3261 A71-25306 D COOPLIIGS DAUPIIG Coupling characteristic effects on dynamic Effects of sound danpinq elements in subsonic wind response of axially coupled turborotors with tunnels digital computer proqram based on transfer [RAE-LIB-TRANS-1465] 871-21885 matrix techniques DATA ACQUISITIOI E71-22712 Pan hmerican reliability program effect on airline CEAIES maintenance, considering cost effectiveness, Helicopter operation as cranes and for external aircraft performance, data collection and load transportation. discussing operational and analysis economic aspects 1171-2667 1 A71-27142 DATA PROCBSSIIG CEASE LAIDIIG Aircraft gas turbine condition analysis Landing accidents investigations for Hawker instrumentation used for status diaqnosis of Siddeley 748 aircrafts with performance naval turbine engines. discussing sensor and measurements on rongh surfaces electronic data interpretation progress 871-23417 [ ASflE PAPER 71-GT-861 A71-25994 CREEP ROPTURB STBEI6TE DATA EBCOBDIIG Lor alloy steels and superalloys inertia weldinq Onboard data acquisition for improved aircraft in gas tnrbine field, discussing microstructure design and operational flight safety tensile strength and stress rupture A71-23412 [ASEE PAPER 71-GT-211 A71-25965 DATA EEDOCTIOI CRITICAL LOAD116 Data reduction techniques for derivinq aerdynaaic Fatigue failure probabilistic model under variable forces and moments in absence of support amplitude loading, considering relation betueen interference safety factor and fatigue failure probability [ WASA-CR-111844] 1171-23122 1171-25492 DECELEEATIOI Jet fuels deoxyqenation effects on steels antiwear Parachute decelerator towline enerqy absorber properties and critical loading under shock attenuation characteristics, discussinq

A-15 DECISION MAKING SUBJECT INDEX

drop test results ' A71-25852 rAIAA PAPER 70-12021 A71-25527 Analoq recursive computer with serial diqital DECISION MAKING proqram for arithmetic unit and storaqe system Solution of problems in structural desiqn with control emphasis on interaction between materials, 171-27150 structures, and desiqn requirements DIHEDRAL ANGLE [ ?.2-7175761 N7l-22136 Wind tunnel tests to determine effects of winq DECONTAMINATION dihedral anqle on aerodynamic characteristics of Decontamination of petroleum products with honey hiqhly swept fixed-ninq configoration NASA-CASE-XNP-03835 1 N71-23499 [ NASA-TY-X-22611 N71-22622 DEGREES OF FREEDOM DIRECTIONAL CONTROL Six deqree of freedom hybrid diqital computer Inertial naviqation system consisting of qyro proqram for complex fliqht control and horizon compass, direct.iona1 qyro and computer, associated mode loqic desiqn and traininq considering errors due to compass vibrations A71-25852 A71-27169 DELTA WINGS DISPLAT DEVICES Aerodyramic forces and hinqe moments of delta Area naviqation facility, discussinq control and cruciform control surface in blunt-nosed canard display and naviqation standards confiquration for subsonic, transonic and 871-26879 supersonic flows Concorde economic fliqht testing methods, A71-25161 discussing Blagnac fliqht simulator mobile cabin Thin deita winq in hypersonic inviscid flow at visualization and color TV terrain model small anqles of attack, calculatinq motion 871-27fiO8 equations and boundary conditions at small Optical projector system for estabiishinq optiranm Derturbat ions arranqement of instrument displays in aircraft, A71-27330 spacecraft, other vehicles, and industrial Shock interaction effects on flapped delta wing at instrument consoles hypersonic speed, presentinq method for INASA-CASE-XNP-03853 I N71-21882 estimatinq reflected expansion wave impinqement Feasibility of utilizins color cathode ray tubes boundaries and resultinq aerodynamic for aircraft crew station displays coefficients r AD-7 17655 1 N71-22174 A71-27598 DOPPLER RADAR Winimcm draq surface shape of thick liftinq delta Feasibility and desiqn criteria of laser Doppler winq inteqrated with conical fuselaqe for system for detectinq and nappinq turbulence supersonic cruisinq speed levels and wind or velocity profiles in various A71-27710 applications Predictinq aerodynamic characteristics of arrow, [NASA-CR-103105] N71-24081 delta, and diamond winq platforms usinq DOYNUASA Prandtl-Glauert transformation Unsteady flov downwash behind finite span slender r NASA-TN-D-62431 N71-21973 winq durinq supersonic motion at finite strouhal Numerical analysis of influence con€ficients, numbers natural frequencies, and mode shapes of A71-27697 vibration of trianqular inflatable wins Aircraft wake turbulence with downwash loadinq of N71 - 22666 winq span Analysis of sapersonic and hyoersonic flow of [AD-7180241 N71-23660 inviscid ideal qas over conical winqs with sharp DRAG leadinq edqes and attached Shock waves by three Two dimensional laminar boundary layer equation dimensional method of characterigtics local drag coefficient from one and two term i [NASA-CR-17381 N71-22672 Herk expansion in reqions upstream of staqnation Wind tuniel surface-flow visualization of delta point vinq shuttle confiquration at Mach number of 7.4 A71- 270 51 and severdl Reynolds numbers DRAG CHUTES [ NASA-TM-X-620361 N71-23953 Parachute decelerator towline enerqy ahsorbar DENSITY DISTRIBUTION shock attenuation characteristics, discussinq Asymmetric three dimensional aerodynamic density drop test results fields from holoqraphic interferoqrams, applyinq r AIAA PAPER 70-12021 A71-25527 to supersonic flow from free jet DRAG MEASUREMENT A71-25802 Wake flow behind two dimensional perforated Plates DEOXYGENATION normal to air stream, measuring draq, sheddinq, Jet fuels deoxyqenation effects on steels antirear velocity and turbulence at Reynolds number properties and critical loadinq under 25,000-90,000 vibrational and qlidinq friction A7 1- 26 459 A71-27662 DRAG REDUCTION DEPLOTMENT Variable qeometry external fuel tanks for hiqh Bare base shelterhanqar expandable structures for performance aircraft with draq reduction upon rapid worldwide Tactical Fiqhter Orqanization fuel transfer deployment, notinq foam and honeycomb [AIAA PAPER 71-3951 A71-25271 fabrication DROPS (LIQUIDS) rAIAA PAPER 71-3981 A71-25274 Initially spherical liquid droplet transient. DESCENT TUAJECTORIES resDonse under surface tension accelerated by Fuel-optimal retrothrusted soft landinq of external qas flow airdrops throuqh atmosphere rAIAA PAPER 71-3931 A71-25355 r AD-718405 1 N71-23487 DUST DIFFRACTION PATTERNS Effects of flow containinq dust on results of Surface strain measurements in turbine blades by hypersonic wind tunnel experiments time averaqe holoqraphic interferometry, NASA-TT-F-13529 ] N71-23702 reviewinq resonant nodes and holoqraphic frinqe DYNAMIC CHARACTERISTICS patterns Equation error approach to parameter r nsn- PAPER ~I-GT-R~1 A71-25992 identification in third order pitch plane DIPFUSIOII UELDING dynamics for high performance aerodynamically netdl matrix corposite fabrication procedures for controlled aerospace vehicle qas turbine enqine fan blades, stressinq A71-26418 diffusion hondinq process Susceptibility to DTULRIC CONTROL blades volume producibility Mathematical modellinq of aircraft structural r ASHE PliPFR 71-GT-461 A71-25979 response modes to active control system DIGITAL COMPUTERS N71-23212 Six deqrre of freedom hybrid diqital computer DINAIIC IODELS proqram for complex flioht control and Gas turbine enqinp combustor stability dynamic associatod mode loqic desiqn and traininq model, representinq prenixinq and combustion

A-16 SUBJECT IUDEI EUGIBE DESIGN

chambers as Kelmholtz resonators for stability alloy and copper aircraft electric conductors criteria derivation and terminals noting types of tests [ASIIE PAPZR 71-GT-733 A71-25987 [ TRC-BR-197851 N71-23547 Flow field model for steady asymmetric vortex ELECTRIC BOTORS system shed from slender body of revolution in Analysis of solid rotors used in high speed coning motion induction motors for aerospace applications ~AIAA PAPER 70-521 A71-27552 A71-21898 DTUABIC RESPOUSE Technology review on electric automobiles. and Twin spool turbojet engine dynamic response, modified T-33 aircraft system for pyrotechnic discussing simulator predictions, diqital hail suppression seeding computer control, nozzle area variations and [ DME/NAE-1970/4/] N71-22198 operating trajectories ELECTRIC TERIIUALS rASIIE PAPER 71-GT-141 871-25960 Comparison between silicon-naqnesium-aluminum Sailplanes tail load static derivation for alloy and copper aircraft electric conductors instantaneous unchecked longitudinal maneuver, and terminals noting types of tests considerinq aperiodic response [TRC-BR-197851 N71-23547 A71-26486 ELECTBOIAGIETIC COBPATIBILITT Coupling characteristic effects on dynaaic Tests for determining spectral siqnatures of response of axially coupled turborotors with integrated high-frequency antenna systems for diqital computer program based on transfer P-3 aircraft matrix techniques [AD-7180541 N71-23609 N71-22712 ELECTBOBAGIETIC INTERPEBEICE Transfer functions in modellinq human pilot and Landinq systems signal reflection interference on dynamic structural aircraft responses correlation protected instrument landing systen f AGARD-R-580-7 1 1 N71-23210 beans DYUAIIC STABILITT [RAE-TR-70141] N71-23361 Aerodynamic characteristics of slender body of BLECTROBAGIETIC BADIATIOU revolution traveling in long tube with circular Kigh temperature aerodynamics with electromaqnetic cross section. deriving static and dynamic radiation, considering thermally radiating shock stability derivatives formulas layers, electric arc driven wind tunnels and gas 1171-25477 dynamic lasers DTAAIIC STBUCTURAL AUALISIS All-27277 Transfer functions in modellinq human pilot and ELECTROU BEAU VELDIUG dynamic structural aircraft responses Pulsed laser holographic applications to aerospzcc r AGABD-R-580-711 871-23210 components nondestroctire testinq, inspectinq Power spectrnm method for determining gust electron beam welds and internal structural frequency response fwctions in dynamic aircraft flaws draiqn [ ASHE PAPER 71-GT-74 1 A71-25988 N71-23211 ELECTROIIC EQUIPIIEAT Eathematical modelling of aircraft structural Avionics qrowth, discussinq use of diqital response modes to active control system conputers, solid state transducers, integrated N71-23212 circuits, electronic flight instruments, area Conputation and measurements of dvnamic aircraft naviqation and collision avoidar.ce systems transfer functions to atmospheric turbulence A71-26878 N71-23213 ELECTBOUIC EQUIPIEUT TESTS DY IAIIC TESTS Tests for determining spectral siona+nres of low-inertia flow-direction vzne static and dynamic inteoratcl hi;:-frequency antenna systems for wind tunnel tests at subsonic and supersonic P-3 aircraft speeds for in-fliqlt neasurement of bust [ AD-718054 1 1171-23609 velocities ELECTROSTATIC CEARGE [NASA-TN-D-61931 N71-23115 Electrostatic charge by JP-5 jet fuel at truck fill stand with 30-second relaxation chamber and bottom loadinq E [AD-7173471 N71-22232 ECOAOIIIC FACTORS ELEVATORS (CONTROL SURFACES) Socioeconomic chanqes in aeronautics, discussinq Automatic sust alleviation system enployinq faster long range aircraft, airport access inertial sensors and feedback devices with wins problems. technoloqical advances, short haul flaps and elevators, considerinq linkaqe transportation and industry/qovernment relations control, noninteracting control and split A71-27601 control ECONOIIICS A71-25195 Economics and operational planninq for future ELLIPTICITY civil air transportation Comparison of flat plate sharp and blurrt edge N71-22384 effects on heat transfer in supersonic flow and EDGES heat transfer coefficient depezdence on Reynolds Comparison of flat plate sharp and blunt edqe number effects on heat transfer in supersonic flow and [ AD-7178251 1171-221 56 heat transfer coefficient dependence on Reynolds ENERGT CONVEBSIOB number Aerodynamic noise scatterinq near Liqhthill [AD-717825 1 N7 1-22 156 multiples, considering intense near-field energy ELASTIC DAIIPIUG conversion into sound waves Power spectral density analysis of aircraft A71-26448 strnctnral response to taxiinq produced random EUERGY DISSIPATIOU vibrations involvinq landing qear orifice Reynolds number effects on centrifuqal compressor damping and Coulomb friction performance characteristics, discussinq power 871-26311 losses in compressor, inpeller and diffuser ELASTIC SCATTBRIIG staqes and compressor adiabatic efficiency TWO phase supersonic barotropic flor with solid [ ASnE PAPER 71-GT-251 A71-25967 particles around thin profile with allowance for Flutter suppression with dissipated energy reduced elastic particle collisions to quadratic form for control surfaces A71-27450 (VASA-TA-D-61991 N71-23091 ELASTOIEBS EUGINE COITROL Flame retardant silicone elastomers for use as Twin spool turbojet engine dynamic response. aircraft construction materials, describinq discussinq simulator predictions, digital fabrication techniques, mechanical, aqinq an3 computer control, nozzle area variations and weathering properties operating trajectories 871-27412 [ ASHE PAPER 71-GT-14 J A71-25960 ELECTRIC COUDUCTORS BUGINB DESIGU Comparison between silicon-oaqnesiun-aluminum Liqhtueiqht high performance reqenerative gas

1-17 ENGINE PAILORE SUBJECT INDEX

turbine desiqns for aircraft propulsion, Plate and acoustic finite elements simulation of comparinq various compressor, turbine, combustor window-room system coupled transient response to and recuperator arranqements sonic booms, discussinq equations of notion and [ASUE PAPER 71-GT-671 A71-25983 cavity depth effect Low cost short life gas turbine desiqn based on A71-27481 pzrsp?r-.tric performance and component selection, Accelerated supersonic motion of plane at finite outlininq turbojet production anqle of attack r ASME PAPFR 71-GT-69 1 A71-25984 [NASA-TT-F-13525] N71-23278 Vertical straiqht lift turbojet enqine desiqn and EQUILIBRIUI! PLOU development, presentinq component materials Equilibrium air boundary layer flows at three properties/weiqhts. endurance tests and dimensional stagnation points, discussinq flow Performance data characteristics and real qas heat transfer [ASME PAPER 71-GT-751 A71-25989 parameters Supersonic turbine desiqn, preseatinq performance [AIAA PAPER 70-8091 A71-27582 data for film cooled blunt leadinq edge rotor Steady state inflated shape and included volume of blades measured in two dimensional cascade 24 and 30 qore flat circular, extended skirt, experiments porous rinq slot, and porous ribbon parachutes [ ASRE PAPER 71-GT-761 A71-25990 [ AD-7188081 N71-23387 Boron-qlass-epoxy liqhtwziqht composite qear case EQUIPMENT SPECIPICATIOES for aircraft. rnqine reduction qearbox, Expandable structures for midair pilot rescue describinq desiqn, noldinq, machining and device with hot air filled BALLUTE; discussing testinq BALLUTE material development rASME PAPER 71-GT-851 A71-25993 [AIAA PAPER 71-402] A71-25278 Desian and fabrication of Borsic aluminum Aircraft industry materials development, composite fan blades for suuersonic turbofan discussinq innovations in qovernmental proqrams enqincs, considerinq 430 F application without manaqement, procurement specifications and severe vibratory stress Department of Defense contracting procedures r ASIIE PAPER 71-GT-90 1 A71-25937 A71-27677 ConveLtible fan/shaft engine for V/STOL tactical ERROR ANALYSIS and transport aircraft, detailiny mechanical Equation error approach to parameter arranqement. desiqn and performance identification in third order pitch plane A71-26054 dynamics for hiqh performance aerodynamically Gas field nonnniforoity as function of turbine controlled aerospace vehicle enqine combustion chamber desiqn parameters, A71-26418 discussinq hot tube circumferential holes total nodulation cancellation altimeter error analysis area effect and performance optimization 171-27501 A71-27437 ENGINE PAILORE EVAPORATIOE RATE Optimum weiyht urotective system aqainst Benzene evaporation rate determined from flat uncontained rotor failure with radial fraqment plate film boilinq under hiqh temperature air passaqe throuqh turbine enqine casinq flow with applicati3n to qas turbine air [ASH3 PAPEil 71-GT-701 A71-25985 pollution reduction ENGINE HORITORING INSTRUHENTS DLR-FB-70-58 1 N71-22072 Fliqht test completed on onboard real time enqine EXHAUST PLOU SIMULATION PerEormance monitoring system, discussinq One dimensional flow models of internal combustion thernodynanic analysis technique enqine exhaust silencers in noisy systems r ASnE PAPER 71-GT-771 A71-25991 1171-25180 ENGINE NOISE EXRAUST GASES One dimensional flow models of internal combustion Standard equipment and procedures for aircraft gas enqine exhaust silencers in noisy systems turbine enqine exhaust smoke measurement A71-25180 [ASIIE PAPER 71-GT-881 A71-25995 Solution of Liqhthill qas model wave equation for EXHAUST SYSTEHS enqine noise qeneration in circular jets notinq Flow variation effect on velocity and flow anqle cylindrical coordinate system distribution at exit of shrouded radial flow IDiR-FB-70-571 N71-22070 impeller with backward sweut blades, usinq Theoretical analysis of jet mixinq under influence streamline curvature method of nonconstant pressure qradient [ASRE PAPER 71-GT-151 A71-25961 I ARL/UE-127 1 N71-22503 EXPANDABLE STRUCTURES ENGINE PARTS Bare base shelter/hanqar expandable structures €or Jet enqine components inertia weldinq, discussinq rapid worldwide Tactical Fiqhter Orqanization urocess, equipment, low weiqht-cost advantaqe deployment, notinq foam and honeycomb and mechanical properties reproducibility fabrication lASIIE PAPES 71-GT-331 All-25970 (RIA8 PAPER 71-3981 P.71-25274 ENGINE STARTERS Expandable structures for midair pilot rescue Jet fuel starter, describinq small qas turbine for device with hot air filled BALLUTE, discussinq starter, providinq sufficient pressurized qas BRLLUTE material development flow to rotate main enqine [AIAA PAPER 71-4021 A71-25278 IASWE PAPER 71-GT-43 1 1171-25976 EXPERIRENTAL DESIGN ENTROPY Desiqn, fabrication and static testinq of attached Turbomachine Made cascades in supersonic flow, inflatable decelerator models for supersonic notinq wave confiqurations, entropy and counter wind tunnel evaluation PressurF) variations [NASA-CR-1118311 N71-22538 A71-27475 EPOXY RESINS BOKOn-ePOXY structural skins desiqn for F-14 F honeyconb horizontal stabilizer, usinq computer P-111 AIRCBBPT proaran; Cost effectiveness of reliability screeninq A71-25420 proqram from parts procurement throuqh system Graphite-epoxy composite skins for commercial test, usinq experience with attack radar for aircraft fliqht spoiler, discussinq multianqle F-111 aircraft nly dosiqn and fabrication A71-26683 A71-27413 Two variations of qas qenerator method to EQUATIONS OF MOTION calculate thrust of afterburninq turbofan Thin delta winq in hypersonic inviscid flow at enqines installed in F-111A aircraft small anqles of attack, calculatinq motion [NASA-TN-D-6297 1 N71-22614 equat.ions and boundary conditions at small P-14 AIRCRAFT perturbations Boron-epoxy structural skins desiqn for P-14 A71-27330 honeycomb horizontal stabilizer, usinq computer proqram

A-18 SUBJECT IHDEI FLAT PLATES

A71-25420 blades measured in two dimensional cascade PABRICATION experiments Representative Thornel fiber aircraft fuselage [ ESRE PAPER 71-62-76] 171-25090 component nondestructive testing and repair, and Conference on high temperature turbines detailing Thornel fiber, polysulfone and polyamide-imide effect of film coolina on blade profile loss composites fabrication and evaluation RASE-Til-X-67123 J N71-22699 A71-25427 PIHITE DIPPERBHCE THEOBI Resin matrix composite airfoils in qas turbine Finite difference method for calculating sonic enqinen, considerinq performance, fabrication boom overpressure signatures in vicinity of and cost caustics [ ASRP PAPER 71-GT-471 171-25980 [ AD-7188351 N71-23738 Design and fabrication of Borsic aluminum PIUITE ELEUEHT RETEOD composite fan blades for supersonic turbofan Collocation method predictina oscillatory subsonic enqines. considering 430 F application without pressure distributions on interferinq parallel severe vibratory stress liftinq surfaces. considering approach more [ASBE PAPPR 71-GT-901 A71-25997 economical than finite element method Fabrication and tests of C02 flat plate models in rAIAA PAPER 71-3291 A71-25309 He hypersonic wind tunnel Plate and acoustic finite eleEents siaulation of [ SC-'3-69-3215 ] 1-11-23228 window-room system coupled transient response to PAIL-SAPE STSTEUS sonic booms, discussin? emuations of motion and Fatigue life, fail-safe capability and corrosion cavity depth effect resistance of commercial aircraft structures 871-27481 improved through adhesive metal-metal bondinq Koiter method for asymptotic analysis of r Asm P~~PER71-DE-27 1 A71-27325 postbncklinq behavior reformulated in finite FAILURE AHALTSIS element notation Rotor-bearinq system analysis to determine cause AD-7177401 N71-22'485 of brinellirg failure of bearings from vibratlon Finite-element potential flow Eodelinq for tested PLV fans predictinq round liftinq jet rolled up qeometry r AA SA-CP- 11785 5 3 N71-22527 and path convergent into cross-flowins PAUS mainstream as on VTOL or STOL aircraft Axial flow fan noise. investigatinq louvers [ AD-7181211 n71-234i5 effects on sound field Finite element method for free vibrations and 1171-26704 random response of integrally-stiffened panel PAR FIELDS LR-544 3 ~71-24208 Jet noise contrihution to far field sound from PIREPROOPIUG 1.83 meter diameter fan determined for two Plz~cretaidant silicone elastomers for use as simulated nacelle confiqoratinas aircraft construction materials, describinq :EASA-ia-X-67825] 1171-24009 fabrication techniques, mechanical. aging and FATIGUE LIFE weatherinq properties Fatigue failure probabilistic model under variable 171-27412 amplitude loading, considering relation between FIXED UIISS safety factor and fatigue failure probability Wind tunnel tests to determine effects of winq 871-25492 dihedral angle on aerodynamic characteristics of Passenqer aircraft structures accelerated testinq hiahly swept fixed-winq confiquration €or safety and fatisne durability under NASA-TR-X-22611 871-22622 operational conditions, describing tests, PLABEOUT planning and evalaarlen Investigation of helicopter jet euyine flameout A71-269UC. due to inqestion of snow and ice Fatigue life, fail-safe capah+iity and corrosion r NRC-118931 ~71-21927 resistance of commercial aircraft structures PLAIIABILITI improved throuqh adhesive metal-metal bondinq Tests of

A-19 FLEXIBLE BODIES SUBJECT INDEX

Supersonic combustion. fuel injection, and N71-23411 recirculation in hydroqen hypersonic external Onboard data acquisition for improved aircraft combustion at flat plates and bodies of desiqn and operational fliqht safety revolution N71-23412 r DLR-FB-70-641 N7 1-22129 Fliqht simulator and airframe test stand for rnmparison of flat plate sharp and blunt edge evaluatinq operational performance of aircraft effects on heat trdfisfer in wpersonic flow and fliqht control system heat transfer coefficient dependence on Reynoids N71-23413 number Desiqn modificatioi6 GI shcrt takeoff Bronco f AD-717325 1 N71-22156 aircraft resulting from combat operations tests Separated flow over flat plate with blunted fin at N71-23416 zero anqle of attack Landinq accidents investiqations for Hawker ~.~-7i77171 pi71-223OC Siddeley 748 aircrafts with performance Fabrication and tests of C02 flat plate models in measurements on rough surfaces He hypersonic wind tunnel N71-23417 ISC-CP-69-3215 1 N71-23228 safetv measures to eliminate aircraft trailing Interference phenomenon of subsonic turbulent jet voriex hazards exhausts from flat plate in low speed cross flow [NASA-Tn-X-671251 N71-23418 rAD-7187581 N71-23314 Fliqht mechanics problems in accident FLEXIBLE BODIES investiqations for VJ-101 aircraft Validity ranqe of response prediction methods for N71-23428 larqe flexible aircraft to continuoos FLIGHT PATHS atmospheric turbulence, discussinq power SupeLsonic fliqht path curvat.ure effects on local spectral densities and fatique life shock wave production, considerinq no boom zone rP.IAA PAPER 71-3421 A71-25321 and qround rules Computer proqram for aerodynamic forces on A71-26310 flexible plate underqoinq transient motion in FLIGHT PLAAS shear flow, applyinq to panel flut.ter Tu-154 responsibilities of three-man crews, A71-27559 considerinq fliqht plan, refuelinq, carqo FLEXING loadinq and unloadinq Torsional-flexural stability of stiffened Ti A71-25258 panels for application to supersonic transport, FLIGHT SAFETY usinq small deflection enerqy methods Jet aircraft airworthiness standards, discussinq [PIAA PAPEF 71-3381 A71-25317 airline fleet maintenance resources, inspection PLIGHT CHARACTERISTICS systems and future requirements Wicd qradient effect on fliqht characteristics A71-26308 durinq aircraft landinq approach, particularly Fliqht safety performance of V/STOL Harrier path deviation military aircraft havinq jet control A71-25194 N71-23427 Cruisinq fliqht ranqe as function of FLIGHT SIMULATORS supersonic/subsonic transport fuselaqe Concorde economic fliqht testinq methods, qeome t. r i c a 1 param ete r Y discussinq Blaqnac fliqht simulator mobile cabin A71-27494 visualization and color TV terrain model FLIGHT CONTROL A71-27608 Six dcqree of freedom hybrid diqital computer Fliqht simulator and airframe test stand for proqram for complex fliqht cpntrol and evaluatinq operational performance of aircraft associated mode loqic desiqn and traininq fliqht control system A71-25852 N71-23413 Nilitary aircraft fliqht test establishments, PLIGET TESTS discussinq airframe, enqine, fliqht control and Parachutes for low density atmospheres, describing weapons delivery systems tests work flow low and hiqh altitude test results inteqration requirements rAIAA PAPER 70-11641 A71-25525 A71-26315 Fliqht test completed on onboard real time enqine Area naviqation facility, discussinq control and performance monitorinq system, discussinq display and naviqation standards thermodynamic analysis technique A71-26379 rASNE PAPFR 71-GT-771 A71-25991 Hydraulically powered duplex input servos for Military aircraft fliqht test establishments, fliqht control system of VFW-Fokker V/STOL discussinq airframe, enqine, fliqht control and fiqhter aircraft weapons delivery systems tests work flow A71-26884 inteqration requirements Aerodynamic characteristics affectinq stability A7'I- 26 31 5 and controllability of supersonic aircraft European airbus, considerinq fliqht trials of IAD-719474 1 N71-23538 first A.300B hiqh capacity transport aircraft FLIGHT CREUS A71-26921 Operational preparation and comaissioninq of IL-62 Concorde economic fliqht testinq methods. lonq distance jet aircraft, considerinq fliqht discussinq Blaqnac fliqht simulator mobile cabin crew and maintenance personnel traininq at visualization and color TV terrain model O.S.S.R. plant ..171-?7608 - . A71-25256 Fliqbt tests of Boeinq 747 aircraft and Fliqht and operation of IL-62 lonq distance jet operational analysis for supersonic transport aircraft, considerinq fliqht crew composition N71-22386 and traininq, passenqer and carqo handlinq and Pliqht tests of Concorde prototypes, desiqn ref uelinq modifications, and operational costs of A71-25260 supersonic aircraft FLIGHT HAZARDS N71-22387 Husan fectors and control system failures in jet Theoretical analysis of jet mixing under influence uP:rt5 durinq turbulence encounters of nonconstant pressure gradient N71-23424 r ARL/nE- 127 1 N71-22503 PLIGHT INSTROHENTS Accident investiqations, fliqht control systems, Fk,a-ilrility of utilizinq color cathode ray tubes and operational recordinqs for improved aircraft for aircraft crew station displays flight mechanics r ~~-7176551 N71-22174 [ AGARD-CP-76-711 N71-23410 FLIGHT llECHAAICS Desiqn modifications on short takeoff Bronco Accident investiqations, fliqht control systems, aircraft resultinq from combat operations tests and opprational recordinqs for improved aircraft N71-23416 fliqht mpchanics Fliqht test evaluation of military aircraft low '~AGAR~-cP-?~-~~1 N71-23410 altitude hiqh speed performance nprrational fliqht data analysis for improved N71-23421 aviation safety levels

A-20 SUBJECT INDEX PLOW VELOCITY

Beaqle 8125 training aircraft handling tests PLOW GEO8ETBI [ AAEE/963-PT-l] 171-23498 CUrVatUre effects on laninar and turbulent free Plight-measured base pressures from sharp leading jet boundary between irrotational flow and edae upper vertical fin of 1-15 aircraft stagnant fluid, discussinq pressure effects b compared with wind tunnel data for turbulent 871-25482 flow at Each numbers from 1.5 to 5.0 Reattachment angle of supersonic laminar mixed I [ NASA-TN-D-63481 mi-23922 boundary layer, using revolution model with PLIGHT TBAIlIl6 Reynolds number allowance Operational preparation and commissioninq of IL-62 A71-26194 I long distance jet aircraft, considerinq fliqht Finite-element potential flow modalinq for crew and maintenance personnel training at predicting round lifting jet rolled up geometry U.S.S.R. plant and path convergent into cross-flowina A71-25256 mainstream as on VTOL or STOL aircraft PLIGHT TEEICLES r AD-718121 1 N71-23475 Nonlinear self adjustinq and variable structure PLOW EEASUHEHEE~ automatic control systems for piloted and Two dimensional flow in radial turbomachine bladed pilotless fliqht vehicles. considerinq impeller, comparinq numerical solution based on oscillations due to electric servosystems potential theory with experimental results nonlinear characteristics [ ASBE PAPER 71-GT-201 A71-25364 A71-26716 Vortex shedding characteristics of circular Construction of leadiuq edges of surfaces for cylinders at low Reynolds numbers from aerial vehicles performina from subsonic to experiment on tapered models wake structure above transonic speeds 171-27220 rRASA-CASE-XLA-01486] 171- 23497 Unsteady flow measurement around winq sections PLOW CHARACTERISTICS during rapid angle of attack variations, Plow patterns within centrifugal and mixed flow emphasizinq helicopter rotor blades impeller channel, examining velocity A71-27468 distributions. blade surface nressure and flow PLOW BBGULATOBS behavior Plow control system design for hlowdown wind [ASRE PAPER 71-GT-41 J 1171-25974 tunnels and disturbance effects on requlatinq Equilibrium air boundary laver flows at three accuracy dimensional staqnation points, discussing flow [ MAL-TN-221 N71-22476 characteristics and real gas heat transfer PLOW STABILITY parameters naqnetically suspended laminar supersonic cone [AIAA PAPER 70-8093 1171-27582 wake stabilitv from hot rire flactuatiorh and I Windaae tests of cylindrical an_* Lnndcll-conicai spectral components amplitude/phase measurements rotors in ambient air producing Reynolds nnmbers 1171-25475 t up to 100,000 for high speed alternators Additional slot and flow fence effects on rNASA-TS-X-67809] mi-231 16 aerodynamic characteristics of sinqle staqe PLOP DISTOBTIOl compressor blading I Ideal incompressible fluid f low aronnd fixed r NASA-CR-72635 1 N71-21995 obstacle near rectilinear wall, investigating PLOW TEEOBI plane motion with profile couple method Approximation of flow around jet flapped airfoil, 871-26258 discussing qround effect on lift coefficient Effects of wave inlet distortion at high and low increments flow rate on Derformar?ce of axial flow A71-26314 k compressor mhr-? ?ize~ri;snl tarbaiaot Dounaary layer r CUFII/R-TWW,~TR-:C 1 N71-22428 calculations, usinq two diaensional method based PLOW DISTRIBUTIOI on turbulent enerqy equation empirical Time asymptotic solutions for hypervelocity blunt conversion into shear stress transport equation body flow field with coupled nonqray radiation, 871-26443 treatinq shock as discrete surface fmmons spot theorr extension for boundary layer [AIAA PAPER 70-8651 A71-25453 flow on blunt bodies, deducinq spot formation Underexpanded transverse sonic jet-hypersonic rate deDendence on transition Revnolds and nach stream three dimensional flowfield based on numbers inviscid rotational flow model A71-27557 A71-25472 Numerical analysis of inviscid flow fields about Flow patterns within centrifuqal and mixed flow pointed circular cone and conical winq-body impeller channel, examining velocity configuration at various angles of attack distributions, blade surface pressure and flow 1171-22667 behavior Numerical solution of mixed supersonic and r ASEE PAPER ?1-GT-411 A71 -2597 4 subsonic steady wake flows by time-dependent Ideal incompressible fluid flow around fixed method obstacle near rectilinear wall, irvestigatinq N71-22674 plane motion with profile couple method PLOW VBLOCITT A71-26258 Revnolds number effects on centrifuaal compressor Liftinq force of wing with rotating flap, deriving performance characteristics, discussinq Power lift increase due to circnlation redistribution losses in compressor, impeller and diffuser at surface staqes and conpressor adiabatic efficiency A71-27491 r ASBE PAPER 71-GT-253 A71-25O67 Plow field model for steady asymmetric vDrtex Three dimensional boundary layer flow acd velocity system shed from slender body of revolution in profiles in mixed diffuser with equal anqle coninq motion walls f AIAA ?APER 70-521 B71-27552 I ASnE PAPER 71-GT-401 A71-25973 Examininq solutions obtained from streamline Condenser microphones aerodvnamically induced curvature method of calculatinq flow throuqh noise, investigatinq acoustic pressure lower turbomachines for several operatinq points of limit dependence on air flow velocity and Rolls-Royce con pressor turbulence rCUED/A-TURBO/TR-l9] N71-22294 A71-27063 PLOW BQUITIOBS Quasi-three diEensioca1 surface velocities ar'd Laminar boundary layer equations for rotatina choking flow for tnrboaachine blade rows Plate with surface of arbitrary curvilinear calculated by FORTRAN prooram shape, determining external flow pressure r NASA-TN-D-6177 1 N71-23126 qradient leading to separation Air flow velocity, altitude, fuel-air ratio. fuel A71-27502 flow velocity, and pressure effects on fuel Numerical solution of mixed sucersonic and temperature before and after prevaporization in subsonic steady wake flows by time-dependent ramjet enqines method NASA-TT-F- 136G5] N71-2UP53 N71-22674

A-21 FLOU VISUALIZATION SUBJECT INDEX

FLOE VISUALIZATION r NASA-TN-D-61111 N71-22590 Hele-Shaw flow viscous tails frOm.airfoi1, FOG observing hiqh Reynolds number trailinq edqe Foq clearance from airport runways, discussinq flow for separation and initiation of Kntta available techniques, economic aspects and condition importance for military operations A71-26447 A71-27247 Schlieren risnaliz~tionfor supersonic annular POKKER AIRCRAFT fixed cascade and freon compressor wind tunnels, ..nyuLaulically > -_.. pc\-erPd duplex input servos for usinq vane holdinq cylinder devices flight control system of VPu-Pokker V/STOL A71-277 17 fighter aircraft Schlieren and phase contrast methods of hypersonic A71-26884 flow visualization Fatique test equipment for evaluating Pocker N71-22637 aircraft wing Laminar boundary layer transition, separation and r NLR-TR-70008-Ll N71-23 157 streamline direction on rotatinq helicopter FORCE DISTRIBUTION blades Aiqh lift winq characteristics with/without NASA-TN-D-63211 N71-23779 additional devices,.. emphasizinq lift control and Hind tunnel surface-flow Visualization of delta load distribution winq shuttle confiquration at nach number of 7.4 A71-27476 and several Reynolds numbers POBTRAN NASA-TB-X-62036 1 N71-23953 Ouasi-three dimensional surface velocities and Surface flow photovisualization of straiqht wins chokinq flow for turbomachine blade rows orbiter and swept delta winq orbiter calculated by FORTRAN proqraa confiqurations at nach 10.4 and several Reynolds r NASA-TN-D-6177 1 N71-23126 numbers FREE COUVECTION TNASA-Tti-X-620331 N71-24001 Conbined free and forced laminar convective heat FLUID AIIPLIFIBRS transfer to nonNewtonian fluids flowing in High total temperature sensinq probe usinq fluid constant wall temperature vertical tubes and oscillator concept for X-15 hypersonic aircraft controlling parameter analysis N71-22702 r NASA-CR-136772 1 N71-23250 FLUID DYNAIIICS FREE PLIGET Gas and fluid response to hiqh intensity ruby Application of free flight ranqes to hiqh laser beam temperature qas dynamics [AD-717728 J N71-22593 N71-22633 FLUID FLOU FREE FLIGHT TEST APPARATUS Lift and particle displacement around liftinq body Free fliqht tests in hoovering and forward flisht with stream function as fluid motion equation of V/STOL transport model with six wing-mounted inteqral lift fans 1171-27577 [ NASA-TN-D-61981 N71-22069 Laboratory experiment on flow of viscous fluid FREE FLOU alonq travelinq waves Loads induced on infinite aspect ratio winq by N71-22221 straiqht infinite tree vortex in subsonic FLUID JETS compressible freestream, usinq planar liftinq Breakup mechanism of liquid sheets and jets in surface theory supersonic qas stream, usinq spark A71-25474 photomicroqraphs and hiqh speed movies FREE JETS A71-25471 Curvature effects on laminar and turbulent free FLUIDICS jet boundary between irrotational flow and Fluidic fuel control valve €or uniform fuel staqnant fluid, discussinq pressure effects distribution to qas turbine annular combustor, A71-25482 providinq sufficient pressure drop at low fuel FREE VIBRATION flow rates Finite element method for free vibrations and lASIIE PAPER 71-GT-441 A71 -25977 random response of integrally-stiffened panel FLUOR0 COIIPOUNDS r LR-544 1 N71-24298 Performance testinq of fluorosilicone hydraulic FREQUENCYRESPONSE fluid in hiah temperature supersonic aircraft Power spectrur method for determininq gust piston pumps frequency response functions in dynamic aircraft A71-27040 desiqn FLUTTER N71-23211 Flutter suppression with dissipated enerqy reduced FUEL CONSUUPTION to quadratic form for control surfaces Kalman linear least squares filterinq applied to [NASA-TN-D-61991 N71-23091 estimation of fuel quantity and rate for fiqhter FLUTTER ANALYSIS aircraft T tail flutter analysis, considerinq dihedral, r AD-717640 J N71-21922 anqle of attack and aerodynamic force effects FUEL CONTA8INATION 1171-25188 Aircraft fuel tank nitroqen inertinq, fire and Sweptback thin cantilever winq transonic flutter explosion suppression for foreiqn particle density and velocity coefficients, investiqatinq contamination, sludqe and lacquerinq reduction ensine Pod shaped concentrated mass location r ASnE PAPER 71-GT-45 J A71-25978 effects Polyurethane foam effects on fuel contamination A71-25189 durinq installation for fuel system fire and Uinq-fuselaqe-tail interacting low speed flutter, explosion protection considering mechanical tuninq and aerodynamic r ASIIE PAPER 71-GT-541 171-25981 interference couplings FUEL CONTROL rAIAA PAPER 71-3261 A71-25306 Fluidic fuel control valve for uniform fuel Flutter analysis of clamped thin skew panels with distribution to gas turbine annular combustor, midplane forces in supersonic flow, usinq providing sufficient pressure drop at low fuel Galerkin method flow rates A71-26766 I ASnE PAPER 71-GT-44 1 A71-25977 Flutter of buckled plate exposed to static FUEL PLOU pressure differential and streamwise applied in- Air flow velocity, altitude, fuel-air ratio, fuel plane load, comparinq experimental results with flow velocity, and pressure effects on fuel stability boundary calculations temperature before and after prevaporization in A71-27584 ramjet engines PLYING PLATFORNS rNASA-TT-.F-13605] N71-24053 Desiqn and developsent of lunar escape system FUEL PLOS REGULATORS simulator for investiqation of lunar escape Fluidic fuel control valve for uniform fuel problems and simplified manual quidance and distribution to gas turbine annular combustor, control for lunar escave vehicles providinq sufficient pressure drop at low fuel

