Aeronautical Engineering

AERONAUTICAL ENGINEERING

A SPECIAL BIBLIOGRAPHY 1

WITH INDEXES $33

-4-t NASA SP-7037(04) April 1971 March 1971 NASA SP-7037 (05)

AERONAUTICAL ENGINEERING

A Special Bibliography

Supplement 5

A selection of annotated references to uncias- sified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in April 1971 in Scientific' and Technical Aerospace Reports (STAR) International Aerospace Abstracts IIAAI.

Scierrrijic arid Techriical Iirforriialiort Oflice OFFICE OF INDUSTRY AFFAIRS AND TECHNOLOGY UTILIZATION 197 I NATIONAL AERONAUTICS AND SPACE ADMINISTRATION Wa.thitrprorr. D.C. 1

This document is available from the National Technical Information Service (NTIS), Springfield, Virginia. 22 15 1. 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 Aeronautical Eiigitieeriiig-A Special Bibliography (NASA SP-7037) lists 570 reporb, journal article>, and other documents originally announced in April 197 1 in Scieiitific arid Technical Aerospace Reports (STAR1 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 (including aircraft engines) and associated components, equipment, and systems. It also includes research and development in aerodynamics, aeronautics, and ground support equipment for aeronautical vehicles. Each entry in the bibliography consists of a standard bibliographic citation accompanied by an abstract. The listing of the entries is arranged in two major sections, IAA Eiitries and STAR Eiirries 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 indexessubject, personal author, and contract number-are included. An annual cumulative index will be published.

iii AVAILABILITY OF CITED PUBLICATIONS

IAA ENTRIES (A71-10000Series)

All publications abstracted in this Section are available from the Technical Information Serv- ice, American Institute of Aeronautics and Astronautics, Inc.. (AIAA), as follows: Paper copies are available at $5 00 per document up to a maximum of 20 pages The charge for each additional page is 25 cents Microfiche"' are available at the rate of $1 00 per microfiche for documents identified by the # symbol following the accession number A number of publications, because of their special characteristics, are available only for reference in the AIAA Technical Information Service Library Minimum airmail postage to foreign countries is $1 00 Please refer to the accession number, e g , A7 1- 10613, when requesting publications

STAR ENTRIES (N71-10000 Series)

A source from which a publication abstracted in this Section is available to the public is ordinarily given on the last line of the citation. e g , Avail NTlS The following are the most commonly indicated sources (full addresses of these organizations are listed at the end of this introduction) Avail: NTIS. Sold by the National Technical Information Service at a standard price of $3.00 for hard copy (printed, facsimile, or reproduced from microcopy) of 300 pages or less. Documents in the 301 to 600 page range are sold for $6.00 in hard copy. and those in the 601 to 900 page range are sold at $9 00. Documents exceeding 900 pages are priced by NTlS on an individual basis. These prices apply retro- actively to all documents in the NTlS collection, but in addition, documents of 300 pages or less that are over two years old (from date of announcement in Govern- ment Reports Announcements, or STAR for those items announced only in STAR) will have a surcharge of $3.00 added for a total price of $6.00. No additional surcharge will be added for documents over 300 pages. Microfiche is available from NTlS at a standard price of 95 cents (regardless of age) for those documents identified by the # sign following the accession number (e.9.. N71-1041 1#) and having an NTlS availability shown in the citation. Avail: SOD (or GPO). Sold by the Superintendent of Documents, U.S. Government Printing Office, in hard copy. The price is given following the availability line. (An order received by NTlS for one of these documents will be filled at the SOD price if hard copy is requested. NTlS will also fill microfiche requests, at the standard 65 cent price, for those documents identified by a # symbol. SOD does not sell microfiche.) Avail. NASA Scientific and Technical Information Office. Documents with this availability are usually news releases or informational brochures available without charge in paper copy. Avail AEC Depository Libraries. Organizations in U.S. cities and abroad that maintain collections of U.S. Atomic Energy Commission reports, usually in microfiche form, are listed in Nuclear Science Abstracts. Services available from the USAEC and its depositories are described in a booklet, Science Information Avallable from the Atomic Energy Commission (TID-4550). which may be obtained without charge from the USAEC Division of Technical Information. Avail Univ. Microfilms. Documents SO indicated are dissertations selected from Disserta- tion Abstracts. and are sold by University Microfilms, Inc. as xerographic copy (HC). microfilm. or microfiche at the prices shown. Microfiche are available only for those dissertations published since January 1, 1970. All requests should cite the author and the Order Number as they appear in the citation.

(1) A microfiche IS a transparent sheet of film. 105 x 148 mm In size. containmg up to 72 pages of information reduced to micro images (not to exceed 20 1 reduction)

ilv Avail: HMSO. Publications of Her Majesty's Stationery Office are sold in the U.S.by British Information Services (61s). New York City. The U.S. price (including a service charge) is given, or a conversion table may be obtained from BIS. Avail: National Lending Library, Boston Spa, England. Sold by this organization at the price shown. (If none is given. an inquiry should be addressed to NLL.) Avail: ZLDI. Sold by the Aentralstelle fur Luftfahrtdokumentation und -Information, Munich, Federal Republic of Germany, at the price shown in deutschmarks 'DM). Avail: Issuing Activity, or Corporate Author, or no indication of availability: Inquiries as to the availability of these documents should be addressed to the organization shown in the citation as the corporate author of the document. Avail: U.S. Patent Office. Sold by Commissioner of Patents, U.S. Patent Office, at the standard price of S.50each, postage free. Other availabilities: If the publication is available from a source other than the above, the publisher and his address will be displayed entirely on the availability line or in combination with the corporate author line.

GENERAL AVAl LAB I LITY

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

SUBSCR IPTI 0 N AVAl LAB I LlTY i This publication is available on wbccrtption 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 subscriptions should be referred to the NTI S

V ADDRESSES OF ORG A NlZATlON S

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

National Lending Library for Science British Information Service and Technology 845 Third Ave. Boston Spa, Yorkshire, England New York, N.Y. 10022 National Technical Information Service Springfield, Virginia 22 1 5 1 Commissioner of Patents U.S. Patent Office Superintendent of Documents Washington. D.C. 20231 U.S. Government Printing Office Washington, D.C. 20402 Defense Documentation Center Cameron Station University Microfilms, Inc Alexandria, Virginia 22.11 4 A Xerox Company 300 North Zeeb Road ESRO/ELDO Space Documentation Service Ann Arbor, Michigan 48 106 European Space Research Organization 1 14, av. de Neuilly University Microfilms, Ltd 92-Neuill~-sur-Seine,France Tylers Green London, England Her Majesty's Stationery Office P.O. Box 569. S.E. 1 U S Atomic Energy Commission London, England Division of Technical Information PO Box62 NASA Scientific and Technical Information Oak Ridge, Tennessee 37830 Facility P.O. Box 33 Zentralstelle fur Luftfahrtdoku- College Park, Maryland 20740 mentation und-Information 8 Munchen 86 Postfach 880 Federal Republic of Germany

vi TABLE OF CONTENTS

Page

IAAEntries ...... 181 STAREntries ...... 225

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

TYPICAL CITATION AND ABSTRACT FROM STAR

NASA SPONSORED AVAIUBLE ON DOCUMENT

ACCESSION N71-12035*# Pratt and Whitney Aircraft. East Hartford Conn CORPORATE DEVELOPMENT OF MAINSHAFT SEALS FOR ADVANCED c1 SOURCE AIR BREATHING PROPULSION SYSTEMS, PHASE 2 Final TITLE 2Report PUBUCATION V P Povinelli and A H McKibbin 23 Jun<970 122 p refs DATE (Contract NAS3-7609) AUTHORS COsAfl gas-turbine engines were designed fabricated. and tested The seal CODE CONTRACT concepts incorporated Iih geometrles which used the relatwe motion OR GRANT between the primary seal surfaces to provide positive separation (film lubrication) One design (self-acting) with shrouded Rayleigh step lift pads operated with a gas film separating the sealing faces AVAIUBIUTY REPORT SOURCE NUMBER The other design (hydrodynamicl with a spiral groove geometry operated with oil-film separation Tests of the gas-film seal demonstrated the feasibility of operation at gas temperatures to 1200 F oressure differentials to 250 psi 31-4 sMng speeds to 450 ft/sec Excellent correlatons with analytically predlcted performance parameters were obtained Face wear was less than 0 1 mil after 320 hours at an air temperature of 1000 F a pressure differential of 200 psi. and a sliding speed of 400 ft/sec Average air leakage during that test was 14 scfm These operating conditions exceed the capability of conventional contact seals and the air leakage is 1/ 10 that of a labyrinth seal Testing of the oil-film seal revealed an inadequate seal force balance Author

TYPICAL CITATION AND ABSTRACT FROM IAA

NASA SPONSORED AVAILABLE ON DOCUMENT MICROFICHE

.. ACCE~lON----,~A71-19999 # Sphere drag in mar-freemolecule hypatonico TITLE NUMBER flow. M. I. Kussoy, D. A. Stewart, and C. C. Horstman (NASA,, Ames Research Center, Moffett Field, Calif.). AlAA Journal, vol. 8, Nov. AUTHORS 1970, p. 2104, 2105.9 refs. AUTHOR'S Investigation of the drag coefficient of spheres at hypersonic AFFILIATION Mach numbers for near-free-molecule flow conditions. Sphere drag data in the near-free-molecular regime for flow conditions close to earth satellite conditions, obtained by using a free-flght technique in PUBUCATION the Ames 42-in. hock tunnel are tabulated, shown gaphically, and DATE disused. O.H.

vii AERONAUTICAL ENGINEERING

A Special Bibliography (Suppl. 5) MAY 1971

(NASA, Wallops Station, Wallops Island, Va.). In: EASCON '70; Institute of Electrical and Electronics Engineers, Electronics and Aerospace Systems Convention, Washington, D.C., October 26-28, 1970, Record. 1 New York, Institute of Electrical IAA ENTRIES and Electronics Engineers, Inc., 1970, p. 295-301. 33 refs. Recent applications of separate, single frequency microwave radar and laser (lidar) systems to various earth-oriented, environmental, and domestic areas are briefly surveyed. The advantages of the integration of a separate radar and lidar into a single radarhidar system are discussed from the vantage point of collocated electro- A71-18772 # Fullydeveloped flow in rectangular ducts of optical systems. Attention is focused on the design of a hybrid or nonuniform surface texture. I - An experimental investigation. K. integrated radarhdar system and its potential applications in such HanjaliC and B. E. Launder (Imperial College of Science and areas as geodesy, meteorology, oceanography, navigation, and com- Technology, London. England). In: Heat and mass transfer in munication. In comparison with separate systems, the radarllidar turbulent boundary layers; Boris KidriE lnstitut za Nuklearne Nauke, configuration is shown to be economical to manufacture, operate International Summer School, 1st. Herceg Novi, Yugoslavia, and maintain. The economic attractiveness is further enhanced by September 9-21, 1968, Proceedings. Volume 2. the worldwide availability of numerous tracking radars. Other Edited by P. Anastasijevid, N. Afgan, and 2. Zarid. Belgrade, Boris applications of radar and optical systems in earth survey, air KidriE lnstitut za Nuklearne Nauke, 1970, p. 393410. 12 refs. pollution detection, monitoring and control, and air traffic control Research supported by the Central Electricity Generating Board. are proposed in addition to further study efforts into the utilization Experimental investigation of turbulent flow in a rectangular of airborne and ground-based coherent radar systems. (Author) duct of large aspect ratio in which one of the principal sides was smooth and the other roughened with isolated square ribs aligned A71-18829 Avionics for aeronautical systems. Warren E. normal to the flow. The objectives of the study included the Swanson (North American Rockwell Corp.. Aerospace and Systems determination of the positions of maximum velocity and zero shear Office, El Segundo, Calif.). /€€E Transactions on Aerospace and stress. The results obtained indicate that these two positions were Electronic Systems, vol. AES-7, Jan. 1971. p. 42-46. not coincident, the velocity maximum lying farther from the smooth Advancements in technology have led to increased demand for surface than the position of zero shear stress. Results pertaining to avionics in airborne applications. Although aeronautical system several other objectives of the study are discussed. M.V.E. suppliers have implemented improved procedures and design approaches which are generally effective, challenges continue to exist. This paper explores several areas where overall aeronautical system A71-18808 Communications, navigation and surveillance design might be improved by proper emphasis on avionic subsystem for aircraft and marine vessels operating in the North Atlantic region. design. The topics selected include standardization, weight impact, Daniel L. Brandel, Stephen R. Cantor, Ronald M. Hershkowitz, and environmental control, maintainability, and avionic equipment Franklin D. MacKenzie (US. Department of Transportation, Trans- growth. Comparisons are made in terms of ultimate cost to the portation Systems Center, Cambridge, Mass.). In: EASCON '70; aeronautical system user. (Author) Institute of Electrical and Electronics Engineers, Electronics and Aerospace Systems Convention, Washington, D.C.. October 26-28, 1970. Record. New York, Institute of Electrical and Electronics Engineers, Inc., 1970, p. 66-76. 21 refs. A71-18830 Improvement of automatic landing through A baseline air traffic control surveillance model is discussed, and the use of a space diversity ILS receiving system. James R. Fries marine positioning requirements and marine communications in the (Boeing Co., Seattle, Wash.). /€E€ Transactions on Aerospace and North Atlantic region are considered. The model contains a number Electronic Systems, vol. AES-7, Jan. 1971. p. 47-53. 7 refs. of simplifying assumptions. It treats the surveillance problem in only A space diversity method of receiving and processing ILS the lateral dimension, A static, strategic technique is proposed and localizer information has been developed and flight tested. Multiple analyzed. The model provides a complete probabilistic description of laterally separated antennas are used which sense the ILS signal on the system, rather than relying on a worst case analysis. Aspects of and around the approach path. Combining these signals suppresses aircraft communication channel requirements are examined. Ship ILS beam distortion produced by multipath signal interference and distribution in the North Atlantic, the determination of ship provides much improved guidance information to the landing aircraft location, and high seas communication requirements according to the control system. (Author) type of message used are considered. G.R.

A71-18827 * Integrated electro-optical systems for earth- A71-18831 ILS localizer multipath analysis. S. L. Shih oriented, environmental, and domestic applications. Frank E. Has. (IBM Thomas J. Watson Research Center, Yorktown Heights, N.Y.:

181 A7 1-18833

IBM Communications and Engineering Sciences Center, Gaithers- relationship for the laminar heating to the stagnation point of a burg, Md.). IEEE Transactions on Aerospace and Electronic Systems, sphere, and is useful for rapid estimates of maximum equilibrium vol. AES-7, Jan. 1971, p. 54-60. 5 refs. FAA-supported research. temperatures. M.V.E. The scattering effect of structures on Instrument Landing System localizer signals is analyzed in this paper. A generalized computer program results which can be used to determine the reflection from surfaces of most materials and orientations for which A71-18916 # Characteristics of the working flow in hypersonic shock tubes in the radius of curvature is large compared with the wavelength. For the presence of solid-particle impurities most reflecting walls, a closed form solution is used and the (Osobennosti rabochego potoka giperzvukovykh aerodinamicheskikh trub pri nalichii primeri tverdykh chastits). B. Bakum. Inzhenerno- computation time is short. The program will enable users to I. Fizicheskii Zhurnal, vol. 19, Oct. 1970, p. 698-704. 10 refs. In determine the placement of hangars, towers, etc.. in airports and to Russian. find ways to reduce their effect on localizer facilities. (Author) The effects of solid-particle impurities on the flow in a typical hypersonic shock tube were studied from the viewpoint of determining possible sources of error in blunt-body measurements. A71 -18833 Operating system reliability for the Navy Nitrogen was used as the working gas, and the particle diameters advanced avionic digital computer. Ronald S. Entner (US. Naval Air were 5. 50, and 500 microns. It is shown that the particle Systems Command, Washington, D.C.) and Edward H. Bersoff temperature reaches the gas temperature from 1 to 10 msec after the (Logicon, Inc.. Falls Church, Va.). /E€€ Transactions on Aerospace onset of the experiment, and the particles pass into the nozzle after and Electronic Systems, vol. AES-7, Jan. 1971, p. 67-72. 5 refs. being so heated throughout most of its duration. In the nozzle, there This paper discusses reliability aspects of a modular multi- is a significant dynamic and thermal lag of the particles in processor currently under development by the Naval Air Systems comparison to the gas. As a result, supersonic flow can occur around Command. The operating system, or executive, of this computer may the particles, leading to a shock wave and flow turbulence in the be implemented in various ways. These include a totally software wake. Such supersonic flow around the particles can also occur in the 'floating executive,' one dedicated to a specific processor, or an shock layer ahead of the blunted model, causing additional tur- executive consisting of special-purpose hardware. The objections to bulence. T.M. hardware executives, especially for avionic applications, include a supposed degradation in system reliability. This paper shows that under certain conditions this degradation need not occur. (Author) A71-18924 # Nature of the anomalous seeded flow past blunted bodies in hypersonic wind tunnels (0 pirode anomal'nogo obtekaniia zatuplennykh tel zapylennym potokom giperzvukovykh A71-18835 Nonlinear estimation via Kalman filtering. J. J. aerodinamicheskikh trubl. B. I. Bakum, lu. N. Shestakov, and V. N. Kappl (Hughes Aircraft Co., Culver City, Calif.). I€€€ Transactions Shmanenkov. lnzhenerno-fizicheskii Zhurnal, vol. 19, Nov. 1970, p. on Aerospace and Electronic Systems, vol. AES-7, Jan. 1971, p. 925-928. In Russian. The extended Kalman-8ucy filtering algorithm is applied to the Experiments are described in which a cylinder with a small body problem of estimating the system parameters of a single-channel (thread) in front of it was placed in a hypersonic air flow containing missile attitude control system. In particular, noisy observations of suspended particles. The observed 'anomalous' distortion of the body angular rate, normal acceleration, and control surface deflec- separated shock wave at the cylinder is studied as a function of the tion are used in the algorithm to obtain estimates of body angular spacing between the cylinder and the thread, It is shown that the rate, angle of attack, control surface deflection, air density, and distortion of the shock wave (usually in the form of one or more missile velocity. Computational results obtained for this problem are fluid cones in front of the wave) may be attrlbuted to effects which presented. These results are evaluated to determine the applicability occur when the end of an aerodynamic wake produced by lagging of this estimator as a part of an adaptive control scheme. In addition, particles (the head of the wake travels at the particle velocity and its V.P. a general approach to the formulation of practical nonlinear end at the gas velocity) catches up with the cylinder. estimation problems is suggested. (Author)

A71-19014 # Problems of air navigation. J. P. Hach A71-18900 # A new correlation of parachute weight data. (Deutsche Lufthansa AG, Hamburg, West Germany). In: Max-Planck- Kenneth E. French (Lockheed Missiles and Space Co., Sunnyvale, lnstitut fur Aeronomie, Symposium on the Future Application of Calif.). Journal of Spacecraft and Rockets, vol. 8, Jan. 1971, p. 71, Satellite Beacon Experiments, Lindau uber Northeim, West Germany, 72. 5 refs. Research supported by the Lockheed Missiles and Space June 2-4, 1970, Proceedings. Symposium co- Independent Development Program. sponsored by the Deutsche Gesellschaft fur Ortung und Navigation. Statistically treated correlations of weight, configuration, and Edited by W. Dieminger and G. K. Hartmann. Lindau uber Northeim, strength for 59 various parachutes are presented in tables and a West Germany, Max-Planck-lnstitut fur Aeronomie, 1970, p. 14-1 to diagram in order to assist the parachute designer. The specific tasks 14-6. for which they may provide help include (1) the rapid assessment of Discussion of systems used as aids in air navigation, in the final nominal parachute weight, (2) tolerance estimates on the nominal approach and landing of aircraft, and related navigational problems. weight, and (3) calculation of weight tradeoffs with respect to The instrument landing system (ILS) is briefly described, together variations in parachute size and strength parameters, M.V.E. with a potential successor to it, as well as the vhf omnidirectional radio range (VOR), the distance measuring equipment (DME), and present long-distance aids. The potential of satellite systems for long-distance aircraft operation is briefly discussed. M.M. A71-18902 # Estimation of the maximum temperature of a swept leading edga for an equilibrium glide entry. Davis H. Crawford (NASA, Langley Research Center, Space Systems Research Div., A71-19049 # Gas flows past blunt bodies. Part 1 - Methods Hampton, Va.). JournalofSpacecraftand Rockets, vol. 8, Jan. 1971, of calculating and analyzing flows (Techeniia gaza okolo tupykh tel. p. 75, 76. 5 refs. Part 1 . Metod rascheta i analiz techenii). A. N. Liubimov and V. V. A simple relation for estimating the maximum stagnation line Rusanov. Moscow, Izdatel'stvo Nauka, 1970. 287 p. 217 refs. In temperature on the wing leading edge during an equilibrium glide Russian. entry is derived. This relation. amenable to hand calculation, is based A finite-difference method for studying inviscid gas flows past on a modified form of the Detra, Kemp, and Riddell (1957) blunt bodies is developed and analyzed in this book. The method is

182 applied to two-dimensional, axisymmetric. and threedimensional modifying the nature of the technical procedures, the time frames, steady flow of an ideal gas, allowance being made for physico- and the contractual arrangements of the next decade. These changes chemical transformations. The analysis makes use of special al- will carry the seeds of serious management problems if they are not gorithms developed on the basis of exact calculations of flows past properly understood and addressed. (Author) spheres, paraboloids, ellipsoids, hyperboloids, truncated cones, and similar bodies. Intended for scientists and engineers dealing with computational mathematics, theoretical aeromechanics, and aero- A71-19078 # The F-15 air superiority fighter. James W. dynamic flight-vehicle design, the book should be useful also to Wood (USAF, Washington. D.C.). (Society of Experimntzl Test teachers and students. V.P. Pilots, Symposium, 14th, Beverly Hills, Calif., Sept 24-26, 1970.) Society of Experimental Test Pilots, Technical Review, vd. 10, no. 2, 1970, p. 9-15.

A71-19050 # Gas flows past blunt bodies. Part 2 ~ Tables of Description of the militaiy requirements, program management gasdynamic functions (Tscheniia gaza okdo tupykh tel. Part 2 - procedures, and present developmental status of the F-15 fighter TaMitsy pazodinamiheskikh funktsii). A. N. Liubimov and V. V. aircraft. The speed. maneuverability, acceleration, and weaponry Rusanov. Moscow, Izdatel'stvo Nauka. 1970. 379 p. In Russian. considerations that led to the present configuration are outlined, and The book contains tables compiled on the basis of systematic the progam management structure is explained in terms of the major calculations of twodimensional axisymmetric, and threedimensional military decision making channels and contractor responsibilities. gas flows past blunt bodies. Mixed flows past small-aspect-ratio Emphasis is placed on the flight test programs envisioned for both bodies were calculated by a finitedifference method developed in categories of operation. T.M. Part 1. Supersonic flows were calculated by a finite-difference method proposed by Babenko et al. (1964).The tables contain the values of gasdynamic functions for axisymmetric and two- and threedimensional flows past spheres, cylinders, paraboloids, hyper- A71-19079 # The development of a coilision avoidance boloids and similar bodies in the subsonic and supersonic regions. system. Raymond D. Hunt (McOonnell Douglas Corp., St. Louis, Results of calculations of axisymmetric flows with allowance for Mo.). (Society of Experimental Test Pilots, Symparium, 14th, dissociation and ionization, as well as molecular gas compositions Beverly Hills. Calif., Spt. 24-26, 1970.1 Society of Experimtaf and thermodynamic functions for axisymmetric flows are also Test Pilots, Technical Review, vd. 10, no. 2, 1970, p. 17-22. tabulated. The tables are compiled for a wide range of parameten. Discussion of test experience gained with the airborne Eliminb Accurate and convenient for use, they are intended for engineers tion Range Zero (EROE) system for mid-air collision avoidance. dealing with gasdynamia and aerodynamics. V.P. EROZ operates as a cooperative system in which airborne units are synchronized by a master oscillator at the ground station. E& aircraft transmits a radio signal at a precise instant known to at1 other aircraft. The time delay between the transmission and reception tells A71-19076 Soaety of Experimental Test Pilots, Sympo- the receiving system the distance between the two aircraft. The sium. 14th. Beverly Hills, Calif., September 24-26. 1970, Proceed- Doppler effect provides information on how fast the distance is ingr. Society of Experimental Test Pilots, Technical Review, vol. 10, closing. Maneuvering instructions are presented to the pilot automati- no. 2.1970. 285 p. cally. Over 15,000 operational flights performed with this system Flisht-test procedures, equipment, and experience for qxcific testify to its effectiveness, and it is expected that initial cost would aircraft are described, including technical deai!? nf mine aircraft. SE $!5W for a piduction run of 10,OOO units. T.M. engines, and avianics systems. Development and certification tests are outlined for the F-15. Arava, Bwing 737, Yankee, DC-10. F-IWD. and A-7 aircraft. A section on the manned space-flight A71-19080 # Airborne measurement, key to environmental progam includes flight experience with the Apollo 12 and 13 management. W. L. Dowdy and R. L. Gorham (North American spacecraft, space-shuttle and Skylab project reviews, and pilot Rockwell Corp., El Segundo, Calif.). (Society of Experimental Test evaluations of liftingbody requirements. A new approach to high- Pilots, Symposium, 14th, Beverly Hills, Calif., Sept. 24-26, 1970.) velocity helicopter testing is described, and control aspects of the Society of Experimental Test Pilots, Technical Review, vol. 10, no. Concorde power plant are explained. The material includes handling 2, 1970, p. 23-35. and performance evaluations, control system specifications, and Airborne surveillance techniques and equipment are discussed recommendations for optimum test procedures. T.M. for monitoring environmental parameters to provide initial data in a large-scale earth resources management program. Airborne sensors such as aerial cameras, IR scanners, side-looking radars, scattero- meters, and spectrometers would be used to measure such diverse A71-19077 # Navy testing in the next decade. John G. parameters as thermal water pollution, extent of crop disease, Wissler (US. Naval Air Test Center). (Society of Experimental Test salinity, and geological structure. Specific tests conducted with a pilok, Symposium, 14th. Beverly Hills. Calif., Sept. 24-26,1970.1 specially equipped D-18 Twin Beechcraft are reviewed, and some society of Experimental Test Pilok, Technical Review, vol. 10, no. problems of pilot training, procedures, and data processing are 2, 1970, p. 1.7. considered. T.M. A realistic appraisal of the trends in Naval Aviation testing during the 70s has to consider the dynamically changing environment that has affected naval testing during the past two decades. The 50s A71-19081 # The Concorde powerplant. James Pollitt were characterized by a relatively leisurely pace of prototype testing (Rolls-Royce, Ltd., Bristol Engine Div.. Bristol, England). (Society of made possible by the world political scene, US. nuclear supremacy Experimental Test Pilots, Symposium, 14h, Beverly Hills, Calif., and a substantial inventory cushion of World War I1 and Korean War Sept. 2426, 1970.) Society of Experimental Test Pilots, Technical aircraft. Conversely, the 60s were characterized by quick reaction Review, vol. 10, no. 2, 1970. p. 43-58. Southeast Asia programs, concurrent production and a disappointing The design and operation of the Concorde powerplant is number of expensive weapons systems failures. Navy testing in the described in terms of main technical features of the Olympus 593 70s must satisfy the divergent requirements of accurate visibility two-spool turbojet engine, the variable nozzle assembly, afterburners, during early development to guide major funding commitments, the variable intake, and the engine control system. The use of a contrasted against long lead time Fleet outfitting schedules brought variable primary nozzle system allows control of the number one on by a sharply declining inventory of aircraft. This dichotomy of spool independent of the number two spool. The electronic engine naval aviation testing requirements will be the dominant factor in control system does not require reversion to manual Control and its

