PREVIOUS BIBLIOGRAPHIES IN THIS SERIES

NASA SP-7037 Scptemher 1970 Jan. itug. 1970 W'ASA SP-7037 (01) Januar~197 I Scpt. Uec. 1970 NASA SP-7037 (02)

AERONAUTICAL ENGINEERING

A Special Bibliography

Supplement 2

A selection of annotated references to unclas- sified reports and journal articles that were introduced into the NASA scientific and tech- nical information system and announced in January 1971 in Scientific and Technical Aerospace Reports (STAR) International Aerospace Abstracts (IAAI.

Scieirtijic atrd Techirical Iirjomratioir 0jfic-e OFFICE OF INDUSTRY AFFAIRS AND TECHNOLOGY UTILIZATION 1971 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION This document is available from the National Technical Information Service (NTIS), Springfield, Virginia 221 51 for $3.00. 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 Aeroiiautical Eiigiiieeriiig-A Special Bibliographj. (NASA SP-7037) lists 394 reports, journal articles, and other documents originally announced in January 197 1 in Scieiitific aiid Technical Aerospace Reports (STAR)or in Iiiteriiatioiial Aerospace Abstracts (IAAI. 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 (includ- ing aircraft engines) and associated components, equipment, and systems. It also in- cludes research and development in aerodynamics, aeronautics, and ground support equipment for aeronautical vehicles. Each entry in the bibliography consists of a standard bibliographic citation accom- panied by an abstract. The listing of the entries is arranged in two major sections, IAA Entries and STAR Entries in that order. The citations and abstracts are reproduced exactly as they appeared originally in IAA or STAR, including the original accession numbers from the respective announcement journals. This procedure, which saves time and money, accounts for the slight variation in citation appearances. Three indexes-subject. personal author, and contract number-are included. An annuai cumulative index will be published.

... 111 AVAILABILITY OF CITED 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 NTlS The following are the most commonly indicated sources (full addresses of these organizations are listed at the end of this introducrionj 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 550 pages or less. Documents in excess of 550 pages up to and including 1100 pages are sold for $10.00 per hard copy. Those in excess of 1100 pages are priced individually by NTIS. Microfiche(') are available from NTlS for 95 cents for those documents identified by. the # sign following the accession number (e.g., N71-101 14#). 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 re- ceived 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 Scien:ific 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 ~n microfiche form. are listed in Nuclear Science Abstracts Services available 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 Dissertation 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 All requests should cite the author and the Order Number as they appear in the citation 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 1

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IV 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 availahility line or in com- bination with the corporate author line

IAA ENTRIES (A71-10000 Series)

All publications abstracted in this Section are available from the Technical Information Service, American Institute of Aeronautics and Astronautics, Inc., (AIAA). as follows: Paper copies are available at $5 per document up to a maximum of 20 pages. The charge for each additional page is $0.25. Microfiche are available at the rate of $1.00 per microfiche for documents identified by the symbol # following the accession num- ber. A number of publications, because of their special characteristics, are available only for reference in the AIAA Technical Information Service Library. Minimum airmail postage to foreign countries is $1. Please refer to the accession number, e.g.. A71- 10613. when requesting publications.

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 local libraries prior to order- ing any publication inasmuch as many of the documents have been widely distributed by the issuing agencies, especially NASA. A listing of public collections of NASA docu- ments is included on the inside back cover.

SUBSCRIPTION AVAILABILITY

This publication is available on subscription from the National Technical Information Service (NTIS) The annual subscription rate for the monthly supplements, excluding the annual cumulative index, is $1 8 00 All questions relating to suhscwptions should be referrea to the NTIS

V ADDRESSES OF ORGANIZATIONS

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ESRO/ELDO Space Documentation Service University Microfilms, Ltd European Space Research Organization Tylers Green 114. av de Neuilly London, England 92 - Neuilly-sur-Seine, France U S Atomic Energy Commission Her Majesty’s Stationery Office Division of Technical Information P 0 Box 569. S E 1 P 0 Box62 London. England Oak Ridge. Tennessee 37830

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vi TABLE OF CONTENTS

Page IAAEntries ...... 1 STAREntries ...... 33

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

TYPICAL CITATION AND ABSTRACT FROM $;TAR

NASA SPONSORED AVAILABLE ON DOCUMENT 7f MICRoFICHE ACCESSION NUMBER- N71-12035*# Pratt and Whitney Aircraft East Hartford Conn CORPORATE DEVELOPMENT OF MAINSHAFT SEALS FOR ADVANCED SOURCE AIR BREATHING PROPULSION SYSTEMS, PHASE 2 Final TITLE 2Report PUBLICATION V P Povinelli and A H McKibbin 23 Jun3 970 122 p refs I DATE (Contract NAS3-76091 (NASA CR 72737 PWA-39331 Avail NTIS&SCLZlE- Two mainshaft face seal configurations for advanced I CWITl gas-turbine engines were designed fabricated and tested The seal WM CONTRACT concepts incorporated lift geometries which used the relative motion OR GRANT between the primary seal surfaces to provide positive separation (f,:iri iubricoiwrl; One oesign self-acting) witn shrouded Rayleigh AVAllABlLITY REPORT step lift pads operated with a gas film separating the sealing faces 1 SOURCE NUMBER The other design (hydrodynamic) with a spiral groove geometry 3-operated with oil-film separation Tests of the gas-film seal demonstrated the feasibility of operation at gas temperatures to 1200 F pressure differentials to 250 psi and sliding speeds to 450 ft/sec Excellent correlations with analytlcally predicted perfonnance parameters were obtained Face wear was less than 0 1 mil after 320 hours at an air temperature of lo00 F a pressure differential of 200 DS~and a slrdnqg sooed of 400 *,‘see ave-23e anr leakage during that test was 14 scfm These operating conditions exceed the capability of conventional contact seals and the air leakage IS l/10 that of a labyrinth seal Testing of the oil-film seal revealed an inadequate seal force balance Author

TYPICAL CITATION AND ABSTRACT FROM /AA

NASA SPONSORED AVAILABLE ON DOCUMENT MICROFICHE

ACCESSlON-A71-10969 # Sphere drag in near-free-molecule hypeMnic TITLE NUMBER Row. M. 1. Kunoy, D. A. Stewart. and C. C. Horstman (NASA, Ames 77Research 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 usinga freeflight technique in PUBllCATlON the Ames 42-in. shock tunnel are tabulated, shown graphically, and DATE discussed. O.H. 7’

vii AERONAUTICAL ENGINEERING

A Special Bibliography (Suppl. 2) FEBRUARY 1971

criteria for design with respect to overall safety and particularly to afford minimum risk exposure to cabin attendants and paaengers Rom injuries due to: (1) routine use of galley installations; (2) galley components becoming dislodged under routine or abnormal operat- ing conditions and under survivable crash or ditching conditions; and (3) malfunctions of or defects in galley equipment. M.M.

IAA ENTRIES A71-10030 Emergency evacuation illumination. SA€ Aerospace Recommended Practice, ARP 5036, Aug. 1, 1970.4 p. Description of the purpose and provisions of practice ARP 5036 recommended for emergency evacuation illumination. The purpose A71-1001 5 An appsisal current shortcomings in of the of the practice is to provide criteria which will lead to standards of procurement and commissioning processes flight simulators. R. H. of illumination for emergency evacuation in passenger or cargo trans- J. Bellm. In: Royal AeronauZical Society. Two-Day Symposium on port aircraft that the emergency illumination will facilitate Flight Training Simulators for the '7* London, England, October such eg-. M.M. 14, 15, 1970, Proceedings. London, Royal Aeronautical Society, 1970, p. C.iC.9. Discussion of the steps involved in the procurement and commissioning of flight simulators taking into consideration certain A71-1M41 # Equipment for gas-flame heating of heat- difficulties and approaches to overcome difficulties. Difficu!ties these resistant materials during fatigue testing (Ustmovka dlia faclog *&siriluiator manufacturers because of different aircraft gazoplamennogo nagreva zharoprochnykh materialm pri ispytaniiakh confi(lurations are considered, and advantages to be derived by na ustalost'). A. M. Pen'kov, 6. N. Sinaiskii, A. M. Demchenko, A. D. standardization of equipment and procedures are discussed. G.R. Pogrebniak, and V. B. Mironov (Akademiia Nauk Ukraimkoi SSR, lnstitut Mekhaniki, Kiev, Ukrainian SSR). Fiziko-Khimicheskaia Mekhanika Materialov, vol. 6,no. 4,1970, p. 76-79. In Russian. A71-10022 Training for low visibility landing. 6. D. Description of a device for gas heating of samples of heat Armstrong and G. Musker (Royal Aircraft Establishment, Bedford, resistant materials subjected to fatigue tests at temperatures up to England). In: Royal Aeronautical Society, Two-Day Symposium on 1300 C. This device makes i: pasibie to create environmental Flight Training Simulators for the '70s. Lszdon, Engiana, October conditions which are similar to those in gas turbine engine during ?4, 15, 1970, Proceedings. London, Royal operation. A design layout diagram of the device is included. Z.W. Aeronautical Society, 1970, p. K.1-K.16. Discussion of some of the principles and practice of training for low visibility landings taking into consideration training in a ground-based simulator of comparatively modest dimensions. It is A71-10103 Index of starting system specifications and shown that worthwhile training can be imparted in such a simulator standards. SA€ Aerospace information Report, AIR 1174, July 15, provided considerable care is taken with the visual attachment. The 1970. 8 p. most important objectives of training for low visibility operations are Index of military and industry specifications and standards believed to be to impress pilots with an understanding of the extreme which are used in aerospace engine starting systems. Cartridge variability of fog; to establish fully effective crew procedures; and to pneumatic, electric, gas turbine, hydraulic. mechanical, and pneu- help pilots to acquire a grasp of the detailed meaning of the runway matic starting systems are included. Only those hardware standards lighting patterns. G.R. which have been specifically designed for engine starting systems are listed. Revisions and amendments which are current for these applications and standards are not listed. O.H.

A71-10028 Flight compartment glare. SA€ Aerospace lnfonnation Report. AIR 1151, Aug. 1, 1970. 3 p. 9 refs. Description of the purpose, goal, basic concepts, and sources of A71-10108 # The flow throu@~planar cylinder lattices in flight compartment glare. The goal of this report is to improve the range of transonic velocitii (ober die Durchstr6mng von visibility conditions for the flight crew by minimizing conditions ebenen Zylin- im Bereich schallnaher Geschwindigkeiten). which contribute to glare, Five recommendations are made for C. Kramer (Rheinisch-WestfalisheTechnische Hochschule, Aachen, minimizing glare. M.M. West Germany). Rheinisch-Westfi/ische Technixhe Hochschule, 4erodynamkches Instirut, Abhandlungen, no. 20,1970, p. 25-30. 10 refs. In German. Study of the phenomenological aspects of the flow through a A71-10029 Galley installations. SA€ Aerospace Recom- lattice making use of lattices with cylinders having a diameter of 15 mendedPractim, ARP 695A. Aug. 15,1970.7 p. rnp. Optical methods and recordings of the flow pattern by means of Description of the purpose, definition, and criteria of recom- a highspeed camera were used for observing the flow through the mended practice 695A. The purpose of this practice is to provide lattice. The flow in the region of the vortex street is discussed, and

1 A71 -101 09

photographs and Mach-Zehnder-interferograms are presented. The Steadily increasing computer capabilities, accompanied by easily phenomena involving the blocking of the flow when velocities near employed programming techniques, are providing maintenance and the sonic speed are reached are investigated. G.R. logistics analysts with powerful tools. Properly employed, these tools can serve a variety of applications at reasonable costs and will result in increased airline operations and maintenance effectiveness. This A71-10109 # The diffraction of shock waves at sharp paper describes simulation modeling techniques (Monte Carlo) used corners (Ober die Beugung von Stoawellen an wharfen Kanten). S. to study and quantify reliability and maintainability interrela- Schultz (Rheinisch-Westfalische Technische Hochschule, Aachen, tionships among large commercial transport aircraft. (Author) West Germany). Rheinisch-Weste Technische Hochschule, Aerodynarnisches i'm:itct, AbhandIun.g?n, no. 20, 1970, p. 31-35. In German. A71-1Oi29 T!ARA light aircraft engines A new genera- Study of the shape of diffracting shock waves taking into . consideration the temporal behavior of a disturbance involving a class tion. Wm. A. Wisernan and E. J. Ounsted (Teledyne, inc., Hawthorne, Calif.). Society of Automotive Engineers, National of shock fronts produd by J diffractinn at an angle of -165 deg. The physical principles pf shock wave diffraction are examined giving Business Aircraft Meeting, Wichita, Kan.. Mar. 18-20, 1970, Paper attention to the effects of angles and pressure ratios. The results of a 7&7205. 24 p. Members. $7 .Xi axrnnmhPrs; $1.50. numerical computation for an angle of -165 deg are shown in a The paper introduces a new family of aircooled, opposed. llght graph. The applicability of the results to other diffracting angles is aircraft engines consisting of four, six, and eight cylinders. with and investigated. G.R. without turbosupercharging. The paper explains an evolutionary approach to sizeable improvements in horsepower per pound of engine weight, horsepower per cubic inch displacement, and horse- power per cubic foot of bulk. A unique method of torsional control A71-10114 # Investigation of maintenance systems for com- eliminating pendulum dampeners and greatly reducing vibratory mercial jet aircraft and the factors which have an effect on them torque is also explained in detail. (Author) (Untenuchung von lnnandhaltunguystemen fur Strahlver- kehrsflugzeuge und deren Einflurzfaktomn). Klaus Harling. Berlin, Technische Universitat, Fakultat fur Maschinenwesen, Dr.-lng. Dis- sertation, 1969. 261 p. 90 refs. In German. A71-10132 # Detailed measurements in the transition region Discussion of the characteristics and the objectives of main- of a two-dimensional wake. Hiroshi Sat0 and Yoshio Onda (Tokyo. tenance systems of commercial jet aircraft giving attention to the University, Tokyo, Japan). Tokyo, University, institute of Space and various individual factors which have to be considered in establishing Aeronautical Science, Reporr no. 453, vol. 35, Aug. 1970, P. maintenance programs. The characteristic aspects involved in the 317-377. 10 refs. maintenance of commercial aircraft, and in changes and adaptations Study of the laminar-turbulent transition of a two-dimensional of the aircraft necessary to improve its performance are analyzed. wake with three kinds of imposed disturbances: the natural Objectives and problems of aircraft maintenance systems are dis- disturbance in a wind tunnel, a single-frequency sound, and an cussed. The various factors which are significant for such systems and external sound of two frequencies. In all cases the transition to the interaction of these factors are investigated taking into considera- turbulence is qadual. When a sound of single frequency is introduced tion questions of the reliability of the aircraft, its equipment, and its into the wake, the induced velocity fluctuation is regular and operation. Aspects of the deterioration of structural components are periodic and it persists, resulting in a transition delay. When a sound discussed, and the various types of costs involved in the operation of of two frequencies is introduced, two velocity fluctuations are the aircraft are analyzed. The development of a maintenance system induced. They vow independently while amplitudes are small. When is considered and various types of maintenance systems are amplitudes exceed certain values, two fluctuations interact and both described. G.R. amplitudes are reduced. The amplification of randomness in the transition process may be accomplished by the mutual suppression of amplitudes and by the generation of low-frequency components from high-frequency components. M.V.E. A71-10115 # System analysis of future jet and fan propul- sion systems for vertically starting commercial aircraft (Syrtemanalyse zukunftiger Strahl- und Geblaseantriebe fir vertikal- startende Verkehrsflugzeuge). Horst Pakendorf. Berlin. Technische A71 -101 66 The fatigue strength of nickel-base superalloys. Universitat, Fakultat fur Maschinenwesen, Dr.-lng. Dissertation, M. Gell, G. R. Leverant, and C. H. Wells (United Aircraft Corp., Pratt 1969. 194 p. 74 refs. In German. and Whitney Aircraft Div., Middletown, Conn.). In: Achievement of Study of jet and fan propulsion systems of VTOL commercial hi& fatigue resistance in metals and alloys; American Society for aircraft intended for short and intermediate runs on the basis of the Testing and Materials, Annual Meeting, 72nd. Symposium, Atlantic propulsion technology expected to be available during the time from City, N.J., June 22-27, 1969, Proceedings. 1975 to 1980. It is found that an optimal adaptation of propulsion Philadelphia, American Society for Testing and Materials (ASTM system and aircraft design will make it possible to obtain a reduction Special Technical Publication No. 467). 1970, p. 113-1 53; Discus- in weight of 18%and savings in operating cos% of 11% in comparison sion, R. N. Wright (Allegheny Ludlum Steel Corp., Brackenridge, with the state of the technology of the Do 31. The adoption of a Pa.). p. 296; Authors' Closure, p. 296-298. 68 refs. fuselage in the form of a spindle would result in further improve- The service lives of nickel-base superalloy components in gas ments of about 10%. Questions of the dimensioning of the turbine engines are frequently limited by their fatigue properties. propulsion system are examined and problems of the transition to This paper reviews what is known about the fatigue behavior of the aerodynamic flight are investigated. The effects of noise minima nickel-base superalloys and suggests methods for improving their specifications on the design of VTOL aircraft are discussed. G.R. properties. Low-temperature crack initiation occurs preferentially at microstructural defects such as pores and brittle phases in cast materials and at defects such as brittle phases and annealing twin boundaries in wrought materials. The brittle phases may contain A71-10128 Application of maintenance simulation tech- inherent cracks or be cracked during working operations or service niques to commercial transport aircraft. T. F. Weber, Jr. (Lockheed exposures. Plastic deformation at low temperatures is concentrated California GI., Burbank, Calif.). Society of Auromorive Engineers, in coarse planar bands, and as a result matrix cracking is predomi- National Air Transportation Meeting. New York, N. Y., Apr. 2023, nantly transgranular and crystallographic. Techniques are discussed 1970, Paper 700345. 7 p. Members, $1 .OO;nonmembers, $1.50. for increasing the low-temperature fatigue properties by minimizing

2 A71-1 0359

the role of microstructural defects and achieving a more homoge- A7 1-10270 Dynamic aspects of cockpit temperature con- neous distribution of deformation. At elevated temperatures, inter- trol on combat aircraft (Aspects dynamiques du contrble de le granular cracking predominates and methods are discussed for temphature cabine d'un avion de combat). Re& Jaeger (Breguet- improving fatigue properties through gain size control, the use of Aviation, Velizy-Villacoublay, Yvelines; Centre de Documentatior columnar-gained and singlecrystal materials, and the application of pour I'Armement, Paris, France). L'A6ronautique et I'Astronautique, oxidation-resistantand fatigue-resistant coatings. (Author) no. 23, 1970, p. 75-80. In French. Discussion of the means required for: (1) adjusting the cockpit temperature to pilotselected values (temperature control), (2) maintaining the selected temperature in the face of changing externalenvironment conditions (downstream regulation). as well as A71 -10170 Fatigue life improvement through stress (3) in the face of varying jet-engine rpm-speed operation (upstream coining mmthodr. E. R. Speakman (Douglas Aircraft Co.. Long regulation). For the ficst two temperaturecontrol varieties, an easily Beach, Calif.). In: Achievement of high fatigue resistance in metals applicable solution consists in regulating the amplification factor of and alloys; American Society for Testing and Materials, Annual the control loop while, for the third variety, the introduction of a Meeting, 72nd. Symposium, Atlantic City, N.J.. June 22-27, 1969, phase-advance corrective circuit is called for. M.V.E. Proceedings. Philadelphia, American Sodety for Testing and Materials (ASTM Special Technical Publication No. 467). 1970, p. 20923; Discussion, C. S. Yen (Hughes Tool Co., Culver city, Calif.), p. 226; Author's Closure, p. 226, 227. A71-10339 # Arbimly plane CarCBde consisting of thin and Description of the use of stress coining, a quick and economical siiidy curved profiles in a potential flow (Beliebiges ebener Gitter new process for bringing about an aircraft structure with a more aus den diinnen und schwachgew6lbten Rofilen in der Potential- balanced fatigue strength than was previously possible. Basically, the strfimung). Gheorghe Zidaru (Bucure$ti, Institutu1 Politehnic stress coining procedure, a proprietary method, involves controlling Gheorghe Ghwrghiu-Dej, Bucharest, Rumania). Bucumsfi, InStitUtuI the yielding material inside holes and in the material surrounding Politehnic Gheorghe Gheorghiu-Dei, Buletinul, vol. 32, Mar.-Apr. holes and dots. Stress coining induces residual compressive stresses 1970, p. 111-124. In German. that offset load-induced tensile stresses concentrated arwnd these Extension of the Birnbaum-Glauert method to the study of loadcarrying areas. The procedure can be used in highly stressed plane, linear cascades of thin, slightly curved profiles. The applica- areas to increase fatigue life and resistance to stress corrosion of tion of the method makes it possible to obtain approximations for structural members. Salvage rework reaming, stress coining, and the circulation around the cascade profiles, the flow velocities at installing an oversize fastener increases the remaining fatigue life to points infinitely upstream and downstream, the lifting force and approach that of a virgin stresscoined structure. The fatigue life of pressure moment acting on the profile leading edge, and the test specimens for various aircraft has been improved by a factor of influence coefficient of the cascade. M.V.E. approximately four. M.M.

A71-10345 # Quantification of the noisiness of 'approach- ing' and 'recedng' sounds. George Rosinger (Battelle Columbus A71-1 022% A hybrid frequency response technique and its application to aircraft flight flutter testing. J. M. Simmons, J. W. Laboratories, Columbus, Ohio). Charles W. Nixon. and Henning E. Benson, and J. P. Fiedler (LockheedGeorgia Co., Marietta, Ga.). In: Von Gierke (USAF, Aerospace Medical Research Laboratories, American Federation of Information Processing Societies, Fall Joint Wright-Patterson AFB, Ohio). Acoustical Society of America, Computer Conference. Las Vegas, Nev., November 18-20, 1969, Journal, vol. 48, Oct. 1970. pt. 1, p. 843-853. 17 refs. USAF- Proceedings. Montvale. N J AFlPS Press (AFIPS ruppnrted =sears!. Coi;nference Proceedings. Volume 35). 1969, p. 801-807.6 refs. Description of three experiments designed to quantify subjective Description of the use of a hybrid computing system and a new responses to timevarying sounds representative of those produced by rapid frequency response analysis technique in aircraft flight flutter aircraft flying over an observer at rest. The basic sound employed represented 'approaching' and 'receding' sources that continuously testing. The theory of flight flutter testing IS briefly reviewed, and the new data reduction system is described. In this system, twenty of increased or decreased in frequency and/or intensity. The compara- the data signals which are telemetered from the aircraft to the tive noisiness of such sounds was evaludted by means of paired Found receiving station are further transmitted in multiplexed comparison and individual adjustment judgements. The results are discussed and summarized. O.H. frequency modulated form to the hybrid computing area. Z.W.

A71 -10350 A new low-resistance nozzle for complete A71-10266 Contribution to the study of unsteady flows power compensation in variometers (Eine neue widerstandsame (Contribution a IYtude des Ccoukmemr instationnaires). Marcel Diire zur Totalenergiekompensation von Variometern). D. Althaus Chabonat. L'A6ronautique et I'Asb-onautique, no. 23, 1970, p. (Stuttgart. Universitat, Stuttgart, West Germany). (Organisation 23-37.9 refs. In French. Scientifique et Technique Infernationale du Vol a Voile, CongrPs. Review of early and recent research in the field of unsteady 1M,Alpine, Tex., 1970.) Aero-Revue, Oct. 1970, p. 600,601. In flows. Early theoretical research prompted a number of experimental German. studies, among which the one verifying the Katzmayr effect and Description of a low-resistance nozzle, a modification of the performed at the Saint-Cyr Aeronautical Institute in 1923 is given Irving nozzle, designed to produce a complete power compensation special consideration. The analysis of the results then obtained made in rate-of-climb indicators. The modified nozzle, unlike the original it possible to determine the conditions for an airborne test using a Irving nozzle, can be effectively used in high performance aircraft. glider. The test was performed with positive results at Beynes in Specifications of this nozzle and suggestions for its installation in 1949. This, in turn, made possible the setup of a series of model tests aircraft are given. V.Z. performed in the Eiffel Laboratory wind tunnel from 1962 through 1968. In the course of these tests, the influence of each of the major parameters affecting the performance of a flapping wing was determined, and a considerable performance improvement was A71-10359 Inturana- and liability questionr in connec- achieved by cornparison with wings operating in steady airflow. tion with the hijacking of aircraft, acts of sabotage, and armed M.V.E. attacks against an aircraft (Venictrerungr- und Haftungsfragen bei

3 A71 -10399

Flugzeugentfuhrungen, Sabotagehandlungen und bewaffneten Establishment Valcartier, Quebec, Canada). Metal Progress, vol. 98, Angiffen gegen ein Luftfahrzeug). Alex Meyer. Zeitschrift fur Nov. 1970, p. 84-86. Luftrecht und Weltraurnrechtsfragen, vol. 19. Oct. 15, 1970, p. Investigation of the crash of an aircraft in which 52 passengers 293-296. In German. and crew members were killed. The methods used in the investigation Discussion of questions of liability and insurance arising in are discussed taking into consideration conclusions reached and the connection with unlawful Seizures of aircraft and the forcible evidence upon which the conclusions are based. It was found that the diversion of civil aircraft in flight giving particular attention to crash was caused by an explosion and that the explosion center was conditions in the Federal Republic of Germany. It is pointed out in a lavatory compartment on the floor. G.R. that the general insurance of an aircraft does not cover damages which ;he aircrzft rGffPrs in connection with such cases. However, it is possible to obtain insurance which covers these cases. Questions of the liability of the airlines against passengers suffering damage in A71-10461 # On supersonic laminar boundary iayei; :&ai connection with the unlawful seizure of airlines are discussed. G.R. convex corners. K. Stewartson (Queensland, University, Brisbane, Australia; University College, London, England). Royal Society iionciorr;, F,-,xeed,%g:, Series A,. vol. 319, no. 1538, Oct. 27, 1970, p. 289-305. 15 refs. Examination of the structure of a laminar supersonic boundary A71-10399 Combating fire risks in aircraft. R. J. # W. layer near the convex corner, turning the flow through a given angle Cockram (Pyrene Co., Ltd., Sunbury-on-Thames, England). Tech Air, of incidence to flow, alpha, on the assumption that the product of VOI.26, NOV.1970, p. 2-7. alpha and the Reynolds number to the 1/4 power is about 1. In Discussion of approaches to reduce the hazards posed by fires in common with related problems already examined, the boundary aircraft taking into consideration problems of early fire detection, layer takes on the character of a triple-deck with the initial pressure fire extinguishing equipment, and survival in emergency landings. fall occurring upstream of the corner. Numerical studies show that as The use and the further development of optical detectors including the product of alpha and the Reynolds number increases so does the optical vision periscopes for detecting fires are discussed. The main proportion of the total pressure fall which occurs upstream of the fire risks in the fuselage area are examined and protective measures corner, and an analysis is given which strongly suggests that as the such as smoke detectors are considered. Various approaches and product of alpha and the Reynolds number to the 1/4 power media for extinguishjng fires are described. The reduction of fire approaches infinity, the relative pressure fall downstream of the risks due to electrostatic causes and lightning strikes is discussed. G.R. corner vanishes. The theory is carried over to include angles alpha which are small but finite and an earlier theory, due to Matveeva and Neiland, is made uniformly valid and completed. Comparisons with experiment are made which, while not being decisive, are en- A71-10409 # Automated device for conducting fatigue tests couraging. O.H. with programmed load variation (Avtomat dlia provedennia utomle- nisnikh viprobuvan' pri programnii zmini navantazhennia). A. V. Grechukha. Avtornatika, vol. 15, July-Aug. 1970, p. 67-70. In Ukrainian. A71-10465 Light turbine helicopter Dornier Do 132 Description of equipment for programmed control of electrical (Leichter Turbinen-Hubrchrauber Dornier Do-132). Gerhard inputs to an electrodynamic vibration stand used in fatigue testing of Kannamiiller (Dornier AG, Friedrichshafen, West Germany). aircraft structures. The system described can operate over a wide Flugrevue/Flugwelr International, Nov. 1970, p. 31-34, 39. In range of loading program variations both in terms of load durations German. and amplitudes. A block diagram of the entire system is explained, Technical analysis of the light five-seat tip-drive turbine-powered and circuits of switching functions are given. The equipment can be helicopter Do 132. It is pointed out that the aircraft is suitable for a used to evaluate the effects of load cycle quantities and amplitudes wide range of civil and military applications. Three prototypes are on the fatigue strength and to verify hypotheses about damage being built under a Federal Defense Ministry contract. Flight testing accumulation. Applications of the control system are not limited to will be started in 1971. The market situation is examined, and the endurance testing, and usage in other fields of industrial process design criteria are considered. The rotor drive system, the hot-gas control is feasible. T.M. generator, landing gear, fuel system, the electric system, and the instrument panel are discussed. G.R.

A71-10425 # Study of the interaction between plane super- sonic off-design jets and obstacles by the hodograph method A71-10466 Basis development - VFW-Fokker VC 400 (Isdedovanie vzaimodeistviia ploskikh sverkhzvukovykh neraschet- (Basirentwicklung VFW-Fokker VC 400). H. Rabel (Vereinigte nykh strui i pregrad metodom godografa). V. A. Filimonov (Moskov- Flugtechnische Werke-Fokker GmbH, Bremen, West Germany). skii Gosudarstvennyi Universitet, Moscow, USSR). Moskovskii Uni- Flugrevue/Flugwelt International, Nov. 1970. p. 4CL42. In German. versitet, Vestnik, Seriia I - Matematika, Mekhanika, vol. 25, Discussion of the component and system development and of July-Aug. 1970, p. 134-136. In Russian. the testing phase of VFW-Fokker's VC 400 tilt-wing VTOL cargo and Development of a scheme for constructing the flow pattern passenger transport project. The VC 400 development history is occurring during the interaction of a plane supersonic overexpanded briefly considered. The advantages of the tilt-wing concept and of jet with an obstacle. Both the case of normal incidence of the jet and the tandem wing layout of the aircraft are examined. The future the case of incidence at an angle to the direction of the velocity are development schedule is discussed giving attention to the completion considered. It is shown that the proposed scheme, which involves the of the VC 400 test rig at the end of 1971 and the rollout of the V1 use of hodographs. makes it possibleto determine the location of the and V2 prototypes in 1973. G.R. shock waves arising in the jet and to estimate the pressures on the obstacle. A.B.K.

A71-10479 # Use of the computer in design of gas turbine A71-10456 Investigating an aircraft disaster. Ralph D. mainshaft seals for operation to 500 ftlsec (122 mhec). L. P. Barer (Defence Research Establishment Pacific, Victoria, British Ludwig, J. Zuk, and R. L. Johnson (NASA, Lewis Research Center, Columbia, Canada) and Thomas S. Sterling (Defence Research Cleveland, Ohio). Illinois Institute of Technology and Fluid Power

4 A71-10501

Society, National Conference on Fluid Powr, Chicago, Ill., Oct A71-10501 The role of man in navigation; institute of 13-15, 1970, Paper. 37 p. 10 refs. Navigation, Anniversary Year Meeting, 25th. US. Air Force Computer programmed analyses of the seal temperature field, Academy, Colorado Springs, Colo., July 1-3. 1970. Rdngs. elastic displacements and seal force balance were used in an iterative Washington, D.C., Institute of Navigation, 1970. 550 p. Members, design procedure to arrive at a final mainshaft seal design. For high $15.; nonmembers, $25. speeds, temperatures and pressures in advanced engines, the sealing surfaces must not operate with rubbing contact. Hence, self-acting Contents: lift pads were incorporated to achieve positive separation of the Preface. W. A. Newsome, p. 1-3. sealing surfaces. Therefore, a small gas film separating the sealing Transcriptions of theme pariel discussion. W. M. Wrigley, C. surfaces is achieved and the associated high gas-film-stiffness forces McDowell, M. M. Macomber, T. Jorris, D. Sott, and D. G. Hoag, p. the seal nosepiece to dynamically track the runout motion of the seal $29. face. Analysis revealed that the pressure profile across the sealing Navigation and education. E. W. Anderson (Smiths Industries. dam was significantly affected by sealing face deformation and that Ltd.. Cheltenham, Glos., England), p. 3045. choked flow occurs at pressure ratio of greater than 4 to 1. The Navigation is a state of mind. T. D. Nicholson (American effect of this face deformation and choked flow was considered in Museum of Natural History, New York, N.Y.), p. 46-51. establishing the seal force balance. Further, to mitigate the effects of The role of man in the Aerospace Defense Command. R. M. thermal deformation it was necessary to structurally isolate the seat ahute (USAF, Aerospace Defense Command, Ent AFB, Colo.), p. from the shaft. The role of the computer in the seal design is 52-57. discussed. Tests confirm operation as predicted by the design The role of man in navigation. R. J. Astrella (USAF, Bombing analysis. (Author) and Navigation Branch, Offutt AFB. Neb.). p. 5864.

The role of man in tactical air navigation. C. H. Allison (USAF, Tactical Air Command, Langley AFB, VaJ, p. 6570. A71-10485 # Research in U.S.A. on LNG as an airplane fud. Richard J. Weber (NASA, Lewis Research Center, Cleveland, Ohio). The role of man in the Militaw Airlift Command. J. R. International Gas Union, International Institute of Refrigeration. and Livingstone (USAF, Military Airlift Command, Altus AFB, Okla.), p. International Institute of Gas Technology, International Conference 71-87. 5 refs. on Liquefied Gas. 2nd. Paris, France, Oct. 19-23. 1970, Paper. 11 p. Man's future role as an aircraft navigator. C. S. Hoffman and J. Methane, the principal constituent of liquefied natural gas, is an J. Czaja (North American Rockwell Corp., Anaheim, Calif.), p. attractive fuel for advanced airplanes. In particular, the commercial 881OO. I supersonic transport derives considerable benefit from methane's Operational aspects of advanced avionics. K. G. Conner (North improved heating value and cooling capacity compared to con- American Rockwell Corp., Anaheim, Calif.). p. 101-104. ventional kerosene. Potential increases of about 30 per cent in payload and a like reduction in direct operating m-t hs.v.5 &en iviecnanization and test of DME updated inertial. R. J. Holm (Litton Industries, Inc., Woodland Hills, Calif.), p. 105-110. ...-,a~~~~te.(i.A:- However, the characteristics of liquid methane, such as its low boiling temperature and relatively low density. cause practical problems in airplane design and operation. Research is being Inertial systems and area navigation in the US. domestic conducted by NASA in an attempt to illuminate and solve these airspace. J. M. Del Balzo (FAA, Washington, D.C.), p. 111-123. 6 problems. The work includes such areas as fuel tanks and insulation, refs. engine fuel systems, combustors, and turbines. (Author) Operating experiences using dual inertial navigation systems as the sole means of navigation. J. Z. Amacker (American Airlines, Inc., Tulsa, Okla.), p. 124-133. L~?aniiall\-aided on-board Apollo cislunar navigatton. P. J. Brennan and I. S. Johnson (MIT, Cambridge, Mass.). p. 134-163. 6 A71-10486 # Air transportation constraints - Their im- refs. plication on short haul. Kearney G. Robinson. H. C. Tinney, and L. Apollo transition in the art of piloting a vehicle. J. L. Nevine L. Leisher (Boeing Co., Renton, Wash.). American Institute of (MIT, Cambridge, Mass.). p. 164-206. 18 refs. Aeronautics and Astronautics, Annual Meeting and Technical Display, 7th. Houston, Tex., Oct 19-22, 1970, Paper 70-1309. 8 p. Man's ability to perform useful work in cabin atmospheres and Members, $1 50;nonmembers, $2.00. planned space missions. A. G. Koestler (USAF, Aeromedical Re- Examination of the economic contribution attributable to the search Laboratory, Holloman AFB. N. Mex.), p. 207-211. US. domestic airline industn, in the 1970-1980 time period, and the economic significance of airport-facilityconstrained growth of Influence of perturbing effects on a manual rendezvous system. passenger travel, with particular emphasis on the economic impact on A. M. Schneider, H. M. Koble, and E. T. Wilson (California. short haul. The national economic contribution attributable to the University, La Jolla. Calif.), p. 212-252. 6 refs. US. domestic airline industry is shown to be 3% to 4% of expected 1970-1980 personal consumption expenditures. It is also shown that Laboratory and field tests of a lunar surface navigation system. this contribution may be reduced if necessary airport and airway B. F. Walls, W. C. Mastin, and P. H. Broussard. Jr. (NASA, Marshall development does not occur. This analysis indicates that the Space Flight Center, Huntsville, Ala.), p. 253-269. magnitude of this reduction is minimized if resultant growth constraints are satisfied by reducing the frequency on shorthaul Man-machine considerations in system design for all-weather, flight segments. The expected impact of such action is found to be a low-level navigation. G. V. S. Raju and D. L. Horwitz (Ohio 45% reduction in 1980 short-haul airline revenue and a 25% University, Athens, Ohio), p. 270-280. 5 refs. reduction in the 1970-1980 accumulated short-haul revenue. The potential of using a STOL system to recover this reduced market Navigation training in current spaceflight. F. Hughes and C. potential is investigated and compared to the requirements imposed Floyd (NASA, Manned Spacecraft Center, Kennedy Space Center, by continued expansion of the existing conventional system. No Fla.), p. 281-291. clear investment requirement superiority of one system over the Star charts for manned space flight. T. A. Guillory, G. E. other is indicated. It is concluded that the case for or against use of Gentry, and J. W. O'Neill (NASA, Manned Spacecraft Center, STOL rests on the validity of several key assumptions and on Houston, Tex.), p. 292-313. customer and public service issues regarding both short haul and Application of the Kalman filter to orbit determination. G. E. STO L . O.H. Elliott, T. R. Filiatreau, and R. W. Johnson (USAF, Institute of

5 A71 -10502

Technology, Wright-Patterson AFB, Ohio), p. 314-331. 7 refs ry Year Meeting, 25th. U.S. Air Force Academy, Colorado Springs, Colo., July 1-3, 1970, Proceedings. Washington, Use of planetaria in navigation instruction. K. W. Brotnov (US. D.C., Institute of Navigation, 1970, p. 6570. Air Force Academy, Colorado Springs, Colo.). p. 332-337. Discussion of the role of the navigator in the Air Force since the introduction of navigators into the tactical forces weapon systems. An advanced ship system with dockside training. T. D. Mara and Navigational precision in tactical reconnaissance and fighter aircraft J. de Spautz (Marine Digital Systems, Inc., North Plymouth, Mass.), is shown to have become mandatory in order to meet the challenge p. 338-351. of sophisticated hostile environments and the wide spectrum of Fix expansion and the 3rd dimension in submerged navigation. operational requirements. Rapid technological advances in sensors W. G. Clautice (U.S. Navy, Naval Submarine School, Groton, Conn.), and navigational systems enable the navigator to attain a precision p. 352-357. previously unknown in tactical fighter and reconnaissance missions, A trade off - Ship personnel navigation training and equipment but have ais0 increabid iha ;iadi:icna! dimensions of his role to that capability. M. X. Polk (Northrop Corp., Hawthorne, Calif,), p. of a highly trained and versatile Weapon System Officer. M.V.E. 358-362. Project K-V. H. Halamandaris ibreiiiie Fosi:ioniq Corn , Encino, Calif.), p. 363-376. The future of navigation training at the US Naval Academy. F. A71-10504 # The role of man in the Military Airlift Com- R. Whalen (U.S. Naval Academy, Annapolis, Md.), p. 377-390. mand. John R. Livingstone (USAF, Military Airlift Command, Altus Time and navigation. R. Haupt (U.S. Naval Observatory, AFB, Okla.). In: The role of man in navigation; Institute of Washington, D.C.), p. 391-399. Navigation, Anniversary Year Meeting, 25th. U.S. Air Force The Ben Franklin Gulf Stream Drift Mission. W. Rand Academy, Colorado Springs, Colo., July 1-3, 1970, Proceedings. (Grumman Aerospace Corp., Bethpage, N.Y.), p. 400.407. Washington, D.C., Institute of Navigation, 1970, Navigator training. J. R. Burgess (USAF, Air Training p. 71-87. 5 refs. Command, Randolph AFB, Tex.), p. 408-415. Discussion of the range of responsibilities of the Military Airlift Command (MAC) navigator. Advances in MAC aircraft equipment Navigator training analysis. R. E. Hull (Douglas Aircraft CO., include inertial navigation systems, multimode radar operating in the Long Beach, Calif.), p. 416-428. X and Ku frequency bands, new loran-C equipment, and an energy Aircraft navigator training system design. J. A. Benson and W. management analog computer to monitor enroute fuel requirements. A. DeTally (Douglas Aircraft Co., Long Beach, Calif.), p. 424465. 7 The MAC navigator is employed by the Command not only to refs. I navigate, but to serve as a staff officer for the aircraft commander. Training philosophy for complex navigation systems. A. L. As such, he acts in a variety of roles. He is a navigator, weather Sterzer (North American Rockwell Corp.. Anaheim, Calif.), p. analyst, fuel manager, and flight planner. He has significantly 466-476. enhanced the Command's safety record by monitoring approaches Improved crew member tiaining through multimedia instruc- and departures. In order to perform his assigned combat duties, he tion or . The process. M. E. Wood (USAF. Human Resources has become an expert at low level pilotage and aerial delivery. Laboratory Williams AFB, Ariz.), p. 477-485. 6 refs. M.V.E.

Software - Man's ultimate aid to navigation. J. W. Rigdon (Grumman Aerospace Corp.. Bethpage, N.Y.). p. 486-500. Summary of project THEMIS study on automatic navigation. A. P. Sage and J. L. Melsa (Southern Methodist University. Dallas, A71-10506 # Operational aspects of advanced avionics. Tex.), p. 501-521. refs. 9 Kenneth G. Conner (North American Rockwell Corp., Autonetics The future role of man in the repair of navigation systems. R. M. Div., Anaheim, Calif.). In: The role of man in navigation; Institute of Genet (USAF, Aerospace Guidance and Meteorology Center, Navigation, Anniversary Year Meeting, 25th. U.S. Air Force Newark, Ohio), p. 522-528. Academy, Colorado Springs, Colo., July 1-3, 1970, Proceedings. The pole of simulators in navigational training . Past, present, Washington, D.C., Institute of Navigation, 1970, and future. B. R. Groves (Goodyear Aerospace Corp.. Akron, Ohio). p. 101-104. p. 529-540. 10 refs. Discussion of the requirements placed on modern avionics by the designer's task of maximizing the pilot's chances of surviving the mission and destroying a selected target. Man's vital importance to aerial warfare is obviously his mental capacity. Aerial warfare is A71-10502 # The role of man in navigation. Ralph J. tactics, and tactics involve clever on-the-spot judgment which in turn Astrella (USAF, Bombing and Navigation Branch, Offutt AFB. requires man's mind despite his inherent limitations. All of the Neb.). In: The role of man in navigation; Institute of Navigation. system design should be for the purpose of removing those Anniversary Year Meeting, 25th. US. Air Force Academy, Colorado limitations to enhance the effectiveness of the pilot's irreplaceable Springs, Colo., July 1-3. 1970, Proceedings. mental processes. This must be accomplished by increasing sur- Washington, D.C.. Institute of Navigation, 1970, p. 58-64. vivability, by extending the sources of pertinent input data, and by Discussion of the basic theme of 'The role of man in navigation' eliminating preoccupation with routine computations and reactions. from a Strategic Air Command point of view. Attention is focused When properly designed, the system supports man and augments his on the three primary areas of mission, machine, and man. Mission unique judgmental capacity and response to novel situations. A few profiles are presented for past, present, and future operations and are highlights of current system mechanizations are presented. M.V.E. followed by a review of the machinery or equipment required to support the mission concerned. The demands of the special environ. ment upon man are discussed in order to determine his role in A71-10507 # Mechanization and test of DME updated iner- navigation during the coming decade. M.V.E. tial. Robert J. Holm (Litton Industries, Inc., Woodland Hills, Calif.). In: The role of man in navigation; Institute of Navigation, Anniversa- ry Year Meeting, 25th. U.S. Air Force Academy, Colorado Springs, Colo., July 1-3, 1970, Proceedings. Washington, A71-10503 ,4 The role of man in tactical air navigation. D.C., Institute of Navigation, 1970, p. 105-110. Clark H. Allison (USAF, Tactical Air Command, Langley AFB, Va.). A Litton LTN-51 inertial navigation system augmented by two In: The role of man in navigation; Institute of Navigation, Anniversa- rlinital nMFc was flown in an FAA flight inspection aircraft for

6 A7 1 -1061 3 evaluation of performance in the domestic area. The LTN-51 inertial A71-10567 # Measurement of dear air turbulence in the computer received range inputs from two separate DME stations. The lower stratosphere using the Millstone Hill L-band radar. R. K. Crane geographic fix of the two DME ranges was used to update the inertial (MIT, Lexington, Mass.). In: American Meteorological Society, wstem. Data were recorded automatically every four seconds, and Radar Meteorology Conference, 14th. Tucson, Ariz., November performance was validated bv comparison with flight inspection 17-20. 1970, Proceedings. Boston, American data. A total of 150 successful flight hours covering the western Meteorological Society, 1970, p. 101-106. USAF-sponsoredresearch. United States were achieved in 2-1/2 months. The data show that the Discussion of the thin turbulent layer detections made at heights deviation at 1150 ft was 50%; at 1410 ft, 68%; at 2400 ft. 95%; and above the tropopause, using the Millstone Hill L-band radar, at 3100 ft, 100% (50th percentile points). Terminal approaches were complemented by radiosonde soundings and a few U-2 aircraft also demonstrated. ( AJthor ) probes. The information obtained on the structure of scattering layers in the upper troposphere and lower stratosphere is expected to prove useful in the prediction of tropospheric and stratospheric layers. M.V.E. A71-10508 # Inertial systems and area navigation in the US domestic ah-. Joseph M. Del Balzo (FAA, Systems Research and Development Service, Washington, D.C.). In: The role of man in navigation; Institute of Navigation, Anniversary Year Meeting, 25th. A71-10587 # Development of procedures for vectoring air- U.S. Air Force Academv. Colorado Springs, Colo., July 1-3, 1970, craft around thunderstorms. William Lewis (FAA, National Aviation Proceedings. Washington, D.C., Institute of Facilities Experimental Center, Atlantic City, N.J.). In: American Navigation, 1970, p. 111-123.6 refs. Meteorological Society, Radar Meteorology Conference, 14th. Discussion of the performance requirements for airborne area Tucson, Ariz., November 17-20, 1970. Proceedings. navigation systems as proposed in FAA Advisory Circular W45.and Boston, American Meteorological Society, 1970, p. projection of these performance requirements through 1995. The 301-304. 7 refs. application IT rits of an inertial navigation system with position Discussion of the use of traffic-radar-generatedweather contours updating from conventional gound referenced navigation aids to by air traffic controllers in helping aircraft avoid severe weather. It is meet these present and forecast performance requirements are shown that in using these weather contours, controllers must allow assessed, and the effects on pilot workload are discussed. Also an additional clearance distance obtainable from historical radar included is a brief discussion of a planned flight evaluation assessing weather data made available by the National Severe Storms Labora- the effects of an integrated InertiaVDME-DMElmap display area tory. Peripheral contour clearance distances are presented. With their navigation system on aircraft navigation performance and pilot help, a vectoring plan based on a reasonable assessment of all factors workload. M.V.E. involved can be worked out for the guidance of air traffic controllers. M.V.E.

A71-10509 # Operating experiences using dual inertial navi- gation systems as fhe sole means of navigation. Jefferson Z. Amacker A71-10606 # Solution of the problem of flutter of a wing (American Airlines, Inc., Tulsa, Okla.). In: The role of man in wiU~a rigid aileron by the method of electronic modeling (Reshenie navigation; Institute of Navigation, Anniversary Year Meeting, 25th. zadachi o Rsttere kryla s rhestkim eleronorn metodom ek?&tnmnopo US. Air Force Academy, Colorado Springs, Colo.. July 1-3, 1970, modelirovaniia). S. A. Bidkhov and lu. V. Ponomarev (Moskovskii Proceedings. Washington, D.C., Institute of Gosudarstvennyi Univwsitet Moscow, IJSSR). Moskovskii Unk-

Navigation, 1970, p. 124-133. sitet, Vestnik, Seriia 111 ~ Fizika, Amonomiia, vol. 11, July-Aug. Discussion of some major inferences drawn from American 1970, p. 41 M21. In Russian. Airlines' experience with dual inertial navigation systems in the Outline of a procedure for solving the problem of flutter of a North Pacific as the sole means of navigazion. The important facts wing with a rigid aileron with the aid of an analog computer. The brought to light by *is experience include the following. Equipment problem is solved by a method based on the reduction of the reliability is the foremost element in obtaining crew confidence and solution of the corresponding boundary value problem to the promoting operational success. Design of the cockpit panels is solution of a certain set of Cauchy problems. The values of the crucial, and should be done painstakingly using both operational and critical flight velocity and the critical vibation frequency for a given engineering inputs. Adequate system training is required on a value of the aileron suspension elasticity are determined. A com- recurring basis for both flight and line maintenance personnel. parison is made with the results obtained by the Bubnov-Galerkin Operational problems can generally be traced back to one of the method. A.B.K. three elements just mentioned and, therefore, are the responsibility of the engineer rather than the flight or maintenance crews. M.V.E.

A71-10613 # Flow fUd associated with the impingement of an overexpanded jet against a cone (Pole techeniia pi natekanii A71-10515 # Manmachine considerations in system desip pererarthirennoi svedchzvukovoi mi na konur). M. V. Sushchikh for all-wasther, low-level navigation. G. V. S. Raju and D. L. Horwitz and V. I. Pogorelov (Leningradskii Mekhanicheskii Institut. (Ohio University, Athens, Ohio). In: The role of man in navigation; Leningrad, USSR). Inzhenemo-fiziclx?rtii Zhumal, vol. 19, Aug. Institute of Navigation, Anniversary Year Meeting; 25th. U.S. Air 1970, p. 269271. In Russian. Force Academy. Colorado Springs, Colo.. July 1-3, 1970, Proceed- Application of the method of characteristics to the calculation ings. Washington, D.C., Institute of Navigation, of a supersonic overexpanded flow past a cone. It is shown that a 1970. p. 270-280.5 refs. DOD-sopportedresearch. semibounded supersonic jet with a barrel-type structure forms at the This paper is concerned with man-machine considerations in cone surface. This jet possesses only one period within the limits of system design for low-level nmigatipn. In particular, computer which the flow attains supersonic speeds. The barrel-type structure generation of command information and visual display preoentation leads to the formation of a trailing shock and can be reflected from are described. Simulated results are presented which indicate that the the cone surface in a regular or irregular way. The coordinate of the Pilot's ability to fly on a given route is improved with the roll point of irregular reflection is determined from the condition of command display. (Author) minimum static pressure behind a trailing shock. V.P.

7 A71 -1071 8

A71.10718 # Synthesis of selective multidimensional invari- auxiliary power unit (APU) field from 1948 to the present are ant systems (K voprosu sinteza selektivnykh invariantnykh mnogo- discussed, The technical evolution of the APU and the operational mernykh sistem). N. P. Kolpakova. In: Theory of invariance of requirements that have dictated the APU design are described. The automatic systems; All-Union Conference on Invariance Theory and advancements in compressors and combustor design, the decrease in Its Application in Automatic Control Systems, 3rd, Kiev, Ukrainian noise level, the decreased fuel consumption and the improvements in SSR, May 31-June 5, 1966, Transactions. Volume 1 (Teoriia specific weight over the past 23 years are discussed. The units that invariantnosti avtomaticheskikh sistem; Vsesoiuznoe Soveshchanie today are being designed for the next generation of aircraft are po Teorii Invariantnosti i ee Primeneniiu v Sistemakh Avtomati- considered. G.R. cheskogo Upravleniia, 3rd. Kiev, Ukrainian SSR, May 31-June 5, !$!&e,Trudy Volume 1). Edited by lu. G. Gurevich. Moscow, Izdatel’stvo Nauka, 1970, p. 22&224. 8 ds. In Russian. A71-10752 A cornpararive stiidy cf aircraft gust arralvsis Theoretical study of the couplings between the control coordi- procedures. R. A. Cox (Imperial College of Science and Technology, nares db a fac?or in designing multidimensional invariant control London, England). Aeronautical Journal, vol. 74. Oct. 1970. P. systems. The selection of a root control channel and of the number 80?-8!1.6 refs. of controlled couplings to make a control system of this class Review of the various currently avaiiabie nieihod: of rllCtilatin!l selectively invariant is discussed. A theorem is formulated and proved the response of an aircraft to turbulence and of obtaining design to determine these variables when constructing an optimal invariant loads. The power spectral methods, which are expected to form the control system. The results are applied to the optimization of a basis of a future airworthiness requirement, are discussed in some turboprop engine with a differential reductor. V.Z. detail. Only static strength (rather than fatigue) aspects are con- sidered. Preliminary results obtained in a recent series of calculations G.R. for a typical T-tail aircraft are presented and discussed. A71-10748 Air traffic control by satellites . End of the 1970 test programs (ContrBle ‘aerien par satellites . Fin des campagnes d’essais 1970). Pierre Langereux. Air et Cosmos, vol. 8, A71-10753 Collision avoidance systems. G. L. Perry Oct. 24, 1970,~.14, 15. In French. Results of the-second and last test program conducted at (Royal Air Force College, Cranwell, England). Aeronautical Journal, Aire-sur-Adour within the framework of the Dioscures project of VOI.74, Oct. 1970, p. 814-816. satellite control of air traffic. The CNES-SGAC and ESRO ex- Discussion of the technique employed in prototype equipment periments are briefly described, and attention is given to a possible designed to prevent aircraft collisions taking also into consideration 1971 experiment with the Concorde. F.R.L. an original principle as a design basis for a collision avoidance system. The presently investigated American system for avoiding mid-air collisions is evaluated. It is found that the weak point of this system stems from the fact that it is a cooperative system. and relies on the A71-10749 The Bertin company proposes a new formula presence and serviceability of other equipment. A system is proposed for a short takeoff aircraft (La societe Bertin propose une nouvelle which is non-cooperative. The principle of the system is based on the formule d’avion a decollage court). Jacques Morisset. Air et Cosmos, mechanics of the collision situation. G.R. vol. 8, Oct. 24, 1970, p. 26, 27. In French. Description of the Aladin 2 STOL transport concept, developed by Bertin, which would be used for very short interurban flights (30 to 60 mi). The concept could incorporate bypass Rolls-Royce- A71-10754 Direct lift control. W. J. G. Pinsker (Royal SNECMA M 45 H engines assoclated with Bertin-designed silencers. Aircraft Establishment, Bedford, England), Aeronautical Journal, The resulting let would be deflected by flaps on the blown wings. It vol. 74, Oct. 1970, p. 817-825. 12refs. is proposed to test the formula on a Nord 262 fuselage. Special Discussion of the feasibility of direct lift control (DLC) for attention is given to noise reduction. F.R.L. aircraft taking into consideration the results of flight and simulator experiments available to date. The possible role of DLC in the aircraft is discussed and the various design aspects raised by its introduction are analyzed. Questions of coordination with conven- A71 -10750 The Thomson-CSF IEP validates the possi- tional elevator control are considered. The theory of aircraft bilities of the human pilot fL’1.E.P. de Thomson-C.S.F. met en valeur response to direct lift application and the repercussions in such fields G.R. les possibilites de pilote humainl. Jean-Claude Trichet. Air et as stall margins and piloting are discussed. Cosmos, vOI. 8. Oct. 24, 1970, p. 32, 33. In French, Description of the IEP (Indicateur Electronique de Pilotage/ Electronic Pilotage Indicator) developed by Thomson-CSF for airline A71-10774 fl Supersonic wing-body interference. R. W. use. The equipment consists of a seven-in. cathode ray indicator. It is Clark (University College, London, England). Cambridge possible to present information actually furnished by seven different Philosophical Society, Proceedings, vol. 68, Nov. 1970, p. 719-729. iristiuments: liedding, io11 and pitch, speed and speed tendency, Research supported by the Science Research Council. altrtude altitude tendency, glide and localizer patterns, and and Consideration of the supersonic inviscid flow past a wing-body flying control oiders. The system divides the symbols into three combination consisting of a semiinfinite plane wing symmetrically Colnts - red for symbols related to the aircraft, green for those related placed about an infinite convex cylinder. When the cylinder is to the ground, and yellow for the others. F.R.L. circular in cross section, a formal solution for the Laplace transform of the velocity potential exists. This solution is given in the form of a series which is only slowly convergent near the boundary surface separating the disturbed and undisturbed regions. However, this slow A71-1 0751 The development of small gas turbines for convergence has been overcome by Waechter (1969) using the aircraft auxiliary power (Tenth Halford Memorial Lecturel. C. H. Poisson summation formula on the Series solution. The solution to Paul (AiResearch Manufacturing Company of Arizona, Phoenix, the problem in the neighborhood of this boundary surface is Ariz.). Aeronautical Journal, vol. 74, Oct. 1970, p. 797-805. mathematically related to short wave diffraction by a cylinder, and Discussion of the history of the development of small gas this relationship is exploited in the solution given. Using this analogy, turbines for aircraft auxiliary power giving particular attention to the combined with boundary4ayer analysis, Stewartson (1966) examined activities at the Garrett Corporation. The significant events in the the solution again for the circular case. An alternative approach is

8 A7 1- 10859 given by Jones (19671, who develops the problem for an arbitrary combustors. In particular, there is a requirement for a chamber cylinder using electromagnetic diffraction theow based on the operating with a weak mixture in the primary zone, at all engine method of Green’s functions. The results obtained are in agreement conditions. (Author) with those of Jones (1967) for the general cylinder, and with Stewartson (1966) and Waechter (1969) for the circular cylinder. M.V.E. A71-10821 # A rapid method for the matching of twospool turbojeB. H. I. H. Saravanamuttoo (Carleton University, Ottawa, Canada). Canadian Aeronautics and Space Journal, vol. 16, Oct. A71-10818 # Aerodynamics low and dow (The W. Rupert 1970, p. 345,346. Turnbull Lecture). R. J. Templin (National Aeronautical Establish- Description of a method for the matching of two-spool turbojet ment, Ottawa, Canada). (Canadian Aeronautics and Space Institute, engines, assuming that both the high- and the low-pressure turbines Annual General Meeting, Ottawa, Canada, May 18, 19, 1970.1 are choked and that the turbine flow characteristics are independent Canadian Aeronautics and Space Journal, vol. 16, Oct. 1970, p. of rotational speed. The procedure involves superposition of the 318-328. 16 refs. low-pressure turbine choking line on the high-pressure compressor Survey of Canadian ;search on low-speed air motions at characteristic. The results are valid over most of the running range altitudes below about 2OOO ft. Laboratory-scale simulation studies of provided both turbines remain choked. and the method can be the gum and irregular motions in the earth’s surface wind layer are readily extended to include secondary effects. T.M. described, and some results are given in the form of wind turbulence spectra. The efficiency of slow powered-lift aircraft flight is examined in terms of thrust requirements, and miscellaneous aspects of biological aerodynamics are treated. T.M. A71-10825 Electronic flight control is getting set to take off. J. P. Sutherland and R. C. Hendrick (Honeywell, Inc.. Aerospace Div., Minneapolis, Minn.). Electronics, vol. 43. Nov. 9, 1970, p. 87-92. A71-10819 # Noise reduction - A must for air tranrportation Discunion of the current flight-test stage in the field of progress. R. Dixon Speas (R. Oixon Speas Associates. Inc., elecnonic control of the actuators of aircraft flaps, ailerons and Manhasset, N .Y .I. (Canadian Aeronautics and Space Institute and other flight control surfaces as a promising alternative to the present American Institute of Aeronautics and Astronautics, Joint Meeting, mechanical linkages. The history and the future prospects of the new Toronto, Canada, July 9, 10, 1970.) Canadian Aeronautics and Space control systems are surveyed. The high complexity of the current Journal, vol. 16, Oct. 1970, p. 333-337. 18 refs. mechanical control systems is pointed out as a condition urging A plea is made for a concentration of technological attention improvement. The tradeoffs involved in the selection of redundant upon noise reduction, as a primary task for those concerned with the designs for new electric wire contrc! :ystcrn; zie siialyzed. it is a.’vxcen;ez? sf air iransporrarion in me seventies. Acknowledge- expected that the new systems will eventually permit a hi@er ment is given to quiet engine programs currently being accomplished aircraft maneuverability and a superior reliability in flight. V.Z. by aircraft and engine manufacturers under government sponsorship. A need is cited for intensified research supported by cost-benefit analyses of economic benefits to communities, users of air trans- portation, and the aircraft industry. The economic benefits which A71-10844 Approximate solution of a singular integral would accrue are considered more substantial than usually estimated. equation relating to the subsonic flow past oscillating wings. S. N. A program of three positive steps forward in noise reduction is Chaudhuri (Tennessee, University, Tullahoma, Tenn.). International proposed: (1) development of objectives which will provide a Journal of Engineering Science, vol. 8. Oct. 1970. P. 829-842 8 refs. reasonable balance between ?!?eccns of techno!ogical improvements An approximate method has been developed to solve the and noise reduction benefits received; (2) projection of the quest for singular integral equation occurring in the theory of three- quieter engines into major programs of intensified research and dimensional wings oscillating harmonically in subsonic flow with development; (3) establishment of a realistic and practical timetable arbitrary frequencies. If the oscillations are slow enough and the for research and development, engineering flight testing, operational Mach number not too near unity, Garner has shown that the flight testing in a real life airportcommunity relationship, and governing differential equation of the complex amplitude of the certification of achieved objectives. Alleviation of aircraft noise enthalpy can be approximated by the Laplace equation. However, if problems as currently experienced in airport operations and airport the frequency of the oscillating wing is not low, the acceleration planning is considered the major technological challenge of air putential satisfies the homogeneous form of the Helmholtz equation. transportation in the seventies. (Author) The solution of this differential equation with the known oscillatory boundary condition then leads to the complicated singular integral equation obtained by several authors. The presence of the ex- ponential term in the chordwise integrals together with the infinite limit of integration complicates matters. By splitting up the range of A71-10820 # Air pollution by gas turbines ~ Is control possible. J. Odgen (Universite Laval, Quebec, Canada). (Canadian integration in a particular manner it is shown in the present paper Aeronautics and Space Institute. Annual General Meeting, Ottawa, that the integral equation can be solved for any arbitrary frequency. Canada, May 18, 19, 1970.1 Canadian Aeronautics and Space The method has been applied to the calculation of pitching Journal, vol. 16, Oct. 1970. p. 339-344. 15 refs. derivatives with first order frequency effects for sweptback wings in The paper takes a very practical look at the removal of the subsonic flow and the results compared with those given by Garner major pollutants present in gas turbine exhausts. Two of these, to check the accuracy of the calculations. (Author) carbon (smoke) and hydrocarbons, are nonequilibrium compounds and there is no theoretical reason why they cannot be eliminated by improvements in engineering design. Carbon monoxide, because of its rapid rate of decomposition, should also be capable of being A71-10859 # Scale length m atmospheric turbulence as reduced in quantity. Nitrogen oxides present a much more difficult measured from an aircraft. R. J. Taylor, N. E. Bacon (Common- problem because of their extreme dependence upon temperature as a wealth Scientific and Industrial Research Organization, Div. of rate controlling factor. The main solution to this form of pollution Meteorological Physics. Aspendale, Victoria, Australia), and J. lies in preventing its formation, rather than trying to reduce the Warner (Commonwealth Scientific and Industrial Research Organiza- content after formation. If complete control of pollutants is tion, Div. of Radiophvsics, Epping. New South Wales, Australia). required, then there will have to be radical changes in the design of Royal Meteorological Society, Quarterly Journal, vol. 96, Oct. 1970.

9 A71-10875

p. 750-755. 10 refs. predictions that much of the sail compression flow will be nearly Scale lengths, defined in four different ways, have been derived centered. (Author ] from previously reported spectra and autocorrelations of vertical air velocity component measured from an aircraft at heights between 10 and 1310 m. Below about 200 m the scale length increases with height more slowly than linearly and it does not seem possible to A71-10930 # Results from a new wind-tunnel apparatus for attribute this result to stability effects. At higher levels, no studying coning and spinning motions of bodies of revolution. Lewis systematic height dependence can be shown. The results offer some B. Schiff and Murray Tobak (NASA, Ames Research Center, Moffett support for the suggestion that the scale length is greater in lapse Field, Calif.). AlAA Journal, vol. 8, Nov. 1970, p. 1953-1957. 6 refs. m~ditionsthan ntherwise. (Author) Description of an apparatus which reproduces either separate or combined coning and spinning rrioiions of B kdy of eio!n?inn in a wind tunnel, using a sixcomponent strain gage balance to measure the aerodynamic forces and moments. Results of experiments with a A71-10875 # -.I ne sraius of federa; invokemen: in &::h-u! slender cone in coning motion show that at small angles of attack the air transportation. Richard D. FitzSimmons and William E. Thurman. side-force and side-moment coefficients normaiiied by the ccning American Institute of Aeronautics and Astronautics, Annual Meeting rate are linear functions of the angle of attack, the slopes of which and Technical Display, 7th, Houston, Tex.. Oct. 19-22. 1970, Paper are in excellent agreement with the damping-in-pitch coefficients. 701286. 3 p. This agreement, predicted by linearized theory, indicates that at The paper discusses the interagency cooperation that could lead small angles of attack the dynamic damping-in-pitchcoefficients of a to a short haul air transportation program taking into account the body of revolution can be measured as the steady side force and realities of fiscal restraints and the somewhat overlapping agency moment coeff iciena of the body undergoing coning motion. For responsibilities. Some of the aspects of federal involvement are larger angles of atrack, where vortices appear on the leeside of the discussed. Some thoughts on the interaction of civilian and military body, the normalized side force and moment coefficients become agencies and the private industry and municipalities are described. nonlinear functions of angle of attack. Photographs of vortices reveal Finally, the impact of this new involvement of the government is that they are displaced from the angle-of-attack plane by coning developed in view of the many benefits which should accrue to the motion. O.H. nation. (Author)

A71-10931 # Drag of rectangular cavities in supersonic and A71-10926 # Compressible laminar boundary layer on a transonic flow including the effects of cavity resonance. 0. Wayne cone at high angle of attack. Russell A. Smith and Paul K. Chang McGregor (General Dynamics Corp., Fort Worth, Tex.) and Robert (Catholic University of America, Washington, D.C.). AlAA Journal, A. White (Illinois, University, Urbana, Ill.).AIAA Journal, vol. 8, vol. 8, Nov. 1970, p. 1921.1927. 19 refs. Contract No. N Nov. 1970, p. 1959-1964.21 refs. NSF Grant No. GK-2053. 00017-67-C-0008, The drag of relatively short rectangular cavities (length-todepth 4ri approximate integral method is applied to the three- ratios of 0.50-3.0) with turbulent shear layers has been measured at dimensional laminar boundary-layer equations, including the energy transonic and supersonic Mach numbers (0.3-3.0). Of particular equation for Prandtl number equal to unity. to obtain a solution to importance is the effect of pressure oscillations within the cavity the attached boundary layer on slender cones in hypersonic flight at (commonly referred to as cavity resonance) which is shown to high angles of attack. The velocity and total enthalpy profiles are of increase the drag as much as 250%. Cavity resonance is found to the Timman type. The crossflow velocity profile is a two-parameter occur over the entire Mach number range investigated and other family allowing for nonzero crossflow at streamline inflection points. work has shown it to occur at both lower and higher Mach numbers. Because of the high angles of attack considered, the solution includes The frequency of the pressure oscillations is best predicted by the the effect of large crossflow velocity on the boundary layer. Using vortex-wave interaction model presented by Rossiter. The effects of the pressure data available in the literature, results for the heat external reinforcement of resonance by reflection of radiated transfer coefficient, surface shear stress direction, and position of pressure waves are examined both experimentally and analytically. separation are computed. The computations compare favorably with Existing methods for predicting cavity drag are inadequate to cope data from the literature. (Author) with this phenomena. A new model for predicting the lower bound of cavity drag (nonresonating cavity) is presented and agrees well with experimental data, Analytical considerations are utilized to indicate the qualitative effect of resonance on cavity drag. (Author)

A71-10927 # Statics and aerodynamics of lifting decelera- tors. L. H. Townend (Royal Aircraft Establishment, Farnborough, Hants., England). (American Institute of Aeronautics and Astro- A71-10932 # Kinetic theory analysis for the flowfield of a nautics, Aerodynamic Deceleration Systems Conference, El Centro, two-dimensional nozzle exhausting to vacuum. A. A. Peracchio Calif., Sept. 23-25, 1968, Paper 68.945.) AlAA Journal, VOI.8. Nov. (United Aircraft Research Laboratories, East Hartford, Conn.). 1970, p. 1928-1935. 27 refs. (American Institute of Aeronautics and Astronautics. Fluid and At supersonic and hypersonic speeds, llfting decelerators may Plasma Dynamics Conference, San Francisco, Calif., June 16- 18,

take the form uf par'iwings or two-dimcnsioiial "sails. I' For free- 1969, Paper 69-658.) AIAA Journal, vol. 8. Nov. 1970, p. stream M.rch nunibcrs between 10 and 4, an analysls is made of 1965-1972. 12 refs. Research supported by the United Aircraft CorD. the profiles 'issunled and isentropic waves produced in nonvlscous Analytical study based on the Bhatnagar-Gross-Krook (BGK) flows by twn-din~ens1~~1~~1sails, under pure tension clnd of flnltc rquation. The nonlinear BGK equation is solved iteratively by weight. At thc hlghcr trcr-stream M,lch numbers, 1.irge pirts of integration through usc of the method of charactcristlcs. A thr comprcssiun tlctw drc virtually centered. and even for long computer program based on the resulting equations is described, sdils (c.g. , 100-ft chvrd) at ,i high Mdch nunibcr (e. g., IO) and low and plots of density, tempcraturr, and velocity for the exhaust stress (e.g. , 5 tons/in. L), the wcight of such ri mc.rnbr.inc necd rcginn arc shown for two nozzle Reynolds numbers (or chamber not excerd 1 Ib/ftL. The twu-dlmrlrsi~rn,II .in.ilysls cdn include thc prcssurcsl. As expectrd, thc results dvvlate from continuum cffects of skin frictlijii nil 15 extrndcd to singly-curved "c,,ret" predictions. The flowfield cxists evcrywhurc, not only within the sails, whlch dll<)w Ic,idlng c.dg~,sto bc swept but CAII stlll product, limiting strramhne predicted by Lontinuum thc~ory. An uncxpccted two-diinrnsion.il w.ivcs; cqullibnutn can stlll bu mdintctincd by rise in static temperature is notc~din tht, <,xpanslon Ilowficld near ppr opri .I t c~ 1y cippli ~YIten h I 1c f (1 rc e s . Expc r 1 me nt ciI r vid uiic c on thr curncr of thc nozzle where the. largrst drv~atlonsfrom the two-dimrnsiun.il, rectnnguldr sails tends tu support thr thcoretical assumptions of continuum fluid mc.chanics occur. (Author)

10 A71-1 101 6

A71-10939 # . Discrete element approach to flutter of skew A71-10969 # Sphere drag in near-freemolecule hypersonic panels with inplane forces under yawed supersonic flow. Kariappa, flow. M. 1. Kussoy, D. A. Stewart, and C. C. Horstman (NASA, Ames B. R. Somashekar, and C. G. Shah (National Aeronautical Labora- Research Center, Moffen Field, Calif.). AlAA Journal, vol. 8, NOV. tory, Bangalore, India). AlAA Journal, vol. 8, Nov. 1970. p. 1970, p. 2104, 2105. 9 refs. 2017-2022. 12 refs. Investigation of the drag coefficient of spheres at hypersonic The flutter problem of skew panels, with in-plane forces under Mach numbers for near-free-molecule flow conditions. sphere drag yawed supersonic flow, has been considered in this paper through the data in the near-free-molecular regime for flow conditions close to application of matrix displacement methods. Necessary kinematically earth satellite conditions, obtained by using a free-flight technique in consistent aerodynamic influence coefficient matrices (AIC), which the Ames 42-in. shock tunnel are tabulated, shown graphically, and are applicable to yawed supersonic flows, have been developed and discussed. O.H. are employed in the formulation of the dynamic equations of motion. The results have also been compared with the other available results and the agreement is found satisfactory. This approach makes it possible to tackle flutter problems of panels with practically any A71-10971 # Comment on 'A memod for extracting aero- boundary condition including cut-outs, if any, and subjected to dynamic Coefficienk from fms-flight data.' Charles H. Murphy (U.S. thermal or other midplane forces. (Author) Army, Ballistic Research Laboratories, Aberdeen Proving Ground, Md.). AlAA Journal, vol. 8, Nov. 1970, p. 210921 11. 5 refs. Comment on the recent Chapman-Kirk iterative technique of finding the parameters of various differential equations from A71-10940' # Comparison of thwry and experiment for free-flight data. A comparison is made of this technique with a nonlinear flutter of loaded plates. C. S. Ventres and E. H. Dowell simpler quasi-linear technique for the case of a missile with nonlinear (Princeton University, Princeton, N.J.). (American Institute of damping and static moments. Moreover, a discrepancy in the Aeronautics and Astronautics, Structural Dynamics and Aero- Chapman-Kirk fit to the motion of the missile is explained. O.H. elasticity Specialist Conference, New Orleans, La., April 16, 17, 1969, Proceedings, p. 285-2951 AlAA Journal, vol. 8, Nov. 1970, p. 2022-2030. 17 refs. Grant No. NGR-31-001-124. Theoretical analysis of the flutter behavior of plates with in- A71-10979 Wingan air traffic control environment. plane boundary support flexibility exposed to transverse pressure Eli J. Dalabakis and Timothy R. Holmes (Electronic Communiw loadings, or buckled by uniform thermal expansion. Quasi-steady tions, Inc., St. Petersburg, Fla.). In: NTC 70; Institute of Electrical aerodynamic theory and Von K&m&'s plate equations are employed. and Electronics Engineers, National Telemetering Conference, Los Two sets of in-plane boundary conditions are considered: (1) zero Angeles. Calif., April 27-30, 1970, Proceedings. in-plane motion normal to the edges, and (2) zero in-plane stress at the edges. A modal expansion of the transverse deflection is used New York, Institute of Electrical and Electronics Englmrr, !nc.. n-.- .UYJU, in conjunction with Galerkin's method tn obtair. a sei ui noniinear p. 31-36.Contract No. AF 33(615)-64C-1127. siciinary differential equations which are integrated numerically The problem of simulating an Air Traffic Control (ATCI to determine the flutter motion. It is shown that the stability bound- communication environment is investigated. A mathematical model aries of low aspect ratio plates with zeroedge restraint are more is developed using actual (ATC) statistics. The model consists of sensitive to pressure loads than are those of plates with complete defining the statistical properties of the airborne message generators edge restraint. Moreover, comparisons with available experimenta which represent the airborne terminals, and the statistical properties data indicate that zero edge restraint is a good assumption for some of the ground based generator representing the tower. This is panel configurations. Finally, it is indicated that fair agreement accomplished by taking raw ATC data from transcribed tapes and between theory and experiment can be obtained for buckled plates. reducing such data into meaningful statistics. The second element is (Author) the ckue!opmer.: sf s computer algorithm that accepts the input statistics and performs the necessary scheduling of events. A polling subroutine is also developed, to accommodate a burst data link, to compare traffic (number in queues, waiting times, channel utiliza- A71-10948 # Nonaffine similarity laws inherent in tion) with and without polling, where the polling time shares the Newtonian impact theory. Howard Jaslow (Technik, Inc., Jericho, voice channel. (Author) N.Y.). AlAA Journal, vol. 8, Nov. 1970, p. 2062-2064. 5 refs. Derivation of nonaffine similarity laws and transformations wbject to the limitations of Newtonian impact theory. Applying these transformations to different configurations, the lift and drag coefficients of complementary configurations can then be related A71-11014 Solution of the equations of motion of mrough the appropriate similarity laws. It is pointed out that the coupled-bending tonion vibrations of turbine blades by the method results obtained may be extended to three-dimensional configura- of RitzCalerkin. J. S. Rao and W. Carnegie (Surrey, University, tions and generalized to configurations which are not com- Guildford, England). lnternational Journal of Mechanical Sciences. plementary. O.H. vol. 12, Oct. 1970, p. 875882. 15 refs. In this paper Galerkin's procedure is applied to determine the natural frequencies of a straight cantilever blade with an asymmetric wrofoil cross-section executing coupled-bending torsion vibrations. The results obtained are compared with the calculations made by a numerical procedure developed by Rao and the theoretical and A71-10956 # Application of Whitham's theory to sonic experimental results of Carnegie and Dawson. The results obtained boom in the mid- or near-field. Y. S. Pan (Tennessee, University, by Galerkin's process are shown to be in good agreement with the Tullahoma, Tenn.). AlAA Journal, vol. 8, Nov. 1970, p. 2080-2082 theoretical and experimental results mentioned above. (Author) 7 refs. Contract No. FA-70-WA-2260. Discussion of the validity of Whitham's (1952) theory of supersonic flow in the modified and near field of a slender body. The consideration of this theory is related to sonic-boom research in A71-11016 A review of methods for assessing loss co- large-model wind tunnel work where only mid-field and near-field efficienk in radial gas turbines. Rowland S. Benson (Manchester, simulation is done. General quantitative and qualitative modifiw University, Manchester, England). lnternational Journal of Mechani- tions of Whitham's theory are attempted, and an extrapolation of a cal Sciences, vol. 12, Oct. 1970, p. 905932. 22 refs. Research known disturbance signature to the far field is performed. M.V.E. supported by CAV, Ltd.

11 A71-11019

A number of methods for representing the losses in radial gas (Determination exp6rimentale des fluctuations de pression sur les turbines for predicting the off-design performance are reviewed. It is aubes fixes d'un compresseur axial de grande puissance). Guy Fasso shown that reasonable predictions of the Turbine performance may and Robert Larguier. fa Recherche Aerospatiale, Sept.-Oct. 1970, p. be made using one-dimensional theories if the nozzle gas exit angle is 272,273. In French. based on the l/cos(o/s) rule with some deviations due to rotor speed Summary of the results obtained from a series of wind-tunnel and if the rotor exit angle is based on the l/cos(o/s) rule at the mean tests carried out for the purpose of studying periodic pressure radius. The rotor losses may be divided into two parts. The first part fluctuations occurring on the fixed blades of a high-power axial-flow is an incidence loss and the second part the rotor passage loss, A compressor. An attempt is made to determine the dynamic character- number of methods for representing these separate losses are istics of three different types of pressure sensors used in these reviewed. It is shown that the shock loss method is satisfactory to studies. It is shown that it is possible to obtain periodic steady represent the incidence loss, and that the method suggested by Fuiual iandom va!"er of the pressures on the stator blades of a large-size and Wasserbauer gives the simplest method for predicting the rotor axial-flow compressor, The results obtained provide a tentative idea passage loss. (Author) of the amplitude of the forces exciting the vibrations and also shed light on the behavior of the rotor wakes and their effect on the stator biaries. A.B.K.