A-22 SUBJECT IRDEI GAS TURBIRES

flow rates GAS GERERATORS rASBE PAPER 71-GT-4UI A71-25977 Jet fuel starter, describing small qas turbine for FUEL IRJECTIOH starter, providinq sufficient pressurized qas LOW pressure drop fuel liquid injectors for jet flow to rotate main enqine enqine combustors, using gas turbine vaporizer [ ASIE PAPER 71-GT-431 A71-25?76 desisn Gas generators as vertical takeoff aircraft enerqy [ASUE PAPER 71-GT-381 A71-25972 sources to operate lift fans or helicopter Supersonic combustion, fuel injection. and rotary winqs recirculation in hydrogen hypersonic external 971-22104 combustion at flat plates and bodies of Two variations of qas qenerator method to revolution calculate thrust of afterburninq turbofan IDLR-PB-70-64 I 1171-22129 enqines installed in F-111A aircraft FUEL PUBPS [ NASA-TB-D-62971 ii71-226 io nigh speed vane type main enqine fuel pump for GAS LASERS small gas turbine engines High temperature aerodynamics uith electroaaqnetic TASIE PAPER 71-GT-241 A71-25966 radiation, considerinq thermally radiating shock FUEL STSTEBS layers, electric arc driven wind tunnels and qas Soviet book on aircraft and rocket engines control dynamic lasers automation, discussinq nuclear poser plant/fuel A71-27277 systems design and control simulation metbods GAS STREA8S A71-26403 Breakup mecharism of liquid sheets and jets in FUEL TARKS supersonic gas stream, usinq spark Variable qeometry external fuel tanks for hiqh photomicrographs and hiqh speed movies performance aircraft uith draq reduction upon 1171-25471 fuel transfer GAS TRARSPORT [AIAA PAPER 71-3951 A71-25271 Gas qenerators as vertical takeoff aircraft energv Aircraft fuel tank nitroqen inerting. fire and sources to operate lift fans or helicopter explosion suppression for foreign particle rotary uinqs contamination. sludge and lacquering reduction A71-22194 rASIE PAPER 71-GT-453 A71-25978 GAS TURBIRE ERGIIES FUEL VALVES Aiqh speed vane type main enqine fuel DUMP for Fluidic fuel control valve for uniform fuel small qas turbine enqines distribution to qas turbine annular combustor. [ ASUE PAPER 71-GT-241 A71-25966 providing Sufficient pressure drop at low fuel Jet fuel starter, describinq small uas tnrbin? for flow rates starter, providinq sufficient pressurized uas TASIE PAPER 71-62-44] 117 1-25977 flow to rotate aaiz cnqine FUSELAGES rASU3 PAPER 71-GT-431 871-25976 Brpiesentative Thornel fiber aircraft fuselaqe Uetal matrix composite fabrication procedures for component nondestructive testinq and repair, and aas turbine engine fan blades, stressinq Thornel fiber, polysulfone and polyamide-imide diffusion bondinq process susceptibility to composites fabrication and evaluation blades volume producibility A7 1- 2 5427 rASIE PAPEB 71-GT-463 A71-25979 Prototype graphite fiber/plastic fuselage Resin matrix composite airfoils in aas turbine comrmnent desiqn. test and performance er.qines, considering perf ormance. fabrication prediction. usinq structural analysis methods and cost A71-25428 [ASaE PAPER 7ll;T-471 A71-25980 Cruising fliqht ranqe as fanction of Liqhtweight hiqh performance reqenerative qa= supersonic/subsonic transport fuselaqe I~rbi;.~ for aircraft propulsion, qeometrical Parameters comparinq various compressor. turbine, combustor A71-27494 and recuperator arrangements r ASUE PAPER 71-GT-673 A71-25083 Gas turbine engine combustor stability dynamic G model, represeutinq premixinq and combustion GAS BAGS chambers as Helmholtz resonators for stability Cargo airship standard atmosphere operation modes, criteria derivation discussinq lonq ranqe gas capacity and short [ASIE PAPER 71-GT-731 A71-25987 ranqe applications for larqe compact loads Aircraft gas turbine condition analysis A7 1- 26 309 instrumentation used for status diaqnosis of GAS CBROIATOGRAPBT naval turbine engines, discussinq sensor and Conference on propulsion and energetics techniques electronic data interpretation proqress for diagnosinq hiqh relocitr flows [ ASIE PAPER 71-GT-86 1 A71-25994 [ AGARD-CP-381 R71-22626 Gas field nonuniformity as function of turbine GAS DBISITT engine combustion chamber desiqn parameters, Viscous flow in supersonic de Lava1 nozzle, discussing hot tube circumferential holes total measuring gas density and rotational area effect temperatures by electron beam techniques 1171-27501 [AIAA PAPER 70-810] A71-27555 Requirements analysis of airbreathinq gas turbine 6AS DTHABICS enqines for shuttle vehicles Canadian research on aerospace sciences and [ RASA-TU-1-67806 ] 1171-23764 engineering. gas and plasma dynamics, and GAS TUREIRES related topics Low alloy steels and superalloys inertia weldinq N71-22515 in gas turbine field, discussinq microstructure Gas and fluid response to high intensity ruby tensile strenqth and stress rupture laser beam [ ASIE PAPER 71-GT-211 A71-25965 [ AD-7177281 R71-22593 Hiqh subsonic flow two dimensional turbine cascade Application of free fliqht ranges to hiqh design by approximate hodoqraph method, notiuq temperature gas dynamics pressure distribution measureaents vi-22633 r ASIE PAPER 71-GT-343 871-25971 GAS FLOW Low pressure drop fuel liquid injectors for jet Initially spherical liquid droplet transient enqine combustors. usinq gas turbine vaporizer response under surface tension accelerated by desiqn external gas flow [ASBE PAPER 71-GT-38 J A 7 1.2 5 97 2 rAIAA PAPER 71-3931 A71-25355 Low cost short life qas turbine desiqn based on Analysis of supersonic and hypersonic flow of parametric performance and component selection, inviscid ideal gas over conical uinqs with sharp outliuinq turbojet production leading edaes and attached shock uaves by three I ASRE PAPER 71-GT-69 1 A71-25994 dimensional method of characteristics Standard equipment and procedures €or aircraft qas [NASA-CR-l738J 87 1-22 672 turbine enqiue exhaust smoke measurement [ASIE PAPER 71-GT-881 A71-25995

A-23 GEODETIC SURVEYS SUBJECT INDEX

steady transonic flow throuqh two dimensional qas lona distance jet aircraft, considerinq fliqht turbine cascades predicted with time dependent crew and maintenance personnel trainino at formulation of flow equations, qivinq airfoil U.S.S.R. plant surface pressure distributions A71-25256 [ hS5E PAPEF 71-GT-891 A71-25996 GROUND EFFECT Friction ooints, and oil system of aviation qas Approximation of flow around jet flapped airfoil, tErbine enaines discussing qround effect on lift coefficient [ AD-717835 1 X7!-?20!! increments Benzene evaooration rate determined from flat A71-26314 plate film boilina under hiqh temperature air GROUND EFFECT MACHINES flow with application to qas turbine air Hiqh speed tracked air cushion vehicles dynamic pollution reduction interactions with quideways, considering model r DLR-FB-70-58 1 N71-22072 of lumped double-sprung vehicle masses travelinq Conference on hiqh temperature turbines detailinq in tandem alonq simply supported beams effect of film coolinq on blade profile loss [AIAA PAPER 71-3861 A71-25350 [NASA-TI-X-671231 N71-22699 Numerical analysis of dynamic and thermodynamic GEODETIC SURVEYS state of plenum-type air-cushion vehicle to Airport qeodetic control stations, discussinq determine heave response and control system obstruction chartinq proqram operatinq characteristics A71-27537 [ NASA-TN-D-62571 N71-22589 GLASS FIBERS Hind tunnel study of auqmented ram-winq vehicle Glass fiber reinforced plastir.: aerospace with various blowing arranqements applications coverinq radomes, dielectric IPE-~~~U~I N71-23283 panels, aircraft ducting, secondary structures, GROUND AANDLING furnishinqs, mouldinqs and toolinq Beaqle 8125 traininq aircraft bandlinq tests A71-25652 rAAEE/963-PT-1 1 N71-23498 Glass fiber rotor blades desiqn with longitudinal GROUND OPERATIONAL SUPPORT SYSTER pressure tappinqs for cascade wind tunnel and Bare base shelter/hanqar expandable structures for turbomachinery flow research applications rapid worldwide Tactical Piqhter Orqanization A71-263 16 deployment, notinq foam and honeycomb GLIDE PATHS fabrication Aircraft approach and landinq under low altitude rAIAA PAPER 71-3981 A71-25274 wind shear conditions, discussinq flyinq hazards GUIDANCE (MOTION) and qlide path correction procedures Hiqh speed tracked air cushion vehicles dynamic A71-26364 interactions with quideways, considerinq model GLIDERS of lumped double-sprunq vehicle masses travolinq Sailplanes tail load static derivation for in tandem alonq simply supported beams instantaneous unchecked lonqitudinal maneuver, [AIAA PAPER 71-3861 A71-2535(! considerinq aperiodic responsp Quasi-optimal proportional naviqation, derivina

A71-26496 feedback~~~~ auidance laws for interceptor Sailplanes control, derivinq incremrnt.al aerodynamically controlled missiles aerodynamic load on horizontal tail PrOdUcad by A71-26409 i nst antaneous elev d t or deflection Simolified linear quidance and control for keepinq A71-26487 trajectory deviations minimal N71-21915 GRADIENTS AD- 7 17567 1 Wind qradient effect on fliqht characteristics GUST ALLEVIATORS durinq aircraft landinq approach, particularly Automatic qust alleviation system employing path deviation inertial sensors and feedback devices with wins A71-25194 flaps and elevators, considerinq linkaqe GRAPAITE control, noninteracting control and split Prototype qraphite fiber/plastic fuselage control component desiqn, test and performance A71-25195 prediction, usinq structural analysis methods Analysis of effects of spanwise variations of qust A71-55428 velocity in isotropic turbulence on Air Force development proqrams with qraphite vane-controlled qust alleviation system reinforced composites. discussinq matrix r NASA-TN-D-61261 N71-22068 materials and cost and weiqht savinqs GUST LOADS [ASRE PAPER 71-DE-131 All-27323 Yeasurement of force and pressure fluctuations on Graphite-epoxy composite skins for commercial airfoils durinq transverse and streamwise qust aircraft fliqht spoiler, discussinq multianqle flows ply desiqn and fabrication [CUED/A-TORBO/TR-21] N71-22374 A71-27413 GUSTS Ti, B ani qraphite fiber composites application to Power spectrum method for determininq qust aircraft desiqn, discussinq mechanical frequency response functions in dynamic aircraft properties and market competition desiqn A71-27676 N71-23211 GRAPRS (CRIIRTS) GYRO EORIZONS Predictinq aerodynamic characteristics of arrow, Inertial naviqation system consistinq of qyro delta, and diamond ring platforms usinq horizon compass, directional qyro and computer, Prandtl-Glauert transformation considerinq errors due to compass vibrations NASA-TH-0-62431 N71-21973 1171-27169 Effect of enqine position and hiqh lift devices on GYROCOBPASSES aprodynamic characteristics of external flow, Inertial naviqation system consistinq of qyro jet flap STOL model - qraphs horizon compass, directional qyro and computer, INASA-TN-D-6222 1 N71-23124 considerinq errors due to compass vibrations Estimatinq unsteady pressure distributions in T A71-27169 tail confiquration from measured distribution and theory [ NLR-TR-60048-L] N71-23131 H PorformancP test of sinqle staqe turbine with low AAIL solidity tandem rotor blade asspmbly Technoloqy review on electric automobiles, and NASA-CH-18031 N71-23132 modified T-33 aircraft system for pyrotechnic Low subsonic lonqitudinal aerodynamic hail suppression seedinq charactpristics of twin body space shuttle rDRE/NAE-1970/4/1 N71-22198 boostrr confiquration usinq low turbulence Rodified T-33 aircraft system for pyrotechnic hail prp:isurr tunnel - qraphs suppression seedinq [ NASA-TM-X-21621 N71-23135 N71-22200 GROGND CREWS AALL EFFECT 0pC.rational prfvaration and commissioninq of 1~-62 Beasurement of macroscopic aerodynamic quantities

A-211 SUBJECT IBDEI EOBETCOBB STBUCTOBES

in plasma jets produced by electrothermal and Normal and compound helicopters to be used as hall current accelerators short haul aircraft in view of burden on today’s N71-22639 air traffic control EABGABS N71-22189 Bare base shelterhangar expandable structures for HIGE ALTITUDE EIIVIBOIBEHTS rapid worldwide Tactical Fighter Organization Parachutes for low density atmospheres, describing deployment, noting foam and honeycomb low and high altitude test results fabrication [AIAA PAPER 70-11641 171-25525 [AIAA PAPER 71-3981 871-25274 HIGE ASPECT BAT10 EABDEIIIIS Three dimensional jet flapped wing matched Baterial properties, irpregnation, shaping, asymptotic expansion solution for high aspect hardening and structnral design in mass ratios based on thin airfoil theory assuming production of reinforced laminates for aircraft inviscid and incompressible flow construction 171-27217 A71-26954 Bigh aspect ratio planing surface gliding on EABBOBIC OSCILLATIOB infinitely deep, incompressible, inviscid, and Airfoils unsteady stall by testing two dimensional gravity-free fluid model in harmonic pitchinq oscillation for [ AD-717667 J N71-22345 helicopter rotor blades characteristics EIGE SPEED A71-27609 Bigh speed tracked air cushion vehicles dynamic EAUKEB SIDDELET AIBCBAPT interactions with quideways, considering model Operational performance of Bawker siddeley of lumped double-sprung vehicle masses traveling aircraft automatic flight approach and landing in tandem along simply supported beams control system [AIAB PAPER 71-3861 A71-25350 N7 1-2341 4 Plight test evaluation of military aircraft low BEAT FLUX altitude high speed performance Heat flux sensor adapted for mounting on aircraft N71-23421 or spacecraft to measure aerodynamic heat flux BIGE STBEIIGTE ALLOTS inflow to aircraft skin Tungsten reinforced oxidation resistant columbinn [NASA-CASE-XFR-O3802] N71-23085 alloys with operating temperature above 2000 P BEAT BESISTABT ALLOTS for use in gas turbine engines Superalloy dispersion strenqthened and fused [AD-7179691 1171-23673 slurry silicide coatings for aircraft gas HIGE STBEIIGTE STEELS turbine engines and suace shuttle heat shields Optical holographic interferometry for radial A71-25555 microcracks detection from bolt holes i”_hiqh Low allov steels an4 saperzllcys ineitia raiding strength aircraft steel in qas turbine field, discussing microstructnre [ ASHE PAPER 71-BET-C] 1171-27312 tensile strenqth and stress rupture HIGH TEBPEBATIJBE [ASHE PAPER 71-GT-211 A71-25965 Application of free fliqht ranges to high BEAT TBABSPEB temperature qas dynamics Equilibrium air boundary layer flows at three * 871-22633 dimensional staqnatiou points, discussinq flow Aigh total temperature sensing probe using fluid characteristics and real gas heat transfer oscillator concept for X-15 hypersonic aircraft parameters f NASA-CR-116772] 171-23250 [AIAA PAPER 70-809 J A71-27582 BIGE TEBPEBATUEE AIR BEAT TBAISPBB COEPPICIEIITS Bigh temperature aerodynamics with electromaqnetic Conference on high temperature turbines detailins raniition, corsiderizq thermalljr iailiating snock effect af fila couiing on blade profile loss layers, electric arc driven wind tunnels ana gas r NASA-TB-X-671231 mi-22699 dynamic lasers EELICOPTEB DESISII 1171-27277 Stability analysis and design optimization with HIGE TEBPERATOBE BESEABCH dynamics and aeroelastics constraints for Conference on hiqh temperature turbines detailing helicopter rotor blade minimua seisht with effect of film cooling on blade profile loss hendins torsion flutter and favorable fresuencv.. [ NASA-TR-X-67123] N71-22699 placenints EIGB PEBPERATOBE TESTS [AIAA PAPER 71-3881 A71-25352 Perfornance testing of fluorosilicone hydraulic Helicopter auxiliary power unit /APU/ life cycle fluid in high temperature supersonic aircraft cost computation piston pumps A71-26679 A71-27040 EELICOPTEB EBGIHES HODOGBAPES Belicopter jet propulsion systems. considerinq Bigh subsonic flow two dimensional turbine cascade turbocompressors. qas qenerators, turbine air design by approximate hodosraph method. notins jet systems. pulsed jet enaines, ramjet enqines pressure distribution measurements and rocket enqines [ASHE PAPER 71-GT-341 A71-25971 A71-25259 EOLOGBAPHT Investigation of helicopter jet engine flameout Asymmetric three dimensioLa1 aerodynamic density due to inqestion of scow and ice fields from holographic interferograms, applying I NRC-118931 N71-71977. - ._ to supersonic flou from free jet BELICOPTEB PBOPBLLEB DBIVE A71-25802 Laminar boundary layer transition, separation and Pulsed laser holographic applications to aerospace streamline direction on rotatinq helicopter components nondestructive testing, inspectinq blades electron beaa welds and internal structnral r NASA-TN-D-6321] N7 1-23779 flaws HELICOPTEBS [ASHE PAPER 71-GT-741 171-25988 Hntual aerodynamic effects of SH-1 helicopters Surface strain measurements in turbine blades by during simultaneous takeoff and landinq, time average holographic interferometry, determiuinq minimum distances between reviewing resonant modes and holographic frinqe helicopters patterns 171-26953 [ ASRE PAPER 71-GT-841 A71-25992 Helicopter operation as cranes and for external Optical holographic interferometry for cadial load transportation, discussinq operational and microcracks detection from bolt holes in hiqh economic aspects strenqth aircraft steel A71-27142 f ASHE PAPER 71-HET-Cl A71-27312 Conference proceedings on vertical takeoff EOIIETCOBB STBUCTORES aircraft technoloqy. notins tandem winq Boron-epoxy structural skins desiqn for F-14 aircraft, tilt winq aircraft, helicopters, lift honeycomb horizontal stabilizer, usinq computer fans. and jet enqines program [ DLR-HITT-70-151 mi-22186 871-25420

A-25 89-748 AIRCRAFT SUBJECT INDEX

HS-748 AIRCRAFT Analysis of supersonic and hypersonic flow of Landinq accidents investiqations for Hawker inviscid ideal gas over conical winqs with sharp Siddelev 748 aircrafts with performance leading edges and attached shock waves by three measurements on rouah surfaces dimensional method of characteristics N71-23417 [ NASA-CR-17383 N71-22672 EUISAN FACTORS ENGINEERING Hypersonic wind tunnel test on conical and ogival Transfer functions in modellin4 human pilot and nosed static pressure probes dynamic structural aircraft response; 29L/A-327! N71-23778 f AGARD-B-58@-71] N71-23210 Wind tunnel surface-flow visualization of delta Human factors and safety requirements in aircraft winq shuttle configuration at nach number of 7.4 desiqn and several Reynolds numbers N71-23423 [NASA-TN-X-62036 ] N71-23953 Human factors and control system failures in jet HYPERSONIC BEAT TRANSFER upsets durinq turbulence encounters Enthalpy and wall heat flux calculations for N71-23424 stagnation region aft of blunt axisymmetric Flyinq safety factors in close to ground bodies in hypersonic axial flow operational desiqn of XH-51 helicopter [AD-7174181 N71-22087 N71-23430 HYPERSONIC INLETS Identification and control of aeromedical factors Use of qun tunnel as low temperature test facility associated with aircraft noise and acoustic for hypersonic intake research measurements dUKinq C-lul operational missions N71-22635 r AD-718097 i N71-23748 HYPERSOIIIC SPEED AYBRID COMPUTERS Effect of heat conduction of material on Complex real time hybrid computer simulator for temperature distribution in vicinity of wins captive two blade rotor platform dynamic problem leading edqe in hypeKsoniC fliqht solvinq [ REPT-690 1 ] N71-22494 A7 1-2 5847 Wind tunnel investigation of hypersonic transport Six deqree of freedom hybrid diqital computer model aerodynamic characteristics at nach proqran for compiex fliqht control and numhers to 6 - graphs associated mode loqic desiqn and traininq [NASA-TN-D-61911 N71-23127 A71-25852 HYPERSONIC VEEICLES HYDRAULIC FLUIDS Hypersonic cruise vehicles biscous interactions Performance testinq of fluorosilicone hydraulic areas, examininq compression corners, shock fluid in hiqh temperature supersonic .aircraft interactions, laminar and turbulent flow, piston pumps boundary layer separation, etc A71-27040 [AIAA PAPER 70-7811 A71-27551 HYDROCARBON FUELS Enqineering desiqn analysis of hydroqen cooled Evaluation of Aqua-Glo free water detector for use structural pacels for application to hypersonic in neasurins undissolved water in hydrocarbon aircraft fuels r NASA-CR-16501 N71-22625 r AD-7184la 1 1371-23438 HYPERSONIC WAKES HYDRODYNAIICS Hypersonic wakes of two dimensional slender wedqes Unsteady hydrodynauic loads on two dimensional and flat plate, testinq stahility in transition hydrofoil reqion in wind tunnel r AD-7179'531 N71-23591 A71-27561 HYDROFOILS AYPERVELOCITY PLOW Unsteady hydrodynamic loads on two dimensional Time asymptotic solutions for hypervelocity blunt hydrofoil body flow field wit.h coupled nonqray radiation, r AD-717953 1 N71-23591 treating shock as discrete surface HYDROGEN FUELS fAIAA PAPER 70-8651 A71-25453 Supersonic combustion, fuel injection, and HYPERVELOCITY WIND TUNNELS recirculation in hydroqen hypersonic external Pressure orifices inclination in low density flow combustion at flat plates and bodies of from experiments with cooled flat plate model in revolution hypersonic low density wind tunnel IDLR-FB-70-64 1 N71-22129 A71-25490 EYPERBOLIC FUNCTIONS Isentropic-compression tube techniques producinq Time dependent asymptotic solution for transonic hypersonic flow in wind tunnels includinq flows in hyperbolic nozzle and turbine cascades isentropic flow and free-piston shock tube modes with oblique shock [AD-7177271 N71-22158 rasns PAPER ~I-GT-~z] A71-25975 Fabrication and tests of C02 flat plate models in HYPERSONIC FLIGET He hypersonic wind tunnel Shock interaction effects on flapped delta winq at [SC-CR-69-32151 N71-23228 hypersonic speed, presentinq method for Effects of flow contaiuinq dust on results of estimating reflected expansion wave impingesent hypersonic wind tunnel experiments boundaries and resultinq aerodynamic [NASA-TT-F-135291 N71-23702 coefficients A71-27598 AYPERSONIC PLOW I Underexpanded transverse sonic jet-hypersonic IDEAL FLUIDS stream three dimensional flowfield based on Ideal incompressible fluid flow around fixed inviscid rotational flow moZel obstacle near rectilinear wall, investiqatinq A71-25472 plane motion with profile couple mrthod Reentry vehicles confiquration lift and draq All-2625R coefficients in hypersonic flow from pressure Three dimensional incompressible flow about distribution and balance measurements, comparinq slender foil in perfect fluid, stressinq v0rtt.x with isolated cone data field effect 171-2'5487 171-27477 Small surface curvature effect on unsteady IDEAL GAS hypersoltic flow over thiri oscillatinq wedqe, Steady supersonic isoenerqetic flow ot thermally usinq Perturbation theory and calorically perfect qas past circular cones A71-26197 at zero anqle of attack, usina dimensional Thin delta winq in hypersonic inviscid flow at perturbation method small anqles of attack, calculatina motion 171-26939 equations and boundary conditions at small IL-62 AIRCRAFT perturbations Operational preparation and coamissioninq of IL-62 A71-2733@ lonq distance jet aircraft, considering fliqht Schlieren and phase contrast acthods of hypersonic crew and maintenance personnrl traininq at flow visualization U.S.S.R. plant N71-22637 All-252'56

A-26 SUBJECT IEDEX IETERPEROIETRI

Pliqht and operation of IL-62 long distance let IEERTIAL lATI6ATIOll aircraft, considering flight crew composition Inertial navigation system consistinq of gyro and training, passenqer and carqo handlino and horizon compass, directional qyro and computer. refueling considering errors due to compass vibrations 1171-25260 A71-27169 ILIUSEIE AIRCRAFT IIIPLATABLE STRUCTURES Flexible runway snrfaces classification by LCN Design, fabrication and static testing of attached method, calcnlating for Ilyushin aircraft inflatable decelerator models for snpersonic 871-26201 wina tunnel evalnation IIPACT LOADS [NASA-CR-l11831] X71-22538 Analysis of normal acceleratioos through center of Numerical analysis of influence coefficients, qravity of aircraft due to landing impacts ar;d natural frequencies, and mode shapes of qround operations associated with taxi, takeoff, vibration of triangnlar inflatable winq and landing 1171-22666 [NASA-TIN-D-61241 171- 22620 Steady state inflated shape and included voluae of IIPELLERS 24 and 30 gore flat circular, extended skirt, Plow variation effect on velocity and flow anqle porous ring slot, and porous ribbon parachutes distribution at exit of shrouded radial flow r AD-718808] N71-23387 impeller with backward swept blades, usino IIIPLATIUG streamline curvature method Inflation of initially spherical balloon of [ASUE PAPER 71-GT-153 A71-25961 elastic rubber-like material. discussing tensile Impeller blade loading vorticity on stream surface instability of revolution for mixed flow coapressor, nsinq A71-25445 annular cascade theory ISPBARED IIISPECTIOS [ASIE PAPER 71-GT-171 1171-25962 Traversinq Infrared Inspection System for C-5 Tvo dimensional flow in radial turbomachine bladed aircraft fail-safe strap panels of bonaed Ti-A1 impeller. comparing numerical solution based on laminates, discussinq desiqn and application potential theory with experimental results lASIE PAPER 71-DE-371 A71-27327 fASIE PAPER 71-GT-201 A71-25964 IlGBSTION (EIIGIEES) IIPREGEA'ZIlG Investioation of helicopter jet enqine flameout material properties, impregnation, shaping, due to inqestion of snow and ice hardeninq and structural design in mass [NRC-l1893] N71-21927 production of reinforced laminates for aircraft IIIJECTORS construction Low pressure drop fuel liquid injectors for jet 171-26954 engine combustors, using gas turbine vaporizer 11-PLIGHT IOlITORIlS desi- Lou-izertia fiou-direction vane static and dynamic [ ASUF PAPER 71-GT-381 A7 1-25972 wind tunnel tests at subsonic and snpersonic IELBT PLOV speeds for in-fliqht measurement of bust Three dimensional bonndary layer flou and velocity velocities profiles in mixed diffuser uith equal anqle [NASA-TR-D-6193] N71-23115 ualls Airborne equipment for approach path control on [ASRE PAPER 71-61-40] A71-25073 reduced noise trajectories in Boeing transport Quasi-three dimensional surface velocities and aircraft traffic choking flow for tnrboaachine blade rows 171-23425 calculated by FORTRAN program ISCOIPRESSIBLE PLOW fNASA-TI-D-67777 N71-23126 Prandtl first order boundary layer equations for IUSPECTIOE tu0 dimensional laminar incomoressible flov pact ;eteirination of inspection intervals and nature circulation controlled circular liftinq rotor of inspections for safe and economical operation A71-25494 of aircraft structures Three dimensional incompressible flow about [PFA-120] N71-22431 slender foil in perfect fluid, stressing vortex INSTBUIIEIIT APPROACE field effect Index of standard instrument approach procedures A71-27477 for domestic and foreiqn airports Ouasi-axisymmetric and superposed fine fluctuating 171-23233 structure of ideal incompressible vortex flows operational performance of Hawker Siddeley in axial flow turbines, assuminq infinite mutual aircraft automatic fliqht approach and landing blade proximity control system A71-27714 171-23414 Nonlinear limit rotation velocity and circulation IlSTBUIElT ERRORS induced by wheel in axial flow turbomachine for nodulation cancellation altimeter error analysis incompressible ideal fluid, using iterative and performance optimization numerical algorithm 1171-27437 A71-27715 IlSTBUIElT LAlDIlG SISTEIIS Graphical computer simulation of incompressible Radio frequency interference monitoring for flow about airfoil instrnment landing system in automatic landing [ TE-71-21 17 1-22 149 [ RAE-TR-700763 E71-23356 IICOIPRESSIBLB ?LOIDS Landinq systems signal reflection interference on Ideal incompressible flnid flow around fixed correlation protected instrument landinq system obstacle near rectilinear vall, investigatinq beams Plane motion with profile couple method [ RAE-TR-701411 N71-23361 171-26258 IITEBPACIAL TEES101 IEDEP1lDElT VARIABLES Initially spherical liquid droplet transient Equation error approach to parameter response under surface tension accelerated by identification in third order pitch plane external gas flow dynamics for high performance aerodynamically [AIAA PAPER 71-3931 A71-25355 controlled aerospace vehicle IlTERPERElCE 171-26418 aethods for predicting speecb interference uithin IIDEXES (DOCUIEl'ZATIOl) cockpits of fixed winq and rotary winq aircraft Tabulation of B-57 aerial cloud photography of I AD-7180981 N 7 1-2,352 8 tropical convection systems for 11 to 28 July IlTEEPERElCE LIFT 1969 with flight path over Barbados Islands Collocation method predicting oscillatory snbsonic [ESSA-TU-ERLTI-BOIAP-11 N71-23746 pressure distributions on interferinq parallel IIERTIA PRIICIPLE liftinq surfaces, considering approach more Jet engine components inertia velding. discnssing economical than finite element method process, eqnipment. low weight-cost advantaqe [AIAA PAPER 71-3291 A71-25309 and mechanical properties reproducibility IlTEEPEROIETBI rASIIE PAPER 71-62-33] 1171-25970 Asymmetric three dimensional aerodynamic density fields from holographic interferoqrams, applying

1-27 INTERNAL COMBUSTION ENGINES SUBJECT INDEX

to supersonic flow from free jet JET AIRCRAFT A71-25802 Jet aircraft airuorthiness standards, discussinq Surface strain measurements in turbine blades by airline fleet maintenance resources. inspection time averaqe holooraphic interferometry, systems and future requirements reviewino resonant modes and holoqraphic fringe A71-26308 patterns JET AIRCRAFT NOISE r ASNE FAPER 71-GT-E4 J R71-25992 Development and description of basic descriptors Optical holoqraphic inteLicioiditr7 far radi.1 used to analyze jet enqine noise, aircraft microcracks detection from bolt holes in hiqh noise, and noise level of aiipuiis strength aircraft steel N71-21980 [ASNZ PAPER 71-NET-CJ A71-27312 Noise characteristics of circular double jet INTERNAL COHBUSTION ENGINES issuins from 3 cm and 6 cm diameter nozzles One dimensional flou models of internal combustion compared uith those of sinqle jet enqine exhaust silencers in noisy systems NAL-TR-212 1 N71-22469 A71-25180 Determination of low speed jet noise from fan INTERNATIONAL COOPERATION enqine for simulated nacelle confiquration Us cooperation uith ESRO UHF satellite system r NASA-TN-D-63141 N71-23134 development for air traffic control in Europe Identification and control of aeromedical factors {NASA-TT-F-136511 N71-23967 associated uith aircraft noise and acoustic INVARIANCE measurements durinq c-141 operational missionsN71-23748 Aircraft lonqitudinal coordinates invariance r AD-7180971 relative to atmospheric disturbances, qivinq Jet noise contribution to far field Sound from simultaneous thrust variation, rudder deflection 1.03 meter diamctpr fan determined for tu0 and flap deflection control rules simulated nacelle confiqurations A7 1-27339 r NASA-TM-X-67825 1 N71-24F09 INVISCID FLOW JET BOUNDARIES steady three dimensional subsonic nonviscous flow Curvatore effects on laminar and turbulent free throuqb turbomachine vith arbitrary hub and jet boundary between irrotational flow and shroud shapes and finite blade number, usinq staqnant fluid, discussinq pressure effectsA71-25482 iterative blade to blade procedure [ ASRE FRPEE 71-GT-2 1 A71-25048 Plane and circular turbulent let boundary layer Thin delta winq in hypersonic inviscid flow at expansion in slipstream, comparina analytical small anqles of attack, calculatins motion uith experimental results A71- 27505 equations and boundary conditions at small perturbations JET ENGINE FUELS P. 7 1 - 27 3 3 0 Jet fuel starter, describinq small 48s turbine for Application of inteqral relations to inviscid starter, providing sufficient pressurized qas supercritical flou over symmetric airfoils at flow to rotate main enqine zero anqle of attack r ASflE PAPER 71-GT-U3 J A71-25976 [AD-7173391 N71-2200R Jet fuels deoxyqenation effects on steels antiwear Nueerical analysis of inviscid flou fields about properties and critical loadinq under pointed circular cone and conical winq-body vibrdtional and glidinq friction confiquration at various anqles of attack A71-27662 N71-22667 Tests of jet enqine fuels to determine effects of Asymptotic solution of low frequency uinq sloshins and vibration in aircraft fuel tanks on oscillations in transonic shockless adiabatic flammability hazards inviscid qas flow bascd on complete r AD-718091 1 N71-23805 approximation JET ENGINES N71-23193 Jet enqine components inertia ueldinq, discussinq ISBNTROPIC PROCESSES process, equipment, low ueiqht-cost advantaqe Isentropic-compression tube techniques producinq and mechanical properties reproducibility hypersonic flow in wind tunnels includinq r ASNE PAPER 71-GT-33 J A71-25970 isentropic flou and free-piston shock tube modes Low pressure drop fuel liquid injectors for jet r AD-717727 J N71-22158 enqine combustors, usinq qas turbine vaporizer ISOENERGETIC PROCESSES desiqn Steady supersonic isoenerqetic flou of thermally [ASflE PAPER 71-GT-381 A71-25972 and calorically perfect gas past circular cones Iuvestiqation of helicopter jet enqine flameout at zero anqle of attack, usinq dimensional due to inqestion of snow and ice perturbation method r NRC-118931 N71-21927 A71-26939 Conference p;oceedinqs on vertical takeoff ISOTROPIC TURBULENCE aircraft technology, notinq tandem wins Analysis of effects of spanuise variations of qust aircraft, tilt uinq aircraft, helicoptprs, lift velocity in isotropic turbulence on fans, ani jet enqines vane-controlled gust alleviation system r DLR-NITT-70-151 N71-22186 TNASA-TN-D-6126 J 871-22068 DO-231 V/STOL airdraft des: qn, notinq passenqer ISRAEL comfort, aerodynamic noise, aerodynamic Planninq for Boeinq 747 aircraft intearation into characteristics, and cost analysis Israel airline operations N71-22187 N71-22388 Theoretical analysis of jet mixinq under influence Intrqrated systems approach for developinq of nonconstant pressure qradient requirements of increased civil aviation in r ARL/NE- 127 J N71-22503 Israel JET EXHAUST N71-22391 Structure constant of jet exhaust turbulence of 5-57 with afterburner by laser beam probinq compared with scintillation and hot-uire J anemometer measurements 5-57 ENGINE A71-26304 StructurP constant of let exhaust turbulence of Air pollutinq nitric oxide and soot production by J-57 uith afterburner by laser beam probinq jet aircraft, discussinq mixinq process and compared uith scintillation and hot-uire atmospheric dispersion anemometer mrasurements r AIAA PAPER 70-1151 R71-27560 A71-2630U Interference phenomenon of subsonic turbulent jet J-85 ENGINE exhausts from flat plate in low speed cross flou Wind tunnel tests for instantaneous and dynamic TAD-7187981 N71-23314 analysis of effects of time-variant distortions JET FLAPS produced in supersonic inlet on J85-GE-13 Approximation of flow around jet flapped airfoil, turbojet rnqine discussinq qround effect on lift coefficient NASA-TH-X-678211 N71-23927 increments A71-26314

1-28 SUBJECT IADEX LATERAL COIITROL

Three dimensional jet flapped wing uatched Prandtl first order boundary layer equations for asymptotic expansion solution for high aspect two dimensional laminar incompressible flow past ratios based on thin airfoil theory assuming circulation controlled circular lifting rotor inviscid and incompressible flow A71-25494 A71-27217 Bypersonic cruise vehicles viscous interactions Effect of engine position and high lift devices on areas, examining compression corners, shock aerodynamic characteristics of external flow, interactions, laminar ana turbulent flow. jet flap STOL model - qraphs boundary layer separation, etc [ NASA-TN-D-62221 N71-23124 [AIAA PAPER 70-781] A71-27551 JET PLOW Combined free and forced laminar convective heat Underexpanded transverse sonic jet-hypersonic transfer to nonNewtonian fluids flowing in stream three dimensional flowfield based on constant wall temperature vertical tubes and inviscid rotational flow model controlling parameter analysis A71-25472 N7 1-22702 Sound generation by small perturbation jet flow Sound generation by small perturbation jet flow [ DLR-PB-71-02] N71-23596 r DLR-PB-71-02] 871-23596 JET IIPIAGEIEIIT LAIINAB WAKES Screech noise generation by supersonic jet Plat plate trailinq edge problem solution impingement on flat plate, discussing jet consistent with second order boundary layer disinteqration mechanism with resultant shock theory, establishing laminar wake evolution wave oscillations nature and upstream influence A71-25521 871-25469 JET LIFT naqnetically suspended laminar supersonic cone Optimal blowing wall jet prediction for wake stability from hot wire fluctuation and suppressinq separation from hiqh lift aerofoils spectral components amplitude/phase measurements with incomplete mixing of upstream boundary A71-25475 layer LAIIDIllG A71-26196 lutual aerodynamic effects of S8-1 helicopters Finite-element potential flow modelinq for durinq simultaneous takeoff and landinq. predicting round lifting jet rolled up geometry determininq minimum distances between and path converqent into cross-flowinq helicopters mainstream as on VTOL or STOL aircraft 1171-26953 r AD-718121 ] N71-23475 LANDING AIDS JET PROPIJLSIOII Technical aspects of tactical all-weather Relicopter jet prouulsion systems, considerina instrument landinq system of Swedish STOL turbocompressors. gas generators, turbine air aircraft Sazb 37 Viggei jet systc:s, pnlsrd jet engines, ramjet enqines A71-25233 and rocket enqines Report on quidance system for approach and 1171-25259 landinq. discussing airports, aircraft, approach JP-5 JET FUEL and landing paths, service classes, f4ilure Electrostatic charqe by JP-5 jet fuel at truck protection and weather penetration fill stand with 30-second relaxation chamber and A71-25534 bottom loadinq Aviation qround lightinq. visual landing aids, [ AD-7 17347 1 N71-22232 dual baseline transmissometer, photometric measurements of deck-landinq projector siqht. and lamp for Fresnel optical landino system K [ NBS-105081 N71-22U56 KALOA1- SCBlIDT PILTERIIIG ;hipb.s,rd test proceaure of Fresnel lens optical Kahdn linear least squares filtering applied to landinq system M 6 ROD 2 for carrier landings estimation of fuel quantity and rate for fiqhter [AD-718335) N71-23488 aircraft LARDING GEAR [ AD-7 17640 ] N71-21922 Power spectral density analysis of aircraft KUTTA-JOUKOWSKI COADITIOA structural response to taxiing produced randon Aele-Shaw flow viscous tails from airfoil, vibrations involving landinq gear orifice observinq hiqh Reynolds number trailing edqe dampina and Coulomb friction flow for separation and initiation of Kutta 171-2631 1 condition LAADIllG LOADS 871-26447 Analysis of normal accelerations through center of qravity of aircraft due to landing impacts and qronnd operations associated with taxi, takeoff, L and landing LAIIAAB BOUADAFIl LATER '[NASA-TN-D-61241 N71-22620 Reattachnent angle of supersonic laninar mixed Developnent of mechanistic models for predictins boundary layer, using revolution model with behavior of landing mat systems Reynolds number allowance N71-22891 A71-26194 LARDING SIIIJLATIOA TWO dimensional laminar boundary layer eqnation Development of mechanistic models for predicting local drag coefficient from one and two term behavior of landinq mat systems nerk expansion in reqions upstream of staqnation N71-22891 point LAIIDIIS SITES A71-27051 Tables and maps of selected landina airfields for Laminar boundary layer perturbation by sinusoidal shuttle orbiters with various crossranqes wall rouqhness, analyzinq effect on transition I RASA-Tll-X-67080 1 N71-21995 nature and position Development of mechanistic models for predictins A71-27470 behavior of landinq mat systems Laminar boundary layer equations for rotatinq N71-22891 Plate uith surface of arbitrary curvilinear LASERS shape, determininq external flow pressure Structure constant of jet exhaust turbulence of qradient leadinq to separation 5-57 with afterburner by laser beam probina A71-27502 compared with scintillation and hot-wire Laminar boundary layer on winq and body of anemometer measurements revolution in presence of blowinq 871-26304 INA SA-TT-P- 13627 1 N71-23796 LATERAL COATROL LAOIAAB PLOS iiinq design criteria imposed by hiqh speed Curvature effects on laminar and tnrbulent free reqnirement for short takeoff aircraft, jet boundary between irrotational flow and considering thin sweptback wing with small staqnant fluid, discussinq pressore effects aspect ratio for lateral control 171-25482 1171-27471