183 A71 -19082

operation is based on three basic loops. A governing and a School). (Society of Experimental Test Pilots, Symposium, 14th. positioning loop (effective in the high and low power ranges, Beverly Hills, Calif., Sept 24-26, 1970.) Society of Experimental respectively) act upon the fuel throttle valve. An 'E' schedule control TestPilots, Technical Review, vol. 10, no. 2, 1970, p. 199-219. loop is effective throughout the power range and acts upon the Discussion, for the case of the F-104D aircraft, of side stick primary nozzle. T.M. control system design and function, of curriculum maneuvers which have been verified in the alrcraft on side stick, and the observed reliability of the electrical components. The major conclusions developed from the Aerospace Research Pilot School (ARPS) A71-19082 # Flight test of the 'ARAVA Israel STOL experience with an electrical fly-by-wire flight control system and a airplane. Avraham Hacohen (Israel Aircraft Industries, Ltd., Lod side stick controller are that a side stick is usable and offers Airport, Israel). (Society of Experimental Test Pilots, Symposium, improvements for aircraft control, that pilot selectable gains, force 14th, Beverly Hills, Calif.. Sept. 24-26, 1970.) Society of Experi- gradients, and viscous damping should be included in future side mental Test Pilots, Technical Review, vol. 10, no. 2, 1970, p. 59-74. stick design, and that arm rest adjustment must be incorporated to Description of the design and handling of the Israeli ARAVA account for size of pilot's hands and bulk of garments. F.R.L. aircraft intended for short-haul STOL operations with payloads of 20 passenger: or 4400 Ibs of cargo. The ARAVA is a 12,500-lb gross takeoff weight, twin-turboprop aircraft characterized by a high-wing geometry and a hanging fuselage with a swinging aft section. A A71-19093 # A new approach to helicopter H-V testing with twin-boom tail and rudder structure is used together with a fixed preliminary results from the OH-58A Kiowa and AH-1G Huey Cobra landing gear arrangement. Flight test experience is quoted for helicopters. John A. Johnston (US Army, Washington, D.C.). longitudinal stability, lateral-directional stability. flap response, and (Society of Experimen tal Test Pilots, Symposium, 14th, Beverly landing characteristics. T.M. Hills, Calif., Sept. 24-26, 1970.) Society of Experimental Test Pilots, TechnicalReview, vol. 10, no, 2, 1970, p. 221-244. 14 refs. Discussion of height velocity (H-V) testing, mathematical modeling, and the applicability of test results to service use. A71-19083 # Developing the advanced 737 airplane. Attention is also given to two H-V aircraft programs presently being Raymond L. McPherson (Boeing Co., Seattle, Wash.). (Society of conducted. U.S. Army Aviation Systems Test Activity (USAASTA) Experimental Test Pilots, Symposium, 14th, Beverly Hills, Calif., established procedures have substantially improved the safety of Sept. 24-26, 1970.) Society of Experimental Test Pilots, Technical helicopter H-V flight testing. While mathematical modeling is Review, vol. 10, no. 2, 1970, p. 75-97. providing some insight into specific areas, it is not yet sufficiently Test experience gained in evaluating configuration changes developed to provide a basis for eliminating further H-V flight meant to improve the takeoff and landing performance of the Boeing testing. F.R.L. 737 aircraft. Emphasis is placed on improvements in high-lift systems and stopping capability. Attention is given to the effects cf BLC modifications, wider nacelle struts, extended Krueger flaps, increased A71-19094 # Spinning the A-7. Donald D. Smith (US. Slat chord and camber, increased main flap angles, and increased aft Navy, Washington, D.C.). (Society of Experimental Test Pilots, flap chord. Performance evaluations are given for an improved Symposium. 14th, Beverly Hills, Calif., Sept. 24-26, 1970.) Society antiskid system, an automatic braking system, and softer main gear T.M. of Experimental Test Pilots, Technical Review, vol. 10, no. 2, 1970, oleo struts. p. 245-253. Concise summary of the progress of the spin evaluation program of the A-7 low altitude tactical fighter, the mission of which calls for A71-19084 #f The development of the Yankee. Richard 6. vigorous maneuvering capability as well as for the carriage of a wide Kemper (American Aviation Corp., Cleveland, Ohio). /Society of variety of external stores. The aircraft is considered to have an Experimental Tesr Pilots, Symposium, 14th, Beverly Hills, Calif., unsatisfactory departure mode because there are departure charac- Sept. 24-26, 1970.) Society of Experimental Test Pilots, Technical teristics which are, in fact, occurring within a reasonable maneuver- Review, vol. 10, no. 2, 1970, p. 99-104. ing envelope of the aircraft, and which will limit the envelope of the The Yankee is the result of considerable redesign and develop- aircraft at low altitude. The aircraft will spin readlly when it is ment of an aircraft known initially as the BD-1, which was built in loaded asymmetrically, and will always spin away from the heavy store. F.R.L. late 1963 by Bede Aircraft, Incorporated in Columbus, Ohio. The BD.1 received substantial publicity at the time of its development since one version of the aircraft, stripped of all accessories and equipped with a low horsepower, remanufactured engine, was priced A71-19095 # Fighter testing - Spin test or spin prevention to the consumer at $2500. The aircraft featured aluminum honey- test. Burt Rutan (USAF. Flight Test Center). (Society of Experi- comb in the fuselage, metal-to-metal bonding, and folding wings for mental Test Pilots, Symposium, 14th, Beverly Hills, Calif., Sept. towing and home storage. (Author) 24-26, 1970.J Society of Experimental Test Pilots, Technical Review, vol. 10, no. 2, 1970, p. 255-260. Discussion of a philosophy of requirements for testing and A71-19085 # Flight testing the DC-10. Felix E. Blum aircraft improvement, in view of the severe operational limitations of (McDonnell Douglas Corp., St. Louis, Mo.). fSociety of Experimental high angle of attack, with summary of the results of the recent USAF Test Pilots, Symposium, 14th. Beverly Hills, Calif., Sept. 24-26, F-4E Stall/Near Stall Investigation. It is suggested that a most 1970.) Society of Experimental Test Pilots, Technical Review, vol. important aspect of high angle of attack handling qualities is too 10, no, 2, 1970, p. 105-107. often being overlooked - i.e., spin avoidance or spin resistance. Brief outline of the DC-IO flight test program, with a descrip- F.R.L. tion of the handling characteristics under typical test conditions. Takeoff and landing procedures are discussed, and comments are given on the flutter. stall, and stability characteristics. Reverser tests A71-19175 Fiber optic faceplates for contrast enhance- and antiskid braking system tests are also considered. T.M. ment under high ambient light conditions for cockpit displays. Anthony M. Detarando (Bendix Corp., Mosaic Fabrications Div., Sturbridge, Mass.). In: Fiber optics: Applications and technology; A71.19092 # F-104D side stick control system. Byron W. Society of Photo-optical Instrumentation Engineers, Seminar-in- Theurer and Kenneth E. Staten (USAF. Aerospace Research Pilot Depth, Dallas, Tex., January 28, 29, 1970, Proceedings. Seminar

184 A71-1 9361

co-sponsored by the U.S. Army. Redondo Beach, Calif., Society of local fuel-air mixture, whichever is encountered first above the Photo-optical Instrumentation Engineers (SPIE Seminar Proceedings. surface. This domam is calculated for a laminar boundary layer over Volume 21). 1970, p. 103-108. a flat pool of fuel. The agreement between this predicted boundary Discussion of the use of fiber optic faceplates to solve the and the boundary found here experimentally is generally quite good. problem which arises, particularly in cockpits of commercial and Second is the problem of uetermining what factors control the military aircraft, when visual displays such as cathode ray tubes and ignitability of a liquid pool of fuel at a subflash temperature. The rear projection screens are viewed under high ambient light con- heating of such a pool to the point of ignition, by an energy source ditions. Optical phenomena responsible for a decrease in the display in the space above it, is retarded considerably by motion induced in contrast. such as the ghost, halo, and especially the direct sunlight the pool. Suppression of the motion enhances the ignitability problem, are explained. Two techniques commonly used to improve markedly. The induced motion produces a vortex cell whose size the contrast - i.e., the use of a neutral density filter and a circular depends on various fuel and igniter parameters. The driving force polarizer - are discussed. The principles underlying the method of causing this fluid motion is postulated to be a combination of the using a fiber optic faceplate as a CRT screen are explained in detail, forces resulting from buoyancy in the pool and surface tension and the prerequisites for designing a fiber optic system for cockpit gradient on the surface. (Author) displays are specified. It is demonstrated that the system suggested eliminates all the problems considered; the ghost, halo, and direct sunlight problem is solved, and an increased display brightness and an improved color rendition and sharpness of image is achieved. O.H. A71-19255 * # On the diffraction of a shock wave by general two-dimensional distuhnces. Y. S. Pan (Tennessee, University. Tullahoma, Tenn.). Quarterly of Applied Mathematics, vol. 28. Jan. 1971, p. 539.552. 6refs. Grant No. NGL-33416-119. A71-19183 ft Study of inviscid flows of a radiating gas with Solutions for the diffraction of a plane shock wave by general the aid of differential ap(noxim&ons (Issledovanie neviazkikh two-dimensional weak disturbances caused by moving bodies are techenii izluchaiushchego gaza s pomoshch'iu diffenntsial'nyld., presented. The technique employed is the method reported by priblizhenii). S. D. Bezrukikh and V. N. Fomin. Zhurnal Vychislite1'- Ludloff (1953) for the aerodynamics of blasts. The solution shorn noi Matematiki i MatematicheskoiFiziki, vol. 10, Nov.-Dec. 1970, p. that the flow fields behind the shock and the plane shock are 1503-1511. 8 refs. In Russian. disturbed not only by the portion of the body ~assedover by the Study of the P sub 3 and P sub 5 approximations of the method shock but also by the portion of the body ahead of the shock. For a of spherical harmonics for solving problems of hypersonic inviscid stationary body the present solution reduces to the corresponding gas flow past blunt bodies, and comparison of these approximations solution reported by Ludloff. It is pointed out that the present with the P sub 1 approximation. Owing to the unwieldiness of the P solutions can be appiied to many shock diffraction problems of sub 3 and P sub 5 approximations, the study is performed on a practical interest. such as blast effects on aircrafts and on wings at comparatively simple gasdynamic model in which the flow of angles of attack. G.R. radiating gas in the vicinity of the forward stagnation point of the blunt body is considered. In addition, a study is made of a two-stage approximation with respect to frequency of the real absorption coefficients of air for the purpose of ascertaining the possibility of A71-19354 # A motion of a rapidly rotating body in air (ob using such a model for an approximate calculation of the selectivity odnom dvizhenii bystrovrashchaiushchegosia tela v vozdukhe). 6. la. of the radiation. A.B.K. Lokshin (Moskovskii Gosudarstvennyi Universitet. Moscow, USSR). !!wskoi&~i L:7i:sersitet, 'wfatnik.SerL'a 1 - Maieodika, Mekhaiiika, vol. 25, Nov.-Dec. 1970, p. 93-98. In Russian. Consideration of a gliding-type motion of a rapidly rotating A71 -19203 Low profile optical system for an aircraft axisymmetric body in air. It is assumed that the axis of symmetry of beacon. A. H. Schwartz (SCM Research and Development Labora- the body is horizontal and does not change its orientation, while the tory. Palo Alto, Calif.). (Optical Society of America, Annual center of gravity velocity vector is perpendicular to the axis of Meeting, Chicago, Ill., Oct. 21-24, 1969.1 Applied Optics, vol. 10, symmetry and forms a certain angle with the vertical. Conditions of Feb. 1971, p. 358-362. 8 refs. stability of such a motion are obtained, and the stability of plane An optical system producing an annular cone of radiation from motion is proved under certain assumptions regarding the aero- a point source using a low profile front lens is shown to have dynamic coefficients. A.B.K. application as a beacon for high speed vehicles. The system comprises a high pressure short arc light source with axial electrodes and integral collector, a conical reflector, and a divergent meniscus lens that has low protrusion over the surface of the vehicle. The system A71-19355 # Ricocheting of a plate from the surface of an has minimal drag, and the radiation is distributed in directions close ideal inmmpressible fluid (Rikoshet pbstinki ot poverkhnosti to the plane perpendicular to the optical axis. The influences of ideal'noi neszhimaemoi zhidkosti). V. A. Eroshin (Moskovskii various parameters such as lens camber, lens aperture, source size, Gosudarstvennyi Universitet, Moscow, USSR). Moskovskii Uni- collector shape, collection efficiency, and beam divergence are versitet, Vestnik. Seriia I - Matematika, Mekhanika. vol. 25, discussed. A prototype was built at Eimac Division of Varian using a Nov.-Dec. 1970, p. 99-104. In Russian. xenon short arc lamp with metal ceramic structure and integral Consideration of the problem of the ricocheting and nonself- collector. (Author) similar landing of a seaplane step (a flat plate) on an ideal incompressible fluid. The effect of trailing vortices is taken into account, and the wetted length of the plate is determined by calculating the height of the fluid rising ahead of the plate. The shape A7 1-1 9245 A study of some factors influencing the of the free surface is determined. A.B.K. ignition of a liquid fuel pool. R. J. Murad (Northern Research and Engineering Corp., Cambridge. Mass.), J. Lamendola. M. Summerfield (Princeton University, Princeton, N.J.), and H. Isoda. Combustion and Flame, vol. 15, Dec. 1970, p. 289-298. 9 refs. Two particular problems concerning the ignitability of a pool of A7149361 # Synthesis of a multicomponent mechanism liquid fuel are considered. First is the problem of defining the with transmission angles diverging minimally from ninety degrees domain of ignitability of a pool of fuel at a superflash temperature (Sintez mnogozvennogo mekhanizma pri uglakh peredachi, naimenee subjected to a cross wind. It is postulated that this domain is otkloniaiushchikhsia ot devianosta gradusov). V. 0. Fokin. Mashino- bounded by the lean mixture limit or by the blowoff limit of the stroenie, no. 11, 1970, p. 55-60. In Russian.

185 A71 -19417

Consideration of the synthesis of a multicomponent plane flap A71-19492 # Variation of the high-temperature properties mechanism with allowance for the most advantageous values of the of jet fuels during prolonged storage (Izmenenie vysokotempera- transmission angles by using the method of least squares. The turnykh svoistv reaktivnykh topliv pri dlitel'nom khranenii). 2. A. problem is reduced to the synthesis of a mechanism with respect to Sablina, A. A. Gureev, A. A. Kukushkin, N. I. Melent'eva, B. A. three positions with optimal transmission angles over the entire range Englin, A. M. Fomina, and A. P. Griaznov. Khimiia i Tekhnologiia of divergence of the working sections of the mechanism. For the TopliviMasel, vol. 15, no. 12, 1970, p. 39-42. 10 refs. In Russian. purposes of the calculation the mechanism is divided into four closed Study of the thermal stability and corrosive properties of jet vector contours, for each of which an additional condition is given fuels stored for five years under normal conditions. The following which ensures a rigorous solution to the problem. A.B.K. general rules of fuel behavior in storage were established: (1) the initial temperature for extensive formation of nonsoluble products decreases by 10 to 20 C, (2) in the initial storage period, the thermal stability of fuels deteriorates faster than during further storage, and (3) the high-temperature properties of fuels vary depending on A71-19417 To the moon and beyond. Robert R. Gilruth chemical composition and type of fuels. The mechanism of the (NASA, Manned Spacecraft Center, Houston, Tex.). Aeronaurical Journal, vol. 75, Jan. 1971, p. 1-17. deterioration of the high-temperature properties of fuels is briefly discussed. Z.W. The history of manned flights from the ascent cf the Montgolfier Balloon to the X-l research aircraft is briefly considered, and the various phases of the space program are discussed. Aeronautical developments during the two world wars are examined, and the first steps in the area of manned space flight are reviewed. A71-19493 # Laboratory device for studying antiwear prop- The various space ventures culminating in the Apollo space flights are erties of jet fuels (Laboratornyi pribor dlia issledovaniia proti- described. The phases of lunar exploration are evaluated up to the voiznosnykh svoistv reaktivnykh topliv). A. F. Aksenov and A. A. Apollo 13 mission. Incentives for a return to the moon after Apollo Litvinov. Khimiia i Tekhnologiia Topliv i Masel, vol. 15, no. 12, are discussed giving attention to the establishment of a permanent 1970, p. 47-49. 6 refs. In Russian. lunar base. Asoects of the development of the space shuttle as the Description of a device for measuring the antiwear properties of keystone to the practical age of space travel are considercd. G.R. fuels under conditions of rolling friction. The results obtained for different fuels are presented in terms of relationships for the wear as a function of load cycles, rolling rate, contact load, and bulk fuel temperature. The accuracy of results obtained is estimated. Z.W. A71-19421 Some notes on helicopter stability under constraint. P. E Kumar (Hawker Siddeley Aviation, Ltd., Hatfield. Herts.. England) Aeronautical Journal, vol. 75, Jan. 1971, p. 48-52. 5 refs. Some aspects of longitudinal stability under constraint as A71 -19494 Integrated drive generators for aircraft. R. J. applicable to the flight of a helicopter in the forward and the hover Kennett (Rotax Aircraft Equipment, Ltd., Bradford, Yorks.. modes are considercd. The lonyitudinal equatlons of motion of a England). ElectronicsandPower, vol. 17, Feb. 1971, p. 73-76. helicopter are examined. Questions of stability in forward flight Discussion of recent improvements in the power/weight ratio of under constraint are investigated taking into account attitude aircraft ac generators. A 60 kVA integrated drive generator (IDG) is

constraint. height constralnt, and speed constraint. Stability in described ' ihich is designed to supply 400 Hz 3-phase power at 11 5 hovering flight is explored under conditions of attitude constraint, V (line to neutral) to the aircraft bus bars. The compact IDG height constraint, and horizontal speed constraint. The need for harnesses to best effect the advantages of the direct liquid-cooled ac suitable cyclic pitch control in view of the instabilities occurring generator. It is of the 3-stage, rotating rectifier configuration. F.R.L. during certain flight conditions when constraints are being applied is pointed out. G.R. A71-19556 The application of computer aids in the analysis of fault data generated by a large data handling system. M. J. Reynolds and T. V. Attwood (Plessey Co., Ltd., Liverpool, England). A71 -19424 Static discharge. B. L. Per1 y (Air Registration In: Reliability in electronics; Institution of Electrical Engineers, Board, Redhill, Surrey. England). Aeronaurical Journal, vol. 75, Jan. Conference, London, England, December 10-12. 1969, Proceedings. 1971, p. 70, 71. London, Institution of Electrical Engineers (IEE Ai7 attempt is made to outline the hazards which can arise due Conference Publication No. 60).1969, p. 45-51. to static electricity giving attention to cases involving light aircraft. Discussion of the development of the data logging, classification, Conditions under which static electrical build-up can occur are analysis, and reporting methods currently in use in a large integrated examined, and accidents caused by this build-up are discussed. air traffic control system now in course of commissioning. The first Elements producing a dangerous situation are analyzed, and step towards automatic processing was taken when it became obvious approaches to reduce accident hazards are investigated. G.R. that the amount of data to be analyzed would be greatly in excess of the capability of the available staff. A standard punched card was devised to hold all the basic data such as locations and serial A71 -19425 De-icing of runways from the air. John Briscoe numbers, types of component involved, number of hours in service, a (British Airports Authority, London, England). Aeronautical terminal automation has and will be performed in an attempt to Journal, vol. 75, Jan. 1971, p. 71, 72. promote safety and relieve congestion in the nation's major terminal Discussion of various approaches for de-icing runways taking air traffic systems. This paper describes the work which has been, is into consideration the use of aircraft and of vehicles for spreading being, and is intended to be pursued in this area. (Author) de-icing chemicals. The solution of heating runways is dismissed as impractical. Reasons are the high cost and the fact that flocks of birds are attracted to heated runways. The use of chemicals as A71-19557 Experience gained from reliability trials on an de-icing agents is discllssed. In Europe liquid mixtures of solvents and airborne radar. J. E. Green (Royal Radar Establishment, Malvern. accelerators often diluted with water are used, while urea is Worcs., England) and P. H. Mead (Ferranti, Ltd., Hollinwood, Lancs.. employed in the US. The spreading of the chemicals by aircraft is England). In: Reliability in electronics; institution Of Electrical discussed. It is pointed out that the spreading can also be done from Engineers, Conference, London, England, December 10-12, 1969, a wehicle, which can be a traikr or a prime mover. G.R. Proceedings. London, Institution of Electrical

186 A71-1 9705

Enginan (IEE Conference Publication No. 60). 1969, p. 52-56. 8 aircraft regardless of means of propulsion or design speed regimes, rafr. including V/STOL types. Appropriate references for crew restraint, Review of reliability aspects of a terrain following radar escape, flight deck interior doors, fire and smoke hazards, and designed for the TSRL aircraft, with recornmendations for future personnel environmental protection are cited. F.R.L. improvement in reliability. Reliability testing of subunits made the largest contribution to reliability. The MTBF was increased through reliability trials and subsequent modification by a factor of about five to over 90 hr and potentially much higher with further A71-19644 Aircraft indicating systems. SA€ Aerosppace development work. The optimum bum-in time for this equipment Recornmended Practice, ARP 1088. Dec. 15.1970.4 p. Recommendation of certain basic considerations which the appeared to be 150 to 200 hr. The general circuitry accounted for design engineer should observe when designing a visual warning only 20% of the failures, and the transmitter, receiver, and certain indicating system. Categories of indicating systems are those dis- special parts contributed the most failures. The average pafts failure playing warnings, a need for caution, or indicators of advice. Design rate of the general circuitry reflected special efforts in initial design uiteria. color and brightness recommendations, and standards for in such areas as selection, derating, and bum-in parts, in addition to master indicators are outlined. F.R.L. the benefits of reliability trials. F.R.L.