A71-11019 # Pressure field induced on a lifting surface by an isotropic atmospheric turbulence (Pression induite sur une surface portante par une turbulence atmospherique isotrope). Gabriel A71-11048 # Construction and design of high-pressure Coupry (ONERA, Chdtillon-sous-Bagneux, Hautsde-Seine, France). balloons made from fiberglass-reinforced plastics (Konstruirovanie i (International Council of the Aeronautical Sciences, Congress, 7th. raschet ballonov vysokogo davleniia iz stekloplastika). B. A. Bigula. Rome, Italy, Sept. 14-18> 1970, Paper /CAS 70-30.)La Recherche A. T. Vasilenko, la. M. Grigorenko, V. S. Gumeniuk. A. A. Kritsuk, Aerospatiale, Sept.-Oct. 1970, p. 241-249. 5 refs. In French. and A. I. Shinkar' (Akademiia Nauk Ukrainskoi SSR, lnstitut Discussion of the aerodynamic theory of a lifting surface and of Mekhaniki, Kiev, Ukrainian SSR). Prikladnafa Mekhanika, vol. 6, the integral equation which relates the pressure field to the angle of Aug. 1970, p. 117-120. In Russian attack of a wing. The solution of this integral equation is shown to Development of a method of calculating the stless strain state of give an approximate Green function of the problem. This provides a balloons made from fiberglass-reinforced plastics. The method makes method for computing the cross power spectrum of the pressure field use of a numerical technique (programmed for the 2M computer) induced by an isotropic atmospheric turbulence, once the cross proposed by Vasilenko et al. (1970) for calculating the stress-strain power spectrum of the vertical component of the turbulence is given, state of orthotropic multilayer shells of revolution with layers of The method is not more complicated than the one which relies on variable rigidity. The method is shown to be suitable for obtaining the assumption of uniformity of turbulence in span. As an example, optimum designs of balloons and similar structures made from the transfer function of the CONCORDE to turbulence has been fiberglass-reinforced plastics. V.P. computed by both techniques. M.M.

A71-11020 # Calculating the kernel of the lifting surface A71-11063 f, Experimental study of rotating stall in high- integral equation in unsteady subsonic flow (Sur le calcul du noyau pressure stages of an axial-flow compressor (Eksperimental'noe de I'equation integrale de la surface portante en ecoulement issledovanie vrashchaiushchegosia sryva v vysokonapornykh subsonique instationnaire). Roland Dat and Jean-Pierre Malfois. La stupeniakh orevogo kompressora). V. S. Beknev, A. V. Zemlianskii, Recherche Aerospatiale, Sept.-Oct. 1970, p. 251-259. In French. and R. 2. Tumashev (Moskovskoe Vysshee Tekhnicheskoe The kernel of the integral equation linking the pressure on the Uchilishche, Moscow, USSR). Mashinostroenie, no. 8. 1970, p. lifting surface to the downwash includes an integral difficult to 116-122. In Russian. compute with the usual numerical integration processes, and most Results of an experimental study of rotating stall in axial-flow authors faced with this problem calculate this kernel neglecting a compressor stages with different types of profiling along the blade logarithmic singularity. A method is proposed which, while re- height and with different calculated regimes of flow past a profile in maining reasonably fast, respects this singularity. ( AUt h o r ) the cascade. It is found that, in spite of the different safety margins with respect to boundary layer separation in the cascades of the different stages, their boundaries of stable operation are almost the same. It is shown that profiling taking into account end effects has a A71-11022 # Computation of aircraft wing and turbo- stabilizing influence and leads to a smoother transition to the machine or helicopter blade airfoils for the exact compressibility law rotating stall regime. The flow in rotating stall zones is shown to be (Calcul de profils d'ailes d'avions, de pales d'helicopteres ou d'aubes of threedimensional nature, It is shown that this threedimensional de turbomachines pour la loi de compressibilite exacte). Robert Structure can be detected with the aid of straight and L-shaped Legendre. La Recherche Aerospatiale, Sept.-Oct. 1970, p. 269. In tensoanemometer probes. A.B.K. French. Attempt to remove a certain limitation on a method of calculating a reversible transonic flow proposed by Bevierre and Bados (19701. The method proposed by Bevierre and Bados suffers A71-11167 Radiation from a dipole near a conducting from the fact that it is difficult to perform the calculation of the cylinder of finite length. Julius Goldhirsch, Dennis L. Knepp. and correction functions with the required accuracy. As a result, these Richard J. Doviak (Pennsylvania, University, Philadelphia, Pa.). IEEE authors limited their method to the calculation of profiles such that Transactions on Electromagnetic Compatibility, vol. EMC-12, Aug. no correction was necessary. An attempt is therefore made by the 1970, p. 96-105. 10 refs. Contract No. DA-28-043-AMC-02411. author to substitute for the finitedifference procedure proposed by Antennas radiating in free space or above a reflecting plane Bevierre and Bados a classical Fredholm procedure which lends itself produce radiation patterns which are in general predictable. When to the solution of the Dirichlet problem within a given contour. these same antennas are mounted on bodies such as aircraft, A.B.K. submarines, or satellites, secondary currents may be induced on the fuselages and nearly conducting members. These secondary currents often result in unpredictable radiation in the forms of newly A71-11024 # Experimental determination of pressure fluc- introduced polarizations or unwanted lobe structures which together tuations on stationary blades of a high power axial-flow compressor may manifest themselves in the form of radio-frequency interference.

12 A71 -11263

As a model of the fuselage of either of the aforementioned projectile, a flat delta wing with supersonic leading edges, and thin conducting bodies, a cylinder of finite length is considered and the wedges with or without yaw. V.Z. radiation fields of a radial dipole in the immediate vicinity of such a cylinder are determined by a theoretical-numerical technique. A cross-polarized field due to axial currents induced along the cylinder A71-11248 # The promise of the supersonics. John M. is found to represent a predominant feature of the radiation Swihart (Boeing Co.. Supersonic Transport Div., Seattle, Wash.). characteristics of the dipole-cylinder configuration. (Author) American Institute of Aeronautics and Astronautics, Annual Meeting and Technical Display. 7th. Houston, Tex., Oct. 19-22, 1970, Paper 701217. 8 p. Members, 51.50; nonmembers. $2.00. Discussion of the current status of the U.S. SST program as it A71-11178 # SST environmental effects - Some conridera- relates to airline operation in the late 19705 and early 19805. The tions. Gerald M. Daniels (Avco Everett Research Laboratory, Everett, initial production configuration, performance, economics, and Man.). Astronautics and Aeronautics, vol. 8, Nov. 1970. p. 22-25. operations are presented and compared with contemporary 80.32 refs. subsonics. A review of the payloadlrange growth of subsonic jet Discussion of the modification of the radiation balance of the transports is presented as groundwork for the prediction of payload/ earth produced by water vapor, carbon dioxide, carbon monoxide, range growth for the SST's. The economic potential.of both subsonic nitric oxide, and dust which would be deposited by a fleet of 400 to and supersonic transportation is reviewed. highlighting the com- 500 supersonic transports (SST) in the altitude region from 16 to 22 plementary nature of supersonic aircraft in providing improved km. Stratospheric air motions are examined and stratospheric- passenger service in the years to come, particularly in the area of water-vapor mixing ratios are considered. The determination of the long-haul intercontinental passenger transportation. M.V.E. temperature increase at the earth's surface is discussed. Estimates obtained indicate that routine SST commercial operation can increase the water-vapor content of the lower stratosphere by 60% and the surface temperature of earth by 0.6 C in a latitude band from 45 to 60 deg N. The scheduling of SST flight paths to involve A71-11252 ECM manufacturing process to produce air- stratospheric regions where the residence time for the pollutants craft engine components. T. A. Welte (United Aircraft of Canada, deposited by the aircraft is short is considered. G.R. Ltd.. Montreal, Canada). Society of Manufacturing Engineers, Inter- national Engineering Conference and Tool Exposition, Detroit, Mich., Apr. 13-17. 1970, Paper MR 70206. 14 p. Members, $1.50; nonmembers, $2.00. Discussion of electrochemical machining (ECMI, a metal A71-11180 # On turbine engine development policy. removal process based on reversed platinq which invo!?ec rzpid retai Benjamin Pinkel and J. R. Nelson (RAND Corp., Santa Monica, Jiswiuiion by electrolysis. ECM has been developed and accepted as Calif.). Astronauticsand Aeronautirc YC!. e, Ns:.. 1970, p. 52-63. a production and manufacturing technique for a large variety of Discusion of methods for reducing the risk of mismatch aircraft engine components. Many weight reduction problems with between engine and airframe when the airplane enters the flight-test aircraft engines can be resolved by employing ECM, especially where phase. The Advanced Turbine Gas Generator program established by elaborate conventional contouring costs become excessive, as in the the Air Force is discussed. Categories of R and D activities and case of superalloy materials of low machinability ratings. Time sources of funding for R and D are considered. Programs for comparisons with conventional methods and description of various demonstrating competitive technologies for engine development, ECM tooling techniques are presented, and the evaluation criteria for called austere demonstrator programs are examined, and the ECM applications are discussed. A few specific ECM apdications establishment of prototype demonstrator programs designed to review& iic!~dz:,;bine dno compressor disks of a turboprop ensure that precise specifications are met is repcrted. G.R. engine, a low turbine rotor of a JT-15D jet engine, and an impeller for a turboprop engine. M.V.E.

A71-11181 Evolution of the jet engine. Edward S. Taylor. # A71-11253 Electrochemical machining promise and reali- Astronautics and Aeronautics, vol. Nov. 1970, p. 64-72. 8. sation. A. H. Meleka (Rolls-Royce, Ltd.. Derby, England). Society of Discussion of the evolution of the jet engine taking into Manufacturing Engineers, International Engineering Conference and consideration increases in size and efficiency made during the past 25 Tool Exposition. Detroit, Mich., Apr. 13- 17. 1970. Paper MR years. Continuous improvements of takeoff thrust per unit weight 70-193. 14 p. Members, 51.50; nonmembers, $2.00. for jet engines are considered and changes in combustion chamber Review of the experience gained to date in the application of design are discussed. Fans, high-pressure-ratio compressors. and high electrochemical machining to contouring operations, blade aerofoil turbine-inlet temperature are cited as the major contributors to machining, turning, drilling. grinding, and deburring. The basic improvement in efficiency. Efforts to control jet noise and reduce principles of electrochemical machining are discussed. Special at- emission of pollutants are discussed. G.R. tention is given to the use of this method for turbine blade drilling and contouring operations in large castings. It is concluded that the process and productivity of electrochemical machining can be considerably improved. Z.W. A71-11227 # A unified meory for linearized hock+nhodc interaction problems. Narendra La1 Arora. Delft, Technische Hoge- school, Technische Natuurkunde, Doctor in de Technische Weten- schappen Dissertation, 1969. 168 p. 9 refs. A71-11263 Polyimidehron reinforced plastic structures. Analysis of a nonuniform flow field produced by the interaction Lloyd E. Hackman (North American Rockwell Corp., El Segundo, of a plane shock wave of arbitrary strength and twodimensional thin Calif .). Society of Manufacturing Engineers, International Engineer- aerofoils, slender bodies of revolution, or threedimensional thin ing Conference and Tool Exposition, Detroit, Mich.. Apr. 13-17, wings moving at supersonic speed. The boundary value problem 1970, Paper EM 70-133. 19 p. Members, $1.50; nonmembers, $2.00. concerning the pressure produced by perturbation is solved by Discussion of the development of polyimide/boron reinforced applying a sequence of integral transforms. The flow density field structures, and description of their use in the fabrication of leading and the shock wave shape are obtained as a result. The more specific edge structure. A system of vacuum bag processing of these materials applications of the results of this study include a slender conical was developed to achieve the lowest cost potential. To protect the

13 A71 -11267

polyimide/boron structure from temperatures of 750 F and to nuclear powered cruise hypersonic transport aircraft. Hypersonic reduce the operating temperature to 500 F for long-term operation, a transports are considered a natural continuation of supersonic ceramic insulation system was developed. Z.W. transport development, and their payload carrying ability and range characteristics are believed to be attractive. It is also indicated that the use of current space shuttle designs in a point-to-point A71-11267 Recent developments in high velocity metal- transportation mode may be economically competitive with super- working. E. J. Breznyak (Macrodyne Chatillon Corp., Doylestown, sonic transports. It is further maintained that new nuclear propulsion Pa.). Society of Manufacturing Engineers, International Engineering techniques make nuclear engines capable of driving hypersonic Conference ana Too; Ea-peskik, Eet~;t,Mich., A.pr. 13- 17, 1970, transports and that nuclear transports powered by gaseous nuclear reactors should be inherently safer than nuclear subsonic aircraft. Paper MF 70-278. 17 p. 10 refs. Members, $1.50; nonmembers, V.Z. $2.00. Description of some of the more common parts, both symmetri- cal and nonsymmetrical, that nave beell piGdi;cCd usi!?~controlled energy flow forming equipment, recent progress in forging airfoil A71-11311 # Teiuvisad giephlc clis?!ay* for steep approach- configurations, and results of a development program for the to-landing research. Henry C. Elkins and Jack J. Hatfield (NASA, ausforging of bearing race blanks. Tooling lives for the various parts Langley Research Center, Hampton, Va.). Society for Information are given, and the more prominent features of successful tooling Di@ay. National Symposium on Information Display, 1 lth, New design for high velocity metalworking applications are outlined. It is York, N. Y., May 26-28, 1970, Paper. 3 p. shown that high velocity metalworking techniques are coming of age An integrated, graphic, situation display concept for low- and can be considered as useful production tools. Although high visibility, noise-abatement, steep approach-to-landingis presented. A velocity processing should not be considered a metalforming terminal area display research facility for studying this concept under panacea, ever further applications continue to be developed as more actual flight conditions is described. Symbols and graphic images are experience and knowledge are gained. Considerable interest has been generated in a television format by ground-based equipment and generated for scaling up present high velocity forming capabilities 4 transmitted to the aircraft for display. Initial flight results, including to 5 times. Designs have been completed for a 1,800,000 foot-pound kinescope recordings and radar plots, are presented. Continuing counterblow high velocity metalworking machine under Air Force efforts to improve the graphic display format are described. (Author) sponsorship, and these designs are presently being evaluated. M.V.E.

A71-11320 # Aviation fuels, lubrication materials, and A71-11277 # The age of composites. W. M. Powers (General special fluids (Aviatsionnye topliva, smazochnye materialy i Technologies Corp., Reston, Va.). SAMPE Quarterly, vol. 2, Oct. spetsial'nye zhidkosti) (2nd revised and enlarged edition). A. F. 1970, p. 9-15, Aksenov. Moscow, Izdatel'stvo Transport, 1970. 256 p. 12 refs. In Advanced composites are being used in a wide variety of Russian. aerospace prototype hardware. Although current filament prices are Aviation fuels, lubrication materials, and special fluids are high, projected reductions should provide the necessary cost effec- described in terms of fabrication, composition, operational character- tiveness for an ever increasing number of applications. Boron istics, and control procedures. The refining of petroleum fuels is filaments are already scheduled for two new production aircraft, and examined, and the fractional and chemical compositions are dis- graphite fiber composites will go into commercially manufactured cussed. Requirements posed for fuels are treated in terms of the sporting goods this year. (Author) important physicochemical properties, and engineering aspects of application are examined, including stability, filtration, pumping, corrosion, wear-inhibiting characteristics, mixibility, combustibility, A71-11281 # Development of advancecl composite struc- and deposit formation. Special characteristics and operational re- tures for aircraft. R. T. Beall, G. W. Burton, and W. V. Rich quirements are outlined for fuels used in jet and piston engines, (Lockheed-Georgia Co., Marietta, Ga.). SAMPE Quarterly, vol. 2, supersonic aircraft, and rockets. Fabrication, properties, and be- Oct. 1970, p. 41-45. havior of lubricants for aerospace applications are extensively The Lockheed-Georgia Research Laboratory has built two examined, together with similar aspects of hydraulic fluids, deicing liquids, and cleansing compounds. T.M. 35-square-foot relief crew compartment panels to demonstrate the cost-effectiveness of unique advanced-composite structures. The experimental panels have only 3/5 the weight and 1/2 the thickness of the aluminum structure presently being used. A single-stage layup using adhesive prepregged graphite fibers bonded to Nomex honey- A71-11322 # Antenna radomes of flight vehicles (Obtekateli comb core, guarded by fiberglass edge members and titanium antenn letatel'nykh apparatov). B. A. Prigoda and V. S. Kokun'ko. doublers, represents an unusual marriage of advanced materials. Moscow, Izdatel'stvo Mashinostroenie, 1970. 288 p. 8 refs. In Unusually simple tooling concepts and manufacturing techniques Russian. clearly demonstrate the adaptability of this technology to mass- Information dealing with the calculation, design, and fabrication produced aircraft systems. Detailed descriptions of the tests to which of antenna radomes for aircraft and missiles is presented in a the panel was subjected are included. (Author) systematic textbook form. Initial chapters are devoted to the passage of electromagnetic radiation through various dielectric media, and methods are described for fabricating radomes which will retain the A71-11302 # The hypersonic transport . The technology original properties of the dielectric material. Different types of and the potential. Maxwell W. Hunter, I1 and Dietrich W. Fellenz radomes are described in categories based on position, structure, and (Lockheed Missiles and Space Co., Sunnyvale, Calif.). American useful wavelengths. The operational factors acting on the radomes Institute of Aeronautics and Astronautics, Annual Meeting and are outlined for the purpose of illustrating the effects of aero Technical Display, 7th, Houston, Tex., Oct. 19-22, 1970, Paper dynamic forces, heating, and climatic phenomena. Fabrication 70-1218. 48 p. Members, $1.50; nonmembers, $2.00. techniques are examined for plastic reinforced glass, ceramics, and Evaluation of hypersonic 'conventional' and rocket transport other radome materials. Calculations of radome losses are explained, craft in terms of production technology and application potential. together with methods of compensating for the resulting angular The rocket guide range, propellant and airframe costs, and exhaust propagation errors. Quality control and reliability aspects of radome and noise pollution are discussed. Special attention is given to fabrication are also treated. T.M

14 A71 -11545

A71-11377 * History of NACAlNASA rotating-wing aircraft investigations. Work done by the Institute in the field of space research, 19151970. IV. Frederic 6. Gustafson (NASA, Langley aerodynamics is described. The findings of the Aeroelasticity Research Center, Hampton, Va.). VeniFlite, vol. 16, Nov. 1970, p. Division during the period from 1953 to 1969 are reviewed, and the 69.8 refs. development of the electronic computer equipment of the Institute Description of events and views concerning rotating-wing is asessed. The tasks completed by the Operation and New Test aircraft research during the 1955-1970 segment of the 19151970 Equipment Division during the period from 1945 to 1969 are period. It is considered that major attention by NACA and NASA on enumerated. A.B.K. nonrotor VTOL work had a deleterious effect on rotating wing research. On the favorable side, heavy use of the full-scale wind tunnel for rotor work began early in this period, and is continuing. The general view now seems to be that the horizons are unlimited A71-11468 Influence of retarded time on jet noise. Ian S. both for rotating-wing aircraft and for other vertical-lift aircraft F. Jones (Sydney, University, Sydney, Australia). Physics of Fluids, types. Rotor flow studies, rotor-blade pressure distribution, and vol. 13, Nov. 1970, p. 26292633. 7 refs. Research supported the airfoil behavior in rotors are discusred, as well as methods for Boeing Co. performance improiement. F.R.L. The acoustic radiation from a region of turbulence can be expressed in terms of the fluctuating turbulent stresses and for estimates of the noise, it is common to neglect the change in retarded time between different regions of correlated turbulence. From A71-11392 # The track-while-ccan technique for sea& measurements of the wavenumber frequency spectrum of one of the radar. I - Acquisition and processing of aircraft radar data. Takashi turbulent stresses in a jet, the influence of retarded time on the lida, Moriyuki Mizumachi, and Minoru Higashiguchi. Tokyo, Univer- amustic radiation is shown to be small for sound radiated at right sify, Institute of Space and Aeronautical Science, Bulletin. vol. 6. angles to the jet axis but to be significant at small angles to the jet Sept. 1970, p. 652-688. In Japanese, with abstract in English. axis. This provides a partial explanation of the success of Lighthill's Discussion of a design philosophy and basic experiments for U super 8 law even when convection is important. (Author) processing radar data for digital tracking computation. Aircraft search radar data, obtained scan by scan, are recorded on perforated tapes through a radar video digitizer (RVD) and buffer memory devices. The track-while-scantechnique is investigated b an off-line A71-11539 Beryllium - An aircraft and spacecraft struc- computer using these recorded data. M.M. tural material (Beryllium - Ein Werkstoff fiir die Luft- und Raumfahrt). F. Gerhard (Messerschmitt-BolkoBlohm GmbH, Munich, West Germany). Luftfahrrrechnik Raumfahmechnik, vol. 16, Os. ?370,p. 243-247. i3 refs. In German. A71-11393 # The tack-vhiiescan technique for rearch Brief review of the mining and metallurgy of beryllium, and radar. II - The theoretical analysis of aircraft tracking by the discussion of its mechanical and physical properties, corrosion applion of Kalman fifter. Takashi lida, Moriyuki Mizumachi, and behavior, toxicity, fabrication processes and applications. Beryllium Minoru Higashiguchi. Tokyo, Univwsity, Institute of Space and metal is shown to possess a combination of special properties such as Aeronautical Science, Bulletin, vol. 6. Sept. 1970. p. 684700. In cannot be found or duplicated in any other material. It is uniquely Japanese, with abstract in English. fit for applications in parts requiring high stiffness combined with Description of a theoretical model for the analysis of the great buckling strength and low weight. The relatively high price of track-while-scan technique for search radar. The Kalman filter is such parts, caused by the complex and costly processing of beryllium introduced on condition that the root-meamquare tracking error be manufactured products. Is offset by the only mus achievable minimized, and assuming the input signa! rc be stochastic. The model combination of end-product properties. M.V.E. IS analyzed by computing gain functions on different types of input signals. It is concluded that the Kalman filter theory can be applied to the linear tracking computation. M.M. A71 -11540 Evaluation of some new airuaft structure materials by methods of fracture mechanics (Bewertung neuer Flugzeugbauwerkstoffe mit den Methodem der BNchmeChanik). H. A71-11395 # Mechanical degradation of aeroplane materids Leis (Messenchmitt-Bolkow-Blohm GmbH, Ottobrunn, West by their fatiye and its detection. 1. Kozo Kawata, Shozo Hashimoto, Germany) and W. Schutz (Industrieanlagen-BetriebsgesellschaftmbH, and Akira Hondo. Tokyo, Univwsify, Institute of Space and Ottobrunn, West Germany). Luftfahrtiechnik Raumfahmhnik, Aeronautical Science, Bulletin, vol. 6, Sept. 1970. p. 716-728. In vol. 16, Oct. 1970, p. 247-251. 21 refs. In German. Japanese, with abstract in English. Discussion of the significance and implications of certain fatigue Investigation of possible changes in the mechanical properties of cracks and structural failures due to cracks that have recently the static stress of specimens previously repeatedly loaded at variws occurred in several military and civilian aircraft. The inferences of stress levels. An appreciable decrease in the breaking strain at these accidents are discussed in detail. Crack propagation, residual different stress levels and a slight decrease in the breaking stress at static strength, and fracture toughness have been determined for two specific stress levels are fwnd, denoting that embrittlement bdns highstrength aluminum alloys of the AI-Zn-MpCu type. Both alloys before the appearance of macroscopic defects. M.M. showed an excellent combination of mechanical properties, quite competitive with that of titanium alloys 50 important for modern fail-safe design. Crack propagation data derived with the aid of Forman's formula proved to be in good agreement with ex- A71-11406 # The attingen Aerodynamic Test institute perimentally obtained results. M.V.E. from 1945 to 1969 (Die Aerodynamisdw Vmuchsautslt Giittingen von 1945 bis 1969). Gottingen, Aerodynamische Venuchsanstalt, 1969. 144 p. 592 refs. In German. Summary of the accomplishments of the various divisions of the A71-11565 Synthesis of future hi+ lift systwm. Richard Gottingen Aerodynamic Test Institute during the period trom 1945 Sdwrrer (LockheedCalifornia Co., Burbank, Calif.). Society of to 1969. The development, organizational changes, and major Autornative Engineers, National Aeronautic and Space EngirWering research findings of the Aerodynamic and Gasdynamic Divisions are and Manufacturing Meeting. Los Angeles, Calif.. Oct. 5-9, 1970, outlined, emphasizing, in particular, the results of wind tunnel Paper 7oQB11. 11 p. 29 refs. Members, $1.00; nonmembers, $1.50.

15 A71-11546

Discussion of possible high lift systems for fourengine turbofan, of some of the nozzle parameters is discussed. A semiempirical M = 0.8, commercial and military, STOL aircraft capable of method is presented for calculating the boundary-layer correction. operation from 1800-foot fields. Both first- and secondgeneration Calculated values agree within about 15% with experimental valucs 1 vehicle concepts are considered. Propulsion, aerodynamics, and obtained in 50-in. diameter water-cooled nozzles over a Mach numb,.' design trends of these aircraft are examined. The propulsion trends range of 6 to 12. (Author) are projected as the effect of STOL requirements on engine weight, shape, and thrust deflection efficiency. Aeropropulsion, low speed interference effects are discussed briefly in relation to acceptable engine locations. Aerodynamic trends are limited to those regarding A71-11580 # An approximate method for predicting achievement of theoretical limit circulation lift values by use of pressure distributions on blunt bodies at angle of attack. Robert L. leading and trailing edge flaps with blowing boundary iayer coniio!. S:a!!ings, Ir. end James F. Campbell (NASA. Langley Research The objective of future flap designs is not so much to indicate how Center, Hampton. Va.). (American Institute of Aeronautics ana to get high lift but to find plausible means for minimizing the Astmnautics, Aerospace Sciences Meeting, 8rh, New York, N. Y.. Jan. arnvuiii of b!=:*:'iy per iinit circulation lift. The discussion of design 19-21, 1970, Paper 70-208.JJournal of Spacecraft and Rockets, vol. trends is oriented toward bringing the projected aerodynamic ana 7, Nuv. !8X,p. !305-!3!C!. !E rpfc propulsion trends together into a possible family of aircraft. Three An approximate method, based on Love's sinZ deficiency particular members of the family are then rationalized as being most method for zero angle of attack, is described; and results, both in the representative of future vehicles and one of these is illustrated. O.H. form of pressure distributions and force and moment coefficients, are critically assessed by comparison with experimental measure- ments for two families of blunt bodies. These families consist of: (1) bodies of revolution having variable nose and shoulder radii varying A71-11546 Electric thrust control system for supersonic from a flat disk to a hemisphere, and (2) large angle cones having transport power plant. Richard F. Gorman and Donald L. Morrow apex angles ranging from 120 to 180 deg. Hand calculations for both (Boeing Co., Supersonic Transport Div., Renton, Wash.). Society of families have been made for angles of attack up to 15 deg and for a Automotive Engineers, National Aeronautic and Space Engineering free-stream Mach number of 4.63. Good agreement is generally and Manufacturing Meeting, Los Angeles, Calif., Oct. 5-9, 1970, shown between experiment and calculated values through the range Paper 700879. 9 p. Members, $1.OO; nonmembers, $1.50. of variables investigated. Sonic-point and stagnation-point locations The design of the propulsion control system for the supersonic are required inputs of the approximate method. An iteration scheme transport (SST) is a culmination of three years of design trade is presented which adequately predicts the sonic-point locations, studies. An analysis was made of the throttle systems of the Boeing however, it was necessary to use experimental stagnation-point 747, XB-70, Concorde, and other airplanes with a view toward the locations in the approximate method. (Author) applicability of these systems for use on the SST. The major considerations that led to selection of a redundant channel electro- hydraulic propulsion control system are: safety, operational- reliability, performance, and weight. Presented here is a description of the SST propulsion control system which is composed of two A71-11624 ,$ An ultrasonic altitude-velocity sensor for air- subsystems, the thrust control subsystem and the mode control planes in the vicinity of the ground. I. Hiroshi Maeda, Yoshikuni su bsvstem. (Author) Umeda, and Norio Arihara (Kyoto University, Kyoto, Japan). Kyoto University, Faculty of Engineering, Memoirs, vol. 32, Apr. 1970, p. 249-259. Discussion of the properties and merits of an ultrasonic sensor for detecting from the ground the altitude and vertical velocity of A71-11550 Peen forming. Davis L. Baughman (Carbo- low flying aircraft. The results of preliminary experiments and rundum Hagerstown, Md.). vol. 42, Nov. 12, Co., Machine Design, simulation studies indicate that an ultrasonic sensor should make it 1970, p. 156-160. possible to detect the accurate altitude of a low flying aircraft, and Discussion of the advantages and the technology of peen that this instrument would be much simpler than a radar altimeter. forming. It is pointed out that peen forming is a potentially cheaper By differentiating the altitude signal with respect to time, it should way to form sheet and plate where the required part is large and be possible to detect the vertical velocity of the aircraft. This where only gentle curvatures are needed. Moreover, peen forming instrument could be used as a sensor for the automatic control easily produces compound curvature, which is often quite difficult to systems of aircraft. An inherent weakness of this instrument is, produce with press forming, The main attraction of peen forming is however, the time lag due to ultrasonic wave propagation. Funda- that no dies or presses are required. Some of the considerations mental data of potential usefulness for the design of an ultrasonic involved in peening complex shapes are illustrated by the techniques altimeter are presented. M.V.E. used to produce a dihedral break in an airplane wing skin. G.R.

A71-11578 P Aerodynamic design of axisymmetric hyper- sonic wind-tunnel nozzles. James C. Sivells (ARO, Inc., Arnold Air A71-11627 Solid-state switching for aircraft electric Force Station, Tenn.). (American Institute of Aeronautics and systems. Lee D. Dickey and Clyde M. Jones (LTV Aerospace Corp., Astronautics, Aerodynamic Testing Conference, 4rh, Cincinnati, Dallas, Tex.). IEEE Spectrum, vol. 7, Nov. 1970, p. 73-79. Ohio, Apr. 28-30, 1969, Paper 69-337.) Journal of Spacecraft and Discussion of an application of semiconductor technology to the Rockets, vol. 7,Nov. 1970, P. 1292-1299. 29 refs, management and control of aircraft electric systems giving particular Description of a unified approach to nozzle design in which an attention to problems of separating power switching from signal inviscid contour is first drterminrd and then correctrd to account switching and of switching power through a minimum number of for the growth of a turbulent boundary layer along the contour. The inviscid contour is obtained by the axisymmrtric method of rharac- semiconductor devices. A conventional electric system in an A-7 teristics from a prescribed distribution of velority along thc nozzle aircraft is compared with an electric system on a solid state basis and axis. The velocity distribution matchrs throretical transonic condi- advantages in weight, volume, reliability, and maintenance for the tions at the throat, conical-source flow conditions through an inter- solid-state system are shown. An advanced control logic, power mediate region, and design flow conditions at the nozzlr exit. Thr controllers, a dc-load power controller, an ac-load power controller, a second derivative of the axial velocity is continuous throughout and bus-switching power controller, and aspects of package design are is zero at the sonic point and at the exit point. The intcrdcprndcncr discussed. G.R.

16 A71-11660

A71-11628 Exploiting AR. R. A. Cole. Shell Aviation aircraft are shown to be in excellent agreement with the widely News, no. 387.1970. p. 10-15. accepted 'one dominant' model proposed by Swerling. (Author) Consideration of the direct relationship between the aspect ratio of a civil aircraft and its commercial viability. The requirement for as generous an aspect ratio as possible stems from the need for minimum induced drag at any wing loading. Comment is made on the ultralow aspect ratio design approach, as appljed to the Concorde and the Canberra. When supersonic transports become commonplace A71-1 1658 LAMS - A technology to control aircraft it is considered to be doubtful if their maximum aspect ratios will be structural modes; Institute of Electrical and Electronics Engineers, much above four. Within the range of subsonic transports, the aspect Case Studies in System Control, Georgia Institute of Technology, Atlanta, Ga., June 1970, Proceedings. New York. Institute of ratio values will probably rise slightly. F.R.L. 23. Electrical and Electronics Engineers, Inc.. 1970. 126 p.

Contents: A71-11641 # Determination of wheel trajectories. Ezra Introduction and summary (LAMS). R. P. Johannes (USAF, Hauer (Technion . Israel Institute of Technology, Haifa, Israel). Flight Dynamics Laboratories, Wright-Patterson AFB, Ohio), p. 2-12. ASCE, Transportation Engineering Journal, vol. 96, Nov. 1970, p. 463-470. 5 refs. LAMS fllght control system analysis and design. G. 0. Analytical determination of the main gear trajectory when the Thompson (Boeing Co.. Wichita, Kan.), p. 1341 front wheel of a taxiing aircraft follows straight or circular paths or any combination thereof. The differential equation describing the LHMS test vehicle modification and system tests. G. J. Kass motion of a vehicle with a steerable front wheel is presented. This (Boeing Co.,Wichita, Kan.), p. 42-96. equation can be used to determine numerically the position of the LAMS flight demonstration. J. B. Dempster (Boeing Co., vehicle when the front wheels follow any curve of known curvature. Wichita, Kan.), p. 97-125. Analytical solutions of the differential equation for a vehicle Conclusions. R. P. Johannes (USAF, Flight Dynamics Labora- negotiating circular curves and straight lines are given. The resulting tories. Wright-Patterson AFB, Ohio), p. 126. formulas are not so simple as to hold an advantage over the use of graphs and tables. They may be of practical importance when programmed for the computer, when aircraft position has to be determined at isolated locations, when tables are either unavailable or inadequate in their range of accuracy. Some results for transition A71-11659 # Introduction and summary (LAMS). R. P curves are also given. M.V.E. Johannes IUSAF, F!igh? Cynsmics Laboratories. Wright-Patterson AFB, Ohio). In: LAMS - A technology to control aircraft structural modes; Institute of Electrical and Electronics Engineers, Case Studies in System Control, Georgia Institute of Technology, Atlanta, Ga.. A71-11642 # Environmental aspects of airport system June 23, 1970, Proceedings. Yew York, Institute planning. John F. Brown (Landrum and Brown, Cincinnati, Ohio). of Electrical and Electronics Engineers, Inc., 1970, p. 2-12. (American Society of Civil Engineers, Transportation Engineering Discussion of the present stage of a R & D program initiated in Conference, Chicago, Ill.,Ocr. 13-17, 1969.J ASCE, Transportation 1966 at the Air Force Flight Dynamics Laboratory to demonstrate Engineeriw Journal, vol. 96, Nov. 1970, p. 543559. 5 refs. the capability of an advanced flight control system to alleviate gust Discussion of some fundamental criteria pertaining to judgments loads and to control structural modes on G krge fiexiole aircraft as to the alternatives involved in the planning of airport systems that using conventional aerodynamic control surfaces. The major are to serve B c=~-miin;ty or reglon. It IS suggested that the proper elements of this program are described as (1) establishment of role of the professional airport planner should be that of measuring performance criteria applicable at all phases of the program, (2) these criteria concretely and objectively so that they may be analysis of the 8-52 to select the control techniques to be developed, properly weighted in considering a final solution. In summary, these (3) demonstration of the applicability of analytical techniques by criteria are: (1) local air travel market characteristics and distribu- applying them to the C-5A. (4) production of an operable LAMS- tion; (2) effect of airport accessibility on the realization of the air FCS, (5) conversion of an existing 6-52 to an appropriate test bed to travel potential; (3) air space utilization and control; and (4) present demonstrate the LAMS-FCS, and (6) demonstration of the perfor- and planned land use. With meaningful objective measures of these mance of the LAMS-FCS during flight through a turbulence. The environmental aspects, the planner, the community, and the civil results of various tests conducted within this program are evaluated, engineers can make better and more meaningful judgments in regard noting the positive turbulence test results for fatigue damage rates, to the proper location of airports and the compromising of these maximum expected stresses, and rms accelerations. V.Z. locations for other purposes. M.V.E.

A71-11660 # LAMS flight control system analysis and A71-11643 The estimation of loss of echoing area with design. G. 0. Thompson (Boeing Co., Wichita, Kan.). In: LAMS - A wry high resolution radars. D. C. Cooper (Birmingham, University, technology to control aircraft structural modes; Institute of Elec- Birmingham, England). (Aerospace, Maritime, and Military Systems trical and Electronics Engineers, Case Studies in System Control, Grow. Symposium on High Resolution Radar Systems, London, Georgia Institute of Technology, Atlanta, Ga., June 23, 1970, England, Apr. 8, 1370.1 Radio and Electronic Engineer, vol. 40, Oct. Proceedings New York, Institute of Electrical 1970, p. 159-164.5 refs. and Electronics Engineers, Inc., 1970, p. 1341. The paper considers the use of recently published experimental Analysis of the design features of LAMS flight control systems data in estimating the manner in which the echoing area of an aimed at the reduction of turbulence-induced fatigue damage rates in aircraft is reduced when the range resolution cell of the observing the 6-52 and C-5A aircraft. The 6-52 and C-5A mathematical models radar is smaller than the aircraft dimensions. A simple mathematical used in structural performance and stability analysis are discussed. model of the echoing process is postulated and the experimental Problem identification, system synthesis, and performance evaluation results are used in selecting the model parameters. The model is then are considered as basic elements of the analytical technique used in used to predict the behaviour of the echoing area, and in addition, the study. Block diagrams are given for 6-52 and C-5A LAMS flight the echoing properties for a resolution cell which embraces the whole control systems. V.Z.

17 A71 -11661

A71-11661 # LAMS test vehicle modification and system A71-11686 # Aerodynamic problems of reentry (The tests. G. J. Kass (8oeing Co., Wichita, Kan.). In: LAMS - A Daniel and Florence Guggenheim Memorial Lecture). Carlo Ferrari technology to control aircraft structural modes; Institute of Elec- (Torino, Politecnico, Turin, Italy). International Council of the trical and Electronics Engineers, Case Studies in System Control, Aeronautical Sciences, Congress, 7th, Rome, Italy, Sept. 14-18, Georgia Institute of Technology, Atlanta, Ga., June 23, 1970, 1970, Paper /CAS 7001. 20 p. 80 refs. Proceedings. New York. Institute of Electrical Review of the following aerodynamic problems of spacecraft and Electronics Engineers, Inc.. 1970, p. 42-96. reentry: (1) lifting bodies at hypersonic speeds and high altitude; (2) Discussion of the 6-52 test vehicle modification and in- shock wave and flow field development in hypersonic reentry; (3) srrllmentation used in the flight demonstration phase of the LAMS aerodynamic heat transfer; (4) radiative contribution to the mass and vehicle and system test program. The modified kiii6;C$ cf ?!?eB-52 energy transfer, equation of the radiative energy transfer in non- test vehicle include structural changes in the aft fuselage and vertical equilibrium, bouridarq conditinnr of the eauations of the photon's tail section, a gust probe installed in the vehicle nose, new hydraulic gas; and (5) problems connected with the ionization in reentry, ana activcrors ?e the elevators, ailerons and rudder, a new servo valve for reentry blackout suppression. M.M. spoiler panels, a fly-by-wire pilot station, a copiior srariori ionve;:ed into a safety monitor station, and a bomb-nav station modified to a flight engineer station. System and component evaluations per- A71-1 1 698 A conflict prediction algorithm for use in formed within the framework of this program are reviewed. V.Z. procedural domestic airspace. F. N. D. Gilbert and P. L. Battrum. Journal of Air Traffic Control, vol. 12, Nov. 1970, p. 18-21. Discussion of a six-step conflict prediction algorithm based on the principle that an aircraft can only be assigned airspace if it is free A71-11662 # LAMS flight demonstration. J. B. Dempster of conflict with respect to other aircraft, and that each aircraft (Boeing Co., Wichita, Kan.). In: LAMS - A technology to control entering the system will be paired and checked sequentially for aircraft structural modes; Institute of Electrical and Electronics conflict with all other aircraft in the control area. The first two steps, Engineers, Case Studies in System Control, Georgia Institute of Technology, Atlanta, Ga., June 23, 1970, Proceedings. a gross time sort and a gross level sort. are conducted on the basis of New York, Institute of Electrical and Electronics the overall flight plan. The remaining steps are conducted on the Engineers, Inc., 1970, p. 97-125. basis of comparison of route segments. The technique proposed is to Discussion of the results of the flight demonstration phase of conduct simple gross sorts first, in order to identify potential conflict the LAMS program, designed to validate the analytical techniques situations in the shortest possible time. Fine sorts and detailed used in the system design by comparing test data with analytical analyses, which take longer but are much fewer in number, are conducted after to minimize the response time of the algorithm. V.P. performance predictions. It is shown that the LAMS test vehicle with powered controls with or without the Baseline SAS has an adequate flutter boundary. Repeatable sinewave and step function transients were introduced into the control surfaces at selected frequencies and amplitudes to verify the functional operation of the control systems. A71-1 1699 Procedural changes for a better ATC system. Transient testing data were used to define open and closed loop John P. Woods. (Radio Technical Commission for Aeronautics, responses of the aircraft and its systems. The control surface Annual Assembly Meeting, Washington, D.C., Nov. 20, 21, 1969.1 authority and effectiveness data obtained by tests agreed well with Journal ofAir Traffic Control, vol. 12, Nov. 1970, p. 22-25. the predicted analytical values. The LAMS-FCS provided reductions Discussion of possible means of improving the FAA's 'positive in the stress and fatigue damage rates equal to or greater than the control' ATC procedure, which is currently pressed beyond capacity. ones predicted by the analysis. V.Z. Considerations (based on an approach in which aviation safety is stated in terms of probabilities rather than in terms of absolutes) concerning steps that would unload the control system are outlined. A separate system, directing traffic into procedurally ordered streams, is advocated. V.P. A71-1 1676 Situation of aerospace industry in the European Community (La situation de I'industrie aerospatiale de la Communautb europbenne). Louis Gravigny and Daniele Verdiani. (€urospectra, vol. 9, no. 2, 1970.) Schweizerische Technische A71-11700 /i Technological factors in short haul air trans- Zeitschrift, vol. 67, Nov. 5, 1970, p. 870-874. In French. portation. George C. Kenyon and Hubert M. Drake (NASA, Ames Analysis of the achievements and future tasks of the European Research Center, Moffett Field, Calif.). American Institute of Economic Community in the development of aerospace projects. The Aeronautics and Astronautics, Annual Meeting and Technical Dis- role played by the aerospace industry in the economy is briefly play, 7th, Houston, Tex., Oct. 19-22, 1970, Paper 70-1287. 7 p. 15 discussed. The organizational problems of the aerospace industry are refs. Members, $1.50; nonmembers, $2.00. examined, and the current projects are discussed. The prospects for Identification of some of the important technological factors the years 1970 to 1980 are examined. Z.W. affecting short haul transportation from the standpoints of the operator, the passenger, and the community. The aircraft concepts of CTOL. VTOL, STOL, and light aircraft are considered for five missions. A hypothetical commute mission example shows the A71-11682 RB.211 - Transatlantic bridgehead. Peter dominance of indirect over direct costs for the short range mission. Middleton. Flight International, vol. 98, Nov. 5, 1970, p. 708-714. Technology is considered from three points of view: the operator, 720. who needs competitive economics, the passenger who wants attrac- Description of the Rolls-Royce RB.21 1 engine, which will tive service, and the community, which demands low impact on the represent 60% of the British civil powerplant business during its 15 environment, particularly for new transportation systems. The years' production lifetime. Because of its use in the Lockheed elements that provide competitive economics, attractive service, and TriStar, the engine should represent a massive export potential for low environmental impact are presented, along with the accom- rhe U.K. The engine is also expected to find application in the BAC panying technological factors. Indirect operating costs are shown to Three-Eleven, and possibly the A.3008 Airbus. Emphasis has been on dominate the economics for these short range missions. The combustion development, and lightweight fans are undergoing a distribution of airports within short distances from metropolitan critical analysis. The three:shaft layout results in good handling and centers is discussed, and noise comparisons are made for these low vibration levels. The engine was designed from the outset with aircraft concepts with background noise. Projections are made as to date of availability of new aircraft for these missions. M.M. noise reduction in mind. F.R.L.

18 A71-11787

A71-1177'7 Summer Computer Simulation Conference, A71-11783 # The use of digital simulation for the nonlinear Denver, Colo., June 10-12.1970, Proceedings. Volume 1. Conference analysis of an integrated actuator package. H. E. Harschburger sponsored by the Association for Computing Machinery, S.H.A.R.E., (McDonnell Douglas Corp., St. Louis, Mo.). In: Summer Computer and the Simulation Councils. New York, Association for Computing Simulation Conference, Denver, Colo., June 10-12, 1970. Proceed- Machinery, 1970.749 p. $1 5. ings. Volume 1. Conference sponsored by the Association for Computing Machinery, S.H.A.R.E., and the Simula- Contents: tion Councils. New York. Association for Computing Machinery, Symbolic partial differentiation . A simulation tool. G. Fischer 1970, p. 393400. and L. Patmore (ESL, Inc., Sunnyvale, Calif.), p. 12-20. Description of the use of digital simulation in studying the nonlinear characteristics of a prototype integrated actuator package. DARE II - Fast on-line digital simulation on a small computer. A complete dynamic mathematical model is developed which T. A. Liebert (Arizona, University, Tucson, Ariz.), p. 21-28. 5 refs. includes the surface inertia, the mass of the package, the structural and oil spring rates, and the aerodynamic force. The nonlinear DIHYSYS. ..A hybrid systems simulator. J. L&n. C. 0. portion of the simulation includes the soft cutoff hydraulic pump Alford. and J. L. -Hamrnond, Jr. (Georgia Institute of Technology, characteristics, position and flow limits. linkage freeplay, the stalling Atlanta, Ga.), p. 42-48. 10 refs. of the actuator by the aerodynamic force, and changes in the flow A standard structural description for nonlinear differential gain due to changes in pressure drop across the valve. Corroboration equations. R. D. Gustafson, p. 49-55. of simulation accuracy was obtained through testing of an actual Modeling the performance of a satellite system. E. Gordon and package on a test stand. The presented mathematical model and T. P. Jackson (Aerojet-General Corp., Azusa. Calif.), p. 113-120. 6 simulation should be useful in the analysis of any future integrated refs. actuator package using soft cutoff pumps. M.V.E. The use of digital simulation for the nonlinear analysis of an integrated actuator package. H. E. Harschburger (McDonnell Douglas Corp., St. Louis, Mo.), p. 393400. Technique for fast, in-depth use of computer simulation data in tactical missile flight test planning. J. K. Wright, Jr. and W. H. Gilbert, Jr. (Martin Marietta Corp.. Orlando, Fla.). p. 433-47Q A71-11786 P A real-time 6 degree of freedom aircraft simulation with SL-1. Sanford Schram and Jim Boren (Xerox Data Tactical missile control system performance analysis using Systems. El Segundo, Calif.). In: Summer Computer Simulation hybrid computer simulation methods. H. S. Steinmetz and W. H. Conference, Denver. Colo., June 10-12, 1970, Proceedings. Volume Gilbert, Jr. (Martin Marietta Corp., Orlando, Fla.), p. 450461.6 refs. 1. Conference sponsored by the Association for Computing Machinery, S.H.P..R.E., wid me Simulation Councils. A real-time 6 degree of freedom aircraft cimu!a?ic:: ~ithSi-i . S. New York, Association for Computing Machinery, 1970, p. 471480. 5khiiifi-i and J. Boren (Xerox Data Systems. El Segundo, Calif.), p. Description of a recent successful implementation of a sig- 471480. nificant aircraft simulation study. Its importance lies in that it shows The use of C.S.M.P. digital simulation language in manual flight how SL-1, a CSSL-based language, can be applied to a large Scale control analyses. M. S. Eden (Lockheed-California Co., Burbank. problem in real time. The problem used in the demonstration was to Calif.), p. 481493. : simulate an .aircraft and its control system in real time . i.e., to The use of TRANSIM in the simulation of POGO in the Saturn provide 8 seconds of flight within 8 seconds of computer run time. V second stage. I. Y. Bar-Utzhack (Bellcomrn. .lnc., Washington, The simulation had previously been implemented and the results D.C.), P. 494-503.9 refs. were known, therefore the accuracv of the SL ! sim.":a:ioo and the A general sixdegree-of-freedom simulation usina CSSC II C. E. &curacy ot the techniques used could be evaluated. To effect the Brc?wv !Dr~n,:a-~rn~nySciences Corp.. Los Angeles. Calif.), p. execution in real time, the problem equations were divided into three 504-509. groups: (1) the translational equations of motion; (2) the rotational Hybrid computer structural response simulation. L. M. Landrv. equations of motion; and (3) the control system. Different integra- Jr. (Bell Helicopter Co., Fort Worth, Tex.), p: 51P-515. tion rates and algorithms were used for each group. After experimen- tation with various step sizes and algorithms at run time, the goals of Apollo Command and Service Module visual display simulation. accuracy and computation efficiency were achieved. M.V.E. D. Hernandez (North American Rockwell Corp., Downey, Calif.). p. 524-540. Apollo Command and Service Module simulation program - Block II. A. J. Maureri (North American Rockwell Corp., Downey, Calif.).p. 541-551. N-body real time simulation of the Apoilo Command and A71-11787 # The use of C.S.M.P. digital simulation language Service Module's G&C systems and mission. T. L. Mason (North in manual fli&t control analyses. M. S. Eden (LockheedCalifornia American Rockwell Corp., Downey. Calif.), p. 552-564. 8 refs. Co., Burbank, Calif.). In: Summer Computer Simulation Conference, Denver, Colo., June 10.12, 1970, Proceedings. Volume 1. Considerations for the hybrid computation of trajectories for Conference sponsored by the Association for Com- missiles and aircraft. A. I. Rubin (Electronic Associates, Inc.. puting Machinery, S.H.A.R.E.. and the Simulation Councils. New Princeton, N.J.), p. 602-609. York, Association for Computing Machinery, 1970, p. 481493. Computer simulation of the Apolls electrical power system on Discussion of closed loop piloted simulations in low speed Skylab Program missions. L. Ule (North American Rockwell Corp., longitudinal flight maneuvers. A continuous mathematical pilot Downey, Calif.), p. 610-629. 5 refs. model is used to close the aircraft pitch attitude loop, which A digital simulation of radar systems and the environment. G. D. responds to simple rational commands appropriate to the particular Halushynsky (Vitro Laboratories, Silver Spring, Md.) and D. H. Cook maneuver. The pilot model has some roots in manual control theory, (TRW Systems Group, Washington, D.C.). p. 641-649. which indicates the likely crossover characteristics fclosed loop frequency and stability criteria) which would obtain in the piloted An all digital hybrid simulation. J. Sheehan and J. De Veber situation. The development of a speed schedule and takeoff (Raytheon Co., Bedford, Mass.), p. 650-656. 9 refs. technique consistent with the intricacies of Federal Aviation Re- Hybrid techniques in the development of a missile simulation. J. quirements (FAR) and ana\yses of the FAR stall maneuver are Smith and E. Mitchell (Raytheon Co., Bedford, Mass.), p. 657-664. 5 discussed in detail. The advantages of using CSMP language in these refs simulations are reviewed. M.V.E.

19 A71 -11794 ! A71-11794 P Considerations for the hybrid computation of nylon insert that thermally isolates an unshielded platinum wire trajectories for missiles and aircraft. P. I. Rubin (Electronic sensor. Reverse flow into the housing is induced by the conical tip Associates, Inc., Princeton, N.J.I. In: Summer Computer Simulation which develops a negative pressure in the flow field. The sensor can Conference, Denver, Colo., June 10-12, 1970, Proceedings. Volume be influenced by static pressure differences and by flow angles at the 1. Conference sponsored by the Association for probe site. The local static pressure, measured by a Pitot-static tube, Computing Machinery, S.H.A.R.E., and the Simulation Councils. is higher than the free stream static pressure. Wind tunnel and flight New York, Association for Computing Machinery, 1970, p. 602-609. tests were conducted to measure the local total and static pressures Demonstration of how time sharing and hybridization may ahead of the probe tip, static pressure within the probe cavity, static ,educe analog equipment count. A good deal of hybridization can and dynamic pressures corresponding to aircraft and environmental I reduce the digital computation time siytiificaii:ly in a typical conditions, reverse flow temperatures, and reference temperatures. trajectory calculation. This leads to the postulation of a hybrid split These tests defined sysrenidtii Source$ sf orrsr iwhirh can be of the translational portion of the trajectory to minimize digital corrected during data reduction. T.M. I compe!atinn time, retain necessary and/or reasonable accuracy in the , displacement calculation, and at the same time produce ooiiiinuou; velocity variables for control systems studies. In order to take full advantage of the proposed hybrid split, it is necessary to have a large A7141870 ,# A simple model of the pseudo-shock mech- number of MDACs (DAMS) for fast, continuous generation of the anism. R. Yamane, Y. Tomita, and S. ltaya (Tokyo Institute of aerodynamic coefficients. Thus, effective hybrid computation of Technology. Tokyo, Japan). Tokyo Institute of Technology, trajectories rests ultimately on the size, speed, and quality of the Bulletin, no. 100. 1970, p. 1-13. 7 refs. D/A interface. F.R.L. Description of a tentative model of the mechanism of the pseudoshock, based on the idea that in the upstream region the 1 shock wave repeats a kind of reflection on the boundary surface between the main flow and the low speed region near the wall, and A71-11809 !. Airlines maintenance model. Elroy M. Smith that the expansion waves and the oblique shock waves emanate near (IBM Corp., San Francisco, Calif.). In: Summer Computer Simula- the reflection points. This model can explain the fact that the static tion Conference, Denver, Colo., June 10-12. 1970, Proceedings. pressure in the main flow increases and decreases alternately in the Volume 2. Conference sponsored by the Associ- upstream region while that on the wall increases monotonously. The 1 ation for Computing Machinery, S.H.A.R.E.. and the Simulation calculated pressure change and the distance between the successive Councils. New York, Association for Computing Machinery, 1970, p. shock waves are in good agreement with experimental results. O.H. 1 1125-1133. The Airlines Maintenance Model is a simulation model using the GPSS language. The model simulates the maintenance performed on aircraft. The purpose of the model is to study the utilization of I A71-11884 Heat transfer and frictional drag in the longitu- 1 equipment, work forces and physical areas such as terminals and dinal flow of a gas with variable physical properties past a plate. V. aircraft parking spaces. The model gives important information on N. Popov (Moskovskii Energeticheskii Institut, Moscow, USSR). 1 the effects of maintenance operations on departure schedules. (Teplofizika Vysokikh Temperatur, vol.. 8, Mar.-Apr. 1970, p. Arriving aircraft are generated as transactions, based on predeter 333-345.) High Temperature, vol. 8, Mar.-Apr. 1970, p. 311-321. 11 i mined arrival schedules. The aircraft then undergo a maintenance refs. Translation. check. Upon completion of the maintenance check, the aircraft Description of a method of calculating the heat transfer and become available for departure, and depart when the departure friction drag during turbulent flow past a plate by a gas the physical schedule requires it. The model produces statistics on the availability properties of which depend arbitrarily on temperature. The proposed and occupancy of terminals, the utilization of men and equipment, method can be applied not only to a chemically homogeneous gas the frequency of departures. The model contains approximately 800 but also to a gas in dissociated or ionized equilibrium. Moreover, this blocks. (Author) method takes more accurate account of the variation of the 1 tangential stress and heat flux density over the boundary layer cross section, it does not involve an arbitrary division of the boundary I layer into a viscous sublayer and a turbulent core, no artificial A71-11821 # An inflatable restraint collar for balloons. Karl assumptions are made regarding the mixing length in the case of Stefan (National Center for Atmospheric Research, Boulder, Colo.). constant physical properties, and more accurate account is taken of I Facilities for Atmospheric Research, June 1970, p. 2-6. I the cross-sectional variation of the turbulent transport coefficient. In I Description of an inflatable restraint collar which both clamps the case of variable physical properties it is necessary to introduce a the uninflated balloon material below the launch bubble and serves certain hypothesis concerning the mixing length. On the basis of this I as an attachment point for a restraining cable during single-cell hypothesis a relation is obtained which relates the turbulent I balloon launch operations. The inflated collar is held by a restraint transport coefficients for the cases of constant and variable physical cable connected to the winch. After balloon inflation, the cable is properties. A.B.K. I paid out, and a fastener connecting it to the collar is released at the desired height. Upon release of the fastener, the collar opens and j imparts a forward momentum to the balloon and rearward momen- tum to itself, yielding a clean separation of the two. The collar i consists of two double-walled, inflatable half-cylinders hinged A71-1 1949 Improvements in fatigue testing of sailplanes. together at one side and equipped with a releaseable fastener at the Jozsef Gedeon (Budapesti Muszaki Egyetem, Budapest, Hungary). other. The developmental studies are summarized, and the forces (Organisation Scientifique et Technique Internationale du Vol a acting on the collar are illustrated. T.M. Voile, Congress, 12th, Alpine, Tex., June 27-July 4, 1970.) Aero- Revue, Nov. 1970, p. 665-668. 17 refs. Combining data from the more detailed analysis of sailplane G records with some recently published theoretical results gives the 1 A71-11822 # Evaluation of reverse flow temperature probe. possibility to calculate more exact load spectra taking into account Facilities forAtmospheric Research, Jim 1970, p. 11-14. some dynamical characteristics of the type in the design stage Results of tests conducted with a reverse flow temperature already. In view of a life safety factor of at least 5 for safelife 1~ probe used to provide accurate temperature measurements and designs dictated by the impossibility of making more than a sole vertical soundings from aircraft. The probe housing consists of a full-scale complete fatigue test in most cases, the development of , cylindrical radiation shield with a conical Teflon front tip and with a fail-safe structures is of prime economic importance. The possibility I

20 1 A71-12164 of developing fail-safe light metal sailplane wings has been proved by Detailed examination of the design and production program succeaful preliminary tests. The relatively weakest part in fatigue leading up to the first flight of the Grumman F-14A twin-engine, testing is damage calculation. Limitations of the Palmgren-Miner variable geometry, carrier-based jet fighter designed for the U.S. theory applied so far by us are well understood. but several other Navy to provide air superiority and fleet air defense. A fully proven formulas tried hitherto failed to come up to expectations. A series of F-14A weapon system is scheduled to undergo fleet introduction two-stress level rotating bending and axial tensile fatigue tests were only 51 months after contract award to Grumman. The development run to investigate the adaptability of some new ideas to dural type program receives extensive attention, followed by description of alloys. (Author) manufacturing techniques and processes. Comment is made on production and systems testing, program commitments, mainte- nance, and future prospects. F.R.L.

A71-11950 Wind-tunnel measurement on profiles wifh flaps for moderate Reynolds numbers. I (Windkanalmesrungan an Profilen mit Klappen bei mittleren Reynolduahkn. I). D. Althaus A71-1 21 62 Aircraft pavement design; Institution of Civil (Stuttgart, Univenitat, Stuttgart, West Germany). (Organbation Engineers, Symposium, London, England, November 12. 1970, Scientifique et Technique Internationale du Vol a Voile, congress, Proceedings. London, Institution of Civil Engineers, 1970.78 p. 12tf1, Alpine, Tex., June 27July 4, 1970.) Aero-Revue, Nov. 1970. p. 669,670. In German. Contents: Discussion of wind tunnel tests performed at moderate Aircraft development in relation to pavement design. K. V. Reynolds numbers with a variety of cambered and symmetric wing Bonney (Hawker Siddeley Aviation, Ltd., Hatfield. Herts., England), profiles and flap configurations. The aerodynamic data obtained for p. 1-6. various flap chords, aspect ratios, and deflections are intended to Undercarriage effects on (a) rigid pavements (b) flexible Serve as reference data in wing-flap design. Measurements obtained pavements. J. L. Dawson (Roskill Commission) and R. L. Mills with a laminar wing profile are plotted vs the angle of attack. V.P. (Ministry of Public Building and Works, London, England), p. 7-20.9 refs. Developments in pavement design in the USA - Rigid pavements. E. R. Breihan (Horner and Shifrin, Inc., St. Louis, Mo.). p. 21-29. A71-113558 # Supersonic flow around a circular cone equipped with cross-shaped wings (Miprea supersonici in iurul unui Developments in pavement design in the USA - Flexible con circular prevkut cu aripi cruciforme). Rodica Chirili Socolescu pavements. R. G. Ahlvin (US Army. Engineer Waterways Ex, (Academia Romlni, lnstitutul de Matematid, Bucharest, Rumania). periment Station, Vicksburg, Miss.), p. 31-36. 13 refs. Studii si Cercedri Matematice, vol. 22, no. 10, 1970. p. 1415-1425. 5 refs. In Rumanian. Developments of pavement design both rigid and flexible on the Investigation of a circular cone with cross-shaped wings in the continent of Europe. G. Moraldi (Roma. Univeniti. Rome. Italy), p. middle of a supersonic flow. A linearization method proposed by 3746. 32 refs. Germain (1948, 1949) is used to determine the characteristicsof the Current British pavement design. F. R. Martin (Ministry of flow, velocities, pressure, and the pressure resultant. The results Public Building and Works, London, England) and A. R. Macrae obtained are compared with those obtained by Socolescu (1966) and (British Airports Authority, London. England), p. 47.58. lacob (1961). M.M. Strengthening of pavements. H. Jeinings (Ministry ot Public Building and Works, Condx, Er.g:,;,di diiu F. i. ti. Straw (Public Works Department, Birmingham, England). D 59-68.

A7141959 'I Sandwich structures in aircraft and space Deiign and construction of aircraft pavements in unusual vehicles (Le strutture smdwich nei veicoli aerei e spaziali). Gwseppe conditions. F. W. Spencer and J. K. Holt (Scott Wilson Kirkpatrick Surace (Torino. PolitPcnic.o, Turin: Bari, Universita, Bari, Italy). and Par!ners, London, England), p. 69-74. Tecnica, vol. 24. Oct. 1970. p. 755.;41 Critical evaluatlon of sanciwcl1strutilies I :le r?a.actv .'*I., L' c?ndv;ich S!I ucture rompnnsmr. rnanuf?ctiiririg ;:'Jcesxj. awi me A71-12163 Aircraft development in relation to pavement clraniral testing are e~ami~,ed. hil,iiographic search sandwich A of design. K. V. Bonney (Hawker Siddeley Aviation, Lrd , tiatfield, structure applicatioiis ir t)?? 1a:est space vehicle: is provicle;l. Herts., England). In' Aircraft pavement design; Inst::(.::nq of Civil toyether with the curve5 of the gocdness inch 07 cnmrno"i.t?Uy Engineers, Symposium, London, England, Novembci 12. 1970, standardiwd sandwicli st*iictiiie iornpwents. M.M Proceedings. London, lnstitutiun of Civil En- gineers, 1970, p. 1-6. Discussion of the limitations of ?'re pressures a-d multiwheeled landing gears for transpor: aircraft 0: tw 19GO'c and those being

A71-12044 A synthstic aperture at 10.6 microns. I S developed for the 1970's. Vdr\oii,- locol'sns foi insrdiling the main Lewis and ti S Hutchins (United Aiicraft Rrsealcl: Labordiuries. gear are described, and cornpar~sonsdre made betwfeti old and new East Hartford. C0nn.i. I€€€. Proicerlings, vol. 58, act. 1970, p. forms of wheel arrangemeits. Po;sit;li. mprovements in pavements 1781. 1782 and aiicraft to obtaic a smoother ride arc cowdrred. Procedure for Description of an experimental demonstration of synthetic takeoff and landing, and design requirement5 fot devices on the aperture radar principles using a CO2 laser. The experiment consisted aircraft are described, followed by a review of problems resulting Of the feasibility of operating a synthetic aperture system at ir from inadequacies in pavement design. The ha:ards of ingestion into wavelength of 10.6 microns. The most important aspect of the an engine of stones, water, and slush are deal! with in some detail. experimental results shown is that an essentially point target was well Aquaplaning and poor tire adhesion are real rt'ohlems when excessive resolved within an approximately 2-in. diam beam at the target using quantities of water are present. F.R.L. synthetic aperture techniques. M.M.

A71-12050 Grumrnan prepares the F-14A for its first a71-12164 Undercarriage effects on (a) rigid pavements flight. Douglas Cornell. Interavia, vol. 25, Nov. 1970, p. 1384-1387. (ht flexible pavements. J. L. Dawson (Roskill Commission) and R. L.

21 A71 -121 65

Mills (Ministry of Public Building and Works, London, England). In: flexible pavements the most common design procedure is the CBR Aircraft pavement design; Institution of Civil Engineers, Symposium, method. Rational methods of design, based on the multilayer elastic London, England, November 12, 1970, Proceedings. theory and the method of equivalents, are rapidly gaining favor. London, Institution of Civil Engineers, 1970, p. 7-20. Aggregate or crushed stone bases have been generally superseded by 9 refs. bitumen-bound layers. Plate bearing tests and impact methods are Description of current multiwheel undercarriages, with con- used to evaluate pavements. Some suggestions are given for overlay sideration of future trends in undercarriage design. Observed modes procedures. F.R.L. of failure in flexible and rigid pavements are examined, and criteria re cuggested for different categories of pavements. For each category graphs are presented ot load vs iiie piessz- !or B range of undercarriage arrangements and for different subgrade charac- A71-12168 Currenr ijriiish pavemen? des@. F. R. Martin teristics. The graphs are based on test and experimental work and (Ministry of Public Building and Works, London, England) and A. R. ~i)i~ipii:c: c~!CLilatinns.Their derivation and validity is discussed. The Macrae (British Airports Authority, London, England). In: Aircraft concept of the equivalent single wheel load ana the iud ila;sifi- Favement design; Institution of Civil Engineers, Symposium,

cation number is briefly described, and some incompatibilities are London, England, November 12, i970, P:ccaer’iw-c2~ identified. F.R.L. London, Institution of Civil Engineers, 1970, p. 47-58. Brief examination of the history of aircraft pavements which have been designed, built, and borne traffic in the past 30 years, with explanations of why particular decisions have been taken which have A71-12165 Developments in pavement design in the USA - led to the design methods currently used. Types of pavement Rigid pavements. E. R. Breihan (Horner and Shifrin, Inc.. St. Louis, recommended are plain unreinforced concrete (rigid), continuous Mo.). In: Aircraft pavement design; Institution of Civil Engineers, reinforced concrete surfaced with bituminous courses (composite), Symposium, London, England, November 12, 1970, Proceedings. and cement, bitumen, or tar-bound bases surfaced with bituminous London, Institution of Civil Engineers, 1970, p. courses (flexible), In eddition to strength requirements the need to 21-29. provide pavement surfaces of high stability and acceptable texture is Review of the processes currently used in the design of rigid discussed. F.R.L. pavements for the Lambert-St. Louis Municipal Airport, considering the supporting effects of the soil subgrade, the asphaltic concrete sub-base, and the basic strength of the pavement itselt. The criteria used in the design are those of the FAA and of the Portland Cement A71-12169 Strengthening of pavements. H. Jennings Association. The different types of joints that are presently used for (Ministry of Public Building and Works, London, England) and F. L. rigid pavements in the US. are discussed. Since there have been joint H. Straw (Public Works Department, Birmingham, England). In: tailures, it is evident that additional research is required in this area, Aircraft pavement design; Institution of Civil Engineers, Symposium. as well as in many other areas 3f rigid pawments, to determine the London, England, November 12, 1970, Proceedings. causes of failures and to recommend remedial measures. F.R.L. London, Institution of Civil Engineers, 1970, p. 59-68. Consideration of various methods of strengthening existing runways, aprons, and taxiways to accommodate higher tire pressures, heavier aircraft, higher landing speeds, and to provide improved A71 -12166 Developments in pavement design in the USA - standards of surface riding quality. The specification and use of Flexible pavements. R. G. Ahlvin (US. Army. Engineer Waterways concrete and bituminous materials is discussed. In view of the fact Experiment Station, Vicksburg, Miss.). In: Aircraft pavement design; that many airports have to be kept in operation while the paved areas Institution of Civil Engineers, Svmposium, London, England, are strengthened, emphasis is placed on the difficulties which arise in November 12, 1970, Proceedings. London, In- practice while carrying out civil engineering works. Reference is also stitution of Civil Engineers, 1970, p. 31-36. 13 refs. made to the surface treatment of the concrete and asphalt to minimize the risk of standing water causing aircraft to aquaplane Discussion of trends in flexible pavement design concepts, during adverse weather conditions. F.R.L. including theoretical developments and applications, treatments of load repetitions, total systems, environmental effects, etc. Current emphasis on providing for the new giant transports is recognized, and the effects of the heavy loads and many-wheeled gear on flexible pavements are treated. Expedient airport pavements in support of A71-12170 Design and construction of aircraft pavements military trends toward greater air mobility are discussed. Attention is in unusual conditions. F. W. Spencer and J. K. Holt (Scott Wilson given to civil use of austere or expedient airports. Various ancillary Kirkpatri,ck and Partners, London, England). In: Aircraft pavement developments such as pavement compaction, failure criteria, skid design; Institution of Civil Engineers, Symposium, London, England, resistance. quality control, and vibratory tes:ing are considered. November 12, 1970, Proceedings. London, In- F.R.L. stitution of Civil Engineers, 1970, p. 69-74. Study of three sets of circumstances in which soil or other conditions create pavement design and construction problems re- quiring special solutions. These are: (1) the construction of airport A71 -12167 Developments of pavement design both rigid pavements over deep deposits of soft, compressible soils, (2) the and flexible on the continent of Europe. G. Moraldi (Roma, construction of pavements on subgrades composed of expansive soils, Universita, Rome, Italy). In: Aircraft pavement design; Institution of and (3) the construction of pavements on subgrades which vary in Civil Engineers, Symposium, London, England, November 12, 1970, engineering properties and distribution. Illustrative examples of Proceedings. London, Institution of Civil En- solutions adopted in the past are quoted for various airport projects. gineers, 1970, p. 37-46. 32 refs. F.R.L. Review of various pavement design and construction practices followed by European nations. Unreinforced or crack-reinforced slabs, designed according to Westergaard’s theory, are the most commonly used for rigid pavements. There is a definite tendency to AJ1-12192 # Heat exchange and drag in a circular pipe avoid expansion joints and to adopt stabilized base courses. during laminar flow of a gas with variable properties. II - Results of Prestressed pavements have been frequently applied in Germany. calculations at constant wall temperature (Teploobmen i sopro- Structurally reinforced slabs are common practice in Sweden. For tivlenie v krugloi trube pri laminarnom techenii gaza s peremennymi

22 A71-1 2380

svoistvami. II ~ Rezul'+ay rascheta pri postoiannoi temperature alkylated salicylic acid, calcium dodecyl succinate, and a vinyl/ stenki). V. D. Vilenskii, B. S. Petukhov, and B. E. Kharin (Akademiia methacrylate copolymer, are given. The effect of static dissipator Nauk SSSR, Nauchno-lssledovatel'skii lnstitut Vysokikh Tempe additives on fuel properties is examined, together with means being ratur, Moscow, USSR). Teplofizika Vysokikh Temperatur, vol. 8, devised to counteract the tendency of ASA-3 to lose its-potency with time. July-Aug. 1970, p. 817-827. In Russian. V.P. Results of heatexchange and drag calculations for laminar flow of air in a circular pipe at constant wall temperature in cases of parabolic and uniform velocity profiles at the inlet. The study involves both cooling and heating of air at atmospheric pressure and A71-12368 Air transport (Le transport aPrien). J. Muffang is limited to situations where the effects of free convection, (Union de Transports Aeriens. Paris, France). Revue Franpise compressibility, and kineticenergy dissipation can be neglected. The de MPcanique, 2nd Quarter, 1970, p. 23-28. In French. calculations involved numerical integration of the equations of Description of a method for controlling the reliability of motion and energy in a boundary-layer approximation for ratios of turbojet engines by comparing the performance data indicated by the wall to inlet temperatures ranging from 1/9 to 9. A substantial on-board devices with a gauge of normal performance using a special influence of the variable properties of the gas on the flow and heat slide rule. This method makes it possible to reveal any anomaly in transfer characteristics is discovered. Nusselt numbers and drag the operation of the engine as soon as it occurs. The following coefficients obtained differ by several orders of magnitude from advantages are obtained: (1) optimization of the maintenance those in the case of constant gas properties. T.M. methods, (2)increase of the performance and mean time between failures, (3) decrease of accident toll and flight breaks, (4) substantial decrease of repair costs, and (5) decrease of risks of nonscheduled exchanges of engines. Z.W. A71-12274 Autoland all-wealher props. J. W. Wilson. Flight International, vol. 98, Nov. 12, 1970, p. 750-752. Discussion of the present consolidation phase of automatic landing development. The search for minimum component weights allied to maximum reliability is related to developments connected A71-12376 ,# Boundaryqayer separation at a free streamline. with the ultimate problem areas such as ground-roll guidance. Recent I - Twodimensional flow. R. C. Ackerberg (Brooklyn, Polytechnic developments in the Smiths system installed in the Hawker Siddeley Institute, Farmingdale, N.Y.). Journal of Flud Mechanics, vol. 44, Trident 3B are discussed. Some results obtained by the French Nov. 11. 1970, p. 211-225. 13 refs. Contract No. DA-31-124- internal airline Air Inter with Caravelle aircraft operating to 15 m ARO(DI-444. decision height and 150 m RVR are presented. F.R.L. Study of the boundary-layer flow just upstream of the trailins &e of a fiat plate when a free streamline is attached to the edge. The separation of the edge occurs with an infinitely favorable pressure gradient and is characterized by a skin friction which is A71-12275 Technology for better all-weaher landings. proportional to the inverse eighth power of the distance from the Malcolm Moulton (Elliott Flight Automation, Ltd., Rochester, Kent, edge. The proportionality factor for the first-order term is indepen- England). Flight International, vol. 98, Nov. 12, 19?0, p. 753755. dent of the upstream boundary-layer flow. The streamwise velocity 758. profile at separation is nonanalytic near the wall Y 5 0, and starts Description of the Elliott Flight Automation landing systems for with the term Y to the 2/3 power. (Author) the VC10. BAC One-Eleven, and Concorde. During the past decade there has been a virtual explosion in electronic technology. and this hac prgduced a breakthrough in mechanizing automatic landing systems more quickly. more reliably, and with more repeatable A71-12377 fc The aerodynamic noise of smallperturbation performance. It is considered that it should be possible to land the subsonic flow. Roy Amiet and W. R. Sears (Cornell University, VClO automatically in 97% of all weather encountered at Heathrow. Ithaca, N.Y.). Journal of Fluid Mechanics, vol. 44, Nov. 11, 1970, p. F.R.L. 227-235. 13 refs. Application of the method of matched asymptotic expansions to simplify calculations of noise produced by aerodynamic flow involving small perturbations of a stream of nonnegligible subsonic A71-12299 Non-metallic aircraft materials. Peter Jowitt Mach number. This technique is restricted to problems for which the (Royal Aircraft Establishment, Farnborough, Hants.. England). Shell dimensionless frequency is small. By combining Lorentz and Galilean Aviation News, no. 388, 1970. p. 10-13. transformations, the problem is transformed to a space in which the Survey of the advantages and perils of using wood and synthetic approximation appropriate to the inner region is found to be resin as aircraft materials. The timber species used in aircraft incompressible flow and that appropriate to the outer, classical construction. and the requirements placed on them are examined, acoustics. This approximation for the inner region is the unsteady and the types of failure that occur are illustrated. The selection of counterpart of the Prandtl-Glauert transformation, but is not timber for repair is shown to be a highly complex business. The use identical to use of that transformation in a straightforward quasi- of epoxy and polyester resins as aircraft materials is described, and steady manner. For wings in oscillatory motion, it is the same the various failures which have to be watched for are outlined. V.P. approximation as was given by Miles. To illustrate the technique, two examples are treated, one involving a pulsating cylinder in a stream, the other the impinging of plane sound waves upon an elliptical wing in a stream. O.H.

A71-123OO Experience with static dissipator additive in aviation fuels. R. G. Davies (Shell International Petroleum Co., Ltd., London, England) and R. W. Knipple (Shell Oil Co., Houston.Tex.1. Shell Aviation News, no. 388, 1970, p. 14-24. A71-12380 # Exmndon of Goldstein's series for the 0- Discussion of experienoe gained with fuel-soluble conductivity- drag of a rphere. Milton Van Dyke (Stanford University, Stanford, improving static dissipator additives in aviation fuels as a means of Calif.). Journal of Fluid Mechanics, vol. 44, Nov. 11, 1970, p. eliminating electrostatic charging hazards. Results obtained in labora- 365372. 17 refs. Contract No. AF 44(620)-64c-0036. tory and in flight tests with the ASA-3 static dissipator additive, a Extension of Goldstein's expansion of the Oseen drag of a three-component mixture of equal parts of the chromium salt of an where in powers of Reynolds number to 24 terms by computer. The

23 A71-12408

convergence is found to be limited by a simple pole at R = -4.18172. flight equipment are outlined and the specific procedures adopted The series is recast using a Euler transformation and other devices to for testing the individual equipment or items are discussed. The areas yield accurate results for large R. O.H. of application of other nondestructive inspection methods, such as magnetic particle, penetrant, and X-ray inspection, are also shortl-4 reviewed. O.H.

A71-12408 /# Considerations on the wave drag of a delta thin wing with leading edge separation. Elie Carafoli and Stefan Staicu (Bucuresti, Institutu1 Politehnic Gheorghe Gheorghiu-Dej, A71-12477 Development and test of carbon epoxy fibre Bucharest, Rumania). (CurifdieXe 9Jstic.n;7k de Mecanique cnrr?pnsite for helicopter tail rotor applications. Bernd Bongers. Appliqude, Bucharest, Rumania. June 23-27, 1969.1 Revue Klaus Brunsch, and Wolfgang Jonda (Messerschniii~-Ddlk=:^:B!nhm Roumaine des Sciences Techniques. Serie de MPcanique Appliquie, GmbH, Munich, West Germany). In: British Plastics Federation, ~nl15,no. 5, 1970.p. 1101-1124. 11 refs. International Reinforced Plastics Conference, 7th. Brighton, Calculation of the aerodynamic characieri,i;is of zi :hit $e!!? inglaiid, C)c?c!~er 20-72. 1970, Proceedings. wing with allowance for the vortex streets at the tip wings resulting London, British Plastics Federation, 1970, p. 1/1-1/7. from flow separation at the subsonic leading edges. Lift and rolling Discussion of the development and testing of tail rotor blades moment coefficients are obtained from the pressure distribution on for the Messerschmitt-BolkowBlohm BO-105 helicopter using the wing. Drag coefficients are determined both for a thin delta wing carbon fiber reinforced composites (CFC). An evaluation and and for a system of wings of symmetrical thickness. V.P. analysis of various fibers with regard to this specific application is made, showing the outstanding mechanical properties of carbon fibers. The design features of the semirigid two-blade tail rotor for the 80-105 helicopter with CFC blades are presented. In order to A71-12420 # Superpressure balloon and precise pressure determine the effect that various grades of stiffness have on the radio-sonde system for the research of vertical air-motion. Shoji Ohta dynamic behavior, the flapwise, chordwise and torsional frequencies and Tomoyuki Ito (Ministry of Transportation, Meteorological of a tail rotor blade with filament-wound carbon skin were tested in Research Institute, Tokyo, Japan). Papers in Meteorology and comparison to a glass-reinforced plastic rotor blade. The approach Geophysics, vol. 21, Apr. 1970, p. 45-72 14 refs. In Japanese, with selected to improve the processing techniques to such an extent that abstract in English. specifications could be established for production of a blade which Description of a superpressure balloon and a precise pressure could be flight-tested is described. Finally fatigue tests and a fight radiosonde system for studying airflows over mountainous regions. test conducted on the CFC tail rotoi blade are discussed. 0.H. The balloon is about 1.7 m in diam and is made of 50-micron thick film. The sphere consists of 12 segments. Field observations were carried out, and over 30 balloons have been successfully landed so far. It was found that vertical air current within a height of 5 km and A71-12487 Polyimides in advanced composites for aero- a range of 100 km or more could be measured with an accuracy of space applications. M. C. Cray (British Aircraft Corp., Ltd.. plus or minus 1 mb. The system proved to be quite stable and Stevenage, Herts., England). In. British Plastics Federation, lnter- Dractical for the field measurement of vertical air motion. M.M. national Reinforcpd Plastics Conference, 7th. Brighton. England, October 20 22, 1970, Proceedings. London, British Plastics Federation, 1970. p. 2711 27/4 10 refs. Discussion of the various aspects of polyimide composites A71-12439 Skynet traffic systems. J W. Gunning (Signals developed for high strength and random aerospdce applications. Research and Development Establishment, Christchurch. Hants., Following an outline of the chemistry of polyimides, their com- England) In: Skynet; Institution of Electrical Engineers. Meeting. mercial applications are briefly reviewed. Composite manufacture London, England. April 20. 1970, Proceedings. with the British resin is then described, and the results of tests of London, lnstltution of Electrical Engineers (IEE Conference Publica- glass fiber, carbon fiber, and asbestos composites are presentd A tion No. 631. 1970, p. 137-145. comparison with a foremost American volyimide resin is then made. Description of the Skynet communications system and of its Finally. some problem areas, such as void content, volatiles, and main control organs and control center. A technical description of a moisture absorption are reviewed, and the future of polyimides in typical trunk is given, together with details of the engineering and aerospace applications is considered O.H. systems control The Skynet satellit- repeater ha? been equipped with wide-band and narrow-band pathways which provide long distance strategic communication links between a number of earth statlonj on permanent sites. In addition, a number of mobile A71-12488 Carbon fibre 111 aviatioi : Frav (Hawker air/helicopter portable stations are also provided which enable a Siddeley Aviation, Ltd., Kingston-upon-Thames, Surrey, England) mobile force headquarters, or similar unit. to gain entry into the In. British Plastics Federation, International Reinforced Plastics strategic system. The overall control of the system IS exercised by the Conference, 7th. Brighton, England, October 20-22, 1970, Proceed Master Engineering Control Center whose facilities and functions are ings. London, British Plastics Federation, 1970, outlined Communications trials so far conducted indicate that the p. 2811 -2815. traffic capacity of the Skynet system may be expected to measure up Discussion of the use of carbon fiberlsynthetic resin, particular- to specification. M.V.E. ly epoxy resin composites in aircraft industry. Following a brief review of the historical background, specific streta5!!1s and specific moduli of carbon fiber/epoxy resin composites made with high^ strength and high modulus fibers at 60% fiber volume fraction are A71-12449 NDT techniques for airline maintenance in- compared with the equivalent properties of the common aircraft spection. W. J. Weldon (American Airlines. Inc., New York, N.Y.). materials. The high fatigue lite of these composites. meeting exactly Ouality Progress, vol. 3, Nov. 1970, p. 22-24. the requirements of aircraft structural materials, is emphasized. On Description of the application of the various methods of the other hand, several problems resulting from some of the nondestructive testing to insure the integrity of aircraft. Airline properties of these composites are also discussed. Some examples of mdiritenance inspection as performed by American Airlines, Inc., is a variety of experimental aircraft structures from these composites considered. Specific areds IP which ultrasonic and eddy current are presented Finally, future utilization and the influence of cost is maintenance inspection is used to insure the integrity of various considered. O.H.