A-29 LEADING EDGE SUEEP SUBJECT IIIDEX

LEADING EDGE SUEEP LIFTING BODIES Flaps and leadinq edge modifications for improved Liftinq surfaces supersonic-hypersonic flutter at aerodynamic control stability of military angle of attack determined by shock expansion, aircraft Nertonian flow and local flow piston theory N71-23422 [AIAA PAPER 71-3271 A71-25307 LEADING EDGES Lift and particle displacement around liftinq body Effect of heat conduction of material on with stream function as fluid motion equation tenpsiatore distribzticn :I! vicinity of winq inteqral leadinq edqe in bypetsonic flight aii-27577 REPT-6901 ] N71-22494 aulthopps subsonic liftinq surface theory, Using construction of leadinq edqes of surfaces for least squares method aerial vehicles performinq from subsonic to TNAL-TN-241 N71-22472 above transonic speeds LIFTIUG ROTORS TNASL-CASE-XLA-01486 1 N71-23497 Comparative vertical turbulence and loss LEARUIIIG TEEORT restrictive stochastic models for threshold Adaptive self-orqanizinq and -1earninq control crossinq rotor blade flapping vibrations at low systems with lonq and short term memory lift hiqh advance ratio retention, usinq loqic random searches to find [AIAA PAPER 71-3891 A71-25351 parameter values Prandtl first order boundary layer equations for [ ASRE PAPER 71-DE-221 A71-27324 two dimensional laminar incompressible flow past LEAST SQUARES UETEOD circulation controlled circular liftinq rotor Kalman linear least squares filterinq applied to A71-25494 estimation of fuel quantity and rate tor fiqhter narqinal vortex effects oc aerodynamics of aircraft helicopter liftinq surfaces, considerinq blade r AI)-7 17640 1 N71-21922 form and noise spectrum tested in hydrodynamic aulthopps subsonic liftino surface theorv. usino tunnel least squares method 1171-27473 r NIL-TN-24 ] N71-22472 LIGET SCATTERING LIFT Photometric observations of auroral scatterinq by Reentry vehicles configuration lift and draq CV 990 aircraft coefficients in hypersonic flow from pressure T NASA-CR-117466 1 N71-22135 distribution and balance measurements, comparinq LIGETEILL GAS MODEL with isolated cone data solution of Lighthill gas model wave equation for 871-25487 enqine noise qeneration in circular jets notinq Approximation of flow around jet flapped airfoil, cylindrical coordinate system discussinq qround effect on lift coefficient T DLR-FB-70-57 1 N71-22070 increments LIGETRILL METHOD A7 1-263 14 Aerodynamic noise scatterinq near Liqhthill Liftinq force of winq with rotatinq flap, derivinq multiples, considerinq intense near-field energy lift increase due to circulation redistribution conversion into sound waves at surface A71-26448 A71-27491 LIGRTIUG EQUIPMERT Litt and particle displacement around liftinq body Performance tests and characteristics of capsule- with stream function as fluid motion equation type and prismatic-head liqhts used for airport inteoral approach and runway lighting systems A71-27577 [ NBS-101211 N71-22453 Hind tunnel investiqation of lift-induced sonic LIBEAR SYSTEBS boom characteristics of two simple winq models Simplified linear quidance and control for keeping at aach numbers from 2.3 to 4.63 trajectory deviations minimal r NASA-TN-D-6201] N71-23125 TAD-7175671 N71-219 15 LIFT DEVICES LIQUID ATO!¶IZAT~ON Liftinq surfaces supersonic-hypersonic flutter at Breakup mechanism of liquid sheets and jets in anqle of attack determined by shock expansion, supersonic qas stream, usinq spark Newtonian flow and local flow piston theory photomicroqraphs and hiqh speed movies [AIAA PAPER 71-3271 A71-25307 A71-25471 Vertical straight lift turbojet enqine desiqn and LIQUID SLOSEIUG development, presentinq component materials TeStS of jet enqine fuels to determine effects of properties/weiqhts, endurance tests and sloshinq and vibration in aircraft fuel tanks on performance data tlaomability hazards r ASflE PAPER 71-GT-75 J A71-25989 AD-7180911 N71-23805 Hiqh lift winq Characteristics with/without LOAD DISTRIBUTIOII (FORCES) additional devices, emphasizinq lift control and Hiqh lift wino characteristics with/without load distribution additional devices, emphasizinq lift control and A71-27476 load distribution Effect of engine position and hiqh lift devices on 171-27476 aerodynamic characteristics of external flow, LOADIIIG OPERATIOIIS 'jet flap STOL model - qraphs Tu-154 responsibilities of three-man crews, I NASA-TN-D-6222 ] N71-23124 considerinq fliqht plan, refuelina, carqo LIFT FANS loadinq and unloading Discrete frequency rotor interaction noise from All-25258 lifting fans, usinq force harmonics actinq on Fliqht and operation of IL-62 lonq distance jet blades aircraft, considerinq flight crew composition [ASME PAPER 71-GT-121 A71-25958 and traininq, passenqer and carqo handlinq and Free fliqht tests in hooverinq and forward fliqht refuelinq of V/STOL transport model with six winq-mounted All-25260 lift fans LOADS (FORCES) NASA-TN-D-6198 1 N71-22069 Flexible runway surfaces classification by LCN short haul vertical takeoff aircraft with lift method, calculatinq for Ilyushin aircraft fans incorporated in aircraft body, notinq wide A71-26201 aircraft compartment sailplanes tail load static derivation for N71-22190 instantaneous unchecked lonqitudinal maneuver, Gas qenerators as vertical takeoff aircraft enerqy considerinq aperiodic response sources to operate lift fans or helicopter A71-26486 rotary winqs Unsteady hydrodynamic loads on two dimensional N71-22194 hydrofoil Comparison of two lift fan confiqurations usinq TAD-7179531 N71-23591 wind tunnel aodel pressure distributions LOIIGITUDIUAL COITROL N71-22195 sailplanes tail load static derivation for instantaneous unchecked lonqitudinal maneuver,

A-30 SUBJECT IIDBX MEASUBIIG IISTRUMENTS

considerinq aperiodic response Data reduction techniques for deriving aerodynamic A71-26486 forces and moments in absence of support Aircraft lonqitudinal coordinates invariance interference relative to atmospheric disturbances. qivinq [ NASA-CR-111844 ] N71-23122 simultaneous thrust variation, rudder deflection EANAGBEEIT PLAIII16 and flap deflection control rules soviet airlines operations planninq. discussinq All-27339 principal objectives, methodoloqy and LONGITUDINAL STABILITY organizational principles wind tunnel evaluation of analytical method for A71-27144 predicting lonqitndinal stability and planning for expected civil aviation developments aerodynamic characteristics of large flexible caused by change-over to Boeinq 747 aircraft and aircraft applied to supersonic transport Supersonic transport confiquration N71-22381 [AIAA PAPER 71-3431 A 7 1- 2 5 3 2 2 Planning for civil aviation operations inclndinq LOUVERS Boeiaq 747 aircraft and snpersonic aircraft Axial flow fan noise, investigating louvers mi-22382 effects on sound field Economics and operational planninq for future 871-26704 civil air transportation LOP ALTITUDE 971-22384 Plight test evaluation of military aircraft low Planninq for Boeing 747 aircraft inteqration into altitude hiqh speed performance Israel airline operations N71-23421 A71-22388 LOP ASPECT BAT10 Support systems planning for expanded passenqer Rotatinq low aspect ratio turbomachinery blades and cargo traffic in civil aviation natural frequencies and mode shapes, nsinq 1171-22390 finite element method for equilibrium equations EAPS eigenvalue problem Tables and maps of selected landing airfields for [AIAA PAPER 71-3741 A71-25347 shuttle orbiters with various crossranqes LOP DENSITY PIlD WllELS [ NASA-Tfl-X-670801 W71-21996 Pressure orifices inclination in low density flow MARIUE PBOPULSION from experiments with cooled flat plate model in Aircraft gas turbine condition analysis hypersonic low density wind tunnel instrumentation used for status diaqnosis oE A71-25490 naval turbine enqines, discussing sensor and LOW SPEED PIED TUINELS electronic data interpretation progress Estimating unsteady pressure distributions in T [ ASnE PAPER 71-GT-86 ] A71-25994 tail configuration from measured distribution EABKET BESEABCE and theory Boron and qraphite fiber market competition. r Ala-TR-58318-i 871-23131 considerinq aerospace application LOP TEEPBBATUBB A71-25400 Use of qun tunnel as low temperature test facility Comparison of automobile, rail transportation, and for hypersonic intake research short haul aircraft performance by means of N71-22635 market research noting central city airports LOP TUBBULEICB N71-22192 Dependence of low turbulence flow in supersonic IIASS DISTBIBUTIOI wind tunnel on conditions in supply header Sweptback thin cantilever winq transonic flutter [AD-7182271 171-23480 density and velocity coefficients, inrestiqatinq LUBBICATIIG OILS engine pod shaped concentrated nass location Friction points. and oil system of aviation qas effects turbine engines A71-25189 [AD-717833 1 871-22011 MATERIALS SCIBICE LUlAB ESCAPE DEVICES Abstracts of papers presented at US Air Force Design and developaent of lunar escape system materials symposium held at Miami Beach, Florida simulator for investigation of lnnar escape in May, 1970 problems and simplified manual guidance and [AD-7184321 1171-23625 control for lunar escape vehicles MATEEIATICAL MODELS [ NASA-TN-D-61111 N71-22590 Aircraft tires mechanical data from small models, LUIAB OBBITBB discussing mechanical properties, tire stresses Wind tunnel tests to determine sonic boom and tire temperatures characteristics of straight wins and delta winq [AIAA PAPER 71-3461 A71-25325 space shuttle durinq reentry into earth Riqh speed tracked air cushion vehicles dynamic atmosphere interactions with guideways. considerinq model fNASA-TM-X-62030] 871-23296 of lumped double-sprung vehicle masses traveling in tandem along simply supported beams [AIAA PAPER 71-3861 A71-25350 M Patique failure probabilistic model nuder variable MACE IUMBBB amplitude loading, considerinq relation between Triple Point trajectory of shock-shock Bach safety factor and fatigue failure probability reflection off plane wall, comparinq to Whitbam A71-25492 theory Variable sweep winq aircraft anqular motion A71-26192 mathematical model, analyzing inertial moments IIACHIIB TOOLS influence on control dynamics noire effect analysis of stress and strain of A71-25661 machine parts and structural elements plow field model for steady asymmetric vortex f AD-7178261 A71-22168 system shed from slender body of revolution in MA61BSIUI ALLOTS coning motion Comparison between silicon-magnesium-aluminum [AIAA PAPER 70-521 1171-27552 alloy and copper aircraft electric conductors Engineering design analysis of hydrogen cooled and terminals notinq types of tests structural panels for application to hypersonic TTRC-BB-197851 1171-23547 aircraft IAGIBXIC IBDUCTIOI rtIaSA-CR-16501 N71-22625 Analysis of solid rotors used in hiqh speed Transfer functions in modellinq human pilot ‘and induction motors for aerospace applications dynamic structural aircraft responses N71-21898 [ AGARD-R-580-71] N7 1-2 32 10 IAGIBTIC SUSPBISIOII Fabrication and tests of C02 flat plate models in Eaqnetically suspended laminar supersonic cone Be hypersonic wind tunnel wake stability from hot wire fluctuation and f SC-CR-69-32151 871-23228 spectral components amplitude/phase measurements MEASUR116 IISTBUMBITS A71-25475 standard equipment and procedures for aircraft qas turbine engine exhaust smoke measurement

A-31 MECAANICAL DRIVES SUBJECT INDEX

[ AS8E PAPER 71-GT-88 1 A71-25995 Hilitary aircraft fliqht test establishments, MECAANICAL DRIVES discussing airframe, enqine, fliqht control and Boron-qlass-epox7 liqhtweiqht composite gear case weapons delivery systems tests work flow for aircraft enqine reduction qearbox, integration requirements describing design, moldinq, machininq and A71-26315 testinq Terrain following radar for airborne guidance of [ASflE PP.PER 71-GT-851 A71-25993 low flvinq military aircraft A71-26881 nECBfitiiCii PBOPERTSES Aircraft tires mechanical data from small models, fliqht test evaluation of military aircraft low discussinq mechanical properties, tire stresses altitude hiqh speed performance N71-23421 and tire temperatures rAIAA PAPER 71-3461 A71-25325 MILITARY AVIATION naterial properties, impreqnation, shapinq, Foq clearance from airport runways, discussing hardeninq and structural desiqn in mass available techniques, economic aspects ana production of reinforced laminates for aircraft importance for military operations construction A71-27247 A71-26954 MILITARY AELICOPTERS METAL COATINGS Fliqht safety performance of V/STOL Sarrier Superalloy dispersion strenqthened and fused military aircraft havinq jet control slurry silicide coatinqs for aircraft qas N71-23427 turbine enqines and space shuttle heat shields MINIl%Uf! DRAG A71-25555 Minimum draq surface shape of thick liftinq delta METAL MATRIX COMPOSITES winq inteqrated with conical fuselaqe for netal matrix composite fabrication procedures for supersonic cruisinq speed qas turbine enqine fan blades, stressinq A71-27716 diffusion bondinq process susceptibility to nIss DISTANCE blades volume producibility Midair collisions analysis for civil-military [ASRE PAPEE 71-GT-461 A71-25979 inteqrated ATC air space, discussinq near miss Desiqn and fabrication of Borsic aluminum volume, random headinq aircraft density and composite fan blades for supersonic turbofan pilots evasive action vs avoidance percentaqes enqines, considerinq 430 F application without A71-27509 severe vibratory stress Radar avoidance action loqic for converqinq [ASRE PAPER 71-GT-901 A71-25997 aircraft safe passaqe, discuosinq near miss and Tunqsten reinforced oxidation resistant columbium collision situations alloys with operatinq temperature above 2000 F A71-27600 for use in qas turbine enqines MODAL RESPOUSE r AD-7179691 N71-23673 Rotatinq low aspect ratio turbomachinery blades METAL PLATES natural frequencies and mode shapes, usinq Fliqht service effects on residual tensile finite element method for equilibrium equations properties of C-130 aircraft center win4 plate eiqenvalue problem section [AIAA PAPFR 71-3741 A71-25347 [NASA-CR-1118281 N71-24021 nodal characteristic pick-up system for vibration METAL-METAL BONDING tests of rockets or aircraft on qround, usinq Fatique life, fail-safe capa,bility and corrosion small size accelerometers with individual resistance of commercial aircraft structures electronic circuit improved throuqh adhesive metal-metal bondina A71-27719 rAS!'E PAPER 71-DE-271 A71-27325 Mathematical modellinq of aircraft structural Traversinq Infrared Inspection System for C-5 response modes to active control system aircraft fail-safe strap panels of bonded Ti-A1 N71-23212 laminates, discussinq desiqn and application MOIRE EFFECTS [ASflE PAPER 71-DE-371 A71-27327 noire effect analysis of stress and strain of METEOROLOGICAL BALLOONS machine parts and structural elements Aerodynamically stable meteoroloqical balloon [ AD-7178261 N71-22168 usinq surface rouqhness effect MOMENTS OF INERTIA YNASA-CASE-XFF-04163) N71-23007 Variable sweep winq aircraft anqular motion MICROCRACKS mathematical model, analyzing inertial moments Optical holoqraphic interferometry for radial influence on control dynamics microcracks detection from bolt holes in hiqh p71-25661 strenqth aircraft steel MOMENTUM TAEORY rASNE PAPER 71-YST-C1 A71-27312 Momentum thickness of boundary layer of circular MICROPHONES cylinder in cross flow at hiqh Reynolds numbers Condenser microphones aerodynamically induced from static pressure and skin friction noise, investiqatinq acoustic pressure lower measurements limit dependence on air flow velocity and A71-27738 turbulence MONITORS A71-27063 Radio frequency interference monitoring for MICROWAVE EQUIPMENT instrument landing system in automatic landing Reinforced plastics components in supersonic r RAE-TR-70076 1 N71-23356 transport nose radome and missile radar M 0 R T A L I T Y antennas, discussinq noldinq, sandwich saterials Weather factors in fatal civil transport aircraft and computer controlled sprayinq techniques accidents A71-27016 N71-23431 MIDAIR COLLISIONS MULTIPATH TRANSMISSION Nidair collisions analysis for civil-military Hultiple access digital communication system for inteqrated ATC air space, discussinq near miss low flyinq aircraft with infrequent users volume, random headinq aircraft density and N71-21855 pilots Pvasivr action vs avoidance percentaqes MULTIPAASE FLOW 171-27599 Impeller blade loadinq vorticity on stream Surface MILITARY AIR FACILITIES of revolution for mixed flow compressor, usinq Bar'? base shelt-rhanqar expandable structures for annular cascade theory rapid worldwide Tactical Fiqhter Orqanization [ASnE PAPER 71-GT-171 A71-25962 deployment, notinq foam and honeycomb Three dimensional boundary layer flow and velocity fabrication profiles in mired diffuser with equal anqlp r AIRA PAPER 71-3981 A71-25274 walls MILITARY AIRCRAFT [ ASflE PAPER 71-GT-403 b71-25973 RPlium weiqht NARC C-1A tactical transport Reattachment anqle of supersonic laminar mixed aircraft technical specifications boundary layer, usinq revolution model with A71-25231 Reynolds number allowance A71-26194

A-32 SUBJECT IEDEI AUSSELT EUIBEB

[ ASRE PAPER 71-GT-74 J A71-25988 Optical holographic interferometry for radial N microcracks detection from bolt holes in hiqh BACELLES strength aircraft steel Determination of low speed jet noise from fan [ ASI'E PAPER 71-IET-C] 871-27312 engine for simulated nacelle confiquration Fabrication and tests of C02 flat plate models in [NASA-TU-D-6314) 1171-23134 Be hypersonic wind tunnel Jet noise contribution to far field sound from [ SC-Ck-69-32151 N71-23228 1.83 meter diameter fan determined for tu0 EOIPLAEIABLE IATEBIALS simulated nacelle configurations Flame retardant silicone elastomers for use as rNASA-Tll-X-67825J W71-24009 aircraft construction materials, describing EASA PBOGBAIS fabrication techniques, mechanical. aqinq and NASA reliability program provisions for ueatherinq properties aeronautical and space system contractors, 171-27412 reviewinq evolution process BOELIEEAB STSTEIS A71-26667 Nonlinear self adjustinq and variable structure E AT IOE S automatic control systems for piloted and Air and cosmic space common lau, discussinq pilotless flight vehicles, considerinq boundaries, sovereiqnty over state territories oscillations due to electric servosystems and jurisprudence related to travel development nonlinear characteristics A71-26325 A71-26716 IAIIGATIOI Nonlinear systems optimal control computational Quasi-optimal proportional navigation. derivinq method, usiuq Chebyshev algorithm feedback quidance laus for interceptor 171-21592 aerodynamically controlled missiles EOBBEWTOEIAB FLUIDS 1171-26409 Combined free and forced laminar convective heat BAVIGATIOE AIDS transfer to nonNeutonian fluids flovinq in Area navigation facility, discussing control and constant wall temperature vertical tubes and display and navigation standards controllinq parameter analysis A7 1-26879 N71-22702 BIOBIUI EOZZLE DESIGE Tungsten reinforced oxidation resistant columbium supersonic propelling nozzle optimal parameters alloys uith operatinq temperature above 2000 P for maximum thrust coefficient. discussinq for use in qas turbine enqines nozzle control and efficiency [ AD-717969 J N71-23673 171-27504 EITEIC OXIDE AOZZLE PLOW Air polluting nitric orin- an2 soot prcdoction by Viscous flou in supersonic de Lava1 nozzle, jet aircraft, discussing mixinq process and measuring gas density and rotational atmospheric dispersion temperatures by electron beam techniques [AIAA PAPER 70-1151 A71-27560 [AIAA PAPER 70-8101 A71-27555 EITBOGEE Viscous converqent-diverqent nozzle flow slender Aircraft fuel tank nitrogen inertinq, fire and channel approximation. discussinq nozzle explosion suppression for foreign particle geometry, Reynolds nunber and uall temperature contamination, sludqe and lacquering reduction effects [ASEE PAPER 71-GT-451 171-25978 [AIAA PAPER 69-6541 871-27556 1OISE IETEESITY noise characteristics of circular double jet TWO dimensional soend wave equation solution in issuinq from 3 cm and 6 cm diameter nozzles terms of time retarded arquments, derivinq rn~o;lr-3 with thcsc of ciilqJie let analvtiral exprcszioos ior aircraft noise r NAL-TR-212 1 N71-22469 intensity and pouer EOZZLE GEOIETBY A71-25144 Tuin spool turbojet engine dynamic response, Transonic compressor shock wave noise qeneration discussinq simulator predictions, dioital and decay rates at multiple tones, usinq sonic computer control, nozzle area variations and boom analysis operatinq trajectories [ASIlE PAPER 71-GT-71 A71-25953 rhSnE PAPER 71-GT-141 A71-25966 Temporal and spectral stimuli combinations effects Viscous convergent-diverqept nozzle flow sleoder on judqed noisiness of aircraft sounds by channel approximation, discussing nozzle college students qeometry, Reycolds nunber and uall temperature 871-27531 effects Development and description of basic descriptors [ AIAI PAPER 69-6541 A7 1-275 56 used to analyze jet enqine noise. aircraft EOZZLE TBBUST COEPPICIEBTS noise, and noise level of airports Supersonic propellinq nozzle optimal parameters 871-21980 for maximum thrust coefficient. discussinq BOISE BEDUCTIOE nozzle control and efficiency hxial flou fan noise, investiqatinq louvers 1171-27504 effects on sound field EUCLEAR POWER PLAETS 871-26704 Soviet book on aircraft and rocket enqines control Noise characteristics of circular double jet automation, discussinq nuclear pouer plant/fuel issuing from 3 cm and 6 cm dianeter nozzles systeas desiqn and cortrol simulation methods compared with those of sinqle jet A71-26u03 [ NAL-TR-2 12 1 N71-22469 EUIERICAL ABALTSIS Airborne equipment for approach path control on Two dimensional flou in radial turbonachine bladed reduced noise trajectories in Boeinq transport impeller, comparina numerical solution based on aircraft traffic potential theory with experimental results N71-23425 rASRE PAPER 71-GT-201 A71-25964 Identification and control of aeromedical factors NUIERICAL IETEGBATIOB associated with aircraft noise and acoustic Aosprical integration method based on poter.tia1 measurements during C-141 operational missions flou theory to evaluate aerodyoamic [ AD-71 8097 J N71-23748 characteristics of thin supersonic winqs EOBDESTBUCTIIE TESTS [DLR-PB-71-011 N71-23597 Representative Thornel fiber aircraft fuselage EOSSELT EUIBEB component nondestructive testinq and repair, and Beat transfer to airfoil in oscillating flou at Tbornel fiber, polysulfone and polyamide-imide larae angles of attack, shouinq vortex shed composites fabrication and evaluation reattachment and Nusselt numbers increase A71-25427 [ASIlE PAPER 71-GT-181 A71-25963 Pulsed laser holoqraphic applications to aerospace components nondestructive testinq, inspecting electron bean welds and internal structural flaws

A-33 OBLIQUE SROCK WAVES SUBJECT INDEX

[ NASA-TR-X-620331 N71-24001 ORIFICE PLOU 0 Pressure orifices inclination in low density flow OBLIQUE SROCK UAVES from experiments with cooled flat plate model in Time dependent asymptotic solution for transonic hypersonic lon density wind tnnnel flons in hyperbolic cozzle and turbine cascades A71-25490 nith oblique shock OSCILLATING PLOU rASMt, PAPER 7i-GT-G:j a71-75975 Heat transfer to airfoil in oscillating flow at OIL ADDITIVES larqe anqles of attack, siiuuinq TertFx shed Friction points, and oil system of aviation qas reattachment and Nusselt numbers increase turbine engines rASME PAPER 71-GT-181 A71-25963 IAD-717835 1 N71-22011 Quasi-axisymmetric and superposed fine fluctuating ONBOARD EQUIPMENT structure of ideal incompressible vortex flows Fliqht test completed on onboard real time enqine in axial flow turbines, assuminq infinite mutual performance monitorinq system, discussinq blade proximity thermodynamic analysis technique All-27714 [ASME PAPER 71-GT-771 A71-25991 OIIDATIOI RESISTANCE ONE DIMENSIONAL PLOU Tunqsten reinforced oxidation resistant columbium One dimensional flon models of internal combustion alloys nith operatinq temperature above 2000 F enqine exhaust silencers in noisy systems for use in qas turbine enqines A71-25180 IAD-7179691 N71-23673 OPERITIONAL PROBLERS Subsonic and supersonic airline operations, restraints, considerinq noise, air pollution and P inadequate airport facilities P-3 AIRCRAFT A71-26870 Analysis of inteqrated hiqh frequency antenna OPERATIONS RESEARCH system for P-3C aircraft radio communications Accident investiqations, fliqht control systems, r AD-7181671 N71-23306 and operational recordinqs for improved aircraft Tests for determininq spectral signatures of fliqht mechanics inteqrated hiqh-frequency antenna systems for . [ AGARD-CP-76-71] N71-23410 P-3 aircraft OPTICAL CORRECTION PROCEDURE r AD-7180541 N71-23609 Automatic approach and landinq system with flash PANEL PLUTTEE warninq siqnal for caravelle aircraft control Cylindrical shells panel flutter analysis for N71-23429 internal stress and supersonic flow, considerinq OPTICAL EQUIPMENT still air hucklinq data useful for determininq Combined optical attitude and altitude indicatinq bucklinq loads instrument for use in aircraft or spacecraft [AIAA PAPER 71-3281 A71-25308 rNASA-CASE-XLA-019071 N71-23268 Ueiqht minimization of semiinfinite €lat sandwich Shipboard test procedure of Fresnel lens optical panel at constant dynamic pressure in supersonic landinq system MK 6 UOD 2 for carrier landinqs flon subject to flutter constraint, usinq finite r AD-718335 1 N71-23488 element model OPTICAL MEASOREMENT r AIAA PAPER 71-3301 A71-25310 Structure constant of jet exhaust turbulence of Flutter analysis of clamped thin skew panels with 5-57 with afterburner by laser beam probinq midplane forces in supersonic flow. usinq compared with scintillation and hot-nire Galerkin method aneiometer measurements A71-26766 471-26304 Computer proqram for aerodynamic forcps on Ootical holoqraphic interferometry for radial flexible plate underqoinq transient motion in microcracks detection from bolt holes in tiqh shear flow, applyinq to panel flutter strenqth aircraft steel A71-27559 [ASME PA?ER 71-MET-CI A71-27312 PANELS OPTIMAL CONTROL Finite element method for free vibrations and Quasi-optimal proportional navigation, derivinq random response of inteqrally-stiffened panel feedback quidance laws for interceptor r LR-541) 1 Nll- 24 29R aerodynamically controlled missiles PARACHUTES A71-26409 Stokes flow parachute extremely liqhtneiqht Nonlinear systems optimal control computational decelerator for increasinq altitude and rocket- method, usinq Chebyshev alqorithm borne radiosondes atmospheric data samplinq A71-27592 quality OPTIMIZATION AIAA PAPER 71-1)oi 1 A71-25277 Ueiqht minimization of semiinfinite flat sandnich Parachutes for lon density atmospheres, describing panel at constant dynamic pressure in supersonic lon and hiqh altitude test results flow subject to flutter constraint, usinq finite rAIAA PAPER 70-11641 A71-25525 element model Steady state inflated shape and included volume Of ~AIAA PAPER 71-3301 A71-25310 24 and 30 qore flat circular, extended skirt, Automated optimal neight fully stressed larqe porous rinq slot, and porous ribbon parachutes scale structural desiqn of aircraft, usinq [ AD-718808 1 N71-23387 matrix- mathematical proqramminq technique PARTICLE COLLISIONS [AIAA PAPER 71-3611 A71-25340 Two phase supersonic barotropic flow with solid Stability analysis and desiqn optimization with particles around thin profile with allowance for dynamics and aeroelastics constraints for elastic particle collisions helicopter rotor blade minimum neiaht nith A71-27450 bmdinq torsion flutter and favorable frequency PARTICLE INTERACTIONS placements Particle interaction nith uedqe surface in r AIAA PAPEP 71-3881 A71-25352 supersonic two phase flow, determininq incidence Optimal bloninq wall jet prediction for coordinates and collision frequency as function suppressinq separation from hiqh lift aerofoils of initial conditions nith incomplete mixinq of upstream boundary A71-27665 laypr PARTICLE TREORI A71-26196 Lift and particle displacement around liftinq body Modulation cancellation altimeter error analysis nith stream function as fluid motion equation and performance optimization intearal A7 1- 27 437 A71-27577 ORBITER PROJECT PASSENGER AIRCRAFT Surface flon photovisualization of straiqht ninq ATC requlations considered for Concorde orbiter and swept delta wins orbiter introduction to passenqer service, discussinq confiqurations at flach 10.4 and several Reynolds landinq and takeoff characteristics numbers A71-25232

A-34 SUBJECT IUDEI PLATES (STRWCTURAL EEEBBRS)

Passenqer aircraft structures accelerated testinq [ NASA-CR-1174661 A71-22135 for safety and fatigue durability nuder PILOT PERPOREAUCE operational conditions, describinq tests, midair collisions analysis for civil-military planninq and evaluation inteqrated ATC air space, discnssinq near miss 071-26946 volume, random headinq aircraft density and Support systems planninq for expanded passenqer pilots evasive action vs avoidance percentaqes and carqo traffic in civil aviation A71-27599 871-22390 Aircraft safety and aircraft reliability, notinq PERPOEATBD PLATES pilot performance, landing approach and takeoff. Wake flow behind two dimensional perforated Plates and clear air turbulence normal to air stream, measurinq drag, shedding, N71-22147 velocity and turbulence at Reynolds number Transfer functions in modelling hUDan pilot and 25,000-90,000 dynamic structural aircraft responses 171-26449 [ AGAFD-F-580-711 R71-23210 PERFOBEAUCE PILOT TEAIEIEG Reynolds number effects on centrifuqal compressor Routine unprotected exposure to acoustic r.oise performance characteristics, discussinq power vithin cockpits of trainer aircraft presentinq losses in compressor, imwller and diffuser potential hazardous stress staqes and compressor adiabatic efficiency [ AD-7178523 W71-22426 rASBE PAPER 71-GT-251 1171-25967 PIPES (TUBES) PBBPORIAECE PBRDICTIOU Combined free and forced laminar convective heat Validity range of response predictioc methods for transfer to nonBertonian fluids flowinq in large flexible aircraft to continuous constant wall temperature vertical tobes and atmospheric turbulence. discnssinq power controlling parameter analysis spectral densities and fatigue life W71-22702 [AIAA PAPER 71-3421 A71-25321 PITCE (IECLIRATIOU) Steady transonic flow throuqh two dimensional qas Equation error approach to parameter turbine cascades predicted with time dependent identification in third order pitch plane formulation of flow equations, qivinq airfoil dynamics for hiqh performance aerodynamically surface pressure distributions controlled aerospace vehicle [ASBE PAPER 71-GT-891 A71-25996 A71-26418 Helicopter blades inherent vibration dampinq, Airfoils unsteady stall by testinq two dimensional comparing theoretical and semiempirical model in harmonic pitchinq oscillation for predictions to experimental results helicopter rotor blades characteristics A71-27123 A71-27609 Modulation cancellation altimeter error analysis PITC!3IIIC- !WEPITS aud performance optimization Pitching moment suppression on VTOL aircraft model 1171-27437 by deflecting jets in wind tunnel test PBBPOBEAUCE TESTS [ BAL-TR-2091 N71-22147 Performance testing of fluorosilicone hydraulic PLAEIUG fluid in high teiperature supersonic aircraft ~iqbaspect ratio planinq surface qlidins on piston pumps infinitely deep, incompressible. inviscid, and A71-27040 qravity-free fluid Windage tests of cylindrical and Lundell-conical [ AD-7176671 N71-22345 rotors in ambient air producinq Reynolds nunbers PLASIA DTEAEICS up to 100,000 for high speed alternators Canadian research on aerospace sciences and [ NASA-TE-X-67809] 871-23116 enqineerinq. qas and plasma dynamics, and Theorv. calculation, and .‘-=sL3r clf =fntrif;gal relarea topics compressor machines N71-22515 TAD-7178781 N71-23297 PLASLIA JETS Pliqht simulator and airframe test stand for neasureaent of macroscopic aerodynamic quantities evaluating operational performance of aircraft in plasma jets produced by electrothermal and flight control system hall current accelerators 1171-23413 N71-22679 Operational perfornance of automatic V/STOL fliqht PLASEA PAVES control systems using jet thrust or air bleed Laboratory high beta plasma shock wave generation N71-23415 [ AD-7173971 N71-22166 Operational performance and handling safety PLASLIAS (PHTSICS) requirements for single engine boundary layer Gas and fluid response to hiqh intensity ruby controlled aircraft in STOL mode laser beam N71-23419 [ AD-7177281 N71-22593 Fliqht safety performance of V/STOL Harrier PLASTIC AIRCRAFT STRUCTURES military aircraft having jet control Boron-epoxy structural skins desiqn for P-14 N71-23427 honeycomb horizontal stabilizer, usinq computer Pliqht mechanics problems in accident program investigations for VJ-101 aircraft A71-25420 1371-23428 Graphite-epoxy composite skins for commercial Aerodynamic performance of sveptback-bladed aircraft fliqht spoiler, discussinq multianqle centrifuqal compressor in argon as function of ply desiqn and fabrication equivalent weight flow 1171-27413 [ RASA-TO-1-2269 ] N71-23659 PLASTIC DEFORIATIOE Hypersonic wind tunnel test on conical and ogival Rotor-bearing system analysis to determine cause nosed static pressure probes of brinellinq failure of bearinqs from vibratior [ ARL/A-327] N71-23778 tested PLv fans PERTURBATIOU TEEOBI [NASA-CR-117855] N71-22527 Steady supersonic isoenergetic flow of thermally PLATES (STRUCTURAL IEIBBES) and calorically perfect gas past circular cones Plate and acoustic finite elements simulation of at zero angle of attack, usinq dimensional vindow-room system coupled transient response to perturbation method sonic booms, discnssinq equations of motion and 171-26939 cavity depth effect PEOTOIUTEBPRETATIOE 1171-27481 Statistical diameter size distribution of random Coapnter proqram for aerodynamic forces on circles on plane or spheres in space from flexible plate underqoiuq transient motion in* satellite and aircraft measurements for aerial shear flow, applying to panel flutter and cloud photography 171-27559 A71-27100 Flutter of buckled plate exposed to static PEOTOIETBT pressure differential and streamwise applied in- Photometric observations of auroral scattering by plane load, conparinq experimental results with CV 990 aircraft stability boundary calculations