A71-19592 On the nature of fluctuating circulation, lift A71-19645 Design objectives for flying qualities of civil and flowinduced structural vibrations. T. L. Shaw (Bristol, Uni- transport aircraft. SAE Aerospace Recommended Practice, ARP versity, Bristol, England). Journal of Sound and Vibration. vol. 14. 8426, Nov. 30.1970. 19 p. Jan. 22,1971, p. 251-261.7 refs. This Aerospace Recommended Practice sets forth the design It is commonly considered that periodic oscillations of a objectives for flying qualities for subsonic, transonic. and supersonic structure in relative motion through a fluid result from vortices being civil transport type aircraft. It is based on the military specification shed into the wake of the body. It is contended that this concept MIL-F-8785 (ASG) which comes closest to expressing the type of accounts for the observed vibration of cables, stacks, towers, and the material and format desired. However, the content is modified, like. even though the similar behavior of other structures, wch as updated, and pointed toward desirable modem transport flying sluice gates, may not similarly be explained. This paper reconsiders qualities. V.P. the fluid-mechanic phenomena accompanying flow past two- dimensional bodies of various forms, and concludes that vortex shedding is associated with, but not the cause of, pressure fluctuations and structural vibrations. (Author) A71-19646 Escape provisions - Flight deck. SA€ Aero- space RecommendedPractice, ARP 808A. Dec. 15,1970.3 p. The purpose of this Aerospace Recommended Practice is to establish criteria for the provision of crew escape facilities from the A71-19628 Special purpose talemeter for a jet engine flight deck area of commercial transport aircraft. It applies to all environment. Dominick Colangelo (GE Electronics Laboratory, transport category aircraft certificated under FAR 25. regardless of Syracuse, N.Y.) and Fred Schlereth (Inficon. Inc.). Telemetry means of propulsion. design speed regime. or type of PaYlod. v.p. Journal, vol. 6, Feb.-Mar. 1971, p. 15-18. 5 refs. Research supported by the General Electric Co. Problems involved in the design of special purpose telemeters are examined, with particular reference to a special telemeter intended A71-19647 Gas turbine engine steady state performance to transmit strain and temperature data from the rotor of a jet presentation for digital computer progams. SA€ Aerospace Recorn- engine. It is shown how a difficult design problem which arose out of mendedPactice, ARP 6818. Dec. 15,1970. 16 p. the requirement to provide a large number of channels of informa- This Aerospace Recommended Practice provides a method for tion simultaneously while still providing a rather wide bandwidth in the presentation of gas turbine steady-state performance as calcu- the strain channels could be solved by using a time division multiplex lated by means of digital computer programs. It is intended to to transmit six temperature channels on a single RF channel, and facilitate wch calculations without unduly restricting the method of then using separate RF channels in a manner indicated. V.P. calculation used by the program supplier. A general description of the engine is provided. The description includes the type of engine, general arrangement, and all general characteristics that are necessary to understand the performance and operation of the engine A71-19642 Electronic equipment cooling by the draw- represented by the computw program. V.P. through method in commercial jet transports. SA€ Aero- Information Report, AIR 64A. Oct. 26, 1970. 9 p. Formalization of the applicable design concepts considered acceptable for draw-through cooling of electronic (avionic) equip A11.19705 # Airplane high-lift system design by interactive ment installed in subsonic amd supersonic commercial iet transports. qaphics system. Aadu Karemaa (General Dynamics Corp., Convair TO improve the reliability of operation and to minimize operational Div., San Diego, Calif.). American lnstitufe of Aeronautics and penalties and dirt contamination caused by undercooling, uniform Astronautics, lntegrated lnformation Systems Conference, Palo Alto, standards of providing adequate and effective ‘draw-through’ cooling Calif.. Feb. 17-19, 1971, Paper 71-227.9 p. 17 refs. Members, $1.50; Of this equipment are set based on the described method of internal nonmembers. $2.00. air circulation and collection. A sketch of a typical internal Description of equipment and procedures for the development circulation system and design data for internal circulation are of wing high-lift or flap designs using an interactive graphics system presented. O.H. as the link between the computer and the user. The operator changes the high-lift section geometry on a display tube by means of a light pen. A high-speed digital computer calculates pressure distributions A71-19643 Crew safety provisions for cargo aircraft. SA€ about the individual wing and flap sections and integrates the Aerospace Recommended Practice, ARP 1139, Dec. 15, 1970. 1 p. pressures to obtain forces and moments. The latter are displayed to Recommendations of provisions for crew safety and survival the operator together with pressure distributions for each section. which are intended to apply to cargo aircraft and equipment. This The operator can compare these aerodynamic data with the results of Aerospace Recommended Practice applies specifically to cargo other data sets to obtain conclusions about the effects of geometric

187 A71 - 19710 changes on the lift, drag, pitching moments, and pressure distribu- Information Systems Conference, Palo Alto, Calif., Feb. 17- 19, tions. The system is not intended to eliminate the classical wind 1971, Paper 71-240. 12 p. 6 refs. Members, $1.50; nonmembers, tunnel, but can be used to reject nonoptimum configurations from $2.00. the tunnel test scheme. A specific application is described which Basic features of the collision avoidance problem are sum- involves the design of a high-lift system for the Space Shuttle marized, and a three-phase time-ordered functional organization is booster. TN. proposed for Ground-Based Collision Avoidance. Information flows are identified, with particular emphasis on information provided to the controller through interactive displays. Three generic types of display capability are proposed, and alternative formats are discussed A71-19710 # A passive computer-augmented antenna- for each type. Experience gained with a dynamic simulation model pointing system. Andrew P. Moll (RCA, Missile and Surface Radar incorporating some of these capabilities is discussed. Some specific Div., Moorestown, N.J.). American Institute of Aeronautics and problem areas are indicated which must be understood prior to Astronautics, In regrated Information Systems Conference, Palo Alto. further development of Ground-Based Collision Avoidance. (Author) Calif., Feb. 17-19, 1971, Paper 71-233. 9 p. 6 refs. Members, $1.50; nonmembers, $2.00. Description of an airborne antenna pointing system which A71-19717 Automation of terminal Air Traffic Control accurately tracks communications satellites by computing pointing # - Past, present and future. J. C. Nelson and R. P. Sunderman (Sperry angles based on stored ephemeride data, time of day, aircraft Rand Corp., Univac Div., St. Paul, Minn.). American Institute of position, and attitude. An error analysis is presented, showing that Aeronautics and Astronautics, Integrated Information Systems Con- the limiting error component is aircraft position. Stabilization is ference, Palo Alto, Calif., Feb. 17-19, 1971. Paper 71-242. p. 11 carried out by a hybrid computer-gyro loop. Tradeoffs in bandwidth, 9 refs. Members, $1.50; nonmembers, $2.00. sampling rates, and word length are discussed, and program flow The intention of this paper is to provide an overview of the charts are illustrated together with the input-output interrupt evolutionary process of system automation in the terminal Air structure. Ground-based pointing errors of less than 30 arc minutes over a 4-hr period have been achieved. T.M. Traffic Control environment, Most of the funding and work in the area of Air Traffic Control automation during the past 10 years has been directed toward the area of enroute Air Traffic Control, specifically toward the function of directing and controlling traffic A71-19711 # Automatic processing of multispectral observa- between terminal air spaces. With the advent of the passage of the tions. M. Y. Su (Northrop Corp.. Huntsville, Ala.) and F. R. Krause Airports and Airways Bill by Congress, much additional work in (NASA, Marshall Space Flight Center, Huntsville, Ala.). American terminal automation has and will be performed in an attempt to Institute of Aeronautics and Astronautics, Integrated Information promote safety and relieve congestion in the nation's major terminal Systems Conference, Palo Alto, Calif., Feb. 17-19, 1971. Paper air traffic systems. This paper describes the work which has been, is 71-234. 13 p. 13 refs. Members, $1.50; nonmembers, $2.00. being, and is intended to be pursued in this area. (Author) Statistical methods for inventory boundary determination and data flow compression are examined in application to the automatic processing of multispectral remote earth observations from aircraft and spacecraft. A simple statistical method is developed for the ~71-197ia ,Y Exploring future tactical air information subdivision of a strip map into inventory areas. The method employs distribution by simdlation. Richard E. Zapolin (Mitre Corp., a variance test for classification of individual resolution elements by Bedford, Mass.). American Institute of Aeronautics and Astronautics, analyzing the deviations of reflectance spectra. Training areas and Integrated Information Systems Conference, Palo Alto, Calif., Feb. reference spectra are not needed for this analysis. The automatic 17-19, 1971, Paper 71-243. 7 p. Members, $1.50; nonmembers, determination of inventory boundaries is illustrated for specific data $2.00. obtained by a multispectral scanner. Data flow compression is PLRACTA is an advanced development program for a multiple- accomplished by replacing all resolution elements of an inventory access, real-time tactical information distribution system. To reduce technical risks and to confirm that PLRACTA can enhance ractical area with their area average. T.M. air operation, the Mitre Corporation is designing and constructing a tactical air control system test facility. The use of cockpit simulators in this facility provides an economical, flexible means of examining the system's performance and evaluating capabilities provided by A71-19714 # A project information and simulation system various design alternatives. This paper discusses factors considered in for aerospace management. A. C. Singhal, J. J. Rosati, and G. Doeh consolidating the information needs of tactical aircraft, how the (TRW Systems Group, Redondo Beach, Calif.). American Institute of Aeronautics and Astronautics, Integrated Information Systems Con- design options are tested, and how the results influence the final ference, Palo Alto, Calif.. Feb. 17-19. 1971, Paper 71-238. 9 p. integrated information system design. (Author) Members, $1.50; nonmembers, $2.00. An integrated system, requiring a dynamic data base, provides management decision data related to the overall effect of typical A71-19719 # An overview of the National Airspace System. problems in aerospace vehicle development programs. Simulation J. W. Rabb and K. P. Gray (FAA, National Airspace System Program models allowing management to determine the impact of engineering Office, Washington, D.C.). American Institute of Aeronautics and changes and delays on program and subprogram costs and schedules, Astronautics, Integrated Information Systems Conference, Palo Alto, with a technique for project status evaluation, are presented, Calif., Feb. 17-19, 1971, Paper 71-244. 12 p. Members, $1.50; Analytical simulation models permit design optimization, evaluation nonmembers, $2.00. of competitive proposals, vehicle and system performance verifica- Description of the FAA program for modernization of the air tion, configuration tradeoff studies, and identification of potential traffic control system by increased automation of en route and problems. Advantages of the system to project management are terminal facilities. The program, when completed, will provide discussed and several examples of simulation model usage for a automation at each of the 20 air route traffic control centers and hypothetical helicopter program are given. (Author) those terminals where automation is warranted. These facilities will be interconnected by data transmission links, and the entire complex will function as a single nationwide real-time automated system to A71-19716 li A conceptual outline for ground-based col- ensure increased capacity and safety. NAS (National Airspace lision avoidance. D. R. McMillan (Mitre Corp.. Bedford, Mass.). System) En Route Stage A is the term applied to the en route American Institute of Aeronautics and Astronautics, Integrated portion of the automation program, while ARTS Ill (Advanced

188 A71 -19740

Radar Terminal System) covers the terminal automation program. conditions of a blunt body into the earth's atmosphere. The These plans are outlined in terms of the required central computer composition and parameters of a molecular nitrogen flow impinging complex, display subsystems, computer programs, and software and on a shock wave are calculated. V.P. hardware design features. T.M.

A71-19732 # Transonic gas flow in axisymmetric Laval nozzles with steep walls (0transzvukovom techenii gaza v osesim- A71-19721 # Displays in the National Airspace System. W. metrichnykh soplakh Lavalia s krutymi stenkami). V. I. Kireev and R. Sousa (Mitre Corp., McLean, Va.), H. I. Brody (FAA,Washington, lu. B. Lifshits. Akademiia Nauk SSSR, Izvestiia, Mekhanika D.C.), and R. W. Lanzkron (Raytheon Co., Lexington, Mass.). Zhidkosti i Gaza, Nov.-Dec. 1970, p. 55-58. 9 refs. In Russian. American Institute of Aeronautics and Astronautics, Integrated Numerical results obtained by several investigators for gas flows Information Systems Conference, Palo Alto, Calif., Feb. 17-19, in the transonic region of a circular Laval nozzle with a small throat 1971, Paper 71-247. 16 p. Members, $1.50; nonmembers, $2.00. radius of curvature are analyzed for the case where the flow The computer display channel (CDC) design is broadly described parameters vary appreciably in the transverse direction. It is found as a flexible real-time data processing and display subsystem for en that, although hydraulic theory (in which the transverse distribution route air traffic control. The CDC contains a general purpose central of the flow parameters is neglected) usually provides acceptable processor and special purpose wired processors coupled to modular pressure distributions at the wall and in the flow core, this theory is buffer memories and refresh memories for servicing sixty alpha- not applicable in the case under consideration. V.P. numeric display consoles. These consoles provide a plan-view air situation display composed of symbolic radar data, aircraft track identification and altitude data, weather data, and geographic map data. Display selection controls, data filtering keys, and message A71-19733 # Experimental determination of the magnitude entry devices are provided for operator use. (Author) of intensified molecular diffusion during the turbulent mixing of supersonic slipstreams (Eksperimental'noe opedelenie vdichiny uskorennoi molekuliarnoi diffuzii pri turbulentnom smeshenii sput- nykh sverkhzvukovykh potokov). A. I. Mal'tsev. Akademiia Nauk A71-19722 # The role of communications in the National SSSR, lzwstiia, Mekhanika Zhidkosti i Gaza, Nov.-Dec. 1970, p. Airspace System. R. G. Nystrom (Mitre Corp.. McLean, Va.) and K. 59-65. 6 refs. In Russian. F. Bierach, Ji. (FAA, Washington, D.C.). American institute of A relation between the magnitudes of molecular diffusion and Aercnastks and Astaxautics, Inlegrared InfixZath Systems Con- ti;ibulent #mixing is derived on the basis of experimental data ference, Palo Alto, Calif.. Feb. 17-19, 1971, Paper 71-248. 6 p. obtained in a cylindrical mixing chamber by an opticaldiffusion Members, $1.50; nonmembers, $2.00. method proposed by Prudnikov. It is shown that the relative value of The role of data communications is discussed as a vital part of molecular diffusion increases when the absolute value of turbulent the National Airspace System. The data communications subsystem mixing decreases. V.P. provides for radar data and flight data acquisition, as well as for intersystem data transfer. In addition, data and voice communications play a major role in the present farflung Air Traffic Control System. A vast network provides for air-ground and A71-19739 ,# Strong viscous interaction on a delta wing and intercontroller voice rommunicationz as well as backup for data on an oblique airfoil (0sil'nom viazkom vzaimodeistvii na treugo1'- transmission. These roles are reviewed both as they exist today and nom i skol'ziashchem kryl'iakh). I. G. Kozlova and V. V. Mikhailov. as they will appear in the era of Automated Air Traffic Control Akademiia Nauk SSSR. Izvestiia, Mekhanika Zhidkosti i Gaza, across the next decade. M.V.E. Nov.-Dec. 1970, p. 94-99. In Russian. Derivation of self-simulating equations for the flow of a viscous gas on a delta wing and on an oblique airfoil at incident-flow Mach numbers equal to infinity. It is shown that solutions for the flow in a A71-19729 fu Nonstationary lowdensity flows possessing state of strong viscous interaction are not unique for both wings. A symmetry (0 nestatsionarnykh techeniiakh razrezheniia, obladaiu- condition is derived which must be satisfied by the solution at the shchikh sirnmetriei). 0. V. Rysev. Akaderniia Nauk SSSR, Izvestiia, symmetry axis of a delta wing with infinite span. A class of Mekhanika Zhidkosti i Gaza, Nov.-Dec. 1970. p. 34-39. In Russian. self-similar flows in the boundary layer on a thin delta wing is Analysis of the system of two equations describing non- described. T.M. stationary isentropic lowdensity flows possessing axial or central symmetry. By using a canonical form of the relations which are fulfilled along the characteristics, it is shown that in certain cases nonstationary lowdensity flows can contain a characteristic along which the rate of flow and the speed of sound vary in the same A71-19740 # Nonlinear theory of a rotor in an axial regime manner as in a flow from a stationary source. V.P. (K nelineinoi teorii rinta v osevom rezhime). M. M. Barshai. Akademiia Nauk SSSR, Izvestiia, Mekhanika Zhidkosti i Gaza. Nov.-Dec. 1970, p. 100-104. 9 refs. In Russian. Aerodynamic synthesis of a helicopter rotor under hover and A71-19730 # Role of radiation absorption in front of a vertical ascent conditions, using a nonlinear vortex approach where shock wave in the hypersonic flow past a blunted body (0 roli the shape of the free vortex surface is determined in the process of pogloshcheniia izlucheniia pered udarnoi volnoi pri giperzvukovom calculation. One set of calculations is based on a rotor model in obtekanii zatuplennogo tela). V. K. Vertushkin and E. A. which the free vortex surfaces are determined from a set of rotor Romishevskii. Akademiia Nauk SSSR, Izvestiia, Mekhanika Zhidkosti vortex lines whose pitch varies along the radius and depends on the iGaza, Nov.-Dec. 1970, p. 40-47. 10 refs. In Russian. induced velocity at a given blade radius in the rotor's rotational Theoretical considerations are presented concerning the inter- plane. This is in contrast to the linear vortex approach where the action between the radiation emitted from the shock wave region pitch is specified a priori. In another set of calculations, it is assumed and the oncoming cold air flow, in the case of hypersonic flows past that the pitch of the vortex lines varies along the vertical coordinate blunted bodies. The conditions at a strong shock front are derived as well as along the radius, and allowance is made for jet contraction with allowance for the absorption of the leading radiation. The role behind the rotor. The overall characteristics of the rotor are of the dimensionless parameters which occur in this case is identified, specified, and the load distribution along the blade radius is and the value of these parameters are evaluated for several reentry determined. T.M.

189 A71-1 9741

A71-19741 # Limits of applicability of one exact solution of gas to which heat is supplied participates in creating the lifting force the problem involving interaction of a shock wave with a wedge as well as the thrust. This situation involves the tendency of the moving at supersonic speed (Granitsy primenimosti odnogo tochnogo engine to participate in the lift formation process. T.M. resheniia zadachi vzaimodeistviia udarnoi volny s klinom, dvizhu- shchimsia so sverkhzvukovoi skorost'iu). G. M. Arutiunian. Akade- miia Nauk SSSR, Izvestiia, Mekhanika Zhidkosti i Gaza, Nov.-Dec. I 1970, p. 104-107. In Russian. A71-19748 # Influence of the suppression of chemical re- I Analysis of the geometry of regions formed by intersecting actions in a nonequilibrium laminar boundary layer on the heat wavefronts during the interaction of a bow shock wave with an exchange (0vliianii na teploobmen zamorazhivaniia khimicheskikh incident shock wave whose front is parallel to a wedge surface, reaktsii v neravnovesnom laminarnom pogranichnom sloe). V. G. Emphasis is placed on the boundary between a region of undisturbed Voronkin. Akademiia Nauk SSSR, Izvestiia, Mekhanika Zhidkosti i flow over the trailing portion of the surface and a region of disturbed Gaza, Nov.-Dec. 1970, p. 127-129. In Russian. flow caused by the interaction of the bow shock wave with the Investigation of local heat flux values in a laminar boundary reflected front of the incident wave. Three different geometrical layer of multicomponent dissociating airflow over a two-dimensional configurations of this boundary are defined as a function of shock blunted body of constant thickness whose surface has equal catalytic wave velocities, gas parameters, and the bow shock wave's separation properties for oxygen and nitrogen. The pressure over the surface changes near the angular frontal regions, leading to a suppression of angle. T.M. chemical reactions in the boundary layer. It is shown that the heat flux ratios can differ significantly from the nonequilibrium case due to a varying degree of suppression of the chemical reactions in A71 -19743 # Investigation of threedimensional separation different regions of the boundary layer. T.M. flow around half-cones mounted on a flat plate (Issledovanie trekhmernogo otryvnogo obtekaniia polukonusov, ustanovlennykh na ploskoi plastine). V. S. Avduevskii and V. K. Gretsov. Akademiia Nauk SSSR, Izvestiia, Mekhanika Zhidkosti i Gaza, Nov.-Dec. 1970, A71-19750 # Experimental stub, of flow in the wake p. 112-115. In Russian. behind thin plates (Eksperimental'noe issledovanie techeniia v slede Experimental study of the influence of viscosity on the za tonkimi plastinami). A. N. Sekundov and 0. V. lakovlevskii. supersonic flow around circular half-cones mounted on a flat plate. Akademiia Nauk SSSR, Izvestiia, Mekhanika Zhidkosti i Gaza, The geometrical characteristics of the regions of turbulent boundary Nov:Dec. 1970, p. 131-137. 14 refs. In Russian. layer separation on the plate are determined along with the physical Experimental data for the flow structure in the wake behind features of flow in these regions. The positions of the spreading and thin plates in a wind tunnel at free-stream velocities of 2 and 10 separation lines on the cones are specified as a functioq of the cone's m/sec and Reynolds numbers between 155 and 730. Nonsimilar flow orientation to the undisturbed flow direction. T.M. regions in the wake are analyzed for transient and turbulent flow conditions. Measured values of velocity fields, temperature, turbulence intensity, and the scale of turbulence are compared for different flow conditions in the wake behind plates. Comparison is A71-19744 # Similarity of supersonic separation regions also made with data available in the literature for wakes behind (Podobie sverkhzvukovykh sryvnykh zon). M. G. Morozov. cylinders. It is shown that the most complex flow structure occurs in Akademiia Nauk SSSR, Izvestiia, Mekhanika Zhidkosti i Gaza. the wake behind a plate with a turbulent initial boundary layer. T.M. Nov.-Dec. 1970, p. 115-118. In Russian. Experimental study of supersonic air flow patterns over rectangular indentations on plane and axisymmetric surfaces. Static pressure and adiabatic temperature distributions were examined A71-19773 # Investigations on the transonic flow around along the contours of notches with edges positioned both evenly and aerofoils. Bernardus Maria Spee. Delft, Technische Hogeschool, at different levels. Measured data are given for the drag of a Afdeling der Technische Natuurkunde, Doctor in de Technische conical-cylindrical body with a circular notch at different notch Wetenschappen Dissertation, 1969. 45 p. 40 refs. Research supported lengths and trailing-edge heights. T.M. by the Nederlands lnstituut voor vliegtuigontwikkeling. A detailed description of the behavior of unsteady disturbances in transonic flows is given, and the results of an experimental investigation, set up as a verification of the theoretical potential flow A71-19745 # Flow around an arbitrary star-shaped contour around quasi-elliptical aerofoil sections are discussed. The develop- (Obtekanie proizvol'nogo zvezdnogo kontura). V. V. Pak. Akademiia ment of the transonic flow around aerofoils is considered, and the Nauk SSSR, lzvestiia, Mekhanika Zhidkosti i Gaza, Nov.-Dec. 1970, nature of a local supersonic zone is described. The different p. 119-121. In Russian. arguments advanced against the existence of shock-free flow are Analysis of the flow pattern around an arbitrary (closed or summarized and discussed. A detailed analysis on the stability of open) star-shaped contour. An expression is derived for the complex transonic flows with respect to unsteady disturbances is given. potential on the plane of a supplementary variable which is a Experiments which show clearly the physical significance of tran- function of velocity constructed in such a manner that the given sonic potential flow solutions are discussed. G.R. contour passes into the abcissa axis when mapped onto the supplementary plane. The function mapping the supplementary plane on the desired flow plane is obtained by integration. T.M. A71-19860 # Numerical methods for nonreacting and chemically reacting laminar flows - Tests and comparisons. Clark H. A71-19746 # Supersonic threedimensional flon with heat Lewis (Virginia Polytechnic Institute and State University, supply and stream deflection (Sverkhzvukovoe prostrznstvennoe Blacksburq. Va.). Journal of Spacecraft and Rockets, vol. 8, Feb. techenie s podvodom tepla i otkloneniem potoka). V. S. Sadovskii 1971.p. 117.122. 10refs. and G. I. Taganov. Akademiia Nauk SSSR, Izvestiia, Mekhanjka Assessment of calculations of eqililibrium, nonequilibrium, and

'Zhidkosti i Gaza, Nov.-Dec. 1970, P. 121-125. In Russian. ideal gas (gamma 2 1.4) laminar boundary layers and viscous shock Analysis of flow conditions at large supersonic flight velocities layers over a 10 deg half-angle hyperboloid, 50 nose-radii long, for where the mass of air participating in the formation of thrust per three 20,000-fps cases, one at 100,000-ft altitude and two at unit time is comparable to the mass of air deflected downward by 250,000 ft. The predicted skin-friction and heat-transfer coefficients the wing. Attention is given to the aerodynamic-force producing and displacement-thickness distributions over the body, as well as efficiency of a body characterized by the fact that the same mass of property profiles across the layer at the ends of the body, are

190 A71 -19892 cwnpared. The conditions were chosen to test the ability 0%the A71-19887 # Effects of rotary inertia on the supersonic numerical methods to predict nonequilibrium viscous-layer flows flutter of sandwich panels. Frank A. Marafioti and E. Russell near and far from chemical equilibrium and the applicability of Johnston, Jr. (Connecticut, University, Storrs, Conn.). AlAA boundary-layer theory at low-Reynolds-number conditions. Results Journal, vol. 9. Feb. 1971, p. 245-249. 8 refs. NSF Grant No. GJ-9. show that recently developed finitedifference methods can be used A theoretical analysis is presented for the supersonic flutter of a to compute finite rate, chemically reacting flows near chemical simply-supported isotropic sandwich panel. The aerodynamic loading equilibrium. and iterations of implicit finitedifference solutions are is described by a static approximation valid for a wide range of Mach required for accurate results. At 250,000-ft altitude, higher-order number. Small deflection theory for sandwich plates which considers boundary-layer theory is not adequate and a fully viscous shock-layer transverse shear deformations and rotary inertia in addition to technique must be used. At the higher altitude, stagnation heat bending is used. The purpose of this study is to demonstrate the transfer is strongly affected by shock slip. (Author) effect of the rotary inertia parameter on the critical flutter speed of simply-supported panels. Previous investigators have neglected this effect and results obtained are of an anomalous nature for certain A71-19872 # Flight measurement of aerodynamic co- plate parameters. The effect of such plate parameters as rotary efficisnts on a bomb. Neil Edmund Gilbert (Weapons Research inertia, transverse shear, and midplane stress resultants on the critical Establishment, Salisbury. Australia). Journal of Spacecraft and flutter speed are presented in graphical form. (Author) Rockets, vol. 8, Feb. 1971, p. 186-189. 11 refs. Free flight measurement of aerodynamic lateral force and static normal and side moment coefficients on bombs stabilized by fixed cruciform fins. In particular, one type of flight instability, namely A71-19890 # Computation of nonequilibrium merged stag- the catastrophic yaw. was studied. The dependence of the derived nation shock layers by successive accelerated replacement. Thomas aerodynamic forces and moments upon the total angle of incidence, C. Dellinger (GE Fluid Mechanics and Chemistry Laboratory, angular orientation relative to the plane of incidence, and the angular Philadelphia, Pa.). (American Institute of Aeronautics and Astro- velocity components, is determined by fitting the flight data to a nautics, Fluid and Plasma Dynamics Conference, San Francisco, mathematical model of the force and moment system developed by Calif., June 16-18, 1969, Paper 69655.1 AIAA Journal, vol. 9, Feb. Maple and Synge. The instrumentation and experimental procedure 1971. p. 262-269. 17 refs. is described. The free flight data recorded by the various instruments Results for fully merged shock layer computations in the stagna- used are compared with those obtained in a wind tunnel and tion region of a hypersonic body. Piumerical solutions are obtained analyzed. O.H. with a new technique which avoids several troublesome aspects of previotir methods. The effects cf "oneq,ui!ibrium chemistry are studied for a multicomponent air mixture, and the resulting electron A71-19877 * # Flow coefficients for supersonic nozzles with concentrations are calculated. The analysis assumes a continuum comparatively small radius of curvature throats. L. H. Back and R. F. approach and employs the well-known "locally similar" flow model. Cuffel (California Institute of Technology. Jet Propulsion Labora- The governing system of equations constitutes a two-point bound- tory, Propulsion Research and Advanced Concepts Section. ary value problem which is solved using a simple finite difference method called successive accelerated replacement (SAR). Special Pasadena, Calif.). Journal of Spaowraft and Rockers, vol. 8, Feb. attention is given to a singularity that appears in the continuity 1971, p. 196-198. 20refs. equation, and the importance of an acceleration factor on the Determination of the mass flow rate through supersonic nozzles, convergence of the solution is discussed. The application of the with emphasis on nozzles with comparatively small ratios of throat numerical technique to solve the downstream flowfield is suggested. radius of curvature to throat radius (between 0 and 2.0) tested at Solutions are obtained for a Revnolrls niimher ran!- of 814 to 4000 relatively high Reynolds numbers (larger than I .~,OOOi.Measured and for flight speeds from 15,000 to 26,000 ft/sec. Predicted results values of the mass flow coefficient are presented for nozzles recently for the electron concentration are compared with experimental data, tested at the Jet Propulsion Laboratory and for those tested and good agreement is obtained. (Author ) previously in other investigations. The measurements provide a basis on which to evaluate the effect of the throat radius of curvature/ throat radius ratio on the flow coefficients and to appraise existing prediction methods for isentropic flow by other investigators. O.H. A71-19891 # Anemometer measurements of velocity and density in projectile wakes. Jay Fox and Harald Rungaldier (TRW Systems Group, Redondo Beach, Calif.). (American Institute of Aeronautics and Astrorwutics, Fluid and Plasma Dynamics Confer- ence. Los Angeles, Calif.. June 24-26, 1968, Paper 68-701.1 AIAA A71-19879 ft Electron thermochemical nonequilibrium Journal, vol. 9. Feb. 1971, p. 270-276. 24 refs. Contracts No. AF effects in reentry boundary layers. Doyle Knight (General D. W(694)-992; NO. AF 04(701)-6&C-o041; NO. AF Electric co.. Space Div., Philadelphia, Pa.). (American Institute of p4(701)-69-C-0119. Aeronautics and Astronautics, Aerospace Sciences Mmting, 7th, New Mean and fluctuating wake properties including both velocity York, N. Y., Jan. 20-22. 1969, Paper 6982.1 AlAA Journal, vol. 9, and density (which is equivalent to inverse temperature in the Feb. 1971, p. 193-199. 19 refs. constant-pressure far wake) were measured with hot-film anemom- Results of calculated nonequilibrium electron temperature and eters. The projectiles were . 22-in. blunt bullets at 4000ft/sec. concentration characteristics in boundary layers are presented for half-inch spheres at 6500 ftlsec, and slender cones at 6500 ftlaec. reentry conditions of flight velocity from 27, 500 to 34, 000 ft/sec, Simulated altitude was used during many tests, data being analyzed and altitude from 110, 000 to 150, 000 ft. These results show the from 100 to 160, 000 diameters behind the projectiles. Excellent effects of reactions, collisions, electrical current, and electron agreement was obtained between the measured mean wake velocity reflection on the electron heat transfer and temperature. The elec- and the analytical computations using the Lees-Hromas-Webb (LHW) tron conservation equations in boundary-layer form were solved in theory. Agreement was obtained between the measured space the quasi-neutral region with collisionless sheath boundary conditions correlation length and the predictions of the LHW theory. Thus the or approximate boundary conditions derived from the collisionless understanding of these important parameters has been increased by sheath expressions and valid wlth collisions in the sheath. A numeri- the verification of the LHW theory by laboratory measurements. cal solution was obtained by a finite-difference technique after a (Author) similarity transformation and quasi-linearization of the equations. The solutions show significant temperature nonequilibrium. Elec- tron current and reflection, combined into a single parameter, reduces electron temperature and increases conduction of energy A71-19892 # Boundary layer on a hypersonic sharp cone at but does not explicitly affect electron concentration. Diffusion of small angle of attack. H. A. Dwyer (California, University, Davis, ionization energy is insensitive to electron reflection. (Author) Calif.): AlAA Journal, vol. 9, Feb. 1971, p. 277-284. 14 refs.