24 A71-1 2606

A71-12551 # Influence of forward speed on the aero- apparata na kharakteristiki stupenei osevogo komprenora s dynamic characteristics of an air-cushion vehicle (Vliianie skorosti lopatkami malogo udlineniia). A. D. Griga, V. V. Kovalevskii. and A. postupatel'nogo peremeshcheniia na aerodinamicheskie kharakter- E. Poliakov. Samoletostroenie i Tekhnika Vozdushnogo Flota, no. istiki apparata na vozdushnoi podushke). L. F. Kalitievskii. Same 17, 1970, p. 38-40.In Russian. letostroenie i Tekhnika Vozdushnogo Flota, no. 17. 1970, p. 3-9. 6 Analysis of the results of an experimental investigation of the refs. In Russian. influence of the aspect ratio of guide vanes on the efficiency of Development of an analytical method of determining the high-pressure stages of two axial-flow compressors (K-70-10C and influence of forward horizontal speed on the aerodynamic character- OKVD-50). it is shown that, for small aspect ratio vanes, stage istics of an air-cushion vehicle employing a circular nozzle and efficiency can be increased in many cases by using guide and rotor cylindrically or conically shaped curtains. The method proposed vanes with different aspect ratios. V.P. makes it possible to determine the distortion of the curtain by the oncoming flow and the velocity distribution at various cross sections of &e curtain. Using these data, it is then possible to calculate the principal aerodynamic characteristics in horizontal flight. V.P. A71-12559 # Utilization of continuous fuel feed in a rotary- piston engine with planetary motion of the rotor (Priinenie nepreryvnoi podachi topliva v rotorno-porshnevom dvigatele s planetarnym dvizheniem rotora). A. M. Frid, lu. S. Shoshin, and P. P. A71-12553 # Approximate method of calculating the Pershin. Samoletostroenie i Tekhnika Vozdushnogo Flora, no. 17, minimum suction rate preventing boundary layer separation for a 1970. p. 41,42. In Russian. semibounded jet (PriMizhennyi metod rascheta minimal'noi skorosti Discussion of an internal mixing scheme for a Wankel engine, in otsasyvaniia, iskliuchaiushchei otryv pogranichnogo sloia pduograni- which the fuel is injected continuously by means of a nozzle into the chennoi strui). A. M. Mkhitarian and A. P. Girol'. Samolemstroenie i working cavity during the intakecompression cycle. By placing the Tekhnika Vozdushnogo Flota, no. 17,1970, p. 14-18. In Russian. injection nozzle close to the major axis of the chamber, the time Development of a method of calculating the lowest suction rate mixing time is increased and the fuel losses (of the next charge) due that would prevent laminar boundary layer separation from a to overlapping of the intake and exhaust openings are eliminated. curvilinear porous surface situated in a jet flow expelled from a thin Experiments performed with a swirl injector at injection pressures of slot into a slipstream. The method is based on the use of a less than 15 kg/sq cm revealed the effectiveness of the scheme dimensionless momentum equation for the boundary layer and of a proposed. V.P. velocity profile in the form of a fourth-order polynomial. The maximum velocity at the interface between the boundary layer and me main flow is determined from an integral momentum relation for the main flow. V.P. A71-12562 # Determination of the cross-sectional dimen- duns of ioadcarrying elements of delta wings from the static strength and weight conditions (Opredelenie razmv sechenii A71-12554 # Laminar boundary layer on a wing and a body nesushchikh elementov trwgol'nykh kryl'ev po udoviiim statiche of revolution in the presence of blowing (Laminarnyi pogranichnyi skoi prochnosti i vesa). V. M. Riabchenko and M. P. Tepenitsyn. sloi na kryle i tele vrashcheniia pri nalichii vduvaniia). L. F. Kozlov Samoletostroenie i Tekhnika Vozdushnogo Flota, no. 17. 1970. p. and A. I. Tsyganiuk. Samoletostroenie i Tekhnika Vozdushnogo 63-70. 5 refs. In Russian. Flota, no. 17, 1970. p. 19-25. In Russian. Consideration of delta wings with a skin reinforced by longitudi- Development of a method of calculating the characteristics of a nal and transverse thin-walled longeron beams and ribs. A method of two-dimensional axisymmetric incompressible boundary layer on a designing wings with symmetrical upper and lower panels is blown wing, using a sixth-order polynomial for approximating the described, and an aigorirhm for minimizing the theoretical weight is velocitv distribution BCTOSS:he bomdai y idyer. An arbitrary velocity developed. It is shown that the proposed method, provided certain distribution at the outer boundary of the layer is assumed. A assumptions are made, makes it possible to solve the problem of solution to the problem is obtained with the aid of Karman's integral optimal designation of the parameters of load-carryingelements of a relation. The method proposed is essentially an extension of the delta wing, if the structural complexity of the wing does not make Schlichting-Ulrich (1942) method to include porous surfaces. Using solution on serial-type computers difficult. A.B.K. Stapanov's (1947) transformation, the method can be readily extended to the calculation of blown laminar boundary layers on bodies of revolution. V.P. A71-12570 # Influence of the test time and contact stresses on the antiwear properties of jet fuds under conditions of rolling friction (Vliianie prodolzhitel'nosti ispytaniia i kontaktnykh A71-12555 # Determination of the point of laminar- napriazhenii na protivoiznosnye svoistva reaktivnykh topliv pri trenii turbulent transition with the aid of a traveling indicator (Oppde(enie kacheniia). A. F. Aksenov and A. A. Litvinov. Samoletostroenie i tochki perekhoda laminar- pogranichnogo doia v turbulentnyi Tekhnika Vozdushnogo Flota, no. 17. 1970. p. 130-133. In Russian. tkol'ziashchim koordinatnikom). V. E. Zozulia and 0. R. Experimental investigation of the influence of various factors on Cheranovskii. Samolemstroenie i Tekhnika Vozdushnogo Flora, no. the wear of jet fuels (T-1, TS-1, T-7, and T-7 with antiwear 17, 1970, p. 26-30. In Russian. additions), using the magnitude of wear and the increment in fuel Description of a device employing a hot-wire anemometer and temperature as criteria for evaluating the antiwear properties of the an oscilloscope to determine the point of laminar-turbulent trans!- fuels. Particular attention is given to the influence of contact stresses, tion on a wing. With the aid of an electrically driven mechanism, the the rate of rolling friction, and ti:,€. It is shown th;! these factors sensor is made to move in the boundary layer in opposite direction can have a substantial influence on the quantitdtrLc 6Pd.qualitative to the flow. The point of laminar-turbulent transition is determined relationships between friction and wear. This indicates that the (by linear measurements) from oscillograms of the velocity pulsa- antiwear properties of such fuels should be studied in the laboratory tions in the boundary layer. V.P. for a wide range of external effects. V.P.

A71-12558 # Influence of the aspect ratio of guide vanes on A71-12606 # 'Research on swept-back blades laid between the characteristics of axial-flow compressor stages with small parallel walls. II - Experimental research on Clark Y 8% and NACA aspect-ratio vanes (Vliianie udlineniia lopatok napravliaiushchego 6509 blades with aspect ratio of 2.0. H.Murai, T. Narasaka (Tohoku

25 A7 1- 12607

University, Sendai, Japan), Y. Hirata (Akita University, Akita, 231-272. Japan), and Y. Aoki. (Japan Society of Mechanical Engineers, Meeting for Hydraulics and Hydraulic Machines, 792nd, Tokyo, Hovercraft. R. Stanton-Jones (British Hovercraft Corp., Ltd., Japan, Sept. 26, 1969.) Tohoku University, Institute of High Speed East Cowes, Isle of Wight, England), p. 273-283. Mechanics, Reports, vol. 21, 1969-1970, p. 189-252. Experimental study of the effects of the thickness, camber, and Avionics - Towards the Twenty-first Century. P. A. Hearne leading edge radius of sweptback blades placed between parallel walls (Elliott Brothers /London/, Ltd., Camberley, Surrey, England), p. on the flow patterns and other characteristics of these wings. In the 284-306. experiments, sweptback blades with cross-sectional forms of Clark Y 8% and NACA 65% aeiofci!: $!?.IthP aspect ratio of 2.0 were The future of rotorcraft. R. Hafner, p. 307-323. examined, The results are given graphically, tabulated, and discussed. O.H. The prospect for materials. A. J. Kennedy (British Non-Ferrous Metals Research Association, London, England), p. 324-343.

A71-12607 M49 Larzac testing under way. Donald E. Education arid iiaining i:: tho second century. J. Black (Bath Fink. Aviation Week and Space Technology, vol. 93, Nov. 23, 1970, University of Technology, Bath, Somerset, England), p. 344-367. p. 40, 41,43, 44. Management of design. J. T. Stamper (Hawker Siddeley Discussion of the M49 Larzac turbofan engine under develop- Aviation, Ltd., Hatfield, Herts.. England), p. 368-400. ment by SNECMA and TURBOMECA. It will have an initial thrust rating of 2300 Ib, which will be increased to 2965 Ib in the first Law for aerospace activities 1966.2066, H. Caplan (Inter- development phase. The engine has an ultimate potential of 4400 Ib national Insurance Services, London; England), p. 401-440. thrust without afterburner. One version will be used on some models of the Aerospatiale SN-600 Corvette utility jet, and the Dassault Airports and air transport growth and transformation. A. H. Falcon 10 executive jet. Another version has been selected for the Stratford (Alan Stratford and Associates). p. 441.473. Franco-German Alphajet trainer. The intent of the design effort was to develop an engine which is relatively simple and is inexpensive to Air traffic and navigation in the second century. A. Stratton buy and operate. Current versions of the engine are constructed from (Defence Operational Analysis Establishment, England), p. 474.500. a combination of steel, light alloy, and titanium. F.R.L. Looking ahead in aeronautics and astronautics . A US view. R. Smelt (Lockheed Aircraft Corp., Burbank, Calif.), p. 501-529.

A71 -12609 The future of aeronautics. Edited by J. E. Looking forward again - Notes on the needs, probabilities and Allen (Hawker Siddeley Aviation, Ltd., Kingston-upon-Thames, possibilities in aeronautics. H. R. Cox (Berger, Jenson, and Surrey, England) and Joan Bruce. London, Hutchinson and Co.. Nicholson), p. 530-543. Ltd., 1970. 575 p.$12.60. Index, p. 545-552.

Contents: Foreword. Philip, The Duke of Edinburgh, p. vii. Preface. F. R. Banks, p. ix. A71-12629 # Inviscid ideally conducting fluid flow past a Looking ahead in aeronautics. J. E. Ailen (Hawker Siddeley thin foil in a transverse magnetic field (Obtekanie tonkogo profilia Aviation, Ltd., Kingstonupon-Thames, Surrey, England), p. 1-23. neviazkoi ideal'no provodiashchei zhidkost'iu v poperechnom An aerodynamicists prospect of the second century. D. rnagnitnom pole). G. B. Sher'iazdanov. Magnitnaia Gidrodinamika, Kijchemann (Royal Aircraft Establishment, Farnborough, Hants., vol. 6, July-Sept. 1970, p. 67-73. 10 refs. In Russian. England), p. 24-38. Derivation of a closed-form solution to the problem of inviscid ideally conducting fluid flow past an arbitrary thin foil in a The future tor agricultural aviation. A. H. Wheeler, p. 39-54. transverse magnetic field. The unknown functions are represented in the form of an asymptotic expansion in powers of a small parameter, The future role of computers with special reference to aero- and in the first approximation the problem coincides with the dynamic design. 8. Thwaites (Westfield College, London, England), approximation of Sears and Resler (1959). The determination of the P. 55-77. rotational and irrotational parts of the solution is reduced to finding an unknown harmonic function. In contrast to Sears and Resler and Astronautics - Its development during the second century of the other authors, a closed-form solution for an arbitrary thin foil is Royal Aeronautical Society (1966-2066). A. V. Cleaver (Rolls- obtained which depends on the Alfven number. A flow past a Rovce. Ltd., Derby, England), p. 78-105. three-parameter profile is considered as an example; the aerodynamic force coefficients and the load distribution are determined. In the The atmospheric environment mdaircraft - Now and the future. case of the absence of a magnetic field the results obtained coincide F. O'Hara and J. Burnham (Royal Aircraft Establishment, Bedford, with the results for an ordinary hydrodynamic flow. A.8.K. England), p. 106140.

The world of the strucfural engineer. W. G. Molyneux (Royal Aircraft Establishment, Farnborough. Hants., England), p. 141-165. A71-12676 # Size effects in conventional aircraft design. F. A. Cleveland (Lockheed Aircraft Corp., Burbank, Calif.). (American Unconventional flight. 8. S. Shenstone, p. 166-197. Institute of Aeronautics and Astronautics, Aircraft Design and Operations Meeting, 2nd. Los Angeles, Calif., July 20-22, 1970, Power generation for aircraft in the second century. M. W. paper 70-940.) Journal of Aircraft, vol. 7. Nov.-Dec. 1970, p. Thring (Queen Mary College, London, England), p. 198-208.- 483-512. 27 refs. As subsonic aircraft size has increased, the useful-load/gross Propulsion. L. G. Dawson (Rolls-Royce, Ltd., Derby, England), weight ratio has improved despite the so-called squarekube 'law;' p. 209-230. despite increasing requirements for such things as safety, reliability, and maintainability; and despite demands for greater comfort, speed, Man-machine hybrid . An evolving entity. G. M. Jones (Defence range, and productivity per dollar. Though future growth potential Research Board, Ottawa: McGill University, Montreal, Canada), p. appears unlimited if adequate technology improvement time obtains,

26 A71- 12603 the economic advantage gain rate is flattening and further increases A71-12680 # Numerical investigations of an airfoil in a are likely in smaller increments. Nonetheless, one gross weight nonuniform stream. F. Chow, E. Krause, C. H. Liu, and J. Mao (New doubling, and possibly two, is predicted by 1985; nuclear power can York University, New York, N.Y.). Journal of Aircraft, vol. 7. drive the optimum weight to five or ten million pounds before the Nov.-Dec. 1970. p. 531-537. 11 refs. Contract No. DA-31-124- year 2OOO. (Author) ARO(D)-464. Solution of the nonlinear differential equation for the flowfield around an airfoil in a two-dimensional nonuniform parallel stream by the finite difference method. The numerical results show that even A71-12677 P Evaluation of the design parameters for op- for a thin airfoil at small angle of attack, the stagnation pressure and timum heavily loaded ducted fans. Tern/ Wright (Georgia Institute of the vorticity carried by the streamline passing around the airfoil are Technology, Atlanta, Ga.; Westinghouse Fluid Systems Laboratory, significantly different from the corresponding values carried by the West Lafayette, Ind.). Journal of Aircraft, vol. 7, Nov.-Dec. 1970, P. undisturbed streamline through the body under the linearized 512-517. Grant No. DA-HC04-68-C-004. approximation. When the deviation upstream from the uniform flow A consistent mathematical model for the ultimate vortex system is represented by a Gaussian profile to simulate the velocity of an optimum heavily loaded ducted fan has been developed for increment behind a propeller, the numerical results show that there is zero hub diameter and neglecting compressibility, viscosity. and tip an optimum vertical location of the airfoil relative to the upstream clearance. The compatability relationships to be satisfied are pre- profile for maximum lift. A correlation between the maximum lift sented with a brief description of the model. For any choice of blade and a nonuniformity parameter of the upstream profile is obtained. number and pitch angle, it is shown that the blade bound vortex This parameter is a combination of two paranwters. the maximum strength dinribution for the heavily loaded ducted fan may be velocity deviation and the spread of the nonuniformity. When the extracted from the lightly loaded case through the use of a simple upstream velocity profile changes from one uniform stream to scaling factor. In addition, expressions are developed for the power, another through a layer with a steep velocity gradient, there is a thrust, and induced efficiency for the heavily loaded system which significant gain (loss) in lift. if the vorticity is in the same (opposite) may also be extracted from the lightly loaded results. Some sample sense as the circulation around the wing. A more drastic change in results are presented for a ducted fan with 2,4, 6;and 8 blades with lift occurs, however, when the circulation is in the opposite Sense as loadings from a light load to the static thrust condition. (Author) the vorticity. This occurs when the layer with a steep velocity gradient passes over the upper surface of the airfoil. This phenom- enon of a sudden change in lift is of importance when an airplane encounters an atmospheric disturbance. M.M. A71-12678 ## New longitudinal handling qualities data - Carrier approach. George E. Miller (Princeton University. Princeton, N.J.). (American Institute of Aeronautics and Astronautics, Guid- ance, Control, and FliMt Mechanics Conference, Prk&ton, iW., A71-12682' #' A new model performance index for en- Aiiy. ;a^-20, 1969, Paper 69897.1 Journal of Aircraft, vol. 7. gineering design of flight control systems. Herman A. Redies Nov.-Dec. 1970, p. 519-522.9 refs. (NASA, Flight Research Center, Edwards, Calif.) and H. Philip Results of an aircraft flying qualities research program Whitaker (MIT. Cambridge, Mass.). (American Institute of Aero- sponsored the Naval Air Systems Command. Navy pilot by test nautics and Astronautics, Guidance, Control, and Flight Mechanics evaluations in form of Cooper ratings and specific comments of the Conference, Princeton, N.J., Aug. 18-20, 1969, Paper 69-885.) several longitudinal handling characteristics were obtained for a Journal of Aircraft, vol. 7, Nov.-Dec. 1970, p. 542-549. 12 refs. simulated carrier landing task. The investigation made use of a Grant No. NGR-22-009-229. variable stability aircraft which accurately simulated the longitudinal Description of the ttteor; and application of a new performance short period response characteristics and the effects of atmospheric index, the Model PI, that brings engineering design specifications into turbulence. The f!ying quaiires associated with variations in short the analytical design process. A parameter optimization design period frequency, lift curve slope, and the use of direct lift control procedure is established that starts with practical engineering are presented. The data are compared with similar data obtained specifications and uses the Model PI as a synthesis tool to obtain a from flight and ground simulator tests. A gradual decline in good satisfactory design. The Model PI represents a new criterion for handling qualities was noted for reductions in short period frequency approximating one dynamical system by another, based on a novel and lift curve slope. Direct lift control using a thumb controller was geometrical representation of linear autonomous systems. It is shown found to be desirable for this task on all configurations. (Author) to be an effective performance index in designing practical systems and to be substantially more efficient than a comparable model- referenced integral squared error performance index. The design A71-12679 # Transonic buffet characteristics of a 60- procedure is demonstrated by designing a lateraldirectional stability swept wing with design variations. J. F. Mayes, M. E. Lores. and-H. augmentation system for the X-15 aircraft. (Author) R. Barnard (LTV Aerospace Corp., Dallas, Tex.). JournalofAircraft, vol. 7, Nov.-Dec. 1970, p. 524-530. 13 refs. Results of wind-tunnel tests of a typical swept-wing fighter aircraft conducted to determine the improvement in the buffet-onset lift coefficient resulting from wing camber and from leading and A71-12683 # Aircraft performance benetits from modam trailing edge deflection. The coefficient was determined from trailing control systems technology. Richard B. Holloway. Paul M. Burris edge pressure, wing-root bending moment, fluorescent oil flow (Boeing Co.. Wichita, Kan.), and Robert P. Johannes (USAF, photographs, and force data. All four types of data are arranged in a Wright-Patterson AFB, Ohio). (American Institute of Aeronautics composite graphical form to insure proper Selection of the co- and Astronautics, Aircraft Design and Operations Meeting. Los efficient and to identify the location on the wing where separation Aneles. Calif., July 14-16, 1969, Paper 69-767.) Journal of Aircraft, first occurs. Results at Mach 0.9 showed that 0.2 increase in camber VOI.7, Nov.-Dw. 1970, p. 554553. (airfoil design lift coefficient) increased the coefficient approxi- In conventional approaches to aircraft design. the flight control mately 0.08; a 5deg leading edge droop 0.15; and 3 5deg inboard system is designed to meet specified handling requirements after the trailing edge flap 0.12. Analysis of design trends shown by previous configuration is optimized to meet the mission performance require- experimental results are described for the effects of wing thickness ments. The performance benefits which accrue by considering the ratio. sweep, aspect ratio, and camber on the coefficient. Specific control system design throughout the configuration studies am buffet problems related to variable swept wings are discussed. discussed. The approach employed to integrate control system design (Author) into aircraft design engineering, the discussion of control techniques

27 A71 -12684 and their impact on the design, and the performance benefits induced drag by the Vortex Lattice Method (VLMI The scaled expected are elements of the work. Concepts to be examined include spanwise distribution of induced drag is shown and IS compared to relaxation of inherent static stability, ride quality control, flutter the best results obtained by Garner, Hewitt, and Labrujere (1968) margin control, and maneuver load control. (Author) The comparison IS excellent Further cornpansons with results of other methods are made The VLM can also be used for estimating certdin quasi steady rotary derivativer required In stability and control analyses MM A71-12684 # Pilot and aircraft augmentation on the C-5. Leo J. Mueller (Honeywell, Inc., Minneapolis, Minn.). Journal of Aircraft, vol. 7, Nov.-Dec. 1970, p. 553-556. Description of some approaches, both simulation and actual, A71-12719 # Nonlinear conical gas flows ihieiineinyi k~fii- used it- testing the C-5 military transport. The gross weight, large cheskie techeniia gaza). 6.M. Bulakh. Moscow, Izdatel’stvo Nauka, pi:ch, ywinertia. and low landing speed of this aircraft presented 1970. 344 p. 234 refs. In Russian. new problems. These problem areas have been alleviated by an Aii a:;emp: is mde ?o consider all the essential problems arising augmentation system designed to improve the handling qualities of in the theory of nonlinear conical gas flows. The general properties the C-5. The aircraft’s pilots were able to log more than 500 hr on a of conical gas flows and certain particular forms of such flows are simulator before the first flight. This simulator was a valuable assist reviewed. Among the particular forms considered are axisymmetric in the analysis and design of the augmentation system. M.M. flow past a circular cone, axisymmetric conical flows, flow past pyramidal bodies, and simple conical waves. In considering super- sonic conical gas flows, a study is made of flow past conical bodies entirely contained in the Mach cones of the unperturbed flow. Flow A71-12687 # A system analysis view of aerodynamic past a circular cone at an angle of attack, flow past conical bodies coupling. Peter Hamel (Braunschweig, Technische Universitat, Braun- with flow separation, flow past conical bodies located outside the schweig, West Germany). Journal of Aircraft, vol. 7, Nov.-Dec. 1970, Mach cones of the unperturbed flow, and flow past conical bodies p. 567-569. 7 refs. partly projecting from the Mach cones of the unperturbed flow are Application of system analysis methods to stability investiga- also investigated. In considering hypersonic conical gas flows, a study tions of coupled flight vehicle motions. An effort is made to give the is made of flow past conical bodies in cases where the head shock stability and control analyst some feel of and a simple procedure for waves are attached only to the tips of the bodies and of flow past determining aerodynamic coupling effects due to steady sideslip. On conical wings in cases where the head shock waves are attached to A.B.K. the basis of the feedback analogy, it is shown that the root locus the leading edges of the wings. technique is a powerful tool for inspecting and predicting the single contributions of the aerodynamic coupling derivatives on the characteristic roots for a wide variety of aircraft classes. M.M. A71-12722 Aircraft power plants: Systems and devices (Aviatsionnye silovye ustanovki: Sistemy i ustroistva). N. T. Domotenko, A. S. Kravets, A. I. Pugachev, and T. I. Sivashenko. Moscow, Izdatel‘stvo Transport, 1970. 352 p. 62 refs. In Russian. A71-12688 Pitot inlet additive drag. E. L. Crosthwait p General problems of the design and operation of aircraft power (General Dynamics Corp., Fort Worth, Tex.). Journal of Aircraft, plant equipment are considered. A method of designing aircraft vol. 7, Nov.-Dec. 1970, p. 569, 570. 6 refs. power plant systems and devices is presented. The assumptions made Description of a unique Pitot inlet additive drag approximation for teaching purposes have little effect on the accuracy of the results defined in simple terms of capture area ratio, together with static and make it possible to obtain comparatively simple formulas and pressure coefficient and total pressure coefficient ahead of the inlet. graphs which are convenient for monitoring the operation of the The values obtained for the approximate expression for additive drag systems and devices and for designing them. Data concerning the coefficient for a specific Pitot inlet are compared with analytical layout of power plants, the attachment of engines and gondolas, the levels presented by Sibulkin (1954) and others (Gibbings, 1961; characteristics of propellers, and the control of power plants are Seddon, 1954). The agreement is well within plus or minus 0.003. presented. Fuel systems, oil systems, cooling systems, deicing M.M. systems, fire-fighting systems, suction systems, and exhaust systems are considered, Problems in monitoring and operating power plant equipment are discussed. A.B.K.

A71-12690 # Upwash interference on a jet flap in slotted tunnels. ChingFang Lo (ARO, Inc., Propulsion Wind Tunnel Facility, Arnold Air Force Station, Tenn.). Journal of Aircraft, vol. A71-12723 Threads used in the aircraft industry: Hand- 7. Nov.-Dec. 1970, p. 572-574. 8 refs. book (Rez‘by, primeniaemye v aviatsionnom proizvodstve: Description of the upwash interference on a two-dimensional Spravochnik). A. E. Vaisman. P. S. Denisov. 0. V. Morozenko, T. V. jet-flap wing in a slotted-wall tunnel. The formulation is based on the Beglova, and V. Barabasheva. Moscow, Izdatel’stvo Mashinostroe- small disturbance theory and the linearized model of the jet-flap 2. nie, 1970. 368 p. 18 refs. In Russian. wing as derived by Spence (1956, 1957). An analytical solution is Standardized definitions are given for the basic parameters of developed for the upwash interference, and some numerical results threads used on aircraft bolting and coupling elements, and criteria are shown graphically. M.M. are listed for quality control and reliability requirements. Numerous practical recommendations are included for selecting thread profiles and configurations as a function of the materials employed and the conditions of operation. The text consists of very detailed tables of A71-12691 H Spanwire distribution of induced drag in sub- specifications for various applications as prescribed by the Soviet sonic flow by the vortex lattice method. T. P. Kalman, J. P. Giesing GOST standards. Practical reference data are given for thread cutting (McDonnell Douglas Corp.. Long Beach, Calif.), and W. P. Rodden. instruments and tools, and cutting processes are explained for inner Journal of Aircrafr, vol. 7. Nov.-Dec. 1970, p. 574-576. 15 refs. and outer threads with emphasis on special demands posed by Research sponsored by the McDonnell Douglas Independent Re- aircraft materials and high-tolerance requirements. Special quality search and Development Program. control and diagnostic methods are recommended, and assembly Review of the calculation of the spanwise distribution of operations for threaded components are discussed. T.M.

28 A71 - 12094

A71-12740 The Mirage 'Milan' (Le Mirage 'Milan'). Transactions, vol. 1, Nov. 1970, p. 3101-3105. 16 refs. Jacques Morisset. Air et Cosmos, vol. 8, Nov. 21, 1970, p. 21-28. In Hot-salt stress-corrosion threshold data were determined for the French. Ti-8Al-1 Mo-1 V alloys under simulated turbineengine compressor Description of the Mirage 'Milan' ground attack fighter, which is environmental conditions. Threshold data determined by residual the latest addition to the Mirage 3 and Mirage 5 families. It can tensile ductility were demonstrated to be a more sensitive indication assure air superiority up to Mach 2. It embodies improvements which of hot-salt stress-corrosion than threshold data determined from consist of a forward mounted retractable 'moustache,' which aids in crack observations. Specimens that had been stress-relieved by increasing lift, a more powerful engine, and modern electronic chemically milling exhibited drastically lower threshold stresses than navigation and attack equipment. Low speed handling and operation did specimens in the as-machined condition. A Mach 0.7 airflow with from short airstrips with steep approaches are superior, and the a dewpoint of -120 F did not significantly reduce stresscorrosion maintenance rate is very low. F.R.L. when compared to static air conditions. (Author)

A71-12892 The impact of helicopter operations on aii A71-12746 Concorde and the air travel market. E. H. traffic control in the 1970s. James G. McFadden (US. Army, Office Burgess (British Aircraft Corp., Ltd.. Filton. Bristol, England). Em of the Director of Defense Research and Engineering, Washington, Air World, vol. 23, no. 2, 1970, p. 4951. D.C.). (Institute of Navigation, National Air Meeting on Air Traffic Discussion of the economical and operational prospects of the Control in the 1970s. St. Louis, Mo., April 14-16, 1970, Proceed- Concorde. Studies and experience indicate that the high speed of ings, p. 27-39.) Navigation, vol. 17, Fall 1970, p. 246-252. travel on Concordes would appeal to passengers notwithstanding a The integration of helicopter operations into the clvil air traffic 35% increase in fares. It is expected that a profitable operation of the system has been initiated. The quantitative impact in the next decade Concorde will prove realizable. It is maintained that a mixed fleet of is difficult to forecast but it appears that in total numbers, Concordes and subsonic airliners, tailored to the operator's route and helicopten will not create particularly great problems in air traffic traffic characteristics, will achieve a higher return on capital control. They will, however, require special systems and procedures, investment than an all-subsonic fleet of equivalent capacity. V.Z. particularly in terminal areas. Their slow operating speeds make them generally incompatible with fixed wing operations. Further, from the standpoint of operational efficiency, their VTOL capabilities and high maneuverability must be exploited in air traffic management. A71-12840 # Meteorological conditions of supersonic air- Military experience in Viet Nam provides valuable insight into craft flights (Meteomlogicheskie udoviia poletov sverWvukovykh operation of helicopters in mixed fixed and rotary wing terminal samoletov). I. G. Pchelko, N. V. Petrenko, and G. S. Buldovskii. environments. (Author) Leningrad, Gidrometeorologicheskoe Izdatel'stvo, 1970. 164 p. 147 refs. In Russian. The structure of the atmosphere is analyzed, with emphasis on A71-12893 Analysis of a capacity concept for runway and the general characteristics of meteorological conditions in the finalappmach path airspace. A. J. Goldman (National Bureau of troposphere and stratosphere. Seasonal regularities of atmosphwic Standards, Operations Research Section, Washington, D.C.). (Insti- circulation in the stratosphere are outlined, and the relationhip tute of Navigation, National Air Meeting on Air Traffic Control in between stratospheric and tropospheric processes is examined. the 1970's. St. Louis, Mo., April 14-16, 1970, Proceedings, p. Stratospheric cyclones, anticyclones, jet streams, and warmings are 119131.) Navigation, vol. 17, Fall 1970, p. 253-259. 8 refs. described, together with typical vertical wind and temperature This paper describes some highlights of a short-term analytical distributions. The main features of supersonic flight are explained in study leading: (a) to a 'maximum thvxghpct rate' capacity concept terms of relationships between the atmospheric Darameters and the in the context of a service facility handling a stream of customers of aircraft speed, altitude. fuel consumption, and sonic boom forma- various types, and (b) to the specialization of this concept to a tion. Current knowledge about turbulence in the stratosphere is stream of IFR landings at a runway. The specialization is shown to surveyed, and data are given for turbulence zone characteristics, be representable by a simple mathematical formula, of potential meteorological sources of turbulence, and prediction of aircraft value (for example) in connection with costeffectiveness analyses of buffeting in turbulence. The effects of convective activity, icing, proposed changes in ATC equipment or procedures. Directions for ozone. and solar flare radiation are examined. T.M. further research are identified, and the paper concludes with some general remarks on conceptual difficulties associated with the notion of 'capacity. (Author)

A71-12852 A preliminary investigation of gas turbine combustor modelling. Dean C. Hammond, Jr. and Arthur M. Mellor (Purdue University, Lafayette, ind.). Combustion Science and A71-12894 Timesynchronized approach control.flalph L. Technology, vol. 2, Nov. 1970, p. 67-80. 27 refs. Grant No. Erwin, Jr. (Boeing Co., Renton, Wash.). (Institute of Navigation, DA-AE-07-69-0756. National Air Meeting on Air Traffic Control in the 1970s. St. Louis, An analytical model for the design of tubular gas turbine Mo.. April 14-16. 1970, Proceedings, p. 163-173.) Navigation, vol. combustors is developed by combining the desirable portions of 17, Fall 1970, p. 26B266. several models from the literature. A literature survey covering the Time-synchronized approach control is a concept that takes three major theories of combustor analysis, turbulent flame speed, advantage of available aircraft precision navigation and guidance microvolume burning. and stirred reactors is briefly summarized. capabilities. It combines these with advanced ATC equipment to Based on the results of the literature survey a combustor model provide an improved method of air traffic control. The basic concept composed of stirred reactors is proposed. A kinetic formulation for is for ATC to assign each aircraft a threedimensional approach path the combustion of propane in a singlestaged stirred reactor is and schedule that the aircraft must then maintain with an error that developed, and limited results are presented. (Author) is small compared to the allowable longitudinal spacing between approaches. The advantages of reduced control workload and increased control precision are used as a basis for computing potential benefits in terms of inceasing peak-hour operations A71 -12885 Hot-salt stress-corrosion of a titanium alloy in without increasing delay. This paper describes the concept. the a dynamic air environment. Hugh R. Gray and James R. Johnston airborne and ground-based equipment capabilities, the expected (NASA, Lewis Research Center, Cleveland, Ohio). Metallurgical performance, and the potential benefits. (Author)

29 A7 1- 12895

871-12895 Avoiding collisions in a timely manner..Robert described, together with a brief summary of the fiber processing and E. Perkinson (McDonnell Douglas Astronautics Co., St. Louis, Mo.). properties as an aid to preliminary design studies. (Author) (Institute of Navigation, National Air Meeting on Air Traffic Control in the 1970s. St. Louis, Mo., April 14-16, 1970, Proceedings, p. 185-198.) Navigation, vol. 17, Fall 1970, p. 267-276. 7 refs. The Air Transport Association Collision Avoidance System is in its final stages, and a number of programs have been conducted over A71-12911 # A reliable high temperature transducer for the last year to verify and confirm assumptions made in the system. engine vibration measurement. R, Hatschek (Vibro-Meter, S.A.. The results of these programs are discussed in this paper, and the Fribourg, Switzerland) and G. Schofield (Vibro-Meter, Ltd., verification of systeln concepts and times is discussed based on: (1) a Manchester, England). Aircraft Engineering, vol. 42, Nov. 1970, p. computer simulation program IO verify the j.y's.tein pa:amc:c::, 25-27. accuracies, and maneuver times; (21 a program to verify pilot Discussion of the design and fabrication of reiiabk high capability to observe and react to the CAS displays under instrument temperature transducers for engine vibration monitoring in the flight load conditions in airline cockpit simulators; (3) the work done difficult environment of modern jet engines. Design considerations by NAFEC in analyzing probability ot alarm under reai-iiie CWB- aii given !or o~vermmin~the difficulties of fabrication due to the ditions; and (4) the final proof-of-the-pudding flight test that was temperature, acoustic noise, pressure, humidity and other factors of conducted last fall on the CAS systems supplied by three electronics a jet engine environment. The properties of the piezoelectric companies. (Author) materials used are analyzed. V.Z.

A71-12896 Results of the ATA CAS flight test program. Martin J. Borrok and David C. Rider (McDonnell Douglas Corp., St. A71-12912 # Development testing of the RB.211 turbofan Louis, Mo.). (Institute of Navigation, National Air Meeting on Air engine. Aircraft Engineering, vol. 42, Nov. 1970, p. 28, 30. 31. Traffic Control in the 1970'5, St. Louis, Mo., April 14-16, 1970, Account of a test program for the development of the advanced Proceedings, p. 199-213.) Navigation, vol. 17, Fall 1970, P. 278-289. RE.211 turbofan for the Lockheed L-1011 airliner. Test equipment The Collision Avoidance System Flight Test and Evaluation of the Aerodynamic Test Facility at Hucknall, including open air test Program was conducted by the Martin Marietta, Baltimore Division, beds, an RB.211 flying test bed and a pilot's engine, is described. The under contract with the Air Transport Association of America. The instrumentation techniques used in tests are outlined. V.Z. purpose of the test program was to evaluate the compatibility and effectiveness of the Collision Avoidance System as set forth in the airline industry CAS specification. ANTC Report No. 117. CAS equipments designed and built by three companies, Bendix Avionics, A7 1-12924 Goniometry by laser gyro (Goniombtrie par McDonnell Douglas and joint team of Sierra Research Corporation gyromhtre laser). J. M. Lamarre and J. J. Roland (CNRS, Service and Wilcox Electric Company, were furnished for this test and d'Aeronomie, Verrieres-le-Buisson, Essonne. France). L'Onde Elec- evaluation program. A total of 124 CAS test flights (greater than 300 trique, vol. 50, Nov. 1970, p. 869-871. In French. Research flight hours) were flown from 6 June 1969 to 19 November 1969. supported by the Direction de Recherches et Moyens d'Essais. From the total 124 flights, 75 flights (210 flight hours) yielded Description of laser gyro test manipulations, and assessment of sufficient quantitative data for adequate analysis of the CAS. the results of measurements of fluctuations and angular measure- Approximately 260 intercepts, the majority involving two aircraft ments at low rotational velocities. The principal characteristics of a encounters, were flown. Test results from this program show that goniometry device improved within the framework of inertial CAS operating normally in the synchronized mode, per ANTC 1 17 detection are considered, noting, in particular, a countuplcountdown specification, provide the proper pilot command in adequate time to detection system developed for this purpose. A.B.K. perform the evasive action to prevent a potential midair collision. (Author)

A71-12935 Utilization of a niobium alloy in the fabrica- A71-12909 # Inlet flow field simulation techniques for tion of a hypersonic vehicle (Utilisation d'un alliage de niobium dans engine/compressor testing. J. L. Younghans, M. T. Moore, T. P. la rbalisation d'un vbhicule hypersonique). Perez, Syre (Trefimbtaux Collins, and J. G. Direnzi (General Electric Co., Evendale, Ohio). GP, Argenteuil, Val-d'Oise, France), Billon (Societe Nationale Indus- i Aircraft Engineering, vol. 42. Nov. 1970, p. 12-17. trielle Aerospatiale, Paris, France), Pichoir, and Guyot (ONERA, Development of an inlet flow field simulator design for ChBtillon-sous-8agneux, Hauts-de-Seine, France). lDil&ation Gin.+- engine/compressor tests to ensure inletlengine compatibility for a rale a la Recherche Scientifique et Technique and Direction des stable operation under all flight conditions. The available distortion Recherches et Moyens d'Essais, Colloque sur les Journees Niobium. testing devices (distortion screens, a discrete frequency generator, a Paris, France, Ocr. 20,21, 1969.)Revue de Physique Appliquie, vol. pulse jet, a turbulator) are reviewed briefly, showing their limited 5, June 1970, p. 455-465. In French. efficiency. Ramp angle effects, screen location effects, and diffuser Review of the various studies performed by some of the length effects are considered. The good simulating performance of contributors to the VERAS project, an experimental structure for a the proposed simulator is demonstrated. V.Z. hypersonic glider model involving the use of a niobium-based alloy. The Pechiney group perfected the formulation and processing of the alloy, and determined its general characteristics (mechanical proper- ties, resistance to oxidation, etc.), which are presented in tabular A71-12910 # Preliminary design of structural components in form. The Nord,Aviation Company worked out the described carbon fibre reinforced plastics and metals. A. S. Henney (Ministry full-scale technology of sandwich panel fabrication and protection by of Technology, London, England). Aircraft Engineering, vol. 42. appropriate coatings. The ONERA group performed a comprehensive Nov. 1970, p. 18-24. 30 refs. oxidation prevention study - i.e., selection of the protective coating The importance of the utilization of carbon fibers in commer- and perfecting of the coating application method . whose specific cially useful as well as experimental structures is discussed. This may application results are presented in detail, following an outline of the be achieved by using the fibers in conjunction with conventional general features of this study. It is noteworthy that some of the sheet metal components, as a preliminary step toward the 100 per techniques developed in the course of these studies have been cenr reinforced plastic structure. A few such applications are earmarked for use in the space shuttle proiect. M.V.E.

30 ~~

A71-12939

A71-12939 ProMsms involvsd in thc application ot niobium alloys to turbine bbder (ProbYmer pods pour I'application des alliages de niobium aux suber de turbine). G. Gauje and R. Brunetaud (SNECMA, Paris, France). /D&I&tion Gedrale a la Recherche Scientifique et Technique and Direction des Recherches et Moyens dlEssais. Colloque sur les Jour&s Niobium, Paris, France, Oct. 20, 21, 1969.1 Revue de Physique Appliquk, vol. 5, June 1970. p. 513-518. In French. Review of advantages gained from the use of niobium alloys for the hottest and mobile parts of a gas turbine. Using these alloys, it is expected that the working temperatures can be up to 150 C higher than those possible with currently used Ni-Cr alloys. The critical problem in the development of niobium alloys is shown to be the development of suitable protective coatings. The relatively high brittleductile transition temperature of these alloys is shown to cause some Concern. Improvements which have to be made to reach the phase of engine development are reviewed. Z.W.

31 N71-10115

Penetration of sound into a body of water from a simulated airborne sonic boom was measured in an acoustically scaled experiment Dynamite caps were used to produce spherically spreading N-waves which impinged upon the water Microphones at the water surface and hydrophones at various shallow depths were used to measure the exponentially attenuating penetration of the airborne pressure field into the water under total reflection conditions Agreement between the scaled experimental STAR ENTRIES measurements and predictions based on existing theory was generally good Application of the theory to the case of actual sonic booms impinging upon the ocean and comparisons with measurements of typical deep-ocean ambient noise indicate that underwater sonic boom noise will be discernible only at very low frequencies and at shallow depths Pressure fluctuation spectrum levels due to N71-10021*# Mechanical Technology. Inc.. Latham. N.Y. surface waves will be higher than levels due to sonic booms FLEXIBLE ROTOR BALANCING BY THE EXACT Author POINT-SPEED INFLUENCE COEFFICIENT METHOD Final Report Juergen M. Tessarzik [1970] 1 15 p refs (Contract NAS3-13473) (NASA-CR-72774: MTI-70TR59) Avail: NTIS CSCL 131 A test program was conducted to confirm experimentally N71-101lo*# Air Force Flight Test Center, Edwards AF6. Calif. the validity of the exact point-speed influence coefficient method IFR EXPERIENCE WITH UNPOWERED, for balancing rotating machinery. and to assess the practical LOW-LIFT-DRAG-RATIO LANDING APPROACHES aspects of applying the method to flexible rotors. Testing was Peter C. Hoag and 6. Lyle Schofield ln NASA. Flight Res. Center performed with a machine having a 41-inch long. 126-pound rotor. Flight Test Results Pertaining to the Space Shuttlecraft Oct. The rotor was operated over a speed range encompassing three 1970 p 109-125 refs rotor-bearing system critical speeds: two rigid body criticals and Avail: NTlS CSCL 17G one flexural critical Rotor damping at the flexural critical was very The results of IFR flight studies are discussed and two low due to the journal bearings being located at the nodal points terminal area guidance schemes are presented specifically designed of the shaft The balancing method was evaluated for three for terminal area energy management and guidance of unpowered. different conditions of initial rotor unbalance. The method was found low L/D ratio vehicles. The studies involved the F-11t.4. F-704. to be effective and practical. Safe (and slow) passage through SI! aii: NS-5iB aircraft. The approaches considered include ILS. IFR. the critica! speeds was obtained after a reasonable number of and ground controlled. It was found that IFR approaches made in balancing runs. Success of the balancing method was. in large part. the N6-526 airplane were no more difficult to fly than similar due to the accuracy of the instrumentation system used to approaches with the smaller aircraft. In addition, ILS approaches obtain phase angle measurements during the balancing procedure. were found easier to perform than ground controlled approaches Author under the same conditions. D.L.G.

N71-10052*# National Aeronautics and Space Administratio” N71-10114~ Federal Aviation Administration, Washington. D C Langlev QF’SPJ-CC Ce$hier Langley Station Va Systems Maintenance Service LOW SPEED WINO-TUNNEL INVESTIGATION OF A SERIES REPORT ON SYSTEMS MAINTENANCE PROGRAM OF TWI N-KEE L ALL-FLEX1BLE PARAWINGS EVALUATION CONDUCTED IN THE EASTERN REGION, 22 Rodger L Naeseth Washington Oct 1970 103 p refs JULY-15AUGUST1969 (NASA TN-D-5936 L-7096) Avail NTlS CSCLOlC Oct 1969 42 p ref Low-speed wind tunnel studies were made to obtain the Avail NTlS static aerodynamic characteristics of a series of 10 twin-keel Significant strengths and weaknesses identified in the SMS all flexible parawings The parawings in flat planform had a evaluation of the Eastern Region maintenance program are leading edge sweep angle of 45 deg and generally a 20-percent summarized Findings are based on visits to sectors and Airway keel length cut off of the apex of the basically triangular shape The Facilities Branches (AFB) in the Region’s four areas (Washington. nose of each parawing model was contoured in such a manner that Cleveland, Boston and New York), to the Airway Facilities Division the airfoil sections in the center panel of the model had rounded (AFD) and other regional headquarters elements, and on study of leading edges Twin keel parawings were found to have improved pertinent documents It is concluded that budgetary limitations and performance characteristics as compared with single keel parawings other factors have affected SM program management and execution The maximum lift-drag ratios of the models ranged from 26 to Author 3 2 Results of a limited flight-test program indicated that the twin-keel parawings would glide when the rigging except for control-line length was set as determined in the small scale wind-tunnel tests Author N71-10115# National Transportation Safety Board Washington. DC SYSTEMS APPROACH TO ACCIDENT INVESTtGATION C 0 Miller [1969] 22 p refs Presented at Flight Safety Found Ann Seminar Montreux Switz 28 Oct 1969 N71-10094# Hydrospace Research Corp . Rockville. Md Avail NTlS PENETRATION OF SONIC BOOM ENERGY INTO THE The complex aerospace world has generated a systems OCEAN: AN EXPERIMENTAL SIMULATION Final Report management methodology to efficiently and effectively achieve John F Waters and Ray E Glass Jun 1970 55 p refs stated objectives in accident investigation The systems approach to (Contract N00014-70-C-0374. FA-70-WAI-185.) accident investigation is discussed wherein the resultant process (AD-711963. HRC-TR-288) Avail NTlS CSCL1/ 1 is referred to as accident inquiry management Author

33 N71-10116

N71-10116# Department of Transportation Washington D C instructions The Lockheed P-3C aircraft was chosen as the subject TRAVELER SERVICE STUDY for test and evaluation of the program The currently operational Jul 1970 334 p Prepared by Golightly and Co Intern Inc propeller of this aircraft was tested to compare the programs (PE 193300) Avail NTlS CSCLO5B prediction of aircraft performance against flight test information An The principal traveler service problems in domestic intercity air attempt was then made to select a propeller which could provide bus and rail transportation were studied The specific experiences better performance under the same constraints as those imposed and problems of the young the elderly the poor the ill and the in design of the operational propeller Author (TAB) handicapped traveler received particular attention Over 200 oassenqers were interviewed during June and July 1970 in terminals located at New York Chicago ana nOubiGn lii:c~v!e*.vc were conducted at Pennsylvania Station Port of New York Authority Bus N71-10126# Royal Radar Establishment. ividlvatn (Cngland) Terminal East Side Airlines Terminal and LaGuardia Airport in New RRE NEWSLETTER AND RESEARCH REVIEW, NO. E Yo-' CI Hgrp International Airport in Chicago and the international 1969 151 p refs airport and private bus terminals in Houston Travelers ai0 IdW Conyright Avail NTlS enforcement officials and carrier personnel at these terminals were Newsletters are presented on research in electronics. soiiri also interviewed The approximate distribution by mode of the state devices. microwave equipment. electro-optics. magnetic fields. passenger interviews was air 57 percent bus 28 percent and semiconductors. integrated circuits. and their aDDlications rail 15 percent Copies of the questionnaires used for passenger interviews are appended Author

N71-10163# Royal Radar Establishment, Malvern (England). A TRAFFIC SAMPLE FOR AIR TRAFFIC CONTROL MODEL N71-101le# France. Direction de la Meteorologie Nationale. EVALUATION Paris. R. W. Greaorv In irs RRE Newsletter and Res. Rev., No. 8 1969 OBSERVATION AND MEASUREMENT OF GROUND VISIBILITY. AUTOMATIC CALCULATION OF THE VISUAL 4P Copyright. Avail: NTlS RANGE OF AIRPORT RUNWAYS [OBSERVATION ET Computer models are becoming increasingly important as MESURE DES VlSlBlLlTES AU SOL. CALCUL a means of testing new ATC techniques. This traffic sample was AUTOMATIQUE DE LA PORTEE VISUELLE DE PISTE SUR generated as an input to such models; for the traffic situation in LES AERODROMES] the London terminal area during the peak summer periods of the C. Perrin de Erichambaut and A. Eettan Aug. 1970 57 p refs 1960s. The sample relates only to movements at. Heathrow. In FRENCH Its Monographie No 76 Gatwick. and a third London Airport. It takes no account of minor Avail: NTlS airport traffic, but it does include traffic overflying London. It IS based on the following assumptions: (1) All three airports are CONTENTS: omni-directional. (2) Heathrow and the third London Airport each 1. OBSERVATION AND MEASUREMENT OF GROUND have a maximum sustainable movement rate of 70 per hour. while VISlElLlTY C. P. de Erichambaut p 1-29 Gatwicks maximum sustainable rate is 45 per hour. (3) All three airports aresubject to noise restrictions and, as a result. these rates 2. AUTOMATIC CALCULATION OF THE VISUAL RANGE can only be maintained between the hours 0700 to 2300. (4) OF AIRPORT RUNWAYS A. Eettan p 31 -51 refs SSTs operating in the London area have a performance similar to subsonic jets. Author

N71-10120# France Direction de la Meteorologie Nationale Paris AUTOMATIC CALCULATION OF THE VISUAL RANGE OF N71-10164# Royal Radar Establishment Malvern (England) AIRPORT RUNWAYS [CALCUL AUTOMATIQUE DE LA A PROPOSAL FOR PRIMARY RADAR AUTOMATIC PORTEE VISUELLE DE PISTE SUR AERODROME] TRACKING IN TERMINAL AREAS A Eettan In ifs Observation and Meas of Ground Visibility Aug T Euckley In irs RRE Newsletter and Res Rev, No 8 1969 1970 p 31 51 refs InFRENCH 3 p refs Avail NTlS Copyright Avail NTlS An operational system to measure compute and supply With the ever-increasing density of civil air traffic in terminal runway visual range data automatically is discussed Data are taken areas such as that of London, there IS a case to be made. on for luminance atmospheric transmission and diffusion and visibility grounds of both the safety and capacity of the air traffic control range of the running track The stability and performance of the system. for a three-dimensional radar system Such a system must system are also discussed Trans1 by E H W be capable of automatically and accurately tracking all the aircraft in a terminal area One proposal for such a system IS outlined and the more obvious advantages are highlighted Author

N71-10122# Naval Postgraduate School Monterey Calif COMPUTERIZED AERODYNAMIC OPTIMIZATION OF AIRCRAFT PROPELLERS N71-10167# Federal Aviation Administration Washington D C Robert Linford Shaw (M S Thesis) Jun 1970 102 p refs DATA FILE EDITING AND PRELIMINARY ANALYSIS (AD 710356) Avail NTlS CSCL 1/3 CLEVELAND-HOPKINS AIRPORT ACCESS STUDY The objective of the thesis was to develop d practical computer May 1970 179 p system for use of empirical data in the aerodynamic optimization Avail NTlS of aircraft propellers The system was designed for use with the A survey is presented on types of transportation used to reach IBM 2741 on line computer terminal This program provides the Cleveland Hopkins Airport before and after the construction iiistructions to the operator during execution and allows interaction of direct rapid rail trahsit service The factors influencing the by the operator for input and alteration of data and for program demand for rapid rail transit to airports were determined J A M

34 N7 1- 10249

N71-10170# Federal Aviation Administration Washington. D C Rawinsonde wind profile data provide accurate wind shear THE DEMAND FOR USE OF WASHINGTON NATIONAL information for intervals Delta L > or = to 1 km. To specify wind AIRPORT shears for Delta z < 1 km for space vehicle design, detailed wind JosephV Yance Jan 1970 82 p refs profile information like that provided by the FPS-16 radar/Jimsphere Avail NTlS system or an extrapolation procedure is required. It is assumed that The air carrier demand for use of Washington National any realtzation from an ensemble of wind profiles can be represented Airport (DCA) is studied (based on a CAB survey of flights) at the in terms of a Fourier integral. This permits the calculation of the Washington-Baltimore area airports to determine the feasibility of ensemble standard deviation and mean of the corresponding shear a pricing system for landing and takeoff slots to reduce the ensemble for any altitude and shear interval Delta z in terms of congestion at DCA The two components of passenger traffic the power spectrum of the ensemble of wind profiles. To czlculate enplanements (and deplanements) at area airports. and through how the mean and standard deviations depend on Delta z, it is traffic are analyzed It IS concluded that a pricing palsy would result in assumed that (1) the wind profile power spectrum behaves like k economic benefits to the airport. communtty. and the passengers to the minus 2.4 power at sufficiently large values of the vertical FOS wave number k. (2) the vertical variation of the power spectrum can be neglected locally in the calculations of the ensemble mean and standard deviations of the wind shear. and (3) the probability N71-10171# Department of Transportation. Washington. D C distribution function of the standardized shear variate is invariant FIRST FEDERAL AIRCRAFT NOISE ABATEMENT PLAN, FY with Delta z. The results of these calculations show that the mean 1969 -1970 and standard deviations of the shear ensemble, as well as the NOV 1969 79 p refs shear for any percentile. asymptotically behave like (delta z) to the Avail NTlS 0.7th power. This result is in excellent agreement with shear data The reduction of aircraft noise is studied for achieving from Cape Kennedy. Florida. Author compatibility between airports and the adjacent metropolitan environs The sonic boom phenomenon and the effects of meteorological conditions on the magnitude are described The government and nongovernment research and development programs are presented wlth the emphasis of the noise reduction studies on airplane and N71-10247# Colorado State Univ., Fort Collins. engine design flight procedures. and reducing the impact of the TRANSPORTATION RESEARCH NEEDS RELATED TO CIVIL noise on communities FOS ENGINEERING Robert F. Baker Jun. 1970 288 p refs Prepared in cooperation with Am. SOC of Civil Engr. (PB-193388: CER69-70C WT41) Avail: NTlS CSCL 15E -n- - .Ilr &;I riigineering research needs in the field of transporta- N71-10183# Air Force Academy Cdc! F:xk J Seiier iiesearch tion are reported. A program is drawn looking to the future needs of Lab the profession for the type of engineering information. data. and DETERMINATION OF REALISTIC PERFORMANCE findings best developed through purposeful research. The present TRADE-OFFS IN THE AIR-TO-AIR ROLE Final Report and immediate future needs for research in the civil engineering Roger W Gallington and David Finkleman Jul 1970 15 p refs aspects of transportation are discussed. Needed research in Presented at AlAA 2nd Aircraft Design and Operations Meeting. associated fields is indicated but not detailed Transportation is Los Angeles, 20 - 22 Jul 1970 Its AlAA Paper No 70-930 considered as a system made up of a grouping of parts, or (AD-710497. SRL-69-0007) Avail NTlS CSCL 1517 sub-systems. of social and economic programs The role of Recent air superiority fighter studies have failed to include transwrtation in soccie?;. a23 :he qnieiest that me civil engineer has in systematically the trade-offs between ordnance acd airciaft transportation are established A program of research is presented -apahiities Compromises among performance demands must be in considerable detail with estimates of the level of funding studied along with the capabilities of current technology in order to considered to be necessary if the profession IS to improve and arrive at the most effective weapons system within the enlarge its capabilities to meet the future needs for transportation state of the-art The investtgation described has led to the formulation of the society. Many subjects. such as, soil mechanics and of a realistic design philosophy which allows analysis of the foundations. structures. and environmental considerations, which interrelated demands upon armament detection capability. thrust are vital to overall development of a transportation system were speed and load factor Author ( TA 6) treated lightly. Author

N71-10184# Naval Postgraduate School, Monterey Calif A PILOT EVALUATION OF MOVABLE AND RIGID N71-10249# Technion-Israel lnst of Tech. Haifa AIRCRAFT CONTROLS INVESTIGATION OF HEAT TRANSFER IN BASE TYPE James Daniel Cole (M S Thesis) Jun 1970 82 p refs SUPERSONIC LAMINAR AND TRANSITIONAL SEPARATED (AD-709934) Avail NTlS CSCL 1/3 FLOWS A simulator facility employing a two-axis compensatory Josef Rom. Arnan Seginer. and Michael Green Apr 1970 48 p tracking task with a random-appearing signal was used to evaluate refs the performance of fifty-five pilot and pon-pilot :est subjects using (Contract F6 1052-70-C-0005) four separate control sticks--two movable and two rigid Pilot (AD-710347. TAE-111, ARL-70-0142. SR-1) CSCL20/4 acceptance of the rigid cockpit controllers was determined by Heat transfer rate distributtons were measured in the separated comparing individual pilot ratings of the sticks Author (TAB) regions of a two-dimensional backward facing step an axially symmetric backward facing step. a blunt two-dimensional base, a sharp protruding two-dimensional leading edge and in the leading N71-10240*# National Aeronautics and Space Administration edge bubble over the surface of a flat nosed two-dimensional Marshall Space Flight Center. Huntsville. Ala model The results of these measurements are compared with ON THE RELATIONSHIP BETWEEN SMALL-SCALE WIND measurements of heat transfer rates in various base type separated SHEARS AND WIND PROFILE POWER SPECTRA flows obtained in various wind tunnels and to a calculation of heat George H Fichtl 27 Oct 1970 32 p refs transfer behind a backward facing step based or. the integral (NASA-TM-X-64562) Avail NTlS CSCLO4B method In most of these investigations a high peak in the heat

35 N71-10273 transfer rate IS found to occur in the reattachment zone Maximum requirements associated with the implementation of specific heat transfer rate values of up to 10 times the flat plate heat demonstration activities and the regulatory issues assoclated with transfer rate are reported in various investigations An inverse i relation between the value of the peak heat transfer rate and the distance between the separation point to the position of the maximum heating in the reattachment zone is shown to exist Author (TAB)

N71 10280# Aerospace Corp El Segundo Calif Air Tra"sportation Program Royal Aircraft Establishment Farnborough (England) N71-10273# WESTERN REGION SHORT HAUL AIR TRANSPORTAXCN CUMULATIVE FREQUENCY DISTRIBUTIONS OF AIRCRAFT PROGRAM VOLUME 2 TECHNICAL REPORT Definition :A!:'r\!hlG GEAR LOADS [ZUR AUFSTELLUNG VON Phase Report,Jul 1970 LASTKOLLEKTIVEN FUER FLUGZEUGFAHRWkRKEj JUI 1370 2% p refs Snnnsored in part by the Western Conf 0 Euxbaum et al Jun 1970 27 p refs Trans1 into ENGLISH of the Council of State Govt from Luftfahrttech Raumfahrttech (West Germany) v 15 no 11 (ATR-71 (7190) 1 Vol 2) Avail NTlS 1969 p 269 274 The technical and analytical base studies are discussed (RAE LIE Trans 1462) Avail NTlS CSCLZOK The current state of the art and anticipated advances in aircraft The increased damage to modern aircraft landing gears caused avionics and ground systems are assessed primarily from the by frequently repeated loading necessitates detailed analyses of standpoint of identifying available hardware appropriate for near term the fatigue strength of landing gears similar to those carried Out demonstration applications Advanced hardware concepts for the on aircraft wings A provisional working foundation is presented for late 1970 1980 period and periodic addition of improved hardware the collection of all available load spectra whether based on are considered Tradeoff analyses competitive travel modes theoretical or experimental information The proposals offered equipment choices and system operating economics are discussed combine the present state of knowledge with some recent New analytical techniques were developed to assist in determining measurements and extend the ground covered by current theories the potentla1 viability of demonstration programs notable IS the Load cases which are critical from the fatigue viewpoint are transportation modal split program for determining traveler choice summarized and emphasis is placed on defining those data which among competlng modes of transport Author determine the cumulative frequency distributions of undercarriage loads D LG

N71 10283 # Bcll Aerospace Co Buffalo N Y N71-10276*# National Aeronautics and Space Administration. FINAL FLIGHT CONTROL SOFTWARE PACKAGE FOR Langley Research Center, Langley Station. Va. DIGITAL FLIGHT CONTROL AND LANDING SYSTEM EFFECT OF NOZZLE LATERAL SPACING ON AFTERBODY May1970 36 p DRAG AND PERFORMANCE OF TWINJET AFTERBODY (Contract NASl 2 2074) MODELS WITH CONVERGENT NOZZLES AT MACH NUMBERS UP TO 2.2 (NASA CR 110905 Rept 6200 93301 1) Avail NTlS CSCLO9B Donald L Maiden and Jack F. Runckel Washington Oct. 1970 The software required to mechanize the flight control system on 142 p refs an airborne computer is described The majority of the description (NASA-TM-X-2099; L-7192) Avail: NTlS CSCL 21 H is presented in the form of detailed engineering equations and Twin-jet afterbody models were investigated by using two functional block diagrams and only those functions that are peculiar balances to separately measure the thrust minus afterbody drag to the digital nature of the system are presented in the form of Author and the afterbody drag at static conditions and at Mach numbers digital flow diagrams and loglc equations up to 2.2 for a constant angle of attack of 0 deg. Hinged-flap convergent nozzles were tested at dry- and afterburner-power settings with a high-pressure air system used to simulate jet-total-pressure ratios up to 21 .O. Equal nondimensional area distributions were N71-10284'# Bell Aerospace Co Buffalo N Y maintained as the nozzle lateral spacing was varied. In addition to FINAL GUIDANCE SOFTWARE PACKAGE FOR DIGITAL the lateral-spacing study. afterbodies with recessed blunt bases FLIGHT CONTROL AND LANDING SYSTEM were investigated. and the effects of exposing primary nozzle flaps to May 1970 32 p free-stream flow were examined. The results indicate an increase (Contract NASl2 2074) in afterbody axial-force (drag) coefficient with increased lateral (NASA CR 111025 Rept 6200 933012) Avail NTlS CSCLO9B spacing for the shrouded and unshrouded configurationsforsubsonic The software required to mechanize the guidance system and supersonic Mach numbers. with the exception of the shrouded on an airborne digital computer is described The malority of the dry-power nozzle configurations at subsonic Mach numbers (for description is presented in the form of detailed engineering which the trend was opposite) Author equations and functional block diagrams and only those functions that are peculiar to the digital nature of the system are presented in the form of digital flow diagrams and logic equations Author N71-10279# Aerospace Corp El Segundo Calif Air Transportation Program WESTERN REGION SHORT HAUL AIR TRANSPORTATION PROGRAM VOLUME 1 DEMONSTRATION PROGRAM N71-10287# General Accounting Office Washington D C PLAN Definition Phase Report, Jul 1970 IMPROVEMENTS NEEDED IN THE MANAGEMENT OF E R Hinz Jul 1970 132 p Sponsored in part by the Western AIRCRAFT MODIFICATIONS. DEPARTMENT OF THE ARMY Conf of the Council of State Govt (6-157373) Comptroller General's Report to the Congress (ATR 71 (7190) 1-Vol 1) Avail NTlS Elmer B Staats 14 Jan 1970 26 p ref The representative demonstration opportunities and Avail Issuing Activity requirements in the Western Region are described Funding and The procedures used in the aircraft modification program management requirements to implement the program study and Dertinent maintenance and aircraft log records were reviewed

36 N71-10349

It was found that modifications in many cases are not applied PURSUIT-EVASION PROBLEMS OF TWO AIRCRAFT promptly the volume of modification results in work loads beyond the William L Othling Jr (Ph D Thesis) Jun 1970 118 p refs capacity of maintenance activities modification kits are apparently (AD-717055 DS/MC/67 1) Avail NTlS CSCL 1212 IGst by local using units. and kits in some instances are not The pursuit evasion aspect of the two aircraft combat problem received in time for economical installation during overhaul of IS introduced as a fixed time zero sum perfect information aircraft It is recommended that delays be specifically lustified. differential game A realistic aircraft model is presented for which adequate controls be established to ensure proper approval a solution of this combat problem is desired Because of the procedures management of aircraft modification be given immediate non-linear dynamics associated with this model an optimal attention by the Army and management controls be improved closed-loop solution cannot be obtained Three additional simplified I NEN aircraft models are introduced as approximations to the realistic model Optimal solutions and closed-loop control laws are obtained for each of these models Analysis of these solutions and control laws enables the formulation of an approximate closed-loop control N71-10294# Bell Aerospace Co Buffalo N Y law for use with the original realistic model Author (TAB) SYSTEMS PERFORM AN CE DE SI G N R EQU I REM E NTS SPECIFICATION FOR THE CH-46C HELICOPTER DIGITAL FLIGHT CONTROL AN0 LANDING SYSTEM Apr 1970 96 p refs (Contract NASl2 2074) (NASA CR 110889 Rept 6200 933033) Avail NTlS CSCLOlC N71-10339# Advisory Group for Aerospace Research and The performance design development and test requirements for Development Paris (France) an experimental digital flight control and landing system (DFCLS) SI BLI OG RAP HY OF DOCUMENTS CONTAl NIN G for the CH 46C helicopter were established The DFCLS was used NUMERICAL DATA ON PLANAR LIFTING SURFACES to demonstrate and evaluate flight control concepts under closely R Dat Aug 1970 63 p refs (AGARD R 574 70) Avail NTlS 1 monitored flight test conditions and was not intended to be an operational system Author The material presented covers the years 195i to 1968 in chronological order and lists documents that are unsuited to systematic classification but which nevertheless make a considerablt contribution to the literature on unsteady aerodynamic forces Emphasis is placed on experimental results and on comparisons between theory and experiment Program descriptions which may be useful as guides are presented and abstracts inrlilde ?he nafuie cf the ii~uiisana their importance Captions indicate the speed William Cockayne Walter Rusnak and Lvei S!hb ?v;q i970 range whether the results are theoretical or experimental whether 1 -,r IJJ p control surfaces are considered and whether pressure distributions (Contract NAS 12 2074) are given Consideration is limited to planar surfaces and to ‘NASA CR 111024 Rept 6200 933013) Avail NTlS CSCLOlC calculations resulting from the general formulation of the problem A set of control laws were defined for a digital approach Author and landing flight control subsystem The flight control subsystem includes six manual modes with varying degrees of pilot assistance and a fully automatic mode Guidance laws suitable for flight demonstration of the flight control system in an approach and landing under minimal visibtlity conditions were fwmlcla?ed A ea: N71-10347# Federal Aviation Administration. Washington, D C rime c -YICl;t~~~using a piloted cockptt was developed The flight THE THEORY OF AIR CARRIER DEMAND FOR SLOTS 1 control and guidance laws were mechanized on an IBM 7090 computer in a manner similar to that in which they could be JosephV Yance Jan 1970 35p refs mechanized on an airborne computer Performance criteria were (PB-193350) Avail NTlS established and automatic and pilot runs were made A guidance A study directed at exploring the possible use of airport and control configuration was established Subsystem requirements pricing in achieving optimal utilization of airports. particularly those and interfaces were defined to the device level A system signal in the Washington-Baltimore area, IS presented Author flow diagram was developed Author

N71-10349# Washington Univ Seattle EVALUATING THE NOISES OF TRANSPORTATION. PROCEEDINGS OF A SYMPOSIUM ON ACCEPTABILITY CRITERIA FOR TRANSPORTATION NOISE James D Chalupnik ed Apr 1970 406 p refs Conf held at Seattle 26 28 Mar 1969 (Contract DOT OS A9 0361 (P8-191 117 OST ONA 70 2) Avail NTlS Conference papers are presented on noise sources and measurement and individual and community iesponses The major topics covered are aircraft automobile and truck noise noise level measurement effects and evaluation psychophysical studies hearing damage background noise effects factors affecting judgement experiments and effect of pop group music on hearing measuring community responses to noise noise complaints and community action predicting community responses criteria for N71-10328# Air Force lnst of Tech, Wright-Patterson AFB. design and legislation subjective response to community noise Ohio School of Engineering origin and spread of public reaction to noise and traffic noise APPLlCATlON OF DIFFERENTIAL GAME THEORY TO investigation NEN

37 N7 1-10355

N71-10355# Federal Aviation Administration. Washington. D C cost of delay attributed to ATC. airport. and other causes during 1 Aviation Policy Div departure and arrival operations in terminal area Delay costs are SPECIAL STUDY FAA PROGRAM EFFECTIVENESS AND calculated by the reporting airlines and prrmardy represent direct I FACILITY CRITERIA INSTRUMENT LANDING SYSTEMS operating costs Author 1 Aug 1970 95 p refs Avail NTlS The problem of determining the extent to which a decisim model should be pursued for the purpose of making ILS investment :ec,;,cps 0s examined Alternatives are presented from this N71-10370# Regional Planning Commission. Cleveland, Ohio. viewpoint The methodology piesented for making I LS invesuiiiiii SURVEY RESULTS: CLEVELAND HOPKINS AIRPORT decisions represents the highest degree of sophistication which it ACCESS STUDY is believed feasible to consider Topics include a recommendation Jun. 1970 187 p Sponsored by the Dept of Transportation tnar inuiv,dual ccs!/beneflts studies be required to support requests Avail: NTIS for ILS facilities a definition of the recommended method for A statistical analysis was made of the mode of transportation Comparing costs and benefits a definition of the parameters to be to and from the airport before ana aiiai a Ji;cc! r~!!repd transit used and the methodology for estimating them (safety time service was provided from the central business district to the cancellation/diversions and all other benefits) and an examination airport. Among the findings are the following: 57.6% of the rapid of the analytical bases used in selecting parameters and methods transit riders are air passengers, 14.5% of the air passengers ride Author the rapid transit, including more than 25% of passengers with origin or destination in the transit service area: the use of private cars, taxis. and limousines decreased and the use of rented cars and courtesy vehicles increased: 4% of passenger-related visitors N71-10356# National Aviation Facilities Experimental Center. use the rapid transit: 8 4% of the airport employees rode a public Atlantic City. N J bus to work prior ti) the transit opening and 11.2% rode the A HISTORY OF THE NATIONAL AVIATION FACILITIES transit afterwards; and 17% of the riders are casual visitors. CENTER, 1958 1970 N.E N. Aug 1970 102 p ref Avail NTlS A narative account is given of the center's organization and reorganizations resources employee/management cooperation N71-10371# Regional Planning Commission Cleveland Ohio and technology The latter includes air traffic control, all weather DATA FILE FORMATS AND CODE DESCRIPTIONS radar communication aircraft safety bird hazards fire fighting and CLEVELAND HOPKINS AIRPORT ACCESS STUDY human factors engineering Activities of individual divisions are also Jun 1970 94 p Sponsored by Dept of Transportation considered NEN Avail NTlS The file formats and code descriptions are presented for the analysis of transportation to and from the airport befoie and after a direct rail rapid transit was provided from the central N71-10360# Federal Aviation Administration Washington D C business distrlct Air passenger airport employee and casual visitor AIR PASSENGER SURVEY, SELECTED TABULATIONS survey forins and parking lot and rapid transif interview sheets are included NEN CLEVELAND HOPKINS AIRPORT ACCESS STUDY Jun 1970 263 p ref Avail NTlS Results are presented from a survey of airport users at N71-10372# Federal Aviation Administration Washington. D C the Cleveland Hopkins Airport before and after the opening of the FAA STATISTICAL HANDBOOK OF AVIATION Cleveland Transit System (CTS) rail transit service to the airport 1969 287 p Three origin and destination surveys were conducted to obtain Avail SOO$275 NTlS information on both the trip to and from the airport and the trip Data are presented on major civil aviation activities for maker for four groups of airport users The user groups included the 11 year period ending 31 December 1969 The FAA National air travelers originating or terminating trips at Hopkins air traveler Airspace System. civil and general aviation airmen aeronautical related visitors (meeting or sending off passengers) casual visitors production and accidents are covered NEN (sightseeing on business buying tickets or restaurant patrons) and employees The number and percent of trips by mode and passenger residence travel purpose or land use at the local origin or destination of the trip are tabulated at district cordon area and N71-10386# bouthampton Univ (England) lnst of Sound and census tract levels The age sex income purpose duration of trip Vibration Research land use at the origin or destination and the means of access to THE RESPONSE OF, AND THE ACOUSTIC RADIATION or from the rapid transit system are shown by CTS station FROM PANELS EXCITED BY TURBULENT BOUNDARY passenger residence and direction of travel Maps of the CTS LAYERS Technical Report, 1 Dec 1966 30 Nov 1968 stations districts and census tracts are appended JM Edmond Szechenyi Wriqht Patterson AFB Ohio AFFDL Jun 1970 186 p refs (Contract F61052 67 C 0009) (AD 710696 AFFDL TR 70 94) Avail NTlS CSCL 113 N71-10366# Fedeldl Aviation Administration Washington D C The principal aim of the work is to develop approximate Air Traffic Service solutions for both the response of skin stringer panels to turbulent TERMINAL AREA AIRLINES DELAY DATA, 1964 1969 boundary layer excitation dnd the subsequently acoustic radiation Augusta Galbreath and Richard M Warfield Sep 1970 64 p from these structures As a first step the solution for the response refs of single simply supported panels is extended to include panels Avail NTlS with clamped edges Using this as the basic theory solutions for Odta are complled on delays and cost of delays in terminal the response of rows and arrays of skin stringer panels are found by areas served by three airlines The statistical data provide ari applying a method of effective or pseudo wavelengths Equations indication of system effectiveness in the terrninal environment for the radiation characteristics of single panels both with fixed and Basic data consist of the number of delays minutes of delay and with simply supported edges are established from basic principles

38 N71-10434

These solutions are then used to find the radiation from arrays of TRANSPARENT MEDIA [INTERFEROMETRIE bays by introducing a qualitatively derived system of relative bay HOLOGRAPHIQUE POUR L'ETUDE DES MILIEUX phases The combination of the radiation characteristics and of the TRANSPARENTS] response gives acoustic power radiation due to turbulent boundary Jean Surget 1970 5 p refs In FRENCH Presented at the Intern

layer excitation This shows an interesting result which is probably Symp on Appl of Holography Besancon France. 6 ~ 1 1 Jul 1970 particular to this form of excitation. that is. that for most pramcal (TP-851) Avail NTlS configurations the acoustic power radiated by an array of bays does A quantitative study of aerodynamic phenomena by holographic not exceed the arithmetic sum of the powers radiated separately interferometry is presented A comparison of obtained results to the by each bay Author (TAB) one proven by employment of conventional interferometry reveals perfect agreement in the dispersion boundary measurements of the same order of size for the two methods Trans1 by E H W N71-10390# National Research Council of Canada Ottawa (Ontario) Div of Mechanical Engineering DIVISION OF MECHANICAL ENGINEERING AND THE N71-10411*# National Aeronautics and Space Administration NATIONAL AERONAUTICAL ESTABLISHMENT Quarterly FORTRAN PROGRAM FOR COMPUTING COORDINATES Bulletin. 1Jan -31 Mar. 1970 OF CIRCULAR ARC SINGLE AND TANDEM 31 Mar 1970 85 p refs TURBOMACHINERY BLADE SECTIONS ON A PLANE (AD-710638 DME/NAE-1970(1)) Avail NTlS CSCL6/18 William D McNally and James E Crouse Washington Nov 1970 Contents Assessment of the radiation hazards of supersonic 48 p refs transport Comprehensive tidal study of the St Lawrence River (NASA TN-D-6020) Avail NTlS CSCL21E Current projects of the Division of Mechanical Engineering and the A FORTRAN 4 program is presented which computes and National Aeronautical Establishment TAB plots coordinates for circular arc blade sections on a plane Either single blade sections or tandem blade sections with up to 5 segments can be designed Surfaces of blade segments consist of N71-10391'# National Aeronautics and Space Administration single circular arcs The arrangement of segments on the plane is Lewis Research Center Cleveland Chio a function of the input parameters These parameters are overall MEASUREMENT AND ANALYSIS OF LIGHTNING INDUCED blade section quantities such as chord camber. and solidity. as VOLTAGES IN AIRCRAFT ELECTRICAL SYSTEMS well as individual blade segment parameters such as chord camber, Paul T Hacker and J A Plumer (GE Pittsfield Mass) [1970] gap between blade segments overlap of segments, maximum 28 p refs to be presented at the 1970 Lightning and Static thickness and leading- and trailing-edge radii Author Electricity Conf San Diego 9 11 Dec 1970 Ih(AC.6 I, r---- t*.non- ",I IV A DLYUDi Avail NTlS CSCL 01 c A series of measurements weie made of voltages induced in electrical circuits within a metallic aircraft wing by full-scale N71-10417# TRW Systems Group, Redondo Beach. Calif simulated lightning currents flowing through its skin and structure HIGH-SPEED JETPORT ACCESS: FEASIBILITY STUDY OF The measured data were mathematically analyzed to enable A DEMONSTRATION PROJECT IN SOUTHERN FLORIDA determination of voltages across load impedances to which the Find Report circuits might be connected elsewhere in the aircraft Relationships Dec 1969 576 p refs between induced voltages and lightning current wing structural (Contract C-353-66(Neg)) and circuit parameters were determined Induced voltages of 'PB-i 32842 FAA-AT-70-38 TRW-06818.6044 RO-00) Avail magnWees 'kelb cause ddiiidye or inrerrerence with avionics :s NTlS HC $1 0 001 M F $0 65 were measured Author The feasibility of a high speed access system as a transportation demonstration project to a new Southern Florida Jetport was determined Several candidate systems were considered and included vertical-takeoff (VTOL) and short-takeoff (STOL) N71-10394# National Aviation Facilities Experimental Center airborne vehicles in addition to high speed rail (HSR) monorail Atlantic City N J systems (MRS) and tracked air cushion vehicles (TACV) ground STUDY OF THE PERFORMANCE CHARACTERISTICS OF vehicles The evaluation of the perspective alternatives was made THE BENDIX TYPE DRA-12 AIRBORNE DOPPLER RADAR using technical performance and cost considerations over similar SYSTEM Final Report, Feb Oct 1970 routes connecting a jetport to the main population centers in Robert H Mayer Nov 1970 20 p refs Southern Florida Several jetport locations were postulated and (FAA NA 70 50 FAA RD 70 731 Avail NTlS considered in the evaluation of the routes and terminal requirements A study of the performance characteristics of the Bendix A Tracked Air Cushion Vehicle (TACV) system capable of a cruise Radio type DRA 12 Doppler navigation system and the General speed of approximately 150 mph is recommended as the initial Electric miniature heading and artitude system type A A24G 26 for jetport high speed access system This system provides economic the purpose of determining the expected navigation error when transportation for the projected airpon access demands and for flying straight and level and the expected error as a result Of growth to the high speeds desired for future interurban service A making a standard rate turn at a speed of 200 knots is reported performance description preliminary implementation plan and cost A profile of the error while in straight and level flight is presented estimates are provided for the recommended system from a jetpon to which each 180 deg turn error of 184 feet should be added to Miami A general description of the expanded network IS also in quadrature to obtain the expected error at any discrete distance presented with data for long-range planning and the development from the Doppler reference point The results of this study are of programs for financing Author considered useful ii1 determining the extent to which Doppler navigation caii be applied to the Sabreliner aircraft fliqht inspection mission Author N71-10434# Air Force Systems Command. Wright-Patterson AFB. Ohio Flight Dynamics Lab STRESSES AND DEFORMATIONS IN MULTI-PLY N71-10407# Office National d'Etudes et de Recherches AIRCRAFTTIRES SUBJECTTO INFLATION PRESSURE Aerospatiales. Paris (France) LOADING Technical Report.Aug 1968 Dec 1969 HOLOGRAPHIC INTERFEROMETRY FOR THE STUDY OF Howell K Brewer Jun 1970 209 p refs