A-35 POINT SOURCES SUBJECT INDEX

871-27584 stahility boundary calculations A71-27584 POINT SOURCES Sound radiation from time varyinq point force in PRESSURE MEASUREMENTS accelerative motion, applyinq to fan or Larqe axial compressor flow straiqhteninq stator helicopter rotor noise at subsonic tip speeds blades unsteady pressure measurements with short A71-26702 response time detectors POLYURETEANE POAM A71-27469 Polvurethane foam effects on fuel contamination ..-- L...... Luuu,l:"ror+in.+innIlr.rrc-yu--v.. c\f lift-induced sonic durinq installation for fuel system fire and boom characteristics of two simple winq models explosion protection at Mach numbers from 2.3 to 4.63 [ ASME PAPER 71-GT-541 A71-25981 [NASA-TN-D-62011 N71-23125 POTENTIAL FLOW PRESSURE REGULATORS Finite-element potential flow modeling for Flow control system desiqn for blowdown wind predictinq round liftinq jet rolled up qeometry tunnels and disturbance effects on requlatinq and path converqent into cross-flowinq accuracy mainstream as on VTOL or STOL aircraft [ NAL-TN-221 N71-22476 [AD-7181211 N71-23475 PRESSURE SENSORS Numerical inteqration method based on potential Hypersonic wind tunnel test on conical and Ogival flow theory to evaluate aerodynamic nosed static pressure probes characteristics of thin supersonic winqs [ARL/A-327] N71-23778 [DLR-FB-71-011 N71-23597 PRESSURE UELDING POTENTIAL TEEOBY Jet enqine components inertia weldinq, discussinq Solid profile winq motion near solid wall or free process, equipment, low weight-cost ddvantaqe surface, usins acceleration potential method and mechanical properties reproducibility A71-27 174 [ ASNF PBPER 71-GT-331 A71-25970 POTENTIOMETERS (INSTRUMENTS) PROBABILITY TEEOEY Device for controllinq rotary potentiometer Fatigue failure probabilistic model under variable mounted on aircraft steerinq wheel or aileron amulifude loadinq, considerinq relation between control safety factor and fatique failure probabilityA71-25492 r NASA-CASE-XAC-100191 N71-23809 POUER SPECTRA PROCEDURES Power spectral density analysis of aircraft Standard equipment and procedures for aircraft qas structural response to taxiinq produced random turbine engine exhaust smoke measurement vibrations involvinq landinq qear orifice [ ASNE PAPER 71-GT-R8] A71-25995 dampinq and Coulomb friction PROCUREMENT 1171-26311 Cost effectiveness of reliability screening PREDICTIONS proqram from parts procurement throuqh system Ten year forecast for eiqht major traffic test, usins exuerience with attack radar for cateqories at Washinqton National and Dulles F-II~airciaft' A71-26683 International airports for period 1971 throuqh 1982 PRODUCT DEVELOPMENT N71-21979 Vertical straiqht lift turbojet enqine desiqn and Procedures for predictinq properties of transonic development, presentinq component materials flows about thin airfoils and slender bodies properties/weiqhts, endurance tests and [NASA-Cfi-17221 N71-23133 performance data Methods for predictinq speech interference within r ASNE PAPER 71-GT-751 A71-25989 cockpits of fixed winq and rotary winq aircraft Air Force development proqrams with qraphite r AD-7180981 N71-23528 reinforced composites, discussing matrix PEESSURE DISTRIBUTION materials and cost and weight savinqs Collocation method predictinq oscillatory subsonic r ASNF PAPER 71-DE-131 A71-27323 pressure distributions on interferinq parallel Theory, calculation, and desiqn of centrifuqal liftinq surfaces, considerinq approach more compressor machines economical than finite element method [AD-7178781 N71-23247 rATAA PAPER 71-3291 A71-25309 PRODUCTION ENGINEERING Reentry vehicles confiquration lift and draq Metal matrix composite fabrication procedures for coefficients in hypersonic flow from pressure gas turbine enqine fan blades, stressinq distribution and balance measurements, comparinq diffusion bonding process susceptibility to with isolated cone data blades volume producibility A71-25487 [ ASME PAPER 71-GT-461 A71-25979 Hiqh subsonic flow two dimensional turbine cascade PROJECT HAWAGEHEAT deniqn by approximate hodoqraph method, notinq Aircraft industry materials development, pressure distribution measurements discussinq innovations in qovernmpntal proqrams [ASME PAPER 71-GT-341 A71-25971 manaqement, procurement specifications and Glass fibm rotor blades desiqn with lonqitudinal Department of Defense contractinq procedures pressure tappings for cascade wind tunnel and A71-27677 turbomachinery flow research applications PROJECTORS A71-26316 Optical projector system for establishinq optimum Yeasurements of sonic boom pressure distribution arrangement of instrument displays in aircraft, of bodies of revolution at Mach 2.96, 3.83. and spacecraft, other vehicles, and industrial 4.63 in Unitary Plan wind tunnel instrument consoles r NASA-TN-D-fil951 N71-21961 r NASA-CASE-XNP-038531 N71-21882 Estimatinq unsteady pressure distributions in T PROPELLANT COMBUSTION tail confiquration from measured distribution Aircraft fuel tank nitroqen inertinq, fire and and theory explosion suppression for foreiqn particle r NLR-TR-68043-L 1 N71-23131 contamination, sludqe and lacquering reduction PRESSORE EPPECTS [ ASNE PAPER 71-GT-45 1 A71-25978 Turboeachinfs blarlc cascades in supersonic flow, PROPELLANT EVAPORATION notinq wdvv confiqurations, rntropy and counter Air flow velocity, altitude, fuel-air ratio, fuel prrxnsurt! variations flow velocity, and pressure effects on fuel A7 1-27475 temperature before and after prevapocization in PRESSURE GRADIENTS ramjet enqines N71-24053 Laminar boundary layer equations for rotatinq [ NASA-TT-F-13605 J plate with nuriace of arbitrarv curvilinear PROPELLEE DRIVE shape, detprsininq external flow pressur- Propeller-driven short haul tilt winq aircraft qradirnt lradinq to separation notinq aerodynamic noise A71-27502 N71-22191 Flutter of buckled plate exposed to static PROPELLEE SLIPSTREAHS prf'ssure differential and streanwise applied in- Yinq flap slipstream deflection correction method plane load, comparinq experimental results with for evaluation of propeller power effect on lift

A-36 SUBJECT IIIDEX BANDOM accEss MEMORY

and drag coefficients of Arava twin engine STOL aircraft A71-25164 R PROPOBTIOEAL COETBOL RADAR AHTEHBAS Quasi-optimal proportional navigation, deriving Reinforced plastics components in supersonic feedback guidance laws for interceptor transport nose radome and missile radar aerodynamically controlled nissiles antennas, discussing moldinq, sandwich materials A71-26409 and computer controlled sprayinq techniqnes PBOPULSIOII SYSTEM COlFIGURATIOIIS A71-27016 Belicopter jet propulsion systems, considering BADAB DETECTIOII turboconpressors, gas generators, turbine air Feasibility and design criteria of laser Doppler iet systems, pulsed jet engines. ramjet engines system for detectinq and mappinq turbulence and rocket engines levels and wind or velocity profiles in various 171-25259 applications Lightweight high performance regenerative gas [NASA-CR-103105] N71-24081 turbine designs for aircraft propulsion, RADAR EQOIPREBT comparing various compressor, turbine, combustor Cost effectiveness of reliability screening and recuperator arranqements proqran from parts procurement throuqh systen [ ASME PAPER 71-GT-671 171-25983 test, using experience with attack radar for Convertible fan/shaft engine for V/STOL tactical P-111 aircraft and transport aircraft, detailing mechanical A71-26683 arrangement, design and performance RADAR IIAVIGATIOH A71-26054 Terrain following radar for airborne guidance of Measurement of turbojet engine exhaust nozzle low flying ailitary aircraft performance as affected by installation 871-26881 parameters nsinq load cells and calibrated Radar avoidance action logic for convergins engines on P-106 aircraft aircraft safe passage, discussinq near aiss and INASA-TH-X-67816] N71-23822 collision situations PROPIILSIOS SYSTEE PEBPORMAdCE B71-27600 Thrust measurement of aircraft and rocket BADAB REFLECTOBS propulsion systems, comparinq cost and Nonexpandinq reflecting balloon for radar characteristics of mechanical. electrical and measnreaent of stratospheric circulation hydraulic systems [NLL-M-20326-/5828.4P/] N71-23934 A71-26991 RADIAL FLOW Air transport propulsion systems. discussing Plor variation effect on velocity and flor angle aircraft operating economics with reference to fiistribation zt exit of shrouded radial flow weioht, size. poueiplant efficiency, noise and impeller with backward swept blades, usinq air pollution streamline curvature method A71-27542 [ASME PAPER 71-GT-151 A71-25961 measurement of turbojet engine exhaust nozzle Two dimensional flow in radial turbomacEine bladed performance as affected by installation impeller, comparing nunerical solution based on parameters using load cells and calibrated potential theory with experimental results engines on F-106 aircraft r ASBE PAPER 71-GT-20 1 171-25964 [ NASA-Tn-P-678161 N71-23822 Quasi-three dimeqsional method for radial flow PROTECTIVE COaTIHGS compressor blade loadinqs computation, Superalloy dispersion strengthened and fused presenting combined meridional plane and blade slurry silicide coatinqs for aircraft gas to blade solutions for adaptation to cornpntsr turbine engines and space shuttle heat shields {asas PAPEP 71-61-60] A71-25982 A71-25555 Quasi-three dimensional surface velocities and PULSE COMMUNICATIOH choking flow for turbomachine blade rows multiple access digital communication system for calculated by FORTRAN program low flying aircraft with infrequent users [NASA-TN-D-6177] N71- 23126 N71-21855 RADIAL VELOCITY PULSED LASERS Nonlinear limit rotation velocity and circulation Pulsed laser holographic applications to aerospace induced by wheel in axial flow turbomachine for coaDonents nondestructive testing, inspecting incompressible ideal fluid, usinq iterative electron beam welds and internal strnctnral numerical alqorithm flaws A71- 277 15 [ kSmE PAPER 71-GT-743 171-25988 RADIO COM~UHICATION Feasibility and design criteria of laser Doppler Airborne radio conmunication systems, stressinq system for detecting and mapping turbulence electronic equipment desiqn reliability levels aad wind or velocity profiles in various 171-26880 applications Analysis of integrated high frequency antenna [ NASA-CR-1031051 N71-240 8 1 system for P-3C aircraft radio communications PUMPS [~~-7i8167] N71-23306 Perfornance testing of flaorosilicone hydraulic RADIO PRBQUEIICY IBTBRPEREBCE fluid in high tenperature supersonic aircraft Radio frequency interference monitoring for piston pumps instrument landing system in automatic landinq A71-27040 [ RAY-TR-700761 N71-23356 PTROTECEEICS BADIOSOHDES Modified T-33 aircraft system for pyrotechnic hail Stokes flor parachute extremely lightweight suppression seeding decelerator for increasing altitude and rocket- N71-22200 borne radiosondes atmospheric data samplins quality [kIAA PAPER 71-4011 1171-25277 Q RADOME MATERIALS QIJADBATIC EQIJATIOSS Reinforced plastics components in supersonic Flutter suppression with dissipated enerqy reduced transport nose radome and missile radar to quadratic form for control surfaces antennas, discnssinq molding, sandwich materials [ NASA-TN-D-6199] N71-23091 and computer controlled spraying techniques QUALITY COHTROL A71-27016 Traversing Infrared Inspection Systen for C-5 RAMJET EBGIIIES aircraft fail-safe strap panels of bonded Ti-A1 Air flow velocity, altitude, fuel-air ratio, fuel laminates, discussing desiqn and application flow velocity, and pressure effects on fuel [ASME PAPER 71-DE-371 A71-27327 temperature before and after prevaporization in ramjet engines NASA-TT-P-13605 1 N71-24053 BASDOII ACCESS MEMORY Multiple access diqital comaunication system for

A-37 RANDOM PROCESSES SUBJECT INDEX

low flyinq aircraft with infrequent users panels, aircraft ducting. secondary structures, N71-21855 furnishings, mouldings and toolinq RANDOH PROCESSES A71-25652 Finite element method for free vibrations and Reinforced plastics components in supersonic random response of inteqrally-stiffened panel transport nose radome and missile radar rLR-5441 N71-24298 antennas, discussing molding, sandwich materials RAlX!! VIBR~TION and computer controlled sprayinq techniques power spectral density analysis of aircrdri A71-27016 structural response to taxiinq produced random REINPORCEHENT (STRUCTURES) vibrations involvinq landinq qear orifice Haterial properties, impregnation, shaping. dampinq and Coulomb friction hardening and structural design in mass 1171-2631 1 production of reinforced laminates for aircraft REAL TIME OPERATION construction Complex real time hybrid computer simulator for A71-26954 captive two blade rotor platform dynamic problem REINFORCING FIBERS solvinq Representative Thornel fiber aircraft fuselage A 7 1- 2 58 4 7 component nondestructive testing and repair, and Fliqht test completed on onboard real time enqine Thornel fiber, polysulfone and polyamide-imide performance monitorinq system, discussinq composites fabrication and evaluation A71-25427 thermodynamic analysis technique [ASME PAPER 71-GT-771 A71-25991 Prototype graphite fiber/plastic fUSelaqe REATTACRED FLOE component design, test and performance Interaction theory for supersonic separated and prediction, using strurt.ura1 analysis methods reattachinq turbulent boundary layers, comparinq A71-25428 to real flow past conpression ramp Glass fiber reinforced plastics aerospace rAIAA PAPER 71-1281 871-25476 applications coverinq radomes, dielectric Heat transfer to airfoil in oscillatinq flow at panels, aircraft ductinq, secondary structures, larqe angles of attack, showinq vortex shed furnishinqs, mouldings and toolinq reattachment and Nusselt cumbers increase A7 1-25652 rASME PAPER 71-GT-181 A71-25963 Ti, B and qraphite fiber composites application to Reattachment anqle of supersonic laminar mixed aircraft desiqn, discussinq mechanical boundary layer, usinq revolution model with properties and market competition Reynolds number allowance 1171-27676 A71-26194 RELIABILITY ANALYSIS RECONNAISSANCE AIRCRAFT Cost effectiveness of reliability screeninq Statistical diameter size distribution of random proqram from parts procurement throuqh system circles on plane or spheres in space from test, usinq experience with attack radar for satellite and aircraft measurements for aerial F-111 aircraft and cloud photoqraphy A71-26683 A7 1- 27 100 RELIABILITY ENGINEERING RECURSIVE FUNCTIONS NASA reliability proqram provisions for Analoq recursive computer with serial diqital aeronautical and space system contractors, proqralo for arithmetic unit and storaqe system reviewinq evolution process control A71-26667 A71-27150 Pan American reliability proqram effect on airline REENTRY EFFECTS maintenance, considerinq cost effectiveness, Transformation in air components due to marked aircraft performance, data collection and increase in temperature durinq reentry shock analysis wave A71-26671 N71-22640 RESCUE OPERATIONS REENTRY VEEICLES Expandable structures for midair pilot rescue Reentry vehicles configuration lift and draq device with hot air filled BALLUTE, diSCUSSinq coefficients in hypersonic flow from pressure BALLUTE material development A71-25278 distribution and balance measurements, comparinq [AIAA PAPER 71-4021 with isolated cone data RESEARCB AND DEVELOPHENT A71-25487 Research and development in aerospace systems Uind tunnel tests to determine sonic boom includinq desiqn and fabrication of 4-ft characteristics of straiqht winq and delta winq trisonic wind tunnel space shuttle durinq reentry into earth N71-22331 atmosphere RESONANT FREQUENCIES r NASA-TN-X-620301 N71-23296 Rotatinq low aspect ratio turbomachinery blades REFERENCE ATHOSPRERES natural frequencies and mode shapes, usinq Carqo airship standard atmosphere operation modes, finite element method for equilibrium equations discussinq lonq ranqe gas capacity and short eiqenvalue problem ranqe applications for larqe compact loads [AIAA PAPER 71-3741 A71-25147 A71-26309 Numerical analysis of influence coefficients, REFLECTED WAVES natural frequencies, and mode shapes of Triple Point trajectory of shock-shock Nach vibration of trianqular inflatable winq reflection off plane wall, comparinq to Ehitham N71-22666 theory RETROROCKET ENGINES A71-26 192 Fuel-optimal retrothrusted soft landinq Of REFUELING airdrops throuqh atnosphere Fliqht and operation of IL-62 lonq distance Jet TAD-7184051 N71-23487 aircraft, considerinq fliqht crew composition REYNOLDS NUMBER and traininq, passenqer and carqo handlinq and Reynolds number effects on centrifuqal compressor refuelinq performance characteristics, discussinq power A71-25260 losses in compressor, impeller and diffuser Electrostatic charqe by JP-5 jet fuel at truck staqes and compressor adiabatic efficiency fill stand with 30-second relaxation chamber and [ ASHE PAPER 71-GT-251 A71-25967 bottom loadinq Vortex sheddinq characteristics of circular r AD-717347 1 N71-22232 cylinders at low Reynolds numbers from REGENERATIVE COOLING experiment on tapered models wake structure Enqineerinq desiqn analvsis of hydroqen cooled A71-27220 structural panels for application to hypersonic Transonic airfoil testinq techniques in two aircraft dimensional flow, discussinq wind tunnel r NASA-CR-16501 N71-22625 conditions at various Reynolds numbers A71-27467 REINFORCED PLASTICS Glass fiber reinforced plastics aerospace Viscous convergent-diverqent nozzle flow slender applications coverinq radomes, dielectric channel approximation. discussinq nozzle

A-38 SUBJECT IEDEI RUUUAT LIGETS

geometry, Reynolds number and wall temperature rotation of wind driven elements effects [ AASA-CASE-X5F-05224 J n7 1- 2 37 26 rAIAA PAPER 69-6541 A71-27556 ROTOR AERODY NALIICS Romentum thickness of boundary layer of circular Comparative vertical turbulence and loss cylinder in cross flow at hiqh Reynolds numbers restrictive stochastic models for threshold from static pressure and skin friction crossing rotor blade flapping vibrations at low measurements lift hiqh advance ratio A7 1-2773 8 [AIAA PAPER 71-3993 A71-25351 RIGID ROTORS Laminar boundary layer transition, separation and Loads on compressor, ventilator and turbine rotor streamline direction on rotatinq helicopter disks havinq larqe central holes, giving blades formulas for stress distributions r UASB-TN-D-63211 N71-23779 1171-26952 ROTOE BLADES RIGID STRUCTUEES Stability analysis and design optimization with Torsional-flexural stability of stiffened Ti dynamics and aeroelastics constraints for panels for application to supersonic transport, helicopter rotor blade minimum weiqht with nsinq small deflection energy methods bendinq torsion flutter and favorable frequency [ AIAA PAPER 71-338 J A71-25317 placements Boundary layer separation in viscous flow around [AIAA PAPEB 71-388J A71-25352 rigid bodies Complex real time hybrid computer simulator for r AD-717772 I N71-22241 captive two blade rotor platform dynamic problem ROCKET ENGIEE COETBOL solving Soviet book on aircraft and rocket enqines control A71-258U7 automation, discussing nuclear power plant/fuel Discrete frequency rotor interaction noise from systems desiqn and control simulation methods lifting fans, using force harmonics acting on 171-26403 blades ROCKET EEGIlES [ASRE PAPER 71-GT-121 A71-25958 Thrust measurement of aircraft and rocket Aelicopter blades inherent vibration daapinq, propulsion systems, comparing cost and comparing theoretical and semiempirical characteristics of mechanical, electrical and predictions to experimental results hydraulic systems 871-27123 871-26991 ROTOR BLADES (TURBO!lACEIlERY) ROCKET TEST FACILITIES Flow variation effect on velocity and flow anqle nodal characteristic Dick-up system for vibration distribution at exit of shrouded radial flow tests of rockets or aircraft on ground, usinq impeller with backward swept blades, usioq small size accelerometers with individual strez=li-ve ciiisaiure method elertrcnic cir==;i [ASBE PAPER 71-GT-151 A71-25961 A71-27719 Optimum reiqht protective system aqainst ROCKET-BORNE INSTRUIIIRTS uncontained rotor failure with radial fragment Stokes flow parachute extremely liohtveiqht passage throuqh turbine engine casing decelerator for increasing altitude and rocket- [ ASRE PAPER 71-GT-70 ] 1171-25985 borne radiosondes atmospheric data sampling Glass fiber rotor blades desiqn with longitudinal quality pressure tappings €or cascade wind tunnel and rAIAA PAPER 71-4011 A71-25277 turbomachinery flow research applications ROTARY llIEGS A71-26316 Sound radiation from time varying point force in Loads on compressor, ventilator and turbine rotor accelerative motion, applying to fan or disks havinq larqe central hnler;, 7ivirq helicopter rotor noise at subsonic tip -2ee3s iormuias for stress distributions A71-26702 1171-26952 Eelicopter blades inherent vibration dampinq, Performance test of sinqle stage turbine with low comparinq theoretical and semiempirical solidity tandem rotor blade assembly predictions to experimental results NASA-CR-1803l 871-23132 A71-27123 ROTOES Unsteady flow measurement around wing sections Analysis of solid rotors used in hiqh speed during rapid angle of attack variations, induction motors for aerospace applications emphasizinq helicopter rotor blades N71-21898 A71-27468 Windage tests of cylindrical and Lundell-conical narginal vortex effects on aerodynamics of rotors in ambient air producing Reynolds numbers helicopter lifting surfaces, considering blade up to 100,000 for hiqh speed alternators form and noise spectrum tested in hydrodynamic [ NASA-Tn-X-67809 J N71-23116 tunnel RUBBER A71-27473 Inflation of initially spherical balloon of Airfoils unsteady stall by testing two dimensional elastic rubber-like material, discussing tensile model in harmonic pitching oscillation for instability helicopter rotor blades characteristics 1171-25445 A71-27609 BUIWAT COEDITIOES EOTATIES BODIES Flexible runway surfaces classification by LCN Cascade and single stage rotatinq riq data method. calculating for Ilyushin aircraft comparison with aerodynamic predictions based on 1171-26201 intrablade analysis, inclnding vall boundary autual aerodynamic effects of SR-1 helicopters layer model durinq simultaneous takeoff and landing, [ASnE PAPER 71-GP-131 A71-25959 determiuinq minimum distances between Lifting force of wing with rotating flap, deriving helicopters lift increase due to circulation redistribution A71-26953 at surface Fog clearance from airport runvays. discussinq A71-27491 available techniques, economic aspects and Laminar boundary layer equations for rotatinq importance for military operations plate with surface of arbitrary curvilinear A71-27247 shape, determining external flow pressure RUIlSAT LIGETS gradient leading to separation Performance tests and characteristics of capsule- A71-27502 type and prismatic-head liqhts used for ajrport ROTATIl6 FLUIDS approach and runway liahtinq systems Nonlinear limit rotation velocity and circulation NBS-10121 ] N71-22453 induced by wheel in axial flow turbomachine for Aviation qround liqbting, visual landing aids, incompressible ideal fluid, usinq iterative dual baseline transmissometer, photometric numerical alqorithm measurements of deck-landing projector siqht. A71-27715 and lamp for Fresnel optical landinq system EOTATIUG SEAPTS [UBS-l0508] N71-22456 Anemometer with brakinq mechanism to prevent

A-39 SAAB 37 AIRCRAPT SUBJECT INDEX

SELF ADAPTIVE CONTROL SYSTEIS Nonlinear self adjustinq and variable structure S automatic control systems for piloted and SAAB 37 AIRCRAFT pilotless flight vehicles, considerinq Technical aspects of tactical all-weather oscillations due to electric servosystems instrument landinq system of Swedish STOL nonlinear characteristics aircraft SaaL 37 OiqTen A71-26716 871-25233 kerozlastic aircraft self adjustinq automatic SAFETY DEVICES control systems, discussinq elimination oi Safety stardards development analysis for elastic oscillations caused noise from anqular passenqer vehicles and aircraft velocity sensing circuits [AD-718397] N71-23333 A71 -267 le SAFETY FACTORS SELF ORGANIZING SYSTEMS Fatique failure probabilistic model under variable Adaptive self-orqanizinq and -1earninq control amplitude loadinq, considerinq relation between systems with lonq and short term memory safety factor and fatique failure probability retention, usinq loqic random searches to find 171-25492 parameter values safety measures to eliminatp aircraft trailinq [ASNE PAPER 71-DE-221 A71-27324 vortex hazards SEIISPAN IODELS [NASA-TM-X-671251 171-23418 Hind tunnel investiqation of lonoitudinal Opprational performance and handlinq safety aerodynamic characteristics of semispan Wing requirements for sinqle engine boundary layer deflected-slipstream confiquration with double controlled aircraft in STOL mode slotted flap and auxiliary uinq N71-23U19 NASA-TN-D-63231 N71-23861 Speed and field lenqth safety factors for approach SENSORS and landinq mechanics of Brequet aircraft Automatic qust alleviation system employino N71-23420 inertial sensors and feedback devices with win4 Human factors and safety requirements in aircraft flaps and elevators, considerinq linkaqe desiqn control, noninteracting control and split N71-23423 control Human factors and control system failures in jet A71-25195 upsets during turbulence encounters SEPARATED PLOW N71-23424 Interaction theory for supersonic separated and Flyinq safety factors in close to qround reattaching turbulent boundary layers, comparing operational desiqn of XH-51 helicopter to real flow past compression ramp N71-23430 [AIAA PAPER 71-1281 A 7 1-2 5476 SAUDUICA STRUCTURES Hele-Shaw flow viscous tails from airfoil, Weiqht minimization of semiinfinite flat sandwich observing hiqh Reynolds number trailinq edqe panel at constant dynamic pressure in supersonic flow for separation and initiation of Kutta flow subject to flutter constraint, usinq finite condition element model A71-26447 rAThA PAPER 71-3301 A71-25310 Separated flow over flat plate with blunted fin at Reinforced plastics components in supersonic zero anqle of attack transport nose radome and missile radar r AD-717717 1 N71-22300 antennas, discussinq moldinq, sandwich materials SEQUE~TIALANALYSIS and computer controlled sprayinq techniques notion sequential analysis of airways utilization, A71-27016 usinq mathematical-statistical methods SATELLITE NETUORKS A71-27143 satellite applications to aircraft communications, SERVICE LIFE naviqation, and surveillance over US including Aelicopter auxiliary power unit /APU/ life cycle synthesized satellite network and aircraft cost computation A71-26679 equipment for air traffic control r N?. SA -CP- 1 1 7760 ] N71-22339 SBARP LEADIBG EDGES Location/identification transmitter and equipment Fliqht-measured base pressures from sharp leading for use in satellite aoplications in aircraft edqe upper vertical fin of X-15 aircraft communication, naviqation, and surveillance for compared with wind tunnel data for turbulent US air traffic control flow at Mach numbers from 1.5 to 5.0 r NASA-CR-117759 1 N71-22340 [NASA-TN-D-63481 N71-23922 US cooperation with ESRO UHF satellite system SAEAR PLOW development for air traffic control in Europe Computer proqram for aerodynamic forces on r NASA-TT-F-136511 N71-23967 flexible plate underqoinq transient motion in SATELLITE-BORNE PAOTOGRAPAY shear flow, applyinq to panel flutter Statistical diameter size distribution of random A71-27559 circles on plane or spheres in space from SAEAR STRESS satellite and aircraft measurements for aerial Three dimensional turbulent boundary layer and cloud photoqraphy calculations, usinq two dimensional method based A7 1-27100 on turbulent enerqy equation empirical SCALE UODELS conversion into shear stress transport equation Aircraft tires mechanical data from small models, 1171-26443 discussinq mechanical properties, tire stresses SBELTERS and tir- temperatures Bare base shelter/hanqar expandable structures for [AIAR PAPER 71-3461 A71-25325 rapid worldwide Tactical Fiqhter Orqanization SCALIEREN PHOTOGRAPAY deDlovment. noting foam and honeycomb schlieren visualization for supersonic annular fabr iCa tiok flxed cascade and freon compressor wind tunnels, rAIAA PAPER 71-3981 A71-25274 using vane holdinq cylinder devices SAOCK ABSORBERS A71-27717 Parachute decelerator towline enerqy absorber Schlieren and phase contrast methods of hypersonic shock attenuation characteristics, discussinq flow visualization drop test results A71-25527 N71-22637 rATAA, .. PAPER~ 70-12021 SE-210 AIRCRAFT SAOCK LAYERS Automet.ic approach and landinq system with flash Hiqh temperature aerodynamics with electromaqnetic warninq siqnal for Caravelle aircraft control radiation, considerinq thermally radiatinq shock N71-23429 layers, electric arc driven uind tunnels and qas SEALERS dynamic lasers Aircraft Power Plants sealinq materials, A71-27277 emphasizinq porous cermet seals heat resistance SAOCK TUBES undr*r thermal cyclic loads Conference on propulsion and enerqetics techniques A71-27688 for diaqnosinq high velocity flows

A-40 SUBJECT IIDEX SLEIDER WIBGS

[AGARD-CP-383 171-22626 Effect of engine position and high lift devices on SEOCK TUlIELS aerodynamic characteristics of external flow, Simulation of supersonic ramjet combustion chamber jet flap STOL model - graphs in shock tunnel [ NASA-TR-D-62221 N71-23124 B71-22630 Accident investigations. fliqht control systems. SEOCK WAVE ATTEIUATIOI and operational recordings for improved aircraft Supersonic flight path curvature effects on local f liqbt mechanics shock wave production, considering no boom zone [ AGARD-CP-76-71 J n7i-23410 and ground rules Design modifications on short takeoff Bronco A71-26310 aircraft resulting from combat operations tests SEOCK WAVE IIITERACTIOI N71-23416 Triple point trajectory of shock-shock aach Operational performance and handling safety reflection off plane wall. comparing to Whitham requirements for sinqle engine boundary layer theory controlled aircraft in STOL mode A71-26192 171-23419 Bypersonic cruise vehicles viscons interactions SIGIAL REFLECTIOI areas, examining compression corners, shock Landing systems signal reflection interference on interactions, laminar and turbnlent flow, correlation protected instrument landing system boundary layer separation, etc beams [AIAA PAPER 70-7811 A71-27551 [ RAE-TR-701411 N71-23361 Shock interaction effects on flapped delta wing at SILEICEBS hypersonic speed, presenting method for One dimensional flow models of internal combustion estimating reflected expansion wave impingement engine exhaust silencers in noisy systems boundaries and resulting aerodynamic 871-25180 coefficients SILICIDES 871-27598 Superalloy dispersion strenqthened and fused SEOCK WAVE PROFILES slurry silicide coatings for aircraft gas Laboratory high beta plasma shock wave generation turbine enqiues add space shuttle heat shields FAD-7173971 N7 1-221 66 All-25555 SROCK WAVE PROPAGATION SILICON ALLOTS Transonic compressor shock wave noise qeneration Comparison between silicon-magnesium-aluminum and decay rates at multiple tones, using sonic alloy and copper aircraft electric conductors boon analysis and terminals noting types of tests IASBE PAPER 71-GT-73 A71-25953 [ TRC-BR- 19185 ] N71-23547 SEOCK WAVES SILICOlE RUBBEE Transformation in air components due to marked Flame retardant silicone elastaers fcr ass .%s increase in temperature krinq iesnliy shock aircraft construction materials, describins wave fabrication techniques, mechanical, aqinq and N71-22640 weathering properties SRORT HAUL AIRCRAFT 171-27412 European airbus, considerinq flight trials of SILICOIES first A.3008 hiqh capacity transport aircraft Performance testing of fluorosilicone hydraulic A7 1-269 2 1 fluid in high temperature supersonic aircraft Normal and compound helicopters to be used as piston pumps short haul aircraft in view of burden on today's 171-27040 air traffic control SIELILATQFS N71-22189 Desiqn and development of lunar escape system Short haul vertical takeoff aircraft with lift cinolatsr fzr kvestiuation of iunar escape fays izccrporared in aircraft body, noting wide problems and simplified manual guidance and aircraft compartment control for lunar escape vehicles 171-22190 [ NASA-TN-D-6111] N71-22590 Propeller-driven short haul tilt wing aircraft SKIM (STRUCTURAL EEEBER) noting aerodynanic noise Boron-epoxy structural skins design for P-14 N71-22 191 honeycomb horizoutal stabilizer, using computer Comparison of automobile, rail transportation, and program short haul aircraft performance by means of 171-25420 market research notins central citv airports Graphite-epoxy composite skins for cocmercial i71-22192 aircraft flight spoiler. discussing aultianqle Cost analysis in vertical takeoff aircraft ply design and fabrication operation for short haul traffic notins A71-27413 influence of airport operation SKI' TEEPERATURE (IOI-BIOLOGICAL) n7i-22193 Heat flux sensor adapted for mounting on aircraft

SEORT TAKEOFF AIRCRIFT~~~ ~____ or spacecraft to measure aerodynamic heat flux Uing flap slipstream deflection correction method inflow to aircraft skic for evaluation of propeller power effect on lift [NASA-CASE-XPR-O3802] R71-23085 and draq coefficients of Arava twin enqine STOL SLEUDEB BODIES aircraft Aerodynamic characteristics of slender body of A71-25164 revolution traveling in long tube with circular Technical aspects of tactical all-weather cross section, deriving static and dynamic instrument landing system of Swedish STOL stability derivatives formulas aircraft Saab 37 Viggen A71-25477 A71-25233 Three dimensional incompressible flow about Wing design criteria imposed by biqh speed slender foil in perfect fluid, stressins vortex requirement for short takeoff aircraft, field effect considering thin sweptback winq with small All-27477 aspect ratio for lateral control Plow field model for steady asymmetric vortex All-27471 system shed from slender body of revolution in Turbofan STOL transport application to air coning motion transportation congestion, discussing [&IAA PAPER 70-521 A.71-27552 conditioninq landinq field length, Hypersonic uakes of two dimensional slender wedqes naviqational/control problems and jet flap and flat plate, testing stability in transition concepts region in wind tunnel A71-27602 All-27561 Evaluation of short takeoff aircraft for Procedures for predictinq properties of transonic commercial shuttle flight applications to reduce flows about thin airfoils and slender bodies traffic congestion in san Francisco, California NASA-CR-17223 N71-23133 area SLEIDEB WIlGS N71-21874 Loads induced on infinite aspect ratio winq by straight infinite free vortex in subsonic

A-41 SLIPSTREARS SUBJECT INDEX

compressible freestream, usinq planar lifting SOUND GEUERATORS surface theory Aerodynamic sound production and method of matched A71-25474 asymptotic expansions Unsteady flow downwash behind finite span slender N71-22467 winq durinq supersonic notion at finite strouhal Sound generation by small perturbation jet flow numbers TDLR-FB-71-02] N71-23596 A71-27697 SOUND PRESSURE SLIPSTRLAB5 Condenser microphones aerodynamically induced Plane and circular turbulent jet boundary layer noise, investigatiny acoostit i;zezs-re lower expansion in slipstream, comparing analytical limit dependence on air flow velocity and with experimental results turbulence A71-27505 A71-27063 Wind tunnel investiqation of lonqitudinal SOUUD PROPAGATION aerodynamic characteristics of semispan winq Effects of sound damping elements in subsonic wind deflected-slipstream confiquration with double tunnels slotted flap and auxiliary winq [RAE-LIB-TRANS-1465] N71-21885 r NASA-TN-D-63233 N71-23861 SOUND WAVES SLOTS Two dimensional sound wave equation Solution in Additional slot and flow fence effects on terms of time retarded arquments, derivinq aerodynamic characteristics of sinqle staqe analytical expressions for aircraft noise compressor bladinq intensity and power A71-25144 [ NASA-CR-726351 N71-21995 SRALL PERTURBATIOU FLOW sound radiation and wake turbulence spectra from sound qeneration by small perturbation jet flow axial compressor sinqle airfoils, includinq I DLR-FB-71-021 N71-23596 double circular arc profiles SNORE [ASHE PAPER 71-GT-41 A71-25950 Standard equipment and procedures for aircraft qas Aerodynamic noise scatterinq near Lighthill turbine engine exhaust smoke measurement multiples, considerinq intense near-field enerqy . r ASilE PAPER 71-GT-881 A71-25995 conversion into sound waves SNOW A71-26448 Investiqation of helicopter jet enqine flameout Sound radiation from time varyina point force in due to inqestion of snow and ice accelerative motion, applyinq to fan or [ NRC-11893 1 N71-21927 helicopter rotor noise at subsonic tip speeds SOCIOLOGT 1171-26702 Socioeconomic cbanqes in aeronautics, discussinq SOVEREIGNTY faster lonq ranqe aircraft, airport access Air and cosmic space common law, discussinq problems, technoloqical advances, short haul boundaries, sovereiqnty over state territories transportation and industry/qovernment relations and jurisprudence related to travel development A71-27601 A71-26325 SOFT LANDING SPACE LAW Fuel-optimal retrothrusted soft landinq of Air and cosmic space common law, discussinq airdrops tbrouqh atmo5phere boundaries, sovereiqnty over state territories [ AD-718405 1 N71-23487 and lurisprudence related to travel development SONIC BOOnS A71-26325 Transonic compressor shock wave noise generation SPACE PROGRARS and decay rates at multiple tones, usinq sonic Application of spacecraft technoloqy to aircraft boom analysis for improvement in systems, materials, and r ASME PAPER 71-GT-7 J A71-25953 performance Supersonic flight path curvature effects on local r NASA-TR-X-67073 J N71 - 2 2 394, shock wave production, considerinq no boom zone SPACE SEUTTLES and qround rules Tables and maps of selected landing airfields for A71-26310 shuttle orbiters with various crossranqes Plate and acoustic finite elements simulation of r NASA-TM-X-67080 ] N71-21996 window-room system coupled transient response to Lou subsonic lonqitudinal aerodynamic sonic booms, discussinq equations of motion and characteristics of twin body space shuttle cavity depth effect booster confiquration usinq low turbulence A71-27481 pressure tunnel - qraphs ileasurements of sonic boom pressure distribution r NASA-TU-X-2162 1 N71-23135 of bodies of revolution at Mach 2.96, 3.83, and Wind tunnel tests to determine sonic boom 4.63 in Unitary Plan wind tunnel characteristics of straiqht winq and delta winq [NASA-TN-D-61951 N71-21961 space shuttle durinq reentry into earth Proceedinqs and recommendations of conference on atnosphere sonic booms r NASA- Til- X- 6 2 0 30 ] N71-23296 r IG I A- 1 7~4.81 N71-21976 Requirements analysis of airbreathinq qas turbine Wind tunnel investiqation of lift-induced sonic enqines for shuttle vehicles boom characteristics of two simple winq models (NASA-TR-X-67806 ] N71-23764 at Mach numbers from 2.3 to 4.63 wind tunnel surface-flow visualization of dplta r NASA-TN-D-62011 N71-23125 winq shuttle confiquration at nach number of 7.4 wind tunnel tests to determine sonic boom and several Reynolds numbers characteristics of straiqht winq and delta wins [NASA-TM-X-620361 N71-23953 Space shuttle durinq reentry into earth SPACECRAFT DESIGN atmosphere Application of spacecraft technoloqy to aircraft INASA-TM-X-620301 N71-23296 for improvement in systems, materials, and Finite difference method for calculatinq sonic performance boom overpressure siqnatures in vicinity of r NASA-TM-X-67073 1 N71-22394 caustics SPACECRAFT INSTRORENTS IAD-718835 1 N71-23738 Optical projector system for establishinq optimum SOOT arrangement of instrument displays in aircraft, Air pollutinq nitric oxide and soot production by spacecraft, other vehicles, and industrial let aircraft, discussinq mixinq process and instrument consoles atmospheric dispersion r NASA-CASE-XNP-03853 3 N71-21882 [AIAA PAPER 70-1151 A71-27560 Combined optical attitude and altitude indicating SOUND FIELDS instrument for use in aircraft or spacecraft Axial flow fan noise, investiqatinq louvers r NASA-CASE-XLA-01907 3 N71-23268 effects on sound field SPACECRAFT SEIELDIUG A71-26704 Superalloy dispersion strenqthened and fused Aerodynamic sound production and method of matched slurry silicide coatinqs for aircraft qas asymptotic expansions turbine enqines and space shuttle heat shields N71-22467 A71-25555