191 A71 -19893

The compressible, laminar boundary-layer flow over a sharp on some type of wave distortion which is almost invariably exhibited cone has been calculated for an angle of attack slightly greater than by acoustic mode instability in rocket and jet engines, even when the the cone half angle. The calculations have been carried out with an distortion is small and seemingly negligible. The analysis is based on a inviscid flow based on an asymptotic inner and outer expansion of combustion model where the burning rate is simply related to a the flowfield. The asymptotic expansion has been carried out for Reynolds number to the one-half power. The analysis shows wave both first and sec0n.d order in the angle of attack, and the need for distortion to be a crucial variable affecting combustion stability. It the second-order results in the boundary4ayer calculations has been car: amplify the response of a Reynolds number controlled process studied. The flow conditions were chosen so that the theoretical beyond that needed for unstable combustion. It is pointed out that calculations could be compared with experimental results for harmonic distortion in combustors should be minimized because it is important boundary-layer parameters, such as heat transfer and a cause of combustion instability. M.M. boundary-layer thickness. The results of the investigation show that the boundary-layer equations and the second-order inviscid flow describe well the boundary4ayer characteristics, and that higher- A71-19908 # Vortex shedding from circular cylinders in an order boundary-layer influences are not important for the flow oscillating freestream. C. F. Chen and David B. Ballengee (Rutgers conditions studied. The most important interaction effect between University. New Brunswick, N.J.). AlAA Journal, vol. 9, Feb. 1971, the boundary layer and inviscid flow was determined to be the p. 340-342. Contract No. AF 44(620)-68-C-0018. (Author) displacement effect. Description of wind-tunnel experiments on vortex shedding from cylinders in a free stream. The Reynolds number range tested

was from 500 to 4 x 10,000. and the oscillation frequencies were 3 3 A71-19893 # Some experimental results on sphere and disk and 6 Hz. Some of the conclusions suggested by the results are: (1) < drag. Frederick W. Roos (McDonnell Douglas Research Laboratories, in an oscillatory free stream of 3 Hz and Reynolds number up to 4 X St. Louis, Mo.) and William W. Willmarth (Michigan, University, Ann 10,000, the vortex sheddlng from a circular cylinder responds Arbor, Mich.). AlAA Journal, vol. 9, Feb. 1971, p. 285-291. 35 refs. instantaneously to free stream variations; and (2) in the instanta- Army-supported research. neous Reynolds number range of 500 to 4 x 10,000, the instanta- Measurements of the drag on spheres and disks moving neous Strouhal number stays sensibly constant at 0.20 plus or minus rectilinearly through an incompressible fluid for Reynolds numbers 0.01. M.M. (Re) from 5 to 100.000. Test models were mounted on a carriage which rode along a linear air bearing track system. Tests were performed by towing the models through a channel filled with A71-19913 # Reduced-order modeling in aircraft mission glycerine-water mixtures. Forces and moments on the models were analysis. Henry J. Kelley (Analytical Mechanics Associates, Inc., sensed by strain gauge transducers; hydrogen bubble flow visualiza- Jericho, N.Y.). AlAA Journal, vol. 9. Feb. 1971, p. 349, 350. 7 refs. tion was utilized in relating these forces to the unsteady wake flows. Derivation of an alternate third-order particle-dynamics model Steady drag results agreed with existing data except for the disk at used for aircraft motion. The model features instantaneously variable 100 less than Re less than 1000, in which the drag coefficient values speed by means of timexale separation, further pursuing the were up to 50% below the level of existing data; drag force approach taken by Kelley and Edelbaum (1970). The model is unsteadiness during steady motion was always less than 5% for the advanced merely as a slightly more realistic alternative to a sphere and less than 3% for the disk. Sphere drag measurements constant-speed model, for analyses in which it is important to hold under constant acceleration from rest showed the apparent mass the order to three on account of other complicating factors . e.g., concept to be valid (at high Re) until the sphere had traveled multiole aircraft. M.M. approximately one diameter, after which the quasi-steady drag (based on instantaneous velocity) showed good agreement with the actual drag. Interference effects of the sting supports used in these A71-19916 // Lighter-than-air in Canada. B. Hval (Calgary. tests are discussed. (Author) University, Calgary, Alberta, Canada). Canadian Aeronautics and SpaceJournal, vol. 17, Jan. 1971, p. 15-23. Discussion of the various aspects of the potential use of A71-19895 #/ Effects of nose bluntness, angle of attack, and unpowered balloons and, in particular, airships in modern aviation in oscillation amplitude on hypersonic unsteady aerodynamics of Canada. A brief review of the lighter-than-air activities in Canada in slender cones. Lars Eric Ericsson (Lockheed Missiles and Space Co., the recent past is presented. Several commercial possibilities in using Sunnyvale, Calif.). (American lnstitute of Aeronautics and Astro- balloons are outlined. Particular emphasis is placed on the considera- nautics, Aerospace Sciences Meeting, 8th, New York. N. Y., Jan. tion of the advantages and possible areas of application of rigid 19-21, 1970, Paper 70-216.) AlAA Journal, vol. 9, Feb. 1971, p. airships, such as cargo, passenger, and military airships. The problem 297-304. 23 refs. Research supported by the Lockheed Missiles and of planning airship development in Canada, the airship construction. Space Independent Development Program. and the project problems are examined. O.H. A previously developed analytic theory for the unsteady aerodynamics of moderately blunt slender cones has been extended to include the effects of large nose bluntness, nonzero angles of A71-19923 # Design principles of a ground effect vehicle in attack, and finite oscillation amplitudes. It is shown that the which the limitation of volumetric dissipations is accomplished with developed theory agrees well with available experimental data and the help of a fluid boundary obtained by means of the Coanda effect correctly predicts the opposite effects of nose bluntness on static and (Principii de proiectare a unui vehicul cu efect de sol la care limitarea dynamic stability including the highly nonlinear characteristics at disipatiilor volumice se face cu ajutorul unei frontiere fluide, angles of attack and oscillation amplitudes up to cone half angle obtinuti prin efect Coandd). Clement Alecsandrescu. Revista Trans- magnitudes. A universal scaling law has been derived that gives the porturilor, vol. 17, Nov. 1970, p. 489-496. In Rumanian. nose bluntness effects on static and dynamic characteristics for the Brief survey of air cushion vehicles, and discussion of general above anglc of attack and amplitude ranges with sufficient accuracy criteria and structural diagrams proposed for the aerodynamic for preliminary design of conical reentry vehicles, flying ballistic or calculation of a system for limiting volumetric dissipations from the lifting reentry trajectories (Author) vehicle's air cushion and propulsion system. Theoretical considerations are made on the vehicle's propulsion, braking, steering, A71.19906 # Amplification by wave distortion in unstable stability, compression system, and engine. M.M. combustors. M. F. Heidmann (NASA, Lewis Research Center, Cleveland, Ohio). AlAA Journal, vol. 9, Feb. 1971, p. 336-339. 5 A71-19924 # NAE multi-source schlieren apparatus for 5- refs. foot x 5-foot trisonic wind tunnel. A. Bowker (National Aeronautical Brief analysis that shows engine stability to be highly dependent Establishment, Ottawa, Canada), Canada, National Research Council,

192 A7 1-19934

Division of Mechanical Engineering and National Aeronautical Newman (Lightning and Transients Research Institute. Minneapoiis, Establishment, Quarterly Bulletin, no. 3, 1970, p. 2749. 5 refs. Minp.). In: Society of Automotive Engineers and U.S. Air Force Description of the design, operation, and control of a multiple- Avionics Laboratory, Lightning and Static Electricity Conference, source schlieren system dwelopal for flow visualizing work in the San Diego. Calif., December 9-11. 1970, Proceedings. trisonic wind tunnel of the Canadian National Aeronautical Estab- New York, Society of Automotive Engineers, Inc., lishment (NAE). Considerations leading to the choice of this 1970. p. 2535. 6 refs. particular tvoe of schlieren system are discussed, and its advantages The testing of aircraft components for new aircraft has are emphasized. Detailed parameters of the various system elements, introduced problems in trying to meet the specifications with new as well as wstem performance data, verified during the six month materials and construction techniques. Suggested is a more detailed period of system operation, are presented. An overall evaluation of analysis of the lightning characteristics in order that tests may be the system is made showing that under operational conditions it has more precisely defined for specific aircraft components as illustrated proven convenient to use and very reliable. O.H. in swept stroke studies. Of increasing concern is the performance of more vulnerable electronics systems for new aircraft, and guidelines are developed for simple calculation of approximate electric and A71 -19926 Society of Automotive Engineers and U.S. Air magnetic fields to determine pulse penetration into the vehicle Force Avionics Laboratory, Lightning and Static Electricity Con- electrical and electronic systems. Requirements for testing of all ference, San Diego, Calif., December 9-11, 1970, Proceedings. New plastic helicopter blades are also suggested. (Author) York, Society of Automotive Engineers, Inc.. 1970. 315 p. $10.00, The general characteristics of aircraft and rocket triggered natural discharges are defined, and experimental data are given for A71-19931 # Lightning test facilities measurement tech- the charging mechanisms, electromagnetic noise effects, current niques. J. D. Robb (Lightning and Transients Research Institute, transfer properties, and field distribution patterns. Some effects of Minneapolis, Minn.), R. F. Huber, and C. J. Kawiecki (Joslyn lightning on the structural integrity of aircraft and rockets are Manufacfuring and Supply Co.. Goleta, Calif.). In: Society of examined, and new protection systems are described. Test and Automotive Engineers and U.S. Air Force Avionics Laboratory, measurement facilities are outlined, and research reports are included Lightning and Static Electricity Conference, San Diego, Calif., for the structural and electrical damage sustained by advanced December 9-1 1, 1970, Proceedings. New York. composite materials exposed to lightning. The protection of aero- Society of Automotive Engineers, Inc., 1970, p. 3946. 5 refs. space ground facilities from iightning strikes is considered, and the The increasing use of small artificiai lightning generation Apollo 12 lightniny incident is analyzed. T.M. faciiities for deveiopmental testing of aircraft components by the manufacturer has required the measurements of the test currents in the presence of the strong electromagnetic fields associated with the high current discharges. Special techniques are presented for the set A71-19928 # Model studies of stroke probability to selected up of the facility high current paths and for the use of measurement points on aerospace vehicles. J. R. Stahmann (Lightning and equipment such as the oscilloscopes and high current sensors to Transients Research Institute, Minneapolis, Minn.). In: Society of assure that reasonably accurate measurements of the current wave- Automotive Engineers and U.S. Air Force Avionics Laboratory. forms are obtained. (Author) Lightning and Static Electricity Conference. San Diego, Calif., December 9-1 1, 1970, Proceedings. New fork, Society of Automotive Engineers, lnc., 1970, p. 13-16. A71-19933 #/ A study of some fundamental helicopter About sixty-six uniformly spaced fixed probed positions are charging mechanisms. M. E. Rogers (Royal Aircraft Establishment, usually used for a general study to determine the probability of Farnborough, Hants.. England). In: Society of Automotive Engineers lightning stroke contact to various points on a complete aerospace and U.S. Air Force Avionics Laboratory, Lightning and Static vehicle. More detailed studies are usually considered prohibitive Electricity Conference, San Diego, Calif., December 9-1 1, 1970, because of the large number of discharges required. For estimating Proceedings. New York, Society of Automotive very low probability of contact for detailed studies of critical Engineers, Inc., 1970, p. 57-71. 16 refs. regions, probe positions can be restricted to the small solid angle Discussion of ;wo fundamental helicopter charging mechanisms: from which contact is possible. Then, with a relatively small number 'engine' and 'rain precipitation' charging. in each case collected data of probe positions and enough discharges to measure statistical are critically examined and working hypotheses are advanced to variations, a very low probability can be estimated with a limited account for the generation process. In engines the process is seen as number of discharges. typically about thirty. (Author) one of preferential trapping of ions previously separated by thermal ionization. For Whirlwind 10 helicopters where net positive currents are observed it is considered likely that this largely results from positively charged hydrocarbon nuclei colliding with the turbine A71-19929 # Lightning and static hazards relative to air- blades. The rain precipitation process is believed to be an induction worthiness. B. L. Perry (Air Registration Board, Redhill, Surrey, effect which occurs when drops are shattered by impact with the England). In: Society of Automotive Engineers and U.S. Air Force rotor leading edge in the presence of an electric field. It is argued Avionics Laboratory, Lightning and Static Electricity Conference, that such a process could explain the large variations in charging San Diego, Calif., December 9-11. 1970, Proceedings. currents measured in these conditions, as well as the frequent New York, Society of Automotive Engineers, Inc.. 1970, p. 17-23. 11 refs. changes in polarity. F.R.L. The paper updates, and briefly extends, the statistical information on lightning strikes to aircraft given in the author's 1968 paper. The problem and potential dangers of both lightning strikes and A71-19934 # Studies of supersonic vehicle electrification. J. static build-up on aircraft are discussed and illustrated with particular E. Nanevicz and E. F. Vance (Stanford Research Institute, Stanford, reference to airworthiness. Conclusions are drawn regarding problem Calif.). In: Society of Automotive Engineers and US. Air Force and potential problem areas where further information is required Avionics Laboratory, Lightning and Static Electricity Conference, and toward which research effort should be directed. In the light of San Diego, Calif., December 9-11. 1970, Proceedings. the above, current and future airworthiness requirements are New York, Society of Automotive Engineers, Inc., considered. (Author) 1970, p. 73-88. 19 refs. Theoretical and experimental studies of airborne vehicle electri- A71-19930 # Recent developments in lightning protection fication processes are described. Laboratory experiments with for airaaft and helicopters. J. D. Robb, J. R. Stahmann, and M. M. projectiles fired through an ice-fog cloud were used to study the

193 A71 -19935

variation of frictional charging with air speed at supersonic speeds. corrective measures, useable navigation procedures and communica- These experiments demonstrated that the charge imparted by each tions could be retained in the most severe conditions encountered. particle decreases with increasing speed at supersonic speeds. F.R.L. apparently because of ice crystal melting on impact. Flight instrumentation has been designed and fabricated to measure electrification parameters and effects on a supersonic test aircraft. The instrumentation measures, charging rate, discharging rate, charge per A71-19938 # Influence of lightning and static electricity as particle, aircraft potential, streamer current and number of streamer applied to helicopter design. B. John Solak (Boeing Co., Vertol Div., pulses, variation of effective frontal area, and noise spectrum. The Morton, Pa.). In: Society of Automotive Engineers and U.S. Air philosophy of the design and construction of the flight test Force Avionics Laboratory, Lightning and Static Electricity Con- experiments and equipment are discussed. The flight test instrumen- ference, San Diego, Calif., December 9-11, 1970, Proceedings. New York, Society of Automotive Engineers, tation has been installed on an F-4 aircraft, and test flights are being Inc., 1970, p. 179-187. 11 refs. conducted. (Author) Review of three basic domains of static electricity affecting helicopters. These are (1) protection of the rotor blades against the effects of lightning strikes, (2) cargo hook operation and the related problem of active equalization of potential between the cargo and A71-19935 # Lightning current transfer characteristics of the cargo handler, and passive static electricity dischargers as a the p-static discharger installations. M. P. Amason and J. T. Kung (3) method of reducing radio interference, All three domains affect the (Douglas Aircraft Co., Long Beach, Calif.). In: Society of Auto- motive Engineers and U.S. Air Force Avionics Laboratory. Lightning whole blade design, with emphasis on the design of the blade tip. F.R.L. and Static Electricity Conference, San Diego, Calif., December 9-1 1, 1970, Proceedings. New York. Society of Auto- motive Engineers, Inc., 1970, p. 99-109. 12 refs. Research sponsored by the McDonnell Douglas Independent Research and Development A7149939 # Lightning protection for non-metallic rotor Program. blades. J. R. Stahmann (Lightning and Transients Research Institute, This paper presents the results of p-static discharger installation Minneapolis, Minn.) and G. I. Hackenberger, Jr. (Kaman Aerospace lightning tests conducted by the Douglas Aircraft Co. at its Long Corp., Bloomfield, Conn.). In: Society of Automotive Engineers and Beach, Calif. facilities and the facilities of the Lightning and U.S. Air Force Avionics Laboratory, Lightning and Static Electricity Transients Research Institute at Miami Beach, Fla. The paper discusses the lightning current transfer characteristics and lightning Conference, San Diego, Calif., December 9-11, 1970, Proceedings. protection design considerations for the p-static discharger, the New York, Society of Automotive Engineers, Inc., 1970, p. 189-194. discharger retainer, and the aircraft installation. Laboratory lightning test results are also discussed in relationship with the in-service This paper discusses general approaches to the design of experience associated with natural lightning stroke incidents. lightning protection system for nonmetallic helicopter rotor blades. (Author) Possible effect of stroke currents on conducting parts external and internal to the blade are mentioned, and general recommendations are made for disposition of protective materials. Testing of any such design is considered a necessity. A specific example is described, A71-19936 # The effects of lightning attachment phenom- tracing the development of the protective system for one particular ena on aircraft design. R. 0. Brick. L. L. Oh, and S. D. Schneider nonmetallic rotor blade. (Author) (Boeing Co.. Commercial Airplane Group, Renton, Wash.). In: Society of Automotive Engineers and U.S. Air Force Avionics Laboratory, Lightning and Static Electricity Conference, .%n Diego. Calif., December 9-1 1. 1970, Proceedings. New A71-19940 # Lightning protection on advanced fighter air- York, Society of Automotive Engineers, Inc., 1970, p. 139-156. 7 craft. G. L. Weinstock (McDonnell Aircraft Co.. St. Louis, Mo.). In: refs. Contract No. FA-SS-67-e. Society of Automotive Engineers and US. Air Force Avionics A working knowledge of swept lightning strikes has become a Laboratory, Lightning and Static Electricity Conference, San Diego, necessity for the aircraft designer involved in lightning protection of Calif., December 9-1 1, 1970, Proceedings. New aircraft incorporating new structural concepts that depart from the York, Society of Automotive Engineers, Inc., 1970, p. 195-205. conventional riveted aluminum airframe. Swept strokes have been Study of the design challenges and protective measures against simulated in the laboratory to determine realistic protection criteria lightning being used or considered for use on late models of the F-4 for components. Measurements of the maximum swept stroke dwell Phantom I1 aircraft, advanced air superiority aircraft, and electronic time on titanium and aluminum sheet are reported as well as an flight control systems. For practical aircraft protection lightning analysis of various techniques to improve the resistance of fuel tank discharges must be prevented from entering the aircraft interior and skin Panels to swept stroke effects. (Author) damaging electrical and electronic systems. causing possible fuel system explosions, and affecting crew capabilities. Openings in the aircraft skin such as radomes, canopies, camera windows. navigation lights, fuel vents, composite materials, atmospheric sensors, and A71-19937 # Electrostatic charging and noise quieting. unbonded sections all reduce the capability of the aircraft to Robert L. Truax (Dayton Aircraft Products, Inc.. Fort Lauderdale, withstand lightning strikes, Additional lightning protection require- Fla.). In: Society of Automotive Engineers and US. Air Force ments have been necessitated by the introduction of electronic flight Avionics Laboratory. Lightning and Static Electricity Conference, control systems. F.R.L. San Diego, Calif., December 9-11, 1970, Proceedings, New York, Society of Automotive Engineers, Inc., 1970, P. 157-174. Use of a system approach to identify noise sources dbe to ~71-19941 # Lightning and surge protective devices for electrostatic charging, to measurement of charging levels, application survivability of electrical systems. C. J. Kawleckl, W. ti. Kapp, W. T. of noise reduction techniques, and flight test verification. Steps Pranke, H. J. Steinhoff. and R. E. Thompson (Joslyn Manufacturing taken to reduce noise generation when the aircraft became charged and Supply Co., Goleta, Calif.). In: Society of Automotive Engineers electrically included installation of quiet dischargers, conductive and US. Air Force Avionics Laboratory, Lightning and Static coating of plastic frontal surfaces. and use of dc sealed antennas. Electricity Conference, San Diego, Calif., December 9-1 1, 1970, Actual flight tests demonstrated that with proper application of Proceedings. New York, Society of Automotive