39 N7 1 - 10440

(AD 71 1073 AFFDL-TR 70 62) Avail NTlS CSCL 1/3 N71-10467*# National Aeronautics and Space Administration The pneumatic tire casing IS treated as a laminated anisotropic Lewis Research Center Cleveland Ohio toroidal shell of revolution possessing bending rigidity The plies are FORTRAN PROGRAM FOR CALCULATING considered to be homogeneous orthotropic laminae on a AERODYNAMIC FORCES FROM PRESSURE OR VELOCITY macroscopic scale which are constructed of elastic textile cords DISTRIBUTIONS ON BLADE SECTIONS embedded in an elastic rubber matrix Modern micro-mechanics William D McNally Washington Nov 1970 38 p refs theory which is based on the self consistent model of compos te (NASA TM X 2123 E 5652) Avail NTlS CSCLOlA materials is used to calculate the four basic elastic moduli of a A FORTRAN 4 program is presented which calculates single lamina The tire shell IS considered to deform according to aerodynamic forces on turbomachinery blade sections from the classical Love hypothesis The equilibrium strain aispiacemenl ais1riuuiions of press-rc or v@oc,!y along the surfaces Blade sections and laminate constitutive equations governing the tire shell are for which forces are calculated may have either one blade segment reduced to a system of six first order ordinary differential equations or two segments (tandem blades) Input includes blade surface >.v!h \rariahlP coefficients A multi segment forward integration coordinates surface distributions of pressure or velocity and several technique is used which first transforms the two point boundary overall flow parameters Surface dllyles moy .?!E(? he yenA< innut value problem into an equivalent set of initial value problems which or may be computed by the program from spline curves The can then be integrated numerically with a fourth order Runge Kutta program integrates pressure or velocity distributions to obtain routine The finite displacements are taken into account by an components of force on the blade surfaces Meridional and tangential iricremPiiting process which builds up the total solution as sequence forces and lift and drag forces are then computed For tandem of linearized solutions The theor./ and solution technique IS blade sections ratios of forces on rear blade segments to forces on illustrated by means of a numerical example The tire chosen for this front blade segments are also given The program IS particularly purpose is a 32 x 8 8 Type VI1 aircraft tire A complete set of useful in conjunction with existing ideal flow programs which allow numerical data is presented The calculations were verified the analytical study of blading Author experimentally by measuring tire strains and the inflated tire meridian profile The agreement hetween theory and experiment IS good Author (TAB) N71-10470# Air Vehicle Corp San Diego Calif A METHOD FOR CALCULATING HELICOPTER VORTEX N71-10440# Regional Planning Commission Cleveland, Ohio PATHS AND WAKE VELOCITIES Final Report. Nov SURVEY PROCEDURES: CLEVELAND HOPKINS AIRPORT 1968 Dec 1969 ACCESS STUDY E S Levinsky and T Strand Jul 1970 72 p refs May 1970 123 p Sponsored by Dept of Transportation (Contract F33615 69 C 11011 Avail NTlS (AD 710694 AFFDL TR 69 113) Avail NTlS CSCL 1/3 The impact of the rapio rail extension from the central A simple method is developed for calculating the time averaged business district of Cleveland to the Hopkins airport was studied velocity field induced at large distances from the rotor by a The survey of the airport users was conducted in the following helicooter in steady horizontal motion The influence of the ground phases (1) Data collection and processing prior to the opening of plane and of horizontal winds on the rotor wake and velocity field is included Author (TAB) the rapid rail transit link lo the dttport (21 Data collection and processing after the opening of the rapid rail transit link to the airport Questionnaire design and survey procedures are given The results of the study are to be used to develop a model that can help assess the feasibility of rapid transit rail service to airports in other cities FOS N71-10478# Technion Israel lnst of Tech Haifa Dept of Aeronautical Engineering DESIGN OF AN INTERMITTENT, SINGLE JACK FLEXIBLE NOZZLE SUPERSONIC WIND-TUNNEL FOR MACH N71-10461# University of Southern Calif 10s Angeles Dcpt NUMBERS1 5T040 of Aerospace Engineering I Kadushin and J Rom [ 19701 39 p refs MEASUREMENTS OF THE HYPERSONIC, RAREFIED FLOW (TAE-86) Avail NTlS FIELD OF A DISK This report describes the design of a single jack flexible Stewart Berlin Jan 1970 36 p refs nozzle wind tunnel having a 400 mm 500 mm test section and (Grant AF-AFOSR 0697 67) capable of operation between Mach numbers of 1 5 to 40 (AD-710641 USCAE 115 AFOSR 70 0194TR) Avail NTlS Description of the wind tunnel installation the pressure air supply CSCL 2014 and other auxiliary systems of this wind tunnel are presented The The flow density and temperature about a disk normal main design features were tested in one-fifth scale model to a hypersonic rarefied stream were measured The tests were wind-tunnel The results of the model tests are in good agreement conducted in nozzle produced flow fields of dry nitrogen The with the design requirements Author electron beam fluorescence technique (EBT) was utilized to determine local fluid density and rotational temperature In addition impact pressure surveys were made in the wake and photographs of the flow field were obtained by traversing the electron beam with the camera shutter held open Two higher Mach number centerline N71-10495 # National Aeronautics and Space Administration density and temperature profiles show qualitative agreement with Langley Research Center Langley Station Va free molecular and first collision theoretical estimates In general WIND-TUNNEL INVESTIGATION OF A JET TRANSPORT the axial and lateral extents of the disk flow field are much greater AIRPLANE CONFIGURATION WITH HIGH than in continuum flow over the same geometry The rotational THRUST-WEIGHT RATIO AND AN EXTERNAL-FLOW JET temperature data indicates that essentially full temperature recovery FLAP is achieved near the forward stagnation point The maximum shock Lysle P Parlett Delma C Freeman Jr and Charles C Smith Jr layer densities however are somewhat below the Rankine Hugoniot Washington Nov 1970 75 p refs values for the given free stream Mach numbers due to the finite (NASA TN D 6058 L 7166) Avail NTlS CSCLOlA wldth of the electron beam and the thickening effect on the shock An investigation was conducted in a full scale tunnel to of the degree of gas rarefaction Author (TAB) determine the aeiodynamic stability and control characteristics of

40 N7 1- 10563 a jet transport configuration that has a high thrust-weight ratio and were tested with an axial flow fan rotor The rotor performance is equipped with an external-flow jet flap The model IS powered by was stable and repeatable and both configurations suppressed four high-bypass-ratio turbofan engines Maximum lift coefficients rotating stall At the minimum flow points, an increase in inlet of about 8 were measured for test conditions which simulated a temperature in the tip region indicates the existence of an eddy jet transport configuration having a thrust-weight ratio of about 0 5 flow Temperatures remained within operational limits Reductions in Longitudinal instability was encountered at high thrust coefficients torque and flow rate with the 45 deg blockage ring indicate that because of adverse downwash variations in the vicinity of the tail a flow blockage device might ease engine starting requirements This problem was solved by raising the tail and moving it forward and might be used to reduce engine thrust while maintaining high to a more favorable downwash field The model was laterally engine speed Author and directionally stable under all power conditions The moments associated with an engine failure were too large to be trimmed out by conventional aileron and rudder control, spoilers alone provided enough control to offset the engine-out rolling moments but the N71-10546# Cincinnati Univ.. Ohio. Dept. of Aerospace lift loss associated with the use of spoilers was severe Author Engineering. EXPERIMENTAL INVESTIGATION OF THE TRAlECTORlES AND VELOCITIES OF SOLID PARTICLES ENTRAINED BY FLUID FLOWS IN CASCADE NOZZLES W. Tabakoff and M. Hussein Aug. 1970 31 p refs N71-10496# Royal Australian Air Force Academy. Melbourne (Contract DAHC04-69-C-0016; Proj. Themis) THERMAL COATING OF GONDOLA PAYLOADS (AD-711121; THEMIS-AE-70-12: AROD-T-4.18-E) Avail: NTlS J A Thomas 119701 8 p CSCL 1o/ 1 (NYO 3747-12) Avail NTlS The study of the trajectories and velocities of solid particles To help maintain equipment temperature in high altitudes suspended in a fluid flowing through a cascade nozzle is of to that of the laboratory. the radiative properties of the coatings importance to the investigation of erosion damage sustained by the of gondola payloads are investigated Flight tests were carried Out blades. In general, the trajectories and velocities of the particles to determine the actual equilibrium temperatures Aluminum cans depend upon the slope of the cascade nozzle. particle and flow with a variety of coatings were used The recorded temperatures inlet conditions, particle material density. mean diameter. angle of are in good agreement with the values obtained from radiosonde attack and initial place of collision. The particles are more likely data EHW to follow the fluid streamlines when their material density is of the same order of magnitude as that of the fluid and when their mean diameter is small, In the investigation, a cascade row of turbine b!e:es was mounted in a cascade tunnel to produce the desired 171-10531# National Transportation Safety Board Washington gas-particle flow. A high speed camera was used to photograph DC the flow. and the subsequent film analysis provided the data for AIR FRANCE BOEING 747-128, F-BPVD SAINT JEAN PQ. the particle velocities and the particle paths through the cascade CANADA, AUGUST 17, 1970. AIRCRAFT INCIDENT nozzle. The particles used are of mean diameter of 1000 microns. REPORT Author (TAB) 7Oct 1970 14 p (NTSB-AAR-70-26) Avail NTlS The flight from Chicago to Montreal was normal in every respect The takeoff from Montreal at 2226 was routine however N71-10562# Stevens Inst of Tech, Hoboken, N J Dept of *ypr?v-ate:, 9 miiu:es after takoff at 2235 at an altitude of Mechanical Engineering 5.600 feet m s I a separation of the second-stage turbine disk rim RESEARCH ON THE FLUTTER OF AXIAL-TURBOMACHINE of the No 3 engine occurred and pieces penetrated and ruptured BLADING Semiannual Status Report the high pressure turbine case and associated engine cowling The Fernando Sisto and Ron Ho Ni Jun 1970 39 p separation of the turbine disk rim resulted in a localized fire in the (Contract NO0014-67-A-0202-001 6) upper forward portions of No 3 engine A fire warning. which (AD-710794. ME-RT-70004. SASR-2) Avail NTlS CSC'L 1011 came on simultaneously with the turbine failure terminated after Theoretical and experimental phases of a program to study both containers of fire extinguishing agent were discharged The No flutter in turbomachinery blading are summarized The analytical 3 engine was shut down and the flight diverted to John F model serves mainly to describe the unstalled. linearized baseline Kennedy International Airport New York. where it landed safely at from which the large amplitude, possibly stalled data may be 0004 (August 18) There were no injuries to passengers. crew. or compared The effect of significant parameters on quasistatic persons on the ground The Board determined that the probable cause aerodynamic moment is displayed and generalized conclusions are of this incident was the in flight separation of the second-stage drawn Author (TAB) turbine disk rim of the No 3 engine The separation of the disk rim was the result of incorrect assembly of the high-pressure turbine module Author

N71-10563# Naval Postgraduate School, Monterey. Calif EVALUATION OF THE LONGITUDINAL STATIC N71-10537*# National Aeronautics and Space Administration STABILITY OF THE US-2A AIRCRAFT Lewis Research Center. Cleveland, Ohio Paul William Cooper Jr tM S Thesis) Apr 1970 63 p refs EFFECT OF SIMULATED DOWNSTREAM FLOW BLOCKAGE (AD-710722) Avail NTlS CSCL 1/3 DOORS ON THE PERFORMANCE OF AN AXIAL-FLOW The aircraft was equipped with a data acquisition system FAN ROTOR capable of sensing and recording aerodynamic data other than that Walter M Osborn and Jack M Wagner Washington Nov 1970 given by the standard cockpit instruments Recorded data were 26 p refs displayed graphically and the neutral points for stick-free stability (NASA-TN-D-6071.E-5215) Avail NTlS CSCL 21E and stick-fixed stability were determined Stick-free static margin Two downstream flow blockages simulating door positions and stick-fixed static margin were determined and evaluated of 20 deg and 45 deg in the bypass air duct of a turbofan engine Author (TAB)

41 N7 1- 10564

N71-10564# Army Electronics Command Fort Monmouth N J In the operation of the BRL Supersonic Wind Tunnels it Avionics Lab is necessary to hold the air temperature at the entrance to the A METHOD FOR DETERMINING A CONCEPTUAL tunnels to a constant given level This report describes the cooling SOLUTION TO ENSURE 301 system used to accomplish this and a few of the problems involved R Joseph Milelli John F O'Connor Jun 1970 25 p in its operation Author (TAB) (AD 710948 ECOM-3302) Avail NTlS CSCL 1/3 A requirement (ENSURE 301) exists for a system which will enable a pilot to hover in the CH 54 with reasonable precision (nndefinrd) over a predetermined point for 10 minutes or less in IFR conditions while personnel on the ground attacn or remove N71-10681# Army Engineer Waterways Experiment Station Vicksburg. Miss cargo from a sling load Several schemes have been proposed by RESTORATION OF LANDING MAT-SURFACED airframe and electronics contractors including different control sysiiiiij d::p!ays. 2nd wnqors The Government is required to SUBGRADES BY GROUTING METHODS Final Report evaluate the various proposals and the purpose of the paper is to Cec!! D Riirnq and Victor C Barber Jun 1970 81 p /ts Misc illustrate how using a simulation in the evaluation can suggest a Paper S-70-19 conceptual solution Author (TAB) (AD-710962) Avail NTlS CSCL 13/3 Engineering tests were conducted in order to evaluate the use of portland cement and asphaltic materials as grout for the repair of pumped subgrades under heavy-duty airfield landing mats and to develop equipment and criteria for their application N71-10581# Grumman Aerospace Corp Bethpage N Y Author (TAB) Research Dept SUBCRITICAL FLOWS OVER TWO DIMENSIONAL AIRFOILS BY A MULTISTRIP METHOD OF INTEGRAL RE LATl ONS N71-10682# Ohio River Div Labs, Cincinnati R E Melnik and D C lves Oct 1970 10 p refs Presented DEVELOPMENT STUDY FOR A VFR HELIPORT STANDARD at the 2d Intern Conf on Numerical Methods and Fluid Dyn LIGHTING SYSTEM Final Report Berkeley Calif 14 Sep 1970 T H Morrow, Jr Aug 1970 136 p refs Sponsored in part (RE-393J) Avail NTlS by FAA The possibility of using Dorodnitsyn s method of integral (AD-710982 CERL-TR-M-3) Avail NTlS CSCL 1/5 relations (MIR) to treat this classical nonlinear potential flow The report describes a tour part study directed toward a problem is considered The scheme 1 version of the method IS standard lighting system for heliport under visual flight rule (VFR) employed in which the strip boundaries are taken more or less conditions The investigation includes a laboratory model study. a parallel to the airfoil surface This scheme is considered to be best preliminary field layout and two helipad installation tests using suited for airfoil type problems in which the rapid variations are actual helicopter flight operations Results were analyzed by pilot along the airfoil surface The chief advantage of MIR is that questionnaires and interims Tentative recommendations for further because a relatively coarse mesh can be taken across the flow field testing are presented including all particulars of a heliport lighting useful solutions can be obtained with less computer time than system Author (TAB) might be required by other methods This approach offers the possibility of developing an economical calculation scheme for practical airfoil design Author

N71-10705# School of Aerospace Medicine Brooks AFB Tex AIRSPEED INFLUENCE ON NOISE WITHIN FIXED- AND ROTARY WING AIRCRAFT Research Report.Jan 1966 Oct. 1969 N71-10674# National Transportation Safety Board Washington DonaldC Gasaway Jun 1970 22 p refs D C Bureau of Aviation Safety (AD 71 1359 SAM TR 70-27) Avail NTlS CSCL20/1 STUDY OF AIR TAXI ACCIDENTS: A STATISTICAL The influence of increased motive power and airspeed on SUMMARY AND ANALYSIS OF A SPECIAL SEGMENT OF noise levels within 163 fixed- and rotary wing aircraft is depicted US GENERAL AVIATION. 1964-1968 in 9 noise exposure envelopes Increased power and airspeed May1970 190 p refs resulted in increments in cockpit noise in all of these aircraft groups (NTSB-AAS 70-1) Avail NTlS Changes in acoustic spectra and speech interference are illustrated This study was compiled from the records of 995 accidents and described Author (TAB) occurring in Air Taxi flying during the 5-year period 1964-68 Collisions between aircraft are treated as one accident A complete analysis and coding is done on each aircraft involved in collisions This produces two aircraft accident records one for each aircraft involved in the collision Consequently when compiling information on accidents including collisions between aircraft the number of accident records will exceed the number of accidents All analytic N71-10720# National Severe Storms Lab., Norman. Okla. .tables show both records and accidents Author SEVERE THUNDERSTORM RADAR ECHO MOTION AND RELATED WEATHER EVENTS HAZARDOUS TO AVIATION OPERATIONS Peter A. Barclay and Kenneth E. Wilk Jun. 1970 68 p refs (ESSA-TM-ERLTM-NSSL-46) Avail: NTlS Objective techniques for identifying and tracking individual N71-10679# Ballistic Research Labs, Aberdeen Proving Ground storms by radar are described, using digital weather radar data Md Exterior Ballistics Lab with space resolution of approximately 1 n.mi. The minimum time COOLING WATER SYSTEM, COMPRESSOR PLANT NO 1 interval between observatlbns required for deriving storm controid Ernest P Reklis Jun 1970 29 p velocity is 2 to 3 minutes. The optimum signal threshold for (AD-710971. BRL-TN-1735) Avail NTlS CSCL 14/2 defining storm cores for tracking is 1000 to 10.000 mm(6)m(-3)for

42 N71-10815

isolated storms and 100 to 1000 mm(6)m(-3) for squall lines A AERO COMMANDER 1121, N236.JP. RURAL RETREAT. technique is suggested for the extrapolation of arrival of a VIRGINIA.31 OCTOBER 1969 thunderstorm core into a control zone of an airport The degree of 9 Sep 1970 20 p Its File No 3 41 10 confidence in the extrapolated path is measured in terms of timing (NTSB AAR-70-22) Avail NTlS and distance errors resulting from the variance in storm veloclty The Aero Commander 1121 crashed while descending on Analyses of the wind fields associated with several severe squall a radar vector to the final approach course at Tri-City The crew lines show narrow zones of high winds that veer sharply with of two and the one passenger aboard the aircraft were fatally increased speed and contain strong gusts that also increase with injured The aircraft made contact with the ground 2.450 feet above mean wind speed Author sea level while in approximately 60 deg nosedown wings level attitude The impact site was about 2 miles northeast of Mountain Empire Airport Rural Retreat Virginia The probable cause of this accident was that following a malfunction or failure in the 115-volt alternating current electrical system the crew did not take proper N71-10734# Dayton Univ, Ohio Research lnst action resulting in the loss of the pilot’s flight instruments in PARAMETRIC STUDY OF NATURAL FREQUENCIES OF instrument flight conditions and subsequent loss of control SKIN-STRINGER STRUCTURE Author T J McDaniel Wright-Patterson AFB. Ohio AFML Jul 1970 90 p refs (Contract F33615-67-C-1187) (AD-71 1383. AFML-70-145) Avail NTlS CSCL 1/3 National Transportation Safety Board Washington The results of a parametric study of the natural frequencies N71-10813# of a row of skin-stringer structures are contained in this report 0 C Bb:$au of Aviation Safety Typical aircraft structures with hat-section. 2-section. or milled AIRCRAFT ACCIDENT REPORT: MACK TRUCK, INCOR- stringers were considered The effect on the natural frequencies of PORATED LEAR JET 23A. N1021B. HORLICK-RACINE parametric variation of stringer spacing. distance between frames, AIRPORT, RACINE, WISCONSIN, 6 NOVEMBER 1969 thickness of the covering skin. and material properties of the 9 Sep 1970 17 p /fsFile No 3-3766 structure are tabulated These results were obtained from a (NTSB-AAR-70-21) Avail NTlS Lear Jet N1021B. crashed into Lake Michigan while executing delta-matrix procedure which is developed from a transfer matrix an instrument approach to Runway 22 at the Horlock-Racine analysis of the skin-stringer structure Improvements in the transfer Airport Racine Wisconsin There were seven people aboard the matrix analysis of the structure are also developed Author (TAB) aircraft the pilot copilot and five passengers, none of whom have been found to date Radar contact was lost shortly after the fliaht was aavised that it was passing a radar fix 3 6 nautical miles northeast of the radio beacon which is located on the southern boundary of the airport It is determined that the probable cause N71-10735# Army Cold Regions Research and Engineering Lab. of this accident was the continued descent below the prescribed Hanover. N H approach path profile. for reasons unknown Author ICING OCCURRENCE, CONTROL AND PREVENTION. AN ANNOTATED BIBLIOGRAPHY Kevin L Carey Jul 1970 61 p refs (AD-711534 CRREL-SR-151) Avail NTlS CSCL8/12 N71-10814# National Transportation Safety Board Washington Icings present severe problems for highways. railroads. airfields. D C Bureau of Aviation Safety and structures btslls 2‘ a.ng processes, and past and present AIRCRAFT INCIDENT REPORT BOEING 747, N732PA. practices of icing prevention and control, are given in annotations RENTON AIRPORT, RENTON. WASHINGTON. 13 for 93 of 94 bibliographic entries The entries were selected from DECEMBER 1969 over 200 references examined through March 1968 Of the 94 26 Aug 1970 30 p /IS File No 5 0046 entries 51 are from the Soviet Union 37 from the United States. and (NTSB-AAR 70 19) Avail NTlS 6 from Canada Fourteen recent Russian papers were translated The probable cause of this incident was the premature specifically for this study Author (TAB) touchdown of the aircraft during a visual approach to a relatively short runway induced by the pilots not establishing a glidepath which would assure runway threshold passage with an adequate safety margin under somewhat unusual environmental and psychological conditions During an approach to a landing at Renton. N71-10737# Lincoln Lab. Mass. Inst. of Tech., Lexington. the Boeing 747 aircraft struck an embankment approximately 20 AIR TRAFFIC CONTROL Quarterly Technical Summary feet short of the threshold of Runway 15 The ground contact point Report. 1 May-31 Jul. 1970 was approximately 30 inches below the top of the bank and the Herbert G. Weiss 15 Aug. 1970 18 p refs runway level The aircraft came to a stop on the centerline of (Contract AF 19(628)-5167) Runway 15 approximately 3 500 feet beyond the threshold Small (AD-711662; ESD-TR-70-235) Avail: NTlS CSCL 17/7 fires broke out in the No 3 engine wing strut and the No 4 engine Efforts were made to evaluate quantitatively the capabilities forward of the tail cone These were immediately extinguished and limitations of the systems. procedures. and instrumentation Structural damage was confined to the right wing landing gear. right utilized for ATC. A new activity is directed toward defining and flap assemblies and the Nos 3 and 4 engines and their cowlings evaluating the impact that a data-linked cockpit display of Automated Author Radar Terminal System (ARTS) information could have upon terminal area capacity. Also under study is the application of a laser beam alerting system at Logan International Airport to increase the N71-10815# National Transportation Safety Board Washington. usefulness of Runway 4R. Author (TAB1 D C .Bureau of Aviation Safety AIRCRAFT ACCIDENT REPORT: OZARK AIR LINES. IN- CORPORATED DOUGLAS DC-9-15, N974Z. SIOUX CITY N71-10812# National Tra‘nsportation Safety Board. Washington. AIRPORT, SIOUX CITY. IOWA.27 DECEMBER 1968 D C Bureau of Aviation Safety 2 Sep 1970 42 p Its File No 1.0039 AIRCRAFT ACCIDENT REPORT: THE PITTSON COMPANY (NTSB-AAR-70 20) Avail NTlS

43 N71-10816

A Douglas OC 9 crashed while taking off from the SIOUX City HerbertJ Cunningham Washington Nov 1970 39 p refs Airport Sioux City Iowa There were no fatalities The probable (NASA-TN-D-6012, L-6808) Avail NTlS CSCL 20K cause of this accident was a stall near the upper limits of A description is presented of a systematic procedure for ground effect with subsequent loss of control as a result of the obtaining generalized aerodynamic forces from the lifting-surface aerodynamic and weight penalties of airfoil icing The flightcrew theory by the supersonic kernel-function method and for using those failed to have the airfoil ice remove0 prior to the attempted takeoff forces thus obtained in a Galerkin modal flutter analysis The method and selected an improper takeoff thrust for the existing gross is applicable to planforms with subsonic leading and supersonic weight conditions of the aircraft Author trailing edges Analytical flutter results were obtained and compared with experimental values from three flutter models Author

N71-10816# Congress House Committee on Interstate and Foreigii Commerce N71-10867*# General Electric Co Schenectady N Y Research CIVIL AERONAUTICS BOARD AiR iviAiL RATE AUT!-!!X!!?V and Development Center Washington GPO 1970 71 p refs Hearings on H R 16879 HEAT TRANSFER ON A FLAT PLATE iii CO:

44 N71-10948# Weather Squadron (24th). Detachment 11. Reese (LR-530) Avail NTlS AFB. Tex Suction coefficients from zero to unity were applied to a TERMINAL FORECAST REFERENCE FILE. REESE AFB. single-slotted commercial steel circular cylinder at low free-stream TEXAS Final Report Mach numbers Balance measured force data for a full range of Jul 1970 47 p refs slot position in the upper surface are presented and discussed The (AD-71 13901 Avail NTlS CSCL4/2 results indicate slot position and suction coefficient to be powerful The reference file discusses factors affecting the weather means of controlling cylinder lift Measurements at zero slot flow at Reese AFB. TX Included are location and topography. weather demonstrated that the presence of the sharp-edged slot (s/d = controls, climatic aids. and special synoptic studies 3 05) could give rise to sizeable crosswind forces that reversed Author (TAB) direction as cylinder Reynolds number was changcd through the critical value Author

N71-10949# Weather Squadron (24th). Detachment 15. Vance AFB. Okla N71-11003# National Aeronautical Establishment. Ottawa TERMINAL FORECAST REFERENCE FILE, VANCE AFB. (Ontario) Unsteady Aerodynamics Section OKLAHOMA Final Report DYNAMIC VISCOUS PRESSURE INTERACTION IN 15 Jul 1970 83 p refs HYPERSONIC FLOW (AD-71 13811 Avail NTlS CSCL4/2 Kazimierz J Orlik-Rueckemann Jul 1970 86 p refs The reference file discusses factors affecting the weather (LR-535. NRC-11598) Avail NTlS at Vance AFB. Ok Included are location and topography. weather A method is presented for the determination of boundary controls. climatic aids. and special synoptlc study Author (TAB) layer effect on the unsteady pressure distributions on an oscillating body in continuum hypersonic flow The method is based on the concept of dynamic viscous pressure interaction which takes into N71-10982*# National Aeronautics and Space Administration. account the relative motion between the body surface and the Lewis Research.Center. Cleveland. Ohio. boundary layer displacement surface The method can be applied to STUDY OF TURBOJET COMBUSTOR DYNAMICS USING arbitrary bodies and flow conditions provided the relevant SWEEP-FREQUEN.CY DATA inviscid unsteady pressure drstributions and the dependence of the John R. Szuch, Francis J Paulovich. and William M. Bruton boundary-layer displacement on the steady flow variables are known Washington Nov. 1970 42 p refs In its present version the method is limited to low-frequency and (NASA-TN-D-6084: E-5595) Avail: NTlS CSCL 21 H small-amplitude oscillations Calculated examples of oscillatory The analysis of data obtained from sweep-frequency testing pressure distributions phase angles and stability derivatives are of the J85 turbojet combustor is discussed. Bode plots of the J...,'.-a*,-- !=: c !e;-. vYp,czI ~:oG~coiid,:,ons ovei sieiidar wedges ana response cf cc~bii~~ipiesslire to sinusoidai disturbances in slender right circular cones performing oscillation in-pitch about zero fuel-spray-nozzle pressure are presented for a range of fuel flows. mean incidence and completely submerged in the weak interaction An analog simulation was developed and used to match the region of a laminar boundary layer Author experimental data and to identify the combustion dynamics. The effects of primary or burning-zone fuel-to-air ratio on the system response were also investigated. The experimental data were fit by linear transfer function forms to be used in overall system studies. N71-11004*# National Aeronautics and Space Administration Author Langley Research Center Langley Station Va JET-WAKE EFFECT OF A HIGH-BYPASS ENGINE ON WING-NACELLE INTERFERENCE DRAG OF A SUBSONIC N71-1lOOl# Weapons Research Establishment. Salisbury TRANSPORT AIRPLANE (Australia). James C Patterson, Jr and Stuart G Flechner Washington Nov THE USE OF RATE GYROSCOPES IN THE FREE FLIGHT 1970 47 p refs MEASUREMENT OF AERODYNAMIC LATERAL FORCE AND (NASA-TN-D-6067 L-7310) Avail NTlS CSCLOlA MOMENT COEFFICIENTS An experimental wind-tunnel investigation has been conducted N. E Gilbert Mar. 1970 43 p refs recently to determine the aerodynamic interference associated with (HSA-TN-164) Avail. NTlS the wing pylon and high bypass fan-jet engines installed on a Suitable flight data regions are selected for the free flight typical highwing logistics transport airplane configuration and the measurement of aerodynamic force and moment coefficients on interference due to the let wake produced by powered model fan-jet two bombs, each with four fins. The bombs carried an incidence engines These tests were conducted over a Mach number range meter. three rate gyroscopes, and four linear accelerometers. The from 0 700 to 0 825 at angles of attack from 0 deg to 4 deg flight data are fitted to a mathematical model of the force and Author moment system. Pitch and yaw rates and pitch and yaw accelerations derived using rate gyroscope measurements are compared with those derived using other sources and the agreement was found to N71-11005# Massachusetts lnst of Tech Cambridge be very good. Static coefficients are found to be equally well Aeroelastic and Structures Research Lab obtained using any of the various combinations of rate gyroscope AN EXPERIMENTAL STUDY ON THE UNSTEADY and linear accelerometer measurements. Results are given at a BEHAVIOR OF A SHORT BUBBLE ON AN AIRFOIL DURING Mach number of 0.6. and very good agreement ts obtained between DYNAMIC STALL WITH SPECIAL REFERENCE TO THE free flight and wind tunnel measurements of the static forces and MECHANISM OF THE STALL OVERSHOOT EFFECT moments. Author Koji lsogai Jun 1970 27 p refs (Contract DA-31 124 ARO(D1-247) (AD-711540 ASRL-TR-130-2 AROD 4846 12) Avail NTlS CSCL 1/3 N71-11002# National Research Council of Canada. Ottawa Unsteady behavior of the reattachment point of a short (Ontario) Div of Mechanical Engineering bubble on a two-dimensional wing of NACA 0012 airfoil section CIRCULATION CONTROL BY SLOT SUCTION ON A during rapid change of angle of attack was studied by the use of CIRCULAR CYLINDER: PRELIMINARY MEASURED FORCE miniature pressure transducers installed in the model for the DATA purpose of detecting the sudden pressure rise at the reattachment R A Tyler and R G Williamson Feb 1970 49 p refs

45 N71- 11006

point Tests were made for the range of non-drmensional pitch rate at Mach 14 show that a small unsymmetric nose bluntness from 0 to 025 and Reynolds number from 64.000 to 125.000 destroys the rotational symmetry of the stability derivatives of a The results obtained suggest that the delay of the initiation of the slender cone at hypersonic Mach numbers and therefore severely leading edge vortex shedding is. at most. the same order of violates the assumptions of the tricyclic theory Restoring and magnitude as the delay of the movement of the reattachment point damping derivatives in pitch and yaw are reported for a 10 deg Author (TAB) cone with symmetric and unsymmetrically blunted noses The effect of non-equal stability derivatives on the motion are shown for a simplified case A ut hor (TAB1

N71-11006# Georgia lnst of Tech Atlanta School of Aerospace Eng:l-.cc~ing A TWO-DIMENSIONAL REPRESENTATION OF THE N71-1lOO9# National Aerospace Lab Tokyo (Japan) CROSSWIND FOR THEJET INTERFERENCE PROBLEM DYNAMIC STABILITY TEST IN A TRANSONIC WIND Mary Anne Wright (Ph D Thesis) May 1970 156 p refs TUNNEL WITH A ROTARY SYSTEM Sp""aO,cd lii p6i;by ?!SC (Contract DAHC04 68 C 0004 Pro1 Themis! Yasuliro Kobashi, Nagamasa KOno TaKenori Nisiii ani: ?&siifurn, (AD-711578 GIT AER 70 4 AROD T 2 16) Avail NTlS CSCL Miyazawa May 1970 15 p refs In JAPANESE, ENGLISH 2014 summary The problem of a jet exhausting normally from an infinite (NAL TR 196) Avail NTlS flat plate into a crosswind is studied analytically primarily in terms A method is explored for extracting various kinds of of the resulting interference pressures on the plate Three let exit aerodynamics derivatives from forces measured in a wind tunnel by shapes are considered a circle an ellipse with the major axis rotating a model through a bent rotary sting and a straight rotary aligned with the crosswind (streamwise exit) and an ellipse with stinq with --'ark angles The experiments are conducted with the major axis perpendicular to the crosswind (blunt exit) It IS I-~J-Iso,,d the dynamic damping and stiffness derivatives shown that a two dimensional steady potential flow model for the of each longiludinal and lateral direction are obtained The results crosswind in planes parallel to the plate may be used provided of the experiments revealed that this technique is very suitable for the let to crosswind speed ratio is sufficiently large and the wake dynamic tests in a wind tunnel because of small inertia effect region is excluded A blockage sink model is developed wherein the simple model drive and easy measurement of steady dynamic blockage elements represent blockage due to the let plume and derivatives which are important at steady turning flight The due to the presence of the wake and a single sink represents measured derivatives are not obtained from pure modes of move entrainment The model parameters are presented as functions of ment such as pitching or plunging therefore it is necessary to speed ratio and let exit thickness ratio The blocKage and check whether the assumption of linearity is satisfied Comparison entrainment parameters are va led over a range of values to between the present results and those obtained from the conven determine the effects of each on the interference pressure and it tional methods showed fairly good agreement The number of s found that the entrainment factor is quite significant The measurements is limited at present but the obtained values :treamwise and circular let exits are more useful for lifting let agreed well with theoretical predictions Author awlications than the blunt exit because of their favorable coupling 0' the blockage and entrainment effects and their relatively small wake production Author (TAB) N71-11010*# National Aeronautics and Space Administration Lewis Research Center Cleveland Ohio COLD-AIR INVESTIGATION OF A TURBINE WITH N71-11007# ARA Inc West Covina Calif TRANSPIRATION-COOLED STATOR BLADES 2 STAGE INVESTIGATION OF THE EFFECT OF LEADING EDGE ON PERFORMANCE WITH DISCRETE HOLE STATOR BLADES THE AERODYNAMIC CHARACTERISTICS OF A 70 DEG Edward M Szanca Harold J Schum and Frank P Behning SWEPT DELTA WING Final Scientific Report, Nov 1969 Jul Washington Nov 1970 25 p refs 1970 (NASA TM X 2123 E 5812) Avail NTlS CSCLOlA Bernard Mazelsky and Richard B Lohman Jul 1970 36 p refs Turbine performance characteristics were obtained for a (Contract F44620 68 C-0027) single stage axial flow turbine equipped with stator blades (AD 712087 ARA 110 AFOSR 70 1989TR) Avail NTlS CSCL employing transpiration coolant election through discrete holes The 113 turbine was tested over a range of speed and pressure ratio and Measurements were taken to determine the effects of varying with a coolant fraction of 0 03 Additional tests were made at the the gap width of two parallel leading edge slots on the aerodynamic design speed in which the coolant flow was varied from zero to characteristics of a 70 deg swept delta wing The two malor 0 07 of the primary flow The results were compared to similar changes over previous model tests were the use of flush slots and results obtained with a turbine using stator trailing edge coolant study under turbulent boundary layer conditions The slots were ejection A base turbine with no cooling provision was used as a aligned parallel to the leading edges to Simulate leading-edge flaps standard for comparisons Author The report analyzes preliminary computer data and develops a comparative thesis of three delta wlng tests Author (TAB!

N71-11011# Naval Postgraduate School Monterey Calif THE UNSTEADY NORMAL FORCE ON AN AIRFOIL IN N71-1lOOS# Aerospace Research Labs Wright Patterson AFB DSCILLATING FLOW Ohio Maurice R Banning (M S Thesis! Dec 1969 174 p refs EFFECT OF UNSYMMETRICAL NOSE BLUNTNESS ON THE (AD 71 1830) Avail NTIS CSCL2014 STABILITY DERIVATIVES OF A 10 DEG CONE AT MACH The effects of oscillating flow on the pressure force normal to 14 Final Report the chord of a symmetrical airfoil were investigated experimentally Otto Walchner Frank M Sawyer and Kevin E Yelmgren Jul employing a remote pressure transducer to measure the 1970 27 p refs instantaneous pressure distribution An open circuit wind tunnel (AD 71 1921 ARL 70 01 19) Avail NTIS CSCL 2014 having a set of rotating shutter blades located down stream of the In the analysis of the free flight motion of bodies of revolution test section was used to produce the oscillating flow Electrical the tricyclic theory assumes that a small configurational asymmetry signals analogous to the free stream velocity and surface pressure does not violate the rotational symmetry of the stability derivatives were recorded simultaneously on separate tracks of a magnetic in pitch and yaw but does produce a non zero trim angle Tests tape The recorded data were converted to digital representation and

46 N71-11016

numerical techniques utilized to evaluate the spectral composition N71-11014# National Physical Lab., Teddington (England). of the measured pressure distribution. from which the normal force Aerodynamics Div. was calculated It was found that the magnitude of the total OBSERVATIONS OF THREE-DIMENSIONAL FLOW normal force at high angles of attack is significantly greater in PAITERNS OBTAINED DURING STALL DEVELOPMENT oscillating flow than in steady flow and is frequency dependent. while ON AEROFOILS, AND ON THE PROBLEM OF MEASURING at low angles of attack no significant differences were observed TWO-DIMENSIONAL CHARACTERISTICS Progress Report Moreover it was found that higher order harmonics of the N. Gregory, V. G. Quincey. C. L. OReilly. and D. J. Hall Jan. fundamental free-stream frequency constitute a significant fraction 1970 35 p refs of the normal force. and these fractions are also frequency :NPL-AERO-1309: ARC-31702) Copyright. Avail: NTlS oependent The observed results are not adequately predicted by Surface oil-flow patterns were used at low speeds on both quasi-steady aerodynamic analysis Author (TAB) thick and thin airfoils to show the onset of three-dimensionality in either separation or re-attachment when there is an appreciable extent of the separated flcw that accompanies the development of the stall. Observations on a thick airfoil in compressible flow N71-11012# Oxford Univ (England) Dept of Engineering showed a similar trend in the re-attachment behind a shock-induced Science separation. A form of boundary-layer control applied at the corners [AN EXPERIMENTAL INVESTIGATION OF THE LAMINAR at ihe ends ot the airtoil was able to prevent separation of the comer NEAR WAKE BEHIND A CIRCULAR CYLINDER IN A MACH flow but not to inhibit the development of three-dimensionality. 6. RAREFIED AIR STREAM] Author (ESAO) G P D Raiasooria and C L Brundin Jun 1970 103 p refs (Rept 1108/70) Avail NTlS A method is presented whereby the hot wire end loss correction can be directly and accurately determined The more N71-11015# National Aerospace Lab, Amsterdam (Netherlands). important resultsare as follows The surface pressure measurements COMPARISON OF CALCULATED PRESSURE indicate that the magnitude of the pressure recovery at the base DISTRIBUTIONS ON SOME SWEPT WINGS WITH WARREN region of the cylinder decreases with decreasing Reynolds numbers 12 PLANFORM AT SUBSONIC SPEEDS Owing to the relatively small amount of pressure recovery at the A. F. Jones, (RAE, Farnborough). P V. Grey-Wilson (RAE. base region there are IO separation shocks emanating from the Farnborough). and J. W. Slooff 10 Oct. 1969 36 p refs body The wake shock is a broad weak recompression area, the Sponsored by Direc. of Materiel Air, RNUF strength of which decays rapidly in the downstream axial direction (NLR-TN-T-189) Avail: NTlS An expansion region similar to that found behind slender bodies Data are presented from calculetions for the surface pressure is present in the region between the base of the cylinder and the distribution on some particular swept wings with Warren 12 rear stagnation po!nt Furthermore an entropy wake is found to planfnrm Ci~~periscnsa:$ $vcn be:wsen iesuits otiained from an ew? Thss en::op~ wake is caused by tne curved bow shock RAE computer program and a similar program developed at NLR. producing large lateral entropy gradients Author (ESRO) It is shown that small differences exist as a consequence of different numerical procedures and slight changes in formulation of the basic method. Additional comparisons with a numerical solution of the exact equation for incompressible potential flow suggest that thickness effects are reasonably well represented for the N71-11013# National Physical Lab., Teddington (England). configurations considered. Author (ESRO) Aerodynamics Div. THE THEORETICAL TREATMENT OF SLOWLY OSCILLATING PART-SPAN CONTROL SURFACES IN SUBSONIC FLOW H C. Garner and Doris E. Lehrian Oct. 1969 130 p refs N71-11016# National Physical Lab., Teddington (England). (NPL-AERO-1303: ARC-31490) Copyright. Avail: NTlS Aerodynamics Div. To first order in frequency. subsonic lifting-surface theory LOW-SPEED AERODYNAMIC CHARACTERISTICS OF NACA is applied to arbitrary configurations of a thin wing and a 0012 AEROFOIL SECTION, INCLUDING THE EFFECTS OF trailing-edge control The discontinuities in flow direction at the UPPER-SURFACE ROUGHNESS SIMULATING HOAR FROST hinge line and part-span boundaries are surmounted by independent N. Gregory and C. L. OReilly Jan. 1970 41 p refs consideration of smooth equivalent slopes in the chordwise and (NPL-AERO-1308; ARC-31719) Copyright. Avail: NTlS spanwise directions. the combined equivalent incidences depend on Results are presented for the aerodynamic characteristics the aerodynamic quantities to be evaluated. The method yields of NACA 001 2 airfoil section at Reynolds numbers of 2.88 million satisfactory values for lift. pitching, and rolling moments. hinge and 1.44 million with some indications of scale effect at other moment and the associated spanwise distributions. but does not Reynolds numbers. The measurement of the maximum lift coefficient determine the complete load distribution dut to an oscillating control. at a Reynolds number of 2.88 million was uncertain because a Illustrative examples cover four planforms, namely. rectangular and laminar separation bubble disappears intermittently for reasons that cropped delta wings for which there are experimental data on are not fully understood and it was found that the flow broke down hinge moment. an untapered swept wing that has been studied by into a three-dimensional pattern when an appreciable extent of electrical analogue, and a tapered swept wing to be the subject separation was present. Boundary-layer control by suction in the of future experiment. The solutions for each planform are tabulated vicinity of the wing/wall junction was shown to improve the and plotted as functions of control chord, control span or two-dimensionality in the early stages of separation, but did not Mach number and are examined from the standpoint of numerical inhibit the appearance of three-dimensional flow at and beyond the convergence with respect to the number of chordwise collocation stall. Distributed roughness was progressively applied from the points. Consideration is given to the transformed aerodynamic trailing edge forwards over the upper surface of thc airfoil. Both problem on the reversed wing by application of the reverse-flow sparse and dense distributions were used and they were intended theorem. and these alternative numerical results strengthen to simulate the hoar frost deposit remaining after partial cleaning confidence in the present method and give some indication of the of the forward part of the airfoil. Subject to the above qualifications likely accuracy. The optimum central rounding of swept edges is the maximum lift coefficient was not greatly reduced until the front discussed together with mani other refinements of numerical edge of the roughness extends forward of 0 1 chord, at which technique. It is concluded that significant wing forces can be stage the drag increment due to the roughness rapidly became calculated to at least two-figure accuracy Author (ESRO) much larger. Author (ESRO)

47 N71-11017

N71-11017# Von Karman lnst for Fluid Dynamics Rhode ~71-11020# Federal Aviation Administration Washington D c Saint-Genese (Belgium) Flight Standards Service A PARAMETRIC STUDY OF ADIABATIC LAMINAR MODERN SURVEILLANCE OF AIRCRAFT INTEGRITY BOUNDARY LAYER SHOCK WAVE INTERACTIONS BY THE James E Dougherty [I9691 32 p refs Presented at the 5th Ann METHOD OF LEES- REEVE S-KLI NEBE RG Aviation Maintenance Symp Advances in Aviation Maintenance M L Riethmullerand J J Ginoux Jun 1970 90 p refs Techno1 Oklahoma City 9- 11 Dec 1969 (VKI-TN-60) Avail NTlS Avail Issuing Activity The problem of the interactions between a shock wave Terminology such as overhaul at fixed times progressive and a laminar boundary layer with emphasis on the adiabatic case maintenance sampling techniques on condition reliability and is brfeflv discussed A computer program is described which has been condition monitoring is noted The relationship between industry and used for a parametric study the results 01 wnicn are preseiiied goveriitiiani IO> ?he fc:,mJ!atior evalcaticn and nnnroval of graphically Ranges of Mach number from 1 5 to 60 and of maintenance programs is discussed as IS the need for realistic and Reynolds number per meter from 0 8 million to 0 1 x 10 to the 8th scientific appraisal of modern day aircraft maintenance programs ywPr are considered A study of incipient separation shows good The papers prime purpose IS to help speed up recognition and agreement with the theoretical results with the correlation acceptance of conaition moniroriiiy d~ d,,~:~id:o :kc !G?!xc~~:-~ established from experimental data by Needham and Stollery The family of large transport jets as well as the supersonic transports listing of the computer program used for this study is also given still in the embryonic stage Conjecture IS devoted to the possibility Author (ESRO) of condition monitoring serving as the basis for future development of maintenance programs for many of the complex high speed N71-11018# National Aviation Facilities Experimental Center executive jet powered aircraft now in use and now being developed Atlantic City N J for entry in the general aviation field Author FIRE PROTECTION TESTS IN A SMALL FUSELAGE-MOUNTED TURBOJET ENGINE AND NACELLE INSTALLATION Final Report, 1965 1970 Daniel E Sommers Nov 1970 61 p refs N71-11021# Young (Arthur) and Co, Bethesda. Md (FAA NA 70 41 FAA RD 70 57) Avail NTlS PASSENGER DEMAND AND MODAL SPLIT MODELS: Tests under simulated flight conditions were conducted CALIBRATION AND PRELIMINARY ANALYSIS to investigate the potential explosion and fire hazards and detection J M McLynn and T Woronka Dec 1969 172 p refs and fire control methods Hot surface ignition of flammables did Supported in part by Dept of Transportation not occur during simulated flight operating conditions until a (Contract NBS CST-468) change to the normal nacelle configuration reduced cooling airflow (PB-190946, NECTP-230) Avail NTlS CSCL 138 to the hot section of the engine (Zone 1) below 0 15 pound per The report develops demand and modal split models for second The installed detection system did not provide for prompt passenger transportation in the Northeast Corridor of the United detection of all fires originated in the lower forward portion of the States These models are to be used for estimating the patronage compressor compartment (Zone 2) Both the Zone 2 fire detection on intercity transportation systems in the time period up to 20 and the Zone 1 overheat detection system were sensitive to fires years in the future The uniqueness of these models is that they can originating in the inboard portion of Zone 2 The installed be used to estimate patronage on many existing and new modes extinguishing system provided rapid extinguishment of all Zone 2 simultaneously and consistently. ensuring the compatibility of the fires until extensive accumulative damage from fires destroyed the several estimates Author (USGRDR) integrity of the zone Fireproof protection incorporated in the nacelle was very effective in performing its intended function Most susceptible to damage by fire was the aluminum portion of the N71-11022# Naval Acadernv Annapolis Md nacelle especially aluminum receptacles for camlock type fasteners FLYAWAY SEAT an aluminum ventilation louver panel in the top aft portton of Zone Samuel R Swah 15 May 1970 128 p 2 and aluminum ribs formers and baffles inside the nacelle in the (AD 71 1642 USNA-TSPR 3) Avail NTlS CSCL 1/3 path of fire The fire damage to the engine and accessories was An investigation was made to test the feasibility of the insignificant in regard to engine operation Author use of the flexible rotor blades for a new type of election system to be used by pilots in military service to maneuver to safety rather than remain on the mercy of the wind in a parachute Among designs being considered is an ejection system which works on the N71-11019# National Aviation Facilities Experimental Center autogyro principle Since prior research has already been done on Atlantic City, N J flexible blades the primary problem was to adapt them to an INVESTIGATION OF TWO METHODS FOR IMPROVING election system Different blade configurations were tested in order THE CRASHWORTHINESS OF INTEGRAL FUEL TANKS to find one which would be stable through all ranges of RPM within

Final Report, ~ 1967 1970 the structural limits of the blade and which would satisfactorily Robert H Ahlers Nov 1970 19 p ref autorotate Results indicate that the use of flexible blades on an (FAA-NA-70-46 FAA RD-70-56) Avail NTlS escape system is feasible and very advantageous due to their light F-86 droppable fuel tanks fitted with reticulated polyurethane weight and ease of storage within the limited confines of a cockpit foam and filled to capacity with JP-4 fuel, were drop tested and The construction of a model was also undertaken which will be used catapulted to test the effectiveness of the foam in reducing fuel to test the autorotative aualities of the blades Author (TAB) spray and leakage at impact Also. structurally reinforced DC-7 integral wing tanks were impacted against an upright beam restrained by a steel shear pin to limit the loads The forward spar caps were N71-11023# Stanford Univ Calif Oept of Aeronautics and strengthened with aluminum alloy doublers and chordwise Astronautics stiffeners to determine the effect of structural modifications on the OPTIMIZATION TECHNIQUES IN AIRCRAFT crashworthiness of the structure It was determined that the 10 CONFIGURATION DESIGN pores per inch and the 60 pores per inch polyurethane foam have Brent Silver and Holt Ashley Jun 1970 59 p refs little effect on the attenuation of fuel misting and spilling The (Contract F44620 68 C 0036) addition of a 0040 inch thick doubler strip to the upper and lower (AD 711410 SUDAAR 406 AFOSR 70 2361TR) Avail NTlS DC-7 wing skins did not appreciably decrease the vulnerability of the CSCL 1/3 integral tank to leakage. but the front spar rails when reinforced The application of optimization techniques to aircraft by chordwise structural shapes did increase impact resistance configuration design is discussed Advantages and disadvantages of Author automated search methods are compared with those of parametric

48 N71-11030

analysis methods The formulation of the design problem for direct use5 in the generation of the 1969 NECTP (Northeast Corridor search methods using a normalization procedure is developed Transportation Project) record run series A modal configuration can Various direct methods are briefly described Operational results be described by its network and by the vehicles which traverse that using several of these methods are reported for aircraft configuration network The report presents the physical and economic design problems Gradient methods are found to give disappointing characteristics of the VTOL and STOL vehicles and the terminals and results when compared with certain non-gradient methods Reasons links which comprise their service networks Author (USGRDR) are suggested for this behavior The future promise of man-computer interactive design is briefly described Author (TAB1

N71-11028# Rhode Island Statewide Comprehensive N71-11024# National Transportation Safety Board. Washington, Transportation and Land Use Planning Program, Providence. D.C. Bureau of Aviation Safety. STATE AIRPORT SYSTEM INVENTORY: AN INVENTORY AIRCRAFT ACCIDENT REPORTS: BRIEF FORMAT, US OF THE EXISTING AIRPORT SYSTEM IN RHODE ISLAND CIVIL AVIATION, ISSUE NO. 4,1989 ACCIDENTS Kent L. A. Zimmerman, William M. Davies, and Richard J. Shapiro Aug. 1970 501 p irs File No. 1-0047-0057: Oct. 1969 163 p refs Supported by HUD and Dept. of 0059:3-2701-2999.3001-3600 (NSTB-BA-70-4) Avail: NTlS Transportation its Tech. Paper No. 14 Sixty-four accidents including foreign registered aircraft involved 1PB-189332) Avail: NTlS CSCLOl E in accidents in the U.S.are presented. The types of aircraft. pilot Contents, Rhode Island aviation history. State operated Certificates. accidents, aircraft damage, and human injuries are airports and heliport. Private airports. Military airports and heliports, listed in tabular form. J.A.M. and Data summary. USGRDR

N71-11025*# National Aeronautics and Space Administration. Langley Research Center, Langley Station, Va. N71-11029# Mitre Corp Baileys Crossroads Va WIND-TUNNEL INVESTIGATION OF VARIOUS AIR MODE SERVICE ANALYSIS IN THE NORTHEAST SMALL-SCALE ROTOR/WI NG CONFIGURATIONS FOR CORRIDOR VTOL COMPOSITE AIRCRAFT IN THE CRUISE MODE Michael J Roberts and Donald Goldman Dec 1969 209 p James P. Shivers Washington Oct. 1970 227 p refs refs (NASA-TN-D-5945; L-7133) Avail. NTlS CSCLOlC (Contract DOT-7-35248) NECTP-215) Avail NTlS CSCLOlB A subsonic wind-tunnel investigation of a smail-+ci!e rPE-!SC935 kiiR-4i Ti 7n,,,,/,..:-- \--a The innovative air modes analyzed for the NECTP (Northeast .-.-.,wwo~~y Y I UL airpiane has been conducted in a low-speed tunnel with a 12-foot octagonal test section at the Langley Research Corridor Transportation Project) were Vertical takeoff and landing Center to determine the aerodynamic characteristics of the model in (VTOL) and short takeoff and landing (STOL) The report describes the cruise mode. Five three-blade and three four-bland rotor/ wing the air mode operator supply models and the procedures which planforms were tested on a model with a conventional fuselage generate the VTOL and STOL modal service characteristics within and tails. The investigation consisted of tests in the cruise the NECTP model system The results of all of the model system configuration to determine lift. drag, static stability and control runs containing VTOL or STOL are analyzed and presented in characteristics. and the dynamic rolling-stability derivatives Studies summary form Author (USGRDR) with the rotor/wing fixed at various azimuth angles were made to determine the vi!i-.g zr.2 9;iihing moments due to variation of the azimuth angle and the effectiveness of the controls for countering these moments. Author N71-11030# United Aircraft Corp Stratford Conn Sikorsky Aircraft Div EFFECT OF ROOT CUTOUT ON HOVER PERFORMANCE Final Report.Jun 1969 -Apr 1970 Sebastian J Cassarino Wright Patterson AFB Ohio AFFDL Jun N71-11026# National Aeronautics and Space Council 1970 63 p refs Washington D C (Contract F3367 5-69 C-1 176) THE STATUS OF FEDERAL INVOLVEMENT IN SHORT (AD 7 1 1396 SER-5066 1 AFFDL-TR-70-701 Avail NTlS CSCL HAUL AIR TRANSPORTATION 1/3 Richard D FitzSimmons and William E Thurman [1970] 3 p Tests were conducted to determine the effect of blade Avail Issuing Activity root cutout on the hovering performance of a helicopter rotor Interagency cooperation is discussed that could lead to Rotor thrust and torque characteristics were measured on model a short haul air transportation program taking into account the rotors with root cutouts of 10 25 40 and 50 percent radius In realities of fiscal restraints and the somewhat overlapping agency addition. smoke was ejected from various spanwise locations along responsibilities Some of the aspects of federal involvement are the trailing edge of blades with cutouts of 10 and 50 percent The discussed Some thoughts on the interaction of civilian and military wake patterns developed below the hovering rotor were agencies and the private industry and municipalittes are described photographed and examined for several rotor speed/collective pitch Finally. the impact of this new involvement of the government is combinations to determine how these parameters affect the wake developed in view of the many benefits which should accrue to structure The test data revealed a loss in hovering efficiency of the nation Author 5 to 7 percent for the 50 percent cutout rotor at a typical design thrust coefficient This result is in agreement with previous calculations made using blade element-momentum theory The loss in hovering efficiency was highly nonlinear with increasing root N71-11027# Mitre Corp., Baileys Crossroads. Va cutout This behavior was not predicted by blade element-momentum V/STOL MODE DESCRIPTIONS theory or a prescribed wake hover performance analysis using a Donald Goldman and Michael J. Roberts Dec. 1969 68 p refs standard wake pattern The flow visualization phase of the (Contract DOT-7-35248) investigation showed that the increase in root cutout decreases the (PB-190940; MTR-4113: NECTP-220) Avail: NTlS CSCLOlB radial contraction of the tip vortex When this result was included The report documents the various vertical takeoff and landing in the prescribed wake analysis the correlation accuracy was (VTOL) and short takeoff and landing (STOLI modal configurations improved Author ITABI

49 N71-11031

N71-11031+ Air Force Cambridge Research Labs, Bedford. Mass. 14Apr 1970 POINT AND ROUTE TEMPERATURES FOR SUPERSONIC Avail Permanent Subcomm on Invest AIRCRAFT Congressional testimony is reported on investigation of the Irving I. Gringorten and Paul Tattelman 28 Jul. 1970 200 p TFX aircraft contract Testimony is given on the primary mission refs Its AFCRL-AFSIG-223 of the aircraft. the contract schedule, proposed changes in the (AD1712017; AFCRL-70-041 Avail: NTlS CSCL 4/2 design. and difficulties encountered during development and testing The atlas of the Northern Hemisphere temperature field RB at SST attitudes consists of 84 plates showing the isotherms at eirh nf the constant-pressure levels, 100, 5O.and 30 mb. standard altitudes of 53,000, 67.500. and 78,500 ft, respcciively. Fo: each level and season there are seven maps giving the 2-. lo-. 25-. 50-. N71-11035# lnsuiui Fiancc A!!amvd d~ Recherches St Louis 75-. 90-, and 98-percentile temperatures. The charts were prepared (France) !rem !wire-dailv grid-point data obtained frotn charts covering the GROUND AND BUILDING WALL REGISTRATIONS OF area from the North Pole to approximateiy i5 uag N fo: :hz BOOMS AND NOISES CAUSED BY STARFIGHTERS AND period 1959 to 1968. Charts were computer analyzed. Since fuel OTHER SOURCES [KiiALLE UND GEFAIISCHE VON consumption of supersonic aircraft is quite dependent upon STARFIGHTERN UND ANDEREN QUELLEN. AN temperature, each of the 84 plates is accomoanied by a graph BODENPUNKTEN UND HAUSWANDEN REGlSTRlERT] giving the probability that the temperatures on any route plotted on M Froboese G Mathieu and D Seydel 27 Jan 1970 129 p the map will equal or exceed the temperatures shown on the map refs In GERMAN FRENCH summary While the 84 maps are intended for straightforward informational Avail NTlS use in SST flight~planning.there are many noteworthy features that The mechanical effects of sonic booms and detonation are revealed by the percentile-type presentation Author (TAB) waves on buildings were studied during overflights of supersonic Starfighters as well as in connection with explosive detonations of varying force and density and through shock waves triggered by ordnances of differing calibers Pressure loads and shock wave pressure-time propagation were measured and registered at several N71-11032*# Tracor. Inc.. Austin. Tex. Sociometric Research points on the buildings wall and in its vicinity in order to determine Div. qualitative and quantitative modifications in supersonic waves COMMUNITY REACTION TO AIRPORT NOISE, VOLUME during their propagation along the measuring points Also measured 2 Final Report were noise effects of low flying 3ell UH 1D and Sikorsky H 34 4 Sep 1970 245 p refs helicopters and the F 104 on several components of the test (Contract NASw-1549) building Transl by G G (NASA-CR-11131 6. T-70-AU-7454-U-Vol-2) Avail. NTlS CSCL 01E A study of the relationships of large numbers of variables(physica1. psychological. and social) with community reaction !o the noise of aircraft around international airports in large U.S N71-11036# lnstitut Franco-Allemand de Recherches St Louis cities is described The seven malor airports involved were Logan (France) International-Boston. O'Hare International-Chicago. Dallas SONIC BOOM PROPAGATION DURING SUPERSONIC International-Dallas. Stapleton International-Denver. Los Angeles FLIGHT IN UNPERTURBED ATMOSPHERE PART 1: International-Los Angeles. Miami International-Miami, and Kennedy HORIZONTAL STRAIGHT FLIGHT [PROPAGATION DU International-New York. Author BRUIT BALISTIQUE D'UN AVION DANS L'ATMOSPHERE NON PERTURBEE LERE PARTIE AVION EN VOL RECTI LI G NE H OR1ZO NTAL] F Reggiani 25 Feb 1969 36 p refs In FRENCH GERMAN summary N71-11033# TAW Systems Group Washington D C (Contract DRME 69/415) HSGT SYSTEMS ENGINEERING STUDY, TRACKED AIR Avail NTlS CUSHION VEHICLES Final Report, 1967-1969 Numerous formulas are presented that are applicable to Dec 1969 606 p refs the analysis of sonic aircraft boom propagation during supersonic (Contract DOT C-353 661 flight in an unperturbed atmosphere Sound wave characteristics (PB-190939 NECTP-219) Avail NTIS CSCL 13F are used to form the equations for determining the caustic its Eased on requirements and constraints chosen for an intersecting ground points as well as expressions for the radii of operational system subsystem alternatives are evaluated and the curvatures at some important points The two cases considered selected subsystems are synthesized into a TACV system Cost and are (1) a homogeneous atmosphere and (21 an atmosphere with performance are estimated over a range of parameters such as constant temperature gradients Example calculation results for real design cruise speed (150 to 350mph) and vehicle capacity (50 to situations are included the flight path IS always considered 150 passengers per vehicle) The configuration defined consists of rectilinear and horizontal and the atmosphere unperturbed trainable electrically powered TACV s which collect power from Transl by G G trackside power rails mounted on the side of a channel guideway Propulsion is by linear induction motors with variable frequency speed control Control of the vehicles. singly or in trains is automated and centralized The vehicles are supported on and guided by peripheral jet air cushions with high pressure air provided by N71-11037* National Aeronautics and Space Administration. electrically driven axial flow compressors Author (USGRDR) Langley Research Center, Langley Sation. Va. HOT AIR BALLOON DECELERATION AND RECOVERY SYSTEM Patent Stanley H. Scher and James C. Dunavant. inventors (to NASA) N71-11034# Committee on Government Operations (U S Senate) Issued 28 Apr 1970 (Filed 14 Nov. 1968) 5 p CI. 244-31: TFX CONTRACT INVESTIGATION, SECOND SERIES, PART Int CI E64b: Int. CI. 8649 Continuation-in-part of US Patent Appl. SN-665682. Filed 31 Aug. 1967 Washington GPO 1970 220 p refs Hearings before Comm (NASA-Case-XLA-06824.2; US-Patent-3.508.724: on Govt Operations, 91st Congr , 2d Sess , 25 26 Mar, 7, 9. and US-Patent-Appl-SN-7759661 Avail: US Patent Office CSCLOl C

50 N7 1- 11 061

A hot air balloon deceleration and recovery system is described only slight. Compaction of the gravel occurred due to increased The balloon IS equipped with ram air openings which permit inflation depth and to the fact that the gravel had laid undisturbed for a long by admitting aerodynamically heated air The balloon inflates during period. It is recommended that harrowing a gravel arrester to the the descent trajectory and acts as a decelerating device Materials full depth would be worthwhile about every 6 months. Author used in the construction of the balloon and methods of fabrication are discussed Author

N71-11041* National Aeronautics and Space Administration Langley Research Center, Langley Station. Va. VARIABLE SWEEP AIRCRAFT Patent N71-11038; National Aeronautics and Space Administration. Edward C. Polhamus and Alexander D. Hammond. inventors (to Langley Research Center. Langley Station. Va. NASA) Issued 6 Sep. 1966 (Filed 30 Mar. 1965) 7 p CI. 244-46 CONTROL FOR FLEXIBLE PARAWING Patent (NASA-Case-X LA-03659; US- Patent-3,270.989: Francis M. Rogallo and William C. Sleeman. Jr.. inventors (to US-Patent-Appl-SN-444087) Avail: US Patent Office CSCLOl c NASA) Issued 21 Mar. 1967 (Filed 9 Feb. 1966) 6 p CI. 244-44 A variable sweep wing employing provisions to compensate for Continuation-in-part of US Patent Appl. SN 338535. Filed 17 Jan. undesirable longitudinal stability problems encountered by variable 1964 sweep aircraft is described. A double-pivot segmented variable (NASA-Case-XU-06958: US-Patent-3.310.261 ; sweep wing eliminates longitudinal pitch-up without the necessity US-Patent-Appl-SN-551815) Avail US Patent Office CSCL 01 C of a low horizontal tail position and compensates for a portion of A method for controlling a flexible wing is described. Boltropes the aerodynamic center shift during changes in wing sweep angle. from the trailing edge of the flexible wing to a control unit in the The configuration incorporates an auxiliary movable surface at the payload provide the control system. Control is accomplished by junction of the leading edge with the fuselage. Movement of the shortening or lengthening the boltrope. By changing the wing auxiliary surface during wing sweep operations provides increased configuration symmetrically. pitch control is provided. while longitudinal stability. P.N.F. asymmetrical variation of the wing planform will provide roll control. Response of the vehicle is dependent upon the rate at which the boltrope is shortened and lengthened, this speed being determined by a conventional servo mechanism. P.N.F. N71-11042# Royal Aircraft Establishment Famborough (England) REQUIREMENTS FOR EJECTION SEAT SYSTEMS [ANFORDERUNGEN AN SCHLEUDERSlTZSYSTEME1 U Schmidt Inn !970 25 p refs Trans1 into ENGLISH from N71-11039: National Aeronautics and Space Administration Deutsche Luft- und Raumfahrt (West Ger). Mitt 69-11 Manned Spacec:aft Grtiar. iiouston, Tex p 372-393 GRAVITY STABILIZED FLYING VEHICLE Patent (RAE-LIB-Trans-14711 Avail NTlS Harold 1. Johnson, inventor (to NASA) Issued 20 Jan. 1970 (Filed The requirements for ejection seat systems are expounded 14 Nov. 1968) 6 p CI. 244-23: Int. CI. E64c and discussed in terms of some extreme flight conditions specified (NASA-Case-MSC-12111-1: US-Patent-3,490,721; by the parameters airstream velocity. altitude attitude aid rate of US-Patent-AppCSN-775877) Avail: US Patent Office CSCL 01C descent The physiologtcal and functional limiting conditions are A hovering-type flying vehicle for manned or unmanned indicated and some possible means of extending the performance use is described in which the lift vector is normally aligned with range of rescue systems are v-serted Author the direction of the prevailing gravity vector without the need for ancillary stabilizing systsms sxC as yvloscopes or manned guidance. The vehicle consists of an upper body section for containing the payload. a lower body section for housing the lifting engine N71-11043: National Aeronautics and Space Administration and its related components. as essentially frictionless universal-type Langley Research Center Langley Station Va joint affixing the upper body to the lower body, and a biasing TRANSLATING HORIZONTAL TAIL Patent means between the bodies at the joint which is set to retain the Morris L Spearman inventor (to NASA1 Issued 3 feb 1970 (filed centers of gravity of the bodies along a common axis. Illustrations 5 Mar 19681 5 p CI 244 43 Int CI B64c of the vehicle embodying the principle concepts and basic (NASA-Case-XLA-08801 1 US Patent-3 493 197 mechanisms in a static stable condition and subsequent to a US Patent-Appl SN-7105331 Ava4 US Patent Office CSCLOl C J M. destabilizing condition are included. A method for improving aircraft stability through translational motion of the horizontal tail surface IS described The horizontal tail surface is located at the aft of the fuselage during low speed flight and is moved forward toward the fixed wing trailing edge as airspeed increases Variations in the positions of the tail surfaces N71-11040#' Royal Aircraft Establishment. Famborough (England) provide lift. control and stability In varying amounts depending on SOFT-GROUND ARRESTING OF CIVIL AIRCRAFT. the airspeed of the aircraft PNf INFLUENCE OF GRAVEL DEPTH AND TYRE INFLATION PRESSURE E Bade Jan 1969 17 p refs (RAE-TR-690011 Copyright Avail NTiS The arresting trials carried out with a Lightning aircraft N71-11061*# National Aeronautics and Space Administration to examine the influences of gravel depth and tire inflation pressure Lewis Research Center Cleveland Ohio on deceleration are described The mean decelerations achieved at SERVOSYSTEM DESIGN OF A HIGH-RESPONSE normal main wheel tire pressures of 260 Ib/sq in in a 30 inch SLOTTED-PLATE OVERBOARD BYPASS VALVE FOR A depth of 3/4 inch - 1/4 inch rough irregular gravel have compared SUPERSONIC INLET with previous results in depths of 12 inches and 18 inches They George H Neiner Washington Nov 1970 22 p refs show that mean deceleration can be increased by an increase in (NASA-TN-D-6081. E-55291 Avail NTlS CSCL 10A gravel depth but not in direct proportion and that the effectiveness The valve utilizes a muitislotted plate to achieve flow area of increased depth is greatest at lower aircraft speeds Mean change with minimum stroke and mass of moving parts The decelerations achieved at main wheel tire pressures of 190 Ib/sq servosystem uttllzes a hydraulic piston-in-cylinder actuator in were lower than those at 260 Ib/sq in but the difference was close coupled to a two-stage electrohydraulic servovalw Vs:n~

51 N71-11129 electronic compcnsatioq the small-amplitude response of the system, investigators are also analyzing 1 55 cm imagery of Mount Rainier modulating 14 percent of its full flow area, is flat within 0 to -3 where effects of terrain slopes parallel and perpendicdlar to the db to 1 lOHz Full valve flow area was 25 sq in (161 sq cm) A flight line are encountered These data correspond to a LarietV c' mathematical model of the system IS presented and analytical snow and ice conditions Author resDonses are compared with experimental data Author

N71-11422*# General Applied Science Labs, Inc Westbury. N Y N71.1 1129# Boeing SLieiTiqfic Research Lahs Seattle Wash DESCRIPTION AND CAPABILITIES OF A TRAVELING Flight Sciences Lab WAVE SONIC BOOM SIMULATOR SYMPOSIUM ON AIRCRAFT WAKE TURBULENCE Roger Tomboulian and William Peschke Washington GASA ?!=v SeD 1970 72 p refs Conf held at Seattle 1-3 Sep 1970 1970 68 p refs (AD-712080 D1-82-09931 Ami iiiiS CSC: 2a/G (Contract NASl -8940) Session topics Fundamental problems Experimental methods (NAbA-CR-iGSG, TR 734) A\I?II NTlS CSCL 148 Flow visualization presentations and results Wake formation and Studies were made to obtain a more complete undersrandiily character Stability and decay of trailing vortices Aircraft response of performance range and capability of a traveling wave type Sonic to wake turbulence and Control and use of trailing vortices boom simulator Specifically. the studies were cortcerned with TA 8 methods and techniqw? to reduce unwanted let noise. improved definition of the simulator s operating range. development Of non idealired wave shapes in the simulator and the use of shock wave absorber techniques in the sirnulator The simulator was N71-11139# Lehigh Univ Bethlehem Pa Dept of Mechanical investigated in both a valve operated mode and a diaphram operated Engineerilg and Mechanics mode with the valve mode showing advantages for longer duration A STUDY OF FLOW FROM TWO PLANAR NOZZLES and higher overpressure N-waves and the diaphram mode Jerzy A Owczarek Donald 0 Rockwell and Y S Cha Jun 1970 showing advantages for obtaining minirnum rise times Means for 43 p refs substantially reducing the ]et noise and for additional attenuation Of (Contract N00014-69 A 0417 Pro] Themis) unwanted high frequencies were indicated Author (AD-711313 THEMIS-LU TR 1) Avail NTlS CSCL20/4 The report describes an experimental investigation of the characteristics of low-Mach number flow of air from each of two planar nozzles having an aspect ratio of 3 at the exit The nozzles had rectangular inlets with rounded leading edges to channel the N71-11426 *# National Aeronautics and Space AdministratJon flow from round stagnation tanks The nozzle which produced Lewis Research Center Cleveland Ohio nonuniform flow at the exit was tested with and without a flow EVALUATION OF NiCrAl AND FeCrAlY CLADDINGS ON straightener inside Most experiments were performed at the Reynolds T D-NiCr. MACH 1 BURNER RIG TESTS AT2100 F (1149 c) number based on the width of the nozzle at the exit and on the M A Gedwill and S J Grisaffe Nov 1970 13 p refs average flow speed at the nozzle exit of 12 400 The tests showed (NASA-TM-X 52916 E-6021) Avail NTlS CSCL 11F that the planar convergent nozzle having a concave convex inner Foils of several oxidation resistant alloys approximately wall profile without a flow straightener in it produced a very 5 mils thick were diffusion bonded to TD-NiCr The protection nonuniform total pressure distribution at the exit The flow potential of these claddings for use on aircraft gas turbine visualization study showed that the regions of low total pressure are components was examined by conducting Mach 1 burner rig tests associated with vortices whose axes have the general direction of the at 2100 F for time periods up to 160 hours using 1 hour cycles main flow The planar convergent nozzle having a concave-straight The NiCrAl cladding was protective for over 120 hours All of the inner wall profile tested without a flow straightener in it produced FeCrAlY alloys however began suffering from oxidation and loss uniform total pressure distribution at the exit outside of the of cladding after 20 to 40 hours of testing Visual indications of boundary-layer region Small concentrated vortices were observed to interdiffusion were observed in TD-NiCr for both cladding systems exist inside both nozzles Author (TAB1 Author

N71-11466*# Massachusetts lnst of Tech Cambridge N71-11160*# Geological Survey Tacoma Wash Engineering Projects Lab SNOW AND ICE SENSING WITH PASSIVE MICROWAVE AN APPLICATION OF PREDICTOR DISPLAYS TO AIR AND GROUND TRUTH INSTRUMENTATION RECENT TRAFFIC CONTROL PROBLEMS RESULTS, SOUTH CASCADE GLACIER William Bradford Rouse (M S Thesis) Sep 1970 1 15 p refs M Meier and A T Edgerton lr~NASA Manned Spacecraft (Grant NG L-22-009-002) Center 2d Ann Earth Resources Aircraft Program Status Rev Vol (NASA 1 11372. DSR-70283-15) Avail NTlS CSCL 17G 3 1969 15 p refs Prepared in cooperation with Aerolet Gen The feasibility of using a predictor display system to help Corp El Monte Calif (See N71-1 1151 02-13) solve terminal area air traffic control problems is investigated A Avail NTlS CSCL 08L computer-based predictor display is proposed as an aid for the air Field experiments utilizing a multifrequency microwave traffic controller to use in guiding aircraft to the glidepath It was radiometry field laboratory were conducted in the Pacific Northwest determined that learning, in most cases was faster with the to assess the effects of melting layering surface roughness density predictor display However the difference in performance with and variations etc on microwave emission and to determine effective without the predictor display decreased as learning proceeded The penetration as a function of sensor wavelength Laboratory studies predictor display helped to reduce errors, but not task completion involvpd measurement of the dielectric properties of snowpacks at time A prediction which was too long and displayed more than niicrowave frequencies Analytical modelirig consisted of formulation the necessary amount of information increased task completion of models to describe vertically structured media in which both the time The prediction display significantly improved performance for dielectric propeities arid physical temperature are permitted to vary the easier tasks while it did not significantly improve performance with deoth During field studies the investigators experienced for the more difficult tasks Author difficulty in obtaininy reliable ground truth measurements of snow moisture To improve confidence in this measurement a series of tests were conducted on the South Cdscade Glacier where several N71-11470# Office National d Etudes et de Recherches techniques for determining snow moisture were compared The Aerospatiales Paris ( Francel