A-42 SUBJECT INDEX STRESSES

SPACECRAFT STRUCTURES STATOR BLADES Glass fiber reinforced plastics aerospace Large axial compressor flow straightening stator applications covering radomes, dielectric blades unsteady pressure measurements with short panels, aircraft ducting. secondary structures, response time detectors furnishinqs, mouldings and toolinq A71-27469 A71-25652 Cold-air tests to determine oerformance SPECTRAL SIGUATURES characteristics of sinqle-staqe turbine with Tests for deteraining spectral signatures of stator blades eaploying transpiration coolant intearated hiah-freauencv antenna svstems for ejection through wire mesh shell P-3 dircraft . [ NASA-TB-I-21761 N71-23980 1110-718054 1 A71-23609 STEADY PLOP SPEECH Steady three dimensional subsonic nonviscous flow nethods for predicting speech interference within through turbomachine with arbitrary hub and cockpits of fixed wins and rotarv-~ wino aircraft shroud shapes and finite blade number, usinq rAa-718098] €171-23528 iterative blade to blade procedure SPHERES f ASnE PAPER 71-GT-21 a71-25949 Boundary effects of circular wind tunnel on Steady transonic flow throuqh two dimensional qas virtual mass of sphere turbine cascades predicted with time dependent [ AAL-TR-223 ] 171-22159 formulation of flow equations, qiving airfoil SPOILERS surface pressure distributions Graphite-epoxy composite skins for commercial [ ASlE PAPER 71-GT-89 1 A71-25996 aircraft flight spoiler, discussing multianqle Steady supersonic isoenergetic flow of thermally Ply design and fabrication and calorically perfect gas past circular cones A71-27413 at zero angle of attack, using dimensional STABILITY DERIVATIVES perturbation method Data reduction techniques for derivinq aerodynamic 1171-26939 forces and moments in absence of support STEELS interf ereuce Low alloy steels and superalloys inertia weldinq [ NAS A-CR- 11 1844 ] n7i-23122 in gas turbine field. discussing microstructure STAGIATIOI FLOW tensile strength and stress ruuture Enthalpy and wall heat flux calculations for [ASUE PAPZR 71-GT-21 J 811-25965 staqnation reqion aft of blunt axisymmetric Jet fuels deoxygenation effects on steels antiwear bodies in hvwrsonic axial flow properties and critical loading under [AD-717418). N71-22087 vibrational and gliding friction STAGlATI01 POIIT A71-27662 Two dimensional laminar boundary layer equation CTOI[ES FIOR iiriai drag coetficient from one and two term Stokes flow parachute ertrenely liqhtweiqht nerk expansion in regions upstream of stagnation decelerator for increasinq altitude and rocket- point borne radiosondes atmospheric data sampling A71-27051 quality Equilibrium air boundary layer flows at three [AIAA PAPER 71-4011 A71-2 5277 dimensional stagnation points, discussinq flow STRAII RATE characteristics and real gas heat transfer noire effect analysis of stress and strain of parameters machine parts and structural elements [AIAA PAPER 70-8091 A71-27582 [AD-717826] N71-22169 STAGUATIOI TElPERATURE STRAPS Shielded fine wire probe for total temperature Traversinq Infrared Inspection Svstee for C-5 rapid measurement is hiqh speed flows. aircraft fail-safe strap panels of bonded Ti-A1 discussing construction and theoretical laminates, discussing desiqn and application considerations [ASnE PAPER 71-DE-371 A71-27327 A71-25528 STRATOSPHERE STAIlLESS STEELS Aonexpandinq reflecting balloon for radar Elevated temperature effects on fatique life of measurement of stratospheric circulation tensile stressed titanium alloys, aluminum [ALL-!l-20326-/5828.4F/J R71-23934 alloys, and stainless steels STREAI PUICTIOIIS (FLUIDS) TAASA-TI-D-6145) 871-22076 Impeller blade loading vorticity on stream surface STAUDAEDS of revolution for mixed flow compressor. nsinq Standard equipment and procedures for aircraft gas annular cascade theory turbine engine exhaust smoke measurement [ASLIE PAPER 71-GT-17 J A71-25962 IASUE PAPER 71-GT-881 A71-25995 Lift and particle displacement around lifting body Safety standards development analysis for with stream function as fluid motion equation passenger vehicles and aircraft integral [AD-7183971 171- 2 3 33 3 1171-27577 STATIC PRESSURE STRESS (PEYSIOLOGY) Flutter of buckled plate exposed to static Routine unprotected exposure to acoustic noise pressure differential and streamwise applied in- within cockpits of trainer aircraft presentinq plane load, comparing experimental results with potential hazardous stress stability boundary calculations [AD-717852] R71-22U26 A71-27584 STRESS AlALYSIS STATIC STABILITY AUtOmted optimal weight fully stressed larqe Aerodyna=ic characteristics of slender body of scale structural design of aircraft, usinq revolution traveling in long tube with circular matrix- mathematical programming technique cross section, deriving static and dynamic [AIAA PAPER 71-3611 A71-25340 stability derivatives formulas noire effect analysis of stress and strain of 871-25477 machine parts and structural elements STATIC TESTS [ AD-7178261 N71-22168 low-inertia flow-direction vane static and dyuamic STRESS COlCElTPATIOU mind tunnel tests at subsonic and supersonic Loads on compressor, ventilator and turbine rotor speeds for in-fliqbt measurement of bust disks having larqe central holes, giving velocities formulas for stress distributions [ AASA-TW-D-6193 ] A71-231 15 A71-26952 STATISTICAL AIALTSIS STRESS IEASUREIEIT Theory, calculation, and desiqn of centrifuqal Surface strain measurements in turbine blades' by conpressor machines time average holoqraphic interferometry, [AD-717878 1 R71-23297 reviewing resonant modes and holographic frinqe STATISTICAL DISTRIBUTIOlS patterns Pattern of accident distribution for V/STOL [ ASBE PAPER 71-GT-841 1171-25'992 aircraft in United States of America STRESSES ~71-23426 Aircraft tires mechanical data froa small models,

A-43 STROUEAL NUHBER SUBJECT INDEX

discussinq mechanical properties, tire stresses r ASME PAPER 71-GT-34 1 A7145971 and tire temperatures Numerical solution of mixed supersonic and [AIAA PAPER 71-3461 A71-25325 subsonic steady wake flows by time-dependent STROUEAI NUMBER method Unsteady flow downwash behind finite span slender N71-22674 winq durinq supersonic motion at finite strouhal SUBSONIC SPEED numbers Subsonic and supersonic airline operations,

.."71-27697 I restraints. considerina noise. air pollution and STRUCTURAL ANALYSIS inadequate-airport facilities- Winq-fuselaqe-tail interactinq low speed flutter, A71-26870 considerinq mechanical tuninq and aerodynamic Multhopps subsonic liftinq surface theory, usinq interference couplinqs least squares method [AIAA PAPEP 71-3261 A71-25306 [NAL-TN-241 N71-22472 Koiter method for asymptotic analysis of Uind tunnel investiqation of hypersonic transport postbucklinq behavior reformulated in finite model aerodynamic characteristics at Mach element notation numbers to 6 - qraphs AD-717740 1 N71-22485 FNASA-TN-D-61911 N71-23127 STRUCTURAL DESIGN construction of leading edqes of surfaces for Ti intermediate diaqonal tension field shear beam aerial vehicles performing from subsonic to analysis and desiqn for Boeinq SST, usinq above transonic speeds Rayleiqh-Ritz method r NASA-CASE-XLA-01486 1 N71-23497 rAIRR PAPER 71-3401 A71-25319 SUBSONIC UIND TUNNELS Stability analysis and desiqn optimization uith IffecLs of sound dampinq elements in subsonic wind dynamics and aeroelastics constraints for tunnels helicopter rotor blade minimum weiqht uith [RAE-LIB-TRANS-14651 N71-21885 bendinq torsion flutter and favorable frequency SUPERCRITICAL PLOU placements Application of inteqral relations to inviscid [AIAA PAPER 71-3881 A71-25352 supercritical flow over symmetric airfoils at Prototype qraphite fiber/plastic fuselnoe zero anqle of attack component desiqn, test and performance [ AD-7173391 N71-22098 prediction, usinq structural analysis methods SUPERSONIC AIRCRAFT A71-25428 Pertormance testiiiq of fluorosilicone hydraulic Concorde aircraft construction methods, materials fluid in hiqh temperature supersonic aircraft and desiqn piston pumps A71-26882 A71-27040 Automated low cost structural-mechanical desiqn minimum draq surface shape of thick liftinq delta and optimization of winq pivot systems for winq inteqrated with conical fuselaqe for variahle qeornetry aircraft supersonic cruisinq speed [AIAA PAPER 71-4041 A71-27410 A71-27716 Flyinq safety factors in close to qround Planninq for expected civil aviation developments operational desiqn of XI!-51 helicopter caused bv chanae-over to Boeinq 747 aircraft and N71-23430 supersonic transport STRUCTURAL REMBERS N71-22381 Aircraft structural elements thermal behavior Planninq for civil aviation operations inclurlinq under aerodynamic heatinq with linear dc>pon.lence Boeinq 747 aircraft and supersonic aircraft on initial temperature N71-22382 ?. 7 1 - 27 4 9 3 market forecasts and traffic control technoloqies STRUCTURAL STABILITY of Boeina 747 aircraft and supersonic aircraft Torsional-flexural stability of stiffened Ti operations panels for application to supersonic transport, N71-22383 usinq small deflection enerqy methods Civilian airline operations with Roeinq 747 r?.TAA PAPER 71-3381 A71-25317 aircrafts and supersonic aircraft Inflation of initially spherical balloon of 171-22385 elastic rubber-like material, discussinq tensile Planninq parameters for hiqh capacity instability international airport system A71-25445 N71-22389 STRUCTURAL STRAIN Investiqation of lonqitudinal and lateral Noire effect analysis of stress and strain of stability and controllability of supersonic machine parts and structural elements aircraft r ~~-7175261 N71-22168 [AD-7182851 N71-23818 STRUCTURAL UEIGET SUPERSONIC BOUNDARY LAYERS Ueiqht minimization of semiinfinite flat sandwich Interaction theory for supersonic separated and panel at constant dynamic pressure in supersonic reattachinq turbulent boundary layers, comparinq flow subject to flutter constraint, usinq finite to real flow past compression ramp element model [AIAA PAPER 71-1281 A71-25476 [AIAI PAPER 71-3301 A71-25310 fieattachment anqle of supersonic laminar mixed SUBSONIC AIRCRAFT boundary layer, usinq revolution model with Cruisinq fliqht ranqe as function of Reynolds number allowance supersonic/subsonic transport fuselaqe A71-26194 qeometrical parameters Supersonic houndary layer transition on adiabatic A71-27494 wall, discussinq wind tunnel size, surfsce SUBSDNIC PLOP rouqhness and freestream disturbances effects Compressibility correction for subsonic flows Past rAIAA PAPER 70-5861 A71-27554 bluff bodies, considerinq boundary distortion SUPERSONIC COMBUSTION and pr-ssure distribution shift Supersonic combustion, fuel injection, and A71-25149 recirculation in hydroqen hypersonic external Loads induced on infinite aspect ratio winq by combustion at flat plates and bodies of straiaht infinite free vortex in subsonic revolution compressible freestream, usinq planar liftinq [DLR-FB-70-641 N71-22129 surface theory SUPERSONIC COMBUSTION RAMJET ENGINES A71-25474. simulation of supersonic ramjet combustion chamber Steady thrw dimensional subsonic nonviscous flow in shock tunnel throuqh turbomachine with arbitrary hub and N71-22630 shroud shapes and finite blade numbrr, usinq SUPERSONIC PLIGRT iterative blade to blade procedure Supersonic fliqht path curvature effects on local [ASME PAPER 71-GT-21 A71-25948 shock wave production, considerinq no boom zone :Hiqh subsonic flow two dimensional turbine cascade and qround rules d-iqn bv approximate hodoqraph method, notinq A71-26310 pressure distribution measurements

A-44 SUBJECT IHDEX SUPERSOHIC WIHD TUHHELS

Subsonic and supersonic airline operations, 871-27504 restraints, considering noise, air pollution and viscous flow in supersonic de Lava1 nozzle, inadequate airport facilities measuring gas density and rotational 1171-26870 temperatures by electron beam techniques Accelerated supersonic motion of plane at finite [AIAA PAPER 70-8lOl 171-27555 angle of attack SUPEBSOHIC SPBBDS [ NASA-TT-P-135251 N71-23278 Design, fabrication and static testinq of attached SUPEBSOHIC PLOW inflatable decelerator models for supersonic Cylindrical shells panel flutter analysis for wind tunnel evaluation internal stress and supersonic flow, considering [ RASA-CR-l11831] N71-22538 still air buckling data useful for determininq Hind tunnel investigation of lift-induced sonic buckling loads boom characteristics of two simple wiuq models [AIAA PAPER 71-3281 1171-25308 at Each numbers from 2.3 to 4.63 Breakup mechanism of liquid sheets and jets iu [ NASA-TN-P-62013 N71-23125 supersonic gas stream, using spark wind tunnel investigation of hypersonic transport photomicrographs and high speed movies model aerodynamic characteristics at Bach A71-25471 numbers to 6 - graphs Shielded fine wire probe for total temperature [ RASA-TN-D-6791J N71-23 127 rapid measurement in high speed flows, SUPERSOHIC TBAHSPOBTS discussing construction and theoretical ATC requlations considered for Coucorde considerations introduction to passenger service, discussinq A71-25528 landina and takeoff characteristics steady supersonic isoenerqetic flow of thermally A71-25232 and calorically perfect gas past circular cones Torsional-flexural stability of stiffened Ti

at zero auqle of attack, usinq dimensional panels for application to supersonic transport,~~ perturbation method using small deflection energy methods A71-26939 rAIAA PAPER 71-3383 A71-25317 Two phase supersonic barotropic flov with solid wind tunnel evaluation of analytical method for particles around thin proflle with allowance for predicting longitudinal stability and elastic particle collisions aerodynaiic characteristics of large flexible A71-27450 aircraft applied to supersonic transport Turbomachine blade cascades in supersonic flow, confiquration noting wave confiqurations. entropy and counter [AIAA PAPER 71-3431 A71-25322 pressure variations SST problems, including adequate instrumentation A71-27475 and fuel tank iamunization to explosion Partirle interaction vitE rcdqe =orface in 1171-26883 supersonic two phase flow. determininq incidence Reinforced plastics components in Supersonic coordinates and collisioI: frequency as function transport nose radome and missile radar of initial conditions antennas. discussinq molding, sandwich materials A71-27665 and computer controlled spraying techniques Unsteady flow downwash behind finite span slender A71-27016 wins during supersonic motion at finite Strouhal Cruising flight range as function of numbers supersonic/subsonic transport fuselage A71-27697 geometrical parameters Analysis of sopersonic and hypersouic flow of 171-27494 inviscid ideal qas over conical wings with sharp Pliqht tests of Boeing 747 aircraft and leading edges and attached shock waves by three operational analysis for snp-rsonic transport d;aan>iouai nethoa of characteristics N71-22386 [NASA-CR-17381 N71-22672 Aerodynamic characteristics affectinq stability Numerical solution of mixed supersonic and and controllability of supersonic aircraft snbsonic steady wake flows by time-dependent IAD-718474 J N71-23538 method SUPERSOHIC TURBIHBS N71-22674 Supersonic turbine design, presentino performance SUPERSONIC FLUTTER data for film cooled blunt leading edqe rotor Lifting surfaces supersonic-hypersonic flutter at blades measured in tvo dimensional cascade anqle of attack determined by shock expansion. experiments Newtonian flow and local flow piston theorv [ ASBE PAPER 71-GT-76 1 1171-25990 rAIAA PAPER 71-3271 A71-25307 SUPEBSOHIC WAKES Heiqht minimization of semiinfinite flat sandwich aaqnetically suspended laminar supersonic cone panel at constant dynamic pressure in sopersonic vake stability from hot vire fluctuation and flow subject to flutter constraint, using finite spectral components amplitude/phase measurements element model 871-25475 [AIAA PIPER 71-3301 871-25310 Numerical solution of mixed supersonic and Flutter analysis of clamped thin skev panels vitb subsonic steady wake flovs by time-dependent midplane forces in supersonic flow. usinq method Galerkin method 1171-22674 1171-26766 SUPERSOHIC WIHD TURlELS SUPERSOEIC BEAT TBAHSPER supersonic boundary layer transitior! on adiabatic Comparison of flat plate sharp and blunt edqe wall, discussing wind tucnel size, surface effects on heat transfer in supersonic flov and rouqhness and freestream disturbances effects heat transfer coefficient dependence on Reynolds [AIAA PAPER 70-5861 A71-27554 num ber Schlieren visualization for supersonic annular [ AD-7 17825 1 N71-22156 fixed cascade and freon compressor wind tunnels. SUPERSOHIC IHLETS using vane holding cyli?der devices Uind tunnel tests for instantaneous and dynamic A71-277 17 analysis of effects of time-variant distortions Lou-inertia flow-direction vane static and dynamic produced in supersonic inlet on J85-GE-13 vind tunnel tests at subsonic and supersonic turbojet enqiue speeds for in-flight measurement of bust [ NASA-TB-X-678211 N71-23927 velocities SUPEBSOHIC JET PLOW INASA-TN-D-61931 N71-23115 Screech noise generatioc by supersonic jet Dependence of low turbulence flov in supersonic impinqemeut on flat plate, discussing jet uind tunnel on conditions in supply header disintegration mechanism with resultant shock [ AD-7182271 171-23U80 wave oscillations Wind tunnel tests for instantaneous and dynamic A71-25521 analysis of effects of time-variant distortions SOPBRSOHIC HOZZLES produced in supersonic inlet OL J85-GE-13 Supersonic propellinq nozzle optimal parameters turbojet engine for maximum thrust coefficient, dlscussinq NASA-TB-X-67821] N71-23927 nozzle control and efficiency

A-45 SURFACE PROPERTIES SUBJECT INDEX

SURFACE PROPERTIES [ AD-7 177273 N71-22158 Surface strain measurements in turbine blades by Satellite applications to aircraft communications, time average holoqraphic interferometry, naviqation, and surveillance over 0s including reviewinq resonant modes and holoaraDhic,. frinoe synthesized satellite network and aircraft patterns equipment for air traffic control r ASME PAPER 71-GT-84 1 1171-25992 [NASA-CR-117760 1 171-22339 Hiqh aspect ratio planinq surface qlidinq on Location/identification transmitter and equipment infinitely deep. incompressibie. .inviscid, all; for nse in sztellit- applications in aircraft qravity-free fluid communication, navigation. and surveillance for r AD-7176671 N71-22345 US air traffic control SURFACE BEbCTIONS [ NASA-CR-1177591 N71-22340 Finite difference method for calculatinq sonic Uonte Carlo qeneral purpose shielding computer boom overpressure signatures in vicinity of proqram in FORTRAN 4 for IBU 7094 computer caustics [PNSI-TR-70-0301-1-VOL-1] N71-22379 r AD-718835 1 N71-23738 Simulation, analysis, and recommendations for SURFACE ROUGENESS fliqht profile of Concorde aircraft to predict Laminar boundary layer perturbation by sinusoidal and achieve improvements in aircraft operation - wall rouqhness, analyzing effect on transition VOl. 2 nature and position rPNSI-TR-70-0301-2-VOL-2] N71-22380 A71-27470 Flow control system design for blowdown wind SURFACE ROUGENESS EFFECTS tunnels and disturbance effects on regulatinq Supersonic boundary layer transition on adiabatic accuracy wall, discussing wind tunnel size, surface [ NAL-TN-221 N71-22476 rouqhness and freestream disturbances effects [ ATAA PAPER 70-586 3 A71-27554 Aerodynamically stable meteoroloqical balloon T usinq surface rouqhness effect T TAIL SURFACES [NASA-CASE-XRF-O4163] N71-23007 T tail flutter analysis, considering dihedral, Landinq accidents investiqations for Hawker angle of attack and aerodynamic force effects Siddeley 748 aircrafts with performance A71-25188 measurements on rouqh surfaces Estimatinq unsteady pressure distributions in T N71-23417 tail confiquration from measured distribution SURFACES and theory Liftinq surfaces supersonic-hypersonic flutter at [ NLR-TR-68048-Ll N71-23131 anqle of attack determined by shock expansion, T-33 AIRCRAFT Newtonian flow and local flow piston theory Technoloqy review on electric automobiles, and rAIAA PAPER 71-3271 A71-25307 modified T-33 aircraft system for pyrotechnic SWEAT COOLING hail suppression seedinq Cold-air tests to determine performance rDtlE/NAE-1970/4/] N71-22198 characteristics of single-staqe turbine with nodified T-33 aircraft system for pyrotechnic bail stator blades employinq transpiration coolant suppression seedinq ejection throuqh wire mesh shell N71-2220'3 [NASA-TR-X-21761 N71-23980 TABLBS (DATA) SWEPT WINGS Tables and maps of selected landing airfields for Surface flow photovisualization of straiqht winq shuttle orbiters with various crossranqes orbiter and swept delta winq orbiter NASA-TU-X-67080] N71-21996 confiqurations at Uach 10.9 and several Reynolds Operational fliqht data analysis for improved numbers aviation safety levels [NASA-TU-X-620331 N71-24001 N71-23411 SUEPTBACK WINGS TACAN Sweptback thin cantilever wing transonic flutter Technical aspects of tactical all-weather density and velocity coefficients, investiqatinq instrument landinq system of Swedish STOL enqine pod shaped concentrated mass location aircraft Saab 37 Viqqen effects A71-25233 A71-25189 TAIL SURFACES winq desiqn criteria imposed by high speed sailplanes tail load static derivation for requirement for short takeoff aircraft, instantaneous unchecked lonqitudinal maneuver, considering thin sweptback wing with small considering aperiodic response aspect ratio for lateral control A71-26486 A71-27471 Sailplanes control, derivinq incremental SISTERS ANALYSIS aerodynamic load on horizontal tail produced by Analysis of effects of spanwise variations of qust instantaneous elevator deflection velocity in isotropic turbulence on A71-26487 vane-controlled qust alleviation system TAKEOFF [NASA-TN-D-61261 N71-22068 Hutual aerodynamic effects of sn-1 helicopters Fliqht tests of Boeinq 747 aircraft and durinq simultaneous takeoff and landinq, operational analysis for supersonic transport determining minimum distances between N71-22386 helicopters Planninq parameters for hiqh capacity 871-26953 international airport system TANDEM WING AIRCRAFT N71-22389 Conference proceedinqs on vertical takeoff Integrated systems approach €or developinq aircraft technology, notinq tandem winq requirements of increased civil aviation in aircraft, tilt winq aircraft, helicopters, lift Israel fans, and jet enqines N71-22391 [DLR-UITT-70-151 871-22186 Requirements analysis of airbreathinq qas turhine Tandem tilt winq aircraft with tiltinq rotors enqines for shuttle vehicles notinq comparison with other V/STOL desiqns r NASA-TN-X-67806 1 N71-23764 N71-22188 SYSTEMS ENGINEERING TANK TRUCKS Airbornp radio communication systems, stressinq Electrostatic charqe by JP-5 jet fuel at truck electronic equipment desiqn reliability fill stand with 30-second relaxation chamber and A71-26880 bottom loading Hydraulically powered duplex input servos for [ AD-7173471 N71-22232 fliqht control system of VFV-Fokker V/STOL TAXIING fiqhter aircraft Power spectral deusity analysis of aircraft A71-26884 structural response to taxiinq produced random Isentropic-compression tube techniques producinq vibrations involvinq landing qear orifice hypersonic flow in wind tunnels includinq dampinq and Coulomb friction isentropic flow and free-piston shock tube modes A71-26311

A-4 6 SUBJECT IIIDEX TEIH UIBGS

TELECOIIUIIICATIOII TERBAIA POLLOPIIG AIRCRAFT Airborne radio communication systems, stressing Terrain following radar for airborne guidance of electronic equipment desiqn reliability low flying military aircraft A71-26880 A71-26981 TEIPEBATUBE DISTBIBU'ZIOI TEST EPUIPEBIIT Gas field nonuniformity as function of turbine Traiersinq Infrared Inspection System for C-5 enqine combustion chamber desiqn parameters, aircraft fail-safe strap panels of bonded Ti-A1 discussinq hot tube circumferential holes total laminates, discussing desigr. and application area effect [ASBE PAPER 71-DE-371 1171-27327 A71-2750 1 Fatigue test equipment for evaluating focker Effect of heat conduction of material on aircraft wing temperature distribution in vicinity of wing [ ALR-TR-70008-L. J A71-23157 leadinq edge in hypersonic flight TEST FACILITIES CREPT-6901 J 1171-22494 Ailitary aircraft flight test establishments, TEIIPERATUBE EWBCTS discussing airframe. enqine, fliqtt control and Aircraft tires mechanical data from small models, weapons delivery systems tests work flow discussing mechanical properties, tire stresses integration requirements and tire temperatures A71-26315 [AIAA PAPER 71-3461 1171-25325 Use of qun tunnel as low temperature test facility Aircraft structural elements thermal behavior for hypersonic intake research under aerodynamic heatinq with linear dependence P71-22635 on initial temperature Design and characteristics of device for launchinq A71-27493 models in wind tnrrels without disturbance of Elevated temperature effects on fatigue life of air flow tensile stressed titanium alloys, aluminnm rAASP-CASE-XNP-035731 N71-23030 alloys, and stainless steels TETEBBLIIIES [AASA-TN-D-6145 J N71-22076 Parachute decelerator tow1ir.e ererqT absorber TEIPEBATUBE IEASUBEIEWT shock attenuation characteristics, discussinq Shielded fine wire probe for total temperature drop test results rapid measnrement in hiqh speed flows, [ AIAA PAPER 70-1202 J A71-25527 discussinq construction and theoretical TEEEIIAL CTCLIIG TESTS considerations Aircraft power plants sealinq materials, 1171-25528 emphasizinq porous cermet seals heat resistance Viscous flow in supersonic de Laial nozzle. under thermal cyclic loads measuring gas density and rotational 171-27688 temperatures by electron beam techniques TRERII1L RESISTLICE jliii PirPEa io-tilo] 871-27555 Aircraft power plants sealinq materials, Air flow velocity, altitnde, fuel-air ratio, fuel emphasizing porous cermet seals heat resistance flow velocity, and pressure effects on fuel under thermal cyclic loads temperature before and after prevaporization in A71-27688 ramjet engines TEEBIODTIIAIIC BFFICIEICT [ AASA-TT-P-13605J N71-24053 Soviet book on theory of aircraft bladed machines TEIPEBATUBB PROBES covering axial flow, centrifuqal and conPosite Shielded fine wire probe for total temperature turbines and compressors. ttermodynamic rapid measurement in hiqh speed flows, efficiency, control turbocompressor matching, discussing constrnction and theoretical etC considerations A71-26401 :.? 1 - 2 5 5 2 8 TZEi3&3DPSAilIE PPOPEBTIES Eigh total temperature sensinq probe nsinq fluid Computer proqram to qenerate turbine aerodynamic oscillator concept for X-15 hypersonic aircraft requirements, approximate external blade AASA-CR-116772 3 B71-23250 qeometries, and coolant flow requirements for TEIPEBATUBB SEISOBS two staae axial flow turbine Beat flux sensor adapted for mounting on aircraft AASA-TB-X-22291 171-22568 or spacecraft to measnre aerodynamic heat flux TEICK WALLS inflow to aircraft skin solid profile winu motion near solid wall or free [AASA-CASE-XFR-O3802] A71-23085 surface, usinq acceleration potential method TEASILE DBFOBIATIOII 1171-27174 Inflation of initially spherical balloon of TEIA AIRFOILS elastic rubber-like material, discussing tensile Small surface curvature effect on nnsteady instability hypersonic flow over thin oscillatinq wedge, A71-25445 usins perturbation theory TEISILE PROPERTIES A71-26197 Flight service effects on residual tensile Three dimensional jet flapped wing matched properties of C-130 aircraft center winq plate asymptotic expansion solution for hiqh aspect section ratios based on thin airfoil theory assnminq [ BASA-CR- 11 18281 ~71-24021 inviscid and incompressible flow TEISILE STBESGTH A71-27217 Los alloy steels and superalloys inertia weldinq Two phase supersonic barotropic flow with solid in gas turbine field, discussing microstructure particles around thin profile with allowance for tensile strenqth and stress rupture elastic particle collisions [ ASIE PAPER 71-GT-Zl ] A71-25965 171-27450 TBRIIIAL FACILITIBS TEII PLATES Ten year forecast for eight major traffic Flutter analysis of clamped thin skew panels with cateqories at Washington Rational and Dulles midplane forces in supersonic flow, usinq International airports for period 1971 throuqh Galerkin method 1982 A71-26766 A71-21979 TEII SIHGS Performance tests and characteristics of capsule- Sweptback thin cantilever wing transonic flutter type and prismatic-head lights used for airport density and velocity coefficients. investiqatinq approach and rnnway lighting systems engine pod shaped concentrated mass location [ABS-10121] "71-22453 effects Computer graphics display proqram for use in A7-25189 terminal operations and V/STOL. approach and Thin delta wing in hypersonic inviscid flow at departure path synthesis small anqles of attack, calculatinq motion [AASA-CR-117887] 871-23186 equations and boundary conditions at small Index of standard instrument approach procedures perturbations for donestic ana foreign airports A71-27330 N71-23233 Wing desiqn criteria imposed by hiqh speed requirement for short takeoff aircraft, THREE DIlENSIONAL BOUNDARY LAYER SUBJECT INDEX

considerinq thin sweptback winq with small Ti, B and qraphite fiber composites application to aspect ratio for lateral control aircraft desiqn, discussinq mechanical A71-27471 properties and market competition Numerical intearation method based on potential A71-27676 flow theory to evaluate aerodynamic TITANIUl ALLOYS characteristics of thin supersonic wings Elevated temperature effects on fatigue life of r DLR-FB-7 1-01 1 N71-23597 tensile stressed titanium alloys, aluminum PBEEE DiKElSiGUAi DG3KDPBI ?,PYEE alloys, and stainless steels _I.,n-,< Three dimensional boundary layer flow and velocity NASA-TN-D-61457 ..-.n ! I-LLY IY profiles in mixed diffuser with equal anqle TORQUE walls Aerodynamic forces and hinqe moments of delta [ASBE PAPER 71-GT-401 A71-25973 cruciform control surface in blunt-nosed canard Three dimensional turbulent boundary layer confiquration for subsonic, transonic and calculations, usinq two dimensional method based supersonic flows on turbulent enerqy equation empirical A71-25161 conversion into shear stress transport equation TORSIOHAL STRESS A71-26443 Torsional-flexural stability of stiffened Ti Equilibrium air boundary layer flows at three panels for application to supersonic transport, dimensional staqnation points. discussinq flow usinq small deflection energy methods characteristics and real qas heat transfer rAIAA PAPER 71-3381 A71-25317 parameters TRAILIIIG EDGES lAIAA PAPER 70-8091 ~7:-275a2 Flat plate trailinq edqe problem solution THREE DIlENSIONAL PLOW consistent with second order boundary layer Underexpanded transverse sonic jet-hypersonic theory, establishinq laminar wake evolution stream three dimensional flowfield based on nature and upstream influence inviscid rotational flow model A71-25469 A71-25472 Hele-Shaw flow viscous tails from airfoil, Asymmetric three dimensional aerodynaai-c density observing hiqh Reynolds number trailinq edqe fields from holographic interferosrams, applyinq flow for separation and initiatioo of Kutta to supersonic flow from free jet condition A71-25802 A71-26447 Steady three dimensional subsor.ic nonviscous flow TRAILING-EDGE FLAPS throuqh turbomachine with arbitrary hub and Shock interaction effects on flapped delta Wing at shroud shapes and finite blade number, usinq hypersonic speed, presenting method for iterative blade to blade procedure estimatinq reflected expansion wave iapinqement rASflE PAPER 71-GT-21 A71-25948 boundaries and resultinq aerodynamic Three dimensional jet flapped vinq matched coefficients asymptotic expansion solution for hiqh aspect A71-27598 ratios based on thin airfoil theory assuminq TRAINING AIRCRAFT inviscid and incompressible flow Routine unprotected exposure to acoustic noise A71-27217 within cockpits of trainer aircraft presenting Three dimensionzl incompressi.blp flow about potential hazardous stress slender foil in perfect fluid, stressinq vortex r PD-7178521 N71-22426 field effect Beaqle 8125 traininq aircraft handlinq tests 1171-27477 r AAEE/963-PT-l 1 K71-23448 THRUST CONTROL TRAIIIIIIG SIRULATORS Pitchinq moment suppression on VTOL aircraft model Six deqree of freedom hybrid diqital computer by deflectinq jets in wind tunnel test proqram for complex fliqht control and I GAL-TP-2091 N71-22147 associated mode loqic desiqn and trainino THRUST lEASURElENT A71-25A52 Thrust measurement of aircraft and rocket TRANSFER FUNCTIONS propulsion systems, comparinq cost and Transfer functions in nodellino human pilot and characteristics of nechanical, electrical and dynamic structural aircraft responses hydraulic system r AGARD-R-580-71 1 N71-23210 A71-25991 Computation and measurements of dynamic aircraft Two variations of gas qenerator method to transfer functions to atmospheric turbulence calculate thrust of afterburning turbofan N71-23213 enqines installed in P-111A aircraft TRAIISFORlATIOUS (MATKElATICS) INASA-TN-D-629'1 N71-22614 Predictinq aerodynamic characteristics of arrow, TILT SING AIRCRAFT delta, and diamond wing platforms usinq Automated low cost structural-mechanical desiqn Prandtl-Glauert transformation and optimization of winq pivot systems for [ NASA-TN-D-6243 ] N71-21973 variahle qeoroetry aircraft TRANSIENT RESPONSE rAIAA PAPER 71-4041 A71-27410 Initially spherical liquid droplet transient Conference proceedinqs on vertical takeoff response under surface tension accelerated by aircraft technology, notinq tandem winq external qas flow aircraft, tilt winq aircraft, helicopters, lift [AIAA PAPZR 71-3931 A71-25355 fans, and jet enqines Plate and acoustic finite elements simulation of TDLR-MITT-70-15) N71-22186 window-room system coupled transient response to Tandem tilt winq aircraft with tiltinq rotors sonic booms, discussinq equations of motion and notinq comparison with other V/STOL desiqns cavity depth effect N71-22188 A71-27481 Propeller-driven short haul tilt winq aircraft TRAHSITION PLOS notinq aerodynamic noise Laminar boundary layer perturbation by sinusoidal N71-22191 wall rouqhness, analyzinq effect on transition TIlE DEPENDENCE nature and position Ti!mporal and spectral stimuli combinations effects A71-27470 011 iudq-d noisiness of aircraft sounds by Emmons spot theory extension for boundary layer colleqe students flow on blunt bodies, deducinq spot formation A71-27531 rate dependence on transition Reynolds and Mach TIThIIIOl numbers Torsional-flexural stability of stiffened Ti 1171-27557 pancls for application to supersonic transport, TEARSlISSOlETIRS usinq small deflection enerqy methods Development and evaluation of dual baseline IAIAA PAPER 71-3381 A71-25317 transmissometer used to measure and record ,Ti intermediate diaqonal tension field shear beam visibilities in range of nine to fifty analYSiS and desiqn for Boeinq SST, usinq kiloneters Rayleiqh-Ritz method (NBS-103391 N71-22455 [AIAA PAPER 71-3401 A71-25319

8-48 SUBJECT IRDEI TURBIIE UREELS

TRAUSllITTERS 171-22221 Location/identification transmitter and equipment TUN6STEB ALLOTS for use in satellite applications in aircraft Tunqsten reinforced oxidation resistant columbium communication, naviqation, and surveillance for alloys with operating temperature above 2000 P US air traffic control for use in gas turbine engines [ RASA-CR-117759] R71-22340 [ AD-717969) 1371-23673 TEAISOIIC COllPRESSORS TUIIUG Transonic compressor shock wave noise qeneration Uinq-fuselage-tail interacting low speed flutter, and decay rates at multiple tones, usinq sonic considericg mechanical tuning and aerodynamic boom analysis interference couplinqs [ASBE PAPER 71-GT-71 A71-25953 [AIAa PAPER 71-3261 A71-25306 TRAUSONIC PLOW TUPOLET AIRCRAFT Underexpanded transverse sonic jet-hypersonic Tu-154 responsibilities of three-man crews, stream three dimensional flowfield based on considerinq flight plan, refueling, cargo inviscid rotational flow model loading and unloading A71-25472 1171-25258 Tixe dependent aspptotic solution for transoilic TURBIIE BLADES flows in hyperbolic nozzle and turbine cascades Plow patterns within centrifuqal and mixed flow with oblique shock impeller channel, examiniuq velocity [ASnE PAPER 71-GT-423 171-25975 distributions, blade surface pressure and flow Steady transonic flow through two dimensional qas behavior turbine cascades predicted with time dependent [ASHE PAPER 71-GT-411 1171-25974 formulation of flow equations. givinq airfoil netal matrix composite fabrication nrocedures for surface pressure distributions qas turbine engine fan blades, stressing r ASflE PAPER 71-GT-891 A71-25996 diffusion bonding process susceptibility to Transonic airfoil testing techniques in two blades volume producibility dimensional flow, discussiuq wind tunnel [ ASnE PAPER 71-GT-463 1171-25979 conditions at various Reynolds numbers Supersonic turbine design, presenting perforsance A71-21467 data for film cooled blunt leading edge rotor Application of integral relations to inviscid blades measured in two dimensional cascade supercritical flow over symmetric airfoils at experiments zero angle of attack rASflE PAPER 71-GT-761 A71-25990 [ AD-7173391 N71-22098 Surface strain measurements io turbine blades by Procedures for predicting properties of transonic time average holographic interferometry, flows about thin airfoils and slender bodies reviewing resonant moaP.: a??? hol=grap:ic ilinqe IRASA-CR-1722] E?:-23i33 patterns asymptotic solution of low frequency winq [ XSflE PAPER 71-64-84] A71-25992 oscillations in transonic shockless adiabatic Quasi-axisymmetric and superposed fine fluctuating inviscid gas flow based on complete structure of ideal incompressible vortex flows approximation in axial flow turbines. assuminq infhite mutual R71-23193 blade proximity Finite difference method for calculating sonic 1171-27714 boom overpressure siqnatures in vicinity of neasurement of cooling air pressure changes caustics through stationary turbine disk and airflow [ AD-718835 1 871-23738 distribution within a blade at room temperature TRAISORIC FLUTTER and pressures from 28 to 100 psia Sweptback thin cantilever winq transonic flutter U&SA-T'-X-2?711 N71-22580 densitv aod v-lncity cceffizients. investlgating Conference on high temperature turbines detailing enqine pod shaped concentrated mass location effect of film coolinq on blade profile loss effects [ RASA-Tfl-X-671231 971-22699 1171-251 89 TURBIRE ERGIRES TEAISOAIC SPKED Superalloy dispersion strenqthened and fused Construction of leading edges of surfaces for slurry silicide coatinqs for aircraft qas aerial vehicles performinq from subsonic to turbine engines and space shuttle heat shields above transonic speeds 871-25555 [NASA-CASE-XLA-01486] 171-23497 Optimum weiqht protective system aqainst 'PRABSOBIC UIllD TOIUELS uncontained rotor failure with radial fragment Research and development in aerospace systems passage throuqh turbine enqine casinq including design and fabrication of 4-ft [ ASBE PAPER 71-GT-70 ] A71-25985 trisonic wind tunnel neasurement of coolinq air pressure changes 871-2233 1 through stationary turbine disk and airflow TRANSPORT AIRCRAFT distribution within a blade at ro3n tenperature medium weiqht AAflC C-1A tactical transport and pressures from 28 to 100 psia aircraft technical specifications [ NASA-Tfl-X-2171] N71-22680 A71-25231 TURBIUE EIBAUST IOZZLES Validity ranqe of response prediction methods for rime dependent asymptotic scluticn for trarcsonic large flexible aircraft to continuous flows in hyperbolic nozzle and turbine cascades atmospheric turbulence, discussing power with oblique shock spectral densities and fatigue life [ ASnf PAPER 71-GT-423 A71-25975 [AIAA PAPER 71-342) A71-25321 fleasurement of turbojet enqice exhaust nozzle European airbus, considerinq flight trials of performance as affected bv installation first A.300B high capacity transport aircraft parameters using load cells and calibrated 1171-26921 engines on P-106 aircraft Free fliqht tests in hoovering and forward flight [ RASA-T!I-X-67816] R71-23'322 of V/STOL transport model with six winq-mounted TURBIRE PUEPS lift fans High speed vane type main engine fuel pnmp for [ RASA-TR-D-6198 1 N71-22069 small gas turbine engines DO-231 V/STOL aircraft desiqn. noting passenger [ASRE PAPEE 71-GT-241 A71-25966 comfort, aerodynamic noise, aerodynamic TURBIUE WEEELS characteristics, and cost analysis Nonlinear limit rotation velocity and circulation N71-22187 induced by wheel in axial flow turbomachine for Analysis of normal accelerations throuqh center of incompressible ideal flnid. usinq iterative qravity of aircraft due to landicq impacts and numerical alqorithm ground operations associated with taxi, takeoff, Pll-277 15 and landing Couplinq characteristic effects on dynalcic [NASA-TR-D-6124] N71-22620 response of axially coupled tnrborotors with TRAVELING UAVES diqital computer proqram based on transfer Laboratory experiment on flow of viscous fluid aatrix techniques along travelinq waves N7 1-227 12