194 A71 -19997

Engineers, Inc., 1970, p. 207-211. geatest protection of the panels from damage, combined with The proper functioning of an aircraft depends upon the minimum coating weight, was achieved with aluminum wire fabric reliability of its electrical systems. Circuit pollution by foreign and aluminum foil overlays. Other protective coatings which had electrical pulses endangers the survival of essential systems. Natural merit were: plasma sprayed aluminum; conductive paints used with surges such as lightning, and equipment selfgenerated surges cannot aluminum foil strips; and conductive coatings applied over high be avoided entirely. but their effects can be minimized using dielectric strength plastic films. (Author) appropriate lightning and surge protective devices. The surge problem is difficult to cope with; designers often gnore or postpone the problem for lack in knowledge both as to its definition and what to do about it. A cursory treatment of one kind of protector, using A71-19946 # Voltages produced by transient currents flow- sparkgap devices, is presented here for protection against direct and ing upon lie& of cables. F. A. Fisher (GE High Voltage induced lightning strikes, electromagnetic pulses, static charges and Laboratory, Pittsfield. Mass.). In: Society of Automotive Engineers equipment self-generated surges. (Author) and U.S. Air Force Avionics Laboratory. Lightning and Static Electricity Conference, San Diego. Calif., December 9-1 1, 1970, Proceedings. New York, Society of Automotive Engineers, Inc., 1970, p. 299-308. A71-19942 # Lightning protection for dielectric composites. Electromagnetic disturbances to aircraft and to aerospace and J. D. Robb (Lightning and Transients Research Institute, industrial ground facilities often produce large circulating currents in Minneapolis, Minn.). In: Society of Automotive Engineers and U.S. the shields of electrical cables. The electromagnetic disturbances may Air Force Avionics Laboratory, Lightning and Static Electricity be caused by lightning, switching of high voltage circuits or by other Conference. San Diego, Calif., December 9-11, 1970, Proceedings. electromagnetic effects. This paper presents experimental data New York, Society of Automotive Engineers, showing how surge voltages are related to the type of construction of Inc.. 1970. p. 215-221.9 refs. the cable, to the material of the cable shield, to magnitude and Dielectric composites are analyzed in terms of direct damage waveshape of the shield current and the type of termination of the from shock waves, damage from longer duration slower pressures shield. Special attention is given to industrial grade metal conduit since conduit, particularly the rigid steel variety, can have very from vaporization of dielectric or metallic solids, direct magnetic forces and burning from long duration low current continuing effective shielding properties. (Author) components. Studies have included piezo blas? gage pressure measurements and schleiren photography of the shock waves in the laboratory and pressure measurements of triggered natural lightning A71-19959 Acoustic spectra from turbulent jets. William discharges. Theoretical and experimental analysis of probable C. Meecham (California, University; Bolt Eeranek and Newman, Inc., maximum shock pressures, magnetic forces and dower pressures Los Angeles, Calif.). Acoustical Society of America, Journal. vol. 49, indicate that the principal problem is introduced through long arcs Jan. 1971, pt. 2, p. 334.338. 8 refs. developed inside sections and that the best general solution for Determination of the spectrum of the acoustic radiation from providing lightning protection is still to keep the lightning discharge turbulent jets. To solve this theoretical problem. two assumptions are currents on the aircraft exterior or provide conducton with used. First, it is supposed that the turbulent fluid has approximately sufficient cross sectional area to carry the current where the currents must penetrate the aircraft. (Author) Gaussian statistical characteristics. Then, it is supposed that the space-time characteristics for the needed second-order velocity correlation can be obtained by assuming that the fluid is approximately in 'frozen flow.' From these assumptions, the higher- frequency sound-power spectrum is obtained in terms of an integral A71-19943 # Lightning protection for advanced composite over the turbulence energy spectrum. aircraft structures. G. T. Woodrum (USAF, Materials Laboratory, O.H. Wright-Patterson AFB, Ohio). In: Society of Automotive Engineers and US. Air Force Avionics Laboratory, Lightning and Static Electricity Conference, San Diego. Calif., December 9-1 1, 1970, A71-19961 Propagation, distortion, and shock formation Proceedings. New York, Society of Automotive of pressure pulses in a nonviscous fluid of constant state. G. M. Engineers, Inc., 1970, p. 223-231. 5 refs. Schindler (Douglas Aircraft Co., Long Beach, Calif.). Amustical Consideration of the hazard of lightning strikes to composite Society of America, Journal, vol. 49. Jan. 1971, pt. 2, p. 344-351. 9 materials (boronlepoxy. graphitelepoxy. and fiberglasslepoxy), and refs. Research supported by the Douglas Aircraft Independent of means of minimizing the effects. In these materials, the plastic Research and Development Program. matrix acts as a nonconductive material, and the fibers, which are Plane simple compression waves of finite amplitude are studied imbedded, but do not touch each other in the matrix, act as as they propagate into a fluid medium of constant state. Shock conductive materials. The use of metal filled coatings, plasma formation and subsequent expansion, as well as rise and decay of sprayed coatings, and metal foil coverings is described. F.R.L. shock strength. are determined from a boundary-value problem of mixed type involving a fixed boundary (source) and a moving boundary (shock surface). At the source, an overpressure is arbi- trarily prescribed as a function of time; at the shock surface, the A71-19944 # Lightning protective coatings for boron and simple wave solutions are shown to satisfy the exact shock-transition graphite fiber reinforced plastics. John G. Breland, Jr. (USAF, conditions within an accuracy including second powers of shock Materials Laboratory, Wright-Patterson AFB. Ohio), John T. strength, while the shock speed is determined precisely. Shock speed Quinlivan, and C. J. Kuo (being Co., Seattle, Wash.). In: Society of and rise and decay of shock strength are shown to be strongly Automotive Engineers and US. Air Force Avionics Laboratory, dependent on the particular form of the overpressure generated at Lightning and Static Electricity Conference, San Diego, Calif., the source in the course of time. Approximation formulas are derived for weak shocks and are in a detailed discussion of two December 9-11, 1970, Proceedings. I New York, used Society of Automotive Engineers. Inc.. 1970. p. 233-251. examoles. (Author) Coatings and thin conductive overlays for protecting boron fiber reinforced plastics and graphite fiber reinforced plastics from A71-19997 The coming of age of the assodative processor. structural damage by simulated lightning strikes were investigated. J. A. Rudolph, Louis C. Fulmer. and Willard C. Meilander (Goodyear Laboratory tests were made in which test panels, with and without Aerospace Corp.. Akron, Ohio). Electronics, vol. 44, Feb. 15, 1971, coatings, were exposed to currents as high as 200,000 amperes. The p. 91-96. 10 refs.

195 A71-20015

Description'of the design and operation of associative processors schungs- und Versuchsanstalt fiir Luft- und Raumfahrt, (AVA) used in applications requiring high-speed searches of large, rapidly Abteilung Aeroelastik, Gottingen, West Germany). DF VLR- changing data bases with simultaneous arithmetic operations on Nachrichten, Oct. 1970, p. 101-104. In German. many pairs of numbers. In the associative processor, the single An aeroelastic triangle of forces with elastic, inertial, and arithmetic unit of the conventional digital computer has been aerodynamic forces is considered. Aeroelastic problems are in- eliminated, and the location-addressed sequentially-accessed memory vestigated taking into account static and dynamic problems. Changes has been replaced by an associative array, which is a modified in lift produced by the elastic deformation of the aircraft structure associative memory otherwise known as a constant addressed are examined, and effects on the dynamic flight stability are memory, search memory, or parallel search memory. Because the explored. An aerothermoelastic tetrahedron of forces for supersonic associative array can simultaneously compare all the items it contains and hypersonic velocities is discussed. Aeroelastic and related against some input item, it takes only one memory cycle to locate problems occurring in connection with the launching of spacecraft any data item or portion of an item. The logic and arithmetic cells and with the development of a space shuttle are described. The are attached on a one-to-one basis to each word. An associative present state of development of aeroelastic research is critically processor system is scheduled for use by the FAA to track aircraft in examined, and aerodynamic problems which are not yet solved are pointed out. G.R. potentially dangerous situations at busy airports. T.M.

A71 -20064 Electronic controls for aircraft (Elektronische A71-20015 Experimental investigations of caret wings in Steuerungen fur Flugzeuge). Walter Metzdorff (Deutsche Forschungs- hypersonic flow (Experimentelle Untersuchungen an Wellenreiter- und Versuchsanstalt fur Luft- und Raumfahrt, lnstitut fur Flug- Flugeln im Hyperschallbereich). Klausdieter Kipke. Braun- fuhrung, Braunschweig, West Germany). DFVLR-Nachrichten, OCt. schweigische Wissenschaffliche Gesellschaft, Abhandlungen, vol. 2 1, 1970, p. 105-109. In German. 1969, p. 407-428. 16 refs. In German. The history of the development of control systems for aircraft is Investigation of a series of caret wings in a hypersonic gun examined taking into consideration aspects of hydraulic servo- tunnel in the Mach number range from 8 to 15 at corresponding control, questions of the simulation of the forces required in the Reynolds numbers from 2,700,000 to 1,400,000. The design Mach control process, and problems of automatic control. Aspects of the number of the wings was between 6 and 10 and the aspect ratio reliability of mechanical control systems and of electronic control between 0.8 and 1.6. The tests included three-component force systems are investigated, and questions of the technical realization of measurements, pressure distribution measurements in spanwise a reliability model for the electric control are explored. Approaches direction, and determination of shock wave angles by flow visualiza- for changing present aircraft control systems by making use of new tion. The experimental coefficients of lift, drag, and pitching developments in the field of electronic controls are discussed, and moment were compared with the simple wedge theory and, in advantages obtained by such changes are pointed out. G.R. general, a good agreement between theon/ and experiment was obtained, The experimental pressure distributions were also compared with the simple wedge theory and additionally with an A71 -20065 Problems of the acceptance check of airliners extended Newtonian theory. In both cases, the experimental data are (Aufgaben beim Nachfliegen von Verkehrsflugzeugen). Ferdinand fairly well predicted by these theories. Experimental shock wave Schatt and Gerhard Puhlmann (Deutsche Forschungs- und Versuchs- angles show that viscous effects have a significant influence on the anstalt fur Luft- und Raumfahrt, Zentralabteilung Luftfahrttechnik, shape of the shock, especially near the leading edges of the wings. A Oberpfaffenhofen, West Germany). DFVLR-Nachrichten, Oct. 1970, simple method was used to calculate the shock wave angles in the p. 114-119. In German. plane of symmetry including viscous effects. The agreement between The characteristics of acceptance checks conducted as a pre- theory and experiment is good. Due to viscous effects, a severe decay requisite for the official licensing of an airliner in a state are of maximum lift-drag ratios occurs with decreasing Reynolds discussed. During these flight tests the operational characteristics of numbers. The order of magnitude of the maximum lift-drag ratio is an airliner are checked for compliance with data obtained by the about 4 to 6. O.H. manufacturer. Thus, in the western world it is to be ensured that the airliner meets the pertinent requirements of the Federal Aviation Regulations or the British Civil Air Regulations. Aircraft character- A71 -20044 The employment of plastics and metals in istics to be investigated in a simplified acceptance test are discussed aeronautical design comparatively considered using some practical giving attention to the various phases of preliminary work and to the examples (Einsatz von Kunststoffen und Metallen, gegenubergestellt final flight test, Performance checks related to takeoff, landing and an praktischen Beispielen, ausgehend vom Flugkorperbau). G. ascent are considered, and requirements with regard to the control of Fauner. Technische Akademie Wupperfal, Berichfe, no. 2, 1970, p. 85-104. 21 refs. In German. an aircraft, its stability, and its behavior under various conditions are examined, Particular attention is given to questions of the control of The materials used in the design of various types of aircraft, and G.R. in rocket and spacecraft design are discussed giving attention to an aircraft in critical situations. applications of plastics and of metals. The significance of plastic materials for applications requiring extremely light construction A71-20066 Demonstration system for twodimensional elements is discussed taking into consideration the advantages of aircraft motions (Demonrtrationuystem fur zweidimensionale Flug- resin-impregnated materials. The characteristics of a variety of zeugbewegungen). H. Gerd Schluter (Deutsche Forschungs- und structural materials is considered, and the use of these materials in Versuchsanstalt fur Luft- und Raumfahrt, lnstitut fur Flugfuhrung, various components of aircraft structures and missiles is examined. Braunschweig, West Germany). DFVLR-Nachrichfen, Oct. 1970, p. The use of adhesives, the employment of titanium alloys, and design 120, 121. In German. materials for spacecraft are discussed. Materials developed for special Approaches for solving problems of control processes for design problems involving helicopters are described. Newly developed aircraft are discussed giving attention to the importance of simula- plastic materials for high-temperature applications are considered, tion methods. A new approach for the investigation of methods of and changes in plastics characteristics produced by the addition of automatic landing control is described. This approach makes it metallic and nonmetallic powders is reported. G.R. possible to examine the parameters of motion of the aircraft without the use of expensive equipment as for instance a moving cockpit simulator. Only the longitudinal motion of the aircraft is considered. A71-20063 Aeroelastic and related problems for aircraft A two-dimensional sequence of pictures is electronically generated and spacecraft (Aeroelastirche und verwandte Probleme bei Flug- on a television screen in order to indicate the position of the aircraft zeugen und Raumflugkorpern). Hans Forsching (Deutsche For- during the landing maneuver. G.R.

196 A71 -20087

A71-20075 # closeddie forgings for the aircraft industry. 1. Mekhanike Zhidkosti i Gaza, Kazan, USSR, May 28-31, 1969.) J. A. Carver (British Steel Corp., Sheffield, England). Special Srels Seminar PO Kraevym Zadacham. Trudy, no. 7, 1970, p. 122-128. 6 Review, Spring 1970, p. 17-24. refs. In Russian. Description of the procedure and advantages of closeddie Consideration of an approximate method of integrating gas- forging from the viewpoint of a purchaser. Closeddie forgings are dynamics equations and of the application of this method to the classified with respect to the tolerances required into four main wlution of certain boundary value problems. An approximate types: (1 1 coarse toleranm forgings, (2)commercial tolerance die method is developed for solving the equations for a plane subsonic forgings, (3) close tolerance die forgings, and (4) precision die motion of an ideal gas in an adiabatic flow regime. The proposed forgings. It is indicated that, in general, closer tOl~ramXS reduce method is applied to a study of the discharge of a subsonic gas flow material and machining costs, but increase die and forging costs with from a flat channel with a contraction. A.B.K. a corresponding lengthening of time required for dies and tooling. Die costs increase rapidly as more precise tolerances are required. It is shown that there is an optimum tolerance for a minimum total A7120084 # Solution of certain jet problem by the wu- cost per given part. The materials used for closeddie forgings in the pling method (Reshenie nekotorykh struinykh zadach metodom aircraft industry are reviewed. Z.W. sopriazheniia). A. V. Kosterin. (Vsesoiuznaia Nauchnaia Kon- ferentsiia PO Kraevym Zadacham i ikh Prilozheniiam v Mekhanike Zhidkosti i Gam, Kazan, USSR, May 28-31, 1969.) Seminar po Kraevym Zadacham, Trudy, no. 7. 1970. p. 148-152. 6 refs. In A71-20076 All-Union Seientific Conference on Boundary Russian. Value Problems and Their Applications in Fluid and Gas Mechanics, Development of an approximate method of solving certain Kazan, USSR, 28-31, 1969, Reports (Vsesoiumaia Nauchnaia May problems of gas jet theory on the basis of a two-link approximation Konferentsiia po Kraevym Zadacham i ikh Prilozheniiam v of the Chaplygin function. The proposed method, which involves the Mekhanike Zhidkosti i Gam, Kazan. USSR, May 28-31, 1969. coupling of functions to integral equations, is applied to the solution Doklady). Seminar PO Kraevym Zadacham, Trudy, no. 7. 1970. 304 of the problem of separation flow of an ideal gas jet past a p. In Russian. symmetrical arc according to Kirchhoff's scheme. A particular case The results of studies of direct and inverse boundary value of this problem, involving jet flow past a symmetrical wedge with a problems of the theory of analytical and generalized analytical stagnation zone, is also considered. A.B.K. functions, boundary value problems for equations of mixed type. and their applications in hydroaeromechanics and filtration theory are summarized. The application ot me Riemann boundary value problem in classes of single-valued and multivalued functions on a A71-20085 # Sonic flow past a wedge according to Riemann surface to the study of certain complete singular integral Kirchhoff's scheme (0 zvukovom obtekanii klina PO skheme equations is considered. Solutions to a number of boundary value Kirkhgofa). A. V. Kosterin. (Vseswiuznaia Nauchnaia Konferentsiia problems for differential equations of mixed are obtained by type po Kraevym Zadacham i ikh Prilozheniiam v Mekhanike Zhidkosti i the integral equation method. Problems related to the existence and Gaza, Kazan, USSR, May 28-31, 1969.) Seminar PO Kraevym uniqueness of the solutions of certain boundary value problems for Zadacham, Trudy, no. 7, 1970, p. 153-159.6 refs. In Russian. equations of mixed type are examined, as well as the problem of Derivation of an approximate solution to the problem of sonic univalency of the solutions of inverse boundary value problems. flow of an ideal gas jet pact 4 wed[;e accordiq t3 Kixhhoff's scheme. Linear and invtion of a heavy nor.!Inea: 2rotj;em, conciriliiig the After showing that the problem has a unique solution, a solution is fluid with a free surface are analyzed, as well as unsteady problems obtained in the form of series, the convergence of which is of the theory of smooth and cavitation flows, direct and inverse investigated. It is shown how this method of sobition can be problems of the theory of airfoils and airfoil arrays, and problems extended to the case of a jet of infinite width. A.B.K. involving flows in channels or nozzles at subsonic and supersonic velocities. Approximate methods of solving gadynamics equations are described, as well as analytical methods of solving certain direct and inverse boundary value problems of filtration theory in A71-20086 # Motion of a cavitating foil with a jet flap homogeneous soil. A.B.K. under the free surface of a fluid (Dvizhenie kavitiruiushchego profilia s reaktivnym zakrylkom pod svobodnoi poverkhnort'iu zhidkosti). L. M. Kotliar and V. A. Lazarev. (Vsesoiuznaia Nauchnaia Konferentsiia po Kraevym Zadacham i ikh Prilozheniiam v Mekhanike Zhidkosti i A71-20078 # Inverse boundary value problems and their Gaza, Kazan, USSR, May 28-31, 1969.) Seminar PO Kraevym applications in hydroaeromechanics (Obratnye kraevye zadachi i ikh Zadacham, Trudy, no. 7, 1970, p. 168-177. In Russian. prilozheniia v gidroaeromekhanike). M. T. Nuzhin and G. G. Consideration of the problem of cavitation flow of a fluid with a Tumashev. (Vsesoiuznaia Nauchnaia Konferentsiia PO Kraevym free surface past an underwater wing with a jet flap in the case of an Zadacham i ikh Prilozheniiam v Mekhanike Zhidkosti i Gaza, Kazan, arbitrary cavitation number. Equations of motion are derived and USSR, May 28-31, 1969.) Seminar PO KraeVym Zadacham. Trudy, solved for a thin, slightly bent foil, from the trailing edge of which a no. 7. 1970. p. 18-27.28 refs. In Russian. jet emerges at a small angle into a steady flow of an ideal weightless Summary of work done on the theory of inverse boundary value fluid with a free surface. Using a linear approximation, a calculation problems by mathematicians at the University of Kazan. The is made of the hydrodynamic characteristics of the flow. The results formulation of inverse boundary value problems of the theory of of some numerical calculations of this type of flow are presented analytical functions is reviewed. Inverse boundary value problems graphically. A.B.K. involving the construction of profiles from given velocity or pressure distributions are considered. Other types of problems related to fluid mechanics are cited, including problems involving the determination A71-20087 # Flow of a heavy fluid past a plate with partial of the boundaries of a supersonic flow. A.B.K. cavitation (Obtekanie plastiny s chastichnoi kavitatsiei potokom tiazheloi zhidkosti). L. M. Kotliar and A. G. Terent'ev. (Vseswiuznaia Nauchnaia Konferentsiia PO Kraevym 7adacham i ikh Prilozheniiam A71-20083 # Certain new approximations of the Chaplygin v Mekhanike Zhidkosti i Gaza, Kazan, USSR, May 28-31,1969.l function in the subsonic range of gas flow (Nekotorye novye Seminar PO Kraevym Zadacham, Trudy, no. 7, 1970, p. 178-182. In approksirnatsii funktrii Chaplygina v dozvukovoi oblasti techeniia Russian. gad. V. A. D'iachenko and V. M. Fomin. (VsesoiuznaiaNauchnaia Consideration of the problem of a partially cavitating plate in a Konferentsiia po Kraevym Zadacham i ikh Prilozheniiam v heavy fluid according to Riabushinskii's scheme. According to this

197 A71 -20088 scheme, the cavity is closed by a fictitious plate perpendicular to the India). Indian Journal of Pure and Applied Mathematics, vol. 1, Oct. main plate. To solve the problem, the physical plane is mapped onto 1970. p. 594-607. 9 refs. i a semicircle of the parametric plane. It is shown that the presence of Unsteady boundary layer on an axisymmetric body moving in gravity in this problem increases the lifting force of the plate and the the direction of its axis is studied. A general analysis is made I length of the cavity. A.B.K. following Froessling (1940) and Sarma (1964) and two particular ! problems, one the flow past a cone and the other flow past a sphere, ~ are studied in detail. The skin friction coefficient and the dimension- A71-20088 # An unsteady problem of flow past a solid foil less displacement thickness are calculated and their variations with (Nestatsionarnaia zadacha obtekaniia telesnogo profilia). A. V. angle parameter and time are analysed. The ranges of the validity of Kuznetsov . ( Vsesoiuznaia Nauchnaia Kon ferentsiia PO Kraevym solutions for small and large times are determined graphically. The Zadacham i ikh Prilozheniiam v Mekhanike Zhidkosti i Gaza, Kazan, analysis is done in terms of the universal functions and the functions USSR, May 28-31, 1969.1 Seminar PO Kraevym Zadacham, Trudy, are integrated numerically. In the case of sphere the analysis is made no. 7, 1970, p. 198-204. 10 refs. In Russian. for two values of the main stream velocity, one for the theoretical Solution of the problem of small oscillations of a solid foil in an value as done by Schlichting (1955) and the other for the incompressible fluid flow. The problem is solved with the aid of a experimental value as done by Tomotika and lmai (1938). (Author) method previously used by the author in studying problems involving small oscillations of obstacles in flows with jet separation. The problem consists in determining the forces acting on a closed foil which is located in a steady infinite incompressible fluid flow and describes small oscillations about its main position. To solve the A71-20151 # University of Virginia superconducting wind- problem, the physical plane and the region of the complex potential tunnel balance. R. N. Zapata, H. M. Parker, F. E. Moss (Virginia, corresponding to it are mapped onto a curvilinear half-strip with University, Charlottesville, Va.), I. L. Hamlet, and R. S. Kilgore known boundaries. A formula is obtained for the force of the (NASA, Langley Research Center, Hampton, Va.). (National Bureau of Standards, US, Navy, American Physical Society, Institute Of unsteady fluid pressure on the foil. A.B.K. Electrical and Electronics Engineers, and Univenity of Colorado, Applied Superconductivity Conference, Boulder, Colo., June 15- 17. 1970.) Journal of Applied Physics, vol. 42, Jan. 1971, p. 3-5. NSF-supported research; Grant No. NGR-47-005-029. A71-20089 # Construction of a body of revolution in a The design of an electromagnetic balance using superconducting supersonic gas flow from a given chord diagram (Postroenie tela coils is reported. Both dc and ac coils are used to support vrashcheniia, obtekaemogo rverkhzvukovym potokom gaza, PO aerodynamic models in a supersonic (Mach 3) wind tunnel and to zadannoi khordovoi diagramme). L. L. Lebedev. (Vsesoiuznaia simultaneously measure the forces acting on them along 3 orthogonal Nauchnaia Konferentsiia PO Kraevym Zadacham i ikh Prilozheniiam axes. Major design characteristics include: adoption of symmetrical v Mekhanike Zhidkosti i Gaza, Kazan, USSR, May 28-31, 1969.1 coil arrangement to provide maximum space for the wind tunnel; 3 Seminar PO Kraevym Zadacham, Trudy, no. 7, 1970, p. 205-209. In gradient-coil pairs capable of being driven between 0 and 350 A at a Russian. frequency of 30 Hz by specially designed power supplies; a vertical Construction of the surface of a body of revolution from the wind tunnel with a 6-in. test section located in the axial room- distribution of the modulus of the velocity vector along the temperature access of a 250-liter liquid-helium Dewar. Results on ac generatrix of the body. this distribution being given as a function of losses for prototype gradient coils wound of three different the longitudinal coordinate of the generatrix. It is assumed that the superconducting materials are reported. (Author) body has a pointed nose and is located in a supersonic axial gas flow with a given velocity, density, and pressure. Using the method of characteristics developed by Frankl, the surface of the body and the surface of the shock wave are constructed, starting from the nose of A71-20198 # Thermal stress and fatigue analysis in turbine the body, and taking into account the formation of vortices behind rotors. C. L. Chow (Hong Kong University, Hong Kong). (American the shock wave. The generatrices of the body and the shock wave are Society of Mechanical Engineers, Joint Power Generation Confer- constructed approximately, in the form of broken lines consisting of ence, Pittsburgh, Pa.. Sept 27-30, 1970, Paper 70-Pwr-1.) ASME, rectilinear segments. A.B.K. Transactions, Series A - Journal of Engineering for Power, vol. 93, Jan. 1971.p. 13-20. 13refs. A method of thermal stress and fatigue analysis under triaxial A71-20090 # Multilink approximation of the Chaplygin stress conditions is presented. A rotor of a marine steam turbine is function in subsonic and supersonic flow regions (Mnogozvennaia taken as a typical example to illustrate the detailed method of approksimatsiia funktsii Chaplygina v dozvukovoi i sverkhzvukovoi analysis in assessing the cycle damage life of the rotor. A computer oblastiakh techeniia). V. M. Fomin. (Vsesoiuznaia Nauchnaia Kon- technique of iterative block relaxation is devised for the thermal ferenrsiia PO Kraevym Zadacham i ikh Prilozheniiam v Mekhanike stress calculation as the physical geometry of the problem under Zhidkosti i Gaza, Kazan, USSR, May 28-31, 1969.) Seminar PO consideration is fairly complex. This technique is particularly Kraevym Zadacham, Trudy, no. 7. 1970, p. 275-282. 10 refs. In advantageous for such a system as (a) damping the magnitude of the Russian. oscillation in the solution of the ill-conditioned stress equations and Construction of a method of approximating the Chaplygin (b) keeping the number of nodal points required in a converging function in subsonic and supersonic flow regions on the basis of the solution to a minimum. Three different operating procedures of well-known Krtistianovich-Suer approximate method. Coupling starting and loading the marine turbine have been studied with full conditions are derived relative to a modified stream function at the three-dimensional stress and fatigue considerations. One of the three approximation nodes. Graphs showing the good agreement between procedures which is found to be more desirable is recommended with the exact and approximate curves are presented. The proposed the descriptions of detailed steam history and main features of the method is applied to the solution of certain boundary value cold start throughout its whole operation. (Author) problems. A.B.K.

A71-20200 # Design and performance evaluation of four transonic compressor rotors. J. P. Gostelow (Cambridge University. A71-20098 #' Response of skin friction to the angle parame- Cambridge, England). ASME, Transactions, Series A - Journal of ter in flow pert an axisymmetric body moving in the direction of its Engineering for Power, vol. 93, Jan. 1971, P. 33-41. 12 refs. axis. G. N. Sarma and T. R. Gupta (Roorkee, University, Roorkee, NASA-sponsored research.