52 N71-11626

THE AEROTHERMODYNAMIC TEST CENTRE OF The laminar boundary-layer equations were solved for MODANE-AVRIEUX [LE CENTRE D'ESSAIS incompressible flow past a parabola at angle of attack Such flow AEROTHERMODYNAMIQUES DE MODANE-AVRIEUX] experiences a region of adverse pressure gradient and thus can be Marcel Pierre and Guy Fasso 1970 47 p refs In FRENCH employed to study the boundary iayer separation process The ENGLISH summary present solutions were obtained numerically using both implicit and (ONERA NT 166) Avail NTlS Crank Nicholson type difference schemes It pas found that in all The Modane Center supplied directly by water under 800 cases the point of vanishing shear stress ithe separation point) m pressure and giving up to 88 000 kW includes four wind displayed a Goldstein type singularity Based on this evidence. it is tunnels and various smaller facilities The wind tunnels are the S1 concluded that a singularity is always present at separation continuous 8 m diameter sonic wind tunnel the 52 continuous 1 80 independent of the mildness of the pressure gradient at that point m square sub trans- and supersonic (up to Mach 3) wind tunnel Author (TAB) the S3 0 80 m square blowdown trans- and supersonic (up to Mach 4 5) tunnel and the 54 0 60 to 0 90 m diameter blowdown hypersonic (from 6 to 12 Mach) tunnel The smaller facilities N71-11520*# National Aeronautics and Space Administration include vacuum tank exhaust flow Simulation and balance calibration Langley Research Center Langley Station Va benches Both these and the tunnels as well as tests performed BOUNDARY-LAYER TRANSITION STUDY OF SEVERAL at the Center are described ESRO POINTED BODIES OF REVOLUTION AT SUPERSONIC SPEEDS William A Cassels and James F Campbell Washington Nov 1970 69 p refs N71-11474# National Aviation Facilities Experimental Center (NASA-TN-D-6063 L-7159) Avail NTlS CSCL 20D Atlantic City N J Boundary-layer transition by the sublimation and VISUAL AIDS FOR SECONDARY AIRPORTS Final Report. impact-pressure techniques and force tests were performed on three Sep 1968 May 1970 Haack Adams bodies of revolution of fineness ratios 7 10 and Thomas H Paprocki Sep 1970 35 p 13 at zero angle of attack for free-stream Mach numbers of 2 00 (FAA NA 70 51 FAA RD 70 59) Avail NTlS 2 75 and 4 63 and a range of Reynolds numbers based on model A new type lighting and marking system for use at small length of 6 to 15 000 000 with and without a roughness strip The general aviation type airports under VFR weather conditions was grit method of inducing turbulence was found to provide for a installed at the municipal airport Ocean City New Jersey for nearly complete turbulent flow over the models at the lower Mach evaluation The system consisted of fluorescent runway edge and numbers and higher Reynolds numbers considered while the approach lighting systems an incandescent sequenced flashing light amount of trip drag was less than 8 percent of the model drag with system a Simplrfled Abbreviated VisJal Approach Slope Indicator transition fixed A method nf pn?P-p'e::ng sUSl,inaholi dara IS (SAVASI) system painted aiminq ooint riinway -a*kizg; 2nd discussed and used and the results compare well with the rerro-retlective centerline and threshold markers AI1 of these visual impact-pressure results Author aids were evaluated Individually and in addition the fluorescent runway edge lighting fixtures were evaluated in comparison with standard incandescent edge lighting units It was determined that all of the above mentioned visual systems provided satisfactory N71-11579*# National Aeronautics and Space Administration. guidance under VFR conditions and that the fluorescent type of Lewis Research Center, Cleveland. Ohio. runway edge light fixture can provide excellent VFR lighting with DESIGN STUDY OF SHAFT FACE SEAL WITH fewer maintenance problems and lower operating costs than SELF-ACTING LIFT AUGMENTATION. 2: SEALING DAM the present stanoard medium intensity runway edqe liqht flxturp John Zuk, Lawrence P. Ludwig. and Robert L. Johnson Washington Author Nov. 1970 29 p refs (NASA-TN-D-7006: E-5796) Avail: NTlS CSCL 11A Analytical studies made on a 6.50-inch nominal dam diameter seal with sealed pressure to 315 psia revealed that a shaft face N71-11510# Office National d Etudes et de Recherches seal with self-acting lift pads can be designed to yield low leakage Aerospatiales Paris (France) and positive sealing face separation. The study showed that the HOLOGRAPHIC INTERFEROMETRY BY RETRO-DIFFUSION leakage flow through the sealing faces can become choked at [INTERFEROMETRIE HOLOGRAPHIQUE PAR pressure ratios as low as 4 to 1 for typical seal operating film RETRO-DIFFUSION] thicknesses. Slight angular deformations of the sealing faces had a Jean Marie Caussignac 1970 5 p refs In FRENCH Presented significant effect on the pressure gradient within the seallng faces: at the Intern Symp on Holography. Besancon France 6 11 Jul thus. seal force balance was correspondlngly affected. For sealing 1970 Submitted for publication faces having angular deformation, the radial width of the sealing dam (ONERA-TP-852) Avail NTlS was found to markedly affect the seal force balance. Author Interferential holography permits the visualization of fluid flows inside aerodynamic wind tunnels In case of turbomachinery. only a retro-diffusion setup can be considered The material connexion of the diffuser to the wind tunnel entails new constraints The paper deals with the problems related to the dtffuser N71-11626# Advisory Group for Aerospace Research and displacements and deformations ESRO Development, Paris (France) ADVANCED TECHNOLOGY FOR PRODUCTION OF AEROSPACE ENGINES Sep 1970 318 p refs Presented at the 35th Meeting of the N71-11519# Virginia Polytechnic lnst, Blacksburg Dept of AGARD Propulsion and Energetics Panel, London 6-10 Apr Engineering Mechanics 1970 INCOMPRESSIBLE LAMINAR BOUNDARY LAYERS ON A (AGARD-CP-64) Avail NTlS PARABOLA AT ANGLE OF ATTACK. A STUDY OF THE Conference papers are presented on the following areas of SEPARATION POINT research engine manufacturing technology and design. materials M J Werle and R T Davis Aug 1970 29 p refs test techniques. new manufacturing techniques. and influence of (Contract NO0014 70-C 0024) advanced technology on engine accessories (AD-712084 VPI-E-70 17) Avail NTlS CSCL20/4

53 N71-11627

N71-11627# Rolls-Royce. Ltd Eristol (England) Manufacturing The removal of metal components by electrolysis shows Development Dept promise for overcoming some of the problems encountered in ADVANCED MANUFACTURING TECHNOLOGY IN using aeronautical parts in electrolytes. In the case of electrolyte MODERNJET ENGINES rectification. methods and techniques were developed to give A H Meleka In AGARD Advanced Technol for Production of descriptions of the components on the basis of this discovery. The Aerospace Eng Sep 1970 5 p industralization procedure is effective on different motor parts, Avail NTlS rotating machine blades and shafts. The material is a combination Improved manufacturing technology in aerospace indusrry of refractory. steel. and sintered alloys and is free of burns, cracks, encompasses a wide array of methods and processes from value and superficial constraints. The action of the electrolyte is localized engi-eernng analvses to aoolied metal working techniques Special in the work zone. The state of the surface obtained and the emphasis is placed on metal forming part joining electrochemical precision of the surface depends on the quality of the work su~face machining and electron beam welding methods Also stressed are the nondestructive tests that find application during the production of the rotating electrode. Transl. by E.H.W. P'OCPSS DG

N71-11638# Societe Microfusion. Paris (France) CONTRIBUTION OF FOUNDRY PRECISION IN THE N71-11635# Air Force Systems Command, Wright-Patterson DOMAIN OF AERONAUTICALTURBINES [APPORTDE LA AFE Ohio Air Force Materials Lab FONDERIE DE PRECISION DANS LE DOMAINE DES TECHNOLOGY OF MANUFACTURING AND TURBINES AERONAUTIQUES] ADVANCEMENT OF TECHNOLOGY FOR TURBINE ENGINE R Cameo In AGARD Advanced Technol for Production of COATINGS Aerospace Eng Sep 1970 12 p ref John R Williamson In AGARD Advanced Technology for Avail NTlS Production of Aerospace Eng Sep 1970 13 p refs The influence of foundry precision in alloys used for the fabrication of aeronautical turbine blades is discussed A description Avail NTlS of the interior forms and cooling points of the turbine blades is Advancement in engine coating technology is centered around given The results obtained in the models of cylinder wheels for erosion resistance and coatings to permit increased performance gains a special duty machine answer the need of motors in the for future aircraft engines Present programs include development of manufacturing techniques for chemical vapor deposition of apronautical domain Transl by E H W titanium carbide for erosion protection of titanium blades and vanes in helicopter engines. chrome aluminum coatings for oxidation resistance of thoria-dispersion strengthened nickel. and various programs for chromium-titanium silicon coatings for columbium and N71-11639# TRW. Inc., Cleveland, Ohio. tungsten/tungsten disilicide codtings for tantalum Author A COMPARISON OF HIGH ENERGY RADIOGRAPHIC TECHNIQUES FOR LARGE DIAMETER TITANIUM BILLETS F. J. Sattler In AGARD Advanced Technol. for Production of Aerospace Eng. Sep. 1970 15 p refs N71-11636# Societe Nationale lndustrielle Aerospatiale. Paris Avail. NTlS (France) Radiographic techniques for billets up to 17 inches in diameter APPLICATION OF CORRUGATED CORE SANDWICH were established in the programs since some engine disks will be STRUCTURES TO POWERPLANT COMPONENTS forged from the larger diameter billets. Two high energy radiographic [L'EMPLOI DES STRUCTURES DU TYPE SANDWICH A units were investigated for this application. A commercial linear AME ONDULEE DANS LES CONSTITUANTS DES UNITES accelerator and a betatron were used to analyze the effects of MOTRlCES] various lead screen, film, and geometry combinations on image A Gozlan In AGARD Advanced Technol for Production of sensitivity. Standard radiographic penetrameters were employed for Aerospace Eng Sep 1970 14 p refs evaluating the radiographic procedures. The inspection method Avail NTlS resolved a 40 thousandths inch diameter by 40 thousandths inch In order to save weight and withstand increasingly stringent deep hole through 17 inches (432 millimeters) of titanium. Various operating conditions. great use is currently made. in the construction data are illustrated which reveal the effects of front and back lead of airframes and missiles of new types of basic structure where screen thickness on exposure and resolution. The utility of each matter is so distributed as to improve considerably the local unit is discussed in view of the achievable resolution and the stiffness Such is the case with isotropic materials like honeycomb economics of the radiographic procedures. Author sandwich or orthotropic materials like corrugated core sandwich The present paper deals with a material of the latter type made out of stainless or refractory metal sheet and its applicability to N71-11641# Motoren- und Turbinen-Union Muenchen G.m.b.H. some components of power units It is shown how this material (West Germany). can be used in the design of such selfcooled components as are X-RAY FLUORESCENCE ANALYSIS AS AN AID TO internal insulating shrouds for combustion chambers of ramjet. PRODUCTION AND REPAIR OF AIRCRAFT ENGINES turbo-ramjet and turbofan engines Author Harald Simon In AGARD Advanced Technol. for Production of Aerospace Eng. Sep. 1970 14 p Avail. NTlS X-ray fluorescence is a relatively new analytical technique N71-11637# Societe Nationale d'Etude et de Construction de which is reliable. versatile and economic, and is therefore findig Moteurs d'Aviation. Paris (France) Div Hispano Suiza increasing use in industry. The technique uses X-ray radiation of ELECTR OLYTl C RECTIFICATION : APPLl CATION IN THE the specimen to cause excitation and produce fluorescence which AE RONAUT1 CS INDUSTRY [LA RECTI Fl CATION is scanned by a monochromator. measured by detectors, amplified ELECTROLYTIQUE: APPLICATIONS DANS L'INDUSTRIE and recorded. The technique identifies and estimates the elements AERONAUTIOUE] which are sought. Examples of the applications of this versatile J Poyau and P Rame ln AGARD Advanced Technol for analytical tool are: (1) Analysis of raw materials. fuels, chemical Production of Aerospace Eng Sep 1970 17 p processing solutions and metal finishing compounds: (2) inspection of components at overhaul; and (3) detection and correction of Avail NTlS manufacturing defects. Author

54 N71-11681

N71-11644# Motoren-und Turbinen-Union Muenchen G m b H bay. varying in temperature from 1 15 C at the front of the engine (West Germany) to 180 C at the rear The fuel temperature can vary from -54 ELECTRON BEAM WELDING OF HIGH-DUTY ROTATING C to 160 C and the oil temperature from -54 C to over 200 C ENGlNE PARTS With the economics of the Concorde demanding high aircraft Wolfgang Hansen In AGARD Advanced Technol for Production utilization. and the possible hazardous effects of fuel leakage it was of Aerospace Eng Sep 1970 12 p obvious at the start of the project that a high standard of piping Avail NTlS and sealing technology was required It is the purpose of this paper Two examples are used to describe the procedure which to describe some of the areas to which particular attention is being can be used to investigate the suitability of electron beam welding paid to realize this objective Author on rotating components After welding of a turbine disc. residual stresses were measured which exceeded half of the ultimate strength The weld joint between a turbine disc and a shaft could be considerably improved by specific heat treatments From the experiences accumulated up to now, some rules for the design engineer are derived and illustrated Author N71-11654# Pisa Univ. (Italy). FABRICATION TECHNIQUES OF COMPACT FLUIDIC CONTROLEQUIPMENT FOR AEROSPACE ENGINES R. Laneretti. G. Nardi, and D Dini In AGARD Advanced Technol. for Production of Aerospace Eng. Sep. 1970 25 p refs N71-11647# Societe Nationale d'Etude et de Construction de Moteurs d'Aviation. Corbeil (France). Avail. NTlS INTRODUCTION OF THE ECM IN THE AERONAUTICS First attempts to produce fluidic elements made use of INDUSTRY [INTRODUCTION DE L'E.C.M. DANS photosensitive plastics. Now, for industrial applications, superior L'INDUSTRIE AERONAUTIQUE] materials and production techniques must be used. Methods using G. Foucher In AGARD Advanced Technol. for Production of photosensitive ceramics, electroerosion. metal microfusion. etc.. are Aerospace Eng. Sep. 1970 8 p In FRENCH described herein Block combinations for modular systems and complex logic units. having the distinct advantage of small. compact Avail: NTlS assemblies. are presented. These include binary counters cascades. After a rapid presentation of procedure and different types comparators. converters, sequential circuits. liquid level sensors and of machines, some technological definitions on the concepts and entire logic circuits suitable for control of gas turbines and aerospace utilization of cathodes, fixtures, elements. and different problems the engines. Also fluidic carburation and fuel injection control on encountered in this technique are given. Particular attention is reciprocating engines are discussed. Very simple, low cost fluidic given to the problem of lowering fatigue limits and the average of control systems for industrial applications exhibit many superior restoring it in some of the elements. Transl. by E.H.W qualities. Finally, methods suitable for the economical fabrication of compact and reliable control equipment for aerospace engines are investigated. Author N71-11650# Vereinigte Flugtechnische Werke G.m.b.H.. Bremen (West Germany). MODERN JOINING METHODS IN THE AIRCRAFT AND AEROSPACE INDUSTRY N71-11670# American Cyanamid Co.. Stamford, Conn. Central Lutz Dorn In AGARD Advanced Technol. for Production of Research Div. Labs. Aeiospace Eng. Sep. 1970 20 p refs PASSIVATION OF METAL AIRCRAFT SURFACES Final Avail: NTlS Report, 1Jan. -30Jun. 1970 The present day demand in aerospace technology is for Francis C. Rauch and Fred W Luciw Jul. 1970 29 p refs ultra light structures. However. its realisation for the welding (Contract NO0019-70-C-02281 engineer poses at least two problems: the most recently introduced (AD-7 1 1950: Avail: NTlS CSCL 1 1 /3 high strength materials have more or less unfavourable welding An effort was directed toward the screening of a variety properties: the strength of the welded joint in optimised structures of appropriately modified chelating agents as corrosion resistant should be approximate to that of the base metal. These problems and adhesion promoting treatments for mild steel. stainless steel were solved by improving conventional welding methods and by and titanium alloys. The program was essentially an extension of introducing new methods. Several different types of welding earlier work in which the general validity of the concept had been techniques are described and their advantages and disadvantages demonstrated for aluminum substrates. Several types of chelating discussed. Results show electron beam welding to have the least agents were found to be effective in varying degrees as paint amount of welding damage. best protection from contamination of primers on E4130 annealed aircraft steel and 321 stainless steel. weld area, and it can easily be used for integral welding. The formulation previously found to be the most effective for Applications of welding techniques to aerospace structures are also aluminum proved to be an effective treatment for the ferrous discussed. Author substrates as well. Some indications were obtained that it was superior to stateof-the-art phosphatizing treatments and wash primer as a paint primer for steel. Under application conditions similar to those used for aluminum and steel, titanium was found to be resistant to all of the treatments assayed A technique involving N71-1l663# Rolls-Royce. Ltd . Bristol (England) Olympus 593 abrasion of the titanium submerged in a de-oxygenated solution of Design Office the chelating agent was found to give a substantial increase in the THE INFLUENCE OF THE CONCORDE POWERPLANT paint retaining properties of the titanium. Author (TAB) OPERATING CONDITIONS ON THE DESIGN OF THE OLYMPUS 693 FUEL AND OIL SYSTEM R J Syrnon In AGARD Advanced Technol for Production of Aerospace Eng Sep 1970 8 p N71-11681# Office National d'Etudes et de Recherches Avail NTlS Aerospatiales. Paris (France) The nacelle configuration and engine operating conditions SYNCHRONIZATION OF DISTANT STATIONS BY SIMPLE have had a major effect on the design of the Olympus 593 Engine OVERFLIGHT: OPERATION SYNFRAL for tt.e Concorde aircraft At the cruise condition there IS an airflow [SYNCHRONISATION DE STATIONS ELOIGNEES PAR Of 12 Ibs/sec over the outside of the engine. through the engine SIMPLE SURVOL: OPERATION SYNFRALI

55 N71-11766

Jean Besson. Joseph Cumer Roger Gouillou and Jacques Zakhelm FOR REDUCING ELECTROSTATIC HAZARDS IN THE 1970 33 p refs In FRENCH. ENGLISH summary HANDLING OF HYDROCARBON FUELS Summary Report, (ONERA-NT-lC5) Avail NTlS Jun -Nov. 1969 The most accurate means of synchronization are briefly Charles Martel Jul 1970 43 p refs recalled The simple overflight method is then described, and the H (AD-712368 AFAPL-TR-70-22) Avail NTlS CSCL 21 /4 equipment used is presented Results of a synchronization performed The report describes the results of an experimental evaluation in June 1969 between the Paris and Brunswick Observatories, are of the Static Charge Reducer The Static Charge Reducer is a finally presented Author (ESRO) device which automatically neutralizes an electrically charged fuel as the fuel flows through it The tests conducted confirmed the claims that the Static Charge Reducer would reduce the charge aensity of a flowing hydrocarbon fuel to below 30 microcoulombs per N71-11766* National Aeronautics and Space Administration cubic meter The tests also indicate that two corrosion inhibitor fuel additives significantly affect the electrical conductivity of fuel Langley Fiesearcn Srduoii idilyity SLdllVlI 'id Author (TAB) COOPERATIVE DOPPLER RADAR SYSTEM Patent containing the ASA-3 antistatic additive James H Schrader inventor (to NASA) Issued 27 May 1969 (filed 17 Oct 1967) 15 p CI 343 6 5 Int CI GOls9/56 (NASA Case-LAR 10403 US-Patent-3 447 154 US-Patent Appl SN-676391) Avail US Patent Office CSCL 17G N71-11882'# National Aeronautics and Space Administration A Doppler radar system for avoiding midair collisions between Lewis Research Center Cleveland Ohio aircraft is described A protected aircraft carries a transmitter a ACOUSTIC AND AERODYNAMIC PERFORMANCE OF A transponder and a receiver The intruding aircraft carries a 6-FOOT-DIAMETER FAN FOR TURBOFAN ENGINES. 2' transponder Comparison of signals transmitted by the protected PERFORMANCE OF QF-1 FAN IN NACELLE WITHOUT aircraft with return signals from the transponder of the intruding ACOUSTIC SUPPRESSION aircraft provides warning of the proximity of the aircraft and measures Arthur W Goldstein James G Lucas and Joseph R Balombin the distance separating the aircraft in time to take avoiding action Washington Nov 1970 92 p refs Author (NASA-TN-D 6080 E 5757) Avail NTlS CSCLZlE This fan designed for low-noise output produced significantly less perceived noise at take off and approach condltions than fans in current use Measured broadband noise varied with speed but N71-11768# Centre National d Etudes Spatiales Paris (France) not with aerodynamic blade loading Multiple pure-tone noise was THE PRQlECT DIOSCURES GENERAL INTRODUCTION TO present at 80 percent of design speed and above and at 90 percent THE SYSTEM [LE PROJET DIOSCURES INTRODUCTION of design speed was strongly dependent on loading Blade-passing GENERALE DU SYSTEME] tone noise contributed substantially to noise radiation in front of 8 Manuali 1970 18 p refs In FRENCH Presented at the the fan, but very little rearwards At 90 percent of design speed. Space Symp Rennes France 16 19 Jun 1970 sponsored this noise component varied strongly with loading in a manner jointly by CNES Centre de Perfectionnement Tech and Fac des opposite to the loading variation of the multiple pure tones Sci de Rennes Author Avail NTlS The DIOSCURES project aims at meeting the need of both the merchant navy and civil aviation on or over the Atlantic and N71-11890# Army Mobility Equipment Command Fort Belvoir Pacific Oceans It provides for telephone and data links between Va ground stations and aircraft or ships via satellites It also provides PROPOSED NUCLEAR MAGNETIC RESONANCE METHOD for means of plotting their movements for navigation control OF DETERMINING THE AROMATICITY OF HYDROCARBON purposes Five geostationary satellites are to be launched by 1973 FUELS two over the Pacific Ocean and two over the Atlantic Ocean plus JamesV Mengenhauser Jun 1970 21 p refs one as a standby ESRO (AD-711892 USAMERDC 1983) Avail NTlS CSCL21/4 A new method of determining the aromaticity of hydrocarbon fuels is proposed This method utilizes nuclear magnetic resonance spectroscopy to measure complexation of acceptor molecules by aromatic hydrocarbon donors in the fuel Dichloromethane and N71-1l848# Army Foreign Science and Technology Center nitromethane were found to be satisfactory acceptors for this purpose Washington D C Equations were developed for the general case of N different MICROBIOLOGIC CORROSION aromatic donors, each having a different concentration equilibrium [MIKROBIOLOGICHESKAYA KORROZIYA] constant and complexation shift and with the assumption Of A Smolin May 1970 11 p Trans1 into ENGLISH from Aviat rapid chemical exchange of the acceptor among the N competing Kosmonavt (USSR) no 12. 1969 p 38-39 donors For any unknown fuel the acceptor shift IS a precise (AD-712103 FSTC-HT-23-863-70) Avail NTlS CSCL 6/13 reproducible quantity which may be converted to volume per cent The article is concerned with the microbiologic corrosion aromatics by means of a simple equation The constants in this occurring in the fuel tanks of jet aircraft A series of measures are equation may be determined by standardization with any aromatic noted which can be taken for detection of bacteria and fungi in hydrocarbon or with any mixture of aromatics The method IS fuels in order to prevent contamination of aircraft fuel tanks The applicalbe to any liquid hydorcnrbon fuel and unlike many existing most important measure for contending with this problem appears methods is unaffected by olefins dyes and fluorescent corn to be constant checking on the condition of the fuel from the pounds The precision of the shift measurement IS typically refinery through the tank farm to the fueling equipment at airports 04 Hz which corresponds to 02 0 5 percent aromatics and in aircraft wing tanks Author (TAB) Author

N71-11905# National Aviation Facilities Experimental Center. Atlantic City. N J N71-11876# Air Force Systems Command. Wright-Patterson VISUAL APPROACH SLOPE INDICATOR (VASI) SYSTEM AFB. Ohio Aero Propulsion Lab FOR LONG-BODIED AIRCRAFT Final Report. Jan. May AN EVALUATION OF THE STATIC CHARGE REDUCER 1970

56 N71 - 12037

Robert F. Gates Dec. 1970 34 p refs Two mainshaft face seal configurations for advanced (FAA-RD-70-76; FAA-NA-70-59) Avail. NTlS gas-turbine engines were designed. fabricated, and tested. The seal A comparative evaluation was conductel. ..o methods concepts incorporated lift geometries which used the relative motion of modifying the standard VASIS for use for long-bodied aircraft between the primary seal surfaces to provide positive separation operations. Modification was required due to the greater pilot (film lubrication). One design (self-acting) with shrouded Rayleigh eye-to-wheel height of the larger aircraft which placed these aircraft step lift pads operated with a gas film separating the sealing faces. in a potential undershoot situation when the on-course signals of The other design (hydrodynamic) with a spiral groove geometry standard VASIS were flown. Thirty-four subject pilots flying a variety operated with oil-film separation. Tests of the gas-film seal of aircraft. including the 8-747 and C-5A aircraft. participated in demonstrated the feasibility of operation at gas temperatures to the program. The aircraft were tracked with phototheodolite 1200 F, pressure differentials to 250 psi, and sliding speeds to 450 equipment. and the pilots completed questionnaires at the conclusion ft/sec. Excellent correlations with analytically predicted performance of each flight. The three-bar system. a modification consisting of parameters were obtained. Face wear was less than 0.1 mil after an additional component of the standard VASIS. was a significantly 320 hours at an air temperature of 1000 F, a pressure differential better aid than the white-wing system. a modification incorporating of 200 psi, and a sliding speed of 400 ft/sec. Average air leakage the use of white lights only adjacent to the upwind bar of the during that test was 14 scfm. These operating conditions exceed the capability of conventional contact seals and the air leakage is standard VASIS. Author 1/10 that of a labyrinth seal. Testing of the oil-film seal revealed an inadequate seal force balance. Author

N71-11950# National Aerospace Lab Tokyo (Japan) RESULTS OF STRAIN AND DEFLECTION MEASUREMENTS CARRIED OUT ON MODEL WINGS AND THEIR COMPARISON WITH CALCULATED RESULTS N71-12036*# National Aeronautics and Space Administration. 1970 31 p refs In JAPANESE ENGLISH summary Lewis Research Center. Cleveland, Ohio. (NAL TR-195) Avail NTlS GASFILM SEAL, TYPE A, APPENDIX A Six model two spar wings (three non-swept wings two L. P. Ludwig In Pratt and Whitney Aircraft Develop. of Mainshaft thirty degree swept wings. and one forty five-degree swept wing with Seals for Advan. Air Breathing Propulsion Systems Phase 2 ribs perpendicular to the spars) were tested for strain distributions 23 Jun. 1970 p 65-76 refs and deflections Two model wings jointed to a model center wing Avail: NTlS CSCL 11A by bolts were subjected to symmetrical loadings Calculated strain A face seal with self-acting geometry was designed for distributions and deflections were obtained by the finite element operation in gas turbine engines. Because of the noncontacting method Comparison with test results showed satisfactow agreement L-.tsetuie ihe seai has nigh speed and long life potential. Extensive for me strain distributions The comparison showed medifference use was made of molybdenum alloy in the design in orb to for the deflections Experimental error estimations are also described minimize thermal gradients which cause detrimental seal deformation: Author in particular the seat. carbon retainer ring. carbon carrier and secondary seal were made from the molybdenum alloy. The seat was structurally isolated from the shaft by a radial spacer in order to mitigate the deformation effects caused by shaft thermal N71-11968# Texas Univ.. Austin. Engineering Mechanics displacement. Further. the seat was clamped through a bellows Research Lab. which provided a predetermined amount of axial clamping and STRESS AND DEFLECTIONS IN TYPE 2 AND TYPE 4 mitigated clarnp;na ?is?c?izns. Sea: aria; hirinai gradients which AIRDROP PLATFORMS Final Report induce undesirable deformations were minimized by thermal Wen Shing Chang and E A. Ripperger Natick. Mass. Army. shielding and oil cooling. Further oil cooling the nosepiece assembly Airdrop Eng. Lab. Dec. 1969 95 p refs helped reduce the carbon temperature to a level at which oxidation (Contract DAAGl7-67-C-0189) was not a problem. Author (AD-71 1556: TR-70-56-AD) Avail NTlS CSCL 15/7 Severe stress conditions may develop during the extraction and parachute deployment phases of an airdrop with a stressed platform The platform stresses and deflections during that dynamic loading period are computed by treating the platform as a planar network of beams rigidly connected at the joints. Stiffness N71-12037*# National Aeronautics and Space Administration properties of the beams in the network are calculated approximately Lewis Research Center, Cleveland Ohio using standard methods and then refined to more exact values by OIL-FILM SEAL, TYPE B. APPENDIX B comparing measured deflections under static loading to computed L P Ludwig In Pratt and Whitney Aircraft Develop of Mainshaft deflections. These stiffness properties are then used in the analysis Seals for Advan Air Breathinq Propulsion Systems, Phase 2 23 of the dynamic load. Equations of motion are written for each Jun 1970 p 77-8G degree of freedom using a lumped mass representation for the Avail NTlS CSCL 11A loads. Deflections at the joints of the network are obtained by The design goal was to minimize (1) thermal gradients. solving the equations of motion using the Runge-Kurt-Gill numerical (2) nosepiece (and carrier) mass and (3) distortion at the seal dam procedure. Stresses are then determined from the deflections. To obtain this goal. thermal distortion studies were made of all the Author (TAB) seal parts and materials selection was based on di3tortion consideration a6 #ell as strength The seal was designed to fit existing mainshaft seal rigs and consist of a resiliently clamped seat which is thermally isolated by three heat shields Cooling holes are located near the hot gas side and effects of shaft expansion are N71-12035*# Pratt and Whitney Aircraft. East Hartford. Conn minimized by piloting the seal under the seat centroid Seal cooling DEVELOPMENT OF MAINSHAFT SEALS FOR ADVANCED oil is directed to the seal interface from which it is expelled by AIR BREATHING PROPULSION SYSTEMS, PHASE 2 Final centrifugal force and by the pumping action of the spiral grooves Report This spiral qroove and centrifugal force pumping action is sufficient V P Povinelli and A H McKibbin 23 Jun 1970 122 p refs to preclude a static oil pressure increase at the orifice exit (Contract NAS3-7609) Lubrication film thickness over the spiral groove land areas (NASA-CR-72737. PWA-3933) Avail NTlS CSCL 21 E determines the film thickness at the gas sealing dam Author

57 N7 1- 12038

N71-12038*# National Aeronautics and Space Administration N71-12069# Centre National d'Etudes Spatiales. Paris (France) Lewis Research Center, Cleveland Ohio Div 'Politique Industrielle ANALYSIS OF SELF-ACTING GEOMETRY (RAYLEIGH STEP INDUSTRIAL POLICY AT THE CENTRE NATIONAL LIFT PAD) FOR GAS FILM SEAL. APPENDIX C D'ETUDES SPATIALES [IA POLlTlQUE INDUSTRIELLE J Zuk In Pratt and Whitney Aircraft Develop of Mainshah Seals DU CENTRE NATIONAL D'ETUDES SPATIALES] tor Advan Air Breathing Propulsion Systems Phase 2 23 Jun A Simon 1970 12 p In FRENCH Presented at the Space 1970 p 81-95 refs Symp , Rennes. France. 16- 19 Jun 1970, sponsored jointly by Avail NTlS CSCL 1 1A CNES. Centre de Perfectionnement Tech, and Fac des Sci de A parametric study was made on a face seal with a self acting Rennes lift geometry The analysis yielded the following results (1) the Avail NTlS characteristic steep gradient of lift force against gap height of the The Centre National a Etuaes Spariaie (CNiSi ildb d&piCd self-acting geometry was responsible for maintainmg the small the policy of allowing the French aerospace industry to participate in sealing gap height necessary for low leakage Thus the self acting its space program This paper discusses this policy the conditions gen-e?ry prn\m+=s a high Gas film stiffness which is necessary if and operations both in the past and in the future ESRO the nosepiece is to track dynamically the face runout of the seal seat, (2) the gradtent of self acting lift force against film thickness was affected by the recess pad depth the shallower recesses produced a steeper gradient (3) for faces with angular deformation the self acting lift force was less than that for parallel faces N71-12075# Army Foreign Science and Technology Center Calculations for practical values of angular deformation indicated Washington D C that the self acting geometry produces a useful load and (4) the EFFECT OF ELECTRIC AND MAGNETIC CROSS FIELDS ON self acting pad geometry selected was a cornpromise between THE AERODYNAMICS AND THERMA'. REGIME OF A GAS wear and load capacity considerations that is the recess depth FLAME CONE selected was deeper than the optimum and the recess length to land L P Yarin 16 Jun 1970 14 p refs Trans1 into ENGLISH length ratio was smaller than the optimum Author from Teoriya i Prakt Szhiganiya Gaza, Tr Nauchn Tekhn Soveshch (Moscow),~13 1967 p 12fL135 (AD-712336 FSTC-HT-23-086-70) Avail NTlS CSCL 20/13 In the boundary layer there IS a narrow, high temperature zone (a region of active reaction of the original components) within N71-12039*# National Aeronautics and Space Administration which the gas is a conductor Outside this region the conductivity Lewis Research Center Cleveland Ohio 01 fuel oxidizer and the products of combustion in the entire flux SEALING DAM DESIGN ANALYSIS, APPENDIX D field IS believed equal to zero In this connection the calculations J Zuk In Pratt and Whitney Aircraft Develop of Mainshaft Seals for the field of flux outside the effective zcne can be made by the for Advan Air Breathing Propulsion Systems Phase 2 23 Jun usual gas dynamic methods and the unknown values of temperature 1970 p 97 110 refs and velocity at the borders of the zone defined are found from the Avail NTlS CSCL 11A supplementary conditions taking into account the electrical and The results that are found were obtained by using computer magnetic influence The balance of forces and heat equations are programs The design of the gas film seal required finding the used as supplemental conditions Author (TAB) smallest film thickness so the leakage is a minimum but yet a large enough film thickness such that both the power dissipation and subsequent shear heating is tolerable and potential seal face deformations can be accommodated A rough calculation showed that the gap must be at least 0 1 rnil for parallel surfaces A larger N71-12119# Civil Aeronautics Board Washington D C gap than a 0 1 rnil is necessary to accommodate deformation of STUDY GROUP ON LEGAL ASPECTS OF INTERMODAL the sealing faces The effect of the sealing dam radial width TRANSPORTATION (deltaR) on force balance suggested that radial widths of 20 rnil Whitney Gillilland 1970 B p refs Conf held at Washington 50 rnil 80 rnil and 100 rnil be investigated in detail Leakage flow D C 5 May 1970 Sponsored by NAS NRC rates of less than 25 SCFM were desired for all three design Avail Issuing Activity points Author The interactions between air and surface modes in transporting freight are briefly described with respect to statute custom and legal decisions The regulations for pickup and delivery areas within N71-12069# Office National d'Etudes et de Recherches a 25 mile zone, within a 68 mile zone and beyond are mentioned Aerospatiales Paris (France) along those regarding a surface carriers acquisition of an air carrier CALORIMETRIC HEAT FLUX MEASUREMENTS IN and vice versa It is felt that there are many capabilities to WIND-TUNNELS [METHODE CALORIMETRIQUE DE facilitate intermodal domestic transportation and that international MESURE DES FLUX DE CHALEUR EN SOUFFLERIE] agreements will eliminate impediments to international coordination Jean-Pierre Chevallier Jean Ponteziere and Andre Betremieux NEN 1970 27 p refs In FRENCH ENGLISH summary (ONERA NT-159) Avail NTlS The study of kinetic heating of bodies with complicated shapes entails more and more accurate measurements The testing N71-12120# Civil Aeronautics Board Washington D C methods have to be adapted to the specific heating conditions of REMARKS BY THE HONORABLE WHITNEV GILLILLAND. the models and to the facility used With the method developed VICE CHAIRMAN, CIVIL AERONAUTICS BOARD for blowdown wind tunnels it is possible to measure even very 1969 9 p Presented at Am Airlines Ann Meeting of Regional weak convection fluxes with a remarkable accuracy thanks to a Vice Presidents and City Managers Washington D C, 13 Nov refinement of the technique for inserting the thermocouples within 1969 the model skin and to a critical study of the calorimeter design Avail Issuing Activity and conditions of use The technological details and the theoretical The possible benefits of local and trunk air carrier mergers study described must be considered as a whole in the use of the are briefly discussed It is pointed out that the local carriers have process and for ascertaining the accuracy of the results This method had a higher rate of capacity growth over the past 15 years than might easily be extended to very different- measuring conditions the domestic trunks and that the total 1968 transport revenues of such as those met in flight tests Author (ESRO) the local service carriers was nearly $43 .million more than that

58 N7 1-121 90 of the domestic trunks in 1948 A comparison is made between an actual trunk-trunk merger and a hypothetical merger between average local and trunk carriers with respect to passenger miles. revenue, profit. and investment It is concluded that if some trunk-local carrier mergers take place. the air carrier system and its members might be financially stronger and the public might be better served and at lower fares NEN

N71-12139# Aeronautical Research lnst of Sweden Stockholm Structures Dept FFA STRUCTURAL RESEARCH AND TEST FACILITIES 1970 63 p (FAA-61) Avail NTlS The Aeronautical Research Institute of Sweden - Flygtekniska Forsoksanstalten IFFAI is discussed The primary activity of the FFA consists of contract work for the Swedish Air Force and the aircraft industry as well as indoor research programmes The FAA has wind tunnels for the static and dynamic testing of various types of aeronautical models covering the entire range from low subsonic to hypersonic speeds A special theoretical group deals with aircraft and missile simulation In the FFA structural test facilities full scale structures sub-assemblies component and materials are tested under ststic or dynamic loads at various temperatures Author

N71-12190# Civil Aeronautics Board Washington D C SUBSIDY FOR UNITED STATES CERTIFICATED AIR CARRIERS ivov 1Y69 24 p Avail Issuing Authority The subsidies for American certificated air carries are identified in dollar amounts achievements and standards The total subsidy for air carrier services for fiscal 1970 is 940,917,000 Summaries by service carrier groups are presented and include Alaskan, Hawaiian helicopter, local. and domestic trunklines The procedures for the determination of the subsidy are given Tabulated summaries for all certificated carriers for fiscal years 1954 to 1970 are ,-c'udel FOS

59 SUBJECT INDEX - AERONAUTICAL ENGINEERING / A Special Bibliography (Suppl. 2) FEBRUARY 197 1

Typical Subject Index Listing

SUWECT HEADING Poruard horizontal speed influence on aerodynamic ACCIDtlT PREVtlTIO1 characteristics of air cnshion vehicle uith omputer oroqrams and predictor displats for circular nozzles and cylindrically or conically s-lviqa air traffic control problems shaped curtains C WASA-C?-111372 1 I 171 - 11 86 6, A71-12551 Lou-speed uind tonne1 tests of series of tnin-keel all-flexible paranings [ NASA-TU-D-59361 171-10052 NUMBER Computerized aerodynamic optimization of aircraft CONTENT NUMBER propellers [AD-7103563 171-10122 Leading edge effect on aerodynamic characteristics The subject heading is a key to the subject mntent of the document The of 70 deg snept delta wing Notation of Content (NOC) rather than the title of the document. (5 used I AD-7120871 ~71-11007 to provide a more exact description of the subject matter The report number cola air tests on axial flow turbine nith helps to rndrcate the tvpe of document cited leg NASA report translation transpiration cooled discrete hole stator blades NASA contractor report] The accession number IS located beneath and to deternine coolant flow ejection effect on to the right of the Notation of Content e g N71-11466 Under any one turbine aerodynamic performance subiect heading. the accession numbers are arranged In sequence with [ WASA-TN-I- 21 2 31 n7i-iioio the IAA accession numbers appearmg first Lou speed aerodynamic characteristics of airfoil profiles inclndinq effects of upper surface roughness simulatinq hoar frost [ WPL-AERO-1308] 1171-11016 A Subsonic nind tunnel investigation of rotary wing ACCELBBOEBTBRS confignratiaos for ViDi aircraft in cruise mode ?Tee fliiiht measurements of aerodynamic lateral r NASA-TU-D-59451 171-1 1025 force and moment coefficients usinq gyroscopes AERODTlABIC COBFPICIEIITS and accelerometers Aonaffine similarity laws and transformations [ESA-TN-l64] mi- 11001 subject to limitations of nentonian impact ACCIDEBT IUVESTIGATIOI theory for two dimensional bodies. obtaininq Systems approach to accident investigation in aerodynamic coefficients civil aviation and homes A71-10948 n7i-ioii5 Spheres draq coefficient at hypersonic nach ACCIDElT PREVEIITIOI numbers for near free molecular flow Computer proqrams and predictor displays for 871-10969 solving air traffic control problems Critique of Chapman-Kirk iterative nethod for [ NASA-CR- 111372 1 87?-1 ’! 466 Sifferential equations yielding aerodynamic lCOUSTIC BEASUBBEEATS coefficients from free fliqht data Air and land transportation noise sources and A71-10971 measurement. noise level scales, and individual Thin delta ninq nith leading edge separation, and community responses - conference obtaining draq lift and rollinq moment [PB-191117] A71-10399 coefficients and pressure distribution ACOUSTIC VELOCITT A71-12408 Penetration of sonic boom enerav_. into ocean in AERODTBABIC COUPIGWBATIOIS experimental simulation Optimization techniques in aircraft confiauration TAD-7119631 ~7i-ioo94 desiqn ACTUATORS [ AD-7114101 W71-11023 Aircraft flaps and ailerons actuators electronic Development and characteristics of translatiuq fly by nire control as alternative to mechanical horizontal tail assembly for supersonic aircraft linkaqes for maneuverability and reliability in IWASA-CASE-XLA-08801-11 W71-11043 fliqht AERODYIABIC DRAG A71-10825 Supersonic and transonic flow includinq effects of Eathematical model and digital sinulation for pressnre oscillations within cavity, predictinq nonlinear characteristics of prototype rectangular cavities draq from mathematical integrated actuator packaqe for fiqhter aircraft node1 control A71-10931 A71-11783 Spannise aistribution of induced draq in subsonic ADDITIVES flow by vortex lattice method, notinq Static dissipator additives in aviation fuels for applicability to rotary derivatives in stability eliminatinq electrostatic charqinq hazards analysis 1171-12300 A71-12691 ADIABATIC PLOW Wozzle lateral spacing effect on draq and Computerized calculations of adiabatic laminar performance of tnin jet afterbody confiqurations boundary layer and shock nave interactions usinq nith convergent nozzles at Nach 0.6 to 2.2 Klineberq method r NASA-TR-X-20991 W71-10276 r VKI-TR-60 1 A71-110 17 AEBODTAAnIC FORCES AERIAL PEOTOGBAPEY Wind tunnel apparatus for reproducinq coninq and nicronave radiometry for snow and ice sensinq in spinning motions of bodies of revolution, usinq aerial reconnaisshnce six-component strain gage balance for W71-11160 aerodynanic forces AERODYBAEIC CEABACTBRISTICS A71- 10930 Statics and aerodynamics of liftinq decelerators PORTRAWproqram for calculatinq aerodynamic forces haraninqs and sailwinqs/ at supersonic and from pressare or velocity distributions on blade hypersonic speeds sections [AIAA PAPER 68-9453 A71-10927 IWASA-T8-X-2123 1 w7i-10967

A- 1 AERODYNAMIC LOADS SUBJECT INDEX

Flutter analysis for thin liftinq surfaces by Aiqh strength polyimide resin composites, application of supersonic kernel function discussing commerical and aerospace procedure applications, chemistry, void content, volatiles [ NASA-TN-D-60121 871-10866 and moisture absorption Free flight measurements of aerodynamic lateral 871-12487 force and moment coefficients usinq gyroscopes AEROSPACE INDUSTRY and accelerometers Aeronautical projects development and olanning in IASA-TN-164 1 N71-11001 European Economic Community, discussinq AERODYNAMIC LOADS aerospace industry orqanizational problems and LARS fliqht demonstration, discussinq role io economy insilueentaiion, flatter hotlndary and dynamic A71-11676 response, aerodynamic testinq and structural Planufacturing technoioqy and podcction response to turbulence engineering methods in aerospace industry A71-11662 N71- 11627 Low noise turbofan enqine without aerodynamic Plodern weldiuq methods in aircraft and aerospace blade loadinq industrv .---I..-=* r NASA-TN-D-60801 171-1 1882 n I I- I I"_)" AERODYNAMIC NOISE Policies for participation of French aerospace Turbulent jet noise estimation takinq into account industry in space.proqrams retarded time effect on acoustic radiation N71-12069 A71-11468 AENOTBERMODINAMICS Small perturbation subsonic flows aerodynamic Electric and maqnetic cross field effects on noise, usinq matched asymptotic expansions aerodynamics and thermal regime of gas flame method cone A71-12377 [AD-7123361 N71- 12075 AERODYNAMIC STABILITY APTERBODIES systems analysis application to stability of Nozzle lateral spacinq effect on drag and aerodynamic cross couplinq in fliqht vehicle performance of twin jet afterbody configurations motions with steady sideslip, using feedback and with convergent nozzles at Each 0.6 to 2.2 root locus techniques [NASA-TE-X-2099] N71-10276 A71-12687 AILERONS Aerodynamic data recordinq for determininq Critical flutter of winq with rigid aileron lonqitudinal static stability of US-2A aircraft studied by analoq computer modelinq [ AD-710722 J N71-10563 A71-10606 AERODYNAEIC STALLING Aircraft flaps and ailerons actuators electronic Delayed bubble movement on airfoil durinq fly by wire control as alternative to mechanical helicopter stall linkaqes for maneuverability and reliability in AD-71 1540 7 N71- 11005 f liqht AERODYNAEICS A71-10825 Unsteady flow theory, describinq milestone AIR CARGO experiments in aerodynamics Analysis of stresses and deflections in platforms 1171-10266 used for airdrop operations Low altitude slow aerodynamics, discussinq earth [ AD-7115561 N71-11968 surface wind modelinq, powered-lift fliqht AIR MAIL efficiency and animal fliqht Air mail transportation by contract operations 171-10818 N71-10816 Aerodynamic theory of pressure field induced on AIR NAVIGATION liftinq surface by isotropic atmospheric Nan role in future naviqation from SAC viewpoint, turbulence, considerinq transfer function of considerinq relationships to mission and machine Concorde aircraft A71-10502 rICA5 PAPER 70-301 A71-11019 Naviqator role in nilitary Airlift Command /PlAC/ German book on Goettinqen Aerodynamic Research as naviqator, weather analyst, fuel manaqer and Institute /1945-1969/ fliqht planner A71-11406 A71-10504 Spacecraft reentry aerodynamics reqardiuq Airborne inertial and area navigation systems hypersonic hiqh altitude liftinq bodies, shock performance requirements proposed for Q.S. wave and flow field, heat, mass and enerqy domestic airspace, includinq projection throuqh transfer, etc 1995 I ICAS PAPER 70-01 1 871-11686 A71-10508 Pleasureaents of hypersonic, rarefied flow field of Time-synchronized approach control combininq disk aircraft precision naviqation and quidance with r AD-710641 ] N71-10461 ATC equipment AERONAUTICAL ENGINEERING A71 -1289U Aeronautical projects development and planninq in AIR PIRACY European Economic Community, discussinq Airline liability and insurance in relation to aerospace industry orqanizational problems and aircraft hijackinq, sabotaqe, etc role in economy A71-10359 A71-11676 AIR POLLUTION Advanced technoloqy for production of aerospace Gas turbines air pollution control, discussinq enqines - conference exhaust composition, combustion chamber desiqn, r AGARD-CP-64 1 871-11626 enqine efficiency, etc Foundarv Precision in domain of aeronautical 1171-10820 turbines AIR TRAFFIC N71-11638 Air traffic pattern prediction for 1980 peak Introduction of electrochenical aachininq in summer periods in London, Enqland terminal area aeronautical industry N71-10163 N71-11647 AIR TRAFFIC CONTROL AERONAUTICS Traffic radar qenerated weather contours for air Papers on aeronautics coverinq propulsion, power traffic controller in helpinq aircraft avoid qeneration, computer utilization, man machine thunderstorms interaction, pilot traininq, hovercraft, A71 -10587 avionics, etc Air traffic control by satellite, discussinq 171-12609 CNES-SGAC and ESRO experiments within Dioscures AEROSPACE ENGINEERING project test proqram Aerospace enqine startinq systems military and 1171-10748 industry specifications and standards, ATC communication environment simulation Via considerinq cartridqe pneumatic, electric, qas mathematical model based on ATC statistics turbine, hydraulic and mechanical types A71- 10979 A71-10103

A-2 SUBJECT IBDEX AIRCRAFT COIPARTIEATS

ATC automation. usinq conflict prediction Air mode service analysis in northeast Corridor alqorithm based on airspace assignment to [ PB-1909353 n7i-11029 aircraft enterinq system Legal aspects of air and surface carrier 1171-11698 interactions in freiaht transportation ATC system improvement by procedural chanqes. n7i-12119 applyino probability concepts to fliqht safety Possible benefits of local and trunk air carrier 171-11699 merqers Helicopter operations integration into civil air mi-12120 traffic system, notins special reqnirements for AIBBORBE EQUIPBBBT mixed fixed and rotary winq terminal Aircraft electric system control by solid state environments switchinq. discussiuq reliability. service life, 171-12892 versatility and compatibility naximum throuqhput-rate capacity for runvay and A71-11627 final approach path airspace involving multiple Reverse flow temperature probe desiqn and Ifr landings calibration for vertical soundinos from A71-12893 aircraft, comparing to radiosonde method Time-synchronized approach control combininq A71-11822 aircraft precision naviqation and quidance with Performance characteristics of Bendir type DRA-12 aTC equipment airborne Doppler radar system 1171-12894 [ FAA-RA-70-501 A71-10394 Xxperimental desiqn of three dimensional air AIRBORIE/SPACEBORIE COIPUTERS traffic control radar trackina system Fliqht control software package for diqital fliaht 11-11-10164 control and landinq system of CB-U6C helicopter national Aviation Facilities Experimental Center r NASA-CR-110905 1 A71-10283 history and proqrams Gnidance software packaqe for dioital fliaht 1171-10356 control and landinq system of CB-46C helicopter Evaluation of systems, procedures. and rRASA-CR-111025] n7i-10284 instrumentation for air traffic control AIRCRAFT ACCIDEWT IBVESTIGATIOI r AD-7116621 n7i-10737 Aircraft crash investiqation. deducir?q in-fliuht Computer proqrams and predictor displays for explosion by failure analysis techniques solving air traffic control problems All-10456 f NASA-CR-1113721 n7 1-1 i 466 Aircraft incident report and investiqation of air Project Dioscures for qlobal sea and air traffic France Boeinq 747. St. Jean, Canada, Auqust 17. control usinq synchronous satellites for 1970 sround-air-qround communications r ATSB-AAR-70-261 Vi-10531 n7i-11768 Summary and statistical analysis of aircraft AIR TRAASPORTATIOA accidents Economic contributions of U.S. domestic airline rFTSB-AAS-70-11 1171 - 10674 industrr in 1970- reqarginq air. tranzgzrtatiJn Ser aircrart crash durinq instrument approach due constraints and impact on short haul to electrical systems failure TAIAA PAPER 70-1309 J A71-10486 [RTSB-AAR-70-22] n7i-10812 noise reduction relationship to air transportation Lear jet crash during instrument approach due to proqress, considering cost/technoloqy balance, descent belov path profile quiet enqine, research and development proqrams. [ !PSB-AAR-70-21J 1171 -108 13 etc Douqlas DC 9 aircraft crash dnrinq takeoff caused A7 1-1 08 19 by ice formation on airfoils Short haul air transportation in U.S.. interagency [RTSB-AAR-70-20J n7i-10815 cooperation and federal involvement Aircraft accident investiqation 3f united Air IAIAA PAPER 70-1286 J A71-1087s Lines, Boeinq 727-22C near Los AnqeleS, 18 Jan. Airport system planning from environmental 1969 .lieYP^i~t, ZisiGssinq travei market, airport ~PB-I~OB~~] mi-10914 accessibility, airspace utilization ana control statistical tabulation of United States civil and land use aircraft accident histories for 1969 A71-11642 [PB-1907921 n7i-10932 Short haul air transportation technoloqical statistical tabulation of United states civil factors fcr VTOL, STOL, CTOL and liqht aircraft. aircraft accident histories in 1968 considering operatinq costs, passenqer service [ PB- 1908111 1171-10933 and environment impact Aircraft accident investiqation includinq types of [AIAA PAPER 70-12871 A71 -1 1700 aircraft, pilot certificates, and accidents Air transportation reliability through turbojet [ ASTB-BA-70-4J n71- 11024 enqine performance monitorinq AIRCRAFT ACCIDBBTS 1171-12368 Aircraft emergency evacuation illumination COnCOrde role in air traffic market. discussing stanaards, considering independent power source, operatins costs and profit potential crash survivable installation, operation A71-12746 initiation and exit visibility Systems maintenance proqram evaluation of Eastern 1171-100 30 Region air transportation facilities ATA Collision Avoidance System based on time and A71-10114 frequency synchronization ria qronnd stations or Traveler service problems in domestic intercity other aircraft air, bns. and rail transportation A71-12895 [ PB-193300 J 871-10116 AIRCBAPT APPBOACE SPACIWG Demonstration plan for western Reqion short Eaul naximum throushput-rate capacity for runway and air Transportation Program final approach path airspace involvinq multiple [ ATR-71-/7190/-1-VOL-11 n7i-fot79 IPR landings Technical studies for western Region Short Haul A71-12893 Air Transportation Program IIRCRAFT BBAKES r ~~~-7i-/7190/-1-voL-2 1 A71-10280 Influence of qravel depth and tire inflation Aiqh speed access system evaluation for pressure on soft-qround arrestinq of civil transportation from jetport to niami with cost aircraft estimates and netrork descriptions [ RAE-TR-690011 n7i-iiouo [ PB-192842 J mi-10417 AIRCRAFT CARRIERS Status of federal involvement in short haul air Aircraft flying qualities research program. transportation discussinq navy test pilot evaluations and 1171- 11026 longitudinal handliuq characteristics for Various vertical takeoff and landing and short simulated carrier landinq task takeoff modal configurations for air [IIAA PAPER 69-8971 A71-12678 transportation AIRCRAFT CORPARTIllTS [PB-1909401 171-1 1027 Aircraft compartment qlare minimization for fliqht crew visibility conditions and visual

A-3 AIRCRAFT CONTROL SUBJECT INDEX

performance improvement compressors and turbine inlet temperature A71-10028 A71-11181 Aircraft qalley desiqn safety criteria, Electrochemical machininq for aircraft enqine considerinq injuries from routine use, normal, metal components, discussing cost, tine crash or ditchinq conditions component comparisons, toolinq techniques and applications dislodqment, equipment malfunctions and defects r SHE PAPER YR-70-2061 A71- 11252 A71-10029 Electrochemical machining role in jet enqine AIRCRAFT CONTROL industry, discussinq drilling, contourinq, Aircraft direct lift control based on fliqht and electrolyte handling, etc simulator experiments, discussinq effect on rsnE PAPER NR-70-1931 A71-11253 desiqn Electrohydraulic thrust control system for A71-10754 supersonic transport aircraft enqines, Aircraft flaps and ailerons actuators electronic considerinq reliability, performance and weiqht fly by wire control as alternative to mechanical TSAE PAPER 7008193 All-1 1546 linkaqes for maneuverability and reliability in Soviet book on aircraft power plant systems and fliqht :e;icz=s rz~erin,: lzyont; ~naineattachment, A71-10825 propellers, control, fuel and oil systems, fire Nathematical model and diqital simulation for fiqhtinq, monitorinq, etc nonlinear characteristics of prototype A71-12722 inteqrated actuator packaqe for fiqhter aircraft Enqine vibration high temperature transducer, control discussinq piezoelectric materials properties A71-11783 and desiqn considerations relative to Aircraft manual fliqht control analysis usinq temperature, pressure, acoustic noise, humidity continuous mathematical pilot model for closed environment loop diqital simulation A71- 12911 A71-11787 Aircraft qas turbine enqine desion and Aerodynamic data recording for determininq construction lonqitudinal static stability of US-2A aircraft [AD-7117571 N71-10853 TAD-7107221 N71-10563 x ray fluorescence analysis for quality control of Development and characteristics of control system qas turbine aircraft enqine parts durinq for flexible winqs manufacture and overhaul INASA-CASE-XLA-069581 N71-11038 N71-11641 AIRCRAFT DESIGN Influence of Concorde powerplant operating Aladin 2 interurban Stol transport desiqn with conditions on design of olympus 593 fuel and oil blown winqs and jet deflection by winq flaps, system emphasizinq enqine noise reduction N71- 11653 A71-10749 AIRCRAFT EQUIPMENT Small qas turbines for aircraft auxiliary power Aircraft galley desiqn safety criteria, unit, considering compressor and combustor considerinq injuries from routine use. normal, desiqn', noise, fuel consumption and specific crash or ditchinq conditions component weiqht problems dislodqment, equipment malfunctions and defects A71-10751 1171-10029 Aircraft response to atmospheric qust, discussinq Combat aircraft cockpit temperature control system spectral analysis procedures and calculation desiqn and operation results on T-tail aircraft desiqn A71-10270 A71-10752 AIRCRAFT FUEL SISTERS Aircraft direct lift control based on fliqht and Soviet book on aircraft power plant systems and simulator experiments, discussinq effect on devices coverinq layout, enqine attachment, desiqn propellers, control, fuel and oil systems, fire A71-10754 fiqhtinq, monitoring, etc F-14A twin enqine variable qeometry carrier based A71-12722 jet fiqhter aircraft, discussing desiqn, Influence of Concorde powerplant operating development proqram and manufacturinq techniques conditions on desiqn of olympus 593 fuel and oil A71-12050 system Subsonic aircraft size effect in conventional N71-11653 desiqn, discussinq increased weiqht increments AIRCRAFT FUELS and economic gain rate Soviet book on aviation fuels, lubrication TAIAA PAPER 70-9401 A71-12676 materials and special fluids coverinq Swept winq fiqhter aircraft transonic buffet onset compositions, physicochemical properties, lift coefficient from camber and trailinq edqe filtration, etc deflection, considerinq desiqn variations 1171- 11320 A71- 12679 Static dissipator additives in aviation fuels for Fliqht control systems influence on military eliminating electrostatic charqing hazards aircraft desiqn and performance, discussinq A71-12300 static stability. ride quality, flutter marqin AIRCRAFT GUIDANCE and maneuver load controls Time-synchronized approach control combining I AIAA PAPER 69-7671 A71-12683 aircraft precision naviqation and quidance with Piqhter aircraft desiqn with consideration to ATC equipment armament, detection capability, thrust, speed, A71-12894 and load factor performance tradeoffs Guidance software packaqe for diqital fliqht I AD-7 10497 1 N71-10183 control and landinq system of CH-46C helicopter Conqressional hearinq on investiqation of contract r NASA-CR-111025 J N71-10284 for TFX aircraft Systems analysis of flight control and quidance of N71-11034 CA-46C helicopter Visual approach slope indicator system for [NASA-CR-111024] N71-10297 low-bodied aircraft Visual aids for secondary airports I FAA-RD-70-761 N71-11905 IFAA-NA-70-511 171- 11474 AIRCRAFT ENGINES LIBCRAFT MAZARDS Air cooled opposed 4, 6 and 8 cylinder liqht Aircraft fire hazard reduction, discussinq early aircraft enqines with or without detection, extinquishinq equipment and emerqency turbosupercharqinq, considerinq horsepower landinq survival improvement and torsional vibration control A71-10399 lSAE PAPER 7002051 R71-10129 static dissipator additives in aviation fuels for Aircraft turbine enqine development, considerinq eliminating electrostatic charqinq hazards mismatch reduction between enqine and airframe 1171-12300 in fliqht tests Severe thunderstorm radar trackinq and related A71-11180 weather events hazardous to aviation operations Jet enqine evolution, considerinq thrust, [ ESSA-TN-ERLTN-NSSL-46 1 N71-10720 combustion chamber, fans, hiqh-pressure-ratio

A-4 SUBJECT IBDEI AIRCRAFT STRUCTURES

AIRCRAFT IBDUSTR'I Community physical. psychological, and social modern welding methods in aircraft and aerospace reactions to aircraft noise around 7 US indnstry international airports 1171-1 1650 r 11ASA-CR-111316] 1171- 11032 AIRCRAFT IBSXRUIBBTS Low noise turbofan engine vithout aerodynamic Electronic control indicator for human pilot blade loading capability enhancement using color coded cathode C 11ASA-TIT-D-60801 1171-11882 ray displav, presentins information from seven AIRCRAFT PARTS

different instruments ~ Saall gas turbines for aircraft auxiliary power A71-10750 unit, considering compressor and combustor American ATA prototype aircraft collision design. noise, fuel consumption and specific avoidance equipment and proposed noncooperative weight problems system A71 -1 0751 A71-10753 Peen forming of large complex parts from sheet and Aircraft ultrasonic altitude and vertical velocity plate. illustratinq dihedral break in airplane sensor for low flight. discussing VTOL aircraft winq skin automatic hovering control and time laq A71-11550 A71-11624 Soviet book on bolting and coupling elements E-52 LABS test vehicle structural modification and threads used in aircraft industry coverinq instrumentation in fliqht phase configurations selection, cutting, tolerance A71-11661 requirements and quality control naintenance prosrams, evaluation. acceptance, and 1171-12723 monitoring procedures for transport aircraft AIRCRAFT PERFORBAlCE 1171- 11020 Inertial navigation system augmented by digital AIRCRAFT LAlDIB6 distance seasurinq equipment in FAA flight Steep approach to landinu for iet transmrt inspection aircraft for performance evaluation aircraft noise abatement, using qround based A71- 10507 equipment and onboard TV display SST proqram relation to airline operations, 171-11311 comparinq production configuration. performance, Aircraft all weather automatic landing svsten. economics and operation with snbsonics discnssinq component weishts and reliability rAIAA PAPER 70-12171 171-1 1248 connected with probles area Fliqht control systems influence on military A71-12274 aircraft desiqn and performance. discussing All-weather automatic landing electronic static stability, ride quality, flutter margin technology, describing fliqht automation landing and maneuver load controls system for VC 10 BAC 111 and Concorde aircraft rAIAA PAPER 69-7671 1171-12683 A71-12275 Fighter aircraft desiun with consideration to Baximnm throuqhput-rate capacity for runway and armament, detection capability, thrust. speed, final approach path airspace involvinq nnltiple and load factor performance tradeoffs IPR landinqs [ AD-7104971 171-10183 A71-12893 AIRCRAFT PRODUCTIO. AIRCRAFT HAIBTEIAICE F-141 twin enqine variable qeosetry carrier based German monograph on commercial jet aircraft jet fighter aircraft, discussing design. maintenance svstems coverinq chanqes and development program and manufacturing techniques adaptations for performance improvement 171-12050 871- 10114 AIRCBAPT RELIABILITI Commercial transport aircraft naintenance Airline experience with dual inertial systems as simulation Monte Carlo Rodelinq techniqnes. sole means of navigation, considering equioment considering application to airline operations reliability. r~ctnitdesign, rraininq, etc I SAE PAPER 700345 J 477 - 1C128 A71-10509 DiQital sinnlation program in GPSS languaqe for AIRCRAFT SAFETI airline operations including aircraft American ATA prototype aircraft collision maintenance, flight scheduling, terminal space, avoidance equipment and proposed noncooperative equipment, vork forces utilization, etc system A71-11809 A71-10753 Nondestructive testins techniques for airline Feasibility of using flexible rotor blades for maintenance inspection, describing ultrasonic, ejection systems eddy current, maqnetic particles, and X ray AD-7 116423 N71-11022 methods AIRCRAFT STABILITY A71-12449 Rapid hybrid frequency response method for Armv aircraft modification proqram management aircraft flight flutter testinq based on hybrid review and recommendations computinq system 1171-10287 1171-10228 naintenance proqrams, evaluation, acceptance, and LARS fliqht control systems for qust load monitoring procedures for transport aircraft alleviation and structural mode stabilization on 1171-11020 large flexible aircraft, usinq aerodynamic AIRCRAFT BOISE surf aces Auman subjective responses to approachinq and A71-11659 receding aircraft sounds aurins flight over C-5 military transport stability auqmentation for stationary observer pitch and yaw inertia at low speed, usinq pilot 1171-10345 evaluation on cockpit simulator Noise reduction relationship to air transportation 811-12681) Proqress, considerinq cost/technoloqy balance, AIRCRAFT STRUCTURBS quiet engine. research and development prosrams. Aircraft structure fatisue life iaprovement via etc material stress coining inside and around holes 871-10819 and slots Research and developments in aircraft noise A71-10170 reduction Aircraft structures fatique testing device usinq 171-10171 programmed control of electrical inputs to Air and land transportation noise sources and electrodynamic vibration stand, notinq load measurement, noise level scales, and individual cycle effects and damaqe accumulation and community responses - conference A71-10409 r PB-191117 1 lt71-10349 Aiqh velocity metal working, discussing airfoil Response of, and acoustic radiation from panels forqinq, ausforginq of bearinq race blanks, excited by turbulent boundary layers toolinq, etc (AD-7106961 171-10386 rsaz PAPER BP-70-2281 All-11267 Airspeed contribution to noise level vithin fixed Composite materials structure cost effectiveness and rotary wing aircraft demonstrated in airnaft relief crew compartment I AD-71 1359 J 171-10705 panels

A-5 AIRCRAFT TIRES SUBJECT INDEX

1171-11281 AIRLINE OPERATIONS Papers on LAES technology for aircraft structural Airline liability and insurance in relation to mode control coverinq 6-52 and C-5A aircraft aircraft hijacking, sabotaqe, etc A71-11658 A71-10359 LAYS fliqht control systems for qust load Economic contributions of O.S. domestic airline alleviation and structural mode stabilization on industry in 1970s regarding air transportation larqe flexible aircraft, usinq aerodynamic constraints and impact on short haul surfaces r AIAA PAPER 70-13091 1171-10486 A71-11659 Airborne inertial and area naviqation systems 6-52 LAMS test vriiicle strncturzl modification and performance requirements proposed for U.S. instrumentation in fliqht phase domestic: airspace, i~cluainqprojection throuqh A71-11661 1995 Sandvich structures applications in aircraft and A71-10508 space vehicles, discussinq component Airline experience with dual inertial systems as characteristics, manufactuLinq pi~cezcccsr?3 sole means of naviqation, considerinq equipment mechanical testinq procedures reliability, cockpit cioalqn, trilinino; etc A7141959 A71-10509 Aircraft multivheel undercarriaqe effect on riqid SST proqram relation to airline operations, and flexible pavements, examininq failure modes comparinq production confiquration, performance, A71-12164 economics and operation vith subsonics Parametric study of natural frequencies of skin [ AIAA PAPER 70-12171 A71-11248 strinqer structures Diqital simulation proqram in GPSS lanquaqe for AD-7113831 A71-10734 airline operations including aircraft Passivation of metal aircraft surfaces maintenance, fliqht schedulinq, terminal space, [ AD-7119sOl N71-11670 equipment, vork forces utilization, etc AIRCRAFT TIRES A71-11809 Transport aircraft tire pressure and multivheeled Nondestructive testinq techniques for airline landins qear limitations reqardinq pavement maintenance inspection, describinq ultrasonic, desiqn eddy current, maqnetic particles, and X ray A71-12163 methods Stresses and deformations in multi-ply aircraft 1171-12449 tires subject to inflation pressure loadinq Collision avoidance system flight test and r AD-7110731 N71-10434 evaluation proqram €or airline industry CAS Influence of qravel depth and tire inflation specification pressure on soft-qround arrestinq of civil A71-12896 aircraft Pricinq system for landinq and takeoff slots by r RAE-TR-69001 1 N71-11040 passenqer fliqhts for use of Washington National 4IRCRAFT WIKES Airport Reviev of aircraft wake turbulence N71-10170 AD-712080 1 N71-11129 Statistical data on delays and cost of delays at AIRFIELD SURFACE BOVBMENTS airline terminals Taxiinq aircraft position and vheel trajectories N71-10366 for specific nose wheel path Air mail transportation by contract operations A71-11641 N71-108 16 AIRFOIL PROFILES Subsidies for American certificated air carriersN71-12190 Fredholm method for reversible transonic flow in computinq aircraft wins and turbomachine or AIRPORT PLANNING helicopter blade airfoils for compressibility Airport system planninq from environmental law vievpoint, discussinq travel market, airport A71-11022 accessibility, airspace utilization and control Low speed aerodynamic characteristics of airfoil and land use profiles includinq effects of upper surface A71-11642 rouqhness simulatinq hoar frost Aircraft oavement design - Conference, London, IYPL-AERO-13081 N71-11016 November 1970 AIRFOILS A71-12162 Subcritical flows over two dimensional airfoils bv Transport aircraft tire pressure and multivheeled multistrip method of inteqral relations landinq qear limitations reqardiuq pavement rRE-393J1 N71- 10581 desiqn Douqlas DC 9 aircraft crash durinq takeoff caused All-12163 by ice formation on airfoils Eunicipal airport riqid pavements desiqn r NTSB-AAR-70-20 1 N71-10815 considerinq supporting effects of soil subqrade, Oscillatinq flow effects on pressure force normal asphaltic concrete subbase and pavement strenqth to symmetrical airfoil chord A7 1 - 12165 rAD-711R301 N71-11011 Flexible pavements desiqn for qiant transports Three dimensional flov patterns obtained durinq considerinq load repetitions, total systems, boundary laver separation on airfoils environmental effects, etc A71-12166 TNPL-AERO-13091 N71 - 110 1 4 AIRFRAME RATERIALS Runways, aprons and taxiways strenqtheninq to Fiber reinforced composites application in accommodate higher tire pressures and landinq aerospace and aircraft, discussinq boron and speeds, heavier aircraft and surfade ridinq qraphite and cost effectiveness requirements A71-11277 A71- 12169 Be mechanical and physical properties, corrosion Aircraft pavements desiqn and construction behavior, toxicity, fabrication and application problems reqardinq adverse soil conditions as aircraft and spacecraft structural material A71-12170 171-11539 Air traffic pattern prediction for 1980 peak Nonmetallic aircraft construction materials, summer periods in London, Bnaland terminal area discussinq wood epoxy and polyester resins N71-10163 A71-12299 proqram effectiveness and facility criteria for Nb alloys in hypersonic qlider fabrication, ILS investment decisions discussinq mechanical properties, oxidation N71-10355 resistance and sandwich panel desiqn National Aviation Facilities Experimental Center 171-12935 history and proqrams AIRFRANES N71-10356 Aircraft turbine enqine development, considerinq statistical analysis of direct rail rapid transit mismatch reduction between engine and airframe system impact on transportation to Cleveland in fliqht tests airport A71-lllRO N71-10370

A-6 SWBJECT IEDEX ATTACK AlRCRAPT

File formats and code descriotions for analysis of ARALOG SIIlULATIOE direct rail raDid transit svstem iaoact on Critical flutter of vira vith rioid aileron transportation to cleveland.airport studied by analoo computer modelino R71- 10371 1-11-10606 AIRPORTS ANGLE OF ATTACK Rapid rail transit service to airports Three dimensional attacked coaoressible laninar F71- 10167 boundary layer on slender cones in hypersonic Pricinq system for landing and takeoff slots by fliqht at hioh angles of attack derived by passenqer fliqhts for use of Uashinqton National numerical inteqration Airport A71-10926 17:-10170 Pressure distributions prediction on blnnt bodies Air carrier demand for slots particularly in area at angle of attack, considerinq bodies of of lashinaton-Baltimore revolution and larae anale cones I PB-193350 1 8-11-10347 rnma PAPER 70-2081 171- 11580 Selected tabulations from Cleveland Ropkins ABTBBNA RADIATIOE PATTERES Airport user surveys before and after rail Secondary currents on conductinq cylinder near transit service dipole antenna manifested as radio frequency vi-10360 interference, considerino effect on radiation Aiqh speed access system evaluation for oattern transportation from jetport to Riami with cost A71-11167 estimates and network descriptions APPROACR COETROL [ PB-192842 J R71-10417 Time- synchronized approach control combininq Impact of rapid rail transient service fro* aircraft precision naviqation and qnidance with central business district to airport ATC equipment n7i-104~0 A7 1- 12894 Development study for VPR heliport standard APPROACH INDICATORS lighting system Visual aids for secondary airports r AD-7109821 N71-10682 [PAA-RA-70-51 J A71-11474 Inventory of existinq airport system in Rhode Visual approach slope indicator system for Island lonq-bodied aircraft ~~~-1893321 R7 1- 1102 8 rFAA-RD-70-76] N71-11905 Community physical. psycholoqical. and social APPEOPEI ATIOUS reactions to aircraft noise around 7 OS Subsidies for American certificated air carriers international airports N71-12190 TAASA-CR-111316] 1171-11032 ASCEET Visual aids for secondarv airDorts Inflatable restraint collar for larqe balloons TPAA-NA-70-51] 171-1 1474 with heavy loads nsinq winch driven cable AIRSPACE launching ATC antorstion, cslng conflict Prediction 171-11821 alqOrithB based on airspace assiqnment to ASPECT RATIO aircraft enterino system Civil aircraft aspect ratio relationship to 171-11698 commercial viability. considerinq need for AIRSPEED minimum induced draq at wing loadinq to improve Forward horizontal speed influence on aerodynamic payloads. speeds and ranges characteristics of air cushion vehicle vith A71-11628 circnlar nozzles and cylindrically or conically Guide vanes small aspect ratio effect on high shaped curtains pressure staqes of axial flow compressors A71-12551 871-12558 Airspeed contribution to noise level within fixed ASPHALT and rotary winq aircraft Cement and asphaltic materials evalnation for nse rlP-771359j 1171-10705 as qrout under landinq mats ALGORITHIS r AD-7109621 1171-10681 ATC automation, usinq conflict prediction ATIOSPRERIC BOUEDARY LAYER alqorithm based on airspace assignment to Low altitude slow aerodynamics, discnssinq earth aircraft entering system surface vind modeling. powered-lift flight 871-11698 efficiency and animal fliqht ALL-UEATBER AIE EAVIGATIOI A71- 10818 Nan machine considerations in all-weather low ATIIOSPEERIC COIPOSITIOE level navigation system aesiqn, notinq Soviet book on meteoroloqical conditions and off-course error reduction by command supersonic aircraft fliqht coverinq atmospheric information display to pilot composition and structure, temperature A7 1- 10515 distribution, wind effects, etc Aircraft all weather automatic landing system, 171-12840 discnssinq cosponent weights and reliability ATIOSPRERIC TBUPERATURE connected with problem area Reverse flor tesperature probe design and A71-12274 calibration for vertical soundinus from All-weather automatic landinq electronic aircraft, comparing to radiosonde method technology, describing flight automation landing 1171-11822 system for VC 10 BAC 111 and Concorde aircraft ATEOSPRERIC TURBWLEECE 1171- 12275 Scale lengths in atmospheric turbulence from ALTIBBTBRS spectra and aatocorrelation of vertical air Aircraft ultrasonic altitude and vertical velocity velocity component measured in lov flyinq sensor for low fliqht, discussinq VTOL aircraft aircraft automatic hoverinq control and tise lag 171-10859 A71-11624 Aerodynamic theory of pressure field induced on Aircraft accident investigation of United Air liftinq surface by isotropic atmospheric Lines, Boeinq 727-22C near Los Anqeles, 18 Jan. turbulence, considerinq transfer function of 1969 Concorde aircraft TPB-190812 1 1171-10914 TICAS PAPER 70-301 A71-11019 uunInun ALLOYS ATOIIC CLOCKS Airplane materials mechanical properties Synchronization of distant atomic clocks by mere degradation due to fatigne. discussinq breaking overfliqht - Operation Synfral strain of A1 alloy [ ONERA-NT-165 1 R71-11681 171-11395 ATTACK AIRCRAFT Al-Zn-ng-Cu type high strength A1 alloys Iach 2 nirage nilan ground attack fiqhter. notinq mechanical properties evaluation by fractnre lift aid moustache, low speed and steep approach mechanics methods handling from short airstrips A71-11540 171-12740

A-1 AUSPORBING SUBJECT INDEX

AUSPORMING balloons Piqh velocity metal workinq, discUSsinq airfoil A71-11048 forqinq, ausforqinq of bearinq race blanks, Inflatable restraint collar for larqe balloons toolinq, etc with heavy loads usinq winch driven cable r sn~PAPPR nF-70-228 i A71-11267 1a u n c h i n q AUTOMATIC LANDING CONTROL ' A71-11821 Aircraft all weather automdtic landinq system, Development and characteristics of hot air balloon discussinq component weiqhts and reliability deceleration and recovery system connected with problem area INASA-CASE-XLA-06824-21 N71-11037 A71-12274 BASE PLOW All-weather automatic landinq electronic Ec-at transfer in base type supersonic laminar and technoloay, describinq fliqht automation landinq transitional separated flows system for vc 10 BAC 111 and concorde aircraft [ AD-7103471 N71-10249 A71-12275 BENDING VIBRATION AUTOIATIC TEST l!:yOiPiiZB'i Natural frequencies of cantilever turbine blade Aircraft structures fatique testinq device usinq rlth ~zyzzekxirnprofoil under coupled bending- proqrammed control of electrical inputs to torsion vibrations, usinq Ritz-Gaierhin wetho?. electrodynamic vibration stand, notinq load for equations of motion cvcle effects and damaqe accumulation A71 - 11 014 A71-10409 BERYLLIOI AUTOEATIOA Be mechanical and physical properties, corrosion ATC automation, usinq conflict prediction behavior, toxicity, fabrication and application alqorithm based on airspace assiqnment to as aircraft and spacecraft structural material aircraft entering system A71-11539 A71-11698 BIBLIOGRAPRIES AUTOROBILES Biblioqraphy of documents containinq numerical Air and land transportation noise sources and data on planar liftinq surfaces measurement, noise level scales, and individual r AGARD-R-574-70 1 N71-10339 and community responses - conference BILLETS r PB-19 1117 1 N71-10349 Radioqraphic nondestructive testinq method on AUXILIARY POWER SOURCES titanium billets for enqine disk forqinq Aircraft eneraency evacuation illumination N71- 11639 standards. considerinq independent power source, BLOCKING crash survivable installation, operation Simulatinq downstream flow blockaqe doors in initiation and exit visibility bypass air duct of turbofan enqine with axial A7 1 - 10030 flow fan rotor Small qas turbines for aircraft auxiliary power r NASA-TN-D-6071 1 N71-10537 unit, considerinq compressor and combustor BLOWDOWN WIND TUNNELS desiqn, noise, fuel consumption and specific Test facilities, wind tunnels and tests at weiqht oroblems nodane-Avrieux Center A71-1075 1 [ONERA-NT-1661 N71-11470 AVIONICS Calorimetric and thermocouple pyrometer heat flux Avionics system maximizinq pilot chances of measurements in blowdown wind tunnels survivinq mission and destroyinq selected tarqet r ONERA-NT-159 1 N71-12059 bv removina mental limitations BLUNT BODIES 1171-10506 Pressure distributions orediction on blunt bodies Liqhtninq induced voltaqes in aircraft electrical at anqle of attack, considprina bodies of circuits revolution and large anqle cones INASA-TN-X-52906 1 N71-10391 [AIAA PAPER 70-2081 A71-11580 AXIAL PLOW Unsymmetrical nose bluntness effect on stability Simulatina downstream flow blockaae doors in derivatives of slender cone at nach 111 bvpass air duct of turbofan enqine with axial rAD-711921J N71-11008 flow fan rotor BODIES OF REVOLUTION I NASA-TN-D-60711 N71-10537 Wind tunnel apparatus for reproducinq coninq and AXIAL PLOW TURBINE5 spinninq motions of bodies of revolution, usinq Flutter analysis on axial turbomachine bladinq six-component strain qaqe balance for r~D-7107941 N71-10562 aerodynamic forces Cold air tests on axial flow turbine with A71-10930 transpiration cooled discrete hole stator blades Monoqraph on plane shock wave interactions to determine coolant flow ejection effect on coverins supersonically movinq two dimensional turhine aerodynamic performance thin airfoils, slender bodies of revolution and INASA-TM-X-21231 N71-110 10 thin winqs A71-11227 Two dimensional axisymmetric laminar boundary B layer on blown winq and body of revolution, 8-52 AIRCRAFT usinq sixth-order polynomial for velocity LAMS fliqht control systems for turbulence induced distribution fatique daaaqe reduction in 8-52 and C-5A A71-12554 aircraft, usinq mathematical models Boundary layer transition studies of several A71-11660 pointed bodies of revolution at supersonic B-52 LAMS test vehicle structural modification and speeds instrumentation in f liqht phase I NASA-TN-D-6063 1 1571-11520 A71-11661 BODY-WIlG AND TAIL COUPIGURATIONS BACTERIA Rinq-body interference in supersonic inviscid Ricrobioloqical fuel corrosion by bacteria and flow, extendinq Stewartson approach to arbitrary funqi in fuel tanks smooth convex cylinder r AD-712103 1 N71-11848 A71-10774 BALANCING BOEIUG 727 AIRCRAFT Flexible rotor balancinq by exact point-speed Aircraft accident investiqation of United Air influence coefficient method Lines, Boeinq 727-22C near Los Angeles, 18 Jan. [NASA-CR-72774 1 N71-10021 1969 BALLOON SOUNDING r PB-190812 1 N71-10914 nountainous reqion vertical air flow research, BOEING 747 AIRCRAFT describinq superpressure balloon and precise Boeinq 747 aircraft crash landing in Washinqton pressure radiosonde system caused by pilot error 1171-12420 [ NTSB-AAR-70-191 N71-10814 BALLOONS BOLTS Numerical stress-strain calculation for desiqn of Soviet book on boltinq and coupling elements hiqh pressure fiberqlass-reinforced plastic threads used in aircraft industry covering