A-49 TURBINES SUEJECT INDEX

TURBINES [AIAA PAPER 71-3741 171-25347 Performance test of sinqle staqe turbine with low Steady three dimensional subsonic nonviscous flow solidity tan&= rotor blaEe assembyp through turbomachine with arbitrary hub and [NASA-CR-18031 N71-23132 shroud shapes and fifiite blade number, usinq TURBOCOIPRESSORS iterative blade to blade procedure Sound radiation and wake turbulence spectra from [ASnE PAPER 71-GT-21 A71-25948 axial campressor sinole airfoils, includinq Two dimensional flow in radial turbomachine bladed double circular arc profiles i-peller, comoarinq numerical solution based on [ ASME PAPER 71-GT-41 A71-25950 potential theory with experimental resuiis Soviet book on theory of aircraft bladed machines [ASUE PhPER 71-GT-201 871-25964 coverinq axial flow, centrifuqal and composite TURBOMACEINERY turbines and compressors, thermodyriamic Quasi-three dimensional surface velocities and efficiency, control turbocompressor matchinq, choking flow for turboaachine blade rows etc Calculated by FORTRAN program 1171-26401 [NASA-TN-D-6177 J N71-23126 Larae axial compressor flow straiqhteninq stator TURBOPROP ENGINES blades unsteady pressure measurements with short PT6A-6 turboprop enqine technoloqy leadinq to response time detectors turboprop, turboshaft and turbofan enqines A71-27469 development Exaaininq solutions obtained from streamline [SAE PAPER 7103851 A71-27536 curvature method cf calculatinq flow throuqh TURBOSHAFTS turbomachines tor several operatinq points of PT6A-6 turboprop enqine technoloqy leadinq to Rolls-Royce compressor turboprop, turboshdft and turbofan engines [ CUED/A-TURBO/TR- 191 N71-22294 development Effects of wave inlft distcrtion at hiqh and low [SAE PAPER 7103851 A71-27536 flow rate on performar.ce of axial flow TURBULENCE EFFECTS compressor Comparative vertical turbulence and loss [CUED/A-TURB@/Tli-20] N71-22428 restrictive stochastic models for threshold TURBOFAN AIRCRAFT crossing rotor blade flappinq vibrations at low Turbofan STOL transport application to air lift hiqh advance ratio transportation conqestion, discussing [AIAA PAPER 71-3891 A71-25351 conditioninq landinq field lenqth, Condenser microphones aerodynamically induced naviqational/control problems and jet flap noise, investiqatinq acoustic pressure lower concepts limit dependence on air flow velocity and A7 1-27602 turbulence TURBOFAN ENGINES A71-27063 Discrete frequency rotor interaction noise from TURBOLEIICE IETERS liftinq fans, usinq force harmonics actinq on Structure constant of jet exhaust turbulence of blades 3-57 with afterburner by laser beam probinq [ASME PAPER 71-GT-121 A71-25458 compared with scintillation and hot-wire Pesiqn and fabrication of Eorsic aluminum anemometer measurements composite fan blades €or supersonic turbofan A71-26304 enqines, considerinq 430 F application without TURBOLEIIT BOUNDARY LAYER severe vibratory stress Interaction theory for supersonic separated and [AS?IE PAPER 71-GT-101 A71-25997 reattachinq turbulent boundary layers, comparing Convertible fan/shaft enqine for V/STOL tactical to real flow past compression ramp and transport aircraft, detailinq mechanical [AIAA PAPSR 71-1281 A71-25476 arranqement, desiqn and performance Three dimensional turbulent boundary layer A71-26054 calculations, usinq two dimensional method based PT6A-6 turbopron enqine technoloqy leadinq to on turbulent energy equation empirical turboprop, turboshaft and turbofan enqines conversion into shear stress transport equation development A71-26443 [SAE PAPER 7103851 A71-27536 Plane and circular turbulent jet boundary layer TWO variations of gas qenerator method to eroansion in slipstream, comparinq analytical calculate thrust of afterburninq turbofan with experimental results enqines installed in F-111A aircraft A71-27505 [ NASA-TN-D-62971 N71-22614 TURBOLBNT FLOU Determination of low speed jet noise from fan Hypersonic cruise vehicles viscous interactions enqine for simulated nacelle confiquration areas, examininq compression corners, shock TNASA-TN-D-6314 3 N71-23134 interactions, laminar and turbulent flow, Jet noise contribution to far field sound from boundary layer separation, etc 1.83 meter diameter fan determined for two TAIAA PAPER 70-7811 A71-27551 simulated nacelle confiqurations Flight-measured base -pressures from sham leadinq [NASA-TM-X-678251 N71-24009 edqe upper vertical fin of X-15 aircraft TURBOJET ENGINES compared with wind tunnel data for turbulent Twin spool turbojet enqine dynamic response, flow at nach numbers from 1.5 to 5.0 discussinq simulator predictions, diqital [ NASA-TN-D-63481 N71-23922 computer control, nozzle area variations and TURBULENT JETS operatinq traiectories Curvature effects on laminar and turhulent free rASME PAPER 71-GT-141 A71-25960 jet boundary between irrotational flow and Low cost short life qas turhine desiqn based on stagnant fluid, discussing pressure effects pdranetric performance and component selection, A71-25482 outlininq turbojet product ion Interference phenomenon of subsonic turbulent jPt r ASIE PAPER 71-GT-69 1 A71-25984 exhausts from flat plate in low soeed cross flow Vertical straiqht lift turbojet enqine desiqn and rAD-718798] N71-23314 devel ?pent, present inq component materials TURBULENT UAKES properties/weiqhts, endurance tests and Sound radiation and wake turbulence SpeCtrd from performance data axial compressor sinqle airfoils, includinq [ASHE PAPER 71-GT-751 A71-25189 double circular arc profiles Uoasurement of turbojet enqine exhaust nozzle rAS?IE PAPER 71-GP-41 871-25150 performance as affected by inst?ll?tion Hake flow behind two dimensional perforated plates parameters usinq load cells and calibrated normal to air stream. mslsorinq draq, sheadina, enqines on F-106 aircraft velocity and turbulence at Reynolds nomber [NASA-TU-X-678161 N71-23822 25.000-90.000 TURBOI!ACEIRE BLADES A71-26449 Rotatinq low aspect ratio turbomachinery blades Feasibility and desiqn criteria of laser DopplPr natural frequencies and mode shapes, usinq system €or detectinq and mappinq turbulence finite element methoa for equilibrium equations levels and wind or velocity profiles in various eiqenvalue problevl applications

A-50 SUBJECT IRDEI VELOCITY DISTRIBUTIOA

I NASA-CR- 103105] R7 1-240 81 TWO DIIEISIOBAL FLOP Prandtl first order boundary layer equations for V two dimensional laminar incompressible flow past V/STOL AIRCRAFT circulation controlled circular liftinq rotor Convertible fan/shaft engine for V/STOL tactical A71-25494 and transport aizcraft, detailinq aecbmical TWO dimensional flow in radial turboaachine bladed arrangement, design and performance impeller. comparing numerical solution based on A71-26054 potential thaory with experimental results Bydraulically powered duplex input servos for rAS!IZ PAPER 71-61-20 J A71-25964 fliqht control systam of VPW-Pokker V/STOL Hiqh subsonic flow two dimensional turbine cascade fiqhter aircraft design by approximate hodoqranh method, notinq A71-26984 pressure distribution measurements Free flight tests in hooverinq and foruard fliqht rASIE PAPER 71-GT-341 871-25971 of V/STOL transport model with six winq-mounted Steady transonic flow through two dimensionai gas lift fans turbine cascades predicted with time dependent [ UASA-TR-D-619d1 11-17-22069 formulation of flow equations. giving airfoil DO-231 V/STOL aircraft aesiqn, notinq passenqer surface pressure distributions comfort, aerodynamic noise. aerodynamic IASME PAPER 71-GT-891 All-25996 characteristics, and cost analysis Ideal incompressible fluid flow around fixed ~71-22187 obstacle near rectilinear wall. investiqatinq Tandem tilt winq aircraft with tiltinq rotors plane motion with profile couple method- notinq comparison pith other V/STOL nesiqns All-26258 171 - 22188 Three dimensional tnrhuleqt boundary layer Cost analysis in vertical takeoff aircraft calculations, usinq two dimensional method based operation for short haul traffic notino on turbulent energy equation empirical influence of airport operation conversion into shear stress transport equation R71-22193 171-26443 node1 design for vertical takeoff aircraft cockpit Transonic airfoil testiag techniques in two noting navigation aids, visual displays, and dimensional flow. discussing wind tunnel console configuration conditions at vaiious Reynoids numbers U71-22196 All-27467 Computer qraphics display program for use in Laminar boundary layer on wing and body of terminal operations and V/STOL approach and revolution in presence of blouing departure path synthesis [ AASA-TP-F-13627] 1171-23796 r RASA-CR- 117887 ] F7?-23?85 TU0 PEASE FLOW operatianal perforsance of automatic V/STOL flight Two phase super-onic barotiopic fiow with solid control systems usinq jet thrust or air bleed particles around thin profile with allowance for AM-23415 elastic particle collisions Pattern of accident distribution for V/STOL 171-27450 aircraft in United States of America Particle interaction with wedge surface in R71-23426 supersonic two phase flow, determining incidence Plight safety performance of V/STOL Harrier coordinates and collision frequency as function military aircraft harinq jet control of initial conditions R71-23427 All-27665 Finite-element potential flow modelinq for TWO STA61 TURBIIES predicting roind lifting jet rolled in geometry Computer progran to generate turbine aerodynamic and path converaent intn rr?ns-flouinq c requirements. approximate external hlade mainstream as on VTOL or STOL aircraft ?e-metries. aa3 coolant flow requirements for [AD-l18121] A~I-23475 two stage axial flow turbine VAIES [ RASA-TI-1-2229 ] R71-22568 Hiqh speed vane type main engine fuel pump for saall gas turbine enqines r AS55 PAPBR 71-OT-24 ] A71-25966 U VAPORIZERS UIITED STATES OF AIIEUICA Low pressure drop fuel liquid injectors for jet US cooperation with ESRO UHF satellite system engine combustors, using qas turbine vaporizer development for air traffic control in-Europe desiqn r RASA-TT-F-136511 A71-23967 [ ASME PAPER 71-GT-381 871-25912 UBSTBADY FLOP VARIABLE GEOIIETRY STBOCTURES Small surface curvature effect on unsteady Variable qeometry external fuel tanks for hiqh hypersonic flow over thin oscillatinq wedqe, performance aircraft with draq reduction upon usinq perturbation theory fuel transfer 871-26197 [AIAA PAPER 71-3951 A71-25271 Unsteady flow measurement around uing sections Automated low cost structural-nechanical desiqn dUrinq rapid angle of attack variations, and optimization of winq pivot systems for emphasizinq helicopter rotor blades variable geometry aircraft A71-27468 [IiIAA PAPER 71-4041 A71-214 13 Unsteady flow downwash behind finite span slender VARIABLE SVEEP WIIGS wing durinq supersonic motion at finite strouhal Variable sweep wing aircraft anqular motion numbers matheratical model, analyzing inertial moments

171-77697I. . - . - - . influence on control dyaanics Accelerated snwrsonic motion of plane at finite A71-25667 angle of attack VELOCITY DISTBIBUTIOI r NASA-TT-P-135251 R71-23278 Flow variation effect on velocity and flow angle

Unsteady hydrodynaiic loads on two dimensional ~ distribution at exit of shrcnded radial flou hydrofoil impeller with backward swept blades, usina [ AD-717953 ] R71-23591 streamline curratore method UISPEPT PIIGS [ ASRE PAPER 71-GP-151 171-25961 Surface flow photovisualization of straiqbt wing Three dimensional houadaiy layer flow and velocity orbiter and swept delta wins orbiter profiles in mixed diffuser with equal anqle configurations at aach 10.4 and several Reynolds ualls numbers [ASlYE PAPER 71-GT-401 174-25973 [ RA SA-TI-1-62333 ] R71-24001 Plow patterns within centrifuqal and nixed flow UBBAI TRAISPORTATIOI impeller channel, examininq velocity Comparison of automobile, rail transportation, and distributions, blade surface pressure and flow short haul aircraft performance by means of behavior market research notinq central city airports [ASME PAPER 71-61-41 1 A71-25974 A71-22192 Laminar boundary layes on winq and body of revolution in presence of blowinq

A-51 VENTILATORS SUBJECT INDEX

[ NASA-TT-P-13627 1 N71-23796 VISUAL PERCEPTION VENTILATORS Aviation qround iightinq, visual landing aids, Loads on compressor, ventilator and turbine rotor dual baseline transmissometer, Dhotometric disks havinq large central holes, qivinq measurements of deck-landinq projector siqht, formulas for stress distributions and lamp for Fresnel optical landinq system A71-26352 18s-10508 J N71-22456 VERTICAL TAKEOFF AIBCELBT VJ-101 AIRCRAFT Pitchinq moment suppression on VTOL aircraft model Fiiq-ht mcchar?ira problems in accident by deflectinq jets in vind tunnel test investiqations for VJ-101 aircrart r NAL-TR-209 1 N71-22147 N71-23428 Conference proceedings on vercical takeoff VOLUBE aircraft technoloqy, notinq tandem vinq St.eady state inflated shape and included volume of aircraft, tilt winq aircraft, helicopters, lift 24 and 30 qore flat circular, extended skirt, fans, and jet enqines porous rinq slot, and porous ribbon parachutes r DLR-nITT-70-15 1 N71-22186 AD-7189081 N71-23387 Short haul vertical takeoff aircraft vith lift VORTEX BREAKDOWN fans incorporated in aircraft body, notinq vide Heat transfer to airfoil in oscillatinq flow at aircraft compartment larqe anqles of attack, shovinq vortex shed N71-22190 reattachment and Susselt nuabers increase Gas qenerators as vertical takeoff aircraft enerqy rASRE PAPER 71-GT-181 A71-25963 sourcez to operate lift fans or helicopter VORTEX GENERATORS rotary winqs safety measures to eliminate airc:aft trailinq N71-22194 vortex hazards comparison of two lift €an coniiqurations usinq [NASA-Tn-X-67125 J N71-23418 wind tunnel model pressure distributions VORTICES N71-22 195 Loads induced '3n infinite asoect ratio vinq by VIBRATION DABPING straight infinite free vortex in subsonic Helicopter blades inherent vibration dampins, compressible freestream, usinq planar liftinq comparinq theoretical and seiniempirical surface theory predictions to experimental results A71-25474 A7 1-271 23 Vortex shedding characteristics of circular VIBRATION EFFECTS cylinders at lov Reynolds numbers from Inertial naviqation system consistinq of qyro experiment on tapered models wake structure horizon compass, directional qyro and computer, 1171-27220 considerinq errors due to compass vibrations narqinal vortex effects on aerodynamics of A71-27169 helicopter liftinq surfaces, considerinq blade VIBRATION TESTS form and noise spectrum tested in hydrodynamic nodal characteristic pick-up system for vibration tunnel tests of rockets or aircraft on qround, usinq A71-27473 small size accelerometers vith individual Three dimensional incompressible flow about electronic circuit slender foil in perfect fluid, stressing vortex 1171-27 11'4 field effect Theoretical analysis of jet mixinq under influencr 1171-27477 of nonconstant pressurs qradisnt Flow field model for steady asymmetric vortex rARL/nE-1271 N71-22593 svstem shed from slender body of revolution in Rotor-bearinq qstem analysis to determine cause coninq motion of brinellinq failure of bgarinqs from vibrat.ion [AIAA PAPER 70-521 1171-27552 tested PLV fans ouasi-axisvmmetric and superposed fine fluctuatinq NASA-CR-1179551 N71-22527 structure of ideal incompressible vortex flows VIBRATIONAL STRESS in axial flov turbines, assuminq incinite mutual Desiqn and fabrication of Borsic aluminum blade proximitv comDosite fan blades for supersonic turbofan A71-27714 enqiiies, considerinq '433 F aoolication vithout Aerodynamic characteristics of near wakes produced severe vibratory stress by periodic vortex sheddinq from airfoils ASME PRPER 71-GT-30 J A71-25997 r AD-7188931 N71-73245 VIBRATORY LOADS VORTICITY Lift coeffient for vind induced vibration of Impeller blade loadinq vorticity on stream surface skewed cylindrical body of revolution for mixed flov compressor, usinq r AD-7177391 N71-22159 annular cascade theory VISCOUS FLon [ASRE PAPER 71-GT-171 A71-25762 Aypersonic cruise vehicles viscous interactions areas, examininq compression corners, shock W interactions, laminar and turbulent flov, boundary layer separation. etc WAKES r AIAA PAPER 70-781 1 A71-27551 Wake flov behind two dimensional perforated plates Viscous converqent-diverqent nozzle flov slender normal to air stream, measurinq draq, sheddinq, channel approximation, discussinq nozzle velocity and turbulence at Reynolds number qeometry. Reynolds number and vall temperature 25,000-90.003 e? f ects A71-26449 [AXAA PAPER 69-6541 A71-27556 Vortex sheddinq characteristics of circular Boundary layer separation in viscous flov around cylinders at lov Reynolds numbers from riqid bodies experiment on tapered models vaue structureA71-27220 TAD-7177721 N71-22241 VISCOUS FLUIDS WALL mon Laboratory Oxperiaent on flov of viscous fluid Ideal incompressible fluid flov around fixed alonq travplinq vaves obstacle near rectilinear wall, investiqatinq N71-22221 plane motion vith profile couple method VISIBILITY A71-2625R Dcvc>lopnrnt and evaluation of dual baseline Supersonic boundary laver transition on adiabatic transmissomet.er used to measure and record wall, discussing wind tunnel size, surface visibilitips in ranqe of nine to fifty rouqhness and freestrean disturbances effects kilometers rAIAA PAPER 70-5861 A71-27554 r NBS-10339 1 N71-22455 Boundary effects of circular wind tunnel on VISUAL AIDS virtual mass of sphere Concord* economic fliqht testinq methods, NAL-TR-2231 N71-22159 discussinq Blaqnac fliqht simulator mobile cabin WALL JETS visualization and color TV terrain model Optimal blowiuq wall jet prediction for A71-27608 suppressing separation from hiqh lift aerofoils vith incomplete mixinq of upstream boundary

A-52 SUBJECT IlDEX UIBD TUAUELS

layer Lift coeffient for nind induced vibration of 171-26196 skewed cylindrical body UALL TEEPEBATURE [ AD-7177391 N71-22169 viscous convergent-divergent nozzle flow slender VIAD SBEAR channel approximation, discussinq nozzle Aircraft approach and landinq under low altitude geometry, Reynolds number and wall temperature wind shear conditions, discussing flying hazards effects and glide path correction procedures [AIAA PAPER 69-6541 A71-27556 A71-26364 VATEB VIUD TUUIEL APPARATUS Evaluation of Aqua-610 free water detector for use Schlieren visualization for supersonic annular in measuring undissolved rater in hydrocarbon fixed cascade and freon conpressor wind tunnels, fuels using vane holding cylinder devices IAD-7184181 N71-23438 A71-277 17 UAVE EQUATIOUS Design and characteristics of device for launching TVO dinensional sound wave equation solution in models in wind tunnels without disturbance of terms of time retarded argnments, derivinq air flow analytical expressions for aircraft noise [ NASA-CASE-XHP-03578] N71-23030 intensity and power VIUD TUUEEL IIODELS A71-25144 wind tunnel evaluation of analytical method for Solution of Lighthill gas model wave equation for predicting lonqitudinal stability and engine noise generation in circular jets notins aerodynamic characteristics of larqe flexible cylindrical coordinate system aircraft applied to supersonic transport IDLR-PB-70-57 I N71-22070 configuration Aerodynamic sonnd production and method of matched [AIAA PAPER 71-3431 1171-25322 asymptotic expansions Pressure orifices inclination in low density flow N71-22467 from experiments with cooled flat plate codel in WAVE GEAEBATIOU hypersonic low density rind tunnel Laboratory high beta plasna shock wave generation A71-25490 [ AD-7 17397 ] A7 1-22 166 Pitching moment suppression on VTOL aircraft model UAVEFOBES by deflecting jets in wind tunnel test Torbomacbine blade cascades in supersonic flow, r RAL-TR-209 J N71-22147 noting wave confiqnrations. entropy and counter comparison of two lift fan configurations usinq pressure variations wind tunnel model pressure distributions A71-27475 N71-22195 UEAB TESTS Design, fabrication and static testing of attached Jet fuels deoxyqenation effects on steels antiwear inflatable decelerator .crlzls for supersonic properties and critical loading gnder wind tunnel evaluation vibrational and qliding friction [NASA-CR-111831] 171-22538 A71-27662 Desiqn and characteristics of device for launching VEATEEB models in wind tnnnels without disturbance of Weather minimnn standards for civil aircraft, air flow considerinq cloud ceilings, visibility, wind [ NASA-CASE-XNP-03578 ] N71-23330 velocity and direction, onboard and ground-based uind tunnel investigation of lift-induced sonic flight control equipnent and aircraft boon characteristics of two sinple wing models characteristics at aach numbers fro. 2.3 to 4.63 A71-27141 [ NASB-TN-D-6201] 1171-23125 Weather factors in fatal civil transport aircraft aind tunnel study of auqnented ram-winq vehicle accidents w5th vsrisns blouiilg arranqeeents N71-23431 rPB-1894251 N71-23283 UEDGE FLOU sind tunnel tests to determine sonic boom small surface curvature effect on unsteady characteristics of straight wing and delta wing hypersonic flow over thin oscillating wedge. space shuttle during reentry into earth using perturbation theory atmosphere A71-26197 [ NASA-T!l-X-62030 J N71-23296 UEDGES wind tunnel surface-flow visualization of delta Ayoersonic rakes of two dimensional slender wedges viug shuttle configuration at aach number of 7.4 and flat plate, testinq stability in transition and several Reynolds UnBbeKS reqion in wind tunnel r NASA-TB-I-62036 N71-23953 A71-27561 UIHD TUNUEL STABILITY TESTS Particle interaction with wedge surface in Bypersonic wakes of two dimensional slender wedges supersonic two phase flow, determininq incidence and flat plate, testing stability in transition coordinates and collision frequency as function reqion in wind tunnel of initial conditions 1171-27561 A71-27665 Nose bluntness effect on aerodynamic UEIGET (IIASS) characteristics of flared body in supersonic Boundary effects of circular wind tunnel on wind tunnel virtual mass of sphere [ NAL-TR-2213 1171-22160 r NAL-TE-223 ] A71-22159 wind tunnel investigation of static lonqitndinal UEISET AUALXSIS and lateral characteristics of full scale mockup Automated optinal weight fully stressed larqe of liqht twin engine aircraft scale structural design of aircraft, usinq r NASA-TN-D-62381 871-23860 matrix- mathematical prograsming technique wind tunnel investigation of lonqitudinal [AIAA PAPER 71-3611 A71-25340 aerodynanic characteristics of senispan ring WELDIUG deflected-slipstream configuration with double Low alloy steels and superalloys inertia weldinq slotted flap and auxilidry wing in gas turbine field, discussinq microstructure r NASA-TN-D-6323 J N71-23861 tensile strenqth and stress rupture UIUD TUUAEL UALLS [ASBE PAPER 71-GT-21 J A71-25965 Boundary effects of circular wind tunnel on VELDIAG IIACEIUBS virtual sass of sphere Jet enqine components inertia welding, discussing [ HAL-TR-223 1 N71-22159 process, equipment, low weiqht-cost advantage VIUD TUUUELS and mechanical properties reproducibility Aiqh temperature aerodynanics with electrosagnetic IASBE PAPER 71-GT-33 J A71-25970 radiation, considering thernally radiating shock UIUD EFFECTS layers, electric arc driven wind tunnels and gas Wind gradient effect on fliqht characteristics dynamic lasers durinq aircraft landing spproach, particularly A71-27277 path deviation Transonic airfoil testinq techniques in tV0 1171-25194 dimensional flow, discussinq rind tunnel conditions at various Reynolds numbers

A-53 WIND VANES SUBJECT IIIDEX

A71-27467 Flight-measured base pressures from sharp leading Summary of aeronautical research, and wind tunnels edge upper vertical fin of X-15 aircraft N71-23931 compared with wind tunnel data for turbulent WIND VANES flow at Hach numbers from 1.5 to 5.0 Analysis of effects of spanwise variations of qust [ NASA-TN-D-63481 N71-23922 velocity in isotropic turbulence on 18-51 EELICOPTER vane-controlled qust alleviation system Flying safety factors in close to ground r NASA-TN-D-6126 i N71-22068 operational desiqn of XH-51 helicopter Low-inertia flow-direction vane static and dynamic N71-23430 wind tunnel tests at subsonic and supersonic speeds for in-fliqht measurement of bust velocities Z [NASA-TN-D-61931 N71-23115 ZERO ANGLE OF ATTACK WIND VELOCITY IEASUREflENT Application of integral relations to inviscid Low-inertia flow-direction vane static and dynamic supercritical flow over symmetric airfoils at wind tunnel tests at subsonic and supersonic zero angle of attack speeds for in-fliqht measurement of bust [ AD-7173391 N71-22098 velocities Separated flow over flat plate with blunted fin at [ NASA-TN-D-61931 N71-23115 zero anqle of attack WINDOWS (APERTURES) [ AD-7177171 N71-22300 Plate and acoustic finite elements simulation of window-room system coupled transient response to sonic booms, discussinq equations of motion and cavity depth effect A71-27481 WING FLAPS Automatic aust alleviation system employinq inertial sensors and feedback devices with wing flaps and elevators, considering linkaqe control, noninteractinq control and split control A71-25195 Liftinq force of winq with rotating flap, derivinq lift increase due to circulation redistribution at surface 1171-27491 WING LOADING Loads induced on infinite aspect ratio winq by straiqht infinite free vortex in subsonic compressible freestream, usinq planar lifting surface theory 1171-25474 Wind tunnel study of auqmented ram-winq vehicle with various blowinq arranqements r ~~-189425I N71-23283 WING OSCILLATIONS Comparative vertical turbulence and loss restrictive stochastic models for threshold crossinq rotor blade flappinq vibrations at low lift hiqh advance ratio [AIAA PAPEE 71-3891 A71-25351 small surface curvature effect on unsteady hypersonic flow over thin oscillatinq wedqe, usinq perturbation theory A71-26197 Asymptotic solution of low frequency winq oscillations in transonic shockless adiabatic inviscid qas flow based 01 complete approximation 87 1-23 193 WING PANELS Fliqht service effects on residual tensile properties of C-130 aircraft center winq plate section [NASA-CR-1118281 N71-24021 WING PROFILES Solid profile winq motion near solid wall or free surface, usinq acceleration potential method A71-27174 Unsteady flow measurement around winq sections durinq rapid angle of attack variations, emphasizinq helicopter rotor blades A71-27468 WING SPAN Aircraft wake turbulence with downwash loadinq of winq span [AD-718024 1 N71-2366G WINGS Hiqh lift winq characteristics with/without additional devices, eaphasizinq lift control and load distribution 171-27476 X X-15 AIRCRAFT Hiqh total temperature sensinq probe usinq fluid oscillator concept for X-15 hvpersonic.. aircraft~____ [NASA-CR-1167721 871-23250

A-54 PERSONAL AUTHOR INDEX

AERONAUTICAL ENGINEERING / A Special Bibliography (Suppl. 7) JULY 197 1

Typical Personal Author Index Listing

[ ASRE PAPER 71-GT-U6] A71-25974 PERSONAL AUTHOR ALPBEDSOH. E. J. Performarice of exhaust silencer comporents Investiaatim of two methods for improving the crashworthiness intesrsl fuel tanks Final A71-25185 I of ALPEEI, E. report, 1967 1970 W. - Liquid distribotions of a low pressure drop [?AA-qA-70-46] iniection svstem - Gas turbine 'vaporizer' deiiqn TASIlE PAPER 71-GT-381 A71-25972 AIIET; E. K. Aerodynamic sound production and the method of matched asymptotic expansions A71-22467 Listings in this index are arranged alphabetically by personal author The AUDEE.5011, J. D., JB. Kiqh temperature aerodynamics with electromaqnetic title of the document provides the user with a brief description of the radiation sublect matter The repon number helps to indicate the type of document b.71-27277 cited (eg NASA repon translation NASA contractor reponl The accession AUDEEW. J. number is located beneath and to the right of the title eg N71-11019 Subsonic and supersonic operations in the years Under any one authors name the accession numbers are arranged in se ahead - Sir Charles E. Kingsford-Smith memorial quence with the IAA accession numbers appearing first Lecture , A71-26870 AUDBEWS. D. A New Experimental Tc-chniques in Propulsion and AAS. E. G. Enerqetics Research Koloqraphic anlalysis of turbine blades IAGARD-CP-38 I mi-22626 [ASBE PAPER 71-GT-841 A71-25992 APEL. K. ABAD, 6. Experience qained in the operational preparation On the accuracy of lerk's method for solution of and putting into service of the IL-62 lonq-haul laminar boundary-layer equations jet aircraft A71-27051 A 7 1- 2 5256 ABDELBAIID. A. U. AKBEE. J. I Discrete frequency noise from liftina fans Analogue recursive ComDUtc-r [ASBE PAPER 71-GT-12) all-25952 A71-27150 AEEL, I. AEIGA, I. A critical wind-tunnel evaluation of a technique Effects of Reynolds number on performance for predictins static aerodynamic characteristics of a centrifugal compressor characteristics for a highly flexible supersonic [ ASBE PAPER 71-GT-25 J A71-25967 transport configuration AEROLD. J. I. [AIAA PAPER 71-3431 1.71-25322 The effect of active controls on structural ACHBIIBACE. E. responses Experinental determination of the momentum A71-23212 thickness of a circular cylinder in a cross flow ASCAlI, 1. A71-27738 Rapid analysis methods for the desiqn and ACKITOPP. 1. optimization of winq pivot systems for variable The airplane and the airport qeometry aircraft mi-22389 [AIAA PAPER 71-U04] A71-27410 ADACEI, T. ASKPOETE. E. E. A note on the T-tail flutter The operational proving of automatic fliqht A71-25188 control systems in the approach and landiua A6EEI. ZE. S. phase Effect of changing rinq sweep on the dynamics of N71-23414 the controlled processes AXELBAUD, B. I. A71-25661 Quasi-optimum proportional navigation AGGAEPAL, S. E. A71-26409 The role of heat conduction in leading edge heating - Theory and experiment [ BEPT-6901 1 ~71-22494 6 AEAEEAE. E. C. BAILEY, J. I. Lou altitude hiqh speed flight experience Simplified guidance and control n7i-23421 [ AD-7175671 A71-21915 AKSEUOI. A. P. BAILET, E. 6. Effect of the deoxvqenation of iet fuels on their Kiqh total temperature sensing probe for the X-15 antiuear properties hypersonic aircraft A71-27662 r~~s~-~~-i167721 N71-23250 ALEKSAUDBOI. A. D. BAKEE. W. E. Prospective automatic flight-control systems Inherent vibration dampinq of helicopter blades A71-267 16 171-27 123 ALEXAIDEE. E. BAKUE, B. I. Tensile instabilitv of initiallv.. sDherica1 The effects of flow containing dust on the results balloons of hypersonic rind tunnel experiments A71-25445 [AASA-TT-P-135291 U71-23702 ALEIAUDEE. J. A. BALAKBISEIA. S. metal matrix composite fabrication procedures for Wind tunnel pressure requlating systems gas turbine enqine blades [AAL-TN-22] A71-22476 BALE. Y. S. PERSONAL AUTAOR INDEX

BALE, Y. 5. corrections at R1 Ch A new method for the calculations of blade A71-27467 loadinqs in a radial flow compressor BEST, U. A., JR. [ASHE PAPER 71-GT-601 A71-25982 Let's do away with foq BALL, C. 1. A71-27247 Overall performance in argon of a 16.4 centimeter BETTNER, J. 1. /6.44 inch/ sweptback bladed centrifuqal Desiqn and experimental results of a highly compressor loaded, low solidity tandem rotor r NASA-TH-X-22691 N71-23659 [NASA-cR-i8;3i N71-23132 BARKER, 1. K. BIELAUA, R. 1. Analysis of effects of spanwise variations of qust Techniques for stability analysis and desiqn velocity on a vane-controlled qust- alleviation optimization with dynamic constraints of system nonconservative linear systems [NASA-TN-D-61261 N71-22068 [AIAA PAPER 71-3881 A71-25352 BARR, G. BIENIEK. n. e. Recent contributions to experiments on cylindrical Safety factors and the probability of failure in shell panel flutter fatigue [AIAA PAPER 71-3281 A71-25308 A71-25492 BARRON. R. 1. BIGGERS, S. B. Applications of self-orqanizinq and learninq Dynamic interactions of high speed tracked air control to aeronautical and industrial systems cushion vehicles with their auideways - A r ASRE PAPER 71-~~-22I A71- 27 324 parametric study BASTIDON, J. [AIAA PRPER 71-3861 A71-25350 Establishinq safety marqins for the take off and BLAKE, B. A. 1. approach of the Brequet 941 Airborne communications systems N71-23420 A71-26880 BATRA, 5. K. BLATT, J. D. Analvsis of brinellinq failure of bearinas from Technoloqical trends and forecasts for the 1970's vibration tested PLV fans summary report N71-22383 [NASA-CR-1178551 N71-22527 BOICAUK, 0. P. BAUER, A.-J. Theory of an inertial naviqation System Aerodynamically induced noise of condenser constructed on the basis of a qyrohorizon microphones compass A71-27063 A71-27169 BAXTER, R. D. BOISSEAU, J.-P. Heat flux neasurinq system Patent Accelerometric circuits for the measurement Of [NASA-CASE-XFR-038021 N71-23085 modal characteristics BAZIN, n. A71-27719 Review of testinq techniques for transonic BORODIN, A. E. airfoils. I - Apparatus for commercial tests at Effect of the deoxyqenation of jet fuels on their S3nA. I1 - Experimental ztudy of wall antiwear properties corrections at R1 Ch A71-27662 A71-27467 BOSSE, P. C. BEAI. R. A. Preliminary desiqn and analysis of an advanced Optical projector system Patent convertible fan/shaft enqine for V/STOL tactical NASA-CASE-XNP-03853 1 N71-21882 and transport aircraft BEEIAN. E. R.. JR. A71-26054 Flow fields over sharp edqed delta winqs with BOORQUE, C. attached shocks Reattachment of the supersonic laminar boundary [ NASA-CR-17381 N71-22672 layer BEANING. P. P. A71-26194 Cold air investigation of a turbine with BOYCE, n. e. transpiration cooled stator blades 4 - Staqe A new method for the calculations of blade performance with wire-mesh shell stator bladinq loadinqs in a radial flow compressor [ NASA-Tn-X-2176 1 N71-23980 [ASHE PAPER 71-GT-601 1171-25982 BEARENS, U. BOZZOLA, R. Experimental stability studies in wakes of two- A numerical technique for the calculation of dimensional slender bodies at hypersonic speeds transonic flows in turbomachinery cascades A71-27561 [ASHE PAPER 71-GT-421 A71-25975 BELIANSKII, V. P. BRADSEAU, P. Effect of the deoxyqenation of jet fuels on their Calculation of three-dimensional turbulent antiwear properties boundary layers A71-27662 A71-26443 BELITSKII, 6. E. BBENNER, A. Equipment UIT-1200/50 for determininq the heat NAHC C-1A - Japan's tactical transport resistance of sealinq materials 1171-25231 A71-27688 BRENT, J. A. BEN-ARI. 1. single stage experimental evaluation of compressor Probiems of civil aviation in the next decade bladinq with slots and wall flow fences N71-22385 [ NASA-CR-726351 N71-21995 BENJAMIN. J. BRICKSOII, n. E. Determination of CPILS localiser beam noise USAF air mobility via expandable Structures IRAE-TR-701411 N71-23361 TAIAA PAPER 71-3981 A71-25274 BENNETT. R. 1. BRINK; K. B. Effects of temporal and spectral combinations on The VTOL jet for a future V/STOL transport system the judqed noisiness of aircraft sounds N71-22187 A71-27531 BROOKLBI, U. Q. BENNETT, A. n. Cleaner fuel through nitroqen inertinq Analysis of supersonic-hypersonic flutter of [ ASHE PAPER 71-GT-U5] A71 -25978 liftinq surfaces at anqle of attack BRUN, E. A. [AIAA PAPZR 71-3271 A71-25307 Experimental study of the laminar boundary layer BENSON. N. S. uith catalytic reaction of the uall nnaiytical and experimental studies of two- N7 1-22640 dia,=n?ional flous in a radial bladed impeller BUCEIIAIIN, 0. A. (ASIS PAPFR 71-GT-201 A71-25964 An analytical study of hydrogen cooled panels for BERNARD-GUELLE, E. application to hypersonic aircraft Revi<,w of t'?stiiq techniques for transonic f NASA-CR-16501 N71-22625 airfoils. I - Apparatus for commercial tests at BURCAAI, P. W., JR. S3nA. I1 - Experimental study of wall An investiqation of two variations of the qas