198 A71 -20304

a A set of four compressor roton was designed as means of it is pointed out that control systems for alleviating an airplane's optimizing blade camberline in the high-transonic Mach shape rigid-body and elastic mode responses to turbulence have been number region. One blade row was designed for a tip diffusion factor proved feasible by comprehensive analysis and extensive flight test. of 0.35 with the supersonic camber minimized. The other three blade Substantial improvements in riding quality, structural fatigue life, rows were designed for a tip diffusion factor of 0.45 with tip ratios and peak loads have been demonstrated. Such systems are extremely of supersonic to total camber varying from zero to the value sensitive to parameter variations, however, and must be carefully corresponding to a doublecircular-arc blade section. Performance designed to prevent degraded responses and instabilities under maps and blade element data were generated as a result of testing on offdesign conditions. G.R. the four rotors. All rotors exceeded design efficiency and flow at conditions corresponding to design point operation. Operating range, from peak efficiency to stall, is highest in rotors designed for a low tip diffusion factor and which have the minimum amount of A71-20302 # Perspective ol SST airaaft noise problem. II - Thrust losses and installation factors. G. Schairer, J. V. O'Keefe. supersonic camber. (Author) S. and P. E. Johnson (Boeing Co., Seattle, Wash.). Journal of Aircraft, vol. 8, Feb. 1971, p. 72-76. The current state of research concerning noise suppression for A71-20298 # Instruments for studying fogs and douds and SST jet engines is presented. Results of an extensive research measuring humidity (Pribory dlia issledovaniii tumanou i oblakov i program of both model and large scale levels which has investigated izmereniia vlazhnosti). V. A. Zaitsev and A. A. Ledokhovich. many different noise suppressor concepts are described. Test results Leningrad, Gidrometeorologichekoe Izdatel'stvo, 1970. p. 147 256 covered in Part I (previously published in the Journal of Aircraft) refs. In Russian. show several fundamental means to reduce jet noise at different A description is given of n& devices which are being used in frequency regions. In Part II, means to reduce thrust losses associated studies of fogs and clouds and in the solution of engineering and with installed suppressor devices are shown. Installed noise sup- technical problems related to the formation of artificial fogs. the pressor designs are based on these charts. The factors which control dispersion of natural fogs, and the measurement of humidity at noise levels for takeoff are examined. Substantial improvements in positive and negative temperatures. The principles of operation of SST noise footprints are indicated as suppression development the measurement devices are outlined, and the designs of the continues. (Author) instruments and the methods of calibrating them are described. A method of measuring fog and cloud parameters is presented, and i certain results of experimental studies of clouds and fogs are cited. The effect of water content QR the operatiort of jet aircraft engines A71-20303 # Theoretical and experimental aerodynamics of during flight in clouds and precipitation is considered. Particular the sailwing. Robert A. Ormiston (US. Navy: US. Army, Air attention is given to a description ot a new condensation thermo- Mobility Research and Development Laboratory. Moffett Field, hydrometer which measures the air temperature and humidity at Calif.).JournalofAircraft,vol. 8, Feb. 1971, p. 77-84. 17 refs. high to 70 C) and low (-50 to -60 C) temperatures under natural (50 The sailwing is a unique type of semiflexible foldable wing. A A.B.K. conditions and in various chambers. brief description of its construction, basic properties, and some past research, is used to introduce an analytical and experimental study of its aerodynamic characteristics. Emphasis is placed on an approxi- A7120299 fl Supports and suspensions of gyroscopic mate structural analysis which treats the nonlinear behavior of the devices (Opory : podsasy Siroskopichi?skikhusrroistu). L3. P. Kovalev. sail detlection. Two-dimensional flexible airfoil theory and Prandtl Moscow, Izdatel'stvo Mashinostroenie. 1970. 287 p. 48 refs. In lifting-line theory are used to establish the aerodynamic loading. The Russian. results allow prediction of the induced tensions, the nonlinear life The accuracy, reliability, and lifetime of aircraft gyro systems curve, induced drag, and aeroelastic divergence of the sail chordwise are examined as a function of bearing quality and conditions of deflection mode. Selected experimental results are presented for operation. Initial material consists of dynamic equations of motion comparison with the theory, along with a brief discussion of the for a solid body around a fixed point. Factors affecting the accuracy implications of the study regarding flight vehicle applications of the of two- and threedegree-of-freedom gyros are defined, including the sailwing. (Author) effects of external forces, elasticity of the suspension elements, and friction in the gimbal axes. The causes of dynamic reactions in the suspensions are analyzed, together with their effects on the system A71-20304 # Transonic airfoil design. M. S. Cahn and J. R. operation. Methods of calculating and eliminating vibrations and Garcia (Northrop Corp., Hawthorne, Calif.). Journal of Aircraft, vol. b friction are outlined for typical gyro structures. Particular attention 8, Feb. 1971, p. 84-88. 8 refs. is given to a method of solving statistical equilibrium equations for A method recently developed by Northrop consists of a the rotor of a gyro suspended in tension on two identical computer program which will determine an airfoil shape from radial-thrust bearings under the action of radial, axial, or combined predetermined supercritical velocity distributions having extensive loads. Formulas are given for the contact angles, support reactions, regions of supersonic flow. The velocity is given vs the distance forces acting on bearings, and rotor displacements. T.M. around the airfoil. This allows a designer to design to a given lift by specifying the required circulation. Also, boundary-layer problems can be avoided by restricting adverse velocity gradients. Starting with a given compressible pressure or velocity distribution with mixed A71-20301 # Aircraft elastic mode control. Robert L. subsonic and supersonic regions, an airfoil shape can be determined. Swaim (Purdue University, Lafayette, Ind.). Joumalof Aircraft, vol. This is done by making a transformation that cauw the streamline 8, Feb. 1971, p. 65-71. 58refs. and potential line network to give an equivalent incompressible flow. Research and development work concerned with elastic mode This incompressible problem is then solved by complex function wntrol systems which can suppress the level of normal accelerations theory, and the solution is transformed back to the compressible at selected locations on the structure of an aircraft is discussed. plane. A computer program using this method has been applied to Aspects of aircraft comfort are examined, and problems regarding several shapes with known solutions. Agreement between calculated performance criteria suitable for handling riding quality specifica- shapes and actual shapes was excellent. A 4.6% airfoil was designed tions are considered. Power spectral density analysis is discussed, from a prescribed velocity distribution and tested in the wind tunnel structural loads and fatigue are investigated, and approaches for at transonic speeds. Good agreement was obtained between theoreti- elastic mode control are explored. A review of past programs is given, cal and experimental results. Transonic airfoils can be designed by and problems of linear optimal control are examined. In conclusion this method. (Author)

199 A71-20305 , A71-20305 # Approach guidance to circular flight paths. F. A7120308 # A study of fog clearing using a C02 laser. G. J. H. Kishi and I. Pfeffer (TRW Systems Group, Redondo Beach, Mullaney. W. H. Christiansen, and D. A. Russell (Boeing Scientific Calif.). (American Institute of Aeronautics and Astronautics, Aero- Research Laboratories, Seattle, Wash.). (American Institute of space Computer Systems Conference, Los Angeles, Calif., Sept. 8-lo, Aeronautics and Astronautics, Fluid and Plasma Dynamics Con- 1969, Paper 69-986.)JournalofAircraft, vol. 8, Feb. 1971, p. 89-95. ference, San Francisco, Calif., June 16-18, 1969, Paper 69-670.) \ Members, $1.00; nonmembers, $1.50. JournalofAircraft, vol. 8, Feb. 1971, p. 108-113. 11 refs. Description of a novel technique for guiding an aircraft from a Invcstigation of the phys~csof fog removal by a C02 laser and distant point to a given circular orbit over a fixed ground area. The evaluation of thc possibility of clearlng airport runways. While I aircraft navigation system used consists of a Sensor which tracks a ~n~tialestimates of the powcr required to clear a runway, lo6 to IO7 1 ground reference point to give pointing data in aircraft coordinates, for prcscnt-day lascr dcvices, they nlay not be w, (Author) and vertical and directional gyros to give bank and heading vxcessive requirements for futurv systems. information. The system requires a computer (which solves the guidance problem in real time) and a display (which presents bank-angle commands to the pilot). Primary attention is given to the guidance equations required for a smooth, .rapid approach to the desired orbit in spite of system constraints such as sensor-gimbal A71-20309 # Use of ground based simulators in aircraft 1 limits and bank and bank-rate limits. A computer simulation is made design. P. G. Dillenschneider and A. W. Shaw (Vought Aeronautics ' of the system, and typical trajectories derived from the chosen Co., Dallas, Tex.). JournalofAircraft,vol. 8, Feb. 1971, p. 113-119. guidance philosophy are shown. Comparisons are also made between Contracts No. N 00019-68-C-0075; No. AF 33(657)-7868. i the chosen guidance scheme and theoretical optima. (Author) The growth in flight simulation technology in the flight training context and the extension of this technology to engineering oriented ~ flight simulation is discussed briefly. Basic differences between simulation used for training and engineering design are identified. The use of ground based flight simulation in support of aircraft A71-20306 ,# Optimum horizontal guidance techniques for design is demonstrated by presenting three diverse but typical examples. The specific engineering oriented simulations discussed are aircraft. Heinz Erzberger and Homer Q. Lee (NASA. Ames Research an air combat simulation used to evaluate the effect of changes in Center, Moffett Field, Calif.). Journal of Aircraft, vol. 8, Feb. 1971, gross aircraft characteristics on air combat effectiveness, the ap- p. 95-101. 5 refs. proach and landing on board an aircraft carrier at night to evaluate Discussion of automatic flight control techniques for problems aircraft handling qualities in this critical tracking task, and a V/STOL in horizontal guidance, which in current terminal area operations are assault transport simulation used to tailor aircraft dynamics, control solved jointly by the pilot and the air traffic controller. The feel system characteristics and flying qualities over the complete horizontal guidance tasks, which such a flight control system should be capable of performing, have been identified as being of three aircraft flight envelope. (Author) types: (1) guiding the aircraft from any initial location and initial heading to any final location and heading; (2) intercept and fly along a line of specified direction; and (3) a final location with arbitrary final heading. Guidance problems, such as capturing an ILS beam at a A71-20310 # Wind-tunnel tests of small decelerator stabi- specified point on the beam, intercepting a VOR radial, and point to lizers. William B. Pepper and Harold N. Post (Sandia Laboratories, point navigation, can be formulated in terms of these problems. The Albuquerque, N. Mex.). Journal of Aircraft, vol. 8, Feb. 1971, p. guidance laws given minimize the arc length of the trajectories to fly 120. 121. AEC-supported research. between initial and final conditions subject to a constraint on the Discussion of low-speed wind-tunnel tests of small guide surface, turning radius of the aircraft. A simple geometric technique is slotted solid, ring-slot, cross, and streamer decelerators. Parachute outlined for constructing the optimum trajectories graphically. G.R. diameters from 1 to 2 ft were used. Decelerator drag force was measured by means of the wind-tunnel balance system. and stability was recorded by cameras. It was found that the guide surface canopy design was the most favorable, having a high-drag efficiency and excellent stability for all sizes tested. It was also seen that the new alternating pocket streamer design is a cheap, reliable method of A71-20307 ,# Boundary-layer discontinuity on a helicopter providing a small drag increment for initial body stabilization. G.R. rotor blade in hovering. Henry R. Velkoff (Ohio State University, Columbus, Ohio), Kenneth M. Jones (Boeing Co., Supersonic Transport Div., Seattle, Wash.), and Dwight A. Blaser. /American Institute of Aeronautics and Astronautics and American Helicopter A71-20311 # Measurements of particulated gas flow Society, VTOL Research, Design, and Operations Meeting, Georgia Pressure on cascade nozzles. W. Tabakoff and M. F. Hussein Institute of Technology,Atlanta, Ga., Feb. 17-19, 1969, AlAA Paper (Cincinnati. University, Cincinnati, Ohio). /American Institute of 69-197.)Journalof Aircraft, vol. 8, Feb. 1971, p. 101-107. 18 refs. Aeronautics and Astronautics, Propulsion Joint Specja/jst con. Army-supported research. ference, 6th, San Diego, Calif., June 15-19, 1970, Paper 70.712,) An experimental study was conducted using flow-visualization Journal of Aircraft, vol. 8, Feb. 1971, p. 121.123. Grant N~, techniques to investigate the nature of the boundary layer on a DA-HC-04-69-C-0016. helicopter rotor in hovcring. The study revealed that an unanticipated An approximate method for calculating the flow properties Of boundary layer behavior occurred. The primary flow-visualization gas-particle mixture flowing over blades in a cascade is developed. technique involved the use of ammonia injected into the boundary The momentum and heat transfer between the gas and particles as layer at thr leading edge. The blade surface was chemically coated, well as compressibility effects are taken into consideration. The and as the ammonia moved with the local airflow it formed a trace effect of particle concentration, mean diameter, particle material on the surface indicative of the boundary-layer flow. The traces density, particle inlet velocity and temperature on the gas particle initially moved chordwise along the surface then abruptly turned flowproperties are investigated. The flow pressure distribution on outwards. A short distance later, the traces movrd inwards and the blade surface and the particle velocities and trajectories in the then continued aft along the blade in a somewhat diffuse pattern. nozzle are determined experimentally. The experiments are per- Similar traccs werr found over wide ranges of pitch anglrs and rotor formed in a wind tunnel and in a water table. The solid particle sizes speeds. It is hypothesized that a standing laminar separation bubble range from 5 to 1000 microns and the particle concentration range exists on the blade surface aft of the peak pressure position. @"thor) from 0.03 to 0.2. (Author)

200 A71 -20355

A71-20312 # A mnecdon for compressible subsonic planar and some of the advanced means used in its performance are flow. Helge N~rstrud(LockheedGeorgia Co., Marietta, Ga.). Journal discussed for the environments of long-range flight, terminal areas, ofAircraft, vol. 8, Feb. 1971,~.123-125. 13refs. and specialized military missions. An evolutionary development has Discussion of an improvement over the PrandtlGlauert rule for occurred during the past generation with respect to commercial and high subsonic speeds. It is pointed out that the onedimensionality of military requirements, technology. and the crew's navigation func- the Prandtl-Glauert corrosion formula precludes a correct prediction tions. This development can be expected to continue into the future. of the pressure distribution at these speeds. A compressibility (Author) correction formula is given which is essentially a relationship between local variables. but which can be understood as being able to include some global effects. The compressibility correction presented ~71-20344 Man-machine considerations in system design yields reduced corrections to the PrandtlGlauert value at locations for all-weather, low-level navigation. G. V. S. Raju and D. L. of large curvature - e.g., at the nose region. G.R. Horowitz (Ohio University, Athens, Ohio). /Institute of Navigation, Annual Meeting, 25th, Colorado Springs, Colo., July 1, 2, 1970.) Navigation, vol. 17, Winter 1970-1971, p. 412418. 5 refs. DOD- supported research. A71-20313 # Rapid calculation of inviscid and viscous flow This paper is concerned with man-machine considerations in over arbitrary shaped bodii. H. A. Dwyer, D. Doss. and A. E. system design for low-level navigation. In particular, computer Goldman (California. University, Davis, Calif.). Journal of Aircraft, generation of command information and visual display presentation vol. 8, Feb. 1971, p. 125-127.9refs. are described. Simulated results are presented which indicate that the It is shown how the high Reynolds number viscous and inviscid pilot's ability to fly on a given route is improved with the roll flow over arbitrary shaped twodimensional bodies, particularly command display. (Author) airfoils, can be calculated very rapidly and exactly with a modern digital computer. A numerical solution of the potential flow equations by a general method developed by Theodorsen and Garrick (1933) and a finite difference solution of the boundary-layer A71 -20346 The role of man in Aerospace Defense equations near the body surface up to the point of flow separation Command navigation. Richard M. Shute (USAF, Aerospace Defense are considered. These two methods are combined into one computer Command, Ent AFB, Colo.). (Institute of Navigation, Annual program which can calculate the potential and boundary-layer flow Meeting, 25th, Colorado Springs, Colo., July I, 2, 1970.) Navigation, over the body in a matter of seconds on the digital computer. G.R. vol. 17, Winter 19701971, p. 422-425. Navigation and man play indispensable roles in the atccessful mission accomplishment of the Aerospace Defense Command. As A71-20314 # Ratio of turbulent flight miles to total flight new defensive systems are acquired to counter the threat, man's miles in the altitude range 45,000-65.000 ft. Edward V. Ashburn and identity will be greatly changed. Regardless of this change, man will David E. Wac0 (Lockheed-California Co.. Burbank, Calif.). Journalof not be replaced by the machine and will continue to make viable Aircraft. vol. 8. Feb. 1971, p. 127. 128. Contract No. AF contributions in the modernized aerospace defense force. (Author) 33615)-69-C-1552. Evaluation of data obtained during the High Altitude Clear Air Turbulence (HICAT) program reported by Crooks et al. (1967) taking into consideration adjustments made to correct for the effects A71 -20347 lnertial systems and area navigation in the U.S. of repeated flights +h~il&the turbi;leiii ii;y;on>. The ratlos of domestic airspace. Joseph M. Del Ealzo (FAA, Systems Research and turbulent flight miles to total flight miles for the HICAT sample are Development Service, Washington, D.C.). /Institute of Navqation, listed. and a subjective estimate of representative values of percent- Annual Meeting, Colorado Springs, Colo., July I, 2, 1970.) age of flight miles expected to be turbulent is presented. Based on 25th, Navigation, vol. 17, Winter 1970-1971, p. 426431. 6 refs. data from more than 200 flights the percentage of flight miles that lnertial navigation systems are being adopted by air carriers for were turbulent is found to increase with underlying terrain rough- application on long-range oceanic routes and their existence in ness, decrease with altitude, and display a maximum in the winter cockpits in increasing numbers warrants attention to their possible and spring. G.R. application during enroute and terminal. domestic operations. This paper discusses performance requirements for airborne area navigation systems as proposed in FAA Advisory Circular 90-45 and A71-20340 A strapdown magnetic azimuth detector. W. projects these performance requirements through 1995. The applica- A. Shapiro (Bendix Corp., Navigation and Control Div., Teterboro, tion of an INS with position updating from conventional ground N.J.) and C. E. Roemer. Navigarion, vol. 17, Winter 1970-1971, p. referenced navigation aids to meet these present and forecasted 370-374. performance requirements are assessed and the effects on pilot A system is described in which a strapdown 3sensor rnagnetom- workload are discussed. Also included in this paper is a brief eter is used in conjunction with an inertial reference (such as a description of a planned flight evaluation to assess the effects of an vertical gyro). to provide an indication of magnetic heading integrated Inertial/DME-DME/Map Display area navigation system on independent of aircraft attitude. The system eliminates the need for aircraft navigation performance and pilot workload. (Author) stable or pendulous mountings such as were used with previous azimuth detectors. (Author)

A71-20355 The latest airport lighting facilities. Osamu A71-20343 Man's future role as an aircraft navigator. Carl Sato, Kaiji Ishiguro, and Masami Kishimoto (Tokyo Shibaura Electric S. Hoffman and John J. Czaja (North American Rockweli Corp., Co.. Ltd.. Tokyo, Japan). Tohiba Review, Jan. 1971, p. 36-41. Autonetics Div., Anaheim, Calif.). /Institute of Navigation, Annual Discussion of the present status of airport lighting facilities, with Meeting, 25th, Colorado Springs, Colo., July 1.2, 1970.) Navigation, particular emphasis on the situation in Japan, and on the various vol. 17, Winter 1970-1971. p.404-411. lighting fixtures lately developed or expected to be developed to be This paper explores the role of man as a navigator in commercial employed for airport lighting. Several types of marker lights and and military aircraft. Performance of the crew's functions is obstruction lights, and an apron floodlight are described. Examples considered in terms of the increasing stringency of requirements and of some recent major deliveries of airport lighting facilities to the growing availability of navigation aids. These aids include sensors, Japanese airports are reviewed. Notable future trends in the information processing methods, and displays. The navigation task development of airport lighting facilities are outlined. O.H.

20 1 A71 -20364

A71-20364 On the transverse and torsional vibrations of a A71-20405 An adaptive landing system. W. D. T. Ruxton- fuselage-wing combination with wing-tip fuel tanks. C. Y. Lee and L. Davies and F. D. Powell (Bell Aerospace Co., Buffalo, N.Y.). In: I C. Jean, Astronautical Society of the Republic of China, Trans- National Electronics Conference, Chicago, Ill.,December 7-9, 1970, actions, Nov. 1, 1970, p. 1-23. 7 refs. Proceedings. Conference sponsored by the I Calculation of the mass matrix and the stiffness matrix for the Illinois Institute of Technology, the Institute of Electrical and equivalent elastic beam which represents the half-span wing with Electronics Engineers, the Northwestern University, and the Uni- 1 half-fuselage mass attached at one end and the tip tank mass at the versity of Illinois. Oak Brook, Ill., National Electronics Conference, I other. The natural frequencies and the corresponding mode shapes Inc. (NEC, Proceedings. Volume 26). 1970, p. 130-134. for the combined transverse and torsional vibrations are then found. An investigation was conducted to determine whether the I The fuel in the wing-tip tank IS replaced by an equivalent pendulum performance of the mathematical model of the entire Automatic with its pivot moving at the dominant frequency. Stability of the Carrier Landing System including nonlinear elements in the aircraft pendulum swing is then analyzed using the Floquet theory for can be significantly improved by use of a linear adaptive Navigation Mathieu equations. F.R.L. Computer. The effectiveness of the adaptive computer in reducing system errors due to system nonlinearities and noise effects is demonstrated. The results obtained show that the adaptive loop is < capable of improving overall system performance. The 'higher A71-20369 Analysis of nonlinear control systems with derivative' gain signal has proved extremely beneficial in reducing transport lag. Y. K. Chen, K. W. Han, and G. J. Thaler (Chung Shan errors arising from system nonlinearities, even though the basic Institute of Science and Technology; Chiao Tung University. theory assumed a linear system. G.R. Nationalist China), Astronautical Society of the Republic of China, Transactions, Nov. 1, 1970, p. 81-93. 5 refs. Formulation of the parameter plane equations for a nonlinear A71-20546 Filament winding an aircraft wing structure system with transport lag, followed by demonstration that the David G. Whinery (North American Rockwell Corp., El Segundo, imaginary axis of the s-plane can be mapped onto the parameter Calif.), C. E. Ady (Aerojet-General Corp., El Monte, Calif.). and C. plane through these equations. The method is applied to a system Tanis (USAF, Materials Laboratory, Wright-Patterson AFB, Ohio). with transport lag and one nonlinearity and also to a system with Society of Manufacturing Engineers, Technical Paper no. EM 70-406, transport lag and hysteretic nonlinearity. In both cases the existence 1970. 17 p. Members, $1.50; nonmembers, $2.00. and characteristics of limit cycles are studied. The method is applied to an aircraft pitch control system, with both transport lag and Manufacturing methods utilizing unidirectional glass reinforce- hysteretic nonlinearity. F.R.L. ments were applied to design and fabrication of a demonstration wing section representing the T-2B airplane wing station 115 to tip station 207.5. Basic tools for filament winding evolved from missile case winding practice. A rotating winder was developed for diagonal A71-20373 # Problem areas for lift fan propulsion for civil winding the truss spar tension diagonal members. The skin winding VTOL transports. S. Lieblein (NASA, Lewis Research Center, mandrel utilizing retractable steel box-sections and a water soluble Cleveland, Ohio). Deutsche Gesellschaft fur Luft- und Raumfahrt, sand contoured surface is discussed. Other tools consist of access Symposium on VTOL Propulsion, Munich, West Germany, Oct. 22, door molds, honeycomb router guides, and trim fixtures. Achieve- 23, 1970, Paper. 35 p. 45 refs. ment of 106 per cent of design ultimate loads during test of the Problem areas and requirements involved in the lift fan demonstration wing substantiated these manufacturing processes. propulsion system are examined, together with research considera- (Author) tions and approaches aimed at providing design and performance data necessary for a realistic evaluation of the potential applicability of the system for use in VTOL transport aircraft. Propulsion functions and concepts for lift, cruise, transition, attitude control, A71-20556 Vortex devices in aircraft fluid systems. A. F. and their interactions are reviewed, and various methods for driving Taylor (Cranfield Institute of Technology, Cranfield, Beds., the lift fan are discussed. The principal features of these methods are England). In: British Hydromechanics Research Association, examined. Major considerations concerning such installed fan charac- Cranfield Fluidics Conference, 4th. University of Warwick. Coventry, teristics as thrust, noise, weight and component and system design England, March 17-20. 1970, Proceedings. Volume 1. are presented. Factors in fan transition performance are noted. It is Edited by T. E. Brock and H. S. Stephens. Cranfield, shown that the principle problems are encountered in the following British Hydromechanics Research Association, 1970, p. 82-21 to areas: optimum integration of the lift, cruise, control, and transition 82-32, 6 refs. functions; specific design of the fan stage and selection of its drive Consideration of vortex diodes and valves, which have the major system; and fan performance and noise in cross flow. V.P. advantage of low pressure drop in the preferred direction of flow, coupled with the ability to significantly reduce the flow or increase the pressure drop. Some possible applications in aircraft fuel and air conditioning systems are mentioned, and in particular the characteristics of various vortex valves are examined, using all possible A71-20401 National Electronics Conference, Chicago, Ill., combinations of flow patterns into and out of the vortex chamber. December 7-9, 1970, Proceedings. Conference sponsored by the Experimental results show how, for a large range of both positive and Illinois Institute of Technology, the Institute of Electrical and negative control flows, the pressure drop of a vortex valve can be Electronics Engineers, the Northwestern University, and the Univer- expressed in terms of a simple equation. F.R.L. sity of Illinois. Oak Brook, Ill.,National Electronics Conference, Inc. (NEC, Proceedings. Volume 26). 1970. 1050 p. $10.00. The topics include engineering in medicine and biology, digital systems and computers, adaptive systems, ,solid state devices and A71 -20580 The design and construction of a pressure integrated circuits, and circuit theory. Investigations in electro- regulator including fluidic elements. C. Pavlin, E. Mace (Societe acoustics, electromagnetics, optimal control, aerospace electronics, Bertin et Cie., Paris, France), and G. Soviche (Societe ERAP, information theory, and consumer electronics are also Covered. France). In: British Hydromechanics Research Association, Cranfield Studies and developments in the fields of communications, general Fluidics Conference, 4th. University of Warwick, Coventry, England, microwave theory and techniques, communications technology, wire March 17-20, 1970, Proceedings. Volume 2. communication, and educational television are reported. An author Edited by T. E. Brock and H. S. Stephens. Cranfield, British index and a technical papers index are included. G.R. Hvdromechanics Research Association, 1970, p. J1-l to J1-12.