A-8 SUBJECT IIDBX CIVIL AVIATIOR

confiqurations selection, cuttinq, tolerance CARBO1 requirements and quality control Carbon fiber reinforced epoxy composites, A71-12723 evaluating application as helicopter tail rotor BOBOH blade saterial PoliVmide/boron reinforced plastic structures A71-12477 fabrication. discussing use in leading edqes Carbon fiber-epoxy resin composites in aircraft r snE PAPER EM-70-133 3 A71-11263 industry, examining fatiqne life, cost, specific BOOIDART LATEE SEPARATIOII moduli and mechanical properties ROtatinQ stall in axial flov cospressor hiqh 871-12488 pressure staqes, taking into account boundary CAB60 layer separation Legal aspects of air and surface carrier A71-11063 interactions in freiqht transportation Boundary layer separation at free streamline R71-12119 attachment to sharp trailins edge of flat plate, CASCADE PLOW deducing terminal velocity profile for tvo Plane linear cascades of thin curved profiles, dimensional flov obtaining potential flov velocities and lifting All-12376 force on leading edge ninimum suction rate preventinq laminar boundary A71-10339 layer separation from curvilinear porous surface Trajectories and velocities of solid particles in jet flou entrained by fluid flovs in cascade nozzles 1171-12553 [AD-7111211 n7i-10546 Heat transfer in base type supersonic laminar and CAVITIES transitional separated flovs Supersonic and transonic flov including effects of [ AD-7103471 R71-10249 pressure oscillations vithin cavity, predicting Three disensional flou patterns obtained durinq rectangular cavities drag from mathematical boundary laver separation on airfoils sodel rRPL-AERO-1309] mi-1 1o 14 1171-10931 Separation point study of incospressible laminar CEEEETS boundary layers around parabolic bodies at angle Cement and asphaltic materials evaluation for use of attack as grout under landinq mats CAD-712084] R71- 1151 9 [AD-7109621 R71-10681 BOURDART LATER TRAISITIOII CERTRIPUGAL COEPRESSOBS Boundary layer transition studies of several Coolinq vater system for compressor of supersonic Pointed bodies of revolution at supersonic wind tunnel speeds r AD-710971 J nm-10679 I AASA-TR-D-6063] n7i-ii520 CE-46 HELICOPTER BRAKES (FOB ARRBSTIH6 EOTIOl) Plight control softuare package for digital fliqht Statics ana aerodynamics of liftinq decelerators control and landinq system of CA-46C helicopter haravinqs and sailsings/ at supersonic and I...-, mn~k-CA-iiG905i 871-10283 h?------:ySLD~~~~ ~ speeds Guidance softvare package for diqital flight rAIAA PAPER 68-9451 A71-10927 control and landing system of CA-U.5C helicopter BUBBLES [RASA-CR-l11025] mi-10284 Delaved bubble movement on airfoil dnrinq Systems performance/desiqn requirements helicopter stall specifications for CH-46C helicopter digital [AD-711540 1 871- 11005 fliqht control and landinq system BUPPETIIIG [NASA-CR-110889 J n7i-10294 Swept uinq fighter aircraft transonic buffet onset Systems analysis of fliqht control and guidance of lift coefficient fro. camber and trailinq edoe ~~ CA-46C helicopter deflection, considering design variations INASA-CR-1110241 N71-10297 A71-12679 CH-54 EELICOPTER BUILDIIIGS flight simulation for evaluatinq proposed %nit Doom and explosive shock vave effects on stabilization system to ensure helicopter bnildinqs and structural members hoverino precision during carqo loadiig R71-11035 [AD-7109481 A71-10564 BYPASSES CHARNEL PLOW Servosystem design of hiqh-response multislotted Sveptback turboblades in parallel wall channel. bvpass valvinq system for supersonic inlets investiqating thickness, camber and leadinq edge rNASA-TA-D-6081] R71-11061 curvature effects on flow and pressure distributions and vortex taovement A71-12606 C CIRCULAR CORES C-5 AIRCRAFT Circular cone vith cross shaped wings in LARS flight control systems for turbulence induced supersonic flov. determinins glov fatique damage reduction in B-52 and C-5A characteristics, velocities and pressure aircraft, using mathematical models A71-11Q58 A71-11660 CIRCULAR CTLIRDERS C-5 military transport stability augmentation for Circulation control by slot suction on circular pitch and yaw inertia at lov speed, nsinq pilot cylinder evaluation on cockpit sisulator [LR-5301 N71- 11002 1171- 12684 Laminar near vake characteristics behind circular CABLES (BOPES) cylinder in nach 6 rarefied air stream Inflatable restraint collar for larqe balloons [REPT-1108/701 R71- 11 0 12 vith heavy loads usino vinch driven cable CIVIL AVIATIOR launchino Civil aircraft aspect ratio relationship to A71-11821 commercial viability, considerinq need for CALIPOBHIA minimum induced draq at vinq loading to improve Aircraft accident investiqation of Onited Air payloads. speeds and ranges Lines, Boeinq 727-22C near Los Anoeles, 18 Jan. 1171-11628 1969 Systems approach to accident investigation in rPB-1908121 N71- 10914 civil aviation and homes CALORIEETERS N71-10115 Calorimetric and thermocouple pyrometer heat flux Demonstration plan for uestern Region Short Haul measurements in blovdoun vind tunnels Air Transportation Program r ONEBA-AT-159 1 117 1-1 2059 IATR- 7 1-/7 1 9 0/- 1 - VOL- 1 ] n7i-10279 CAEBEEED WINGS Technical studies for Western Reqion Short Haul Cambered and sysmetric wing profiles and flap Air Transportation Program coufiqurations, discussinq wind tunnel tests at IATR-71-/7190/-1-VOL-2] N71-10280 moderate Reynolds numbers Air carrier demand for slots particularly in area A71-11950 of Uashinqton-Baltimore SUBJECT INDEX

IPB-1933501 N71-10347 A71-12896 National Aviation Facilities Experimental Center cooperative Doppler radar system for avoiding history and proqrams midair collisions N71-10356 rNASA-CASE-LAR-104031 N71-11766 statistical analysis of direct rail rapid transit COEBUSTION CHAMBERS system impact on transportation to Cleveland Tubular qas turbine engine combustor desiqn by airport combininq turbulent flame speed, microvolume N71-10370 burninq and stirred reactor models File formats and code descriptions for analysis of A71-12852 direct rail rapid transit sgstea ippact oz Sweeo frequency nozzle pressure oscillation transportation to Cleveland airport effects on turbolet combustor dynaxics N71-10371 r NASA-TN-D-60841 1171-10982 PAR statistical handbook of aviation 1958-1968 COIIEERCIAL AIRCRAFT N71-10372 German monoqraph on commercial jet aircraft Statistical tabulation of United states civil aaintenance svstems coverinq changes and aircraft accident histories for 1969 adaptations for performance improvemerti A71-10114 r PP-1907921 N71-10932 Statistical tabulation of United States civil German monoqraph on systems analysis of future let aircraft accident histories in 1968 and fan propulsion systems for VTOL commercial r P5-190911 J N71-10933 aircraft weiqht and cost reduction Lpqal asoects of air and surface carrier A71-10115 interactions in freiqht transportation commercial transport aircraft maintenance N71-12119 simulation llonte Carlo nodelinq techniques, Possible benefits of local and trunk air carrier considering aDplication to airline operations nersers [SAE PAPER 7003451 A71-10128 N7 1- 12 120 Civil aircraft aspect ratio relationship to Subsidies for American certificated air carriers commercial viability, considerinq need €or N71-12190 minimum induced draq at winq loadinq to jmprove CLAIIPS oayloads, speeds and ranqes Inflatdble restraint collar for larqe balloons A71-11628 with heavy loads usinq winch driven cable FAA statistical handbook of aviation 1958-1968N71- 10372 Iaunchinq A71-11821 Aircraft incident report and investiqation of Air CLEAR AIR TURBULENCE France Boeinq 747, St. Jean, Canada, August 17, Thin CA" laver dptection in lower stratosphere by 1970 N71-10531 I. band radar conplemented by radiosonde and U-2 INTSB-AAR-70-261 3ircraft prohes Influence of qravel depth and t.ire inflation A71-10567 pressure on soft-around arrestinq of civil COATINGS aircraft "h--rinzl coatinss of oondola payloads I QAE-TR-690011 N71-110110 r ~~o-3747-121 N71-10496 Leon1 aspects of air and surface carrier COCKPIT SIIIULATORS interactions in freiqht transportation c-5 military transport stability auqmentation for N71-12119 Ditch and yaw inertia at low speed, usino pilot Possible ber.e?its of local and trunk air carrier evaluation on cockpit simulator merqers A71-12694 N71-12120 Pilot evaluation of movable and riqid cockpit COIIIIUUICATION SATELLITES cov?rol sticks Skynet communication systems, describins lonq r AD-7091391 N71-101D4 distance strateqic communication links between COCKPITS around and mobile air/helicopter stations via Combat aircraft cockpit temperature control system wide and narrow band pathways desiqn and operatior. AT1-12439 A71-10270 COflNUNITIES Airline experience with dual inertial systems as coemunity ohysical, psycholoqical, and social sole means of naviqation, considerinq equipment reactions to aircraft noise around 7 US reliability, cockoit desiqr. traininq, etc international airports A71-10509 r NASA-C'-ll 13161 N71-11032 COHERENT RADAR COIIPARISON Coherent laser synthetic auerture radar at Computer calculations of Drccsure distributions on microwave frequencies for airhorne sround point swept winqs tarqet mappinq TNLR-TW-T-1891 N71-11015 A71-12044 COIIPONENT RELIABILITY COINING Aircraft all weather automatic landins systen, Aircraft structure fatique lift. isDroveaent via discussinq component weiqhts and reliability metrrial stress coininq inside aad arouid holes connected with problem area an4 slots A71-12274 P.71- 10170 CONPOSITE NATERIALS COLD FLOW TESTS Fiber reinforced conoosites application in Cold air tests on axial flow turbine with aerosuace aqd aircraft, discussinq, boron and transuiration cooled discrete hcle stator blades qraphite and cost effectiveness t3 Becermine coolant flow election ~ffector. A71-11277 turhinr aerodvnamic Performance Comnosite materials structure cost effectiveness I NFSA-TI-X-272 3 J Y 7 1 - 1 1 0 1 0 denonstraten in aircraft relief crew compartment COLLISION AVOIDANCE panels 4mPrican LTA prototype aircraft colliqion All- 112R1 avoidaqce equipment and Prooosed noncooperative Carbon $iber reirforced plastics and metals svstrm structural components desiqn, discussinq P 7 1- 1 075 3 properties, processinq and applications ATC automation, usinq conflict predictior. A71-12910 alqoritbn basrd on airspact= assianment to COMPRESSIBILITY EFFECTS aircraft. enterinq system Fredholm method for reversible transonic flow in A71- 11698 computinq aircraft winq and turboEachine or ATA Colliqion Avoidance Systw based on time and helicopter blade airfoils for conDressihility frequency synchronization via qround stations or law other aircraft A71-11022 A71-12895 CONPRESSOR ROTORS

A-10 SUBJECT IRDEX COST EPPECTIVENESS

r NASA-TN-D-607 11 N71-10537 Aircraft pavement design - Conference, London, CO!IPOTATIOII November 1970 PORTRAR proqram for computinq coordinates of 871-12162 circular arc sinale and tandem turbomachinery Air and land transportation noise sources and blade sections on plane measurement, noise level scales, and individual [ N1SA-TN-D-60201 N71-10411 and commnnity responses - conference COBPOTER PROGRAIS r PB-1911171 N71-10349 Flon field of two dimensional nozzle exhaustinq to Raintenance proqrams, evaluation, acceptance. and vacuua, describinq conputer proqram based on BGK monitorina procedures for transport aircraft equation and plottinq exhaust region density, 571-11020 temperature and velocitr ldvanced technoloqy for production of aerosDace IAIAA 2APER 69-6581 A71-10932 enqines - conference Real time six deqree of freedom aircraft fliqht r AGARD-CP-64 1 N71-11626 diqital simulation usinq SL-1 continuous system Radiographic nondestructive testinq method on simulation lanquaqe titanium billets for enoine disk forsina 1171-11786 V71- 11639 Diqital simulation proqram in GPSS lanquaqe for COIIPIGURATIOll BARAGEIENT airline operations inclodinq aircraft Outimization techniques in aircraft conficuration maintenance. fliqht scheduling, terminal space. desiqn equipment, nork forces utilization, etc [ AD-71 1410 1 871-11023 1171-1 1809 comcaL BODIES Plight control softnare packaqe for diqital fliqht Boundary layer transitior. stuaies of several control and landinq systea of CR-46C helicopter pointed bodies of revolution at supersonic r NASA-CR-l10'405] 171-10283 speeds Guidance softnare packaqe for disital fliqht r NASA-TN-D-60631 N71-11520 control and landing system of CE-46C helicopter COIICAL FLOP I NASA-CR-111025 1 N71-10284 Soviet book on nonlinear conical gas flon theory FORTRAN proqram fir conpotins coordinates of coverins flons nith different characteristics circular arc sinqle and tandem turbomachinery uast bodies of various qeometries an8 nositions blade sections on plane ~71-1271~ r NASA-TW-D-6020] 171-10411 CONSTROCTIOI IATERIALS PORTRAN program for calculatinq aerodynamic forces Airolane materials mechanical properties from pressure or velocitv distributions on blade deqradation due to fatique, discussinq breakius sections strain of A1 allop rNASA-TR-X-2123] N71-10467 171-1 1395 Computerized calculations of adiabatic laminar COIITOORS boundary layer and shock wave interactions us'inq !!iniaum suction rate urevertina laminar boundary Klineberq method layer separation from cnrvilincar porous surface I VRI-TN-60 1 N? 1- 3 1017 in jet flov Compnter proqrazs and predictor displays for A71-12553 solvinq air traffic control DrObleBS COITRACTS [VASA-CR-1113721 N71-11466 Air mail transportatign by contract operations COBPOTERIZED DESIGR Y71-10R16 Computerized analysis of seal temperature, elastic Conqressional hearinq on investiqation of contract displacements and seal force balance in for TFX aircraft iterative desiqn method for qas turbine 171-11034 mainshaft seals CONTROL SURFACES A71-10479 Linear theoretical method for arbitrary wino Optiaization techniaues in aircraft confiquration planfora and trailinq edqe control surfaces in desiqn lor fr~n91~n-y3czillatci~ moticn in subsonic TAD-711410 J R71-11023 flon C^_.,.,----vttiizea sealiuo dam design analysis for qas r APL-AERO-I~O~1 N71-11013 film seal of turboshaft CONTROLLERS R71-12039 Pilot evaluation of movable and riqid coctpit COBPQTERIZED SIIULATIOR control sticks Computer simulation - Conference, Denver, June I AD-709934 J 1171-10184 1970 CONVECTIVE BEAT TRANSPER A71-11777 Calorimetric and thermocouple pyrometer heat flux Comuuterized aerodynamic optimization of aircraft measurements in blondonn nind tunnels Propellers [ONERA-NT-1591 171-12059 [ AD-710356 J N71-10122 CONVEB6ERT ROZZLES Computer calculations of pressure distributions on Nozzle lateral spacing effect on drag and swept ninqs oerformance of tnin jet afterbody confiqurations r ALR-TI-T-1891 N71-11015 with converqent nozzles at Mach 0.6 to 2.2 CORCORDE AIRCRAFT [AASA-Tn-X-20991 N71-10276 Concorde role in air traffic market, discussinq COORDIIATES operatinq costs and profit potential FORTRAN proqram for computinq coordinates of 1171-12746 circular arc sinqle and tandem turbomachinery Influence of Concorde ponerplant operatinq blade sections on plane conditions on design of olvmpus 593 fuel and oil [ SASA-TN-D-6020 1 N71-10411 System COBRERS 171-11653 Supersonic laminar boundary layer structure near COEDOCTIIG FLOIDS convex corners for large turninq anoles Inviscid ideallr conductinq fluid flon past thin 1171-10461 foil in transverse maqnetic field, usinq small CoBuosroR RESISTAIICE parameter method Be mechanical and physical properties, corrosion A71-12629 behavior, toxicity, fabrication and application COIES as aircraft and spacecraft structural material Supersonic overexpanded jet f lon past cone, 1171-11539 determininq impingement point by method of COBROGIiTED PLATES characteristics APDliCatiOn of corruqated core sandwich structures A71-10613 to ponerplant components CORPERERCES N71-11636 Role of man in naviqation - Conference, Colorado COST AIALTSIS Sprinqs, July 1970 Statistical data on delays and cost of delays at A71-10501 airline terminals Computer siaulation - conference. Denver, June N71-10366 1970 COST EPPECTIVENBSS A71-11777 SST proqram relation to airline operations,

A-11 COST ESTIHATES SUBJECT INDEX

comparinq production confiquration, performance, N71-10355 economics and operation with subsonics DEFLECTION [AIAA PAPER 70-12171 A71- 11248 calculations and measurements of strain composite materials structure cost effectiveness distribution and deflection on model swept winos demonstrated in aircraft relief crew compartment NAL-TR-1951 N71-11950 panels DEFLECTORS A71-11281 Retrodiffusion interferometric holoqraphy in wind subsonic aircraft size effect in conventional tunnels inclu3ing displacement and deformation desiqn, discussinq increased weiqht increments of deflectors and economic gain rat? r ONERA-TP-8521 N71-11510 rAIAA PAPER 70-94OJ A71-12676 DEGREES OF FBEEDO!! COST ESTIMITES Real time six deqree of freedom aircraft fllqht Hiqh speed access system evaluation for digital simulation usinq sL-1 continuous system transportation from jetport to Niami with cost simulation lanquaqe estimates and nerwoL'n iescripticns A71-11786 [ PB-1928421 N71-10417 DELAY Air mail transportation by contract operations Statistical data on delays and cost of delays at N71- 10816 airline terminals Subsidies for American certificated air carriers 171-10366 N71-12190 DELTA WINGS COST REDUCTION Thin delta winq with leadinq edqe separation, German monoqraph on systems analysis of future jet obtaininq draq lift and rollinq moment and fan Propulsion systems €or VTOL commercial coefficients and pressure distribution aircraft weiqht and cost reduction A71-12408 A71-10115 Optimal cross sectional dimensions of thin walled COUNTING CIRCUITS lonqeron beams and ribs of skin reinforced delta Laser gyro qoniometry for fluctuations and anqular winqs minimizinq weiqht measurements at low rotational velocities, A71-12562 notinq countup/countdown detection systems Leadinq edqe effect on aerodynamic characteristics A71-12924 of 70 deq swept delta winq COUPLING rAD-7120871 N71-11007 Soviet book on bolting and couplinq elements DESCENT TRAJECTORIES threads used in aircraft industry coverinq Lear jet crash durinq instrument approach due to confiqurations selection, cuttinq, tolerance descent below path profile requirements and quality control TNTSB-AAR-70-211 N71-10813 A71-12723 DIPPEUENTIAL EQUATIONS CRASH LANDING Critique of Chapman-Kirk iterative method for Aircraft qalley desiqn safety criteria, differential equations yieldinq aerodynamic considerinq injuries from routine use, normal, coefficients from free fliqht data crash or ditchinq conditions component A71-10971 dislodqment, equipment malfunctions and defects DIGITAL SIMULATION A71-10029 Hathematical model and diqital simulation for Jet aircraft crash durinq instrument approach due nonlinear characteristics of prototype to electrical systems failure inteqrated actuator packaqe for fiqhter aircraft [NTSB-AAR-70-221 N71-10812 control Boeinq 747 aircraft crash landinq in Rashinqton A71-11783 caused by pilot error Real time six deqree of freedom aircraft fliqht [NTSB-AAR-70-191 N71-10814 diqital simulation usinq sL-1 continuous system CROSS COOPLING simulation lanquaqe Systems analysis application to stability of A71-11786 aerodynamic cross couplinq in fliqht vehicle Aircraft manual fliqht control analysis Using motions with steady sideslip, usinq feedback and continuous mathematical pilot model for closed root locus techniques loop diqital simulation A71-12687 A71-11787 CRUISING PLIGBT Diqital Simulation proqram in GPSS lanquaqe for Subsonic wind tunnel investiqation of rotary wins airline operations includinq aircraft confiqurations for VTOL aircraft in cruise mode maintenance, fliqht schedulinq, terminal space, I NASA-TN-D-59451 N71-11025 equipment, work forces utilization, etcA71-11809 CYLINDRICAL BODIES Secondary currents on conductinq cylinder near DIGITAL SYSTEHS dipole antenna manifested as radio frequency systems performance/design requirements interference, considerinq effect on radiation specifications for CH-46C helicopter diqital oattern fliqht control and landing system A71-11167 r NASA-CR-1108891 N71-10294 DIGITAL TECRNIQUES Inertial naviqation system auqmented by diqital D distance measurinq equipment in FAA fliqht DAHS inspection aircraft for performance evaluation Computerized sealinq dam desiqn analysis for qas A71-10507 film seal of turboshaft DIMEHSIONAL AHALYSIS N71-12039 Scale lengths in atmospheric turbulence from DATA LInKs soectra and autocorrelation of vertical air Skynet communication systems. describinq lonq velocity component measured in low flyinq distance strateqic communication links between aircraft qround and mobile air/helicopter stations via A71-10859 wide and narrow band pathways DIPOLE AHTEHNAS 1171-12439 secondary currents on conducting cylinder near DATA PROCESSING dipole antenna manifested as radio frequency Acquisition and processinq of aircraft search interference, considering effect on radiation radar data obtained by track-while-scan pattern technique, usinq off-line diqital computer A71-11167 A71-11392 DIRECT LIFT CONTROLS DECELERATION Aircraft direct lift control based on fliqht and Development and characteristics of hot air balloon simulator experiments, discussinq effect on deceleration and recovery system desiqn [NASA-ChSE-XLA-06824-21 N71-11037 A71 - 10754 DECISION RAKING DISKS (SHAPES) proqram effectiveness and facility criteria for Heasurements of hypersonic, rarefied flow field of ILS investment decisions disk

A-12 SUBJECT IUDEZ BLBCTBOIIC COBTBOL

r AD-7 10641 ] 1171-10461 ECOllOEICS DISPLAY DEVICES Economic contributions of U. S. domestic airline Nan machine considerations in all-veather low industry in 1970s regarding air transportation level navigation system design. noting constraints and impact on short haul off-course error reduction by command [AIAA PAPER 70-13091 1171-10486 information display to pilot Aeronautical projects development and planning in A71-10515 European Economic community, discussins Electronic control indicator for human pilot aerospace industry organizational problems and

capability enhancement using color coded cathode role in economy ~ ray display, presenting information from seven A71-11676 different instruments BDUCATIOA A77- 10750 Airline exuerience with dual inertial svstems as Steep approach to landing for jet transport sole means of navigation. considering- equipment aircraft noise abatement, nsing ground based reliability. cockpit design, training, etc equipment and onboard TV display A71-10509 A71-11311 BJBCTIOU SEATS DISTAUCE EBASUBIIS BQUIPH~T Feasibility of usins flexible rotor blades for Inertial navigation system auqmented by digital ejection- systems distance measuring equipment in FAA flight 1AD-7116421 117i-ii022 inspection aircraft for performance evaluation Requirements for ejection seat systems A71-10507 [BAE-LIB-TRAUS-1471] mi-11042 DITCBIUG (LAWDIUG) BLASTIC PBOPBETIES Aircraft qalley design safety criteria, Rigid and flexible pavement design and considering injuries from routine use, normal, construction in Europe. discussinq unreinforced crash or ditching conditions component and crack reinforced'siabs and CBR method dislodqment, equipment malfunctions and defects A71-12167 1171-10029 ELBCTBIC COUDUCTORS DOPPLBE BADAB Secondary currents on conducting cylinder near Performance characteristics of Bendix type DRA-12 dipole antenna manifested as radio frequency airborne Doppler radar system interference, considering effect on radiation [ FAA-AA-70-501 ~71-10394 pattern Cooperative Doppler radar system for avoiding A71-11167 midair collisions ELECTRIC COATROL [ NASA-CASE-LAR-10403] 871-11766 Electrohydraulic thrust control system for DORAIEB AIBCBAFT supersonic transport aircraft eugines, Do-132 liqht five seat tip drive turbine considering reliability. performance and weight helicopter, discussing applications, fliqht [SAE PAPER 7008191 1171-11546 testins. desiqn ana major components Aircraft electric systems control by solid -+ate ,-I-.r.'.G- Pl I I"* J svitching, discussing reliability, service life, DBAG versatility and compatibility Spheres drag coefficient at hypersonic Each A71-11627 numbers for near free molecular flow ELECTRIC FIELDS A71-10969 Electric and maqnetic cross field effects on Spheres Oseen draq, extending Goldstein expansion aerodynamics and thermal reqime of qas flame for Wavier-Stokes equation in powers of Reynolds cone number [ AD-7123361 w71- 12075 A71-12380 LECTRIC POTEllTIAL DBOP TESTS Liqhtning induced voltaqes in aircraft electrical Drop and impact tests for improvins circuits crashworthiness of integral fuel tanks r NASA-TR-X-52qOS 3 li7 1 - 1 0 33 i F P R I - 1A- 7 0 - 4 6 7 N71-11019 ELECTRICAL FAULTS DUCTED FA. EUGIAES Jet aircraft crash durinq instrument approach due Blade bound vortex system mathematical model for to electrical systems failure optimum heavily loaded ducted fans, includinq [NTSB-BAR-70-22 J N71-10812 thrust, power and efficiency desiqn parameters ELECTBICAL ELISUBBEEAT 171-12677 Liqhtninq induced voltaqes in aircraft electrical Uind tunnel study of aerodynamic interference draq circuits caused by fan jet enqine wake of supersonic RASA-TR-X-529061 N71-10391 transport ELECTBOCKEEICAL EACKIUIIIG I NLSA-TN-D-6067 J 1171-11004 Electrochemical machining for aircraft engine DUCTILITY metal components, discussing cost, time Niobium alloys for qas turbine blades, examining comparisons, tooling techniques and applications workinq temperatures, protective coatinss and r SEE PAPER RR-70-206 1 A71-11252 ductility Electrochemical machining role in jet engine A71-12939 industry. discussing drillius, contourinq, DYAAEIC COUTROL electrolyte handlins, etc Eodel performance index /pi/ providing criterion r SRE PAPER ER-70-1931 A71-11253 for approximatinq one dynamic flight control Introduction of electrochemical machining in system by another based on geometrical aeronautical industry representation of linear autonomous systems 171- 116 47 [AIAA PAPER 69-8851 A71-12682 ELECTRODES DYIIAEIC LOADS Performance of reducing electrode for neutralizing Cumulative frequency distributions of aircraft electrically charqed hydrocarbon fuel flow landins qear loads in determininu fatigue life f AD-7123681 1171- 11876 TRAE-LIB-TRANS-1462 J A71-10273 ELECTBOLYTES DYUAEIC RESPOBSE Applications of electrolyte rectification in Aircraft response to atmospheric qust, discussing aeronautics industry spectral analysis procedures and calculation N71- 11637 results on T-tail aircraft desisn ELECTBOA BEAU UELDIUG A71- 10752 Residual stress measurements and heat treatments for electron beam welding of rotating turbine enqine parts E N71-11644 EABTK EBVIBOBEElT noderu weldins methods in aircraft and aerosuace Commercial SST environmental effects on industry stratospheric air, water vapor content aud earth N71- 11650 surface temperature ELECTRONIC COllTBOL A71-11178 Aircraft flaps and ailerons actuators electronic fly by wire control as alternative to mechanical

A-13 ELECTROSTATIC CEARGB SUBJECT IIDBX

linkaqes for maneuverability and reliability in turbine. hydraulic and mechanical types f liqht All-10103 All-10825 EnGInE TESTS ELECTROSTATIC CEARGE Engine/compressor test inlet flow field static dissipator additives in aviation fuels for simulation, considering ramp angle, screen eliminatiuq electrostatic charqing hazards location and diffuser length effects All-12300 All-12909 ElERGEllCT LIFE SUSTAIIIIG SYSTEBS RB 211 turbofan engine development testing, Aircraft emergency evacuation illumination describing test program. test facilities, st:!!.lardsi considerinq independent power source, equipment and instrumentation crash survivable installation, operation A11- 12912 initiation and exit visibility EnGInEs All-10030 Fabrication techniques of compact fluidic control EnGInE CONTROL equipment for aerospace engines W71-11654 tlaciiohTdr:nlic-_ thrast rnntrol svstem for nn., “mTn. supersonic transport aircraft engines, ----..---_--!smvuwmm~mI cvI..vA--I considerinq reliability. performance and weiqht Commercial SST environmental effects on [ SAE PAPER 7008191 All-11546 stratospheric air, water vapor content and earth EIGINE DESIGN surface temperature Jet enqine evolution, considerinq thrust, All-11178 combustion chamber, fans, hiqh-pressure-ratio Short haul air transportation technological compressors and turbine inlet temperature factors for VTOL, STOL, CTOL and light aircraft, A71-11181 considering operatinq costs, passenger service RB 211 turbofan enaine design, emphasizinq modnlar and environment impact construction, systems inteqration, [AIAA PAPER 10-12871 A71-11700 maintainability and noise reduction EIVIROIIEIT SILIULATIOI A71-11682 ATC communication environment simulation via N49 Larzac turbofan enqine, describinq design, mathematical model based on ATC statistics development, performance data, manufacturing 171- 10979 techniques, operation and maintenance Engine/conpressor test inlet flow field All-12607 simulation, considering ramp angle, screen Blade bound vortex system mathematical model for location an8 diffuser lenqth effects optimum heavily loaded ducted fans, including 171-12909 thrust, power and efficiency desiqn parameters EIVIROIlEITAL EIGIHEBRIIG 171-1 2677 Airport system planning from environmental Soviet book on aircraft power plant systems and viewpoint, discussing travel market, airport devices coverinq layout, enqine attachment, accessibility, airspace utilization and control propellers, control, fuel and oil systems, fire and land use fiqhtinq, monitorinq, etc A71-11642 A71-12722 EIVIROIMEITAL TESTS Tubular qas turbine enqine combustor design by Ti alloy hot salt stress corrosion under simulated combininq turbulent flame speed, microvolume enqine environmental conditions, presentinq hurninq and stirred reactor models threshold data based on residnal tensile 1171-12852 ductility 871-12885 Aircraft qas turbine engine desiqn and construct ion EPOXY RESIHS r AD-711757 1 17i-io853 Nonmetallic aircraft construction materials, EHGIIE EONITORIIG IllSTRUlEllTS discussing wood epoxy and polyester resins Air transportation reliability tbrouqh turbojet All-12299 enqine performance monitorinq Carbon fiber reinforced epoxy composites, 1171-12368 evaluating application as helicopter tail rotor Soviet book on aircraft power plant systems and blade material devices coverinq layout, enqine attachment, A71- 12471 propellers, control, fuel and oil systems, fire Carbon fiber-epoxy resin composites in aircraft fiqhtinq, monitorinq, etc industry, examininq fatique life, cost, specific A71-12722 moduli and mechanical properties ENGIIE NOISE A71-12488 Aladin 2 interurban Stol transport desiqn with EPUIPIEIT SPECIPICATIOIS blown winqs and jet deflection by winq flaps, Fliqht simulators procurement and commissioninq, emphasizinq enqine noise reduction discussinq difficulties due to different A71-10749 aircraft confiqurations, advantaqes of equipment ElGIIE PARTS and procedures standardization, etc Ni base superalloys fatique strenqth improvement A71-10015 for qas turbine enqine components, discussinq Aerospace enqine starting systems military and homogeneous deformation distribution, qrain size industry specifications and standards, control, etc Considering cartridqe pneumatic, electric, gas A11- 10166 turbine, hydraulic and mechanical types Electrochemical machininq for aircraft enqine A71-10103 metal components, discussinq cost, time Collision avoidance system fliaht test and comparisons, toolinq techniques and applications evaluation proqram for airline industry CAS ISPIE PAPER RR-70-206 1 A71-11252 specification A71-12896 Advanced technoloqy for production of aerospace enqines - conference systems performance/desiqn requirements IRGARD-CP-641 N71-11626 specifications for CH-46C helicopter digital Application of corrugated core sandwich structures fliqht control and landinq system to powerplant components [NASA-CR-1108891 N71-10294 N71-11636 EUROPE X ray fluorescence analysis for quality control of Aeronautical projects development and planning in qas turbine aircraft enqine parts durinq European Economic Community, discussinq manufacture and overhaul aerospace industry orqanizational problems and N71-11641 role in economy Residual stress measurements and heat treatments A71- 11676 for electron beam weldinq of rotatinq turbine BUROPlAll SPACE PROGRAlS enqine Darts Air traffic control by satellite, discussinq N71- 11644 CNES-SGAC and ESRO experiments within Dioscures ENGINE STARTERS project test program Aerospace enqine startinq systems military and A71-10748 industry specifications and standards, EVACUATING (TRAISPORTATION) considerinq cartridqe pneumatic, electric, qas Aircraft emerqency evacuation illumination

A-14 SUBJECT ImDEI PLIGET AL?ITUDE

standards, considerinq independent power source, FEEDBACK COITBOL crash survivable installation, operation Aircraft manual flight control analysis usinq initiation and exit visibility continuous mathematical pilot model for closed 171-10030 loop digital simulation EXHAUST GASES A71 -1 1787 Gas turbines air pollution control, discussing C-5 militar~transport stability augmentation for exhaust comnosition. combustion chamber design.~. pitch and yaw inertia at lor speed, using pilot enqine efficiency, etc evaluation on cockpit simulator A71-10820 A71-12684 EIEAUST UOZZLES FIGETEB AIBCBAR Plow field of two dimensional nozzle exhansting to navigator role in TACAU of reconnaissance and vacuum. describinq computer proqram based on BGK fighter aircraft, noting Weapon System Officer equation and plotting exhaust reqion density, functions temperature and velocity A71-10503 ~AIAA PAPER 69-6581 A71-10932 Bathematical model and digital simulation for EIPWIHERAL DESI6U nonlinear Characteristics of prototype Experimental design of three dimensional air inteqrated actuator package for fighter aircraft traffic control-radar tracking system control E71-10164 A71-11703 EIPLOSIOUS Swept ring fighter aircraft transonic buffet onset Aircraft crash investigation. deducing in-flight lift coefficient from camber and trailing edge explosion by failure analysis techniques deflection, considering design variations A71-10456 All-12679 Sonic boom and explosive shock wave effects on Bach 2 nirage nilan ground attack fighter, noting buildings and structural members lift aid moustache, low speed and steep approach 171-11035 handling from short airstrips A71- 12740 Fiqhter aircraft design with consideration to F armament, detection capability. thrust, speed. P-111 AIBCBAPT and load factor performance tradeoffs Conqressional hearinq on investigation of contract r AD-710497 1 1171-10183 for TPX aircraft PIER COUTBOL 171-11034 Navigator role in TACAI of reconnaissance and P-11 AIBCBAPT fiqhter aircraft, noting Weapon System Officer P-141 twin engine variable geometry carrier based functions jet fighter aircraft, discussing design, 171-10503 development program and manufacturing techniques FIBE PIGETIUG 171-12050 Soviet book on aircraft power plant systems and PABBICATIOU a^-IIC.LCSa --- coserinq iayout, enqine attachment. Pahricatisz techniques of compact fluidic control propellers, control, fuel and oil systems, fire equipment for aerospace enqines fiqhting. monitorinq, etc R71- 11654 &71-12722 FAILURE AUALTSIS FIBE PBITEUTIOR Aircraft crash investigation, deducinq in-flight Aircraft fire hazard reduction, discussing early explosion by failure analysis techniques detection, extinquishing equipment and emergency 171-10456 landing survival Aircraft multiwheel undercarriaqe effect on riqid 171-10399 and flexible pavements. examininq failure modes Fire protection tests in small fuselage mounted A7 1-12164 turbojet enqine and nacelle installation FAILURE EODES FAA-UA-70-411 7-7 - 1131 e Sailplane fatigue testing determininq load spectra FIRES c-LP~l ' safe structures and damage calculation Aircraft accident investigation of United Air A71-11949 Lines, Boeinq 727-22C near Los Anqeles, 18 Jan. PATISUE LIFE 1969 Ui base superalloys fatigue strenqth improvement (PB-190812] E71- 10914 for gas turbine engine components. discussinq FLAPS (COIITBOL SURFACES) homoqeneous deformation distribution, grain size Cambered and symmetric wing profiles and flap control, etc configurations, discussing wind tunnel tests at A71-10166 moderate Reynolds numbers Aircraft structure fatigue life improvement via A71-11950 material stress coining inside and around holes FLAT PLATES and slots Flutter analysis of plates with inplane boundary A71-10170 support flexibility exposed to transverse LABS flight control systems for turbulence induced pressure loading or buckled by uniform thermal fatigue damaqe reduction in E-52 and C-5A expansion aircraft, usinq mathematical models 171-10940 A71-11660 Boundary layer separation at free streamline Cumulative frequency distributions of aircraft attachment to sharp trailing edge of flat plate, landinq gear loads in determining fatigue life deducing terminal velocity profile for two [RAE-LIB-TRAlS-1462] 1171-10273 dimensional flow FATIGUE TESTIIG UACEIBES All-12376 Gas flame heater for heat resistant samples under Surface heat transfer rates measured on flat fatique tests, simulating gas turbine engine plates in hypervelocity shock tunnel operatinq conditions [RASA-CB-1692] 171-10867 A71-10041 FLEXIBLE BODIBS Aircraft structures fatigue testing device using LABS flight control systems for gust load proqrammed control of electrical inputs to alleviation and structnral mode stabilization on electrodynamic vibration stand. noting load large flexible aircraft, usinq aerodynamic cycle effects and damage accumulation surfaces A71-10409 A71 -1 1659 FATIGUE TESTS Flexible rotor balancing by exact point-speed Airplane materials mechanical properties influence coefficient method degradation due to fatigue. discussing breaking [NASA-CR-72774] n7i-ioo2i strain of A1 alloy FLEXIBLE SI165 A71-11395 Development and characteristics of control system Sailplane fatigue testing determininq load spectra for flexible rinqs fail safe structures and damage calculation [lASA-CASE-ILA-O6958] 1171-1 1038 A71-11949 PLIGH? AL?ITUDE Ban machine considerations in all-weather lor

A-15 PLIGKT CHARACTERISTICS SUBJECT INDEX

level naviqation system desiqn, notinq Fire protection tests in small fuselaqe mounted off-course error reduction by command turbojet engine and nacelle installation information display to pilot [ FAA-NA-70-411 871 -1 10 18 A71- 10515 FLIGHT SIMULATORS PLIGKT CHARACTERISTICS Fliqht simulators procurement and commissioninq, Aircraft flyinq qualities research proqram, discussinq difficulties due to different discussinq navy test pilot evaluations and aircraft configurations, advantaqes of equipment lonqitudinal handlinq characteristics for and procedures standardization, etc simulated carrier landinq task A71-10015 [AIAA PAPER 69-8973 A71-12678 FLIGKT STABILITY TESTS PLIGKT CONDITIONS Rapid hybrid frequency response method for Soviet book on meteoroloqical conditjons and aircraft fliqht flutter tesiing bise5 nn hybrid supersonic aircraft fliqht coverinq atmospheric computinq system composition and structure, temperature A71-10228 distribution, wind effects, etc PLIGHT TEST INSTRUMENTS -7. .1o,,n nr 0- ILY.." LAPIS fliaht demonstration, discussinq PLIGKT CONTROL instrumentation, flutter boundary and dgEZEiC LAnS fliqht control systems for qust load response, aerodynamic testinq and structural alleviation and structural mode stabilization on response to turbulence larqe flexible aircraft, usinq aerodynamic A71-11662 surfaces FLIGHT TEST VEHICLES A71- 11659 8-52 LAMS test vehicle structural modification and LAnS flioht control systems for turbulence induced instrumentation in flight phase fatique damaqe reduction in B-52 and C-511 A71-11661 aircraft, usinq mathematical models LAnS fliqht demonstration, discussinq A71-11660 instrumentation, flutter boundary and dynamic nodel performance index /Pi/ providinq criterion response, aerodynamic testinq and structural for approximatina one dynamic flight control response to turbulence system by another based on qeometrical A71-11662 representation of linear autonomous systems FLIGKT TESTS r AIAA PAPER 69-8853 k71-12682 Inertial naviqation system auqmented by dioital Fliqht control systems influence on military distance measurinq equipment in FAA fliqht aircraft desiqn and performance, discussinq inspection aircraft for performance evaluation static stability, ride quality, flutter marqin A71-10507 and maneuver load controls Aircraft turbine enqine development, considerinq rAIAA PAPER 69-7671 A71-12683 mismatch reduction between enqine and airframe Pilot evaluation of movable and riqid cockpit in fliqht tests control sticks A71-11180 r AD-7099341 N71-10184 E-52 LARS test vehicle structural modification and Pliqht control software packaqe for diqital fliqht instrumentation in fliqht phase control and landinq system of CH-46C helicopter A71-11661 r NASA-CR-1109051 N71-10283 Collision avoidance system fliqht test and Systems performance/desiqn requirements evaluation proqram for airline industry CAS specifications for CA-46C helicopter diqital specification fliqht control and landinq system A71-12896 TNASA-CR-1108891 N71-10294 FLIGHT TRAINIAG Systems analysis of fliqht control and quidance of Simulated low visibility landinq traininq, CH-46C helicopter discussinq airborne and ground based simulators TNASA-CR-1110241 N71-10297 A71-10022 Fliqht simulation for evaluatinq proposed PLIGKT VEHICLES stabilization system to ensure helicopter Soviet book on antenna radomes of fliqht vehicles hoverinq precision durinq carqo loadinq coverinq electromagnetic rave transmission TAD-7109481 N71-10564 throuqh dielectric media, fabrication, PLIGHT CREUS construction materials, etc Aircraft compartment qlare minimization for fliqht A71- 11322 crew visibility conditions and visual PLOW DEFLECTION performance improvement Plane supersonic overexpanded jet interactjon with A71-10028 obstacle, using hodoqraphs €or flow pattern FLIGKT INSTRUMENTS construction nan machine considerations in all-weather low A71-10425 level naviqation system desiqn, notinq Supersonic laminar boundary layer structure near off-course error reductian by command convex corners for larqe turniuq angles information display to oilot A71-10461 A71-10515 Soviet book on nonlinear conical qas flow theory PLIGKT PATAS coverinq flows with different characteristics missiles and aircraft trajectories computation past bodies of various geometries and positions time reduced via time sharinq and hybridization A71-12719 A71-11794 PLOW DISTRIBUTION PLIGET PLANS Plane supersonic overexpanded jet interaction with Northern Hemisphere temperature field atlas for obstacle, using hodographs for flow pattern SST fliqht planninq construction r AD-7120171 N71-11031 A71-10425 FLIGET SAPETY Plow field of two dimensional nozzle exhausting to Avionics system maximizinq pilot chances of vacuum, describinq computer proqram based on BGK survivinq mission and destroyinq selected target equation and plottinq exhaust reqion density, by removinq mental limitations temperature and velocity A71-10506 [AIAA PAPER 69-6581 A71-10932 ATC system improvement by procedural chanqes, Whitham supersonic flow theory application to mid- applyinq probability concepts to fliaht safety or near-field sonic boom of slender bodies in 171-11699 wind tunnel research PLIGHT SIlULATION A71-10956 Real time six deqrne of freedom aircraft fliqht Sweptback turboblades in parallel wall channel, diqital simulation usinq SL-1 continuous system investiqatinq thickness, camber and leading edqe simulation lanquaqe curvature effects on flow and pressure 1171-1 1786 distributions and vortex movement Leadinq edqe effect on aerodynamic characteristics A71-12606 of 70 deq swept delta winq Numerical analysis of flow field around thin AD- 7 12087 1 N71- 11007 airfoil in two dimensional nonuniform stream, usinq finite difference method

A-16 SUBJECT IUDEX FROST

A71 - 12680 171-11662 Weasurements of hypersonic, rarefied flow field of Flutter analysis on axial turbomachine blading disk [ AD-7107943 871-10562 [AD-710641] 1171-10461 Flutter analysis for thin liftinq surfaces by Recirculation reqiou of flow field caused by jet application of supersonic kernel function in around effect rith crossflow procedure [ AD-7 116651 871-10832 [ 8ASA-TB-D-6012] 871-10866 Three dimensional flow patterns obtained during FLY BY WIRE COHTPOL boundary layer separation on airfoils Aircraft flaps and ailerons actuators electronic [ 8PL-AERO-1309] 1171- 11014 fly by wire control as alternative to mechanical Servosystem design of high-response multislotted linkaaes for maneuverability and reliability in bypass valving system for supersonic inlets flight IASA-TB-D-6081] 87 1- 1106 1 1171-10825 Boundary layer transition studies of several WLDIUG STFtUCTWBS pointed bodies of revolution at supersonic Development and Characteristics of variable sweep sweds wing control system for supersonic aircraft [ AASA-TU-D-6063] 1171-1 1520 [ RASA-CASE-ILA-03659] 1171 -1 1041 FLOW EQUATIOHS FORCE DISTEIBUTIOU Flow field of two dimensional nozzle exhausting to Oscillating flow effects on pressure force normal vacuum, describing computer program based on BGK to symmetrical airfoil chord equation and plottinq exhaust region density, r AD-7118301 n7i-iioii temperature and velocity FORECAST116 [AIAA PAPER 69-6581 A71- 10932 Porecastinq passenqer travel demands PLOW RBSISTAUCE f PB-1924551 871-10299 Low resistance nozzles for complete power FO11GIaG compensation in rate of climb indicators Righ velocity metal workinq, discnssing airfoil A71-10350 forging. ausforging of bearing race blanks. Circular pipe oas laminar flow at constant wall toolinq. etc temperature, determining heat exchange and drag r snE PAPER np-70-2281 171-11267 by motion and energy equations integration in FORIIIIIG TECEIIIQUES boundary layer approximations Peen forming of large complex parts from sheet and 171-12192 plate, illustrating dihedral break in airplane FLOW TBEORT vinq skin unsteady flow theory, describing milestone A71-11550 experiments in aerodynamics FOUUDRIES 171-10266 Poundarv precision in aomain of aeronautical Whitham supersonic flov theory application to -id- turbines or near-field sonic honm of slenr?er 5die i~ Nii-iibjs wind tunnel research FRACTURE EECEAIIICS A71-10956 Al-Zn-8g-Cu type high strength 81 alloys Fredholm method for reversible transonic flow in mechanical properties evaluation by fracture computing aircraft wing and turbomachine or mechanics methods helicopter blade airfoils for compressibility 1171-11540 law FREE FLIGBT 171-11022 Critique of Chapman-Kirk iterative method for Soviet book on nonlinear conical qas flow theory differential equations yieldino aerodynamic coverinq flows with different characteristics coefficients from free flight data past bodies of various geometries and positions 471-10971 A71-12719 FREE FLIGET TEST APPARATUS PLOW P’PLOCITT Yree tiiqht measurements of aerodynamic lateral Two dimensional wake laminar-turbulent transition force and moment coefficients using gyroscopes by sinqle and double frequency sounds imposition and accelerometers and uind tunnel natural disturbance, inducinq [ ESA-T8-1641 A71-11001 velocity fluctuations FREE EOLECULAR FLOW 171-10132 Spheres draa coefficient at hypersonic nach Plane linear cascades of thin curved profiles, numbers for near free molecular flow obtaining potential flow velocities and liftinq a71-10969 force on leading edge PREICR SPACE PROGRABS 1171-10339 Project DIoscURES for global sea and air traffic Circular cone with cross shaped wings in control usinq synchronous satellites for supersonic flow, determining flow qround-air-ground communications characteristics, velocities and pressure 1171-11768 A71-11958 Policies for participation of French aerospace FLOW VISUALIZATIOII industry in space programs Transonic flow through planar cylinder lattices, 1171-12069 discussinq flow pattern visualization and PREQUEIICT RBSPOUSE recording techniques by high speed camera Rapid hybrid frequency response method for A71-10108 aircraft fliaht flutter testinq based on hybrid FLUIDICS computinq system Fabrication techniques of compact fluidic control A71-10228 equipment for aerospace enqines FRBQUEUCI STUCEROIIIZATIOI 171-1 1654 ATA Collision Avoidance system based on time and FLUTTER AIALTSIS freauencv svnchronization via around stations or Rapid hybrid frequency response method for other aigcraft aircraft flight flutter testinq based on hybrid 171-12895 computinq system FRICTIOU DRAG A71-10228 neat transfer and friction draq calculation for Critical flutter of wing with riqid aileron turbulent boundary layer of aas with temperature studied by analog computer modeling dependent physical properties A71-10606 A71 - 11884 Flutter analysis of plates with inplane boundary FBICTIOtl PACTOR support flexibility exposed to transverse Test time and contact stresses effect on jet fuels pressure loading or buckled by uniform thermal antiwear properties under rolling friction expansion A71-12570 871-10940 FROST LA115 flight demonstration. discussinq Low speed aerodynanic characteristics of airfoil instrumentation, flutter boundary and dynamic profiles includinq effects of upper surface response, aerodynamic testinq and structural roughness simulatinq hoar frost response to turbulence [ WPL-AERO-1308 1 1171-11016

A-17 FUEL CORROSIOII SUBJECT IIDEX

FUEL CORROSION claddings on TD-NiCr nicrobioloqical fuel corrosion by bacteria and [ NASA-Tn-X-52916] 171-1 1426 funqi in fuel tanks Sealing dam analysis for design of shaft face seal [ AD-712103 J N71-11848 with self-actinq lift ausmentation for advanced FUEL IBJECTION qas turbine engines Internal mixinq scheme for continuous fuel I NASA-T1-D-70061 171-1 1579 injection in Wankel enqine via swirl nozzle Desiqn and performance of qas-film and oil-film durinq intake-compression cycle lubricated self sealing mainshaft seals for gas A71-12559 turbine engines ?DEL TA1K.5 [ NASA-CR-727371 N71-12035 Drop i-p-ct tests fnr ilprnvinq GAS TURBIIIES crashworthiness of inteqral fuel tanks Small gas turbines for aircraft auxiilary power r PAA-NA-70-U61 N7l-11019 unit, considering compressor and combustor FUEL TESTS design, noise, fuel consumption and specific Test time and contact stresses effect on jet fuels weiqht problems anriwear p~opa~iia~cinder ro:ling friztia:: 1171-10751 A71- 12570 Rotor loss coefficients for prediction of radial Nuclear maqnetic resonance method of determininq gas turbine performance usinq one dinensional aromaticity of hydrocarbon fuels analysis TAD-7118921 171-11890 A71-11016 FUNGI GENERAL AVIATIOI AIRCRAFT Microbioloqical fuel corrosion by bacteria and FAA statistical handbook of aviation 1958-1968 fungi in fuel tanks 171-10372 [ AD-7121031 171-11848 GLAIDS (SEALS) sealinq dan analysis for design of shaft face seal with self-actinq lift auqmentation for advanced G gas turbine engines GAlE TREORI [ NASA-TN-D-7006 1 171-11579 Differential game theory applied to GLARE pursuit-evasion problems of two jet aircraft Aircraft compartment glare minimization for fliqht [AD-7110551 1171-10328 crew visibility conditions and visual GAS FLOW performance improvement Heat transfer and friction draq calculation for 871-10028 turbulent boundary layer of gas with temperature GLIDERS dependent physical properties Sailplane fatigue testing determiuinq load spectra A71-11884 fail safe structures and damage calculation Circular pipe qas laminar flow at constant wall 171-1 1949 temperature, determining heat exchanqe and drag GOIIDOLAS by motion and enerqy equations inteqration in Thermal coatinqs of gondola payloads boundary layer approxinations INYO- 3747- 121 N71-10496 A71-12192 GOAIOf!ETEP.S Soviet book on nonlinear conical gas flow theory Laser qyro goniometry for fluctuations and angular coverinq flows with different characteristics measurements at low rotational velocities, Past bodies of various qeometries and positions notinq countup/countdown detection systems 1171-12719 A71-12924 GAS JETS GRAPES (CHARTS) Electric and maqnetic cross field effects on Wind tunnel investiqation of jet transport aerodynamics and thermal regime of qas flame airplane confiquration with hiqh thrust-weiqht cone ratio and external flow jet flap - qraphs [ AD-7123361 N71-12075 [ NASA-TN-D-60581 N71-10495 GAS LUBRICAUTS GRAVELS Desiqn and performance of gas-film and oil-film Influence of qravel depth and tire inflation lubricated self sealing mainshaft seals for qas pressure on soft-ground arresting of civil turbine enqines aircraft [ NASA-CR-72737 1 A7 1-1 2035 r RAE-TR-69001 1 N71-110110 Desiqn of self-acting gas-film seal for turboshaft GROUND BASED COIITROL of qas turbine enqine Steep approach to landinq for jet transport 171- 12036 aircraft noise abatement, usinq qround based Computerized sealinq dam design analysis for qas equipment and onboard TV display film seal of turboshaft A71-11311 N71-12039 GROUND EFFECT GAS TURBIIE EIGIlES Recirculation region of flow field caused by jet Ni base superalloys fatique strength improvement in qround effect with crossflow for qas turbine enqine components, discussinq [ AD-71 1665] N71-10832 homoqeneous deformation distribution, qrain size GROUID EFFECT BACHIAES control, etc Forward horizontal speed influence on aerodynamic 171-10166 characteristics of air cushion vehicle with Computerized analysis of seal temperature, elastic circular nozzles and cvlindricallr or conically displacements and seal force balance in shaped curtains iterative design method for qas turbine A71-12551 mainshaft seals Investigating hiqh speed qround transportation A71-10479 systems based on tracked air cushion vehicles Gas turbines air pollution control, discussinq r~~-i909391 1171-11033 exhaust composition, combustion chamber desiqn, Hovering type flyinq vehicle desiqn and principle enqine efficiency, etc mechanisms for manned or unmanned use A71-10820 INASA-CASE-MSC-12111-11 N71-11039 Tubular qas turbine enqjne combustor desiqn by GROU1D-AIR-GR001D COMIONICATIOIS combininq turbulent flame speed, microvolume Project Dioscures for global sea and air traffic burnina and stirred reactor models control usina.~ svnchronous satellites for 171-12852 qround-air-qround communications Niobium alloys for qas turbine blades, exanininq N71-11768 working temperatures, protective coatinqs and GROUT ductility Cement and asphaltic materials evaluation for use A71 - 12939 as qrout under landinq mats Aircraft qas turbine enqine desiqn and r AO-7109621 N71-10681 construction GUIDANCE (noTron) r ~~-7117571 N71-10853 Aoverinq type flyinq vehicle desiqn and principle Nach 1 burner riq tests at 2100 F for oxidation mechanisms for manned or unmanned use resistance evaluation of NiCrAl and FeCrblY r NASA-CASE-MSC-12111-1 1 N71-11039

A-18 SUBJECT IIDEX BUIIAl FACTORS E1GIUEBRIUG

GUIDE VAIES mixed fixed and rotarv sins terminal Guide vanes small aspect ratio effect on hiqh environments pressure stages of axial flow compressors A71-12892 171-12558 Derelopmeut study for TPR heliport standard GUST ALLBVIATORS lighting syste8 LAIS fliqht control systems for qust load AD-710982 J 1171-10682 alleviation and structural mode stabilization on Delayed bubble movement on airfoil during large flexible aircraft. using aerodynamic helicopter stall surfaces [ AD-7115401 171-11005 A71-11659 EIGE SPEED GUST LOADS Eigh velocity metal working, discussing airfoil

Aircraft response to atmospheric gust. discUSSing foraina.~ ._ ausforaina ~- of bearina race blanks. spectral analysis procedures and calculation tooling, etc results on T-tail aircraft design [ S(IE PAPER l!F-70-228] A71 - 11267 A71-10752 8168 STRElGTE GYRO EORIXOlS Eigh strength polyimide resin composites, Laser gyro goniometry for fluctuations and angular discussinq commerical and aerospace measurements at low rotational velocities. applications. chemistry, roid content, rolatiles noting countup/countdown aetection systems and moisture absorption A71-12924 A71-12487 GYROSCOPES EIGE STRElGTE ALLOTS Free fliqht measurements of aerodynamic lateral Al-Zn-ng-Cu type high strength A1 alloys force and moment coefficients using gyroscopes mechanical properties evaluation by fracture and accelerometers mechanics methods I HSA-TN-l64] 171-11001 171-11540 EIGE TEIIPERATURS EUVIROlIIElTS Engine vibration high temperature transducer, H discussing piezoelectric materials properties EALIDES and desiqn considerations relatire to Ti alloy hot salt stress corrosion under simulated temperature, pressure, acoustic noise, humidity engine environmental conditions, presenting environment threshold data based on residual tensile A71-12911 ductility EIGE TElPERATURB TESTS 1171-12885 Mach 1 burner rig tests at 2100 F for oxidation EARIOlIC OSCILLATIOl resistance evaluation of 1iCrAl and FeCrAlT Three dimensional wings harmonic oscillation with claddings on TD-HiCr arbitrary frequency in subsonic flow. presenting [ NASA-TI-1-529161 1171-11426 approximation method for singular integral HISTORIES equat ion ELCL/?IASA r~ttatiiigsiag hiLCraft research history A71-10844 durina 1955-1970 period. discussinq wind tunnel BEAT RESISTAFF ALLOTS research ni base superalloys fatigue strength improvement A71 - 11 377 for gas turbine engine components, discussinq EODOSRAPHS homogeneous deformation distribution, grain size Plane supersonic overexpanded let interaction with control. etc obstacle, using hodographs for flow pattern A71-10166 construction BEAT TRAISPXR A71-10425 Circular pipe qas laminar flow at constant wall EOLOGRAPET temperature. determining heat exchange and drag Holographic interferometry for study of by motion and energy equations integration in transparent media boundarv layer 3pprorimations [ TP-8511 171-10407 A7 1- 12192 Retrodiffusion interferometric holography in wind Surface heat transfer rates measured on flat tunnels inclnainq displacement and deformation Plates in hypervelocity shock tunnel of deflectors [ NASA-CR-16923 171-10867 I OUERA-TP-852 1 871-1’1510 EEATIUG EQUIPIEllT EORIZOUTAL FLIGET Gas flame heater for heat resistant samples under Forward horizontal speed influence on aerodynamic fatique tests, simulating qas turbine engine characteristics of air cushion vehicle with operating conditions circular nozzles and crlindrically or conically A71-10041 shaped curtains HELICOPTER DES161 A71-12551 HACA/HASA rotating wing aircraft research history EORIZOUTAL TAIL SURFACES durinq 1955-1970 period, discussing wind tunnel Development and characteristics of translating research horizontal tail assembly for supersonic aircraft A71- 11377 [ lASA-CASE-XLA-08801-1] 171-1 1043 Carbon fiber reinforced epoxy composites. EOVBRIUG eraluatinq application as helicopter tail rotor Blade root cutout effects on hover performance of blade material helicoptor rotors with rotor thrust and torque A71- 12477 characteristics and wake pattern analysis E!ZLICOPTEP PERIORIIAUCE IAD-7113961 171-11030 Blade root cutout effects on hover performance of Eovering type flyinq vehicle desiqn and principle helicoptor rotors with rotor thrust and torque mechanisms for manned or unmanned use Characteristics and wake pattern analysis [XASA-CASE-ISC-12111-1] 171-1 1039 [ AD-7113961 1171-11030 EOVERI16 STABILITY HELICOPTER UAKIS Aircraft ultrasonic altitude and vertical velocity aethod for calculating helicopter vortex paths and sensor for low fliabt, discussing VTOL aircraft wake velocities automatic hoverinq control and time lag [ AD-710694 7 1171-10470 A71-11624 Blade root cutout effects on hover performance of EUMAl FACTORS ElGIlEBRIlG helicoptor rotors with rotor thrust and torque Role of man in navigation - Conference, Colorado characteristics and wake pattern analysis Springs, July 1970 [AD-711396] 1171-1 1030 A71-10501 EILICOPTEIIS Man role in future navigation from SAC viewpoint. Do-132 light five seat tip drive turbine considering relationships to mission and machine helicopter. discussing applications, fliqht A71-10502 testing, design and major components naiiqator role in nilitary Airlift Command /(IAC/ ~71-10465 as navigator, weather analyst, fuel manager and Helicopter operations integration into civil air fliqht planner traffic system, notinq special requirements for A71-10504

A-19 BUMAN PERFORMANCE SUBJECT INDEX

Electronic control indicator for human pilot BYPERSONIC SPEED capability enhancement usinq color coded cathode Unsymmetrical nose bluntness effect on stability r3y display, presentinq information from seven derivatives of slender cone at Hach 14 different instruments I AD-7 119211 N71-11008 A71-10750 AYPERSONIC WAKES AUMAN PERFORMANCE Laminar near wake characteristics behind circular Aircraft compartment qlare minimization for fliqht cylinder in Mach 6 rarefied air stream crew visibility conditions and visual CREPT-1108/70 J N71-11012 performance improvement AYPERVELOCITY UIND TUNNELS A71-10028 Axisymmetric hypersonic wind tunnel nozzle desiqn AUMAN REACTIONS by deter~iningiz.riscid contnnr and correctinq Human subjective responses to approachinq and for turbulent boundary layer growth recedinq aircraft sounds durinq fliaht over rAIAA PAPER 69-3371 A71-11578 stationary observer Surface heat transfer rates measured on flat A71-10345 plates in hypervelocity shock tunnel Air and land transportation noise sources and I NASA-Ln-i692 j n7i-in~h7 measurement, noise level scales, and individual and community responses - conference r pB-1 91 117 1 N71-10349 I Community physical. psycholoaical. and social ICE FORMATION reactions to aircraft noise around 7 us Douglas DC 9 aircraft crash durina takeoff caused international airports by ice formation on airfoils TNASA-CR-1113161 N71-11032 NTSB-ARR-70-20 J N71-10815 BYBRID COMPUTERS nicrowave radiometry for snow and ice sensinq in Missiles and aircraft trajectories computation aerial reconnaissance time reduced via time sharinq and hybridization N71-11160 A71-11794 ICE PREVENTION AYDRAULIC CONTROL Biblioqraphy on control and prevention of icing in Electrohydraulic thrust control system for transportation systems supersonic transport aircraft enqines, r AD-71 1534 ] A71 - 10735 considerinq reliability, performance and weiqht ILLUMIRATION rSAE PAPER 7008191 A71-11546 Aircraft emergency evacuation illumination KYDRAULIC FLUIDS standards, considerinq independent power source, Soviet book on aviation fuels, lubrication crash survivable installation, operation materials and special fluids coverinq initiation and exit vlsibility compositions, physicochemical properties, A71-10030 filtration, etc IMPACT TESTS 171-11320 Drop and impact tests for ilnprovinq AYDROCARBON FUELS crashworthiness of integral fuel tanks Turbciet enqine desiqn for methane element of [ FAA-NA-70-461 N71-11019 lisuifiea natural qas as aircraft fuel, INCOMPRESSIBLE FLOP discussinq supersonic transport applications Separation point study of incompressible laminar 3171-10485 boundary layers around parabolic bodies at anqle Performance of reducinq electrode for neutralizinq of attack electrically charqed hydrocarbon fuel flow r AD-7120841 N71-11519 r AD-7123681 N71-11876 INERTIAL NAVIGATION Nuclear maqnetic resonance method of determininq Inertial naviqation system auqmented by digital aromaticity of hydrocarbon fuels distance measurinq equipment in FAA fliqht r AD-7 11892 1 N71-11890 inspection aircraft for performance evaluation AYPERSONIC AIRCRAFT A71-10507 Hypersonic conventional and rocket transport Airborne inertial and area naviqation systems aircraft, discussinq costs and air and noise performance requirements proposed for 0. S. pollution domestic airspace, includinq projection throuqh rAIAA PAPER 70-12181 A71-11302 1995 AYPERSONIC BOUNDARY LAYER A71-10508 Three dimensional attached compressible laminar Airline experience with dual inertial systems as boundary layer on slender cones in hypersonic sole means of navigation, considerinq equipment fliqht at hiqh angles of attack derived by reliability, cockpit desiqn, traininq, etc numerical inteqration A71-10509 A71-10926 IUFLATABLE STRUCTURES AYPEESORIC PLIGAT Inflatable restraint collar for large balloons Statics and aerodynamics of liftiuq decelerators with heavy loads usinq winch driven cable harawinqs and sailvings/ at supersonic and launchinq hypersonic speeds A71-11821 rAIAA PAPER 68-9451 1171-10927 INJURIES BYPERSONIC PLOP Summary and statistical analysis of aircraft Spheres dras coefficient at hypersonic Mach accidents numbers for near free molecular flow r NTSB-AAS-70-11 A71-10674 A71-10969 INLET FLOW Measurements of hypersonic, rarefied flow field of Enqine/compressor test inlet flow field disk~~~ simulation, considerinq ramp anqle, screen [AD-7106411 1171-10461 location and diffuser lenqth effects Surface heat transfer rates measured on flat 171- 12909 plates in hypervelocity shock tunnel IHLET PRESSURB [NASA-CR-16921 N71-10867 Pitot type intake inlet additive draq in terns of Laminar boundary layer effect on dynamic viscous capture area ratio, static and total pressure pressure interaction in hypersonic flow coefficients 1 LR-5351 N71-11003 A71-12688 BYPERSONIC GLIDERS IHSTRUMERT APPROACA Nb alloys in hypersonic qlider fabrication, Jet aircraft crash during instrument approach due discussinq mechanical properties, oxidation to electrical systems failure resistance and sandwich panel desiqn TNTSB-AIR-70-221 N71-10812 A71-12935 Lear let crash durinq instrument approach due to BIPERSONIC EBENTRI descent below path profile snacecraft reentry aerodynamics reqardinq [ NTSB-AAR-70-213 N71-10813 hypersonic hiqh altitude liftinq bodies, shock IHSTRUIEHT COIPENSATIOR wave and flow field, heat, mass and enerqy Low resistance nozzles for complete power transfer, etc compensation in rate of climb indicators rICAS PAPEIi 70-011 1171-11686 A71-10350

A-20 SUBJECT IIDEX LAEIUAR BOUUDARY LAYER

IUSTBUIEm PLIGUT RULES Differential game theory applied to naximnm throughput-rate capacity for runway and pursnit-evasion problems of two jet aircraft final approach path airspace involving multiple [AD-711055] 871-10328 IF3 landings Jet aircraft crash during instru8ent approach due A71-12893 to electrical systems failure Application of IPR with unpowered, low lift drag [ ATSB-AAR-70-221 11-11-10812 ratio landing approaches Lear jet crash during instrument approach due to t17i-ioiio descent below path profile IISTBUUEUT LAUDIUG STSTEIS [ llTSB-AAR-70-21] A71- 10813 Application of IPR with unpomered, low lift drag JET AIRCRAFT UOISE ratio landing approaches Sonic aircraft boom propagation analysis for N71-10110 horizontal flight in unperturbed atmosphere Program effectiveness and facility criteria for mi-11036 ILS investment decisions JET SI6IUE FUELS 1171-10355 Test time and contact stresses effect on jet fuels Evaluation of systems, procednres, and antiwear properties under rolling friction instrumentation for air traffic control A71-12570 [ AD-7116621 171-10737 Performance of reducing electrode for neutralizing IUTEGBAL EQUATIOIS electrically charged hydrocarbon fuel flow Lifting surface in unsteady subsonic flow. r AD-7123681 n7i-11876 describinq inteqral equation calculation method JET EUGIAES including kernel logarithmic singularity Jet engine evolution, considering thrust, A71-11020 combustion chamber, fans, hiqh-pressure-ratio IUTEBFEBEICE DE16 compressors and turbine inlet temperature wind tunnel study of aerodynamic interference drag A71-11181 caused by fan jet engine wake of supersonic Electrochemical machining role iu jet engine transport industry, discussinq drillinq, contouring. [ AASA-TA-D-6067 3 871-11004 electrolyte handlinq, etc IETEBFEBEICE LIFT [ SNE PAPER RH-70-1931 1171-11253 WDWaSh interference on two dimensional jet flap nanufacturing technology and production wing in slotted wall tunnel, usinq small engineering methods in aerospace industry disturbance theory ~71-11627 A71-12690 JET EXBAUST IUTEBFEROIETRT Two dimensional analysis on jet exhaust into Aolographic interferometry for study of crosswind with miring flow interference transparent media [ AD-7115781 1171-1 1006 CTP-8511 ~71-10407 JET FLAPS Retrodiffusion interferometric holography in wind Opwash interference on two dimensional jet flap tunnels including displacement and deformation wing in slotted wall tunnel, usinq small of deflectors disturbance theory [OAEBA-TP-852] 871-11510 1171-12690 IITERUATIOBAL COOPEHATIOII JET FLOW Project DIOSCURES for global sea and air traffic Supersonic overexpanded jet flow past cone, control using synchronous satellites for determininq impinqeneut point by method of ground-air-qround communications characteristics 1171-1 1768 1171-10613 IIVISCID FLOW JET IIPI8GEBEUT Wing-body interference in supersonic inviscid Plane supersonic overexpanded jet interaction with flow. extendins Stewartson approach to arbitrarv nhstacle, “,sin< Bolioyraphs for flow pattern smoo+h -r)nvez cylinder construction A71-10774 A71-10425 Inviscid ideally conducting fluid flow past thin Supersonic overexpanded jet flow past cone, foil in transverse magnetic field, usinq small determining impingement point by method of Parameter method characteristics A71-12629 1171-10613 IOUOSPHERIC PBOPAGATIOA Recirculation reqiou of flow field caused by jet Research and development of solid state and in qround effect with crossflow electronic equipment, microwave circuits, [AD-7116651 171-10832 semiconductors, and ionospheric radar JET LIFT n71- 1 o 126 wind tunnel investigation of jet transport IROI ALLOYS airplane configuration with high thrust-weight nach 1 burner rig tests at 2100 F for oxidation ratio and external flow jet flap - graphs resistance evaluation of AiCrAl and PeCrAlT [NASA-TN-D-60581 N71-10495 claddings on TD-AiCr JET UIXIBG FLOW r RASA-TB-X-529161 1371-iiw6 Two dimensional analysis on jet exhanst into ISOTROPIC TURBULEECE crosswind with mixinq flow interference Aerodynamic theory of pressnre field induced on r AD-7115781 1171-1 1006 lifting surface by isotropic atmospheric JET BOZZLES turbulence, considering transfer function of nozzle lateral spacing effect on drag and Concorde aircraft performance of twin jet afterbody configurations [ICAS PAPER 70-303 171-11019 with converqent nozzles at Nach 0.6 to 2.2 ITERATIVE SOLUTIO1 [ NASA-T8-X-20991 vi-10276 Critique of Chapman-Kirk iterative method for JETTISOI STSTEIS differential equations yielding aerodynamic Requirements for ejection seat systems coefficients from free flight data RAP-LIB-TRANS-1471 1 N71-11042 1171-10971 K J KERUEL FUUCTIOIS JET AIRCRAFT Plntter analysis for thin liftinu surfaces by German monograph on commercial jet aircraft application of supersonic kernel function maintenance systems covering changes and procedure adaptations for performance improvement [NASA-TN-D-6012] 1171-10866 A71-10114 Steep approach to landinq for jet transport aircraft noise abatement. usinq qround based L equipment and onboard TV display LAIIYAB BOUUDABT LATER A71-11311 Supersonic laminar boundary layer structure near convex corners for larue turninq ar?nles

A-21 LAIINAR FLOP SUBJECT IUDEI

A71-10461 LEADIUG EDGES Three dimensional attached compressible laminar Plane linear cascades of thin curved profiles, boundary layer on slender cones in hypersonic obtaining potential flow velocities and liftinq fliqht at hiqh angles of attack derived by force on leading edge numerical integration A71-1 0339 A71-10926 Poliymidefioron reinforced plastic structures Minimum suction rate preventinq laminar boundary fabrication, discussing use in leading edgesA71-11263 layer separation from cnrvilinear porous surface [ SIE PAPER Ell-70-133 3 in jet flow Thin delta wing with leading edge separation, A71-12553 obtaining drag lift and rollinq moment Two dimensional axisymietric laminar boundary coeiiicisnts 2nd pr-qsure distribution layer on blown wing and body of revolution, A71-1.2908 usinq sixth-order polynomial for velocity Leading edqe effect on aerodynamic characteristics distribution of 70 deg swept delta wing 171-12554 [ AD-7120871 1171-1 1007 Laminar-turbulent boundary layer transition point L EA K A G E on winq, usinq hot-wire anemometer and Drop and impact tests for improvinq oscilloscope crashworthiness of inteqral fuel tanks A71-12555 [ PAA-NA-10-46J 1371-11019 Laminar boundary layer effect on dynamic viscous LEGAL LIABILITY pressure interaction in hvpersonic flow Airline liability and insurance in relation to [ 18-535 1 N7 1- 1 1003 aircraft hijacking, sabotage, etc computerized calculations of adiabatic laminar 171-10359 boundary layer and shock wave interactions usinq LIFT Klineherg method Plane linear cascades of thin curved profiles, [ VKI-TN-60 1 N71-11017 obtaininq potential €low velocities and liftinq Separation point study of incompressible laminar force on leading edqe boundary layers around parabolic bodies at angle A71-10339 of attack Lifting surface in unsteady subsonic flow, [ AD-712084 1 N71-11519 describinq integral equation calculation method LANINAR FLOW including kernel logarithmic sinqularity circular pipe qas laminar flow at constant wall A71-11020 temperature, determining heat exchange and draq Swept vinq fighter aircraft transonic buffet onset by motion and energy equations inteqration in lift coefficient from camber and trailing edge boundary layer approximations deflection, considering desiqn variations 171-12192 A71-12679 Boundary layer separation at free streamline LIFT AUGNENTATION attachment to sharp trailinq edqe of flat plate, Sealing dam analysis for design of shaft face seal deducinq terbinal velocity profile for two with self-actinq lift augmentation for advanced dimensional flow gas turbine enqines A71-12376 TNASA-TN-D-70061 N71- 11579 Aeat transfer in base type supersonic laminar and LIFT DETICES transitional separated flows Aerodynabic theory of pressure field induced on r AD-710347) N71- 10249 liftinq surface by isotropic atmospheric LAMINAR VAKES turbulence, considering transfer function of Two dimensional wake laminar-turbulent transition Concorde aircraft by sinqle and double frequency sounds imposition [ICAS PAPER 70-301 A71- 11019 and wind tunnel natural disturbance, inducing Hiqh lift systems for four-engine Mach 0.8 velocity fluctuations turbofan STOL aircraft, discussing propulsion, A71-10132 aerodynamics and design trends Laminar near wake characteristics behind circular [SAE PAPER 7008111 A71- 11545 cylinder in Mach 6 rarefied air stream Bibliography of documents containinq numerical [ REPT-1108/70 1 N71-11012 data on planar liftinq surfaces LANDING GEAR AGARD-R-574-70 J N71-10339 Transport aircraft tire pressure and multiwheeled LIFTING BODIES landinq qear limitations reqardinq pavement Bibliography of documents containinq numerical desiqn data on planar lifting surfaces A71-12163 [ AGARD-R-574-70] N71-10339 Cumulative frequency distributions of aircraft Linear theoretical method for arbitrary wing landinq qear loads in determining fatique life planform and trailing edge contLo1 surfaces in rRAE-LIB-TRANS-1462] N71-10273 low frequency oscillatory motion in subsonic LANDING LOADS flow N71-11013 Analysis of stresses and deflections in platforms I NPL-AERO-1303 I used for airdrop operations LIFTING REENTRY VEHICLES [ AD-71 15561 N71-11968 spacecraft reentry aerodynamics regarding LANDING SIIULATION hypersonic hiqh altitude liftinq bodies, shock Simulated low visibility landinq training, wave and flow field, heat, mass and energy discussinq airborne and qround based simulators transfer, etc A71-10022 rIcas PAPER 70-011 A71-11686 Aircraft flyinq qualities research proqram, LIGHT AIRCRAFT discussinq navy test pilot evaluations and Air cooled opposed 4, 6 and 8 cylinder light lonqitudinal handlinq characteristics for aircraft engines with or without simulated carrier landinq task turbosupercharginq, considerinq horsepower lAIkA PAPER 69-8971 A71-12678 improvement and torsional vibration control LASER OUTPUTS lSAE PAPER 7002051 A71-10129 Laser qvro qoniometry for fluctuations and anqular Short haul air transportation technological measurements at low rotational velocities, factors for VTOL, STOL, CTOL and liqht aircraft, notinq countup/countdown detection systems considering operatinq costs, passenqer service A71-12924 and environment impact LASERS [AIAI PAPER 70-12871 1171-1 1700 Coherent laser synthetic aperture radar at LIGETNING microwave frequencies for airborne qround point Liqhtninq induced voltaqes in aircraft electrical tarqet mappinq circuits A71-12044 I NASA-TH-X-52906 1 N71-10391 LATTICES LIUEAR FILTERS Transonic flow throuqh planar cylinder lattices, Stochastic model for analysis of track-while-scan discussinq flow pattern visualization and technique for aircraft search radar, based on recordinq techniques by hiqh speed camera Kalman filter theory A71-10108 A71-11393

A-22 SUBJECT IIDEX VBCHAIIICAL PROPERTIES

LIQUEFIED GASES 1AIAGEUEIT PLAIIIIG Turbolet enqine design for methane element Of Systems approach to accident investigation in lignified natural gas as aircraft fuel, civil aviation and homes discussing supersonic transport applications 171-10115 A71-10485 Calibration and preliminary analysis of passenger LIQUID COOLIBG demand and modal split models for Northeast Coolinq water system for comoressor of supersonic Corridor of United States wind tunnel [ PB-1909461 n7i- 11021 r AD-710971 1 171-10679 NAIUAL COBTROL LOADS (FORCES) Aircraft manual flight control analysis using sailplane fatigue testing determining load spectra continuous mathematical pilot model for closed fail safe structures and damage calculation loop digital simulation A71-11949 A71-11787 LOSGEROIS I AIUFACTURIIG Optimal cross sectional dimensions of thin walled manufacturing teChnOlOgy and production lonqeron beams and ribs of skin reinforced delta engineering methods in aerospace industry wings minimizinq weight ~71-11627 171-12562 Uanufacturing and advancement technology for LOIGITUDIlAL COmROL turbine engine coatings Aircraft flying qualities research proqram. 171- 11635 discussinq navy test pilot evaluations and UARKBTIIG lonsitudinal handling characteristics for concorde role in air traffic market, discussing simulated carrier landinq task operatinq costs and profit potential I AIAA PAPER 69-8971 1171-12678 1171-12746 LOW ALTITUDE U A P 1L A ID Scale lengths in atmospheric turbulence from Air carrier demand €or slots particularly in area spectra and autocorrelation of vertical air of Washington-Baltimore velocity component measured in low flying [ PB-1933501 171-10347 aircraft IATERIALS TESTS A71-10859 Airplane materials mechanical properties LOW ASPECT RATIO degradation due to fatigue. discussinq breaking measuring characteristics of low Each number flow strain of A1 alloy of air from two planar nozzles with aspect ratio 171-1 1395 of 3 at exit Al-Zn-Sg-Co type high strength A1 alloys (AD-7113131 171-11139 mechanical properties evaluation by fracture LOW SPElD STABILITT mechanics methods C-5 military transport stability augmentation for A71-11540 oitch snd ?ax inertia at iow sped, usinq pilot UATIiE11ATICAL IODIIIS evaluation on cockpit simulator Commercial transport aircraft maintenance A71-12684 simulation vonte Carlo nodeling techniques, LOW SPEED BIID TUIlELS considering application to airline operations Low-speed wind tunnel tests of series of twin-keel [SAE PAPER 7003451 A71-10128 all-flexible parawinqs ATC communication environment simlation via [ NASA-TU-D-5936 1 171-10052 mathematical model based on ATC statistics LOW VISIBILITY A71-10979 simulated low risibility lanaing training, Stochastic model for analysis of track-while-scan discussing airborne and ground based simulators technique for aircraft search radar, based on 171-10022 Kalman filter theory LUBRICAIITS A71-11393 Soviet book on aviation fuels, lubrication mathematical model and digital simulation for materials ana special fluids covering nonlinear characteristics of prototype compositions, physicochemical properties, integrated actuator package for fighter aircraft filtration, etc control 171-11320 171-11783 LUBRICATI1G OILS Aircraft manual flight control analysis using Desiqn and performance of gas-film and oil-film continuous mathematical pilot model for closed lubricated self sealing sainshaft seals for gas loop digital simulation turbine engines A71-11787 [ IASA-CR-72737 ’] 1171-12035 Psendoshock mechanism model. erplainiug supersonic diffnser main flos static pressure increase and decrease alternately and wall increase M monotonously UAGIETIC FIELDS 1171-11870 Electric and magnetic cross field effects on Blaae bound vortex system mathematical model for aerodynamics and thermal regime of gas flame optimum heavily loaded ducted fans, including cone thrust, power and efficiency design paraseters I AD-7 12336 1 1171-12075 171-12677 8AGBETOHTDRODT~Al!ICFLOW node1 performance index /Pi/ providing criterion Inviscid ideally condncting fluid flow past thin for approrimatinq one dynamic flight control foil in transverse magnetic field, using small system by another based on geometrical parameter method representation of linear autonomous systems A71-12629 [AIAA PAPER 69-8851 A71-12682 ILIITEIASCE Tubular gas tnrbine engine combustor design by Systems maintenance program evalnation of Eastern combining turbulent flame speed, microvolume Region air transportation facilities burning and stirred reactor models 1171-10114 A71 -12852 IAI IACIiIIE SISTlSES Subcritical floss over two dimensional airfoils by Ban role in future naviqation from SAC viewpoint, multistrip method of inteqral relations considering relationships to mission and machine r BE-393J 1 1171-10581 A71-10502 Calibration and preliminary analysis of gassenqer Avionics system maximizing pilot chances of demand and modal split models for northeast surviving mission and destroying selected target Corridor of Qnited States by removing mental limitations [PB-190946] 171-11021 A71-10506 OBCEAlICAL PROPBBTIES Man machine considerations in all-weather 10s Airplane materials mechanical properties level navigation system design, noting deqradation due to fatigue, discussing breaking off-course error reduction by command strain of A1 alloy information display to pilot 1171-11395 171-10515