8-2 PKBSOUAL AUTEOB IBDKI

generator method to calculate the thrust of the diagnosis of naval turbine engines afterburning turbofan engines installed in an [ ASIE PAPER 71-GT-861 A 71 -2 599.4 F-111A airplane CEAPLIU. J. C. [NASA-TN-D-62971 N71-22614 A brief review of some safety studies based on BUBUEAI, J. operational flight recording Weather as a factor in fatal accidents involving N71-23411 civil transport aircraft CREATEAE. E. G. 1171-23431 PlaB8abilitY and design considerations for BUBSTADT. P. 1. commercial airplane interior materials Instantaneous and dpnanic analpsis of supersonic 871-23232 inlet-engine compatibility CEEB. K. K. [ NASA-TI-X-67821 1 171-23927 Extension of E~DOUS'spot theory to flows on blunt BUSCUUOBI. U.-R. bodies Application analysis of VTOL aircraft for future A71-27557 integrated intercitp traffic spstem CEEUG, E. E. B71-22192 Curvature effects in the laminar and turbulent freejet boundary A71-25482 C CBISTTAKOV, P. E. CAIGBB. B. Centrifuqal compressor machines Review of several factors relevant to jet upsets [AD-717878] N71-23297 N71-23424 CLARK, 6. E. CALABESE, II. The applications of satellites to communications. An experimental investigation of the interaction navigation and surveillance for aircraft between a transverse sonic jet and a hypersonic operating over the contiguous United States. stream Volume 2 - Appendices A71-25472 [NASA-CR-l17759] 171-22340 CALLIS, 1. E. CLARK. 1. T. Coupled nongray radiating flows about long blunt The radiation of sound from an airfoil inmersed in bodies a laminar flow [AIAA PAPER 70-8651 A71-25453 rASIlE PAPPR 71-GT-41 A71-25950 CALOGEBAS, J. E. CLARK, S. K. Instantaneous and dynamic analysis of supersonic The structural modeling of aircraft tires inlet-engine compatibility rAIAA PAPER 71-3461 A71-25325 [ AASA-TI-X-67821] N7 1-23927 CLIFFORD. D. E. CABP. D. 0. Approach path control for rcdncad noise and Anemometer with brakinq mechanism Patent improved traffic capacity iXA5A-LASE-XIP-O5224] 871-23726 N71-23425 CAREABT. E. W. COCERAU, R. P. static electricity measurements during refueler Coolinq airflow through a stationary turbine disk loading Interim report and blade r AD-717347 ] N71-22232 NASA-TU-X-217 13 171-22680 CARLSOB, E. W. COHEII, E. Wind-tunnel investigation of sonic-boom Contributions of the space programme to aviation characteristics of two siaple wino models at r NASA-T3-X-67073] 171-22394 Uach numbers fron 2.3 to 4.63 COEEB, E. J. [ NASA-TN-D-62011 R71-23125 Compressibility correction for subsonic flows CARLTOU, E. A71-25149 The use of a sun tonnel f3r hypersonic intake COEEB, S. E. callbrat ion The desiqn and application of the Traversing N71-22635 Infrared Inspection System, TIRIS CARIEL, E. [&SEE PAPER 71-DE-371 A71-27327 Address by the Uinister of Transport COLLIES, D. J. N71-22382 Determination of three-dimensional density fields CARTER. 1. from holoqraphic interferoqrams Recent contributions to experiments on cylindrical A71-25802 shell panel flutter COLTRIN, E. E. [AIAA PAPER 71-3281 A71-25308 Instantaneous and dynamic analysis of supersonic CABTWRIGUT, II. 6. inlet-engine compatibility Analytical and experimental studies of two- [ NASA-Tn-X-678211 N71-23927 dimensional flows in a radial bladed impeller COBVERSE, 1. [ASIE PAPER 71-GT-201 A71-25964 Variable geometry external fuel tanks CASPABI, I. rAIAA PAPER 71-3951 A71-25271 Jet propulsion systems in helicopters COOIBS, 1. F. E. 871-25259 The growth of avionics Crane and external load fliqht with helicopters A71-26878 A7 1-27 142 COUUCILL. E. 1.. JR. CASTLE, C. U. Ground and flight test results for a decelerator Ianufacturing approaches to resin matrix composite towline enerqy absorber airfoils for gas turbine engines [AIAA PAPER 70-12021 1171-25527 rASf!E PAPER 71-GT-471 A71-25980 COUPRY, G. CASTRO. I. P. Critical analysis of the methods used for Wake characteristics of two-dimensional perforated predictinq the response of large flexible plates normal to an air-stream aircraft to contiruous ptmospheric turbulence A71-26449 [AIAA PkPER 71-3421 1171-25321 CATLIII, J. E. Transfer functions of flexible aircraft to USAF air mobility via expancable structures atmospheric turbulence [AIAA PAPER 71-398) A71-25274 N71-23213 CEAIPAGUE, D. 1. COWLEY, P. R. Standard measurement of aircraft qas turbine The PT6 after 5 million hours enqine exhaust smoke [SAE PAPER 7103851 A71-27536 FASEE PAPEE 71-GT-881 A71-25995 CRAGGS, A. CEAUG. I.-D. The transient response of a coupled plate- The deformation and instability of a suddenly acoustic system usinq plate and acoustic finite accelerated liquid drop elements rAIAA PAPER 71-3931 A71-25355 1171-27481 CEARG, J. D. CRAIG, R. R., JR. Aircraft gas turbine condition analysis Optimization of a supersonic panel subject to a instrumentation - Its use for the status flutter constraint - A finite element solution

8-3 CRAIGIE, J. 8. PERSONAL AOTEOR INDEX

rAIAl PAPER 71-3303 A71-25310 r NASA-TN-D-6 195] N71-2 1961 CRAIGIE, J. 8. DOMES, E. B. The applications of satellites to communications, Tungsten reinforced oxidation resistant columbiun naviqation and surveillance for aircraft alloys Final report, 1 NOV. 1969 - 1 Nov. 1970 operating over the contiguous United States. [AD-7179691 N71-23673 Volume 1 - Technical report DOENSEIIER, 0. [ NASA-CR-117760 1 N71-22339 Propeller-driven VTOL aircraft CBiGR1GN. 9. Gi N71-22191 On the scatterinq of aerodynamic noise D@YEI-L; E. E. 871-26448 Generalized aerodynamic torces OD a flcxihle plate CROSS. S. 1. undergoing transient motion in a shear flow with Desiqn and test of a prototype qraphite fiber and an application to panel flutter plastic fuselage component- A71-27559 A71-25428 DUCRENE, A. COMMINGRAI, A. I., JE. Accelerometric circuits for the measurement of A collocation method for predicting oscillatory modal characteristics subsonic pressure distributions on interferinq A71-277 19 parallel lifting surfaces DORVASULA. S. rAIAA PAPER 71-3291 A71-25309 Flutter of clamped skew panels with mid-plane forces in supersonic flow 1171-26766 DUSOLD, P. DAIBER, J. W. Application of a hybrid computer to the Research on advanced qasdynamic test facilities. development of a pilotless captive helicopter Part 2 - Laser-fluid interaction studies Final A71-25847 technical report, 1 Jul. 1966 - 30 Jon. 1970 DZVONIK. 1. I. r AD-717728 3 N71-22593 Rypersonic flow around a thin three- dimensional DAIONGEOT, A. body measurement of unsteady aerodynamic forces and A71-27330 , propaqation of perturbations during rapid variations of the anqle of attack of an airfoil 871-27468 E DANESRYAR. n. EASLET, C. S. The off desiqn analysis of flow in axial The applications of satellites to communications, corn pressors naviqation and surveillance for aircraft rCUEO/A-TURBO/TR-19] N71-22294 operating over the contiquous United States. DASTIN, S. Volume 2 - Appendices First boron composite structural production part [NASA-CR-1177591 N71-22340 A71-25420 EATRER. R. E. DAVIBS, P. 0. A. L. Six channel photometric observations from the CV Performance of exhaust silencer components 990 aircraft Final report 171-25180 [ NASA-CR-1174661 N71-22135 DAVIS, J. E. ECKSTROI, C. V. Operational tests of dual baseline transmissometer Performance of disk-gap-band, ringsail, and cross systems parachutes at low earth altitudes f NBS-10339 1 N71-22455 [AIAA PAPER 70-11641 171-25525 DAVIS, W. F. EDIS, K. shipboard test procedure Fresnel Lens Optical on two dimensional sound sources and sound waves Landinq System IK 6 IO0 2 1171-25144 r AD-718335 I N71-23488 EDWARDS, D. 8. DE mA10, D. A. The Goblin mk35 encline - Investiqation of noise An airspace utilization model for V/STOL terminal and vibration operations [ARL/flE-1271 N71-22503 [NASA-CR-117887) N71-23186 EGGWBRTZ. S. DENIIEY, I. A. study-of inspection intervals for fail safe Aerosoace applications structures A71-25652 [FFA-1201 N71-22431 DENNY, V. E. ERRICR, P. P. Evolution of the laminar wake behind a flat plate A dynamic model of gas turbine engine main and its upstream influence comhustor instability A71-25469 [ASME PAPER 71-GT-731 A71-25987 DESTLER, W. Y. ELIAS, 1. Laboratory study of hiqh-beta plasma shock waves Initial studies of low temperature ablation in a [ AO-7173971 N71-22166 helium hypersonic wind tunnel DEWEY, 1. R., JR. r SC-CR-69-3215 1 N71-23228 Problems encountered in nap of the earth flyiuq ELIEAZ, I. and their effect on aircraft desiqn mission Aircraft power-on polars corrected for propeller performance slipstream deflection N71-23430 A71-25164 DIESINGER, Y. 8. ELLISON, J. C. Numerical method for evaluating aerodynamic Investigation of the aerodynamic Characteristics coefficients of thin supersonic wings at of a hypersonic transport model at Mach numbers anqle-of-attack conditions to 6 [OLR-FB-71-011 N71-23597 [NASA-TN-D-61911 N71-23127 DOAK, P. E. ENDERS, J. A. Effects of louvres on the noise of an axial flow A review of V/STOL aircraft accidents in the US fan N71-23426 A71- 267 OU ERDOS, J. I. DODGE. R. M. Numprical solution of several steady wake flows of Thv structural modelinq of aircraft tires the mixed supersonic/subsonic type by a [AIAJ PAPER 71-3461 A71-25325 time-dependent method DOKAINISH n. A. N71-22674 Naturd. frequpncies of rotatinq. low aspect ratio, EEP, R. K. turbomachinery blades Roloqraphic characterization of aerospace [AIAA PAPER 71-3741 A71-25347 corn ponents DOLLYHIGH, s. m. [ ASNE PAPER 71-GT-741 1171-25988 A wind-tunnel investiqation of sonic-boom pressure ESCEENROEDER, A. Q. distributions of bodies of revolution at Nach Aerophysics research based on free fliqht range 2.96, 3.83, and 4.63 measurements

B-4 PBBSOIAL AUTEOB IMDEI GLUKEOV. V. I.

mi-22633 POIVOBTET. T. G. ESGAB. J. B. The challenge of the supersonic era Eigh temperature turbines All-26883 [RASA-TII-X-67123] 1471-22699 PPIESEII. A. A. ESEEL. S. Roloqraphic detection of microcracks EL-AL's planninq for the integration of the B-747 [ ASBE PAPER 71-BET-C] A7 1-2731 2 R71-22388 PBIESS, 6. ESSEE. J. E. First flight and operation experiences with the 'flying test cell' evaloation and applicatiors IL-62 long-haul jet aircraft [ ASBE PAPEB 71-GT-77 1 A71-25991 1171-25260 EVAIS, D. G. PBUEOESX, J. Computer program describing turbine aerodynamic Thrust measurement of great accuracy of requirements. approximate external blade aeronautical propulsion systems givinq geometries, and coolant flow requirements for a particular attention to a hydraulic device for two stage axial flow turbine measoring the force. I [ RASA-TB-1-2229 ] 1171-22568 871-26991 PBUCBTBAI. I. The supersonic turbine - A design and cascade F StQdy PALAESKI. m. D. [ASBE PAPER 71-GT-761 171-25990 Large-scale wind tunnel investigation of a ducted PUJIUABA, a. fan - Deflected-slipstream model with an On the most feasible configuration for airplane auxiliary sing gust-alleviation system [ RASA-TR-D-6323] N71-23861 A71-25195 PASSO. G. FURGALUS. K. A. Beasurement of onsteady pressures on stator blades Computer program describing turbine aerodynamic of the 52.BA compressor requirements. approximate external blade A71-27469 geometries, and coolant flow requirements for a PAUEOTE. 6. 1. two stage axial flow turbine Design, fabrication, and static testing of r RASA-T!!-X-2229] N71-22568 Attached Inflatable Decelerator /AID/ models [RASA-cR-l1183i] 1171-22538 PAWKE. A. J. G Experimental investigation of methods for GALLAGEEE. B. n. improving the dynamic response of a twin-spool Relicopter auxiliary power unit cost of ownership turbojet engine 17:-26679 [ ASBE PAPER 71-GT-141 171-25960 GISIXkE. 6. a. PAX, J. A. Comparison of two stochastic models for threshold Jet aircraft air pollotant production and crossinq studies of rotor blade flapping dispersion vibrations rAIAA PAPER 70-1151 A71-27560 [AIAA PAPER 71-3891 A71-25351 Pmzeslr. P. J. GARABEDIAI. A. Advanced composites efforts - A status report of The applications of satellites to communications, Air Force programs with graphite reinforced navigation and surveillance for aircraft com PO sites operating over the contiguous united States. rASBE PAPER 71-DE-131 A7 1- 27 323 volume 1 - Technical report PXDOEEIKO, 6. I. [ RASA-CR-117760 1 N71-22339 Self-adjusting automatic control systems for an GABTSEOBE. I. S. aeroelastic aircraft Predictions of the blowing required to suppress A71-26718 separation from high-lift aerofoils PEILEB, C. E. A71-26196 Low-speed jet noise from a 1.83 meter /6ft/ fan GASAUAI. D. C. for turbofan engines cockpit noise within trainer aircraft Final r RASA-TR-D-6314J N71-23134 report, Feb. - Oct. 1970 Low-speed jet noise from a 1.83 meter /6 ft/ fan r AD-7178521 mi-22426 for turbofan engines Conference six indices for predicting speech interference [ RASA-TB-X-67825] R~I-Z~OO~ within aircraft Final technical report, 1 Oct. PEEGUSOI. J. E. 1968 - 6 JUl. 1970 Selection of landing airfields for shuttle f AD-7180981 w7i-23528 orbiters with various crossranges Landing and Noise associated with airborne operation of C-14111 Recover? Division internal note aircraft Final report, 1 Mar. 1969 - 28 Feb. TRASA-TB-X-670801 871-21996 1970 PBETIU, G. [ AD-7180971 N71-23748 Pind tunnel visualization arrangements for fixed GASTBB. 1. or rotating annular cascades Vortex shedding from circular cylinders at low A71-27717 Reynolds numbers PIMK. m. P. A71-27220 A wind tonne1 investigation of static longitudinal GEEBIMG, P. and lateral characteristics of a full-scale Prevaporization of liquid fuel in a small rarjet mocknp of a light twin engine airplane enqine [ NASA-TU-D-6238 I R71-23860 [RASA-TT-P-13605] ~171-24053 PI~K. m. E. GILLIAO, 6. D. Shock wave behavior in transonic compressor noise Data reduction techniques for use with a wind generation tunnel maqnetic suspension and balance system [ ASBE PAPER 71-GT-7 1 171-25953 Interim technical report, Rov. 1968 - Jnn. 1970 FIlK, B. U. [ IIASA-CR-111844] ~71-23122 Screening for reliability growth GILLILLAUD. 1. A71-26683 Captives of industry /goes/ PISCEBR, P. W. n7i-23720 The SST and air traffic control GLAESEB. W. A. A71-25232 Analysis of brinelliug failure of bearings fJom PLIXDEB, U. 6. vibration tested PLV fans Summary report An analytical study of hydrogen cooled panels for [RASA-CR-117855] 1171-22527 application to hypersonic aircraft GLASSIIAI, A. J. [ NASA-CR- 1650] 1171-22625 Shuttle airbreathing propulsion POEXSTIEE, J. 1. [ RASA-TM-X-67806 ] N71-23764 Influence of simDle aerodvnamic modifications on GL11KEOT. T. I. the performance of an aircraft self-adjusting automatic control systems for an 871-23422 aeroelastic aircraft GOBLE. 8. 1. PERSONAL AOTEOR INDEX

A7 1-2671 8 INASA-CASE-XAC-~~~~~ 3 N71-23809 GOBLE, R. 1. EAPTKA, R. T. Ground and flight test results for a decelerator A Koiter type method for finite eleaent analysis towline enerqy absorber Of nonlinear structural behavior. Volume 1 - The r AIAA PAPER 70-1202 1 871-25527 modified structure method Final report, 17 Oct. GOECKE, S. A. 1969 - 17 Oct. 1970 Comparison of uind tunnel and fliqht-measured base r AD-717740 1 N71-22485 prvssiirer: fmm the sharo-leadinq-edqe upper AALLETT, U. N. vertical fin of the X-15 airplane for turbuient Desiqn considerations in inertia weldinq of flow at Hach numbers from 1.5 to 5.0 turbocharqer and qas turbine c-osponerits r VASA-TN-D-63481 N71-23922 rASME PAPSR 71-GT-211 171-25965 GOLEGO, N. 1. EANLEY, D. P. Equipment OIT-1200/50 for detereininq the heat Desiqn and test of a prototype graphite fiber and resistance of sealinq materials plastic fuselaqe component A71-27689 A71-25428 GOMAN. 0. G. EANSOH, C. E. Accelerated supersonic motion of a plane at a An investiqation of the near wake proverties finite anqle of attack associated with periodic vortex shedding from r NASA-TT-P-135251 N71-23278 airfoils GOMBERT. J. [AD-718893] N71-23245 The hiqh-lift wing - Remarks on the prediction of HARDY, P. W. characteristics Quasi-optimum proportional navigation A71-27476 A71-26409 GOODMAN, T. R. EAREL. E. Aerodynamic characteristics of a slender body Development of civil aviation in Israel in the travelinq in a tube 1970's A71-25477 N71-22391 GOPALARKRISENAN, 5. EARGREAVES, 8. A numerical technique for the calculation of Beaqle B 125 Bulldog G-Axeh /Lycominq 10-360AlC/. transonic flows in turbomachinery cascades Part 1 - Preview handlinq trials r ASnE PAPER 71-GT-42 1 A71-25975 IAAEE/963-PT- 1 1 N71-23498 GORLAND, S. E. EARMOU. E. A. Experimental windaqe studies for hiqh speed Performance of compressor blade rows in a sloping alternators flowpath [NASA-TI!-X-678091 N71-23116 [ASNE PAPER 71-GT-131 A71-25959 GOOGAT, P. HARPER. E. I. Ilfluence of a sinusoidal wall perturbation on The deformation and instability of a suddenly transition accelerated liquid drop A71-27470 IAIAA PAPER 71-3933 A71-25355 GRAPTON, S. B. AARRIS, W. J., JR. Flight investiqation of a V/STOL transport model Materials for Air Force - 1980- An industry havinq six winq-mounted lift fans commentary INASA-TN-D-61981 N71-22069 A71-27677 GRANT, E. A. EARTE, 8. J. Performance analysis of the modulation The applications of satellites to communications, cancellation altimeter navigation and surveillance for aircraft A71-27437 operating over the contiquous United States. GREGORT-S1ITE. D. 6. Volume 2 - Appendices The manufacture of qlass fibre rotor blades uith [ NASA-CR-117759 ] N71-22340 pressure tappinqs AARTIANN, A. A71-26316 Lift fans and a flexible solution for the GRISAPPE, S. J. development of VTOL passenqer aircraft A status revieu of Lewis Research Center supported N71-22194 protection system development EAOPT, a. A71-25555 Interface of materials and structures on GROTE, A. U. airframes. Part 2 - Outline of decision process Nozzle performance measurement on underwing in structural design nacelles of an P 106 utilizinq calibrated [ AD-717576] N71-22136 enqines and load cells EAUKINS, R. [NASA-TH-X-678161 N71-23822 The use of a qun tunnel for hypersonic intake GRIIBE, G. 9. calibration The deforaation and instability of a suddenly N71-22635 accelerated liquid drop EEPPERNAN, T. rAIAA PAPER 71-3931 171-25355 Beaqle B 125 Bulldog G-Axeh /Lycominq 10-36CAlC/. GOIOT, R. Part 1 - Preview handlinq trials Lateral control of hiqh-speed aircraft with lift IAAEE/963-PT-1 1 N71-23498 devices AENDERSON, U. P. A71-27471 Subsonic aerodynamic characteristics of a highly GOIRAOD. J.-P. swept fixed wina confiauration with variation in Structure of vortex flows in axial-flow wing dihedral angle turbomachines INASA-TH-X-2261 1 N71-22622 A71-27714 EERB. n. GOT. 1. 8. Air traffic security, today and tomorrow Flame-retardant silicone elastomers for aircraft N71-22197 1171-27412 EERCKEUE&TE. P. Y. 1. GWINN, C. U. Nan/machine combination in the light of safety ApDlicat.ions of self-orqanizinq and learninq requirements control to aeronautical and industrial systems 1171-23423 [ASME PAPER 71-DE-22) A71-27324 EETUOOD, J. B. Jet aircraft air pollutant production and dispersion H rAIAA PAPER 70-1151 A71-27560 AACKETT, J. E. HICKS. E. 1. A thrv1it.t ical investiqation of a circular liftinq An investiqation of sonic boom for straiqbt- and jet in a cross flouinq mainstream Final report, delta-wing space shuttle orbiters . Jul. 19h3 - Dec. 1970 [ NASA-T1- X- 6 20 30 J N71-23296 IAD-718 1211 N71-23475 EIGOCEI, E. AADLAND, U. 0. Aerodynamic characteristics of a flared body with Control device Patent blunt nose

8-6 PEESOIAL AUTEOE IIDEI JUECOSIL, E. 1.

[ NAL-TR-2211 1171-22160 EUBT. G. J.. JE. HILL, 1. J- Development of a simulator for studyinq sinp1ifie.d Analytical and experimental studies of two- lunar escape systems dimensional flows in a radial bladed impeller r RASA-TN-D-6111] 171-22590 [ASEE PAPER 71-GT-201 871-25964 BUTTSELL. 1. J. EILTOI. a. P. AFFDL investigations concerning the coupled Local avoidance of sonic boom from an aircraft wing-fuselage-tail flutter phenomenon A71-26310 [AIAA PAPER 71-3261 A71-25306 EIEA. n. The effect of wind-gradient on the landing approach of an aeroplane I A71-25194 IAKOBSOII, I. V. BIBATA. 1. High-speed methods for testing reliability and Disintegration of a supersonic jet impinging fatigue life of airplane structures normally on a flat plate A71-26946 1171-25521 ICEIKAUA. T. EO, E. I.-5. A note on the T-tail flutter A study of multiple access communication system A71-25188 87 1- 21 855 ILLS. P. EOEPPIEB. E. Fatigue of four stainless steels, four titanium Market situation for V/STOL aircraft alloys, and two aluminum alloys before and after N71-22188 exposure to elevated temperatures for '~pto EOPPBAI. J. S. three years Liquid distributions of a lor pressure drop [NASA-TN-D-61451 171-22076 injection system - Gas turbine 'vaporizer' IllAI. K. design Lift jet engine, JRlOO [ASH?.?PAPER 71-GT-381 A71-25972 r ASME PAPER 71-GT-75 J A71-25989 EOGGE. C. B. IEIG, 1. A. Laser beam probing of jet exhaust turbulence Fatigue of four stainless steels, four titanium A71-26304 alloys, and two aluainum alloys before and after EOEBIIEBSEE, K. E. exposure to elevated temperatures for up to Comparison of two stochastic models for threshold three years crossinq studies of rotor blade flappinq [ RASA-TN-D-6145 1 N71-22076 vibrations IEGLESAKIS. G. [AIAA PAPER 71-3891 A71-25351 Theoretical and experimental study of hla0e EOLCO1B. U. E. casrildec in supersonic flows Design and development of a boron-?lass-spsrg A71-27475 lightweight composite gear case IIGLESBT! J. 1. [ASEE PAPER 71-GT-851 1171-25993 The simple loqic of radar avoidance action EOLEES, D. V. . A71-27600 Experimental pressure distributions on aerofoils IEOUE. 1. in transverse and streamwise gusts The effect of wind-gradient on the landinq [ CUED/A-TUBBO/TR-211 871-22374 approach of an aeroplane EOLVAT, E. P. A71-25194 Model launcher for wind tunnels Patent IEOUIB. K. [BASA-CASE-XNP-O3578] R71-23030 Connection between lift and particle displacement EOEAEI. S. A71-27577 Investigation concerning the fluid flow in the IEGOY, 0. K. mixed-flow diffuser Determination of the optimal dimensions of the ;Ass3 PAPER 71-GT-401 1171-25973 fuselage of a supersonic transport in the BORE, V. preliminary design staqe Recent contributions to experiments on cylindrical 871-27494 shell panel flutter IUASAKI, I. [AIAA PAPER 71-3281 1171-25308 control device Patent EOUBOLT. J. C. [RASA-CASE-XAC-10019] N71-23809 The art of determining gust frequency response functions N71-23211 J EOUABD. J. E. 6. JAEIKZ, 1. P. lleasured and predicted flow near the exit of a Inertia welded jet engine components radial-flow impeller [ ASME PAPER 71-GT-331 1171-25970 [ASME PAPER 71-GT-151 A71-25961 JAtSA. D. E. BOA. I.-C. Integrated hiqh frequency antenna system Pinal Natural frequencies of vibration of a trianqular report, 13 Nov. 1969 - 9 wov. 1970 inflatable wing model [ AD-7 18 1671 N71-23306 N71-22666 JEISEE, 1. C. BUDDIE. D. Graphite epoxy fliqht spoiler - Economics of propulsion systems for air transport. Desiqn/anal ysis/fabricat ion I A71-27413 A71-27542 JOAIIDES, J. C. EUIMIIK. B. Safety factors and the probability of failure in The VTOL jet for a future V/STOL transport system fatigue w7 1-22187 A71-25492 BUNTEB. 1. 6.. JB. JOEISOI, E. T. Results of a strong interaction, wake-like model A turbine-speed, main-enqine fuel pump Of supersonic separated and reattachinq [ASRE PAPER 71-GT-241 A71-25966 turbulent flows JOENSOI, 0. [AIAA PAPER 71-1281 A7 1-25476 A lifting-surface solution for vortex-induced EUNTER, P. A. airloads Summary of center-of-qravity accelerations A71-25474 experienced by commercial transport airplanes in JOEDAI. P. P. landinq impact and qround operations Span loading and wake formation [ NASA-TR-D-6124] 1171-22620 [ AD-7180241 171-23660 EUITOE, G. V. JUICOSA. B. 1. Development of size 22 type D.50.S Fuel-optimal retrothrusted soft landinq throuqh an silicon-maqnesium-aluminiu~ alloy aircraft atmosphere. Project RAND cables and terminations r AD-7184051 N71-23487 [TRC-BR-19785 1 N71-23547

B-7 KAISAND. 1. R. PERSONAL AUTHOR INDEX

KOHLIAN, D. 1. Initial studies of low temperature ablation in a K helium hypersonic wind tunnel KAISAND, 1. R. ISC-CR-69-32151 N71-23228 Residual tensile properties of material from C-130 KOUO, Ne center winq section after service Final report Cylindrical boundary interference on virtual mass [WASA-rR-111828] N71-24021 of a sphere KALAITAN, E. 1. [ NAL-TR-2231 N71 - 221 59 Lubricatinq oils for jet enqines iriodyEanic noise of a circular double jet AD-7 17835 1 N71-22011 [ NAL-TR-212 1 UT!-22469 KALINOVICH, V. N. KOOPIANN, G. 8. Theory of an inertial navigation system Wind induced vibrations of skewed circular constructed on the basis of a gyrohorizon cylinders compass TAD-7177391 N71-22169 A71-27169 KORKEGI, E. 8. KARIIES, R. 1. survey of viscous interactions associated with The impact of automated structural optimization on hiqh Hach number fliqht actual desiqn [AIAA FAPER 70-7811 A71-27551 rAIAA PAPER 71-3611 171-25340 KORSHIN, I. 1. KASS, G. J. Calculation of boundary layer separation from an The effect of active controls on structural arbitrary curvilinear rotatinq plate responses A71-27502 N71-23212 KOZLOV, 1. P. KATSANIS, T. Laminar boundaiy laycr on a winq and a body of PORTRAN proqram for quasi-three-dimensional revolution in the presence of blowing calculation of surface velocities and chokinq [ NASA-TT-P-13627 1 N71-23796 flow for turhomachine blade rows KOZLOV, 1. V. [NASA-TN-D-61771 N71-23126 The effect of edge bluntness of a flat plate on KAWl(tlOT0, I. heat transfer in a supersonic flow Aerodvnamic characteristics of a flared body with r AD-7178251 N71-22156 blunt n@se KRAUSE, S. [ NAL-TR-221 1 N71-22 160 neasurements with aerodynamic probes in plasma KAZnIERCZYK, P. jets produced by electrothermal and Hall Current Classification of flexible runway surfaces by the accelerators LCN method N71-22639 A71-26201 KRAVETS, V. N. KEIIPKE, E. E. notion of a winq of solid profile near a screen Experimental windaqe studies for hiqh speed A7 1- 27 174 alternators KRUPP, J. A. I NASA-TU-X-678091 N71-23116 Finite difference calculation of the behavior of a KHOLSHCAEVNIKOV, K. 0. discontinuous siqnal near a caustic Theory and calculation of aircraft bladed machines r AD-7188351 N71-23738 A71-26401 KUECHLE. A. KIDA, T. Application of a hybrid computer to the E. theory on effect of entrainment, due to jet flap development of a pilotless captive helicopter which hits the qround, for an aerofoil with A71-25847 separation KUETTNER, R. A71-26314 Examination of operational aspects of motion KIDD. W. E. sequences on airways Low cost short life qas turbine desiqn A71-27143 r ASnE PAPER 71-GT-69 1 A71-25984 KUHN, G. D. KIENAPPEL, K. Theoretical analysis of vortex sheddinq from Inclination of pressure orifices in low-density bodies of revolution in coning motion flow [AIAA PAPER 70-521 A71-27552 A71-25490 KUHN, R. E. K18. K. 8. Turbofan STOL research at NASA Curvature effects in the laminar and turbulent A71-27602 freeiet boundary KUKITA. I. A71-25482 Disinteqration of a supersonic jet impinqinq KING, 8. A. normally on a flat plate Aerophysics research based on free fliqht ranqe A71-25521 measurements KUNCIS, W. A. N71-22633 Geodetic control for airports KIRK, C. 1. All-27537 Analysis of taxiinq induced vibrations in aircraft KUTLER, P. by the power spectral density method Application of selected finite difference A71-26311 techniques to the solution of conical flow KISSEL, G. problems Operational provinq of automatic fliqht control N71-22667 systems for V/STOL fiqhter aircraft KUZWETSOV, E. I. N71-23415 Equipment DIT-1200/50 for aetermininq the heat KLEIN, n. J. resistance of sealinq materials Tunqsten reinforced oxidation resistant columbium A71-27688 alloys Final report, 1 NOV. 1969 - 1 NOV. 1970 I AD-717969 1 N71-23673 KLUG, H.-G. L Commercial interpretation of VTOL air liners LACKEY, J. I. N71-22190 The structural modeling of aircraft tires KNOBLOCH, W. H. [AIAA PAPER 71-3461 A71-25325 Helicopter auxiliary power unit cost of ownership LAIBERT, R, A71-26679 The RNAV thinq KO, D. R. S. A71-26R79 Experimental stability studies in wakes of two- LARDEN. E. J. dimensional slender bodies at hypersonic speeds Analoque recursive computer 1171-27561 A71-27150 KOELTZSCH, P. LAIPARD, T. R. G. Aerodynamically induced noise of condenser Radio environment monitorinq for the category 3 micronhones instrument landinq system A7 1- 270 C,i r FRE-TR-700761 N71-23356 PEBSOIIAL AUTEOB IIIDEX NAERER, U. J.

LAI680CK. E. nun. J. B. Problems and aspects of elaboration of weather Development of a torsional-flexural stability minimum conditions for INTERFLOG aircraft analysis of stiffened titanium panels for A71-27141 application to the U.S. Supersonic Transport LAI6IOETHY. E. A. [AIAA PAPER 71-3381 1171-25317 Advanced regenerative qas turbine desiqns for LIVIIGSTOI, E. C.. JB. liqhtweight and hiqh performance Proving the operational capability of a hiqh r ASnE PAPER 71-GT-673 A71-25983 performance flight control system LAEGUIEE. E. N71-23413 neasurement of unsteady pressures on stator blades LOPl'II6. E. 6. of the S2.IA compressor V/STOL in the Royal Air Force - Some lessons from A71-27469 the first 18 months LASSAU. 6. N71-23427 Experimental study of the laminar boundary layer LOGVIIIUK, T. P. with catalytic reaction of the wall Effect of the deoxygenation of jet fuels on their 171-22640 antiwear properties LAUB. 2. 1. 1171-27662 Flame-retardant silicone elastomers for aircraft 111811, 6. A71-27412 Pirst boron composite structural production part LEATBEBWOOD. J. D. A71-25420 Analoq analysis of the heave response and control LUCAS. E. J. of a plenum-type air cushion vehicle Investigation of blunt fin-indnced flow separation r NASA-TN-D-62571 871-22589 region on a flat plate at Iach numbers 2.5 to LEE, J. J. 4.0 Final report Beagle B 125 Bulldog G-AXeh flycoming 10-36OAlC/. [AD-717717] 171-22300 Part 1 - Preview handling trials LUDTKB, W. P. r AAEE/963-PT-l J 1171-23498 A new approach to the determination of the steady LEKOWSKI. U. state inflated shape and included volume of Determination of the mutual aerodynamic effects of several parachute types in 24 gore and 30 gore SI-1 helicopters dnring takeoff and landinq conf iqurations A71-26953 [ AD-718808] nn-23387 LEUKE. D. G. LUTSKII, 1. The arnamic response of axially coupled Stability and controllability of sopersonic turborotors aircraft R71-22712 [ AD-7184741 N71-23538 LBIIBUAII, E. Staoility and controllability of supersonic Measured and predicted flow near the exit of a aircraft

"7. ~ 170.0 radial-flow impeller [ rg-71g2g5> 1.. I L.," I" [ASIE PAPER 71-GT-151 A71-25961 LVOV. 1. E. LEOIAED. J. T. Self-adjnstinq automatic control systems for an Static electricity measurements during refueler aeroelastic aircraft loadiilq Interim report A71-26718 [AD-7173471 1171-22232 LEPPII6TOU. P. 6. On the scattering of aerodynamic noise M A71-26448 UACK, E. J. LEIBIETZ. 8. A wind-tunnel investigation of sonic-boom pressure Variable qeonetry external fuel tanks distributions of bodies of revolution at nach rAIAA PAPER 71-3951 1171-25271 2.96, 3.83, and 4.63 LEVIIIE. S. E. [ NASA-TN-D-6195] A71-21961 A status review of Levis Research Center supported UAEOOD, 1. protection system development Variable geometry external fuel tanks A71-25555 rAIAA PAPER 71-3953 A71-25271 LEVY. L. 1.. JB. UALLBTT, E. E. An investigation of sonic boom for straiqht- and A Koiter type method for finite elemeut analysis delta-wing space shuttle orbiters of nonlinear structural behavior. Volume 1 - The TNASA-TI-X-62030] 871-23296 modified structure method Final report, 17 Oct. LEVBIWII. J. 1. 1969 - 17 Oct. 1970 A flight test establishment - Its function and a TAD-117740) N71-22485 sugqested composition UALLIICKBODT, A. J. A71-26315 The applications of satellites to communications, LEWIS. I. C. navigation and surveillance for aircraft Composites development. fabrication and operating over the contiquous United States. characterization Volnme 2 - Appendices E71-25427 f NASA-CB-?17759] 177-22340 LIBBBUAII. D. S. EALYSEEI, V. I. A faceliftinq for AASA's reliability requirements Effect of the deoxygenation of jet fuels on their A71-26667 antiwear properties LIlDBEB6. 6. 1. A71-27662 Free vibrations and random response of an UAUADALIET, I. A. integrally stiffened panel Plow of a two-phase medium with solid particles [LE-SclU] 871-24298 around a thin profile LIIDBUAIII, J. 871-27450 Considerations regardiuq the design of the cockpit UAIDL. e. for a V/STOL aircraft Effect of small surface curvatnre on unsteady A7 1-22196 hypersonic flow over an oscillating thin wedge LIIDEU. 1. E. A71-26197 Jet aircraft air pollutant production and UAII6IAPAIE, J. A. dispersion Development of Borsic-aluminum composite fan [AIAA PAPER 70-1151 A71-27560 blades for supersonic turbofan engines LIIIDSJOE. 6. [ ASaE PAPER 71-GT-901 871-25997 Study of inspection intervals for fail safe UABCEAIT, D. structures Performance of comDressor blade rows in a sloDina.. rFFA-1201 N71-22431 floupath LITIIIOI, A. A. [ASIE PAPER 71-GT-131 1171-25959 Effect of the deoxygenation of jet fuels on their UAEIBB. a. J. antiwear properties Combined free and forced laminar non-Newtonian A71-27662 convection in a vertical tube N71-22702

B-9 IARSH. H. PERSONAL AUTHOR INDEX

HARSH, E. geometry aircraft The manufacture of glass fibre rotor blades with [AIAA PAPER 71-4041 A71-27410 pressure tappirqs IELLO, R. n. A71-26316 Intermediate diaqonal tension field shear beam IARTEL, C. R. development for the Boeinq SST Evaluation of the Aqua-Glo series 2 free water [AIAA PAPER 71-3401 A71-25319 detector Summary report IELBYK, P. [AD-7184181 171-23438 netal matrix composite fabrication procedures for IARTINO, A. A. qas turbine enqine blades Desisninq rotor burst protection [ASIE PAPER 71-68-46] A71-25979 [ASNE PAPER 71-GT-701 A71-25985 MELVIN, E. E. IASHIIO, T. Wind shear on the approach Effects of Revnolds number on performance A71-26364 characteristics of a centrifuqal compressor IENDE, S. E. FASIIE PAPER 71-GT-251 A71-25967 Six channel photometric observations from the CY IATHER, G. K. 990 aircraft Final report The development and testinq of a pyrotechnic [NASA-CR-1174661 N71-22135 seedinq system on a modified T-33 IENDEL, J. I. N71-22200 Proporty of the equation-error approach to IATSUKI, I. psramrter identification LiFt jet enqine, JRlOO A71-26418 [ ASEE PAPER 71-GT-75 1 A71-25989 IENDOZA, J. P. IATULKA. R. D. An investiqation of sonic hoom for straiqht- and Det.ermination of three-dimensional dnnsity fields delta-wing space shuttle orbiters N71-23296 from holoqraphic interferoqrams [ NASA-TE-X-62030 1 A71-25802 IERCIER. J. IATZKO. R. E. Economic asppcts of the expected development in USA; air mobility via expandable structures air transport in the next decade ~HIAAPAPER 71-3981 A71-25274 N71-22384 IAURER, F. BERKULOV, V. I. Experimental investigations on supersonic Experimental investiqation of fluid flow al0na a cinbu.;tion in the flow fields of bodies of traveling wave xvolation and near a flat plate in tanqential N71-22221 flow IERUTKA. J. P. [DLR-FB-70-641 N71-22129 A status review of Lewis Research Center supported BAY, D. N. protection system development Effects of louvres on the noise of an axial flow A71-25555 fan IETCALPE, A. G. A71-26704 Tunqsten reinforced oxidation resistant columbium IAY, G. T. A. alloys Final report, 1 NOV. 1969 - 1 NOV. 1970 A method for predictinq the number of near mid- [ AD-7179691 N71-23673 air collisions in a defined airspace IEZHLUIIAR, 8. A. A71-27599 Method for determininq unsteady flow downwash IAYBANKS, A. behind a finite-span winq durinq a supersonic Analoque recursive computer motion A71-27150 A71-27697 HC CROSKEY, W. J. IICHAEL, G. J. Measurements of boundary layer transition, Computation of Chebycheff optimal control separation and streamline direction on rotating A71-27592 blades IICEALKE, A. [NASA-TN-D-6321 1 N71-23779 A wave model for sound qeneration in circular jets nc GOWAN. w. A. I DLR-PB-70-57 1 N71-22070 Avoidance of aircraft trailinq vortex hazards Sound qeneration by a disturbed simple laminarN71-23596 jet 1 VASA-TW-X-671251 N71-23418 [DLR-FB-71-021 ICDONALD. C. F. HIDDLETON. D. E. Advanced reqenerative gas turbine dpsiqns for Development of a simulator for studyinq simplified liqhtweiqht and hiqh performance, lunar escape systems [ASaZ PAPEP 71-GT-671 A71-25983 [ NASA-TN-D-61111 N71-22590 ICDONALD. G. E. BIKOLAJCZAK, A. A. Pleasured and predicted flow near the exit of a Performance of compressor blade rows in a slopinq radial-flow impeller flowpath [ASNE PAPER 71-GT-151 A71-25961 [ASME PAPER 71-GT-131 A71-25959 ICDONALD. P. U. HILLER, C. S. The computation of transonic flow throuqh two- The applications of satellites to communications, dimensional qas turbine cascades naviqation and surveillance for aircraft [ LSPE PAPZR 71-GT-89 ] A71-25596 operating over the contiquous United States. HCKAGUE, E. 1. Volume 2 - Appendices Holoqrauhic detection of microcracks [NASA-CR-1177591 N71-22340 [ ASNE PAPER 71-EET-Cl A71-27312 MILLER, D. S. HCLAUGELIN. D. K. Wind-tunnel investiqation of sonic-boom Expprlmental investiqation of the stability of the characteristics of two simple winq models at laminar supersonic cone wake Hach numbers from 2.3 to 4.63 A71-25475 [NASA-TN-D-6201] N71-23125 RECHETNII. V. S. HILLER, P. D. GertpLdiiZPd conditions for the absolute invariance The jet fuel starter qoes operational of an aircraft's lonqitudinal-motion coordinates [ ASRE PAPER 71-61-43] A71-25976 rplativp to atmosoheric disturbances MILLER, E. R. A71-27339 A theoretical investiqation of a circular liftinq HEINTEL. A. J.. JR. jet in a cross flowinq mainstream Final report, combined opticdl attit.ude and altitude indicatinq Jul. 1969 - Dec. 1970 instrument Patent TkD-7181211,-- N71-23475 [ NASA-CAS?-XLA-019071 N71-23268 BILLER, J. A. RELCON, M. A. Heat transfer to an airfoil in oscillatinq flow controliinq structural fatique throuqh adhesive I RSNE PIPE3 71-GT-181 A71-25963 hori d i II 4 aInnEk, G. L. . [nswr: PA PI.:^^ 71-DE-271 A71-27325 Low-speed jet noise from a 1.83 meter /6ft/ fan BELLIN, S. for turhofav enqin-s Hdpj? analy!.i,; mvthod:: €or the desiqn and [ NASA-TN-D-63141 N71-23134 optimizdtion of winq pivot systems for variable

E-10 PEBSOUAL AOTEOB IUDEX UEPSOI, I. 1.. JB.