202 A71 -20686

Description of a pressure regulator which requires a high A71-20674 8 Fundamentals of aircraft engine desigr fluidic proportional chain. Curved wall amplifiers were pressure used. (Osnovy konstruktsii aviatsionnykh dvigatelei). E. L. Fel’dman, G. I. The pressure to be controlled is measured by a Bourdon tube Danileiko, and L. N. Kapustin. Moscow, Izdatel‘stvo Transport, controlling the first amplifier by means of a spoiler displacement. 1970. 272 p. 6 refs. In Russian. The regulator operates in a direct or inverse proportional way. General problems of gas-turbine engine design are discussed. Alternatively, a snap action may be obtained by switching a Structural schemes for the design of such engines are analyzed, and monostable into the chain. The gain, the set point, the proportional, the functioning, construction, and conditions of operation of units, or the snap action can be separately adjusted. Laboratory and field assemblies, and systems are described, as well as the loads to which natural gas test results are given. F.R.L. these components are subjected and the materials of which they are composed. The requirements which structural components and systems must satisfy are outlined, and some very simple strength calculations are performed. A detailed analysis is made of the A71-= Fluidic sensors for mawring engine pressure functioning and design of inlet devices, compressors, combustion ratio adturbine inkt temperature. M. P. Bland (McDonnell Aircraft chambers, turbines, outlet and reversing devices, rotors and their Co.. St. Louis, Mo.). In: British Hydromechanics Research Associ- bearings, reducers, lubrication systems, fuel systems, automatic ation, Cranfield Fluidics Conference, 4th. University of Warwick, control systems. and starting systems. The design of piston-driven Coventry, England, March 17-20, 1970, Proceedings. Volume 2. engines is considered. A.B.K. Edited by T. E. Brock and H. S. Stephens. Cranfield, British Hydromechanics Research Association, 1970, p. L4-49 to L4-64. 10 refs. A comparative study was conducted to determine the feasibility A71-20683 VFR at bad weather - What is to be taken into of using fluidic sensors for the measurement of engine pressure ratio consideration. II - Radio navigation and radio-telephone communica- and turbine inlet temperature on a new, high performance, fighter (VFR bei Schkchtwetter Was gibt zu beachten. II aircraft design. The performance of many recognized fluidic sensor tion - a - Funknavigation und Funkspmchverkehr). Max Korte. Deurscher concepts are compared, based on previous and current laboratory Aerokurier, vol. 15, Jan. 1971, p. 10, 11. In German. tests performed on many types of fluidic components. The most The need for a stricter separation of IFR and VFR traffic in promising fluidic concepts are compared with mnventional force mnnection with the introduction of commercial aircraft of greater balance type, engine pressure ratio sensors and thermocouples for velocity is considered. Aspects of orientation during a hypothetical measurement of turbine inlet temperature. The results of this study flight between two locations in times of bad weather are discussed. It indicate that there are fluidic techniques for sensing engine pressure is assumed that the aircraft is equipped with a radio compass and ratio and turbine inlet temperature which may offer some advantages VOR. Some concfete examples are given how this equipment can be over conventional methods. However, considerable development is used as a navigational aid during the hypothetical flight taking into still necessary before these sensors become production flightworthy consideration the VOR stations located in the area covered by the hardware. (Author) flight. The utilization of VOLMETS during bad weather is recommended, and the advantages of taking into account warnings A71-20581 Development of a fluidic pressure ratio control transmitted by some stations regarding the occurrence of thunder- storms, hail, high wind velocity, and fronts are discussed. G.R. unit for a vertical take-off aircraft lift engine. D. C. Cheffy (Plessey Co., Ltd., llford Essex, England). In: British Hydromechanics Research Association, Cranfield Fluidics Conference, 4th. University of M’aiwick. (hentry, Engldnti, iviarch 17-2G. 1970, Proceedings. A71-20684 Aeronautical electronics for pilots of gliders Volume 2. Edited by T. E. Brock and H. S. and touring aircraft. I (Luftfahrt-Elektronik fiir !&gel- und Reise- Stephens. Cranfield, British Hydromechanics Research Association, flieger. I).Hans Helmut Mogling. Deurscher Aerokurier, vol. 15. Jan. 1970, p. L5-65 to L575. 1971, p. 12, 14-16. In German. Description of the pneumatic pressure ratio control unit, which The importance of aviation electronic equipment for questions limits the fuel flow of the Rolls Royce RB162-81 lift engine to of safety in aeronautical operations is examined. Equipment for prevent engine operation above a specified pressure ratio. The unit radio-telephone communication for gliders is considered. Vhf radio was designed to replace an existing mechanical device within the fuel equipment requirements for aircraft are examined and vhf equipment system. The background and history of the project are outlined. The manufactured by a number of German, and French companies stages of testing and developing the breadboard circuit, the initial US.. is described. Other equipment discussed includes NAViCOM installa- test bed unit, and the final flight standard are reported in some tions and VOR-navigationreceivers. G.R. detail. F.R.L.

A71-20685 The art of centering (hr die Kumt der A7120624 # Petform?mwr of cascade of bhdcr with small Zentrierens). Max Haubenhofer. Deutscher Aerokurier, vol. 15, Jan. aspect ratio. I - krformanwr at the cenkr of blade span. Shintaro 1971, p. 26-28. In German. Otsuka and Showgo Hayashi (Nagoya University, Nagoya, Japan). It is pointed out that the angle of attack and the force exerted (Japan Society for Aeronautical and Space Sciences, Journal, vel. 18. by the air on the aircraft become larger when an aircraft enters an May 1970. p. 178184.) Nawya Uniwmity, Facult?’ of Enginewing. ascending current. The opposite effects are observed when the Experimental study, at the center of blade span, of the aircraft enters a descending current. Motions in an ascending current performance of low aspect ratio (AR) compressor blades in cascade. are analyzed taking into consideration effects on an aircraft which All blades had the same span (50 mm), and their AR’s were 2.08. enters it. Variometer designs are described, and the correct use of a 1.39, 1.04, and 0.83. Stagger angle (alpha) was varied from to 60 0 variometer as an aid for the pilot of a glider is discussed. A number deg. and the angle of attack (alpha sub i) from 0 to 15 deg. Results of flight situations are examined giving attention to impressions as show that the total pressure loss coefficient has a minimum value at perceived by the pilot, his reactions, and possible operational an AR about equal to 1, irrespective of alpha and alpha sub i. At mistakes. G.R. alpha sub i over about 5 deg the turning angle increases, and at alpha sub i = 0 it decreases gradually with increasing AR. In the cafe where alpha = 30 deg, it keeps an almost constant value, irrespective of AR, A71 -20686 Giirter Cichon... conducts a test with at alpha sub i = a constant. In cases of alpha = 50 and 60 deg. it Diamant 18 (Giirter Cichon.. . testet den Diamant 18). Giinter increases when alpha sub i equals or exceeds 5 to 10 deg with - Cichon. Deutscher Aerokurier, vol. 15, Jan. 1971, p. 29-31. In increasing AR. F.R.L. German.

203 A71-20 147

Test conditions are examined, and takeoff operations are A71-20778 /' Nonstationarv aperiodic motion of a lifting described. The behavior of the glider during the flight at a low surface in an incompressible fluid (Zadacha o nestatsionarnorn velocity, during stalling and spinning is reported. The effect of aperiodicheskom dvizhenii nesushchei poverkhnosti v neszhimaemoi velocities up to 240 km/hr is investigated. The effectiveness of the zhidkosti). A. N. Panchenkov. Samoletostroenie i Tekhnika Vozdush- control surfaces is considered. and questions of stability are nogo Flota, no. 21, 1970, p. 18-26. 10refs. In Russian. explored. Details of glider design are presented taking into considera- An asymptotic method for solving problems of the non- tion the cockpit and its equipment. The materials used in the stationary aperiodic motion of a lifting surface is developed. The construction of the glider are described. G.R. method is based on the idea of Panchenkov's (1965) method of function parameters and its version - the 'small-time space method' (Panchenkov, 1969) for solving problems associated with nonstationary processes. The ideal of the method of functional parame- A71-20747 i' Damage to structures due to floor shocks. ters is based on mapping a parametric space into a new space Nelson M. lsada (New York, State University, Buffalo, N.Y.). enclosed within a certain interval. The asymptotic method proposed American Society of Civil Engineers, Structural Division, Journal, makes use of an algorithm for the direct solution of the uniformly. vol. 97, Feb. 1971, p. 561-572. PHS Grant No. EC-00287. correct Cauchy problem for a linear differential equation in Study of the factors affecting impending damage and structural small-time space. V.P. failure in bent-type structures due to pulse-type floor acceleration shocks, such as damage to aircraft seats during crash landing. The governing equations are formulated, time-history solutions are determined and critical structural isodamage curves developed. Some A71-20779 # Method of determining the optimum of the conclusions reached relate the dynamic responses of structures minimum-noise take-off profile of an aircraft (Metod opredeleniia to such factors as the quasi-static ultimate strength characteristic of optimal'nogo profilia vzleta samoleta s minimal'nym shumom na the structure, the natural frequency of the structure, and duration of mestnosti). K. G. Valeev, 6. N. Mel'nikov, V. I, Tokarev. and I. p. the floor acceleration. Recommendations are made for further Shmakov. Samoletostroenie i Tekhnika Vozdushnogo Flota, no. 21, research. M.V.E. 1970, p. 27-31. In Russian. The various aspects of selecting the optimum minimum noise take-off profile are considered on the basis of a rigorous formulation of the problem. The amount of acoustic energy imparted to a point A71-20750 // Practical aerodynamics of the lak-40 aircraft on the earth's surface during a certain time is taken as the noise (Prakticheskaia aerodinamika samoleta lak-40). L. E. Bogoslavskii. criterion. The problem is reduced to obtaining a solution of the Moscow, Izdatel'stvo Transport, 1970. 176 p. In Russian. system of equations of motion of a jet aircraft, which would The design and aerodynamic features of the lak-40 passenger minimize the noise criterion. It is shown that such a solution can be aircraft are discussed, as well as its flight-engineering characteristics. obtained with the aid of methods in the theory of optimal processes. Problems concerning piloting techniques are considered. and specific V.P. recommendations are made on how to carry out flights under various conditions. Information is prusetikd concerning the centering of the Mathematical model of nonstationary gas aircraft. its equilibrium, stabllity, and controllability. flights in A71 -20780 :: special cases; and piloting the aircraft during engine failure and in motion in internal combustion engines (Matematicheskaia model' turbulent air. Certain theorems of flight theory are reviewed which nestatsionarnogo gazoobmena v dvigateliakh vnutrennego sgoraniia). mdke it easiei to study problems of piactical aerodynamics and flight D. A Munshtukov. Sarnoletostroenie i Tekhnika Vozdushnogo Flota, operation. A.B.K. no. 21, 1970, p 32-40 5 refs In Russian. A model describing the motion of the intake and exhaust gas in the cylindeis of a two cycle internal combustton engine. The

A71-20776 11 Lifting properties of some configurations ac characteristic paiameteis of the processes occurring in a cylinder ale cording to the slender body theory (Nesushchie svoistva nekotorykh determined. Systems of equations describing the correlated motions konfiguratsii PO teorii tonkogo tela). A G Sakhno and V. I. of the medium in the cylinders and in the intdke and exhaust V.P. Kholiavko. Samoletostroenle i Tekhnrka VoZdilS/JnOgOFlota, no. 21, manifolds are det ived 1970, p. 3-10 5 refs. In Russian. The aerodynamic characteristtcs of conical and pyramidal configurations of various planforms are analyzed within the frame- A71-20781 !! Methodology of the experimental investigation work of slender body theory in which the three-dimensional flow at of the influence of water supplied to the inlet of a centrifugal compressor on the compressor parameters (K metodike eksperi- incidence past a slendet body is replaced by the two dimensional flow in a plane perpendicular eithei to the velocity vector of the mental'nogo issledovaniia vliianiia vody, podavaemoi na vkhode v oncoming flow or to the longitudinal axis of the body. The influence tsentrobezhnyi kompressor, na ego parametry). A. S. Moskalenko of the cross sectional shape and of such geometrical parameters as and N. L. Zel'des. Sariioletostroen/e i Tekhnika Vozdushnogo Flora, relative thickness and cambci on the lifting characteristics of these no. 21. 1970, p. 41-48. 6 refs. In Russian. bodies is assessed. The formulas dertved are applicable also to Existing methods of cooling the piecompressed tnlet air of a diesel engine are analyzed. The advantages of evaporation cooling, noii-slendei bodies V.P. involving the injection of water into the suction duct are pointed out. The influence of water injection on the operation of the A71-20777 1' Approximate theoretical model of a wing with compresston system of a turbochaiged diesel engine is studied suction and blowing (Priblizhennaia teoreticheskaia model' struinogo theoretically and experimentally. The facility. procedure, and data i ezhektornogo kryla). V. M Suprun. Saruoletostroen/e i Tekhnika processing techniques employed in the expel iintwts ale desct ibed. Vozclushnogo Flota, no. 21. 1970, p. 11-17. In Russian. v P. The potrntial flow past a cylindei with singiilarities in the form of soiirces ant1 sitiks is aiialywd. The results of the analysis are used to construct dn appioximiitc theowtical model for a wing with A71 20782 11 Influence of air temperature on the intake suctioti of the uppw surfacc! and blowing at the lower surface near process of internal combustion engines (Vliidnie temperatury the trailing edge Formulas are detived for calculating the aero- vozdukha na protsess vpuska dvigatelei vnutrennego sgoraniia) B dynamtc chaiactertstics of wiiigs of infinite span with boundary layer Kh Draganov Samoletostroenie I Tekhmka Vozdirshnogo Flota, no control and formulas for determlrltng steady horizontal flight 21, 1970. p 49 55 In Russian parameters as a function of the thrust-weight iatio and wing loading. An expeiimental investigation of the degiee to which the ail V.P. temperature influences the gencidlired charactei istics of the intake

204 A71-20836 process of internal combustion engines IS described The SMD 14N A71 -20802 Towards a unified system of noise assessment. and the YaMZ 236 engines were tested The experimental data were D. W. Robinson (Ministry of Technology, National Physical Labora- processed in dimensionless coordinates with the aid of methods in tory, Teddington. Middx., England). f8ritish Acousrical Society, similarity theory The results are used to derive generalized relations Meeting on Communify Noise Criteria, Loughborough University of for calculating the principal parameters of the intake process V P Technology, Loughborough, Leics., England, July 23, 1970.) Journal of Sound and Vibrafion, vol. 14, Feb. 8, 1971, p. 279-298. 15 refs. Different indices are in current use for expressing the nuisance value of successions of noises, according to the type of noise. It is shown that a. single index, termed noise pollution level, accom- modates the experimental results of surveys of aircraft and of motor A71-20787 fr Analysis of aircraft radio-compass error vehicle noise. The same formula satisfactorily explains the results of (Analiz oshibki samoletnogo radiokompasa). E. 0. Brudnyi. L. la. laboratory tests in which noise intensity is traded against duration to Il'nitskii, and V. I. Baklaikin. Samolerosrroenie i Tekhnika maintain equal impressions of objectionableness. The index is based Vozdushnogo Flora, no. 21,1970, p. 71-77. In Russian. on two terms, one representing the equivalent continuous noise level Problems associated with increasing the precision of aircraft on the energy basis, and the other representing the augmentation of radio compass operation at moderate wavelengths are examined. annoyance when fluctuations of noise level occur. Practical and Radio compass errors owing to inclinations of the loop antenna axis theoretical implications of the index are discussed. (Author) during such maneuvers as banking, diving, or pitch-up are studied theoretically and experimentally. The influence of radio compass error on the accuracy of air navigation is analyzed. V.P. A71-20828 2 Eddy flow of an ideal incompressible fluid past a flat partition (Obtekanie ploskogo zabora vikhrevym potokom ideal'noi neszhimaemoi zhidkostil. V. I. Kholiavko. Samolerosrroenie A71-20792 p Evaluation of the precision of executing the i Tekhnika Vozdushnogo Floa. no. 22, 1970, p. 9-13. In Russian. outside contours of units with allowance for the elastic character- Investigation of a continuous flow past a plate located perpen- istics of the elements assembled and equipment (K otsenke tochnosti dicular to a wall along which an inviscid incompressible fluid with a vypolneniia naruzhnykh obvodov agregatov s uchetom uprugikh linear variation of velocity with height is moving. The problem kharakteristik sobiraemykh detalei i osnastki). lu. A. Boborykin. A. consists in solving the Poisson equation for the stream function for N. Bereziuk, V. V. Knigin, and N. M. Parkhomenko. Samo- the case where this function is equal to zero on the wall and on the letosfroenie i Tekhnik3 VozduL.S/;mg~Fbta, no. 21, 1970. p. plate. A soiution is obtained in finite form. The critical points in the 109-112. In Russian. flow are determined, and the behavior of the streamlines at these The selection of the method of assembling aircraft systems is points is investigated. The results of a calculation of the pressure discussed with allowance for the rigidity of the components and its distribution on the wall for various values of the vorticity parameter influence on the redistribution of errors in the application of are presented. A.B.K. external and internal force fields during the assembly process. It is shown that by taking into account the rigidity of the elements assembled in the relations describing the assembly process, it is A71-20831 Y Study of a 2500-HP turboprop engine as a possible to evaluate the limits of applicability of the variousassembly plant for controlling the gas temperature in front of the turbine methods. V.P. (Issledovanie turbovintovogo dvigatelia moshchnost'iu 2500 I. s. kak ob'ekta regulirovaniia temperatury gazov pered turbinoi). A. K. Ipatov. Samoletostroenie i Tekhnika Vozdushnogo f lota, no. 22. A71-20793 fi Service life of bearing elements of aircraft gear 1970, p. 24-32. In Russian. pumps (0 sroke sluzhby podshipnikovykh uzlov aviatsionnykh Derivation of an equation describing the operation of a shesterenchatykh nasosov). N. P. Artemenko. I. L. Vinokurov, Iu. I. turboprop engine with a high-pressure compressor as a plant for Voloshin, and L. M. Fel'dman. Samolefostroenie i Tekhnika controlling the gas temperature in front of the turbine. Formulas for Vozdushnogo Flora, no. 21, 1970, p. 113-116. In Russian. calculating the dynamic coefficients of the equation are obtained. Design and technological means of increasing the service life of Methods of determining each coefficient are briefly outlined, and the gear-pump bearing elements. Approximate quantitative estimates on results of the calculations are presented in the form of graphs of the the influence of errors in the principal circular pitchhpacing ratio on dependences of the dynamic coefficients on the operatmg mode of the service life of aircraft gear pumps are obtained. It is shown that the engine at various flight altitudes and speeds. A.B.K. the service life of the bearing elements and the pump itself can be increased by limiting the circular pitchkpacing error to 8 to 10 microns, by diminishing the spacing to 18 to 35 microns, and by A71-20832 #' An experimental arrangement for studying the strictly holding to the geometrical, dimensional, and hardness delay time in the components of the propellerhpm controller system specifications. V.P. of a turboprop engine (Eksperimental'naia ustanovlia dlia issledovaniia vremeni zapazdyvaniia v elementakh sistemy vint-reguliator chisla oborotov turbovintovogo dvigatelia). P. P. Minin and A. K. 1371-20797 // Investigation of the influence of operating Ipatov. Samoletostroenie i Tekhnika Vozdushnogo Flora, no. 22, conditions on the mean flight time between overhauls (Issledovanie 1970, p. 33-38. In Russian. vliianiia uslovii ekspluatatsii samoletov na velichinu ikh wednego Description of an experimental arrangement which makes it mezhremontnogo naleta). L. E. Talianker. Samolefostroenie i possible to study the absolute values of the delay times in the Tekhnika Vozdushnogo Flora, no. 21, 1970, p. 148-156. In Russian. propellerlrpm controller system as a whole and to ascertain the Overhaul schedules of civil aviation aircraft are established along effect of various factors on the delay time. In the arrangement prescribed standards but also with consideration to the operational described an rpm controller head of original design is employed, as state of the aircraft. It is proposed to evaluate the influence of these well as special sensors for measuring displacements of the sensing conditions on the magnitude of the mean time between overhauls on element slide valve and the angle of rotation of the blades. A.B.K. the basis of statistical hypotheses concerning the agreement between estimated times between overhauls and estimated values of the characteristic parameter of the operational state of the aircraft. A A71-20836 # Determination of the optimal parameters of procedure of testing the statistical hypotheses on the basis of the agents for protecting the compartments of a flight vehicle from Kolmogorov-Smirnov criterion is proposed. V.P. aerodynamic heating during long flights at high flight speeds

205 A7 1 -20839

(Opredelenie optimal'nykh parametrov sredstv zashchity ot aero- and correlated with engine and combustor exhaust studies It is seen dinamicheskogo nagreva otsekov letatel'nogo apparata pri bol'shoi that solid carbon is the nonequilibrium product of fuel vapor air skorosti i prodolzhitel'nosti poleta). F. G. lasinskii and A. A. combustion in locally fuel rich zones Calculations of carbon Kobylianskii. Samoletostroenie i Tekhnika Vozdushnogo Flota, no. oxidation rates are then used to show that significant fractions of the 22, 1970, p. 61-69. In Russian. carbon formed in the rich regions of the primary zone may be Description of a method of determining the optimal weight of consumed in the leaner regions of the primary zone and in the the outer and inner heat-protection layers of a stressed skin and the secondary zone Finally, combustor design features desirable for optimal efficiency of a cooling system for a compartment of a flight minimal exhaust smoke art summarized, and areas where further vehicle traveling at a high speed (at Mach numbers greater than 5) research would be most beneficial are identified (Author) during a flight lasting several hours. The temperature of the stressed skin is assumed to be given. The density of the outer and inner layers of the thermal insulator is assumed to be temperature-dependent, while a linear temperature dependence is assumed for the thermal A71-20917 Mechanical properties of high-performance conductivity. Radiation from the outer surface of the high- temperature thermal insulator is taken into account. The problem is plastics composites. J. D. Ray (USAF, Materials Laboratory. Wright- reduced to a determination of the relative extremum of a function of Patterson AFB, Ohio). Plastics Institute, lnternational Conference on three variables with the aid of Lagrange multipliers. When a Carbon Fibres. their Composites and Applications, London, England. Feb. 1971, Paper 14 p. 7 refs. $24. per set of 49. ready-made solution is used for the heat balance equation on the 2-4, 29. outer surface of the heat insulator, solutions for the optimal The high-performance composites are characterized as to the thicknesses of the heat-protection layers and the optimal efficiency strength and moduli in tension, compression, flexure, and shear. TWO processes used for boron-epoxy resin system composites are of the cooling system are obtained in closed form. A.B.K. described, and the properties of these composites are summarized. The mechanical properties of composites reinforced by surface. treated and untreated silicon carbide fibers are presented. It is shown A71-20839 i! A gasdynamic stand for testing materials and that certain filament treatments have a marked effect on the structural elements for their resistance to cyclic thermal loading resulting mechanical properties. Three types of beryllium composites (Garodinamicheskii stend dlia ispytaniia materialov i kon- were fabricated and mechanically tested. The properties obtained are strttktivnykh elementov na soprotivliaemost' tsiklicheskomu discussed in comparison to those of other composites. The average teplovomu vozdeistviiu). L. P. Lozitskii. V. A. Konev. B. la. longitudinal properties of unidirectional graphite/epoxy composites Kudsiashov. V. F. Lapshov. and N. A. Snegirev. Samolerostroenie i are tabulated for different types of fibers. The future of these Tekhnika Vozdushnogo Flota, no. 22, 1970, p 81-87, In Russian. composites as high.performance aerospace materials IS briefly dis- Description of a gasdynamic stand which makes it possible to cussed. Z.W. test various structural elements of the hot part of a gas-turbine engine, as well as materials specimens. for their resistance to cyclic thermal loading at various heating and cooling rates in a wide range of thermal cycling with and without the application of mechanical A71 -20929 Carbon-fibre aircraft structures . Some cost loads. The proposed stand, constructed on the basis of a turboprop aspects. J. Fray (Hawker Siddeley Aviation, Ltd.. Stockport. Ches., engine, uses a series-produced turbojet engine ds the compressed-air England). Plastics Institute. International Conference on Carbon geneiator. It is distinguished from other such devices in that the Fibres. their Composites and Applications, London, England, Feb. maintenance of real gas-air flow parameters IS ensured, the lower 2-4, 1977, Paper 46. 5 p. $24. per set of 49. limit of temperature thermal cycling is reduced to 0 to 10 C, and the Study of the likely influence of material cost on the future number of turbine nozzle and working blades or materials specimens utilization of carbon-fiber reinforced composites in aircraft struc- that can be tested simultaneously is increased to 50 to 60 units. tures. It is shown that an aircraft structure manufactured from A.B K. conventional metals can, in general, be made lighter by redesigning it in carbon-fiber reinforced composites. While weight saving is very important, it is always necessary to limit expenditure on weight A71-20843 # Restoration of the working blades of com- saving to what can be justified economically for the particular pressors by vibrational tumbling (Vosstanovlenie rabochikh lopatok aircraft. The actual figure usually falls within the range of 10 pounds kompressorov vibrogaltovkoi). E. la. Korenevskii and V. K. latsenko. sterling per one pound of weight for the smaller conventional aircraft Samoletostroenie i Tekhnika Vozdushnogo Flota, no. 22, 1970, p. to 100 pounds per one pound for sophisticated high-speed aircraft. 121-125. In Russian. At the present time it costs between 60 to 330 pounds to save one Consideration of the problem of improving the surface finish pound of structure weight by using carbon-fiber composites, but if and restoring the fatigue strength of axial compressor blades during the price of fiber falls as is expected, the corresponding figures in regular overhaulings of engines by means of vibrational tumbling. It 1975 will be 15 and EO pounds. Thus, if the material is satisfactory is shown that the fatigue strength of blades made of 1Kh17N2 steel technically the market for carbon fiber in aviation should become quite large. Z.W. is increased by vibrational tumbling, Positive results were also obtained in restoring compressor blades made of 13Khl4NVFRA Steel. It is concluded that the restoration of compressor blades by vibrational tumbling is much more effective and economically more feasible than mechanical manual polishing. A.B.K. A71-21022 # Arrangement of manometric equipment on an oriented satellite (Ob ustanovke manometricheskoi apparatury na orientirovannom sputnike). V. A. Shabokhin, V. F. Kameko, V. M.