1-23 UECAANICS (PHYSICS) SUBJECT INDEX

Be mechanical and physical properties, corrosion UILITARY AIR FACILITIES behavior, toxicity, fabrication and application Reference file of factors affectinq weather at as aircraft and spacecraft structural material Reese AFB, Texas A71-11539 r AD-71 1390 1 N71-10948 Al-Zn-Uq-Cu type hiqh strenqth A1 alloys Reference file of factors affecting weather at mechanical properties evaluation by fracture Vance AFB, Oklahoma mechanics methods F AD-71 1381 1 N 71- 10949 ..a71- . 1'1 540 Inventory of existing airport system in Rhode Runways, aprons and taxiways strenqtheninq to Island accommodate hiqher tire pressures and landinq F PB-1893321 N71-11028 speeds, heavier aircraft and surface ridinq UILITARY AIRCRAFT reouirements Combat aircraft cockpit temperature control system .l.cn fir,-,&,",--. nasion and operation ."170 Nb alloys in hypersonic qlider fabrication, n.._. I I- OVL," discussinq mechanical properties, oxidation Avionics system maximizinq pilot chances of resistance and sandwich panel desiqn surviving mission and destroyinq selected target A71-12935 by removinq mental limitations HECAANICS (PHYSICS) A71-10506 Hoverinq type flyinq vehicle desiqn and principle Fliqht control systems influence on military mechanisms for manned or unmanned use aircraft desiqn and performance, discussinq r NASI-CASE-nSC-12111- 11 N71-11039 static stability, ride quality, flutter marqin UETAL COATIIIGS and maneuver loa3 controls nanufacturinq and advancement technoloqy for [AIAA PAPER 69-7671 A71-12683 turbine enqine coatinqs Army aircraft modification proqram manaqement N71-11635 review and recommendations HETAL SURPllCES N71-10287 Passivation of metal aircraft surfaces UILITARY AVIATION [ AD-7119501 A7 1 - 11670 Uan role in future naviqation from SAC viewpoint, HETAL WORKING considerinq relationships to mission and machine Electrochemical machininq for aircraft enqine A 7 1 - 10502 metal components, discussinq cost, time Naviqator role in Nilitary Airlift Command /nAC/ comparisons, toolinq techniques and applications as navioator.~. weather analyst. fuel manaqer and f SUE PAPER UR-70-206 1 A71-11252 flioht planner Peen forminq of larqc complex parts from sheet and A71-10504 plate, illustratinq dihedral break in airplane UINIHUH DRAG winq skin Civil aircraft aspect ratio relationship to A71-11550 commercial viability, considering need for HETEOROLOGICAL CAARTS minimum induced draq at winq loading to improve Traffic radar qenerated weather contours for air payloads, speeds and ranqes traffic controller in helpinq aircraft avoid 1171-11628 thunderst orms MIRAGE 3 AIRCRAPT A71-10587 Uach 2 niraqe Uilan qround attack fiqhter, noting Northern Aemisphere temperature field atlas for lift aid moustache, low speed and steep approach SST fliqht planninq handlinq from short airstrips l AD-712017) N7 1 - 1103 1 171-12740 HETEOROLOGICAL PARAMETERS UISSILE TRAJECTORIES Soviet book on meteoroloqical conditions and Uissiles and aircraft trajectories computation supersonic aircraft fliqht covering atmospheric time reduced via time sharinq and hybridization composition and structure, temperature A71-11794 distribution, wind effects, etc HISSIOII PLANNING A71-12840 Uan role in future navigation from SAC viewpoint, Reference file of factors affectinq weather at considerinq relationships to mission and machine Reese APB, Texas A71-10502 F AD-7113901 N71-10948 ROWTE CARLO UETAOD Reference file of factors affectinq weather at Commercial transport aircraft maintenance Vance AFB, Oklahoma simulation nonte Carlo nodelinq techniques, F AD-711 38 1 1 N71-10949 considering application to airline operations UETEOROLOGICAL RADAR [SAE PAPER 7003451 1171-10128 Thin CAT layer detection in lower stratosphere by L band radar complemented by radiosonde and U-2 aircraft probes N 1171-10567 NACELLES Traffic radar generated weather contours for air Fire protection tests in small fuselage mounted traffic controller in helpinq aircraft avoid turbojet engine and nacelle installation thunderstorms IPAA-NA-70-41 1 N71-1101E A71-10587 NASA PROGRAMS Severe thunderstorm radar trackinq and related NACA/NASA rotating wing aircraft research history weather events hazardous to aviation operations durinq 1955-1970 period, discussing wind tunnel r ESSR-TU-ERLTn-NSSL-46] N71-10720 research UETHANE A71-1137. Turhoiet enqine design for methane element of IIAVIER-STOKES EQUATIOII liquified natural qas as aircraft fuel, Spheres Oseen draq, extendinq Goldstein expansion discussinq supersonic transport applications for Wavier-Stokes equation in powers of Reynold 171-10485 number UETAOD OF CRARACTERISTICS 1171-1238 Supersonic ovetexpanded jet flow past cone, NAVIGATION determininq impinqement point by method of Role of man in navigation - Conference, Colorado characteristics Sprinqs, July 1970 171-10613 A71-1050 RICROYAVB CIRCUITS AAVIGATIOII AIDS Research and development of solid state and Airborne inertial and area navigation systems electronic equipment, microwave circuits, performance requirements proposed for U.S. semiconductors, and ionospheric radar domestic airspace, includinq projection throuqh N71-10126 1995 RICROUAVE RADIOHETERS A71-105C uicrowave radiometry for snow and ice sensinq in Airline experience with dual inertial systems as aerial reconnaissance sole means of naviqation, considering equipment N71-11160 reliability, cockpit desiqn, traininq, etc A71-1051

A-24 SUBJECT IUDEX OPTIIIIZATIOl

UAIIGATORS nosB COUES Ban role in future naviqation from SAC viewpoint, Unsymmetrical nose bluntness effect on stability considering relationships to mission and machine derivatives of slender cone at Mach 14 A71-10502 [ AD-7119211 N71-11008 Navigator role in TACAN of reconnaissance and NOSE UEEELS fighter aircraft, noting Weapon System Officer Taxiing aircraft position and wheel trajectories fnnct ions for specific nose wheel path 171-10503 A71-11641 Naviqator role in Military Airlift Command /MAC/ llOZZLE DESIGU as navigator, weather analyst. fuel manager and Lou resistance nozzles for complete power flight planner compensation in rate of climb indicators A71- 10504 A71-10350 IIEUMU TEEOBT Axisymmetric hypersonic wind tunnel nozzle desiqn Nonaffine similarity laws and transformations by determining inviscid contour and correcting subject to limitations of Newtonian impact for turbulent boundary layer growth theory for two dimensional bodies. obtaininq [AIAA PAPER 69-3371 A71-11578 aerodynamic coefficients Internal mixing scheme for continnous fuel A71-10948 injection in Wankel engine via swirl nozzle UICKEL ALLOTS during intake-compression cycle Nibbase superalloys fatigue strenqth improvement A71-12559 for qas turbine engine components. discussing IIOZZLE PLOU homoqeneons deformation distribution, grain size Measuring characteristics of low Mach number flow control. etc of air from cwo planar nozzles with aspect ratio 1171-10166 of 3 at exit Mach 1 burner rig tests at 2100 F for oxidation [ AD-7113131 A71-11139 resistance evaluation of NicrAl and FeCrAlT UOZZLE GEOIIETBT claddings on TD-Ricr Axisvmmetric hypersonic wind tunnel nozzle design I NASA-TB-X-529161 871-11426 by determining inviscid contour and correcting UIOBIUII ALLOTS for turbulent boundary layer growth Nb alloys in hypersonic glider fabrication, [AIAA PAPER 69-3371 871-1 1578 discussing mechanical properties, oxidation Nozzle lateral spacing effect on drag and resistance and sandwich panel desiqn performance of twin jet afterbody configurations A7 1- 12935 with converqent nozzles at Mach 0.6 to 2.2 Niobium alloys for gas turbine blades, examining (UASA-TU-X-20993 111-10276 uorkinq temperatures, protective coatings and IUCLEAR BAGUETIC RESOUAUCE ductility nuclear magnetic resonance method of detersininq 171-12939 aromaticity of hydrocarbon fuels NOISE (SOUND) [ AD-7118921 ~71-11890 Airspeed contribution to noise level within fixed FJEEDICIL :Xii.TSiJ and rctxg ring aircraft Numerical stress-strain calculation for desiqn of [ AD-71 13591 mi-10705 hiqh pressure fiberqlass-reinforced plastic NOISE IUTENSITT balloons Unman subjective responses to approaching and A71 -1 1048 recedinq aircraft sounds dnrinq flight over Numerical analysis of flow field aronnd thin stationary observer airfoil in two dimensional. nonuniform stream, 171-10345 usinq finite difference method NOISE REDUCTIOU A71 -12680 Aladin 2 interurban stol transport desiqn with blown winqs and jet deflection by winq flaps, emphasizinq engine noise reduction 0 171-3 e743 OCEANS h'oise reduction relationship to air transportation Penetration of sonic boom energy into ocean in proqress, considering cost/technology balance, experimental simulation quiet engine. research and development proqrass, [AD-7119631 N71-10094 etc OILS A71-10819 Influence of Concorde powerplant operating Steep approach to landina for jet transport conditions on desiqn of olynpus 593 fuel and oil aircraft noise abatement, usinq qround based system equipment and onboard TI display N71-11653 A71-11311 ONBOARD EQUIPMWT Research and developments in aircraft noise American ATA prototype aircraft collision reduction avoidance equipment and proposed noncooperative R71-10171 system UOISE TOLERAWCE A71-10753 Air and land transportation noise sources and OPEUIUGS measurement, noise level scales, and individual Blade root cutout effects on hover performance of and community responses - conference helicoptor rotors with rotor thrust and torque r PB-191117 1 N71-10349 characteristics and wake pattern analysis UOUDESTRUCTIVE TESTS [ AD-711 396 3 A71-11030 Nondestructive testinq techniques for airline OPTICAL MEASUREIIENT maintenance insnection, describing ultrasonic, Ground visibility observations and automatic eddy current, maqnetic particles, and x ray measurement of runway visual range of airport methods runways A71-12449 A71-10118 Advanced technoloqy for product'ion of aerospace Automatic calculation of rnnway visual range of engines - conference airport runways I AGARD-CP-641 N71-11626 N71-10120 Radioqraphic nondestructive testing method on OPTICAL RADAR titanium billets for engine disk forqing Coherent laser synthetic aperture radar at R71-11639 microwave frequencies for airborne qround point UOlUUIFORM PLOW target mapping Numerical analysis of flow field around thin A71-12044 airfoil in two dimensional nonuniform stream, OPTIIIAL COWTBOL usinq finite difference method Optimal synthesis of selective multidimensional 1171-12680 invariant control systems applied to turboprop NORTEBBU HEMISPEERE engine with differential reductor Northern Hemisphere temperature field atlas for 1171-10718 SST fliqht planninq OPTIMIZATIOU [AD-7120171 N71- 110 3 1 computerized aerodynamic optimization of aircraft

A-25 OSCILLATING PLOW SUBJECT INDEX

propellers A71-12162 r AD-7103561 N71-10122 Transport aircraft tire Pressure and multiwheeled optimization techniques in aircraft configuration landing gear limitations regarding pavement design design AD-711 410 ] N71-11023 A71-12163 OSCILLATING FLOW Aircraft multiwheel undercarriage effect on rigid oscillatinq flow effects on pressure force normal and flexible pavements, examining failure modes 'to svmmetrical airfoil chord A71-12164 [ AD-71 18301 871-11011 aunicipal airport rigid pavements design OJBEii iPPBOI?!!LTIO!! considering supporting effects of soil subqrade, Spheres Oseen drag, extending Goldstein expansion asphaltic ccncrete siihhalie and pavement strength for Navier-Stokes equation in powers of Reynolds A71-12165 number Flexible pavements design for giant transports A7 1- 12380 considering load repetitions, total systems, OXIDATlUX PBSIS'iiBCB environmental effects, etc Nb alloys in hypersonic glider fabrication, A71- 12166 discussina mechanical properties. oxidation Rigid and flexible pavement design and resistance and sandwich panel design construction in Europe, discussing unreinforced A71-12935 and crack reinforced slabs and CBR method aach 1 burner rig tests at 2100 F for oxidation A71-12167 resistance evaluation of NiCrAl and FeCrAlY Aircraft pavements in UK, discussing reinforced claddings on TD-NiCr and unreinforced concrete, tar-bound bases and [NASA-TB-X-529161 N71-11426 surface coatings 1171- 12168 Aircraft pavements desiqn and ConStrUCtiOn P problems regarding adverse soil conditionsA71-12170 P-3 AIRCRAFT Computerized aerodynamic optimization of aircraft PEEIIIIIG propellers Peen forming of large complex parts from sheet and r AD-7103561 N71-10122 plate, illustratinq dihedral break in airplane PAD wing skin Analvsis of self-actina lift pad for aas-film seal A71-11550 of-turboshaft PBRFORMAICE TESTS N7 1- 12038 Inertial navigation system augmented by digital PANEL FLUTTER distance measurinq equipment in FAA flight Skew panels with in-plane forces under yawed inspection aircraft for performance evaluation1171-10507 supersonic flow, calculatinq flutter by matrix displacement methods Performance characteristics of Bendix type DRA-12 A71-10939 airborne Doppler radar system PANELS FAA-NA-70-50 J 1171-10394 Response of, and acoustic radiation from panels Design and performance of flexible nozzle excited by turbulent boundary layers supersonic wind tunnel model r AD-7106961 171-10386 [ TAE-86 1 N71-10978 PARABOLIC BODIES Description and capabilities of traveling wave Separation point study of incompressible laminar sonic boom simulators boundary layers around parabolic bodies at anqle NASA-CR-1696 J 171-1 1422 of attack PEOTOGRAPEIC RECORDIIIG [AD-7120841 N71- 11519 Transonic flow through planar cylinder lattices, PARACAUTE DESCENT discussing flow pattern visualization and Analysis of stresses and deflections in platforms recording techniques by high speed camera used for airdrop operations A71-10108 l AD-7115561 N71- 11968 PEYSICAL PROPERTIES PARAWINGS Be mechanical and physical properties, corrosion Statics and aerodynamics of lifting decelerators behavior, toxicity, fabrication and application harawinqs and sailwinqs/ at supersonic and as aircraft and spacecraft structural material hypersonic speeds A71-11539 rAIAA PAPER 68-9451 A71-10927 PIEZOELECTRIC TRANSDUCERS Low-speed wind tunnel tests of series of twin-keel Engine vibration high temperature transducer, all-flexible parawinqs discussing piezoelectric materials properties I NASI-TN-D-59361 N71-10052 and design considerations relative to PARTICLE TRAJECTORIES temperature, pressure, acoustic noise, humidity Trajectories and velocities of solid particles environment entrained by fluid flows in cascade nozzles A7 1 - 12911 [AD-711121 1 N71-10546 PILOT ERROR PASSENGER AIRCRAFT Boeina 747 aircraft crash landing in Washington VC 400 tilt winq VTOL cargo and passenger caused by pilot error N71-10814 transport aircraft, tliscussinq component and INTSB-AAR-70-191 svstem development and testing phase PILOT PERPORl!AACB A71-10466 Avionics system maximizing pilot chances Of PASSENGERS surviving mission and destroying selected tarqet Traveler service problems in domestic intercitv by removing mental limitations air, bus, and rail transportation 1171-10506 ~PB-1933001 N71-10116 Electronic control indicator for human pilot Pricinq system for landinq and takeoff slots by capability enhancement using color coded cathode passenqer fliahts for use of Yashinqton National ray display, presenting information from seven Airport different instruments N71-10170 A71 - 10750 Forecastinq passenqer travel demands Aircraft flying qualities research program, PB-192455 1 N71-10299 discussing navy test pilot evaluations and Selected tabulations from Cleveland Hopkins longitudinal handling characteristics for Airport user surveys before and after rail simulated carrier landinq task transit service rAIAA PAPER 69-8971 1171- 12678 N71-10360 Pilot evaluation of movable and riqid cockpit PASSIVITY control sticks Passivation of metal aircraft surfaces I AD-7099341 N71-10184 I AD-71 1950 1 N71-11670 PILOTS (PERSONNEL) PAVEMENTS Aircraft accident investigation includinq types of Aircraft pavement design - Conference. London, aircraft, pilot certificates, and accidents November 1970 NSTB-BA-70-4 1 N71-11024

A-2C SUBJECT IIDEX PROBABILITY TEEORT

PIPE FLOV [ RlSA-TU-I-64562 J 1171-10240 Circnlar pipe gas laminar flow at constant wall PBECIPITATIOI (EETEOROLO6T) temperatnre. determining heat exchange and draq Reference file of factors affectinq weather at by motion and enerqy egnations inteqration in Reese APB, Texas boundary layer approximations 1 AD-71139@1 A71-10948 171-12192 PREDICTIOIS PISTOI ElSIlES Air traffic pattern prediction for 1980 peak Air cooled opposed 4, 6 and 8 cylinder light summer periods in London, Enqland terminal area aircraft ensines with or without R71-10163 tnrbosupercharqinq, considering horsepower PRBSSUEB DISFBIBUTIO~ improvement and torsional vibration control Aerodynamic theory of pressnre field induced on [SAE PAPER 7002051 A71-10129 liftinq snrface by isotropic atmospheric PITOT TUBES turbnlence, considerins transfer function of Pitot type intake inlet additive draq in terms of concorde aircraft capture area ratio, static and total pressure [ICAS PAPER 70-301 A71-11019 coefficients Pressnre distributions prediction on blnnt bodies 1-11-1x88 at angle of attack, considerinq bodies of PLAWAP STBOCTUBES revolntion and larqe angle cones Heasurinq characteristics of low aach nnmber flov [ana PAPER 70-2081 1171-11 580 of air from two planar nozzles with aspect ratio Sweptback turboblades in parallel wall channel, of 3 at exit investiqating thickness, camber and leadinq edge r AD-71 1313 1 1171-11139 curvatnre effects on flow and pressure PLAEE WAVES distribntions and vortex movement aonoqraoh on plane shock wave interactions A71-12606 coverinq supersonically movinq two dimensional Laminar bonndary layer effect on dynamic viscous thin airfoils, slender bodies of revolution and pressure interaction in hypersonic flow thin wings [LR-5353 n7i-11003 1171-1 1227 oscillating flow effects on pressure force normal PLASEA ARC VELD116 to symmetrical airfoil chord aodern weldinq methods in aircraft and aerospace [ AD-711830] 1171-11011 indnstry Computer calcnlations of pressure distributions on E7 1- 1 1650 swept wings PLASTIC AIRCRAFT STRUCTURES IILR-TB-T-189 1 171-1 1015 Poliymidefioron reinforced plastic structnres lleasuring characteristics of low aach number flow fabrication, discussing use in leading edges of air from two planar nozzles with aspect ratio rsaE PAPER ~a-70-1331 171-11263 of 3 at exit lonmetallic aircraft constrnction materials, [ AD-7113131 171-11 139 discnssinq wood epoxy and polyester resins PRESSURE DUG !i??-12233 Pitot type intake inlet additive draq in terms of Eiqt strenqrh polyimide resin composites, capture area ratio, static and total pressnre discnssinq commerical and aerospace coefficients applications. chemistry. void content, volatiles 171-12688 and moistnre absorption Two dimensional analysis on jet exhaust into 171-12487 crosswind with mixing flow interference Carbon fiber-epoxy resin composites in aircraft [ aD-7115781 1171- 11 006 industry. examining fatigne life, cost, specific PRBSSUEE EFFECTS modnli and mechanical properties shock wave diffraction at sharp edqes, discussing 171-1 2488 physical principles, anqle and pressure ratio PLASTIC DEPORI1TI01 effects Stresses and deformations in multi-ply aircraft 1171-10109 tires subject to inflation pressure loadinq Plutter analysis of plates with inplane boundary [AD-7110731 871- 10934 snpport flexibility exposed to transverse PLATE TEEOBT pressnre loading or buckled by uniform thermal Plotter analysis of plates with inplane boundary expansion support flexibility exposed to transverse 1171-10340 Pressure loadinq or bockled by uniform thermal Circular cone with cross shaped vinqs in expansion supersonic flow. determining flov A71-10940 characteristics, relocities and pressure PlEUE11TIC COITROL A71-11958 Fabrication techniques of compact fluidic control sonic boom and explosive shock wave effects on equipment for aerosoace engines bnildings and structnral members 1171-11654 1171-1 1035 POLYESTER RESIIS PBESSUBE EEASUREIEITS lonmetallic aircraft constrnction materials, mountainous region vertical air flow research, discussing wood epoxy and polyester resins describing snperpressnre balloon and precise A71-12299 pressnre radiosonde system POLTIEIDE BBSIlS 1171-12420 High strength polyimide resin composites, PBBSSUBB OSCILLATIOIS discussing commerical and aerospace Sapersonic and transonic flov including effects of applications. che8istry. void content, volatiles pressnre oscillations within cavitT. predictinq and moistnre absorption rectanqnlar cavities drag from mathematical 171-12487 model POLTIEIDBS A71- 10931 Poliyiidefioron reinforced plastic strnctnres Pressnre flnctnations on fixed blades of axial fabrication. discussing use in leading eaqes flow compressor, determining sensor dynamic [SEE PlPEB BE-70-1333 A71-11263 characteristics POROUS BOUIDABT LAYER COlTROL 171-11024 linimum snction rate preventinq laminar boundary Sweep frequency nozzle pressure oscillation layer separation from cnrvilinear porons surface effects on turbojet combnstor dynamics in jet flov IIaSA-TII-D-6084] ~71-10982 1171-12553 PROBABILITY DISTRIBUTIOII PUICTIOIS POTEITIAL FLOW Relationship between small scale wind shears and Plane linear Cascades of thin cnrved profiles, rind profile power spectra obtaining potential flow velocities and lifting [ IIAS11-TU-1-64562 J 1171- 10240 force on leading edge PROBABILITY TEBORT 1171-10339 AX system improvement by procedural changes, POWEP SPBCTBA applyinq probability concepts to flisht safety Relationship between small scale wind shears and 1171-11699 wind profile power spectra

A-27 PROCUREHENT SUBJECT INDEX

PROCUREHENT Residual stress measurements and heat treatments Fliqht simulators procurement and commissioninq, for electron beam weldinq of rotatinq turbine discussinq difficulties due to different engine parts aircraft confiqurations, advantaqes of equipment N71-11644 and procedures standardization, etc A71-10015 PRODUCT DEVELOPHENT R MU9 Larzac turbofan enqine, describing desiqn, RADAR ANTENNAS deFc:cpmcnt. performance data, manufacturing Soviet book on antenna radomes of fliqht vehicles techniques, operation and maintenance c=veriin el-ctromaqnetic wave transmission A71-12607 through dielectric media, fabrication, PRODUCTION ENGINEERING construction materials, etc Advanced technoloqy for production of aerospace 1171-11322 enqines - c-siifcre~zc RADAR DATA r AGARD-CP-64 1 N71-11626 Acqusaiilon i-2 prxessinq of aircraft search nanufacturinq technoloqy and production radar data obtained by track-while-scan enqineerinq methods in aerospace industry technique, usinq off-line diqital computer N71-11627 A71-11392 Manufacturinq and advancement technology for RADAR ECAOES turbine enqine coatinqs Echoinq area relation to radar range resolution N71-11635 cell size and aircraft dimensions, usinq PROFILES mathematical model A71-11643 Plane linear cascades of thin curved profiles, obtaininq potential flow velocities and liftinq RADAR BEASUREHENT force on leadinq edqe Thin CAT layer detection in lower stratosphere by A71-10339 L band radar complemented by radiosonde and 0-2 PROJECT HANAGEHENT aircraft probes Systems maintenance proqram evaluation of Eastern A71-10567 Reqion air transportation facilities RADAR NAVIGATION N71-10114 Evaluation of systems, procedures, and Armv aircraft modification proqram manaqement instrumentation for air traffic control review and recommendations AD-71 16621 N71-10737 N71-10287 RADAR RESOLUTION PROPELLER BLADES Echoinq area relation to radar ranqe resolution Low noise turbofan enqine without aerodynamic cell size and aircraft dimensions, usins blade loadinq mathematical model r NASA-TN-D-6080 1 N7 1 - 11882 A71-11643 PROPELLER EFFICIENCY RADAR SCANNING Computerized aerodynamic optimization of aircraft Acquisition and processinq of aircraft search propellers radar data obtained by track-while-scan r AD-7103561 N71-10122 technique, usinq off-line diqital computer PROPELLERS A71-11392 Soviet book on aircraft power plant systems and Stochastic model for analysis of track-while-scan devices coverinq layout, enqine attachment, technique for aircraft search radar, based on propellers, control, fuel and oil systems, fire Kalman filter theory fiqhtinq. monitorinq, etc A71-11393 A71-12722 RADAR TARGETS PROPULSION SYSTEl COHFIGURATIOllS Coherent laser synthetic aperture radar at German monograph on systems analysis of future jet microwave frequencies for airborne qround point and fan propulsion systems for VTOL commercial tarqet mapping aircraft weiqht and cost reduction A71-12044 A71-10115 RADAR TRACKING PROPULSION SYSTEll PERPORIANCB stochastic model for analysis of track-while-scan Air transportation reliability throuqh turbojet technique for aircraft search radar, based on enqine performance monitorinq Kalman filter theory A71-12368 A71-11393 MU9 Larzac turbofan enqine, describing desiqn, Experimental desion of three dimensional air development, performance data, manufacturinq traffic control radar trackinq system techniques, operation and maintenance N71-10164 A71-12607 Severe thunderstorm radar trackinq and related PROPULSIVE EFFICIENCY weather events hazardous to aviation operations Air cooled opposed 4, 6 and 8 cylinder liqht r ESSA-TH-ERLTM-NSSL-'46 1 871-10720 aircraft enqines with or without RADIATION HAZARDS turbosupercharqinq, considering horsepower Radiation hazards of supersonic transport, and improvement and torsional vibration control tidal characteristics of Saint Lawrence River rSAE PAPER 7002051 A71-10129 [ AD-7106381 N71-10390 PROTECTIVE COATINGS RADIO FREQUENCY ItiTBRFERENCE Niobium alloys for qas turbine blades, examining Secondary currents on conducting cylinder near workinq temperatures, protective coatinqs and dipole antenna manifested as radio frequency ductility interference, considerinq effect on radiation A71-12939 pattern PSYCHOLOGICAL EFFECTS A71-11167 Human subjective responses to approachinq and RADIO RELAY SYSTEHS recedinq aircraft sounds durinq fliqht over Skynet communication systems, describinq lonq stationary observer distance strategic communication links between A71-10345 qround and mobile airfielicopter stations via wide and narrow band pathways A71-12439 Q RADIOGRAPHY QUALITY CONTROL Radioqraphic nondestructive testinq method on Soviet book on boltinq and couplinq elements titanium billets for enqine disk forqinq threads used in aircraft industry coverinq N71-11639 confiqurations selection, cuttinq, tolerance RLDIOSONDES requirements and quality control Reverse flow temperature probe desiqn and A7 1 - 1272 3 calibration for vertical soundinqs from X ray fluorescence analysis for quality control of aircraft, comparing to radiosonde method qas turbine aircraft enqine parts durinq A71-11822 manufacture and overhaul Mountainous reqion vertical air flow research, N71-11641 describinq superpressure balloon and precise

A-28 SUBJECT IlD1X REVERSED ?LOP

pressure radiosonde system Poliymide/boron reinforced plastic structures A71-12420 fabrication, discussing use in leading edges RADOBES snE PAPER EB-70-1 33 1 A71-11263 Soviet book on antenna radomes of fliqht vehicles Carbon fiber reinforced epoxy composites. covering electromagnetic wave transmission evaluating application as helicopter tail rotor thronqh dielectric media, fabrication, blade material construction materials, etc A71- 12477 A71-11322 Kiqh strength polyimide resin composites. RAIL TRAIISPORTATIOl discussing commerical and aerospace Traveler service problems in domestic intercity applications, chemistry, void content, rolatiles air, bus, and rail transportation and moisture absorption r PE-1 93300 1 1171-ioii6 171-12487 Rapid rail transit service to airports Carbon fiber-epoxy resin composites in aircraft 1171- 10 167 indnstry, examining fatique life, cost, specific Selected tabulations from Cleveland Kopkins moduli ana mechanical properties Airport nser surveys before and after rail A71-12488 transit service REIlPOBCEBIlT (STRWCTWRES) 171-10360 Optimal cross sectional dimensions of thin walled Statistical analysis of direct rail rapid transit longeron beams and ribs of skin reinforced delta system impact on transportation to Cleveland wings minimizing weight airwrt A71-12562 1171-10370 REIIIPORCIlG FIBERS File formats and code descriptions for analysis of Fiber reinforced composites application in direct rail rapid transit system impact on aerospace and aircraft, discussing boron and transportation to Cleveland airport graphite and cost effectiveness 1171-10371 A71-11277 Aiqh speed access system evaluation for Carbon fiber-epoxy resin composites in aircraft transportation from jetport to Biami with cost industry, examining fatigue life, cost, specific estimates and network descriptions moduli and mechanical properties [ PB- 192842 ] ~71-10417 A71-12488 Impact of rapid rail transient service from Carbon fiber reinforced plastics and metals central business district to airport structural components design, discussinq A~I-~OW+O properties, processing and applications Bibliographr on control and prevention of icing in A71-12910 transportation systems RELIABILITY E1GIBEERIIIG [ AD-711534 1 A71-10735 Air transportation reliability throuqh turbojet RAPID TRAIISIT SYSTEUS enqine performance monitorins Impact of rapid rail transient service from ~7?-72350 central business district to airpert KBSISARCB AIID DEVELOPBEIT A71-10440 AACrflASA rotating wing aircraft research history Calibration and preliminary analysis of passenger during 1955-1970 period, discussiuq wind tunnel demand and modal split models for northeast research Corridor of united States All-1 1377 r PB-1909461 1171-11021 Research and development of solid state and Investigatinq hiqh speed ground transportation electronic equipment, microwave circuits, systems based on tracked air cushion vehicles semiconductors, and ionospheric radar r~B-1909391 ~71-11033 A71-10126 RAREFIED GAS DYIIABICS Research and developments in aircraft noise neasurements of hypersonic, rarefied flow field of reduction disk Nil-7017 1 r AD-llOSUl? A7 1- 1046 1 Transportation research needs related to civil Laminar near vake characteristics behind circular enqineerinq cylinder in aach 6 rarefied air stream rPB-193388J N71-10247 rREPT-1108/70 J N71- 11012 Conqressional hearing on investigation of contract RATE OF CLIBB IIIDICATORS for TFX aircraft LOW resistance nozzles for complete power All-11034 compensation in rate of climb indicators RESEARCH FACILITIES 171-10350 German book on Goettingen Aerodynamic Research REAL TIlE OPERAPIOII Institute /1945-1969/ Real time six deqree of freedom aircraft fliqht 1171-11406 digital simulation usinq SL-1 continuous system Transportation research needs related to civil simulation lanquaqe enqineerins A71-11786 r Pa-193388~ All-1 0247 RECOIIAISSAIICE AIRCRAFT Capabilities and functions of Aeronautical navigator role in TACAU of reconnaissance and Research Institute of Sweden fiqhter aircraft, noting Peapon System Officer [PFA-611 N71- 12 139 functions RESOLWTIOII CELL A71-10503 Echoinq area relation to radar range resolution RECTIPICATIOII cell size and aircraft dimensions, nsinq Apolications of electrolyte rectification in mathematical model aeronautics industry A71-11643 A71-11637 RESOIIAIT FREQWEIICIES REE1TRY PHYSICS natural frequencies of cantilever turbine blade Spacecraft reentry aerodynamics regarding with asymmetric aerofoil under coupled bendinq- hypersonic hiqh altitude liftinq bodies, shock torsion vibrations, usinq Ritz-Galerkin method wave and flow field, heat, mass and enerqy for equations of motion transfer, etc 171-11014 r ICAS PAPER 70-01 1 A71-11686 Parametric study of natural frequencies of stin REFRACTORY BATERIALS stringer structures Gas flame heater for heat resistant samples under TAD-7113831 N71-10734 fatique tests, simulating qas turbine enqine REVERSED FLOP operatinq conditions Fredholm method for reversible transonic flow in A71-10041 coiputins aircraft wing and turbomachine or REIIIFORCED PLASTICS helicopter blade airfoils for compressibility Numerical stress-strain calculation for desiqn of law hish uressure fiberalass-reinforced plastic All-11022 balloons Reverse flow temperature probe design and 1171-11048 calibration for vertical sonndings from aircraft, coaparinq to radiosonde method

A-29 RHODE ISLAND SUBJECT INDEX

A71-11822 Runways, aprons and taxirays strengtheninq to RHODE ISLAND accomnodate higher tire pressures and landing Inventory Of existinq airport svstem in Rhode speeds, heavier aircraft and surface riding Island requirements [ PB-1893321 171-11028 A71-12169 RIVERS Aircraft pavements desiqn and construction Radiation hazards of supersonic transport, and problems regarding adverse soil conditions .tidal characteristics of Saint Lawrence River A71-12170 [AD-7106381 171-10390 naximun throughpnt-rate capacity for runway and ROADS final approach path airspace involving multiple eiblioqraphy on control and prevention of icinq in ipB *ayuiDqs,--..a transportation systems 171-12893 I AD-711534 1 N71-10735 Ground visibility observations and autonatic ROLiIUG COUTACT LOADS measurement of runway visual ranqe of airport Test time ana contact stresses effect on let fuels runways antiwear properties under rollinq friction A71 - 101t8 A71-12570 Automatic calculation of runway visual range of ROTARY WING AIRCRAFT airport runways NACA/NIISA rotatinq winq aircraft research history N71-10120 durinq 1955-1970 period, discussinq wind tunnel Bibliography on control and prevention of icing in research transportation systems A71-11377 IAD-7115341 N71-10735 ROTARY WINGS Carbon fiber reinforced epoxy composites, evaluatinq application as helicopter tail rotor S blade material SAFETY FACTORS A71-12477 Aircraft qalley design safety criteria, method for calculatinq helicopter vortex paths and considerinq injuries from routine use, normal, wake velocities crash or ditchinq conditions component [AD-7106941 N71-10470 dislodgment, equipment malfunctions and defects Delayed bubble movement on airfoil durinq I71- 10029 helicopter stall SAILWINGS [AD-7115401 171-11005 Statics and aerodynamics of liftinq decelerators subsonic wind tunnel investiqation of rotary winq /parawinqs and sailwings/ at supersonic and confiqurations for VTOL aircraft in cruise mode hypersonic speeds r NASA-TN-D-59451 N71-11025 [AIAA PAPER 68-9451 A71 - 10927 Blade root cutout effects on hover performance of SANDWICH STRUCTURES helicoptor rotors with rotor thrust and torque Sandwich structures applications in aircraft and characteristics and wake pattern analysis space vehicles, discussinq component IAD-71 13961 N71-11030 characteristics, manufacturinq processes and ROTATING STALLS mechanical testinq procedures Rotatinq stall in axial flow compressor hiqh h71-11959 pressure staqes, takinq into account boundary Ab alloys in hypersonic qlider fabrication, layer separation discussinq nechanical properties, oxidation A71-11063 resistance and sandwich panel desiqn ROTOR AERODYNARICS A71-12935 Rotor loss coefficients for prediction of radial Application of corrugated core sandwich structures qas turbine performance usinq one dimensional to powerplant components analvsis N7l-11636 A71-11016 SATELLITE NAVIGATION SYSTEnS ROTOR BLADES (TURBOI!ACHIUERY) Air traffic control by satellite, discussinq Feasibility of usinq flexible rotor blades for CIES-SGAC and ESRO experiments within Dioscures eiection systems project test proqraa IAD-7116421 N71-11022 1171-10748 ROTORS SATELLITE NETWORKS Flexible rotor balancinq by exact point-speed Skynet communication systems, describinq lonq influence coefficient method distance strateqic communication links between NASA-CR-72774 1 N71-10021 qround and mobile air/helicopter stations via RUNWAY LIGHTS wide and narrow band pathways Development study for VFR heliport standard A71-12439 liqhtinq system SEALS (STOPPERS) r~o-7109821 N71-10682 comouterized analysis of seal temperature, elastic RUNWAYS displacements and seal force balance in Aircraft oavement desiqn - Conference, London, iterative desion method for aas turbine November 1910 mainshaft seals A71-12162 A71-1 0479 Tr’insoort aircraft tire pressure and aultiwheeled Desiqn and performance of gas-film and Oil-film landinq qear limitations reqardinq pavpment lubricated self sealing mainshaft seals for qas desiqn turbine engines A71-12163 [ NASA-CR-72737 1 N71- 12035 Aircraft aultiwheel undercarriaqe effect on riqid Desiqn of self-actinq qas-fila seal for turboshaft and flexible pavements, examininq failure modes of qas turbine enqine A71-12164 N71-12036 Hunicipal airport riqid pavements desiqn Desiqn of oil-film seal for turboshaft of qas considerinq suoportinq effects of soil subgrade, turbine enqine asphaltic concrete subbase and pavement strenqth N71-12037 A71-12165 Analysis of self-actinq lift pad for gas-film Seal Flexible pavements desiqn for giant transports of turboshaft considerinq load repetitions, total systems, N71-12038 environmental effects, etc computerized sealinq dam desiqn analysis for qas A7 1-1 2 166 film seal of turboshaft Rioid and flexible pavement desiqn and N71-12039 construction in Furope, discussinq unreinforced SEARCH RADAR and crack reinforced slabs and CBR method Acquisition and processinq of aircraft search 171-121 67 radar data obtained by track-while-scan Aircraft pavements in UK. discussinq reinforced technique, nsinq off-line digital computer and unreinforced concrete, tar-bound bases and All-11392 surface coatinqs Stochastic model for analysis of track-while-scan A71-12168 technique for aircraft search radar, base4 on SUBJECT IIDEX SOLID STATE DZlICES

Kalman filter theory Eiqh lift systems for four-enqine nach 0.8 A71-11393 turbofan STOL aircraft. discnssinq propulsion, SERICOIDUCMB DElICES aerodynamics and desiqn trends Aircraft electric systems control by solid state FSAE PAPBS 7008111 A71-11545 switchinq, discnssinq reliability, service life, uind tunnel investigation of let transport versatilitr and compatibility airplane confiqnration with tiqb thrust-weiqht A7 1- 11627 ratio and external flow let flap - qraphs SERICOIIDUCTOBS (EATEBIALS) r RASA-TN-D-6058] nl1-1ou9s Research and development of solid state and Various vertical takeoff and landina and short electronic equipment, microware circuits, takeoff modal confiqnrations for air semiconductors. and ionospheric radar transportation 171-1 0126 [ PB- 190940 1 mi-1 1027 SBPABATED FLOW Air mode service analysis in northeast corridor Thin delta winq with leadinq edqe separation, rp~-i909351 1171-11029 obtaininq draq lift and rollinq moment SIDESLIP coefficients and pressure distribution Systems analysis application to stability of 1171-12408 aerodynamic cross conplinq in fliqbt vehicle SEBlORECRAIIISES motions with steady sideslip. nsinq feedback and Servosystem desiqn of hiqh-response mnltislotted root locos techniques bypass valvina system for supersonic inlets All-12687 r BASA-TI-D-60811 1171-1 1061 SIIILABITY THEOBEE SHAFTS (RACE1.E ELEREITS) nonaffine similarity laws and transformations Computerized analysis of seal temperature, elastic subject to limitations of Newtonian impact displacements and seal force balance in theory for tu3 dimensional bodies, obtainins iterative desiqn method for qas turbine aerodynamic coefficients mainshaft seals A71-10948 171-10479 SInULATIoll Sealinq dam analysis for design of shaft face seal Penetration of sonic boom energy into ocean in with self-actinq lift anqmentation for advanced exuerimental simulation qas turbine enqines [ AD-71 19631 171-10094 [ NASA-T1-D-7006 1 171-1 15-19 SIIULATOBS SHAPES Description and capabilities of travelina wave linimnm suction rate preventing laminar boundary sonic boom simulators layer separation from curvilinear porous surface [NASA-CR-16961 n71-11~22 in jet flow SIIlGULAB IUTEGBAL EQUATIOIS A71-12553 Three dimensional winqs harmonic oscillation with SEEAP STRESS arbitrary frequency in subsonic flow, presentinq Stresses and deformations in multi-ply aircraft approximation method for si~qnlrrintegral tirp+ ccbjecl t= inflatioi, pressure ioadina equation [AD-7110731 171-10434 A71-1084U SHOCK WAVE IREBACTIOI SKTIET SATELLITES nonoqraph on plane shock wave interactions Skynet communication systems, describing long corerinq supersonically moving two dimensional distance strategic communication links between thin airfoils, slender bodies of revolution and qronnd and mobile airfielicopter stations via thin winqs wide and narrow band pathways 171-11227 A71-12439 Computerized calculations of adiabatic laminar SLERDEB BODIES boundary layer and shock wave interactions nsinq Whitham supersonic flow theory application to mid- Klineberq method or near-field sonic boom of slender bodies in I VKI-T1-60 1 n71-11011 rind +n.-nel research CROCK WAVE PROPAGATIOU 171-10956 Sonic aircraft boom propagation analysis for nonoqrapb on plane shock wave interactions horizontal fliqht in unperturbed atmosphere coverinq supersonically movins two dimensional 17 1-1 1036 thin airfoils, slender bodies of revolution and SHOCK WAlES thin winqs Shock wave diffraction at sharp edaes, discnssinq 171-11227 physical principles, anqle and pressure ratio SLEWDEB COIES effects Three dimensional attached compressible laminar A71-10109 boundary layer on slender cones in hypersonic Psendosbock mechanism model, explainins snwrsonic fliqht at hiqh anqles of attack derived by diffuser main flow static pressure increase and numerical inteqration decrease alternately and wall increase A 71- 10926 monotonously Unsymmetrical nose bluntness effect on stability A71-11870 derivatives of slender cone at nach 14 SEOBT HAUL AIBCBAPT [AD-711921 J 171-11008 Econoiic contributions of U. S. domestic airline SLOTS industrr in 1970s reqardinq air transportation Air carrier demand for slots particularly in area constraints and impact on short haul of Pashinqton-Baltimore rAIAA PAPER 70-13091 171-10486 r PB-1933501 n71-103ai Short ban1 air transportation in U.S., interagency Circulation control by slot suction on circular cooperation and federal involvement cylinder r AIAA PAPER 70-12861 1171-10875 r ~~-5301 111-11002 Short haul air transportation technological SRALL PEHTUEBATIOI PLOW factors for VTOL. STOL, CTOL and liqht aircraft, Small perturbation subsonic flows aerodynamic considering operating costs, passenger service noise, using matched asymptotic expansions and environment impact method ~AIAAPAPER 70-12871 All-11700 A71-12377 Demonstration plan for Uestern Region Short Ban1 SIOW Air Transportation Proqram Eicrowave radiometry for snow and ice sensinq in rATF-71-/7190/-1-VOL-1] 171-10279 aerial reconnaissance Technical studies for Western Region Short Ran1 171-11160 Air Transportation Program SOIL RECEAIICS rATR-71-/7190/-1-VOL-21 171-10280 Aircraft pavements design and construction SHORT TAKEOPP AIBCBAPT problems reqardinq adverse soil conditions Aladin 2 interurban Stol transport design vith A71- 12170 blown winqs and jet deflection by wing flaps, SOLID STATE DEVICES emphasizing engine noise reduction Research and development of solid state and A71-10749 electronic equipment. microwave circuits, semiconductors, and ionospheric radar

A-31 SONIC BOOMS SUBJECT INDEX

.- standards, consideriw independent power source, SONIC BOOHS crash survivable installation, operation Whitham supersonic flow theory application to mid- initiation and exit visibility or near-field sonic bcom of slender bodies in A71-10030 wind tunnel research Aerospace engine startinq systems military and A71-10956 industry specifications and standards, penetration of sonic boom energy into ocean in considerinq cartridqe pneumatic, electric, qas experimental simulation turbine, hydraulic and mechanical types [AD-7119631 N71- 10094 A71-10103 sonic boom and explosive shock wave effects on STATIC DISCHARGERS buildinqs and structurai members Performance ~f red-cinq electrnde for nentralizina N71-11035 electrically charaed hydrocarbon fuel flow sonic aircraft boom propasation analysis for TAD-7123681 1371-11876 horizontal fliqht in unperturbed atmosphere STATIC PRESSURE N71-11036 Pseudoshock mechanism model, explaininq supersonic Description and capabilities of travelinq wave diffuser main iiow siaile piezz~reincrcilse il-3 sonic boom simulators decrease alternately and wall increase TNASA-CQ-16961 N71-11422 monotonously SOUND PAVES A71-11870 Turbulent jet noise estimation takino into account STATISTICAL AIALYSIS retarded time effect on acoustic radiation statistical data on delays and cost of delays at. A71-11468 airline terminals Response of, ana acoustic radiation from panels N71-10366 excited by turbulent boundary layers Statistical analysis of direct rail rapid transit IAD-71 0696 1 N71-10386 system impact on transportation to Cleveland SPACE HISSIONS airport Policies for participation of French aerospace N71-10370 industry in space proarams summary and statistical analysis of aircraft N71-12069 accidents SPACE SRUTTLES r NTSB-AAS-70-1 ] N71-10674 Application of IFR with unpowered, low lift drag Statistical tabulation of United States civil ratio landinq approaches aircraft accident kiistories for 1969 N71-10110 [ PB-190792 J N71- 10932 SPACECRAFT CONSTRUCTION MATERIALS Statistical tabulation of United States civil Fiber reinforced composites application in aircraft accident histories in 1968 aerospace and aircraft, discussinq boron and ~~~-1908111 N71-10933 qraohite and cost effectiveness STATISTICS A71-11277 FAA statistical handbook of aviation 1958-1968 Be mechanical and Physical prooerties, corrosion N71-10372 behavior, toxicity, fabrication and application STATOR BLADES as aircraft and spacecraft structural material Cold air tests on axial flow turbine with A71-11539 transpiration cooled discrete hole stator blades SPACECRAFT REENTRY to determine coolant flow ejection effect on Spacecraft reentry aerodynamics reqardinq turbine aerodynamic performance hvpersonic hiqh altitude liftinq bodies, shock r NASA-TM-X-21231 "1- 11010 wave and flow field, heat, mass and enerqy STOCHASTIC PROCESSES transfer, etc Stochastic model for analysis of track-while-scan r ICRS PAPER 70-01 1 A71-11686 technique for aircraft search radar, based on SPACECRAFT STRUCTURES Kalman filter theory Sandwich structures applications in aircraft and A71-11393 space vehicles, discussinq component STRAIN GAGES characteristics, manufacturinq processes and wind tunnel apparatns for reproducinq coninq and mechanical testinq procedures spinninq motions of bodies of revolution, usinq A71-11959 six-component strain gage balance for SPECTRUn ANALYSIS aerodynamic forces Aircraft response to atmospheric gust, discussinq A71-10930 spectral analysis procedures and calculation STRATOSPRERE results on T-tail aircraft desiqn Thin CAT layer detection in lower stratosphere by A71-10752 L band radar complemented by radiosonde and 0-2 SPHERES aircraft probes Spheres draq coefficient at hypersonic Mach All-10567 numbers for near free molecular flow Commercial SST environmental effects on A71-10969 stratospheric air, water vapor coCtent and earth Spheres Oseen dras, extendinq Goldstein expansion surface temperature for Navier-Stokes equation in powers of Reynolds 171-11178 number STREAMLINIIG A71-12380 Inviscid ideally conductinq fluid flow past thin spin TESTS foil in transverse maqnetic field, usinq small Wind tunnel apparatus for reproducinq coninq and parameter method soinninq motions of bodies of revolution, usinq A71-12629 six-comoonent strain qaqe balance for STRESS CONCENTRATION aerodynamic forcps calculations and measurements of strain A71-10930 distribution and deflection on model swept Wings STABILITY DERIVATIVES T NAL-TR-195 1 N71- 11950 Spanwisp distribution of induced draq in subsonic STRESS CORROSION flou by vortex lattice method, notinq Ti alloy hot salt stress corrosion under simulated applicability to rotary derivatives in stability enqine environmental conditions, presentinq analvsis threshold data based on residual tensile A7l-12691 ductility ~Jnsvmsetricalnose hluntness effect on stability A71-12885 derivatives of slender cone at lach 14 STRESS RELIEVING rAD-7119211 N71-11008 Aircraft structure fatigue life improvement Via STABILIZATION material stress coininq inside and around holes C-C. military trapsport stability auqmentation for and slots Ditch and yaw inertia at low speed, usinq allot A71-10170 evaluation on cockpit simulator STRESS-STRAII DIAGRAMS A71-12684 Numerical stress-strain calculation for desiqn of STANDARDS hiqh pressure fiberqlass-reinforced plastic Aircraft emerqencv evacuation illumination balloons

A-32 SUBJECT IMDEI SUPBRSOliIC ?LOW

A71-11048 SUBSOIIC AIRCRAFT SPRIIGERS Subsonic aircraft size effect in conventional Parametric study of natural fresuencies of skin design, discussinq increased weight increments stringer structures and economic gain rate r AD-71 13831 171- 10734 TAIAA PAPER 70-9401 A71-12676 STRUCTURAL AKALYSIS SOBSOIIC PLOU Papers on LABS technology for aircraft StrUctUral Three dimensional uinqs harmonic oscillation with mode control coverinq B-52 and C-51 aircraft arbitrary frequency in subsonic flou. presentins A71-11658 approximation method for singular integral Analrsis of self-actins lift pad for qas-film seal equation of turboshaft A71-10844 171-12038 Liftins surface in unsteady subsonic flou. STRUCTURAL DESIGI describing integral equation calculation method Design and performance of flexible nozzle including kernel logarithmic singularity supersonic uind tunnel model A71-11020 [ TAE-86 ] 171- 10478 Small perturbation subsonic flows aerodynamic Desiqn and performance of gas-film and oil-film noise, usinq matched asymptotic expansions lubricated self sealinq mainshaft seals for gas method turbine enqines 171-12377 [NASA-CR-72737 1 171-12035 Spanwise distribution of induced draq in subsonic Desiqn of self-actinq gas-film seal for turboshaft flow by vortex lattice method, notinq of qas turbine engine applicability to rotary derivatives in stability R71-12036 analysis Design of oil-film seal for turboshaft of sas A71-12691 turbine enqine Linear theoretical method for arbitrary winq R71-12037 planform and trailinq edge control surfaces in STRUCTURAL EIGIKIERIKG low frequency oscillatory motion in subsonic Municipal airport riqid pavements desisn flow considerinq supportinq effects of soil subsrade. [ NPL-AERO-1303] A71-11013 asphaltic concrete subbase and pavement strength SUBSOHIC UIID TUIMELS A71- 12165 Subsonic uind tunnel investiqation of rotary wins Flexible pavements desiqn for qiant transports configurations for VTOL aircraft in cruise mode considerinq load repetitions, total systems, [ 8851-TN-D-5945 1 A71-11025 environmental effects, etc SUCTIOII 171-12166 Circulation control by slot suction on circular Riqid and flexible pavement design and cylinder construction in Europe, discussinq unreinforced r LR-5301 ~71-1io02 and crack reinforced slabs and CBR method SOPBRCRARGEBS 871-12167 Air cooled opposed 4. 6 and 8 cylinder liqht Aircraft pavements in UK, discussinq reinforced aircraft engines with or without and unreinforced concrete, tar-bound bases and turbosupercharqinq, considering horsepower surface coatiuqs improvement and torsional vibration control A71-12168 [SAE PAPER 7002051 A71-10129 Runways, aprons and taxiways strenqtheninq to SUPERSOIIC AIRCRAFT accommodate hiqher tire pressures and landinq nach 2 Riraqe Milan qround attack fighter, noting speeds. heavier aircraft and surface riding lift aid moustache, low speed and steep approach requirements handlinq from short airstrips A71-12169 171-12740 Aircraft pavements desian and construction SUPIIRSOAIC BOUADART LAYERS problems reqardinq adverse soil conditions Supersonic laminar boundary layer structure near A71-12170 convex corners for large turning angles STRUCTURAL IBFIBERS 171-10461 Carbon fiber reinforced plastics and metals SUPERSOKIC DIFFUSERS structural components desiqn, discussinq Pseudoshock mechanism model, explaininq supersonic properties, processinq and applications diffuser main flow static pressure increase and A71-12910 decrease alternately and wall increase Sonic boom and explosive shock wave effects on sonotonously buildinqs and structural members 171-1 1870 1171-11035 SUPERSOIIC PLIGHT STRUCTURAL STABILITY statics and aerodynamics of liftina decelerators LAM fliqht control systems for turbulence induced /parawings and sailwinqs/ at supersonic and fatisue damaoe reduction in B-52 and C-5A hypersonic speeds aircraft, wins mathematical models TAIAA PAPER 68-91151 A71-10927 A71-11660 Soviet book on meteoroloqical conditions and Aoplication of corruqated core sandwich structures supersonic aircraft flight coverinq atmospheric to powerplant components composition and structure. temperature A71-11636 distribution, wind effects, etc STRUCTURAL VIBRATIOH 1171-12840 Parametric study of natural frequencies of skin Sonic aircraft boom propagation analysis for strinqer structures horizontal fliqht in unperturbed atmosphere r AD-711383) ~71-10734 n7i-11036 STRUCTURAL UEIGBT SIIPERSOMIC PLOW German monoqrapb on systems analysis of future iet supersonic overexpanded jet flow past cone, and fan propulsion systems for VTOL commercial determining impinqement point by method of aircraft weiqht and cost reduction characteristics A71-10115 A71-10613 Optisal cross sectional dimensions of thin ualled ains-body interference in supersonic inviscid lonqeron beams and ribs of skin reinforced delta flow, extendinq Stewartson approach to arbitrary vinqs ainimizinq weight smooth convex cylinder 871-12562 A71 - 10774 Subsonic aircraft size effect in conventional Supersonic a?a transonic Flow inclndinq effects of desiqn. discussinq increased weiqht increments pressure oscillations vithin cavity, predicting and economic gain rate rectangular cavities draq from mathematical ~AIAAPAPER 70-9401 A71-12676 model SUBCRITICAL PLOU A71 - 10931 Subcritical flows over tvo dimensional airfoils by Skew panels with in-plane forces under yawed moltistrip method of inteqral relations supersonic flow, calculatinq flutter by matrix r RE-393J 1 H71-10581 displacement methods A71-10939

A-33 SUPERSONIC FLUTTER SUBJECT INDEX

Circular cone with cross shaped winqs in SWEAT COOLIIIG . supersonic flow. determinina flow Cold air tests on axial flow turbine with characteristics, velocities and pressure transpiration cooled discrete hole stator blades 1171-11958 to determine coolant flow ejection effect on Boundary layer transition studies of several turbine aerodynamic performance pointed bodies of revolution at supersonic [ NASA-TH-I-2123 ] N71-11010 speeds SWEDEU INASA-TN-D-6063) ~71-11520 Capabilities and functions of Aeronautical SUPERSON.IC FLUTTER Research Institute of Sweden skcy ~=ne?avith ic-pl-ne forces ~ndery.ave3 [ PPI-61 j N71- 12139 supersonic flow. calculatinq flutter by matrix SWEEP FREQUENCY displacement methods Sweep frequency nozzle pressure oscillation A71-10939 effects on turbojet combustor dynamics SUPERSONIC BEAT TRANSFER I NASA-TN-D-60841 N71-10982 ilrai :iansfri inbas. I--^ --..-:_ .--<"..,- *"a Pmw1PI)D.PI c,p's =UysL*""*r LOUIIIUL IYI ""IYL UP_.. transitional separated flows Sweptback turboblades in parallel wall channel, IAD-7103473 N71-10249 investiqatinq thickness, camber and leadinq edqe SUPSRSOIIIC IMLETS curvature effects on flow and pressure Servosystem desiqn of hiqh-response multislotted distributions and vortex movement bypass valvinq system for supersonic inlets A71-12606 INASA-TN-D-6081] N7 1-1 1061 SWEPT WINGS SUPERSONIC JET PLOW Swept rinq fiqhter aircraft transonic buffet onset plane supersonic overexpanded jet interaction with lift coefficient from camber and trailinq edge obstacle, usinq hodoqraphs for flow pattern deflection, considerinq design variations construction 1171-12679 A71-10425 Computer calculations of pressure distributions on SUPERSONIC TRAIISPORTS swept winqs Commercial SST environmental effects on I NLR-TN-T-1891 N71-11015 stratospheric air, water vapor content and earth Calculations and measurements of strain surface temperature distribution and deflection on model swept winqs A71-11178 [ HAL-TR-1951 ~71-11 950 SST prooram relation to airline operations, SWITCEING CIRCUITS comparinq production confiquration, performance, Aircraft electric systems control by solid state economics and operation with subsonics switching, discussinq reliability, service life, IAIAA PRPER 70-12171 A71-11248 versatility and compatibility Electrohydraulic thrust control system for A71-11627 supersonic transport aircraft enqines, SYUCAUOIIISI! considerinq reliability, performance and weiqht Time-synchronized approach control combininq ISAE PAPER 7008191 A71-11546 aircraft precision navigation and quidance with Radiation hazards of supersonic transport, and ATC equipment tidal characteristics of Saint Lawrence River A71-12894 r AD-7106381 N71-10390 Synchronization of distant atomic clocks by mere aind tunnel study of aerodynamic interference draq overflight - Operation Synfral caused by fan jet enqine wake of supersonic IONERA-NT-1651 N71-11681 transport SYMCARONOUS SATELLITES I NASA-TN-D-6067 1 N71- 11004 Project D'ioscures for qlobal sea and air traffic Northern Hemisphere temperature field atlas for control usinq synchronous satellites for SST fliqht planninq qround-air-qround communications I AD-7120171 N71-1103 1 N71-11768 SUPERSONIC WAKES SYNOPTIC HETEOROLOGY aind tunnel study of aerodynamic interference drag Reference file of factors affecting weather at caused by fan jet enqine wake of supersonic Vance APE, Oklahoma transport f AD-711381) 171-10949 [NASA-TN-D-60671 N71- 11004 SYSTEMS ANALYSIS SUPERSOIIIC WIIID TUNNELS German monoqraph on systems analysis of future jet Desiqn and performance of flexible nozzle and fan propulsion systems for VTOL commercial supersonic wind tunnel model aircraft veiqht and cost reduction ITAE-861 N71-10478 A71-10115 Coolinq water system for compressor of supersonic Systems analysis application to stability of wind tunnel aerodynamic cross couplinq in fliqht vehicle TAD-710971 1 N71-10679 motions with steady sideslip, usinq feedback and SURFACE ROUGENESS root locus techniques Low speed aerodynamic characteristics of airfoil R71 -12687 profiles includinq effects of upper surface Systems maintenance program evaluation of Fastern rouqhness simulatins hoar frost Reqion air transportation facilities r NPL-AERO- i 308 1 N71-11016 N71-10114 SURFACE TEMPERATURE Systems approach to accident investigation in Commercial SST environmental effects on civil aviation and homes stratospheric air, water vapor content and earth N71-10115 surface temperature Systems analysis of fliqht control and quidance of 171-11 178 CH-46C helicopter SURFACE VEAICLES r NASA-CR-111024] N71-10297 Leqal aspects of air and surface carrier Requirements €or ejection seat systems interactions in freiqht transportation IRAE-LIB-TRANS-14711 171-11042 N71-12119 SYSTEMS ENGINEERING SURFACES Han machine considerations in all-weather low Minimum suction rate preventinq laminar boundary level naviqation system desiqn, notinq laver separation from curvilinear porous surface of€-course error reduction by command in jet flow information display to pilot A71-12553 A71-10515 Biblioqraohy of documents containinq numerical Airport system planninq from environmental data on planar liftinq surfaces viewpoint, discussing travel market, airport I AGIRD-R-574-701 N71-10339 accessibility, airspace utilization and control SURVEYS and land use Selpcted tabulations from Cleveland Hopkins A71-11642 Rirport user surveys hefore and after rail RB 211 turbofan enqine desiqn, emphasizinq modular transit service construction, systems inteqration, N71-10360 maintainability and noise reduction A71-11682

A-34 SUBJECT IIIDEX TBIII WALLED SBBLLS

nodel performance index /Pi/ orovidiuq criterion equipment, vork forces utilization. etc for approximatinq one dynamic fliqht control A71-11909 svstem by another based on qeometrical Belicopter operations intearation into civil air representation of linear autonomous systems traffic system. noting special requirements for r AIAA PAPER 69-885 J 171-12682 mixed fixed and rotan wins terminal Flexible rotor balancing by exact point-speed environments influence coefficient method A71-12892 I IIASA-CR-727741 171-10021 Systems maintenance proqraa evaluation of Eastern Transportation research needs related to civil Region air transportation facilities engineerins R71-10114 [PB-1933881 871-10247 Traveler service problems in domestic intercity Evaluation of systemsI procedures. and air. bus, and rail transportation instrnmentatibn for- air traffic-control [PB-1933OOJ 1171-10116 IAD-711662 1 N71- 10737 Transoortation research needs related to civil Status of feneral involvement in short haul air euqineerinq transportation r PB- 19338 e 1 171-10247 171- 11026 Statistical data on delays and cost of delays at Roverinq type flvinq vehicle design and principle airline terminals mechanisms for manned or unmanned use 171-10366 l1ASA-CASE-ISC-12111-11 171-11039 Eish speed access system evaluation for transportation from jetport to Riami with cost estimates and netuork descriptions T [ PB-192842 J ~71-10417 T TAIL SURFACES TEST BQUIPEEIIT Aircraft response to atmospheric qust, discussinq BE 211 turbofan engine development testinq, spectral analysis procedures and calculation describins test prosram..-. test facilities. results on T-tail aircraft design cquipmeot and instrumentation A71-10152 A71-12912 T-39 AIRCRAFT TEST FACILITIBS Performance characteristics of Bendix type DRA-12 German book on Goettinqen Aerodynamic Qesearch airborne Doppler radar system Institute /1945-1969/ [ FAA-IA-70-501 1171-10394 1171-1 1406 TABLES (DATA) RB 211 turbofan engine development testinq, Selected tabulations from Cleveland Aopkins describiuq test proqram, test facilities, Airwrt user surveys before and after rail equipment and instrumentation transit service A71 - 12912 171-10360 Each 1 burner rig tests at 2100 P for oxidation TACAII resistance evaluation of IlCrAl and PeCrAlT 22: 11zrinator role in ?:CAR cf rcccnnaizsazcc an6 cIyvvI~\I=,., - - "- ~z TC-XiCr fishter aircraft. uotina.. weaoon Svstem officer [ IASA-TR-X-52916 1 871-11426 functions Test facilities, uind tunnels and tests at 1171-10503 aodane-Avrieux Center TAIL LSSEIIBLIES [ONERA-IT-1663 1171-1 1470 Carbon fiber reinforced epoxy composites, Capabilities and functions of Aeronautical evaluatinq application as helicopter tail rotor Research Institute of Sweden blade material [ PPA-613 nil-12139 A7 1-12477 TEXU TAKEOFF Reference file of factors affectinq weather at Douqlas DC 9 aircraft crash during takeoff ceased Reese AFB, Texas by ice formation on airfoils [AD-7113901 171-10948 iHTSB-AAB-70-i0j 1171-10815 TEEREAL BDCKLIW2 TI11116 Flutter analysis of plates with inplane boundary Taxiinq aircraft position and uheel trajectories support flexibility exposed to transverse for specific nose uheel path pressure loadinq or buckled by uniform thermal A7 1- 1164 1 expansion TBCLIIIOLOGT UTILIZATIOI A71-10940 Air traffic control by satellite, discussins TEERIAL SIIULATIOB CUES-SGAC and ESRO experiments within Dioscures Gas flame heater for heat resistant samples under project test proqram fatigue tests, simulating gas turbine enaine A71-10748 operatins conditions Carbon fiber reinforced plastics and metals A71-10041 structural components design, discussinq TEEBIOCOUPLE PTROEBTERS properties, processinq and-applications calorimetric and thermocouple pyrometer heat flux A7 1- 12910 measurements in blowdovn uind tunnels TEIIPERATWE COITROL OAERA-IT-159 1 871-12059 Combat aircraft-cockpit temperature control svstem TBBRIODTIIAIIC EFFICIBIICT design and operation Rotor loss coefficients for prediction of radial A71-10270 qas turbine performance using one dimensional TEIPBRATORB EFFECTS analvsis Reat transfer and friction draq calculation for A71-11016 turbulent boundary layer of qas with temperature ?EERIODTHAEIC PROPERTIES dependent physical properties Thermal coatings of gondola payloads A11-11884 DTo-3747-12] 171-10496 niobium alloys for qas turbine blades, examiniuq TEII AIRFOILS workins temwratnres._. Protective coatinas and Eonoqraph on plane shock uave interactions ductility covering snpersonically movinq two dimensional A71- 12939 thin airfoils, slender bodies of revolution and TEEPERATORE ESASVBEIIEIT thin winqs Thermal coatings of qondola payloads A71-11227 [110-3747-12 1 N71-10496 Inviscid ideally conducting fluid flow past thin TEIPERATUEE PROBES foil in transverse maqnetic field, usius small Reverse flov temperature probe desiqn and parameter method calibration for vertical soundings from b71- 12629 aircraft, comparing to radiosonde method Numerical analysis of flow field around thin A71-11822 airfoil in two dimensional nonuniform stream, TBREIIIAL FACILITIES usinq finite difference method Diqital simnlatiou proqraa in GPSS language for All-12680 airline operations includinq aircraft TEIII WALLED SHELLS maintenance, fliqht scheduling, terminal space, Optimal cross sectional dimensions of thin ualled

A-35 TAIN WINGS SUBJECT INDEX

longeron beams and ribs of skin reinforced delta TORSIONAL VIBRATION winas minimizinq weiqht Natural frequencies of can+ilever turbine blade A71-12562 with asymmetric aerofoil under coupled bendinq- TRIW WINGS torsion vibrations, usinq Ritz-Galerkin method Thin delta winq with leadin4 edqe separation, for equations of motion obtaininq draq lift and rolling moment All-11014 coefficients and pressure distribution TRACKING RADAR A71-12408 Acquisition and processinq of aircraft search THREADS radar data obtained by track-while-scan r....<-e I.,.,.& 0" l.,.,+i"" *"A r"..r,in- yyv,. "---~..~...I.. -I-r __.. L. ClCEeztz te-h-iqac, ~sxn; off-li~pdigitel coayter threads used in aircraft industry coverinq 171-11 392 confiqurations selection, cuttinq, tolerance Experimental desiqn of three dimensional air requirements and quality control traffic control radar trackinq SVStem A71-12723 Nl1-10164 .TiiBEE Dinj8Sifiifii --_lKALL1Ub-_-__ --_--6UCL3 Three dimensional attached compressible laminar Boundary layer separation at free streamline boundary layer on slender cones in hyoersonic attachment to sharp trailing edqe of flat Plate, fliqht at hiqh anqles of attack derived by deducinq terminal velocity profile for two numerical inteqration dimensional flow A71-10926 A71-12376 Three dimensional flow patterns obtained durinq TRAILING-EDGE FLAPS boundary layer separation on airfoils Linear theoretical method for arbitrary winq INPL-AERO-13091 N71-11014 planform and trailing edge control surfaces in TARUST CONTROL low frequency oscillatory motion in subsonic Electrohydraulic thrust Control system for flow supersonic transport aircraft enqines, INPL-AERO-13031 N71-11013 considerinq reliability, performance and weiqht TRAINING SIMULATORS TSAR PAPER 700819] 871-1 1546 Simulated low visibility landinq traininq, THRUST-WBIGAT RATIO discussinq airborne and qround based simulators wind tunnel investiqation of jet transport A71-10022 airplane confiquration with hiqh thrust-weiqht TRAJECTORY ANALYSIS ratio and external flow jet flap - graphs Taxiinq aircraft position and wheel trajectories NASA-TN-D-60581 N71-10495 for specific nose wheel path TAUNDERSTORHS A71-11641 Traffic radar qenerated weather contours for air Nissiles and aircraft trajectories computation traffic controller in helpinq aircraft avoid time reduced via time sharinq and hybridization thunderstorms A71-11794 A71-10587 TRANSFORMATIONS (HATAEHATICS) Severe thunderstorm radar trackinq and related Nonaffine similarity laws and transformations weather events hazardous to aviation operations subject to limitations of Newtonian impact r ESSA-Tn-ERLTH-NSSL-46 1 N71-10720 theory for two dimensional bodies, obtaininq TIDES aerodynamic coefficients Radiation hazards of supersonic transport, and A71-10948 tidal characteristics of Saint Lawrence River TRANSITION FLOW T AD-710638 J N71-10390 Two dimensional wake laminar-turbulent transition TILT WING AIRCRAFT by sinqle and double frequency sounds imposition VC 400 tilt winq VTOL carqo and passenqer and wind tunnel natural disturbance, inducing transport aircraft, discussinq component and velocity fluctuations system development and testinq phase A71-10132 A71-10466 Heat transfer in base type supersonic laminar and TIME LAG transitional separated flows Turbulent jet noise estimation takinq into account r AD-7103471 N71-10249 retarded time effect on acoustic radiation TRANSITION POINTS A71-11468 Laminar-turbulent boundary layer transition point TIME MEASUREHENT on winq, usinq hot-wire anemometer and Synchronization of distant atomic clocks by mere oscilloscope overflight - Operation Svnfral A71-12555 TONERA-NT-1651 N71- 11681 TRAASLATIONAL MOTION TIHE OPTIMAL CONTROL Development and characteristics of translatino ATA Collision Avoidance System based on time and horizontal tail assembly for supersonic aircraft frequency synchronization via qround stations or TNASA-CASE-XLA-08801-11 N71-11043 other aircraft TRANSONIC PLOW A71-12895 Transonic flow throuqh planar cylinder lattices, TIHE SAARING discussinq flow pattern visualization and nissiles and aircraft trajectories computation recordinq techniques by hiqh speed camera time reduced via time sharinq and hybridization A71-10108 A71-11794 supersonic and transonic flow including effects of TIP DRIVEN ROTORS pressure oscillations within cavity, predicting Do-132 lioht five seat tip drive turbine rectangular cavities draq from mathematical helicopter, discussinq applications, fliqht model testinq, desiqn and major components A71-10931 A71-10465 Fredbolm method for reversible transonic flow in TITANIUM computinq aircraft winq and turbomachine or Aadioqraphic nondestructive testinq method on helicopter blade airfoils for compressibility titanium billets for enqine disk forqinq law N71-11639 A71-11022 TITAUIUM ALLOYS Swept wins fiqhter aircraft transonic buffet onset Ti all09 hot salt stress corrosion under simulated lift coefficient from camber and trailinq edqe enqine environmental conditions, presentinq deflection, considerinq desiqn variations threshold data based on residual tensile A71-12679 ductility TRANSONIC WImD TUNNELS 1171-12885 Rotary system for dynamic stability tests in TOLERANCBS (MECEANICS) transonic wind tunnel Soviet hook on boltinq and couplinq elements [ NAL-TR-196 ] N71-11009 threads used in aircraft industry coverinq TRARSPARENCE confiqurations selection, cuttinq. tolerance Holographic interferometry for study of requirements and quality control transparent media A71-12723 [TP-8511 N71-10407

A-36 SUBJECT IUDLX TURBULBUT BOUUDARY LAYER

TRAISPORT AIRCRAFT [SAE PAPER 700811] A71-11545 Commercial transport aircraft maintenance RB 211 turbofan engine desian, emphasizina modular simulation nonte Carlo nodeling techniques. construct ion. systems integration. considerinq application to airline operations maintainability and noise reduction [SAE PAPER 7003453 A71-10128 A71-11682 VC 400 tilt wing VTOL cargo and passenqer n49 Larzac turbofan enqine, describing design. transport aircraft. discussing component and development. performance data, sannfacturing system development and testing phase techniques, operation and maintenance A71-10466 A71-12607 Aladin 2 interurban Stol transport design with RB 211 turbofan engine development testinq. blown winqs and jet deflection by wing flaps, describing test program, test facilities, emphasizing enqiue noise reduction equipment and instrumentation A71-10749 A71 - 12912 Bypersonic conventional and rocket transport Simulating downstreas flow blockage doors in aircraft, discnssing costs and air and noise bypass air duct of turbofan euoine with axial pollution flow fan rotor TAIAA PAPER 70-12183 1171-11302 [ UASA-TA-D-60711 A71-10537 Transport aircraft tire pressure and mnltiwheeled Low noise turbofan enqine without aerodynamic landins gear limitations regarding pavement blade loading desiqn [AASA-TB-D-6080] ~71-11882 A7 1-12163 TURBOJET EIGIlB COUTROL maintenance programs, evaluation, acceptance, an5 Optimal synthesis of selective multidimensional monitorinq procedures for transport aircraft invariant control systems applied to turboprop 871-11020 engine with differential reductor TEAUSPORT VBEICLBS 1171-10718 Investigatinq hiqh speed ground transportation TUBBOJBT EUGIUES systems based nn tracked air cushion vehicles Turbojet enqine desiqn for methane element of r PB-190939 1 871- 11033 liquified natnral gas as aircraft fuel, TRAESPORTATIOU discussing supersonic transport aoplications Transportation research needs related to civil A71-10485 engineering Two-spool turbojet enqines matching by rapid [ PB-1933881 1171-10247 superposition method TRAVELIUG UAVES 1171-10821 Description and capabilities of travelinq wave Air transportation reliability throuqh turbojet sonic boom simulators enqine perf ormance monitorino [AASA-CR-1696] ~71-11422 171-12368 TORBIIIB BLADES Sweep frequency nozzle pressure oscillation natural freqcencies cf cantilerei tortine biade effects on turbojet combustor dynamics with asymmetric aerofoil under coupled bending- [ AASA-TA-D-6084] A71-10982 torsion vibrations, usinq Ritz-Galerkin method Fire protection tests in small fuselaqe mounted for equations of motion turbojet engine and nacelle installation A71-11014 [ FAA-HA-70-41 1 ~71-11018 Pressure fluctuations on fixed blades of axial TUBBOIACBIUB BLADES flow compressor. determining sensor dynamic Sweotback turboblades in parallel wall channel, characteristics investiqatinq thickness, camber and leadins edge A71- 11024 curvature effects on flow and pressnre Blade bonnd vortex svstem mathematical model for distributions and vortex movement optimum heavily loaded ducted fans, including A71-12606 thrust. power and efficiency desisn parameters PORTRUM Droqras *l)r C?Z:FU~~?-: cisrEinates of 171-12677 circular arc sinqle and tandem turbomachinery Niobium alloys for gas turbine blades, examininq blade sections on plane workinq temperatures, protective coatinqs and [ NASA-TA-D-6020 J ~71-iouii ductility PORTRAA proqram for calculatino aerodvnamic forces 1171-12939 from pressnre or velocity distributions on blade Trajectories and velocities of solid particles sections entrained by fluid flows in cascade nozzles r NASA-TB-X-2123 ] R71-10467 [AD-7111211 R71-10546 TURBOPROP EAGIUES Flutter analysis on axial turbomachine bladinq Optimal synthesis of selective multidimensional [ AD-7107941 A71-10562 invariant control systems applied to turboprop Poundary precision in domain of aeronautical enqine with differential reductor turbines A71-10718 ~71-11638 TUBBOSEAFTS TURBIIE EUGIBBS Desiqn and performance of qas-film and oil-film Aircraft turbine enqine development, considerinq lubricated self sealing mainshaft seals for qas mismatch reduction between enqine and airframe turbine engines in fliqht tests [ RASA-CR-727371 n7i-12035 171-1 1780 Design of Self-acting qas-film seal for turboshaft Advanced technoloqv for production of aerospace of qas turbine enqine engines - conference 171-12036 [ AGARD-CP-643 vi-11626 Design of oil-film seal for turboshaft of gas nanufacturing and advanceaent technoloqp for tnrbine enqine turbine enqine coatings A71-12037 1x71-11635 Analysis of self-acting lift Dad for qas-film seal TURBOCOIPRESSORS of turboshaft Pressure fluctuations on fixed blades of axial 171-72038 flow compressor, determininq sensor dynamic TUBBULLACE characteristics Revieu of aircraft wake turbulence A71-11024 [ AD-712080 J R71-11129 Rotatinq stall in axial flow compressor hiqh TURBULEUCE EFFECTS pressure stages, taking into account boundary LABS flight demonstration. discussina laver separation instrumentation, flutter boundary and dynamic 1171-11063 response, aerodynamic testino and structural Guide vanes small aspect ratio effect on hiqh response to turbulence pressure staqes of axial flow compressors A71-11662 A71-12558 TUBBULEUT BOUUDARY LAYER TURBOFAU EUGIUES Axisyametric hypersonic wind tunnel nozzle design Aiqh lift systems for four-enqine nach 0.8 by determinino inviscid contour and correctinq turbofan STOL aircraft, discnssinq propulsion, for turbulent boundary layer qrowtb aerodynamics and desiqn trends [AIAA PAPER 69-3371 A71-11578