Low speed jet noise from a 1.83 meter /6 foot/ fan nonm. P. E., JB. for turbofan engines Effects of the Pan American reliability proqram on [ NASA-TI-I-67825 J 1171-24009 airline maintenance IIIAI. I. A71-26671 A theory on effect of entrainment. due to jet flap IUGGIA. A. which hits the ground. for an aerofoil with Low Prandtl number staqnation heat flnr separation calculations for a blunt axisymmetric body in A71-26314 hypersonic flow IITAZAEA. I(. r AD-71741 81 N71-22087 Lift jet engine. JRlOO IUBIA~. E. I. [ ASIE PAPER 71-GT-75 J A71-25989 Finite difference calculation of the behavior of a IIZOKI. S. discontinuous signal near a caustic A stndy on the flow pattern within the centrifngal [ AD-718835] N71-23738 and mixed-flow impellers nunorsu. I. [ ASIE PAPER 71-GT-411 A71-25974 on the most feasible confiqnration for airplane EOSLKEB. J. J. P. qnst-alleviation system Man/machine combination in the light of safety A71-25195 requirements IOBBAY, D. 1. N71-23423 Low cost short life gas turbine desiqn IOBI, 1. 3. [ASEE PAPER 71-GT-693 A71-25984 Desiqn considerations in inertia weldinq of IUBBOI, E. E. turbocharger and gas turbine components Performance of disk-aap-band, ringsail. and cross rASIE PAPER 71-GT-21 J A71-25965 parachutes at low earth altitudes IOKELKE. E. [AIAA PAPER 70-11641 All-25525 The unsteady response of an axial flow compressor IUSGBOVE. I. D. with a distorted inlet flow Intermediate diagonal tension field shear beam [ CUED/A-TORBO/TR-20 ] N71-22428 development for the Boeinq SST EOUEERIE. 8. [AIAA PAPER 71-3401 All-25319 Study of the effect of the marqinal vortex from a EYERS, V. A. helicopter blade on the aerodynamic flow aronnd Aiqh level cloud photoqraphy inventory - BOIEX the following blade period 4, 11-28 July 1969 A71-27473 [ ESSA-TI-EBLTM-BOIAP-1 1 N71-23746 IOBELLI. P. ITKITOP, I. J. A static evaluation of the manoeuvring tail load AFPDL investigations concerning the coupled for instantaneous unchecked longitudinal wing-fuselage-tail flutter phenomenon manoeuvres of sailplanes [AIAA PAPER 71-3263 A71-25306 ,-?.?C*DC 5 _I I LY...Y” Elevator-induced manoeuvring loads from the &. standpoint of airworthiness requirements for 0 sailplanes UACEBAB. E. L A71-26487 E Koiter type method for finite element analysis :: IOBPEY. C. 1. of nonlinear strnctural behavior. Volume 1 - The Sound radiation from a point force in circular modified strncture method Final report, 17 Oct. motion 1060 - 17 Octt 1970 A71-26702 r AD-7177401 N71-22485 e IOBISSET. J. UADIB; s. ESRO has begun the initial studies for a Enropean An application of the method of dimensional system of air traffic control via satellite perturbations to compressible flow f [NASA-TT-P-13651] N71-23967 871-26939 IOBITA, ‘1. UAKAGAEA, K. Some effects of systematically varied location of On the most feasible configuration for airplane one concentrated mass on transonic flutter gnst-alleviation system characteristics of sweptback thin cantilever 871-25195 winq. 11 IAKAI, E. 871-25189 Some effects of systematically varied location of IIOBRIS. 0. A. on6 concentrated mass on transonic flutter Wind-tunnel investigation of sonic-boom characteristics of sweptback thin cantilever characteristics of two simple winq models at winq. I1 aach numbers from 2.3 to 4.63 871-25189 [ NASA-TN-D-6201] A7 1- 23 125 EAKASE, I. IIOBBISOI. D. D. iln analysis of flow throngh a mixed flow impeller The applications of satellites to communications. [ASIE PAPER 71-GT-21 1171-25948 naviqdtion and surveillance for aircraft A blade theory of an iapeller with an arbitrary Gpsratinq oyer the contiguous United Srates. surface of revolution Volnme 1 - Technical report [ASIE PAPER 71-GT-171 A71-25962 [NASA-CR-117760] 1171-22339 I~AKATOGAEA. r. IORSB. D. 1. Disintegration of a supersonic let impinqinq Laboratory study of high-beta plasma shock waves normally on a flat plate [AD-7173971 N71-22166 All-25521 BOUT. K. P. EASTASE, A. Larqe-scale wind tunnel investigation of a ducted Influence of a given conical fuselage on the fan - Deflected-slipstream model with an problem of optinizing a delta wing in supersonic auxiliary wing flow [NASA-TN-D-63231 N71-23861 All-27116 IOSEER. D. K. NEPPBBT, E. An experimental investiqation of a turbulent jet Inlet flov and ontlet jet influence on the flow in a cross flow around the wings of two lift fan configurations [~~-7is7981 N7 1-233 14 R71-22195 nosImt, J. E. UESTEBOV, E. D. Decontamination of petroleum products Patent Deteriination of the optimal parameters Of an [ NlSA-CASE-XNP-03835] N71-23499 ejector nozzle under sopersonic fliqht IOSS, ‘1. D. conditions Controllinq structural fatique throuqh adhesive All-27504 boudirq IEIBEBBI. C. F. [ASIE PAPER 71-DE-271 A71-27325 The effect of active controls on structural IOIPOBTE, E. responses A desiqn study for a freiqht-CarrFing airship N71-23212 All-26309 UEPSOI, E. A., JB. Pliqht investiqation of a V/STOL transport model

B-11 NIEDERER, P. G. PERSONAL AUTEOR INDEX

havinq sir wing-mounted lift fans N71-22630 [ NASA-TN-D-61981 N71-22069 PATE, S. 8. NIEDERER, P. G. Supersonic boundary-layer transition - Effects of Structural considerations in the development of rouqhness and freestream disturbances extremely liqhtweiqht decelerators [AIAA PAPER 70-5861 A71-27554 [AIAA PAPER 71-4011 171-25277 PATEL, T. S. NIELSEN, J. 1. Calculation of the lifting force of a wing with a Theoretical analysis of vortex shedding from rotating flap bodies of revolution in coninq motion A71-27491 IAIAA PAPFR 70-521 871-27552 PATTISON, J. E. NIEZGODKA, P.4. Unsteadv hvdrodvnamic loads on a two dimensional Experimental investiqations on supersonic hydrofoii Final report combpstion in the flou fields of bodies of r AD-7179531 N71-23591 revolution and near a flat plate in tanqential PATEOR, G. flow All ueather Sud/Lear landing system installed on [ DLR-FB-70-641 N7 1-221 29 the Caravelle NISSIR, E. N71-23429 Flutter suppression usinq active controls based on PEARSONS, K. S. the concept of aerodynamic energy Effects of temporal and spectral combinations on [ NASA-TN-D-61991 871-23091 the judged noisiness of aircraft sounds UOBACK, R. A71-27531 Description of the equipment for the fatiqne test PERKOISKI, I. S. on the uinq of the Fokker F28 Fellouship Flammability and design considerations for 1NLR-TR-70@@8-L J N71-23157 commercial airplane interior materials NODA, J. N71-23232 Aerodynamic characteristics of a flared body with PBEBIIR, P. * blunt nose Elements of calcnlation for three-dimensional INAL-TR-22 11 N71-22160 aerodynamics in a perfect fluid NOLL, T. E. A71-27477 AFFDL investigations concerninq the coupled PERRIII, J. J. winq-iuselaqe-tail flutter phenomenon Influence of a sinusoidal wall perturbation on [AIAA PAPER 71-3261 A71-25306 trarjsition NONIBILER, T. A71-27470 TLe role of heat conduction in leadinq edqe PERRONE, n. heatinq - Theory and experiment A position paper on vehicle safety IREPT-6901 1 N71-22494 [ AD-7183971 N71-23333 NORBEEG, J. U. PERRT, P. J. Aircraft maintenance Analysis of taxiinq induced vibrations in aircraft A71-26308 by the power spectral density method NOSEK, s. n. A71-26311 Shuttle airbreathinq propulsion PETRILA. T. [ NASA-Tn-X-678061 N71-23764 The profile couple method for studying the flow of NYBAKKEll. G. A. an ideal fluid around a fixed arbitrary obstacle The structural oodelinq of aircraft tires in the prcscncr of a rectilinear wall [AIAA PAPER 71-3461 A71-25325 A71-26258 PETROV, 8. 8. Effect of chanqinq uins sweep on the dynamics of 0 the controlled processes OLDFIELD, P. E. 1171-25661 An application of hybrid roEputinq to desiqn and PETOLSKI, J. traininq Determination of the mutual aerodrnamic effects of A71-25852 Sn-1 helicopters durinq takeoff.and landinq OLSON. n. D. A71-26953 Free vihrations and random response of an PEILBERT, n. inteqrallr stiffened panel Wind tunnel visualization arrangements for fixed LR-544 1 N71-24298 or rotatinq annular cascades OLTARZEUSKI, 8. A71-27717 Fundduental problems in the production of PmLrPeE, J.-J. laminated aircraft structures Unsteady stall of an airfoil A71-26954 A71-27609 ORLIK-RUCKEFIANN, K. PINET, J. Initial studies of low temperature ablation in a nethods utilized in tests of the flying qualities helium hypersonic wind tunnel of the Concorde SC-CR-69- 3215 ] N71-23228 A71-27608 OSTROISKI, P. P. PLATOU. A. S. c’omputer qraphics on Joukowski airfoils wind tunnel supply headers TTN-71-21 871-22149 [AD-7182271 N71-23480 OTT, E. E. . PLOTKIN, A. Effects of fuel slosh and vibration on the Laminar incompressible flow past a circulation- flammability hazards of hydrocarbon turbine controlled circular liftinq rotor fuels within aircraft fuel tanks Technical A71-25494 report, 1 Sep. 1969 - 30 ~pr.1970 POPERL, D. J. IAD-718091 1 N71-23805 Coolinq airflow throuqh a stationary turbine disk OVCAINNIKOV, 0. and blade Planninq of transportation operations at ~EROFLOT INASA-Tn- X- 2 171 ] N71-22680 b71-27144 POLEAIIUS. E. C. Charts for predictinq the subsonic vortex-lift characteristics of arrow, delta, and diamond P winos PAPON. A. [ NASA-TN-D-62431 N71-21973 Theoretical and experimental study of blade PONTEZIERE, J. cascades in supersonic flows Rcvieu of testing techniques €or transonic A71-27475 airfoils. I - Apparatus for commercial tests at PARKS, E. G., JR. S3nA. II - Experimental study of wall netal matrix composite fabrication procedures for corrections at R1 Ch qas turbine enqine blades A71-27467 r AsnE PAPER 71-~~-461 R71-25979 POST, E. PARSONS, R. J. Experimental investiqations on supersonic combustion research in a shock tunnel combustion in the flow fields of bodies Of

B-12 PERSONAL AUTEOR INDEX SCEIEPER. E. E.

revolution and near a flat plate in tanqential REIIIEART, il. n. flow Ranufactnring approaches to resin matrix composite [ DLR-FB-73-64] N71-22129 airfoils for qas tnrbine engines POWERS. S. A. [kS!lP PAPER 71-GT-473 A 71- 2 59 80 Plow fields over sharp edqed delta uinqs with REIBIISER. E. attached shocks Desiqn of a nonexpandinq reflector balloon INASI-CR-17331 N71-22672 jnLL-B-20326-/5828.4F/1 N71-23934 POWERS, W. E. REXBOLDS, E. A. Boron and qraphite fiber market competition Kiqh teiperatnre turbines A71-25400 [ N AS A-Tl- I- 6 7 1231 N71-22699 PRAUSE, R. E. RICEARD, C. E. Analysis of brinellinq failnre of bearinqs from An analytical study of hydrogen cooled panels for vibration tested PLY fans Summary report application to hypersonic aircraft [ NASA-CR-117855 J mi-22527 [ ARSA-CR-1650] W71-22625 PUCCI, P. P. RICEARDS. E. T. Beat transfer to an airfoil in oscillatinq flow Cooling airflow through a stztionary turbine disk r ASEE PAPER 71-GT-181 A71-25963 and blade [NASA-TE-I-2171] 871-22680 RICEARDSOI. X. E. Q Dynamic and static uind tunnel tests of a flow QUAAL. 6. J. direction vane Performance testing of flnorosilicone hydraulic [NASA-TN-D-61931 n71-23115 fluid in hiqh temperature aircraft piston pumps RICEARZ, 0. A7l-270 40 V/STOL accidents or incidents QUICK, E. A. 1571-23428 The jet foe1 starter goes operational ROBERTS. 1. [ASEE PiPEB 71-GT-U3J 1171-25976 The promise of aeronautics A71-27601 ROBERTS, 5. C. R The handlinq qualities required for safe operation RAE. W. J. of sinqle enqine boundary layer controlled Some euaerical results on viscous lou-density aircraft in the STOL mode nozzle flows ir the slender-channel N71-23419 approximation ROCKEBBACE. R. 1. IAIAA PAPER 69-6541 A71-27556 Sinqle staqe experimental evaluation of compressor RAKEEATULIB. KE. A. blading with slots and wall flow fences Piou of a tuo-phase medium uith solid particles INASA-CR-72635 1 N71-7199S around a thin profile ROE., J. A7 1- 27450 Lift and hinqe moments of a delta control surface RAEASE. D. C. in a blunt-nosed canard confinnration Accoamodatinq passengers and cargo 4.71-25161 N71-2239@ BOSBER. J. C. RAEAEWBTIIY. P. Theoretical study of landing mat behavior Some remarks on Irulthopp's subsonic S7l-22891 liftinq-surface theory ROTEE, D. E. r BAL-TN-24 3 171-22472 Electron-beam stndies of viscous flow in RAESEI. C. E. supersonic nozzles Yan/mschine combination in the liqht of safety [AIAA PAPER 70-8101 A71-27555 reqnirements N71-23423 RAO. D. E. S Shock interaction effect on a flawed.. delta wins SAKAI, T. at n equals 8.2 Investigation concerninq the fluid flow in the A71 - 27 5 9 8 mixed-flow biffuser RAUCE. 5. [ASME PAPER 71-GT-40 J A71-25973 Performance analTsis of the modulation A study on the flow pattern within the centrifnqal cancellation altineter and mixed-flow impellers A71-27437 [ASBE PAPER 71-GT-411 A71-25974 RAWTANI. S. SAKAKIBARA. S. Aatnral freqnencies of rotatinq. 10s aspect ratio. Aerodynamic characteristics of a flared body with tUrbO8aChinerT blades blunt nose [AIAA PAPER 71-3741 A71-25347 [ YAL-TR-2211 1171-22160 REBA, I. SAKBLL, 1. Preliminary study of an anamented ram-rinq vehicle an experimental investigation ef the interaction concept Pinal report, 1 Anq. 1967 - 18 lay 1968 between a transverse sonic jet and a hypersonic rPB-1894251 1171-23283 stream REED. T. 0. A71-25472 Effects of Polyurethane foam on fuel system SALOEATOT, V. V. contamination Thermal behavior of aircraft structural elements r ASRE PAPER 71-GT-54 3 A71-2598 1 under conditions of aerodrnamic heatinq RBEVES. B. 1. A71-27493 Results of a Strong interaction, wake-like model SALTAIOV, 6. A. of supersonic separated and reattaching Interaction of particles with a wedqe surface in a tnrbulent flows supersonic two-phase flow [AIAA PAPER 71-1281 171-25476 A71-27665 BBGGIOBI. A. SABAVAlAEUTT00. E. I. E. Lift and drag of a wing-cone configuration in Experimental investigation of methods for hrpersonic flow iaproving the dynamic response of a twin-spool A71-25487 tQrbojet engine BEER. E. 6. [ASRE PAPER 71-GT-143 A71-25960 Besearch on advanced gasdynamic test facilities. SCHETZ, J. Part 2 - Laser-fluid interaction stndies Final Breakup of liquid sheets and jets in a sopersonic technical report, 1 Jul. 1966 - 30 Jun. 1970 gas stream r ~~-7177281 Nll-22593 1171-25471 BIICBEITEAL, J. SCHIEPER, E. E. Lift and hinqe moments of a delta control surface Performance testing of flnorosilicone hydraulic in a blunt-nosed canard confiqnration fluid in hiqh temperature aircraft piston pumps 171-25161 A71-27040

E-13 SCHMIDT, G. PERSONAL AUTHOR INDEX

SCHMIDT, G. SHIRK, M. A. Application of a hybrid computer to the AFFDL investiqations concerning the coupled development of a pilotl.ess captive helicopter winq-fuselaqp-tail flutter phenomenon A71-25847 [AIAA PAYSR 71-3261 A71-25306 SCEIIDTLEIN, 8. SHISHKIN, v. n. Operational provinq of autsuatic fliqht control Determination of the optimal parameters of an systems for V/STOL fiqhter aircraft ejector nozzle under supersonic fliqht N71-23415 conditions SCHNEIDER, 1. I. A71-27504 Evolution of the laninar wake behind a flat plate SHIVERS, J. P. and its uostream influence A wind tunnel investigation of static longitudinal A71-25469 and lateral characteristics of a full-scale SCAOWALTER, U. R. mockup of a light twin enqine airplane On the accuracy of Merk's method for solution of INASA-TN-D-62381 N71-23860 laminar boundary-layer equations SEROUT, 8. 1. A71-27051 A wind-tunnel investiqation of sonic-boom pressure SCHULTZ, K.-J. distributions of bodies of revolutior. at Mach mass transfer investiqations at a flat static 2.96, 3.83, and 4.63 liquid surface in parallel air flow forminq a r NbSA-TN-D-61951 N71-21961 laminar boundary laver SHULEH, W. T. r DLR-FB-70-58 1 N71-22072 HOW to qet there from here with new materials - A SCAULZ, G. desiqner's vieupoint On the measurement of the noise in the 171-27676 neiahbourhood of bodies in subsonic wind SIGALOV, G. P. tundels, part 2 Asymptotic solution of the problem of oscillations [ RAE-LIB-TRQNS-14651 N71-21885 of a solid profile in transonic gas flow SCHULZ. W. J. N71-23193 Development of Rorsic-aluminum composite fan SIKOESKY, S. I. blades for supersonic turbofan enqines Air space congestion ana the conpound helicopter r AsnE PAPER ~I-GT-~O1 A71-25997 N71-22189 SCAUM. A. J. SIMEROTA, J. U. Cold air investiqation of a turbine with Operational tests of dual baseline transmissometer transpiration cooled stator blades 4 - Staqe systems performance with rire-mesh shell stator bladinq [NBS-103391 N71-22455 [ NASA-T#-X-2176 ] ~71-239eo SKEWS, B. W. SCEWARTZ, I(. shock-shock reflection Rapid analysis methods for the design and A71-26192 optimization of uinq pivot svstems for variable SMIRNOPP, ?I. qeonetry aircraft Air and cosmic space common law as the only [AIAA PAPER 71-4041 171-27410 solution of the problem of determininq the SCOGGIIIS, J. R. boundaries of these spaces neteoroloqical balloon Patent A71-26325 [NASA-CASE-XHP-O4163] N71-23007 SIITA. C. C., JR. SBEBASS, E. Effect of engine position and high-lift devices on Finite difference calculation of the behavior of a aerodynamic characteristics of an external-flow discontinuous siqnal near a caustic let-flap STOL .ode1 [AD-7188351 N71-23738 [NASA-TN-D-6222] N71-23124 SEEGIILLEE, E. 1. A vind tunnel investigation of static longitudinal surface-flow visualization investigation of a and lateral characteristics of a full-scale delta wing shuttle confiquration at a Mach nockup of a liqht twin engine airplane number of 7.4 and several Reynolds numbers [ NASA-TN-D-6238 1 N71-23860 [ NISL-TN-X-62036 J N71-23953 SNYDER, G. Surface-flou visualization photoqraphs of the nsc The 6-747 and development of the SST orbiter and a 55 deq swept delta winq N71-22386 modification for several Reynolds numbers at SOLOMONIAN, E. SA. nach no. 10.4 Method for determininq unsteady flow downwash [NASA-TM-X-620331 N71-24001 behind a finite-span wino 4urinq a supersonic SBIEZIS, I. motion The hiqh-lift winq - Remarks on the prediction of A71-27697 charactexistics SPANGLEE, S. B. A71-2747fi Theoretical analysis of vortex shedding frbm SENOO, Y. bodies of revolution in coninq motion An analysis of flow through a mixed flow impeller [AIAA PAPER 70-521 A71-27552 [ASME PAPER 71-G?-2] A71-25948 SPARROW, G. U. A blade theory 3f an impeller with an arbitrary Analysis of effects of spanuise variations of qust surface of revolution velocity on a vane-controlled qust- alleviation [ASME PAPER 71-GT-171 A71-25962 system SHADOWEN, J. E. [ NXSA-TN-D-61261 N71-22058 A fluidic fuel control valve for turbine enqines SPENCER, B., JR. [ASflE PAPER 71-GT-441 A71-25977 Lou-subsonic longitudinal aerodynaoic SHEN, I.-T. characteristics of a twin-body space-shuttle Theory of high aspect ratio planing surfaces booster confiquration Technical report, 1 nay 1969 - 30 Apr. 1970 [NISA-TH-X-2162] N71-23135 r AD-7176671 N71-22345 SPIRIDONOV, IO. A. SHERIDAN, A. G. Influence of some desiqn parameters qas- Desiqn lessons 1-earned from the OV-lOA Bronco turbine-engine combustion chamber on the N71-23416 circumferential nonuniformity of the qas SHERMAN, A. temperature field Breakup of liquid sheets and jets in a supersonic A71-27501 qas stream SPEEITBR, J. R. A71-25471 Calculative techniques for transonic flows about SHERRER, R. E. cprtain classes of airfoils and slender bodies Intermediate diaqonal tension field shear beam NASA-CR-17221 N71-23133 development for the Boeinq SST STAAARA, S. S. [AIAA PAPPH 71-3401 1171-2531 9 Calculative techniques for transonic flows about SAEVIAKOV, A. A. certain classes of airfoils and slender bolles hutosdtion of aircraft and rockpt powpr plants - [ NASA-CR-17221 N71-23133 3rd r-vis:ed 394 enlarqed edition STALKER. K. U. A71-26403 Inertia welded jet enqine cooponents

B-14 PEESOBAL AUTHOR IBDEX TYSL. E. R.

[ASME PAPER 71-61-33] A71-25970 A71-275Gl STALLABEASS. J. E. TARABE, I. Enqine snow ingestion in the Bell 206a jet ranger node1 test on deflected jet pipes of the RAL helicopter Plyinq Test Bed [RRC-11893] N71-21927 f NAL-TR-209 ] R71-22147 STAEGAEDTEE. 8. TABI. T. Development of Borsic-aluminum composite fan Aerodynamic characteristics of a flared body with blades for supersonic turbofan engines blunt nose f ASEE PAPER 71-GT-90 J A71-25997 f NAL-TR-2211 N71-22160 STAELIBG. E. J. TAIUA, E. K. The development of terrain following radar Sound radiation from a point force in circular A71-26881 motion STEAEIAII. E. A71-26702 Recent contributions to experiments on cylindrical TAURESEY, J, 6. shell panel flutter Development of a torsional-flexural stability [AIAA PAPER 71-3281 A71-25308 aralysis of stiffened titanium panels for STEEEE. E. E. application to the U.S. Supersonic Transport Expandable structures for midair pilot rescue [ AIAA PAPER 71-338 J A71-25317 device TAYLOR, E. J. [AIAA PAPER 71-4021 A71-25278 Lessons from operation and trials of twin turbo STEII. I. prop aircraft on rouqh airfields Formalities involvinq the Tu-154 at foreign 1171-23417 airports in the case of three-man crews TELIOIIS. D. P. A71-25258 Boundary layer separation STEWART. C. 1. [ AD-7177721 N71-22241 The development of terrain following radar TEIHOV, V. K. A71-26881 Exparsion of a turbulent-jet boundary layer iU a STEWART. W. 1. slipstream Shuttle airbreathiuq propulsion A71-27505 fNASA-TM-X-67EG61 N71-23764 TBOEAS, J. A. G. STODDAED. P. J. Eicrowave applications of reinforced plastics Research on advar?ced gasdynamic test facilities. A71- 270 16 Part 1 - Studies of the isentropic compression THOEPSOII, E. E. tube as a means for producing hyperrelocity test Research on advanced gasdynamic test facilities. 5iu.s F'hcil technicill report. 1 Jul. 1966 - 30 part 2 - Laser-fluid interaction studies Final Jun. 1970 technical report, 1 Jul. 1966 - 30 Jnn. 1970 [AD-7177271 B71-22158 f AD-7177281 X?!-2?593 SUEPUSA, 8. THOESOB. J. A. Effects of Reynolds number on performance Study of conceptual and operational feasibility of characteristics of a centrifuqal compressor laser Doppler detection systems Progress report [ ASPIE PAPER 71-GT-251 A71-25967 NASa-CR- 1031051 * vi-24081 SUKAAEEV. I. P. THUEEAI. W. E. Investiqations of strains and stresses by means of A review of V/STOL aircraft accidents in the US Eoire patterns N71-23426 [ AD-717826) N71-22168 THYSOB. n. A. SUEUSUE. J. Extersion of Emnous* spot theory to flows on blunt New Zxperimectzl Teckniqnes in Propulsion and bcdies Enerqetics Research A71-27557 [ AGARD-CP-381 N71-22626 TOCEER. J. 1. SUIK. E. ?he impact of automated structural optimization on Application of a hybrid computer to the actual design development of a pilotless captive helicopter lAIAA PAPER 71-3611 1171-25340 A71-25847 TOGBET, A. SWITHEIBAIK. J. Study of the effect of the marginal vortex from a Combustion research in a shock tunnel helicopter blade on the aerodynamic flow around R71-22630 the followinq blade SZAICA, E. E. A71-27473 Cold air investiqation of a turbine with TOKUDA, n. transpiration cooled stator blades 4 - Stage Ln asymptotic theory of the jet flar, in three performance with wire-mesh shell stator bladinq dimensions [ NASA-Tn-X-2176 ] N71-23980 A71-27217 SZCZECIHSKI, S. TOBISAKI. T. Structural-endurance problems for rotor disks in Lift jet enqine, JRlOG turbine engines f ASEE PAPER 71-GT-751 i7?-?5089 A71-26952 TSUKAGOSEI. K. Investigation concerning the fluid flow in the mixed-flow diffuser T [ ASWE PAPER 71-GT-401 A71-25973 TAI. T. C. TSUEUEA. T. Application of the Eethod of Integral Relations On the most feasible configuration for airplane /nIR/ to transonic airfoil problems. Part 1 - gust-alleviation system Inviscid supercritical flou over symmetric A71-25195 airfoils at zero anqle of attack TULIIO. J. 8. [ AD-7173391 171-22098 preliminary desiqn and analysis of an advanced TAKAGI. T. convertible faxdshaftengine for V/STOL tactical Some effects of systematically varied location of and transport aircraft one concentrated mass on transonic flutter 171-26054 characteristics of sweptback thin cantilever TUEIEE, E. E. winq. I1 Anemometer with brakinq mechanism Patent 871-251 89 fNASA-CASE-XBP-O5224] R71-23726 TAKIZAWA, E. I. TYSL. E. E. The effect of wind-Gradient on the landing overall performance in arqon of a 16.4 centimeter approach of an aeroplane /6.44 inch/ sweptback bladed centrifuqal 171-25194 coipressor TALARTOV, A. V. f NBSA-Tfl-X-2269] N71-23659 Influence of some design parameters qas- turbine-engine combustion chamber on the circumferential nonuniformity of the gas temperature field

B-15 OENISRI, A. PERSONAL AUTHOR INDEX

training 171-25852 U QALTERS, P. E. OEUISRI, A. An analytical study of hydrogen cooled panels for A design method and the performance of two- application to hypersonic aircraft dimensional turbine cascades for hiqh subsonic [ NASA-CR-16501 N71-22625 flow WARE, G. E. [ASHE PAPER 71-GT-341 1171-25971 Low-subsonic longitudinal aerodynamic UKOLOV, I. S. characteristics of a twin-body space-shuttle Effect of chanqiug winq sweep on the dynamics of booster configuration the controlled processes [ NASA-TH-X-2162 1 N71-23135 A71-25661 WASRIZO. K. A note on the T-tail flutter 1171-25188 V QATANABE, I. VAS OOSTEROE, T. Effects of Reynolds number on performance Operational fliabt recordinq and its impact on characteristics of a Ceutrifuoal compressor fliqht safety and aircraft desiqn [AZRE PAPER 71-GT-251 A71-25967 N71-23412 Investigation concerning the fluid flow in the VANCO. E. R. mixed-f low diffuser Computer program describing turbine aerodynamic r ASRE PAPZR 71-GT-401 A71-25973 requirements, approximate external blade A study on the flow pattern within the centrifugal qeometries, and coolant flow requirements for a and mixed-flow impellers two staqe axial flow turbine [ ASHE PAPER 71-GT-41 ] 871-25974 [ NASA-Tn-X-2229 ] N71-22568 QATEBS. J. P. VENTRES, C. S. Aolographic characterization of aerospace Flutter of a buckled plate exposed to a static components pressure differential [ ASNE PAPER 71-GT-74 1 A71-25988 A7 1- 27584 Holoqraphic analysis of turbine blades VERET, C. [ ASnE PAPER 71-GT-841 A71-25992 Visualization of low voluretric mass WEIGEL, C. N71-22637 Overall performance in arqon of a 16.4 centimeter VEST. c. n. /6.44 inch/ sweptback bladed centrifugal Holographic detection of microcracks compressor FASHE PAPER 71-RET-C] A71-27312 [ NASA-TE-I-2269] 1171-23659 VEUILLOT, J.-P. WEIUSTEIII, 1. 1. Calculation of the mean flow in an atial-flow A shielded fine-wire probe for rapid measurement turbomachine of total temperature in high-speed flows A71- 277 1 5 ~71-25528 VIKTOROV, B. V. WEISS, C. D. Effect of changing winq sweep on the dynamics of Design considerations in inertia welding Of the controlled processes turbocharger and gas turbine components A71-25661 [ASHE PAPER 71-GT-211 A71-25965 VISBNBVETSKAIA, V. A. QEU, I[. S. Self-adjustiuq automatic control systems for an Aerophysics research based on free fliqht range aeroelastic aircraft measurements A71-26718 N71-22633 VISIUSKT, 1. 1. QENDT. K.-A. Laser beam probing of jet exhaust turbulence Variables influencing the direct operational costs A71-26304 of a V/STOL passenqer aircraft VITTE, 1. N71-22193 Elements of calculation for three-dimensional QRITAKER, R. A. aerodynamics in a perfect fluid Hanufacturing approaches to resin matrix composite A71-27477 airfoils for gas turbine enqines VOGELEY, A. W. [ ASHE PAPER 71-GT-471 871-25980 Combined optical attitude and altitude indicating WICK, 8. 8. instrument Patent Turbofan STOL research at NASA rNASA-CASE-XLA-01907] N71-23268 1171-27602 VOIDEUOV. A. P. QILCOI, R. 1. Equipment OIT-1200/50 for determiniuq the heat A fluidic fuel control valve for turbine engines resistance of sealinq materials [ASHE PAPER 71-GT-443 A71-25977 171-27686 IILDE, E. G. VOKITS, 8. S. Continued proqress on Concorde The feasibility of utilizing color cathode ray N71-22387 tubes for aircraft crew station displays IILET, 1. 8. Technical reDort, Ppb. - nay 1970 Preliminary desiqn and analysis of an advanced [ AD-7176551 N71-22174 convertible fan/shaft engine for V/STOL tactical VOLK, E. P. and transport aircraft Composites development, fabrication and A7 1-260 54 characterization WILKERSOR. J. C. A71-25427 Operational tests of dual baseline transmissometer VOLOSOVICR. 6. A. systens Equipment OIT-1200/50 for determining the heat [NBS-10339] N71-22455 resistance of sealing materials WILLIAIIS, J. C., I11 A71-27688 Curvature effects in the laminar and turbulent VOLBSOU, N. I. freejet boundary Statistical methods of determininq the dimensions A71-25482 and concentrations of various inhomogeneities WILLIAES, J. E. from satellite and aircraft measurement data The Goblin Ilk35 enqioe - Investigation of noise A7 1-27 100 and vibration [ ARL/IE-127 1 N71-22503 QILLIAHS, II. J. W Static pressure probes at nach number 7.5 WALL, A. C. [ ARL/A-327] N7 1-23778 Photometric characteristics of semiflush airport WILSON, J. C. lights Theory of the solid rotor induction machine [ NBS-101211 N71-22453 N71-21898 QALL, P. J- WILSON, J. P. An application of hybrid computinq to desiqn and Dynamic interactions of high speed tracked air

B-16 PEBSOIIAL AUTEOB IADEX ZIIAAA. B. J.

cushion vehicles with their quideuays - A parametric study [AIAA PAPER 71-3861 1171-25350 PIIIKLBR. E. 8. Aiqh temperature aerodynamics with electromagnetic radiation 871-27277 WISE. E. A. Development of a simulator for studying simplified lunar escape systems .~r AASA-TA-D-61111 1171-22590 10116. 6. 6. The applications of satellites to communications, naviqation and surveillance for aircraft operatinq over the contiguous United States. Volume 2 - Aapendices [ JASA-C8-117759] 1171-22340 POIIG. E. I. The role of heat conduction in leadinq edqe heatinq - Theory and experiment [ REPT-69011 mi-22494 WOOD. C. J. Viscous tails in Hele-Shar flow A71-26447 WOBIIOll. D. E. Leadinq edqe curvature based on convective heatinq Patent [ UASA-CASE-ILA-O1486] n7i-23497 POBTllAII. A, Three-dimensional staqnation-point heat transfer in equilibria. air flows [AIAA PAPER 70-8091 A71-27582 10. J. B. T. Computer graphics on Joukorski airfoils :TB-7?-2! ~71-22149 1 Y TALOWITZ. J. S. Integrated hiqh frequency antenna system Final report, 13 mor. 1969 - 9 Nor. 1970 I AD-71 8167 3 U71-23306 TATES, E. C.. JB. Analysis of supersonic-hypersonic flutter of liftinq surfaces at anqle of attack rAIAA PAPER 71-327) A71-25307 TEH. F. C. Cooliuq airflow throuqh a stationary turbine disk and blade rRASA-TB-X-2171] N71-22680 2 ZAGALSKT. 1. B. Optimal fuel system estimation IAD-717640 7 871-21922 ZAKKAT, V. An experimental investigation of the interaction betueen a transverse sonic jet and a hypersonic stream A71-25472 GEIEOUSIAB, B. KX. Structure of vortex flow in axial-flow turbomachines 171-27714 ZIBEABTE. E. K. Aircraft gas turbine condition analysis instrumentation - Its use for the status diaqnosis of naval turbine engines [ASLIE PAPER 71-GT-861 A71-25994 ZIE6LKE. E. The Viqgen landing system A7 1-25233 ZIPPER. I. The applications of satellites to communications, navigation and surveillance for aircraft operating over the contiguous United States. Volume 1 - Technical report [RASA-CR-117760] R71-22339 ZWAAII. B. J. Application of a method for estimatinq pressure distributions to an oscillating T-tail [ ALB-TR-68048-L] 1471-231 31

8-17 CONTRACT NUMBER INDEX

AERONAUTICAL ENGINEERING / A Special Bibliography (Suppl. 7) JULY 1971

Typical Contract Number Index Listing NAS1-9926 UKTSD-C-4539 I 15 A7 1-25983 21 N71-22379 21 N71-22380 NAS3- 7 3 377 NAS2-4151 i 32 A7 1-25351 120-27 N71-10021 I 01 871-23659 1AS2-4765 01 A71-27552 124-07-24-05 NASA ACCESSION 31 171-23135 rig ‘-

1 NASA-Langley, 1971 c- 1. Repat No. 2. G-ment Accession No. 3. Recipient's Catalog No. NASA SP-7037 (07) 4. Title and Subtitle 5. Repon Date July 1971 AERONAUTICAL ENGINEERING 6. Performing Organization cods A Special Bibliography (Supplement 7) I

7. Author(s1 8. Performing Orgdnization Repat No.

~ 10. Work Unit No. 9. Performing Organization Name and Addrers

National Aeronautics and Space Adninistration 11. Contrxt or Grant No. Washington, D. C. 20546

13. Type of Repon and Period Covered 12. Sponsoring Agency Name and Address

14. Sponsoring Agency COQ - 5. Supplementary Notes

6. Abstract

This special bibliography lists 466 reports, articles, and other documents introduced into the NASA scientific and technical information system in June 1971. Emphasis is placed on engineering and theoretical aspects for design, construction, evaluation, testing, operation and performance of aircraft (including aircraft engines) and associated components, equipment and systems. Also included are entries on reseerch and development in aeronautics and aerodynamics and research and ground support for aeronautical vehicles.

17. Key Words (Suggested by Author(s)) 18. Distribution Statement Aerodynamics Unclassified - Unlimited Aeronautical Engineering Aeronautics Bibliographies

19. Security Usnif. (of this report) 20. Security Clanif. (of this page) I 21. No. of Pages I 22 Ria* Unclassified Unclassified I44 I I -$3.00HC t For sale by the National Technical Information Sewice, Springfield, Virginia 22151 PUBLIC COLLECTIONS OF NASA DOCUMENTS DOMESTfC

deposqs its techncal documents and btdrijgraphrc tools *n eleven fedwai Repcmai Techntcat frepaa Centers focaied In the organtzattois i:s& beelow Eacn center is prepared to furnssh ?ne p~bk ference assislance. fnte bans, photocopy sentice, an documerrts for retentic

f Cahfornta, Berkeley imda Hall Ltbrary. Kansas NEW YORK ioradc. Boulder Columbia University New COLUMBIA PENN SY LVANt A hbraq of Congress Carnegie Ltbrary of Pinsbtrrgh GEORGlA TEXAS Georgia Institute of Technology, Atian!a Southern Methodist tinrversrty. Dahs fUfATUtS WASHINGTON The John Crerar Library. Chicago ff nwersity of Washington Seatlle MASSACHUSETTS Massachusens tnstitute of Technoiogy Cambrrdge