A-37 TURBULENT HEAT TRANSFER SUBJECT IADEX

Heat transfer and friction draq calculation for Lifting surface in unsteady subsonic flow, turbulent boundary layer of qas with temperature describing inteqral equation calculation method dependent physical properties includinq kernel loqarithmic singularity A71- 11884 A71-11020 Laminar-turbulent boundary layer transition point UPWASR on winq, usinq hot-wire anemometer and Upwash interference on two dimensional jet flap oscilloscope wins in slotted wall tunnel, usinq small A71-12555 disturbance theory Response of, and acoustic radiation from panels 1171-12690 excited by turbulent boundary iayers ERBkC TO,1!!SPOPTITTON AD-7 10696 J N71-10386 Aladin 2 interurban Stol transport design Wlth TURBULENT BEAT TRAMSFER blown vinqs and jet deflection by wing flaps, Heat transfer and friction draq calculation for emphasizinq enqine noise reduction tcrhlent houndarv laver of qas with temperature 1171-10749 dependent physical properties iiL traffic pzttcxz prediction for 1980 peak A71-11884 summer periods in London, Enqland terminal area- TURBULENT JETS N71-10163 Turbulent jet noise estimation taking into account UTILITY AIRCRAFT retarded time effect on acoustic radiation Aerodynamic data recording for determining A71-11468 longitudinal static stability of US-2A aircraftN71-10563 TURBULENT WAKES rAD-7107221 Two dimensional wake laminar-turbulent transition by sinqle and double frequency sounds imposition and wind tunnel natural disturbance, inducinq V velocity fluctuations V/STOL AIRCRAFT A71-10132 Short haul air transportation technological TWO DIIENSIONAL BODIES factors for VTOL, STOL, CTOL and light aircfaft, Nonaffine similarity laws and transformations considerinq operating costs, passenqer service subiect to limitations of Newtonian impact and environment impact theory for two dimensional bodies, obtaininq [AIAA PAPER 70-12873 A71 -1 1700 aerodynamic coefficients VACUUR EFFECTS A71-10908 Flov field of two dimensional nozzle exhausting to nonoqraph on plane shock wave interactions vacuum, describina computer proqram based on BGK coverinq supersonically movinq two dimensional equation and plottinq exhanst reqion density, thin airfoils, slender bodies of revolution and temperature and velocity thin winqs rAIAA PAPER 69-6581 A71-10932 A71-11227 VARIABLE SWEEP WINGS TWO DIIENSIONAL PLOW Development and characteristics of variable sveep Tvo dimensional wake laminar-turbulent transition winq control system for supersonic aircraftN71-11041 by sinqle and double frequency sounds imposition [ NASA-CASE-XLA-03659 1 and wind tunnel natural disturbance, inducinq VERICLE WREELS velocity fluctuations Aircraft nultiwheel undercarriaqe effect on rigid A71-10132 and flexible pavements, examininq failure modes Boundary layer separation at free streamline A71-12164 attachment to sharp trailing edge of flat plate, VERICIJLAR TRACKS deducing terminal velocity Profile for two Investiqatinq hiqh speed qround transportation dimensional flow systems based on tracked air cushion vehiclesN71-11033 A71-12376 IPB-1909391 Numerical analysis of flow field around thin VELOCITY DISTRIBUTIOA airfoil in two dimensional nonuniform stream, Boundary layer separation at free streamline usinq finite difference method attachment to sharp trailinq edqe of flat plate, A7 1- 12680 deducing terminal velocity profile for two Three dimensional flow patterns obtained durinq dimensional flow boundary layer separation on airfoils A71-12376 INPL-1ERO-13091 N71-11014 lethod for calculatinq helicopter vortex paths and THO STAGE TURBINES wake velocities Two-spool turbojet engines matchinq by rapid [ AD-7106941 N71-10470 superposition method VELOCITY REASURE8EAT A71-10821 Aircraft ultrasonic altitude and vertical velocity sensor for low fliqht, discussinq VTOL aircraft automatic hoverinq control and time laq U A71-11624 ULTRASONIC WAVE TRANSDUCERS VERTICAL AIR CURRENTS Aircraft ultrasonic altitude and vertical velocity Scale lenqths in atmospheric turbulence from sensor €or low fliqht, discussinq VTOL aircraft spectra and autocorrelation of vertical air automatic horerinq control and time laq velocity component measured in low flyinq A71- 11624 aircraft 1171-10859 UNDERCARRIAGES Aircraft multiwheel undercarriage effect on riqid nountainous reqion vertical air flow research, and flexible pavements, examininq failure modes describing superpressure balloon and precise 1171-12164 pressure radiosonde system 1171-12420 UNDERWATER ACOUSTICS Penetration of sonic boom enerqv into ocean in VERTICAL FLIGRT experimental simulation Aircraft ultrasonic altitude and vertical velocity [AD-7119631 N71-10094 sensor for lor fliqht, discussinq VTOL aircraft UNITED STITES OF AMERICA automatic hoverinq control and time lag Airborne inertial and area naviqation systems A71- 11624 performance requirements proposed for O.S. VERTICAL TAKEOFF AIRCRAFT domestic airspace, includinq projection throuqh German monoqraph on systems analysis of future let 1995 and fan propulsion systems for VTOL commercial A71- 10508 aircraft weight and cost reduction Calibration and preliminary analysis of Passenqer A71-10115 demand and modal split models for Northeast VC 400 tilt vinq VTOL cargo and passenqer Corridor of United States transport aircraft, discussinq component and r PB-1909461 N71-11021 system development and testina phase UNSTEADY FLOW A71-10466 Unsteady flow theory, describinq milestone Recirculation reaion of flow field caused by let experiments in aerodynamics in qround effect with crossflow 1171-10266 AD-71 16651 N71-10832

A-38 SUBJECT IBDEX WIID TUl1EL BOZZLES

Two dimensional analysis on jet exhaust into A71-12554 crosswind pith mixinq flow interference WAR 6AMES [AD-7115181 nil-11006 Differential qame theory aoplied to Subsonic wind tunnel investigation of rotary winq pursuit-evasion problems of tu0 jet aircraft. confiqnrations for VTOL aircraft in cruise mode TAD-7110551 wi-10328 I NASA-TW-D-59451 nil- 11025 WARllIlG SYSTEMS Various vertical takeoff and landinq and short ITA Collision Avoidance Svstem based on time and takeoff modal configurations for air frequency synchronization via qround stations or transportation other aircraft r PB- 190940 1 mi-1 1027 171-128Q5 Air mode service analysis in northeast Corridor WASEIIIGTOO. r ~~-1goq351 871-1 1029 Air carrier demand for slots oarticularly in area VIBRATIOl MEASUREMEHT of Washington-Baltimore Enqine vibration hiqh temperature transdncer, IPB-I~~~~OI nii-io3~1 discussing piezoelectric materials properties WATER VAPOR and design considerations relative to Commercial SST environmental effects on temperatnre. pressure, acoustic noise, humidity stratosuheric air, water vapor content aFd earth environment surface temperature All-12911 171-11178 VIBRATIOU SIMOLATORS WAVE DIPPRACTIOI Aircraft structures fatigue testing device nsinq Shock save diffraction at SharU eases, discossinq proqrammed control of electrical inputs to physical princioles, anqle and pressure ratio electrodynamic vibration stand. notinq load effects cycle effects and damaqe accumnlatior 871-1 0109 A71-10409 WEAPO11 SYSTEMS VISCOSITY Pishter aircraft desiqn with consideration to Laminar boundary layer effect on dynamic viscous armament. detection capability. thrust, soeed. pressnre interaction in hyuersonic flow and load factor performance tradeoffs 111-5351 mi-11003 I AD-71 04971 n7i-ioi83 VISIBILITY WEAR TESTS Aircraft compartment glare minimization for fliqht Test time and contact stresses effect on jet fuels crew visibility conditions and visual antiwear properties under rollinq friction performance improvement 1171-12570 All-10028 WEATEER PORECASTIlG Ground visibility observations and automatic Severe thunderstorm radar tracking and related measurement of runvay visual range of airport ueather events hazardous to aviation operations rnnways IESSA-TR-ERLTR-USSL-46 1 Rl?-:0720 A7:-10i76 Reference file of factors affectinq ueather at 11SUAL AIDS Reese APE, Texas Electronic control indicator for human pilot [ AD-71 13903 nii-iogu8 capability enhancement usinq color coded cathode Reference file of factors affectinq ueather at ray display, presentinq information fro. seven Yance APE, Oklahoma different instruments [AD-7113811 1171-10949 A71 - 1 0750 WEIGET IWDICATOBS Visual aids for secondary airports wind tunnel apparatus for reproducinq coninq and [ FAA-AA-70-511 117 1-1 14-14 spinninq motions of bodies of revolution, osinq VISUAL PLIGHT six-component strain qage balance for Development study for VPR heliport standard aerodynamic forces liqhtinq system A71-10930 r AD-~VIW~] 1171-10682 WELDED JOIITS VISUAL PERCISPTIOY Besidual stress measurements and heat treatments Antomatic calculation of runway visnal range of for electron beam veldinq of rotatinq turbine airport runways enoine parts nil-10120 A71-11644 Visual approach slope indicator system for WIlD EFFECTS lonq- bodied aircraft soviet book on meteorological conditions and r FAA-RD-70-76 1 117 1-1 1905 supersonic aircraft fliqht coverinq atmospheric VORTICES composition and structure, temperature Sveptback turboblades in parallel wall channel, distribution, wind effects, etc investigating thickness, camber and leading edge All-12840 curvature effects on flow and pressure WIlD PROFILES distributions ana vortex movement Relationship between small scale wind shea& and A71-12606 wind profile power spectra Blade bound vortex system mathematical model for [1ASA-TU-X-64562] mi-10240 optimum heavily loaded ducted fans, includinq WIUD SREAR thrust. pover and efficiency desiqn parameters Relationship between small scale vind shears and 171-12677 wind profile power spectra Method for calculating helicopter vortex paths and rlASA-TR-I-64562] 1111-10240 wake velocities WIYD TUllEL APPARATUS 1 AD-710694 ] 1171- 10470 wind tnnnel apuaratns for reproducing coning and spinnino motions of bodies of revolution. usinq sir-component strain qaqe balance for W aerodynamic forces WALL FLOW A71-10930 Psendoshock mechanism modei, explaining supersonic Rotary system for dynamic stability tests in diffuser main flov static pressure increase and transonic vind tunnel decrease alternately and vall increase r IIAL-TR-196 J n7i-ii009 monotonously WIlD TUllEL MODELS A11- 1 1870 wind tnnnel investiqation of jet transport WALL TEMPIIRATURB airplane confiquration with high thrnst-weiaht Circular pipe gas laminar flow at constant wall ratio and external flow jet flap - graphs temperature. determining heat exchange and drag [ AASA-TA-D-6058 ] 171-10495 by motion and enerqy equations integration in UIID TWIIEL ROXZLES boundary layer approximations Arisymmetric hypersonic wind tunnel nozzle desion All-12192 by determininq inviscid contour and correctino WAlKEL ElGIlES for turbnlent bonndary layer grovth Internal mixinq scheme for continuous fuel rAIAA PAPER 69-3371 All-11578 injection in Wankel engine via svirl nozzle Design and performance of flexible nozzle during intake-compression cycle supersonic vind tnnnel model

A-39 WIND TUNNEL STABILITY TESTS SUBJECT INDEX

rTAE-861 371-10478 WIND TUNNEL STABILITY TESTS Rotary system for dynamic stability tests in transonic wind tunnel rNAL-TR-1961 N71-11009 WIND TUNNELS Cambered and symmetric wina profiles and flap confiqurations, discussinq wind tunnel tests at moderate Reynolds numbers A71-11950 Petrodiffusion interferometric holosraphy in wind tunnels includinq displacement and deformation nf deflwtors -. .___^ r ONEPA-TP-852 1 NII-ll31u UING FLAPS Upwash interference on two dinensional jet flap winq in slotted wall tunnel, usinq small disturbance theory A71-12690 WING PLOY lETROD TESTS Laminar-turbulent boundary layer transition point on winq, usinq hot-wire anemometer and oscilloscope A71-12555 WING LOADING civil aircraft aspect ratio relationship to commercial viability, considerinq need for minimum induced dram at wins loadina to improve payloads, speeds and ranqes A71-11628 WING OSCILLATIONS Critical flutter of winq with riqid aileron studied by analoq computer modelinq A71-10606 Three dimensional winqs harmonic oscillation with arbitrary frequency in subsonic flow, presentinq aonrorimation method for sinqular intoqral equation A71-108UU Linear theoretical method for arbitrary winq planform and trailinq edqe control surfaces in low frequency oscillatory motion in subsonic flow NE’L-AERO-13031 N71-11013 WING PROFILES Cambered and symmetric winq profiles and flap confiaurations. discussinq wind tunnel tests at moderate Revnolds numbers A71-11950 WING SPAN smnwise distribution of induced draq in subsonic flow by vortex lattice method, notinq apnlicability to rotary derivatives in stability analysis A71-12691 WINGS Circular cone with cross shaped winqs in supersonic flow, determininq flow characteristics, velocities and pressure A71-11958 Two dimensional axisvmmetric laminar boundary layer on blown winq and body of revolution, usina sixth-order polvnomial.. for velocitv distribution A71- 12554 WOODEN STRUCTURES Nonmetallic aircraft construction materials, discussinq wood epoxy and polyester resins A71-12299 X X RAY FLUORESCENCE X ray fluorescence analysis for quality control of qas turhine aircraft enqine parts durins manufacture and overhaul N71-11641

A-40 PERSONAL AUTHOR INDEX

~ AERONAUTICAL ENGINEERING / A Special Bibliography (Suppl. 2) FEBRUARY 1971

Typical Personal Author Index Listing

PERSONAL AUTHOR airplanes in the vicinity of the ground. I A71- 11624 for improrinq the AEIISTEOIG. B. D. crashworthiness of inteqral fuel tanks Final Traininq for lor visibility landings reFOrt, 1'267 - 1Q70 A71 - 10022 C PIA-*A-70-46 J ABOBA, 1. L. A unified theory for linearized shock-on-shock interaction problems 1171-1 1227 ASHLEY, E. Optimization technioues in aircraft configuration desiqn [AD-711410] N71- 11023 Listings in this index are arranged alphabetically by personal author The ASTEBLLA. E. J. title of the document prowdes the user with a brief description of the ?he role of uan in naviqation subject matter The report number helps to indicate the type of document 171-10502 cited (e g , NASA repori translatlon. NASA contractor report) The accesslon number IS located beneath and to the right of the title eg N71-11019 B Under any one authors name the accesslon numbers are arranged In se- quence with the IAA accession numbers appearing first BACOI, 1. E. Scale lenqth in atmospheric turbulence as measured frou an aircraft 1171-10859 A BADE, E. ACKEEBBEG, R. C. soft-qround arrestins of civil aircraft - Boundary-layer separation at a free streamline. I Influence of qravei depth and tyre inflation - Two-dimensional flow Dressnre A71-12376 [ RAE-TR-690011 N71-11CU0 AHLEES, E. E. BAKBB, E. P. Investiqation of two methods for improving the Transportation research needs related to civil crashworthiness of integral fuel tanks Final eEqineer ins report. 1967 - 1970 [ P9- 193388 1 N71- 10247 [ FAA-NA-70-461 871-1 10 19 BALOIBIII. J. E. AELVIX, E. 6. Acoustic and aerodvnamic perforaance of a Developments in paveuent desiqn in the USA - 6-foot-diameter fan for turbofan enqines. 2 - Flexible pavements Perforascre of "-1 f.-c iz zacalle vitbsct 1171- 12 166 acoustic suupression AKSEIOV. A. P. [NASA-TN-D-60801 N71-lleR2 Aviation fuels, lubrication materials. and special BAIlIUG. 1. E. fluids The unsteady normal force on an airfoil in 1171-1 1320 oscillatina flow Influence of the test time and contact stresses on AD-711RIO] N71- 11011 the antiwear properties of jet fuels under BARABASHEVA, Z. V. conditions of rollinq friction Threads used in the aircraft irdustry- Randbook A71-12570 A71-12723 ALLEU, J. E. BARBER, V. C. The future of aeronautics Pestoration 3f landinq-nat-surs3ced subqrades by qrootins met'n-ds Final report

ALLISOLI.~. C. ~ 8.~~. [ AD-7109621 871-10681 The role of man in tactical air navisation BAECLAY, P. A. A71- 10503 Severe thunderstorm ra.?sr echo m3tion and related ALTEAUS. D. weather events barardous to aviation operatiors A new low-resistance nozzle for conplete power I ~SSA-T~-SFLO"-BSSL-4~1 N71-10720 compensation in variometers BARER, E. D. A71-10350 Investigatins an aircraL+ disaster Wind-tunnel measurement on profiles with flaps for h71-19456 moderate Reynolds numbers. I BAEIARD, E. E. A71-11950 Transonic buffet characteristicc ~f a hq-der; AWeGt AIACKER. J. Z. winq with desiqn variations operatinq experiences usino dual inertial A71-1267? navisation systems as the sole means of BATTRUU. P. 1. naviqation A conflict Drediction alooritila USE ir A71-10509 procedural domestic airspace AMIET, E. P~I-~~F.QR The aerodynamic noise of small-Perturbation BAUGEUAI, D. 1. subsonic flows Peen formins n7i-12377 A71-11553 AOKI. I. BEALL, E. T. fcesearch on swept-back blades laid between nevelopnent of advanced composite structures for parallel walls. 11 - Prperimental research on aircraft Clark T 8 percent and NACA 6509 blades with P.71-112Sl aspect ratio of 2.0 BEGLOV.4, T. V. A71-12606 Threads used in the aircraft ixdustrv- 4andbook ARIHAEA, n. 1171-12723 An ultrasonic altitude-velocity sensor for

B-1 BERNING, P. P. PERSOIAL AUTHOR IIDEI

BEBNING, P. P. A71-11642 cold-air investiqation of a turbine vith BRUCE. J. transpiration-cooled stator blades. 2 - Staqe The future of aeronautics performance vith discrete hole stator blades A71-12609 r NASA-TU-X-21231 N71-11010 BRUIIDIII, C. 1. BEKNEV, V- S. An experimental investiqation of the laminar near Eroerimental study of rotatinq stall in hiqh- vake behind a circular cylinder in a Hach 6, Dressure staqes of an axial-flow compressor rarefied air stream A71-11063 r REPT-1108/70] 171-11012 BELLU, 8. B. J. BRUIETLUD. R. An appraisal of current shortcominqs in the Problems involved in the appiication of nioiriun procurement and commissioninq processes of alloys to turbine blades fliqht simulators A71-12939 A71-10015 BRUNSCB, K. BENSOI, J. S. DevelopaeFt and test of carbon epoxy fibre A hybrid frequency response technique and its composite for helicopter tail rotor applications application to aircraft fliqht flutter testing A71- 12477 A71-10228 BRUTOII, W. E. BENSON, 8. S. Study of turbojet combustor dynamics usinq A review of methods for assessinq loss sveep-frequency data coefficients in radial gas turbines rNASA-TN-D-60841 N71-10982 A71- 11016 BUCKLET, T. BERLIN. S. A proposal for primary radar automatic tracking in neasurements of the hypersonic, rarefied flow terminal areas field of a disk N71-10164 r AD-71 064 11 N71-10461 BULALA, B. 1. BESSOI, J. Nonlinear conical qas flovs Synchronization of distant stations by simple A71-12719 overfliqht - Operation Synfral BULDOVSKII. G. S. IONERA-NT-1651 N71-11681 Ueteoroloqical conditions of supersonic aircraft BETREUIEUI. A. fliqhts Calorimetric heat flux measurements in A71-12840 vind-tunnels BURGESS, E. A. IONERA-NT-1591 N71-12059 Concorde and the air travel market BETTAN, A. A71-12746 Observation and measurement of qround visibility. BURNS, C. D. Automatic calculation of the visual ranqe of Restoration of landing-mat-surfaced subqrades by airport runvays qroutinq methods Final report N71-10116 r AD-7109621 N71-10681 Automatic calculation of the visual ranqe of BURRIS, P. n. airport runvavs Aircraft Performance benefits from moaern control N71-10120 systems technology BIDIKAOV, S. A. rAIAA PAPER 69-7671 1171-12683 Solution of the Problem of flutter of a rinq vith BURTON, 6. W. a rigid aileron by the method of electronic Develooment of advanced ccmposite structures for modeling aircraft A71-10606 ~71-11281 BIGOLA, 8. A. BUIBAUM, 0. Construction and design of high-pressure balloons Cumulative frequency distributions of aircraft made 'rom fiberqlass-reinforced Plastics landinq qear loads 1171-1104R IDAE-LIB-TRANS-14621 N71-10273 BILLON Utilization of a niobium alloy in the fabrication of a h-yoersonic vehicle C A71-12935 CAMEO. R. BINION, T. U., JR. Contribution of foundry precision in the domain of Investiqation of the recirculation reqion of a aeronautical turbines flov field caused by a jet in qround effect vith N71-11638 crossflow Final report, 19 nar. - 30 Apr. 1970 CAUPBELL, J. F. r AD-711665 1 N71-10832 An aDDr0ximat.n method for oredictinq pressure BONGERS, 8. distributions on blunt bodies at anqle of attack Development and test of carbon epoxv fibre rA1P.A PAPER 70-2081 A71-11580 composite for helicopter tail rator applications Boundary-layer transition study of several pointed A7 1- 12477 bodies of revolution at supersonic speeds BONNET, K. V. r NASR-TN-D-60631 N71-11520 Aircraft develooment in relation to pavement CARAFOLI, E. desian Considvrations on the vave draq of a delta thin 171-12163 vinq with leadinq edqe separation BOREN, J. A71-12408 A real-time h degree of freedom aircraft CARET, K. 1. simulation with SL-1 Icinq occurrence, control ana prevention. An A71-11786 annotated bibliography BORROK, n. J. TAD-7115341 N71-10735 Results of the ATA CAS fliqht test Droqram CARNEGIE, U. A71-12896 Solution of the rauationn of motion of BREIAAN, E. R. coupled-bondirq torsion vibrations of turbine Developments in pavement design in the USA - Riqid blades by the method of Ritz-Galerkin PavCment s 1171-11014 A71-12165 CASSARINO, S. J. BREWER, A. K. Effect of root cutout on hover perforrance Final str'cssen ar.d deformations in multi-Dlv aircraft r'cport, Jun. 1969 - Apr. 1970 tir- subiect to inflation pressure loadinq r AD-711396 1 171- 11030 Technical report, Auq. 19hS - Dec. 1969 CASSELS, U. A. r AD-7110731 N71-10434 Boundary-layer traasition study of several pointed BREZNYAK, E. J. bodies of revolution at supersocic speeds Recent developments in hiqh velocity metalvorkinq NASA-TN-D-60631 NTl-11520 rsnE PAPER MF-70-2x11 A71- 11267 CAUSSIGNAC, J.-H. BROWN, J. F. fioloqraphic interferometry by retro-dif6usion Fnvironmental a~pectsof airport system DlaEninq r ONERA-TP-852 1 N71-11510

B-2 PERSOIAL AUTEOR ItiDEX DOUGEERTT, J. E.

CEA. T.-S. applications A study of flow from two planar nozzles A71-12487 TAD-7113131 N71-11139 CEOSTEPAIT. E. 1. CBABOEAT. B. Pitot inlet additive draw Contribution to the study of unsteady flows 1171-12688 All-10266 CBOUSE, J. E. CBALUPEIK, J. D. FORTRAN proaram for computina coordinates of Evaluatinq the Noises of Transportation - circular arc sinqle and tandem turbomachinery Proceedinqs of a symposium on acceptability blade sections on a Dlane criteria for transportation noise [ NASA-TN-D-6020 1 N71-10411 [ PB-1911171 871-10349 CULIEB, J. CBAII6. P. K. synchronization of distant stations by simple Compressible laminar boundary layer on a cone at overfliqht - Operation Synfral high anqle of attack [OtiPRA-NT-1651 Ell-11681 All-10926 CUIIIISHAB. E. J. CBAEG, P. 5. Application of a supersonic kernel-function Stress and deflections in type 2 and type 4 procedure to flutter analysis of thip liftins airdrop platforms Final report surfaces [ AD-711556 J 871-1 1968 NASA-TN-D-6012 1 171-10866 CEAUDBURI, S. P. Approximate solution of a singular integral equation relatins to the subsonic flow past D oscillatinq winqs DALAEAKIS, E. J. 1171-10844 aodelinq an air traffic control environmm+ CEERAIIOVSKII, 0. E. L71-1CO79 Determination of the Doint of laminar-turbulent DAIIELS, 6. E. transition with the aid of a travelinq indicator SST environmental effects - SOB- considpratians A7 1-12555 All-11178 CHEVALLIER, J.-P. DAT, 8. Calorimetric heat flux measurements in Calculatina the kprnel of tte liftinq snrfere wind-tunnels inteqral equation in unstea3v subsonic flow r OBERA-BT-159 1 A71-12059 A71-11027 CEOP. P. Biblioqraphv of documents containinq numerical Numerical investiqations of an airfoil in a data on planar liftins surfaces nonuniform stream r AGARD-R-574-701 N71-10330 A71-12680 DIVIES. E. G. CLARK. E. E. Experience with static dissipator additive in Supersonic winq-body interference ariation fuels 1111- 10114 ?hl-l27GG CLEVELAIID, P. A. DAVIES. n. E. Size effects in conventional aircraft desiqn State airport system invpntorv - An invento-v o= IAIAA P11VR 70-9401 A71-12676 the existina airoort system in rihode Island COCKATEK, P. [ PB-1893321 WTl- 1 102 9 Diqital fliqht control and landinq system for the DAVIS, E. T. CB-46C helicopter Final report Incompressible laminar boundary lavers on a r?IASA-CR-111024 J till- 10297 parabola at anale of attack - A study of tbe COCKRAE, E. E. J. separation point Corbatina fire risks in aircraft r AD-71208Ul N71-11515, 1171-10399 DAWSOI. J. 1. COLE. J, D. Undercarriaoe effects on /a/ riqi3 parerects /b/ A pilot evaluation of movable and riaid aircraft flexible pavements con tr01s A71- 32164 f AD-7099341 ti71-10184 DEL BALZO, J. 1. COLK. R. A. Inertial systems an3 area naviqation in the 0.S. Exploitinq AR donestic airspace 1171-11628 A71-10508 COLLIIIS, T. P. DEBCHEIIKO, A. 1. Inlet flow field simulation techniques for Equipment for qas-flame heating OF heat- resistant enqine/compressor testina materials durinq fatiqne testina A71-12909 ~7i-iooai COIIKR. K. 6. DBIPSTEB, J. B. Operational aspects of advanced avionics LAUS fliqht demonstration A71- 10506 A71 - 11662 COOPER. D. C. DEHISOV. P. S. The estimation of loss of echoinq area with very Threads used in the aircraft industry- Tandbook hiah resolution radars 171-12723 A71-11643 DICKEY. L. D. COOPER, P. P.. JR. solid-state switchina for aircraft electric ETaluation of tbe lonqitudinal static stability of systems the US-2A aircraft A71 - 11621 [ AD-710722 J 871-1 0563 DIHI. D. CORIIELL. D. Fabrication techniques of compact fluidic coqtrol Grumman Prepares the F-14A for its first fliqht equipment for aerospace enqines A7 1- 12050 A71 -1 1654 COUPRT, G. DIREIIZI, J. 6. Pressure field induced on a lifting surface by an Inlet flow field simulation techniques for isotropic atmospheric turbulence engine/compressor testina [ICAS PAPER 70-301 A71-11019 All-12909 COX, R. A. DOLIOTEIIKO, I. T. A comparative study of aircraft qust analysis Aircraft power plants- Systems and devices procedures i171- 12722 All- 10152 DOBH, 1. CRAIIK. 8. K. aodern ioinins methods in the aircraft and Eeasurement of clear air turbulence in the lower aerospace industry stratosphere nsinq the Billstone Ail1 I-band 1171-11650 radar DOU6EEBTT. J. B. A71-10567 nodern surveillance of aircraft inteqrity CRAT, E. C. 171-1 1020 PolTimides in advanced composites for aerospace

8-3 DOVIAK, R- J. PERSONAL AUTKOR INDEX

DOVIAK, R- J. [ NASA-TN-D-6067 1 N71-11004 Radiation from a dioole near a conductinq cylinder POUCKER, G. of Finite lenqth Introduction of the ECI! in the aeronautics A71-11167 industry DOHELL, E. n. N71-1 16U1 comparison of theory and exoeriment for nonlinear PRAY, J. flutter of loaded plates Carbon fibre in aviation A71-10940 A71-12488 DBAKE. n= n. FREERAN, D. C., JR. Technoloaical factors in short haul air ninC-run,iri iaveatiqaticn of a Jet transonrt transportation airplane confiquration with hiqh thrust-weiqht rAIAA PAPER 70-12871 1171-11700 ratio and an external-flow jet flap DUNAVANT, J. C. INASA-TN-D-6058 1 N71-10495 iiot air b-llcr? dpcelerntinn and recoverv svstem FRID, A. n. Patent utilization of conrinuous :tiel feeZ i:: 3 [NASA-CASE-XLA-06824-21 N71-11037 rotary-piston enqine with planetary motion of the rotor A71-12559 E PROBOESE, n. EDEU, n. s. Ground and building wall reqistrations of booms The use of C.S.M.P. diqital simulation lanquaqe in and noises caused by starfiahters and other manual fliqht control analyses sources A71-11787 N71-11035 EDGERTON, A. T. Snow and ice sensinq with passive microwave and qround truth instrumentation - Recent results, G South Cascade Glacier GALBREATR, A. N71- 11160 Terminal area airlines delay data, 1964 - 1969 ELKINS, A. C. N71-10366 Televised qraphic displays for steep approach- GALLINGTON, R. 1. to-landinq research Determination of realistic performance trade- offs A71- 1131 1 in the air-to-air role Final report ELLIS, R. A. AD-7104971 N71-10183 National intercity travel - Development and GARIER, A. C. implementation of a demand forecastinq framework The theoretical treatment of slowly oscillating Final report part-span control surfaces in subsonic flowN71-11013 r PB-192455 1 N71-10299 r NPL-AERO-13031 ERWIN, R. 1.. JR. GASAWAT, D. C. Time-synchronized approach control Airspeed influence on noise within fixed- and 171-12894 rotary-winq aircraft Research report, Jan. 1966 - Oct. 1969 [ AD-7113591 N71-10705 F GATES, R. P. PASSO. G. Visual Approach Slooe Indicator /VASI/ system for Experimental determination of Pressure lonq-bodied aircraft Final report, Jan. - May fluctuations on stationary blades of a hiah 1970 power axial-flow compressor r FAA-RD-70-76 1 N71- 11905 A71- 11024 GAUJE, G. The aerothermodynamic test centre of Problems involved in thp aoolication of niobium Modanf- Avrieux alloys to turbine blades IONBRA-NT-166 1 N7 1- 11470 A71-12939 PELLENZ, D. U. GEDEON, J. The hypersonic transport. - The technoloqy and the Improvements in fatique testino of sailolanesA71-11949 pot en tial [AIAA PAPEP 70-12181 A71-11302 GEDWILL, n. A. PERRARI. C. Evaluation of NiCrAl and FeCrAlY CladdinqS on Aerodynamic oroblems of re-ertry TI)-NiCr - Mach 1 burner riq tests at 2100 P rICAS PAPER 70-011 A71-11695 /1149 C/ PICATL, G. A. r NASA-TH- X- 529 161 N71-11426 On the relationship between small-scale wind GELL, n. shears and wind profile power spectra The fatique strenoth of nickel-base superalloysA71-10166 [NASA-TM-X-645521 N71-10240 FIEDLER. J. P. GERKARD, P. A hybrid frequency response technique and its Beryllium - An aircraft and soncecraft structural application to aircraft fliqht flutter testinq material A71-10228 A71-11539 PILIIONOV, V. A. GIESING, J. P. Studv of the interaction between plane supersonic Spanuise distribution of induced draq in subsonic off-desiqn iets and obstacles by the hodoqraph flow by the vortex lattice method method 1171- 12691 A71-10425 GILBERT. P. N. D. PIIK, D. E. A conflict prediction algorithm for use in N49 Larzac testinq under way procedural domestic airspace A71-12607 A71-11698 PINKLEIIAN, D. GILBERT, n. E. Determination of realistic performance trade- offs The use of rate qyroscopes in the free flioht in the air-to-air role Final reoort measurement of aerodynamic lateral force and r AD-7104971 N71-10183 moment coefficients PITZSII%IOIS, R. D. r!iSA-TN-1641 N71-11001 The status of federal involvement in short haul GILLILLAID, U. air transportation Studv Group on Leqal Aspects of Intermodal IAIAA PAPER 70-12861 A71-10875 Transportation The status of fedpral involvement in short haul N71-12119 air transoor t a t ion GIIOUX, J. J. N71-11076 A parametric study of adiabatic laminar boundary FLECANER, S. G. layer shock wave interactions by the method of Jet-wake effect of a hiqh-bypass enqine on Lees-Reeves-Klineberq winq-nacplle interference draq of a subsonic [ VKI-TN-60 1 1171-11017 transport airolane

B-4 PEESOIAL AUTEOB IIDEI EIGASEIGUCEI, I.

GIEOL, A. P. [ AD-7120171 17i-ii03i Approximate method of calculating the minimum GEISAFFE. S. J. suction rate preventing boundary layer Eraloation of RiCrAl and PeCrAlY claddings on separation for a semibounded iet TD-1iCr - nach 1 burner rig tests at 2100 P 1171-12553 /1149 C/ GLASS. E. B. r RASA-TB-X-52916j 1171-11 426 Penetration of sonic boom energy into the ocean - GUIEIIIUK. V. S. An experimental simulation Final report Construction and design of high-pressure balloons C AD-71 1963] 1171-10094 made from fiberglass-reinforced plastics GOLDEIESCE, J. A71-11048 Radiation from a dipole near a conducting cylinder GWIUIIG. J. P. of finite length Skynet traffic systems 171-11167 A71-12439 GOLDIAI, A. J. GUSTAFSOI, P. B. Analysis of a capacity concept for runway and Ristory of AACA/EASA rotating-wing aircraft final-approach.. Dath airsuace research, 1915-1970. IV A71-12893 A71-11377 GOLDIAI. D. GUIOT V/STOL mode descriptions Utilization of a niobium alloy in the fabrication [PB-190940] 171-1 io27 of a hypersonic vehicle Air mode service analysis in the Northeast All-12935 c'orridor r PB- 190935 1 an-11029 GOLDSTEII! A. P. H Acoustic and aerodynamic performance of a BACKER. P. T. 6-foot-diameter fan for turbofan enqines. 2 - neasurement and analysis of liqhtninq induced Performance of QP-1 fan in nacelle without voltaqes in aircraft electrical systems acoustic suppression I NASA-TN-X-52906 J N71- 10391 rRASA-TN-D-6080] 1171-1 1882 BACKIAI, 1. E. GOBIAH. E. P. Polyimide/boron reinforced plastic structures Electric thrust control system for supersonic [ SnE PAPER En-70-133 J A71-11263 transport power plant BALL, D. J. [SAE PAPER 700819 J 171-1 1546 Observations of three-dimensional flow patterns GOUILLOU, E. obtained during stall development on aerofoils, Synchronization of distant stations by simple and on the problem of measuring two-dimensional overfliqht - operation synfral characteristics Progress report [OBERA-1T-165 J 1171-1 1681 [ BPL-AERO-1309 ] 171-1 i 014 GOZLAI, A. BiiiEL, 2. Application of corruqated core sandwich structures A system analysis view of aerodynamic coupling to powerplant components A71 - 12687 171-1 1636 FIAEIOHD. A. D. GBAVIGIT, 1. Variable sweep aircraft Patent Situation of aerospace industry in the European [1ASA-CASE-XLA-O3659] 1171-1 1041 Communitr EAIEOlD, D. C., JE. A71-11676 A preliminary investigation of qas turbine GRAY, E. E. combustor modelling Mot-salt stress-corrosion of a titanium alloy in a A71-12852 dynamic air environment EABSEI, P. A71-12885 Electron beam ueldinq of hioh-aut7 rotatino pnaine 3BECE3KEA. A- V. parts Automaied device for conductinq fatique tests with 171- 11644 proqrammed load variation BAELIUG, K. A71-10409 Investiqaticn of maintenance systems for GBEEB, 1. commercial jet aircraft and the factors which Investiqation of heat transfer in base type have an effect on them supersonic laninar and transitional separated All-101 14 flows AABSCEBURGEB, E. E. r AD-7 10347 3 N71-10249 The use of digital simulation for the nonlinear GREGORT, n. analysis of an integrated actuator package Observations of three-dimensional flow patterns 171-11783 obtained durinq stall development on aerofoils, BASEIIIOTO, S. and on the problem of measuring two-dimensional Uechanical deqradation of aeroplane materials by characteristics Progress report their fatigue and its detection. I [ BPL-AERO-1309 J 1-11-11014 A71-11395 Low-speed aerodynamic characteristics of NACA 0012 EATPIELD, J. J. aerofoil section, includinq the effects of Televised graphic displays for steep approach- upper-surface roughness simulating hoar frost to-landinq research [ APL-AERO-1308] 171-1 1016 171-11311 GREGOBT, E. P. EATSCEEK. E. A traffic sample for air traffic control model A reliable hiqh temperature transducer for enqine evaluation vibration measurement 171-10163 A71-12911 GREY-PILSOI. P. V. EAUER, B. Comparison of calculated pressure distributions on Determination of wheel trajectories some swept winqs with Warren 12 planform at All-11641 subsonic speeds EEEDRICK, R. C. [ RLR-TN-T-189 1 171- 110 15 Electronic flight control is getting set to take GRIGA, A. D. Off Influence of the aspect ratio of guide vanes on A71 - 10825 the characteristics of axial-flow compressor EEBIIET. A. S. staqes with small aspect-ratio vanes Preliminary design of structural components in A71-12558 carbon fibre reinforced plastics and metals GEISOEEIKO. IA- ~.I- 171-12910 Construction and design of hiqh-pressure balloons EIGASBIGUCBI. E. made from fiberglass-reinforced plastics The track-while-scan technique for search radar. 171-11048 I - Acquisition and processinq of aircraft radar GRIIGOBTEI, I. I. data Point and route temperatures for supersonic All-11392 aircraft

B-5 mnz, E. E. PEESOlAL AUTBOE INDEX

The track-while-scan technique for search radar. I1 - The theoretical analysis of aircraft trackinq by the application of Kalman filter J A71-11393 JAEGEE, R. EIUZ, E. E. Dynamic aspects of cockpit temperature control on western reqion short haul air transportation combat aircraft proqram. Volume 1 - Demonstration program plan A71-10270 Definition phase report, Jul. 1970 JASLOU, E. [ ATR-71-/7190/-l-VOL-l] N71-10279 Nonaffine similarity laus inherent in Aewtonian sIB;P;, I. i-p-ct thecry I Research on suept-back blades laid between A71-10948 parallel walls. I1 - Experimental research on JENIINGS, E. Clark Y 8 percent and NACA 6509 blades with strenqtheninq of paveaents aspect ratio of 2.0 A71- 12169 .^___ -^----I- ~lI-ILDUo UUIIADDL~, -n. -r. EOAG, P. C. Introduction and summary /Iras/ IPR experience with unpowered, low-lift-draq- A71-11659 ratio landinq approaches Aircraft performance benefits from modern control A7 1- 10110 systems technology AOLLOUAT, E. B. [AIAA PAPER 69-7671 A71-12683 Aircraft performance benefits from modern control JOEISON, E. I. systems technology Gravity stabilized flying vehicle Patent I AIIA PAPER 69-767) A71-12683 [NASA-CASE-RSC-12111-1] N71-11039 nom, R. J. JOHISOI, E. 1. Iechanization and test of DRE updated inertial Use of the computer in design of gas turbine 1171-10507. ... mainshaft seals for operation to 500 ft/sec /122 EOLIES, T. R. m/sec/ nodelinq an air traffic control environment B71-10479 A71-10979 Design study of shaft face seal with self-acting EOLT, J. K. lift augmentation. 2 - Sealing daa Desiqn and construction of aircraft pavements in [ NASA-TN-D-70061 N71-11579 unusual conditions JOEISTOU, J. E. A71-12170 Hot-salt stress-corrosion of a titanium alloy in a AOBDO, A. dynamic air environment aechanical deqradation of aeroplane materials by 171-12885 their fatique and its detection. I JONDA, U. 171-11 395 Development and test of carbon epoxy fibre AORSTIAN, C. C. coaposite for helicopter tail rotor applications Sphere draq in near-free-molecule hypersonic flou A71-12477 A71-10969 JONES, A. P. RORWITZ, D. 1. Comparison of calculated pressure distributions on Nan-machine considerations in system desiqn for some suept wings with Warren 12 planform at all-weather, low-level naviqation subsonic speeds A71-10515 [ NLR-TN-T-1891 171- 11015 EUNTER, n. w., 11 JOUES, C. 1. The hypersonic transport - The technology and the solid-state switchinq for aircraft electric potential systems [AIAA PAPER 70-12181 A71-11302 A71 - 11627 AOSSEIB, I. JOUES, I. S. P. Experimental investiqation of the trajectories and Influence of retarded time on jet noise velocities of solid particles entrained by fluid A71- 1 1468 flows in cascade nozzles JOUITT. e. [ AD-711 121] 171-10546 Non~metallicaircraft materials A71-12299 EUTCEINS, A. 5. A synthetic aperture at 10.6 microns A71-12044 K KADUSEIA, I. I Design of an intermittent, sinqle jack flexible IIDA, T. nozzle supersonic wind-tunnel for aach numbers The track-while-scan technique for search radar. 1.5 to 4.0 I - Acquisition and processinq of aircraft radar [ TAE-86 1 N71-10478 data KALITIEVSKII, 1. 1. 1171-11392 Influence of forward speed on the aerodynamic The track-uhile-scan technique for search radar. characteristics of an air-cushion vehicle I1 - The theoretical analysis of aircraft A71-12551 trackinq by the application of Kalnan filter KALIAU, T. P. A71-11393 Spanwise distribution of induced drag in subsonic ISOGAI, I(. flow by the vortex lattice method An experimental study on the unsteady behavior of A71-12691 a short bubble on an airfoil durinq dynamic KANNAIUELLEE, G. Stall with special reference to the mechanism of Light turbine helicopter Dornier DO 132 the stall overshoot effect A71-10465 I kD-711 540 1 1171-1 1005 KAEIAPPA ITATA, ,S. Discrete element approach to flutter of skew A simole model of the pseudo-shock mechanism panels with in-plane forces under yawed A71-11870 supersonic flow ITO, T. A71-10939 Superpressure balloon and precise pressure KASS, G. J. radio-sonde system for the research of vertical LAas test vehicle modification and system tests air-motion A71-11661 A7 1- 1 24 2 0 KAWATA, K. IVES, D. C. lechanical degradation of aeroplane materials bv subcritical flows over two dimensional airfoils by their fatigue and its detection. I a multistrip method of inteqral relations A71-11395 (RE-393J1 N71-10581 KEUTOB, G. C. Technoloqical factors in short haul air transportation [AIAA PAPER 70-12871 A71-11100

B-6 PEBSOIAL AUTBOB IIDEX UAO, J.

KEABXP. E. E. LEISEBB. 1. 1. Beat exchanqe and drag in a circular pipe during Air transportation constraints - Their implication laminar flou of a gas uith variable properties. on short haul 11 - Results of calculations at constant wall ~AXAAPAPER 70-13091 A71-10486 temperature LEVEBAIT. 6. B. A71-12192 The fatigue strength of nickel-base superalloys KIEPP, D. 1. A71 - 10166 Radiation from a dipole near a conductinq cylinder LEVIPSKT. B. S. of finite length A method for calculating helicopter vortex paths A71-11167 and wake velocities Final reoort. Uov. 1968 I~. - KIIIPPLB. B. S. Dec. 1969 Experience vith static dissipator additive in [ AD-7106943 1171-10470 aviation fuels LEWIS. T. S. A71-12300 A synthetic aperture at 10.6 microns KOBASEI, I. A71-12044 Dynamic stability test in a transonic vind tunnel LBlIS. P. vith a rotary system Development of procedures for vectoring aircraft IBAL-TR-196> 1171-1 1009 around thunderstorms KOKUEKO. V- S. 1171-10587 Antenna radomes of flight vehicles LITTIIOT. A. 1. 171-11 322 Influence of the test time and contact stresses on KOLPAKOTA, I. P. the antiuear properties of jet fuels under Synthesis of selective multidimensional invariant conditions of rolling friction systeas 171-12570 A71-10718 LIU, C. E. K0.0, 1. Uumerical investigations of an airfoil in a Dynamic stability test in a transonic vind tnunel nonuniform stream uith a rotary system A71-12680 IlAL-TU-196 ’] 871-1 1009 LIVIIGSTOUE, J. 8. KOTALEVSKII, T. T. The role of man in the military Airlift Command Influence of the aspect ratio of guide vanes on A71-10504 the characteristics of axial-flow compressor LO. c.-F. stages with small aspect-ratio vanes Upuash interference on a jet flap in slotted 1171-12558 tunnels KOZLOT, 1. ?. A71-12690 Laminar boundary layer on a wina and a body of LOEUAP. 8. B. revolution in the presence of blorina Iniestigation of ihe effect of iea&na edge on the A71-12554 aerodynamic characteristics of a 70 deq svept KBAUBB, C. delta uing Final scientific reuort. nov. 1969 - The flor throuqh planar qlinder lattices in the Jul. 1970 range of transonic velocities [ AD-7120871 171-11007 1171-10108 LORIS, U. E. KBAUSE, E. Transonic bnffet characteristics of a 60-deu-. slept numerical investigations of an airfoil in a vinq uith design variations nonuniform stream A71 - 12679 171-12680 LUCAS, J. 6. KEATWJ. 1- Z. ACOUStlC and aerodynamic perforaance of a Aircraft pover plants- Systems and devices 6-foot-diameter fan for turbofan engines. 2 - 171-12722 Performance of QF-1 fan in nacelle without KBITSUK, A. A. acoustic suppression Construction and desiqn of hiqh-pressure balloons [NASA-Tn-D-6080] 1171-1 1882 made from fiberglass-reinforced plastics LUDWI6, 1. P. A71-11048 Use of the computer in desiqn of qas turbine KUSSOT, U. I. mainshaft seals for operation to 500 ft/sec /122 Sphere draq in near-free-molecule hypersonic flou m/sec/ A71-10969 1171-10479 Design study of shaft face seal vith self-acting lift auqmentation. 2 - Sealiuq dam L IBASA-TA-D-70061 B71-11579 LAEABBE, J. U. Gas-film seal, type A. appendix A GOniO8etrJ by laser gyro 1171-12036 A71-12924 oil-film seal, type E, appendix B LAI6EBEUI. P. S71-12037 Air traffic control by satellites - End of the 1970 test proqrams A71-10748 M LAB6UIEB. E. UACBAE, A. 8. Experimental determination of pressure Current British pavement desiqn fluctuations on stationary blades of a hiqh A71-12168 power axial-flov coupressor UAEDA, E. A71-11024 An ultrasonic altitude-velocity sensor for LAXIEBSTTI. B. airplanes in the vicinity of the qround. I Fabrication techniques of compact fluidic control 1171-11624 equipment for aerospace engines UAIDLI, D. 1. 1171-11654 Effect of nozzle lateral spacing on afterbody drag L16ElDBE. E. and perforuance of tvin-jet afterbody models Computation of aircraft vinq and turbomachine or vith converaent nozzles at Mach numbers OD to helicopter blade airfoils for the exact 2.2 compressibility la. [ 11ASA-TM-X-20991 1171-10276 A71-11022 UAL?OIS. J.-P. LEBBIAI, D. B. Calculating the kernel of the liftiuq surface The theoretical treatment of slouly oscillating inteqral equation in nnsteady subsonic flov Part-span control surfaces in subsonic flov A71-11020 r HPL-AERO-I~~~I 117 1-1 1013 UAlUALI. 8. LEIS. E. The project DIOSCWRES - General introdnction to Evaluation of some neu aircraft structure the system materials by methods of fracture uechauics 1171-1 1768 171-11 540 IIARTEL, C. R- PERSONAL AOTAOR INDEX

! nonuniform stream A71-10359 1 A71-12680 IIIDDLETON, P. I IIARTEL, C. R- RB.211 - Transatlantic bridaehead 1 An evaluation of the static charqe reducer for A71-11682 I reducing electrostatic hazards in the handlina IIILELLI, R. J. of hydrocarbon fuels Summary report, Jun. - A method for determining a conceptual solution to I NOV. 1969 ENSURE 301 AD-71 23681 N71- 11 876 f AD-7109U81 N71-10564 IIARTIN, P. R. IIILLER, C. 0. n-lr:-L CULLTIIL DLILLaI. pave,=eiit :esiqn ~yste;s approach tc 2ccident inrestioation A71-12168 N71-10115 IIATAIEO, G. MILLER, G. E. Ground and building wall reqistrations of booms New lonqitudinal handlinq qualities data - Carrier and noises caused by Starfiqhters and other approach ..I. 7L-lL) sources iAInii PAP68 69-897j ",, -.I-".Y N71-11035 HILLS, R. 1. IAYER, R. A. Undercarriage effects on /a/ riqid pavements /b/ Study of the performance characteristics of the flexible pavements Bendix type DRA-12 airborne Doppler radar system A71-12164 Final report, Feb. - Oct. 1970 IIRONOV, 0. E. r FAA-NA-70-50 1 N71-10394 Equipment for gas-flame heating of heat- resistant MATES, J. P. materials durinq fatique testinq Transonic buffet characteristics of a 60-deq swept 1171-10041 wing with desion variations IIIYAZAWA, 1. 1171-12679 Dynamic stability test in a transonic wind tunnel IIAZELSKY. E. with a rotary system Investiqation of the effect of leadinq edqe on the T NAL-TR-196 ] N71-11009 aerodynamic characteristics of a 70 deq swept IIZOIIACAI, II. delta winq Final scientific report, NOV. 1969 - The track-while-scan technique for search radar. Jul. 1970 I - Acquisition and processinq of aircraft radar [ AD-7120871 N71 - 11007 data HC DANIEL, T. J. A71-11392 Parametric stuay of natural frequencies of The track-while-scan technique for search radar. skin-strinqer structure I1 - The theoretical analysis of aircraft TAD-7113831 N71-10734 trackinq by the application of Kalman filter IIC KIBBIA, A- A. A71-11393 Development of mainshaft seals for advanced air IKAITARIAN, A. 1. breathinq propulsion systems, phase 2 Final Approximate method of calculatinq the minimum repor? suction rate preventinq boundary layer r NASA-CR-72737 1 N71-12035 separation for a semibounded jet nc LYNN, J. n. A71-12553 Passenqer demand and modal split models - ROORE, II. T. Calibration and preliminary analysis Inlet flow field simulation techniques for r PB-1909461 N71-11021 enqine/compressor testinq nc NALLY, 5'. D. A71-12909 FORTRAN proqram for computinq coordinates of IORALDI, G. circular arc sinqle and tandem turbomachinery Developments of pavement design both rigid and blade sections on a plane flexible on the continent of Europe [ NASA-TN-D-60201 N71-10411 A71 -121 67 FORTRAN proqram for calculatinq aerodynamic forces IIORISSET, J. from pressure or velocity distributions on blade The Bertin company proposes a new formula for a sections short takeoff aircraft TNASA-Tfl-X-21231 N71-10467 A71 - 10749 IICPADDEN, 3. G. The Hiraqe 'nilan' The impact of helicopter operations on air tra€fic A71-12740 control in thp 1970's IIOROZENKO, 0. V. A71-12892 Threads used in the aircraft industry- Aandbook IICGREGOR, 0. W. 1171-12723 Draq of rectanqular cavities in supersonic and IOBROW, D. 1. transonic flow includinq the effects of cavity Electric thrust control system for supersonic resonance transport power plant A71-10931 [SAE PAPER 7008193 A71-11546 IIEIER. 1. IIORROW, T. R., JR. Snow and ice sensinq with passive microwave and Development study for a VPR heliport standard qround truth instrumentation - Recent results, liqhtinq system Final report South Cascade Glacier [AD-7109821 N71-10682 N71-11160 IOOLTON, I. IIELBKA, A. A. Technology for better all-weather landings Electrochemical machininq promise and realisation A71-12275 T SME PAPER MR-70-1933 A71-11253 IOELLER, L. J. Advanced manufacturinq technoloqy in modern jet Pilot and aircraft auqmentation on the C-5 enoines A71-12684 N71-11627 UOPPANG, J. IIELLOR, A. 1. Air transport A preliminary investiqation of qas turbine A71-12368 combustor laodellinq IIORAI, A. A71-12852 Research on swept-back blades laid between IBLIIIK, R. E. parallel walls. I1 - Experimental research on Subcritical flows over two dimensional airfoils by Clark Y 8 uercent and NACA 6509 blades with a multistrip method of inteqral relations aspect ratio of 2.0 rQE-393J1 N71-10581 A71-12606 HEAGENAAOSER, J. V. IIORPAT, C. R. Proposed nuclear maqnetic resonance method of Comment on 'A nethod for extractinq aerodynamic determining the aromaticity of hydrocarbon fuels coefficients from free-flight data' AD-711892 1 N71-11890 A71-10971 IETER, A. Insurance- and liability questions in connection IIOSKER,Traininq G. for low visibility landings with the hijacking of aircraft, acts of A71-10022 sabotage, and armed attacks aqainst an aircraft I PBBSOIIU AUTEOE IIIDBX PICEOIE [ AD-7113131 A71-11139 i N IIABSETE, E. 1. P Low-speed wind-tunnel investiqation of a series of PAKBIIDOBF. E. twin-keel all-flexible parawings system analysis of future jet and fan propulsion [ AASA-TA-D-5936 J 871-10052 systems for vertically starting coamercial IAGAnATSU. E. T. aircraft Aeat transfer on a flat plate in continuum to A71-10115 rarefied bypersonic flows at nach numbers of PAM, I. S. 19.2 ana 25.4 Application of Whitham's theory to sonic boom in [ AASA-CR-16921 1171-1 0867 the mid- or near-field IABASAKA. T. A71-10956 Research on swept-back blades laid between PAPBOCKI. T. E. parallel walls. I1 - Experimental research on visual aids for secondary airports Final report, Clark Y 8 percent and AACA 6509 blades with Sep. 1968 - Hay 1970 aspect ratio of 2.0 [ FAA-AA-70-513 1-11-1 1474 A71-12606 PABLETT. 1. P. IIAEDI. 6. wind-tunnel investigation of a jet transport Fabrication techniaues of comoact fluidic control airplane confiquration with high thrust-weight eyuipment for aekospace engines ratio and an external-flow jet flap 1171 - 11654 [ RASA-TB-D-6058] 1171-10495 AEIABB. 6. E. PATTEBSOII, J. C., JE. Servosystem design of a biqh-response slotted- Jet-wake effect of a bigb-bypass engine on plate overboard bypass valve for a supersonic winq-nacelle interference drag of a subsonic inlet transport airplane [ NASA-TA-D-60811 1171-11061 l NASA-TA-D-60671 1171- 11004 UBLSOA, J. R. PAUL. C. E. On turbine enqine development policy The development of small gas turbines for aircraft 1171-11180 auxiliary power AI, E. E. 1171-10751 Research on the flutter of axial-turbomachine PIULOVICE, F. J. blading Semiannual status report study of turbojet combustor dynamics using I I AD-7107941 1171-10562 sweep-frequency data IIISEI, T. [AASA-TR-D-6084 J B71-10982 Dynamic stability test in a transonic wind tunnel PCEBLKO. I. G. b with a rotary system neteorological conditions of supersonic aircraft I r AAL-TR-196 J 1171-11009 fliqhts IiIXOII. c. 1. A71-12840 Quantification of the noisiness of 'approaching' PBIIKOV, A. 1. and 'recedinqt sounds Equipment for gas-flame heatinq of heat- resistant A71-10345 materials during fatigue testinq t A71-10041 PEEACCEIO, A. A. 0 Kinetic theory analysis for the flowfield of a OCOIIIIOB. J. F. tuo-dimensional nozzle exhaustinq to vacuum A method for determining a conceptual solution to [AIAA PAPER 69-6581 A71-10932 mrcnov ?n* i,',nau r AD-710948 1 1171- 10564 Utilization of a niobium alloy in the fabrication ODGEBS. J. ~f a Ly?ersonic vehicle Air Pollution by qas turbines - Is control 871-12935 possible PEEKIASOA. E. E. 1171-10820 Avoidinq collisions in a timely manner OETA, S. A71-12835 Superpressure balloon and precise pressure PEEBIA DE ERICEAIBAUT, C. radio-sonde system for the research of vertical Observation and measureeent of ground visibility. air-motion Automatic calculation of the visual ranqe of 1171-12420 airport runways OIIDA. I. mi-10118 Detailed measurements in the transition resion of PERRY, 6. 1. a two-dimensional wake Collision avoidance systems A71-10132 A71-10753 OBBILLY. C. I.. PERSEIA, P. P. Observations of three-dimensional flow patterns utilization of continuous fuel feed in a obtained during stall development on aerofoils, rotary-piston engine with planetary motion of and on the problem of measuring two-dimensional the rotor characteristics Progress report 171-12559 [APL-AERO-1303] ~71-11 01 4 PESCEKB. W. Low-sped aerodynamic characteristics of AACA 0012 Description and capabilities of a travelinq wave aerofoil section, incloding tbe effects of sonic boom simulator upper-surface rouqhness simulating hoar frost [ NASA-CR-16961 n7i-11422 [APL-AERO-1308] A71-11016 PETREIIKO. m. T. OBLIK-BUEClCEII&IIII. K. J. neteorological conditions of supersonic aircraft Dynamic viscous pressure interaction in hypersonic fliqhts flow 1171-12840 r LR-5351 1171-11003 PETTIT. U. T. OSEORJ.u. n.. Beat transfer on a flat plate in continuum to Effect of simulated downstream flow blockaqe doors rarefied hypersonic flows at nach numbers of on the performance of an axial-flow fan rotor 19.2 and 25.4 NASA-TA-D-607 1 ] 1111-10537 [ NASA-CR-16921 11-11-10867 OTELIAG. W. 1.. JR. PETUKEOV, E. S. Application of differential qame theory to Heat exchauae and drag in a circular pipe durina pursuit-evasion problems of two aircraft laminar flow of a qas with variable properties. r AD-71 10551 1171-10328 11 - Results of calculations at constant wall OUASTBD, E. J. temperature TIARA light aircraft engines - A new qeneration A71-12192 [SAE PAPER 7002051 A71-10129 PICEOIR I OWCZABBK, J. A. Utilization of a niobium alloy in the fabrication A study of flow from two planar nozzles of a hypersonic vehicle

E-9 PIERRE, I. PERSOIAL AUTEOR IIIDEI

A71-12935 aeronautics industry PIERRE, I. 1171-11637 The aerothermodynamic test centre of RAO, J. S. Iodane- Avrieux solution of the equations of motion of [ ONERA-AT-166 1 1371-11470 coupled-bending torsion vibrations of turbine PIIKEL, E. blades by the method of Ritz-Galerkin on turbine enqine development policy A71-11014 A71-11180 RASSAI. P. R. PIIISKER, W. J. G. National intercity travel - Development and Direct liii control ieple=eot=tion of 5 demenn forecasting framework 1171- 10754 Final report PLUIER, J. A. f PB-1924551 1171- 10299 Measurement and analysis of lightning induced RAUCE, I. C. voltaqes in aircraft electrical systems Passivation of metal aircraft surfaces Final ..-- .^__~ [ NASA-TI-X-5LYUb J NII-IUSY I report, i

B-10 PEPSOIAL AUTHOR IlDEl SEIZE, C. C.. JR.

PWBII. A. I. 171-11035 Considerations for the hybrid computation of SEAE, C. 6. traiectories for missiles and aircraft Discrete element approach to flutter of skev 1171-11794 panels vitb in-plane forces under yaved BWSCXEL. J. F. sapersonic flou Effect of nozzle lateral spacinq on afterbody drag A71-10939 and performance of tvin-jet afterbody models SEAPIRO, B. J. vith convergent nozzles at Each numbers up to State airport system inventory - An inventory of 2.2 the existing airport system in Rhode Island [ UASA-l'B-X-2099] 1171-10276 [PB-189332] 171-1 1028 RWSlAlC. 1. SEAl, E. 1. Diqital fliqht control and landing system for the Computerized aerodynamic optimization of aircraft CB-46C helicopter Final report propellers [ IIA SA-CR- 11 1024 1 1171-1 0297 [ AD-7103561 1171-10122 SHEEP. B. E., JB. Heat transfer on a flat plate in continuum to S rarefied hypersonic flows at Rach numbers of SAPAVAlAEWTTOO, E. I. E. 19.2 and 25.4 A rapid method for the matching of two-spool [ RASA-CR-16 921 871-10867 turboiets SBERIAIDAUOV, 6. B. A71-10821 Inviscid ideally conducting fluid flov past a thin SATO, B, foil in a transverse magnetic field Detailed measurements in the transition region of 171-12629 a tuo-dimensional vake SEIWKAB. A. I. A71-10132 Construction and design of high-pressnre balloons SATTLEP, 1. J. made from fiberglass-reinforced plastics A comparison of high energy radioqraphic ~71-i1048 techniques for large diameter titanium billets SHIVERS, J. P. 171-11639 Wind-tunnel investigation of various small- scale SAWYER, F. B. rotor/ving configurations for ITOL composite Effect of unsymmetrical nose-bluntness on the aircraft in the cruise mode stability derivatives of a 10 leg cone at Each [ IIASA-TR-D-59451 A71-11025 14 Final report SBOSBI11. IO. 5. I AD-7 11921 3 1171-1 1008 utilization of continuous fuel feed in a SCPEP. s. 8. rotary-piston engine vith planetary motion of Bot air ballon deceleration and recovery system the rotor Patent A71-12559 f IIASA-CASB-rlA-06824-21 S71-1 1037 SHIE, 1. SCBEBREB. E. Digital flight control and landing system for the Synthesis of future high lift systeas CH-46c helicopter Final report I SAE PAPER 700811 1 171-11545 [ UASA-CR- 111024 1 1171-10297 SCHIFF, 1. B. SILVBE, B. Results from a nev vind-tunnel apparatus for optimization techniques in aircraft confignration studying coning and spinninq motions of bodies design of revolution [ AD-7114107 1171-11023 A71-10930 SIEEOIS. J. E. SCIIIIIDT. 8. A hybrid frequency response technique and its Requirements for ejection seat systems application to aircrair iiiqbi i1uCtsi Lestkiq IEAE-LIB-TBA1S-14711 1171-11042 A71-10228 SCBOIIELD, B. 1. SXEOI, A. IFR experience vith nnpovered, low-lift-drag- Industrial policy at the Centre national d'Etudes ratio landing approaches Spatiales €171-10110 171-12069 SCBOIImD, 6. S1101, E. A reliable high temperature transducer for engine x-ray fluorescence analysis as an aid to vibration measurement production and repair of aircraft engines A7 1- 12911 171-11641 SCBPADEE. J. 8. SI11AISKlI. B. 1. Cooperative Doppler radar system Patent Equipment for gas-flame heating of heat- resistant [aASA-CASE-LAR-l04031 1171-11766 materials during fatigue testinq SCBPAE. S. A71-10041 A real-time 6 degree of freedom aircraft SISTO, F. simulation vith SL-1 Research on the flutter of axial-turbomachine A71-11786 blading Semiannual status report SCEUETZ, 1. AD-7107941 1171-10562 Evaluation of some nev aircraft structure SIVASBElXO, T- I. materials by methods of fracture mechanics Aircraft pouer plants- Systems and devices A71-11540 A71-12722 SCWLTZ, s. SIVBLLS. J. C. The diffraction of shock vaves at sharp corners Aerodynamic design of axisymmetric hypersonic A71-10109 rind-tunnel nozzles SCHOI. 8. J. [AIAA PAPER 69-3371 171-11578 Cold-air investigation of a turbine vith SKUBACHEVSKII, 6. 5. transpiration-cooled stator blades. 2 - Stage Aviation gas turbine engines. Construction and performance vith discrete hole stator blades desiqn of parts [UASA-Ttl-X-2123] 1171-11010 [AD-7117571 A71-10853 SEARS. S. 3. SLEIUA1. 1. C., JB. The aerodvnamic noise of small-perturbation Control for flexible paravinq Patent subsonic flous [ IIASA-CASE-XLA-069581 1-11-11038 A71-12377 SLOOFF. J. 1. SE611ER. A. comparison of calculated pressure distributions dn Investigation of heat transfer in base type some swept rings vith Warren 12 planform at snpersonic laminar and transitional separated subsonic speeds flovs [ 11LR-TW-T-l89] 171-1 1015 [ AD-7103471 1171-10249 SEITR. c. c., Jp. SBTDM.. D. uind-tunnel investigation of a jet transport Ground and building uall registrations of booms airplane confiquration with high thrast-weight and noises caused by Starfighters and other ratio and an external-flov jet flap sources [ 1ASA-TII-D-6058] 1171-low5

B-11 SIITA, E. R. PERSONAL AUTAOR INDEX

SIITA, E. n. SYAA, S. R. Airlines maintenance model Flyaway seat A71-llR09... [AD-7116421 171-1 1022 SIITA. R. A. SYIAART. J. n. Compressible laminar boundary layer on a cone at The promise of the supersonics hiqh anqle of attack [AIAA PAPER 70-12171 A71-11248 171-10926 SYION, R. J. snoLIA, A. The influence of the Concorde powerplant operatinq Nicrobioloqic corrosion conditions on the desiqn of the Olympus 593 fuel [ an-717103] N71-!1F(UR ao3 oil systeln SOCOLESCU, R. C. N71-11653 Supersonic flow around a circular cone equipoed SIRE with cross-shaped winqs Utilization of a niobium alloy in the fabrication A71-11958 of a hypersonic vehicle rnr.rno-.n 0 n " 7: -:2935 aYY',.,L'LI.\nn, Y. LI. _. Discrete element approach to flutter of skew SZANCA, E. I. panels with in-plane forces under yawed Cold-air investiqation of a turbine with supersonic flow transpiration-cooled stator blades. 2 - Stage A71-10939 performance with discrete hole stator blades SOIRERS, D. E. f NASA-TN-X-21231 N71-11010 Fire protection tests in a small fuselaqe-mounted SZECHENYI, E. turbojet enqine and nacelle installation Final The response of, and the acoustic radiation from report, 1965 - 1970 panels excited by turbulent boundary layers r FAA-NA-70-41 1 N71-11018 Technical report, 1 Dec. 1966 - 30 NOV. 1968 SPEAKNAN, E. R. IAU-7lobsbj N71-10386 Fatique life improvement throuqh stress coininq SZUCA, J. 8. methods Study of turbojet combustor dynamics usinq A71-10170 sweep-frequency data SPEARMAN, n. L. r NASA-TN-D-6084 1 N71-10982 Translatinq horizontal tail Patent r NA SA-CAS E-XLA- 0880 1- 1 3 N71- 11043 SPEAS, R. D. T Noise reduction - A must for air transportation TABAKOPP, Y. oroqress Experimental investigation of the trajectories and 1171-10819 velocities of solid particles entrained by fluid SPENCER, P. P. flows in cascade nozzles Desion and construction of aircraft pavements in [AD-7111211 N71-10546 unusual conditions TATTELIAN, P. 1171-12170 Point and route temperatures for supersonic STAATS. E. B. aircraft Improvements needed in the manaqement of aircraft [ AD-7120171 N71-11031 modifications. Department of the Army TAYLOR, E. S. /B-157373/ Comptroller General's report to the Evolution of the jet enqine Conqress A71-11181 N71-10287 TAYLOR, R. J. STAICU. S. Scale leuqth in atmospheric turbulence as measured Considerations on the wave draq of a delta thin from an aircraft winq with leadinq edqe separation A71-10859 A71-12408 TEIIPLIN, R. J. STALLINGS, R. 1.. JR. Aerodynamics low and slow An approximate method for Predictina oressure A71 -1 0818 distributions on blunt bodies at anale of attack TEPEAITSYN, N. P. rAIAA PAPER 70-2081 A71 -1 1580 Determination of the cross-sectional dimensions of STEFAN, K. load-carryinq elements of delta winqs from the An inflatable restraint collar for balloons static strength and weiqht conditions A71-11821 071-12562 STERLING. T. S. TESSARZIK, J. I. Investiqatina an aircraft disaster Flexible rotor balancinq by the exact point- speed A71-10456 influence coefficient method Final report STEWART, D. A. NASA-CR-727741 N71-10021 Sphere draq in near-free-molecule hypersonic flow TAONAS. J. A. A71-10969 Thermal coatinq of aondola payloads STEWARTSON, K. rNYo-3747-12] N71-10496 On supersonic laminar boundary layers near convex TAOIPSON, G. 0. corners LAMS fliqht control system analysis and desiqn A7 1- 10461 A71-11660 STRAND, T. TAURIAN, P. E. A method for calculatinq helicopter vortex paths The status of federal involvement in short haul and wake velocities Final report, Nov. 1968 - air transportation Dec. 1969 [AIAA PAPER 70-12861 A71- 1 OR75 [AD-7106941 N71-10470 The status of federal involvement in short haul STRAP, P. L. E. air transportation Strenotheninq of pavements N71-11026 A71-12169 TINNBY, A. C. SURACE, G. Air transportation constraints - Their implication Sandwich structures in aircraft and space vehicles on short haul R71-11959 I AIAA PAPER 70-1309 1 A71-10486 SORGET, J. TOBAK, n. Aoloqraphic interferometry for the study of Results from a new wind-tunnel apparatus for transparent npdia studyinq coninq and spinninq motions of bodies f TP-851 1 N71-10407 of revolution SOSECBIKA, n. v. A71-1 0930 Flow field associated with the impingement of an TOIBOULIIN, A. overexpanded jet aqainst a cone Description and capabilities of a travelinq wave A71-10613 sonic boom simulator SOTAERLAID, J. P. r NASA-CR-16961 N71-11422 Electronic fliqht control is qettinq set to take TOIITA, Y. off A simple model of the pseudo-shock mechanism 171-10825 A71-11870

B-12 PEESOIAL AOTEOB IIIDEI TOOITGEAIIS. J. 1.

TOWIEIID. 1. E. WEISS, E. 6. Statics and aerodynamics of lifting decs rrators Air traffic control Quarterly technical summary rAIAA PAPER 68-9453 A71-10927 report, 1 nay - 31 Jul. 1970 TEICEET, J.-C. f AD-7116621 a7i-10737 The Thomson-CSP IEP validates the possibilities of WELDOI. S. J. the human pilot IDT techniques for airline maintenance inspection A71-10750 1171-12449 TSTGAITIUK. A. I. WELLS, C. E.

Laminar boundarv larer on a vinu and a bodv~ of I_ The fatigue strength of nickel-base superalloys revolution in the presence of-blowing A71- 10166

171-12554~~ WSLTE, 1. A. TOIIASEBV. 8. Z. ECE ianufacturinu process to produce aircraft Experimental study of rotating stall in hiqh- engine components pressure stages of an axial-flow compressor r SEE PAPER ER-70-2061 A71- 11252 A7 1- 11063 WEBLE; S. J. TTLEB. B. A. Incompressible laminar boundary layers on a Circulation control by slot suction on a circular parabola at anqle of attack - A studr of the cylinder - Preliminary measured force data separation point [ LR-530 1 n7 1-1 io02 1AD-7120841 a71-1 1519 SEITA~EE, E. P.- A new model performance index for engineering design of flight control systems UEEDA. I. [AIAA PAPER 69-8651 1171-12682 An ultrasonic altitude-velocitr sensor for WHITE, E. A- airplanes in the vicinity of-the wround. I Draq of rectangular cavities in supersonic and A71-11624 transonic flow including the effects of cavity resonance A71-10931 V WILK, K. E. TAISIIAW, A. E. Severe thunderstorm radar echo motion and related Threads used in the aircraft industry- Handbook weather events hazardous to aviation operations A71-12723 rESSA-Ta-ERLTa-ASSL-46] A71-10720 VAIT DTKS, S. WILLIAESOII, J. E. Extension of Goldstein's series for the Oseen draq Technology of manufacturing and advancement of of a sphere technology for turbine enqine coatings 171-12380 871-11635 1ASILEIIKO. A. T. WILLIAESOII, 8. G. Construction sn?i 3esinz cf hiqh-pressnre ballnnns .-:..-..c,,,,l;tion conticilb- 7 ~IVC-.-I =ULLIVU---AI-- on a CilcUldr made from fiberqlass-reinforced plastics cylinder - Preliminary measured force data A71-11048 r 113-530 1 mi-11002 VESTESS. C. S. PILSO~, J. w.* Comparison of theory and experiment for nonlinear Autoland all-weather progress flutter of loaded plates 1171-12274 1171-10940 PISEEAII, WE. A. VEEDIAIII. D. TIARA liqht aircraft engines - A new generation Situation of aerospace industry in the European [SAE PAPER 7002053 871-10129 Community WOODS. 3. P. A /1-1167b Procedural changes for a better BTC system VILEASKII, V. D. 1171-1 1699 c.-L exchange and drag in a circular pipe aurinq WOEOEKA, T. laminar flow of a qas with variable properties. Passenger demand and codal split models - I1 - Results of calculations at constant wall Calibration and preliminary analysis temperature [ PB- 190946 J A71-11021 1171-12192 UBIGHT. E. A. TOI GIEEKE, E. E. A two-dimensional representation of the crosswind Quantification of the noisiness of 'approachinq' for the jet interference problem and 'receding' sounds [ AD-71 15783 1171-11006 A71-10345 WRIGHT. T. Evaluation of the design parameters for optimum heavily loaded ducted fans W 871-12677 UAGIIBE, J. 0. Effect of simulated downstream flow blockage doors on the performance of an axial-flow fan rotor Y [ NASA-TA-D-60711 1171-10537 YAEAIIE, 8. WALCEIIEB. 0. A simple model of the pseudo-shock mechanism Effect of unsymmetrical nose-bluntness on the A71-11870 stability derivatives of a 10 deq cone at Each TAICE, 3. V. 14 Final report The demand for use of Uashinqton National Airport f AD-7119211 171-1 1008 mi-10170 SAEPIBLD. E. 1. The theory of air carrier demand for slots Terminal area airlines delay data, 1964 - 1969 r PB-1933501 R71-10347 mi-10366 TAEII, 1. P. VABIIEE, J. Effect of electric and magnetic cross fields on Scale lenwth in atmospheric turbulence as measured the aerodrnamics and thermal regime of a was from an aircraft flame coni 1171-10859 IAD-7 12336 1 N71-12075 WATEBS. J. P. YELIIGRSII. K. E.' Penetration of sonic boom enerqy into the ocean - Effect of unsymmetrical nose-bluntness on the

An experimental simulation Final~ report stabilitr derivatives of a 10 dew cone at Rach 1D-7119631 n7i-10094 14 Pinai report WEBER. B. J. I AD-711921 1 N71-11008 Research in U.S.A. on LAG as an airplane fuel TOOIGKAITS, J. LI A71-10485 Inlet flow field simulation techniwues for WEBER, T. P.. JE. enqine/compressor testinw Application of maintenance simulation techniques A71 - 12909 to commercial transport aircraft [SAE PAPER 7003451 1171-10128

B-13 PIBSOlAL AOTBOB INDEX

Z ZAKEXIM, J. Synchronization of distant stations by simple overflight - Operation Synfral ONERA-IT-1651 N71-11681 ZIELIAUSKII, A. V. rrperimental studv of rotatina stall in hiuh- pressure staqes of an axial-flow compressor A71-11063 ZIDABU, 0. Arbitrary plane cascade consistinq of thin and slightly =arre.r "rgfilos i"- a pg**=*i*l flCY 171-10339 ZIEEIBIAN, I(. 1. A. State airport System inventory - An inventory of the existinq airport system in Bhode Island I PB-1893321 N7 1 - 1 102 8 ZOZULIA, V. B. Deterlination of the point of laminar-turbulent transition vith the aid of a travelinq indicator A71-12555 ZUK, J. Use of the computer in design of qas turbine mainshaft seals for operation to 500 ft/sec /122 m/sec/ 1171-10479 Desiqn study of shaft face seal with self-actinq lift anqaentation. 2 - Sealinq dam INASA-TN-D-7006] A71-11579 Analysis of self-actinq qeometry /Rayleiqh step lift pad/ for gas film seal, appendix C 171-12038 Sealinq dam design analysis, appendix D N7 1-1 2039

8-14 AERONAUTICAL ENGINEERING / A SpecialBibliography {Suppl. 2) FEBRUARY 1971

Typical Contract Number Index Listing

EllSW-1785 171- 10867 171- io021 IBS CST-46% r' 17I- 1102 1 '--+,IUYBLR 1GL-22-009-002 171-11466 Lstiw m lhis index are arranged alphanumerically by contract number 1GR- 22-009- 229 Under each contract number. the accession numbers denotmg docurnems A7 1- 12682 that have been produced as a resuit of research done under that contract are arranged In ascending order with the IAA accesston numbam appeanng 1GR-31-001-124 first The accession number denotes tha number bv which the cRB11on n 171-10940 identified m enher the IAA or STAR section RSF GK-2053 A7 1- 10931 AP 19/628/-5167 171-10737 P33615-69-C-1176 126-13-10-03 117i-ii030 171 - 1005 2 AP 33/61 5/-69-C- 1127 171-10979 P40600-71-C-0002 126-14-14-01 1171-10832 1171-10866 AP 44/620/-69-C-0036 L71- 12380 F44620-68-C-0027 126-15 ?171-?1Q01 177-1046? AP-APOSR-0697-67 171-1 1579 1171-10461 P44620-68-C-0036 171-1 i 023 720-01-11-02 C-353-66/tiBG/ 171- i 1520 r 1-11-10017 P61052-67-C-0009 171-10386 720-03 DA-28-043-ARC-02411 171- 10982 A71-11167 P61052-70-C-0005 11-11 - 11 01 0 171-10249 171-1 io61 DA-31-124-ARO/D/-247 171-1 io05 PA-70-Pa-2260 720-03-11-01 A71- 10456 W71-10276 , DA-31-124-AROn)/-444 171-12376 PA-70-WAI-185 720-13 1171-10094 1171-10537 DA-31-124-ARO/D/-464 171-12680 100014-67-A-0202-0016 72 1-01 - 10- 01 171- 10562 1171-11025 DAAEO7-69-0756 A7 1- 12852 mooi4-69-~-0417 721-01-11-06 1171-11139 171- 10495 DAAG17-67-C-0189 171-1 1968 1100014-70-c-0024 737-01- 10-0 1 1171-11519 1171-11004 DAHC04-68-C-004 1171-12677 noooi4-70-c-0374 737-52 171-10094 1171-11882 DAIiC04-68-C-0004 171-11006 noooi7-67-c-0008 A71-10926 DLEC04-69-C-0016 1171-10546 noooi9-70-C-0228 DOT-C-353-66 1171-11033 1151-8940 DOT-OS-A9-036 171-10349 RAS3-7609 DOT-7-35248 U71-11027 1AS3-13473 171-1 1029

DRRE-69/415 1AS12-2074 171-11036 P33615-67-C-1187 1-11-10734

P33615-69-C-1101 EASW-1549 1171-10470 c-1

NASA--ley, 1911 1. Repat No. 2. Government -ion No. 3. Recipient’s Catalog No. NASA SP-7037 (02) 4. Title and Subtitle 5. Report Date February.~ 1971 AERONAUTICAL ENGINEERING 6. Performing Organization Code A Special Bib1 iography (Supplement 2)

7. Author(s) 8. Performing Organization Report No.

10. Work Unit No. 9. Performing Organization Name and Addre%

11. Contract or Grant National Aeronautics and Space Administration No. Washington, I). C. 20546 I 13. Type of Report and Period Covered 2. Sponsoring Agency Name and Addm

14. Sponsoring Agency Code

c 15. Supplementary Notes

16. Abslract

This special bibliography lists 394 reports, articles, and other documents introduced into the NASA scientific and technical information system in January 1971. Emphasis is placed on engineering and theoretical aspects for design, construction, evaluation, testing, operation and performance of aircraft (including aircraft engines) and development in aeronautics and aerodynamics and research and ground support for aeronautical vehicles.

17. Key- Words (Suggested by Author(s) ) 118. Distribution Statement Aerodynamics Aeronautical Engineer i ng Unclassified - Unlimited Aeronautics Bib1 iographies

19. Security amif. (of this report) 20. Security Classif. (of this page) 21. NO. of pages 22. Rice. Unclass i f i ed Uncl ass i f ied 122 $3.00 HC F COLUMBJA

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