A71-20867 + Smoke emission from jet engines. Lawrence H. Kovtunenko, E. P. laskevich, and N. V. Dzhordzhio. Kosmicheskie Linden and John E. Heywood (MIT. Cambridge. Mass.). Combustion Issledovaniia, vol. 9, Jan.-Feb. 1971, p. 151, 152. In Russian. Science and Technology, vol. 2, Jan. 1971, p. 401-411. 42 refs, Manometric measurements taken by equipment set up in the Grant No. NGR-22-009378. nose section of Cosmos 149 and Cosmos 320 spacecraft which were The fwndamental processes determining the amount of smoke in stabilized with respect to the velocity vector by an aerodynamic the exhaust of a gas turbine engine are examined, First, the system. Results for the number of particles passing in unit time configuration of modern combustors and the state of knowledge of through a unit area of the sensor's inlet opening show that a plus or the processes occurring within the combustor are reviewed. Data minus 15 deg variation in angle of attack causes only 3.5% error, from laboratory flame studies of carbon formation are then discussed which is covered by the instrumental errors. T.M.

206 A71 -21166

A71-21049 Flight operations to minimize noise. Dennis R. outline of the characteristics of Air Force and Navy aircraft and of their electrical power systems is followed by a review of aircraft Halwes (Bell Helicopter Co.. Fort Worth, Tex.). (American Heli- battery requirements and of specific battery design peculiarities. copter SociW, American Institute of Aeronautics and Astronautics, Information is presented on aircraft battery manufacturing and and University Of Texas, Joint Symposium on Environmental Effects on VTOL Designs, Arlington, Tex., November 16-18. 1970, Proceed- processing, operation and maintenance, as well as on field performance. Special attention is given to factors affecting battery ings.) VefliFh. v.01. 17, Feb. 1971. 0.4-9. 5 refs. performance. such as operating practices, battery conditions aboard Certain helicopter operating conditions are known to produce aircraft, and battery limitations. The future prospects of zinc-silver higher noise levels than others. Flight tes evaluations of various size oxide aircraft batteries are assessed. helicopters are being made to determine which flight conditions M.V.E. cause the higher noise levels. The initial results of these tests have been used to define flight techniques which permit the pilot to avoid generating excessive noise while operating in and out of heliports. A71-21115 Equivaknt tests of aircraft engines. I. N. With these techniques an operator would be able to use heliports in Shkanov, L. I. Burlakov, A. A. Kovalev. and V. P. lurikov (Kazanskii many areas without violating city noise codes. Test results show that Avlatsionnyi Institut, Kazan. USSR). (Problemy Prochnosti, voi. 1, when the helicopter operates without blade slap, the altitude Dec. 1969, p. 30-34.) Srrengrh of Materials, Dec. 1969, p. 596.599. necessary to avoid exceeding noise code limits is one half the altitude Translation. necessary with blade slap. If rhe helicopter flies at the same altitude, Examination of the principal damaging factors affecting the the use of quieter operating techniques can reduce the ground area particular elements of an aircraft engine. A testing program is exposed to the same noise level by as much as 75%. and can reduce established for entire engine which is equivalent to 3OOO hr of a the required distance between a heliport and a noise-sensitive area regular stand test. The evaluation obtained by this program is boundary line by 50%. These reductions in noise exposure result in compared with results obtained by regular tests. Z.W. greater use of the helicopter’s unique capabilities without expozing noise sensitive areas to high noise levels. (Author I

A71-21162 # Statistics of the sound field of a source above A71-21097 Cell and battery case maerials, 041 sealing a rough. imperfectly reflecting surface. Jay C. Hardin and Thomas J. techniques for sealed silver-zinc batteries. A. M. Chreitzberg (ESB, Brown (NASA, Langley Research Center, Hampton, Va.). Acoustical lnc., Raieigh, N.C.). In: Zinc-silver oxide batteries; Electrochemical Society of America, Annual Meering, 80th, Houston, Tex., Now. 3-6, Society, Fall Meeting, Symposium, Montreal, Canada, October 6-11, 1970, Paper. 28 p. 25 refs. 1968, Proceedings. Symposium co-sponsored by A theoretical analysis of the sound field due to a sinusoidal the US. Air Force Aero Propulsion Laboratory. Edited by Arthur source located above a rough reflecting surface with variable Fleischer and J. J. Lander. New York, John Wiley and Sons, Inc., admittance is developed. Both the elevation and the admittance of 1971, p. 313-319. the surface are represented by isotropic random processes. The Review of the case-cover materials for sealed Zn/KOH/AgO cells Helmholtz solution is employed with the boundary conditions and batteries, as well as the cell sealing techniques, developed in the approximated by the field which wwld be present on the local period 1960 to 1968 for Ranger, Mariner, and Surveyor space tangent plane. This yields a formulation in which contributions to missions. Typical material characteristics are given. and cell jar the solution from variations in surface elevation, slopes. and -ate?iz!. ca;jaei:.,- Gzc, o+iu’ hiJ: ,,tr,,uicl LypiLdi ui uiiirlenc iilght 31-i:rar.ce 272 c!ca:!) eVk!e;;:. X~rnentproperties of rhe field are cells are summarized. Examples illustrating several sealing techniques then obtained in terms of the first order and joint characteristic are presented. O.H. functions of the surface and the autocorrelation of the admittance. In certain instances, asymptotic expansions of the integrak representing the mean field yield simple formulas involving tabulated functions. The results are of interest in amnection with ground A71-21102 Applications of zinc-silver oxide batteries. Paul effects on aircraft noise measurement. (Author) L. Howard. In: 2inc.silver oxide batteries: Electrochemical Society, Fall Meeting, Symposium, Montreal, Canada, October 6-1 1. 1968. Proceedings. Symposium co-sponsored by the A71-21163 Jet aircraft noise over residential areas. W. C. U.S. Air Force Aero Propulsion Laboratory. Edited by Arthur Meecham, S. R. Lane, and P. Hurdle (California, University, Los Fleischer and J. J. Lander. New York, John Wiley and Sons. Inc., Angeles. Calif.). Acoustical Society of America, Annual Meeting, 1971. p. 371-373. 80th. Houston, Tex., Nov. 3-6, 1970, Paper. 15 p. General discussion of the applications made possible by the Discussion of excessive noise intrusion caused by the flyover of development of the zinc-silver oxide battery since 1940. The original jet aircraft in the densely populated Los Angeles area. Results of application of this battery was in the underwater area for use in several previous noise measurement studies in this area are presented torpedoes. mines, protective devices, and buoys. Aerial application and analyzed. The measurements show that in ten residential consists of helicopters, aircraft, target drones, pilotless aircraft, and communities (at distances of 15 to 30 miles from the airport) the manned and unmanned stratosphere balloons. For helicopter and noise levels caused by jet aircraft exceed one hundred times ordinary aircraft uses, a specially designed medium high-rate long-life cell is noise. There are four major approach and departure corridors to the used which is comparable in useful life and service to the lead-acid airport with a total number of 500 commercial jet flights every day. cell. M.M. Many communities are thus subjected to about 100 excessively noisy flights during the peak traffic hours (about three hours of the day). As a result, thousands of individuals are subjected to excessive noise A71-21 103 Aircraft zinc-silver oxide batteries. G. H. Miller every two minutes for several hours each day. Almost every flight (USAF Aero Propulsion Laboratory, Wright-Patterson AFB. Ohio) exceeds the noise levels allowed by the municipal codes on and S. F. Schiffer (Yardney Electric Corp., Pawcatuck, Conn.). In: residential noise disturbances. These noise ordinances, however, are Zinc-silver oxide batteries; Electrochemical Sociew, Fall Meeting, not enforced against airlines. Several suggestions are presented to Symposium, Montreal, Canada, October 6-11. 1968, Proceedings. reduce the jet aircraft intrusion. O.H. Symposium co-sponsored by the US. Air Force Aero Propulsion Laboratory. Edited by Arthur Fleischer and J. J. Lander. New York, John Wiley and Sons, lnc., 1971, p. 375-391. A71-21166 a A station-oriented area navigation system. J. Discussion of the service requirements, performance, and merits C. Lumsden and C. A. Muller (Bendix Corp., Avionics Div., Fort of zinc-silver oxide batteries used on US. military aircraft. An Lauderdale, Fla.). Bendix Technical Journal, vol. 3, Winter 1970. p.

207 A71-21167

1-10, application an economic proposition. The central feature of the I A basic type of VOR/DME-station-oriented area navigation Airtruk’s design is the hopper. It has two 23 x 9-in. openings for system is described in which horizontal guidance is provided by a spreading superphosphate, the openings being separated by an special-purpose digital computer solution of the triangle that is I defined by ground station, waypoint. and present aircraft position. inverted V. A unique safety feature during jettison is derived from The objectives of area navigation and its potential advantages are dual tails which are clear of the slipstream. The characteristics of the 1 aircraft make possible a very uniform spread. From the viewpoint of discussed, and attention is given to such system considerations as inputioutput circuitry, Control, Storage, signal processing, and both operator and farmer, the effectiveness of this aircraft lies in its work capacity measured in acres per working hour. F.R.L. guidance equations. (Author) I

A71-21167 p The airline collision avoidance program. W. G. A71-21225 Tetra-Core - A three-dimensional space struc- Shear (Bendix Corp., Avionics Div., Fort Lauderdale, Fla.). Bendix ture. Irving E. Figge, Sr. (US. Army, Aviation Materiel Laboratories, TechnicalJournal, vol. 3, Winter 1970, p, 11-23.6 refs. Fort Eustis, Va.). ShellAviarion News, no. 391, 1971, p. 18-24. The history of the evolution of a collision avoidance system is Discussion of a new structural material (Tetra-Core), based on briefly considered, and the basic principles of the Tau concept are the design potential of composite materials and the need for I examined. Salient aspects of time/frequency technology utilization improved structures. Tetra-Core uses unidirectional filamentary are investigated. The practical collision avoidance system for aircraft composites in a specially oriented space frame structure. This 1 defined by the Air Transport Association is discussed, and details are configuration means that the concept has excellent potential for given regarding a test program for evaluating the compatibility and structural applications because it uses the material in its optimum effectiveness of the equipment considered for the collision avoidance form (unidirectional fibers). Due to the inherent redundancy of the system. The results of the investigations are evaluated giving structure, it also offers potential application in areas where fail-safe , attention to range-rate accuracy. altitude accuracy, communications requirements are high. The basic Tetra-Core elements consist of a reliability, and synchronization. The path to implementation, series of tetrahedrons which are alternately inverted and placed SO questions of system integration with air traffic control. and the that they form continuous planes. F.R.L. current design status are discussed. G.R.

A71-21254 Maintenance of aeronautical charts on a world- ~71.21169 p Position-determination systems for urban wide basis. John B. Moran (USAF, Aeronautical Chart and transit and air traffic control. T. T. Trexler (Bendix Corp., Aerospace Information Center, St. Louis, Mo.). In: American Society of Systems Div., Ann Arbor, Mich.). Bendix Technical Journal, vol. 3, Photogrammetry and American Congress on Surveying and Mapping, Winter 1970. p. 35-44. Technical Conference, Denver, Colo., Octobei 7-10, 1970, Proceed- It is pointed out that the objectives of an automatic vehicle- ings. Falls Church, Va.. American Society of monitoring system would be to supply independent surveillance Photogrammetry, 1970, p. 313-323. information (vehicle identification and location) to a traffic control The problem of updating and keeping current, a multitude of system, to provide airborne users with area-navigation approach and series of charts of various scales supporting many weapon systems, is landing data, and to provide the pilot, vehicle operator, and traffic explained. The objective of maintaining up-to-date aeronautical controller with the real-time information he requires to operate his charts is expounded and the various phases of effort to accomplish vehicle. Position-determination requirements for a number of the task are discussed. These phases start with the review of the potential system users are irtvestigated. Three potential position- requirement and its translation into cartographic terms and extend to determination system configurations are described including a the printing and distribution of the new chart. The levels of chart navigation-satellite-based time difference system, a ground-based evaluation and how these are derived is explained. The author time difference system, and a differential time difference system. explains the maintenance cycle procedures and demonstrates how a G.R. product moves thru the various phases in accord with the continuous review concept. (Author)

A71-21170 fi Digital-filter alignment of strapdown navigators. D. A. Zomick (Bendix Corp., Navigation and Control Div., A71-21266 :: Calculation of losses in the vaneless diffuser of Teterboro, N.J.). Bendix Technical Journal, vol. 3, Winter 1970, p. a centrifugal compressor (K raschetu poter’ v bezlopatochnom 45-53. 28 refs. diffuzore tsentrobezhnogo kompressora). N. A. Alemasova. In vibrating and swaying vehicles. conventional strapdown Kazanskir Aviatsionriyi lnstrttrr, Trudy, Serim Aviatsion/iye Dvrgateli, alignment techniques, such as gravity sensing and gyrocompassing, no 115, 1969, p. 32-40. In Russian. have limited accuracy and reqtiire lengthy alignment times. In this Discussion of a hydrodynamic model of a flow in a diffusei paper, the initial alignment problem is defined and the difficulties are designed as the basis for theoretical estitndtion of energy losses in examined. System dynamics are couched in mathematics appropriate vaneless diffusers of centi ifugal complcssois. The modrl wds to digital filtering, and a number of methods for estimating and developed by experirncntal studies of the thic!e-tlimrilsional structuic correcting thc misalignmerit errors - including Kalman and least- of airflows in such diffusais which iiidicdtt!tl the existi’nce of ievcihe squares filtering - aic described and contrasted with respect to flows at diffusci walls, having a subst;lntidl effect or tho tliffcisei accuracy and computational complexity. The analysis and evaluation perfoimance Scts of equations aic givt’n foi tlic enwyy hlancu at are kept as general as possil)le and ale supplemenfetl by digital the diffusei inlet and outlct foi vaiiou5 ;iitflow stitictUies. Ex simulation results showing the performance of particular filtering pressions foi eneiyy losses ds fuiictions 01 thi, xtivt’ flow width and of an exvonential variabltl are dI\o tki IVCII v 2. schemes iii specific applications. (Author)

A71-21224 Airtruk. J. A. Winterbotham (Transfield pty., A71-21267 Improvement of multistage turbines in gas Ltd.. Sydney. Australia). Shell Aviation News, no. 391, 1971, p, turbine engine designs (0 ratsionalizatsii rascheta mnogo- 14-17, stupenchatykh turbin GTD). V A. Stiunkin. Kazamkrr Aviatsio~irjyi Description of the Tiansavia Airtruk. which is an attempt to Institot, Trudy, Seriia Aviafsiori/iyc Dvrgareli, tio 115, 19G9, p. achieve a level of operational efficiency required to ,make aerial 41-46 In Russian.

208 a71 -21369

Extension of the author's single stage gas turbine improved India). Aeronautical Society of India, Journal, vol. 22, Nov. 1970, p. designing technique (1969) to the calculatlon of palameters in 251-256. multistage gas turbine designs Expressions and nomograms are given The details of design, construction, instrumentation and calibra- for the translation of the previous results to multistage turbine tion of the wind tunnel at H.A.L., commissioned recently, are briefly parameter and component analysis and selection Optimized turbine dealt with, in this report. The wind tunnel is 'Return Circuit' type stage, geometrical characteristics, blade and wheel parameters and and has a 9 x 6 ft rectangular test section with chamfered corners. multistage gas turbine efficiencies can be determined by using these The wind tunnel is driven by a 750 hp electric motor to achieve a expressions in computer calculations vz speed of 200 mph at the test section. A sting type of model support is provided. A six component strain gauge balance in conjunction with a data logging system is used for force measurements. The flow in the test section is generally satisfactory and the deviations are A71-21300 Optimization methods for jet propulsion wtth within tolerable limits. (Author) respect to exergy. L Narjes (Indian Institute of Technology, Madras, India) Aeronautical Socrety of India, Journal, vol 22, Nov 1970. p 209 217 6refs The paper deals with two optimization procedures by introduc A71-21322 On barriers in a problem of collision ing the thermodynamic concepts of exergy and anergy From purely avoidance. W. J. Grantham, E. M. Cliff, and T. L. Vincent (Arizona, thermodynamic considerations. the first part of the analysis leads to University, Tucson, Ariz.). In: Hawaii International Conference on minimum specific fuel consumption or minimum specific exergy loss System Sciences, 4th. University of Hawaii, Honolulu, Hawaii, which corresponds to maximum thermodynamic efficiency The January 12-14, 1971, Proceedings. Conference second takes into account both capital investment and expenses due sponsored by the University of Hawaii and the U.S. Army. Edited by to exergy need (or fuel consumption) of the unit This leads to Shu Lin. North Hollywood. Calif., Western Periodicals Co., 1971, p. minimum total cost flux or an economlcally optimum unit The 136.138. Grant No. NGR-03-002-011. optimum conditions are achleved by varying the compressor pressure A simple dynamical system is used to study the problem of ratio of the unit in both cases The results calculated on the basis of collision avoidance between two aircraft. The barriers separating the adiabatic, incomplete combustion from experimental observations on regions where capture is possible, for various flight conditions, are a furnace burning heavy oil used for steam generation are compared determined by solving an optimal control problem for abnormal arcs wtth the results of adiabatic and compiete combustion in let engine and similarly for a differential game. (Author) combbstion chambets (Author)

A71-21335 * System aspects of air traffic control. Michael A71-21301 Hypersonic airbreathing engines for launching t Athans (MIT, Cambridge, Mass.). In: Hawaii International Con- space vehicles. K. A. Damodaran (Indian Institute of Technology. ference on System sciences, 4th. University of Hawaii, Honolulu, Madras, India). Aeronautical Society of India, Journal, vol. 22. Nov. Hawaii, January 12-14, 1971, Proceedings. 1970, p. 218-224. 11 refs. Con- ference sponsored by the University of Hawaii and the U.S. Army. The cost of the present day space transportation is extremely Edited by Shu Lin. North Hollywood, Calif., Western Periodicals Co.. high due to high operational and vehicle costs. Reduction in the 1971, p. 335337. 6 refs. Grants No. NGL-22-009-124; No. AF overall cost of space exploration programmes appears feasible with a AFOSR 69.17744 iowdltiiy syblriii wnicn uses a composite rocket cum airbreathing This paper considers the problem of coordinating the traffic propulsion unit. By adapting such a system a reduction in operating flow and holding patterns of N aircraft which desire to land in a cost by half to one third of that of the conventional rockets is single runway. A distance separation is to be enforced over the outer expected. A further cost reduction can be achieved by making the marker. It is shown that this problem can be attacked as a variation (Author) System fully or partially recoverable. of a linear-quadratic optimal control problem. The solution of this optimization problem can be used to indicate which aircraft can accomplish headway corrections by velocity control, and which require to undergo path stretching or holding maneuvers. (Author) A71-21302 # Flutter of simply supported skew panels with mid-plane forces in supersonic flow. Somayajulu Durvasula (Indian Institute of Science, Bangalore, India). Aeronautical Society of India, Journal, vol. 22. Nov. 1970, p. 225-234. 28 refs. A71-21343 * Minimum variance estimates of signal deriva- Panel flutter of stressed, flat, simply supported skew panels is tives - A problem in instrument landing systems. J. Campbell Martin, investigated using the classical small deflection thin plate theory. The Bobby J. Prochaska, and Dan C. Stanzione (Clemson University, two-dimensional 'static approximation' is used to represent the Clemson, S.C.). In: Hawaii International Conference on System aerodynamic loading. An approximate solution is obtained by using Sciences. 4th. University of Hawaii, Honolulu, Hawaii, January Lagrange's equations representing the deflection surface in terms of 12-14, 1971. Proceedings. Conference sponsored double Fourier sine series in oblique coordinates. Results of by the University of Hawaii and the U.S. Army. Edited by Shu Lin. numerical calculation for the critical dynamic pressure of stressed North Hollywood, Calif., Western Periodicals Co., 1971, p. 477-479. rhombic panels are presented. The influence of each of the Grant No. NGR-41-001-024. components of orthogonal stress resultants is studied. It is found that This approach uses the form of the Kalman filter as an observer the -critical dynamic pressure is lowered by the compressive and shear for the derivatives of observable signals or states. The gain matrix for forces. In particular the shear stress is found to significantly lower the filter is derived to minimize the variance of the estimate of the the critical dynamic pressure as in the case of rectangular panels. derivative of the state, instead of the state itself. The results are (Author) shown superior to other methods, under prevalent conditions. (Author)

A71-21305 i! Design features and characteristics of the 9 x 6 A71-21369 Are microelectronic circuits reliable enough ft wind tunnel at H.A.L., Bangalore. T. N. Krishnaswamy (Indian for aircratt engine control applications. R. S. Smith (Texas In- Institute of Science, Bangalore, India), Raj Mahindra, S. R. Telang, struments. Inc., Dallas, Tex.). Society of Automotive Engineers, and K. S. Sudheendra (Hindustan Aeronautics. Ltd., Bangalore, Narional Aeronautic and Space Engineering and Mantifactwing

209 A71-21425

Meeting, Los Angeles, Calif, Oct 5 9, 1970. Paper 700822 8 P of sound through ribbed panels and to quantitatively evaluate the Members, $1 00, nonmembers, $1 50 effect of structural damping in altering these parameters. Specifical- Review of ]et engine environmental conditions. along with ly, the program sought to evaluate the significant characteristics of documented microcircuit performance under similar environmental the TL curve in terms of the dynamic characteristics of the panels. conditions Data are provided to enable a design engineer to further The applicability of the results obtained to aircraft structures is seek out devices or equipment to meet his particular requirements It examined. O.H. IS pointed out thdt reliability testing programs are now proving that microcircuits can be tested and selected for severe temperature and vibration environments MM A71-21441 1 0-Star experimental quiet aircraft. E. D. Griffith (Lockheed Mlssiles and Space Co., Sunnyvale, Callf.). Acoustical Society of America, Meeting, 80th. Houston, Tex., NOV. A71-21425 # Experimental atmospheric absorption values 3-6, 1970,Paper. 14 p. from aircraft flyover noise signals. Dwight E. Bishop and Myles A. Discussion of the design and acoustical characteristics of the Simpson (Bolt Beranek and Newman, Inc., Los Angeles, Calif.). Q-Star or Quiet-Star Aircraft built by Lockheed as a research vehicle Acoustical Society of America, Meeting, 80th, Houston, Tex., Nov. to study Quiet Aircraft Technology. The research aircraft is designed 3-6,1970, Paper. 16 p. Discussion of the results of a study performed to obtain to have minimum acoustic noise signature so that it can perform its mission while being undetected aurally by observers on the ground. experimental values of atmospheric absorption coeffictents from Its basic airframe is that of a Schweirer 2-32 sailplane with a recorded noise samples of aircraft flyovers. An attempt is made to 'Wankel'-type rotary combustion, water-cooled engine mounted iust develop and test new methods for analyzing flyover noise signals aft of the cockpit, and an efficient muffler system which minimizes received at different ground positions to obtain experimental values engine exhaust noise. Acoustic data taken from aircraft flyovers at of air absorption, and to compare these values with those predicted altitudes of 125 ft are given graphically showing the aircraft overall by the SAE Aerospace Recommended Practice, referred to as sound pressure level as a function of indicated air speed. Acoustic ARP-866. Atmospheric absorption values over the frequency range characteristics for a three-blade and a six-blade propeller are up to 8000 Hz are obtained and presented graphically. It is shown examined. To provide some iudgmerlr iii the degree of noise that the values are in a good agreement with calculated values over reduction achieved on the 0-Star, a comparison to similar con- the frequency range from 1250 to 6300 Hz. At 1000 Hz and lower ventional aircraft is made. It is shown that at an altitude of about frequencies, the experimental values are significantly greater than the 2000 ft, the Q-Star noise approaches a level that will be masked by calculated ones. It is suggested that this increase in absorption at background noise. O.H. lower frequencies may reflect losses due to scattering in the lower atmosphere not accounted for in the current calculation procedures. There is also poor agreement with calculated values at 8000 Hz, which may, in part, reflect the lessened accuracy in field measure- A71-21450 f Conditions inside cumulus clouds preceding ments due to sharp reduction in data sample sizes at 8000 Hz. O.H. the onset of precipitation. Martin R. Schock and A S. Dennis (South Dakota School of Mines and Technology, Rapid City. S. Dak.). Journal of Applied Meteorology, vol. 10, Feb. 1971, p. 70-72. 8 refs. U.S. Department of the Interior Contract No 14-06-D-5979. A71-21426 Flight test measurement of exterior turbulent Conditions within 16 cumulus congestus clouds were measured boundary layer pressure fluctuations on Boeing model 737 airplane. on aircraft penetrations near the -5C level and precipitation W. V. Bhat (Boeing Co.. Seattle, Wash.). Journal of Sound and development during the subsequent 45 min were noted. Significant Vibration, vol. 14, Feb. 22, 1971, p. 439-457. 19 refs. correlations exist between the in-cloud conditions and the time of Investigation of the turbulent boundary layer pressure fluctua- onset and intenslty of precipitation. The degree of spatial correlation tions on the exterior of high-speed aircraft, based on two separate among the fields of temperature, vertical motion and water content in-flight measurements on Boeing model 737 airplane In these flight within a given cloud proved more important to subsequent develop- tests, a seven-microphone array was used at two different locations ments than did the mean values of these variables. (Author) along the fuselage. The measurements were carried out for Mach numbers of 0.78, 0.6. and 0.45 for the forward location, and for Mach numbers of 0.78 and 0.45 for the aft location. The pressure A71 -21625 Aircraft gas turbine engine technology. I. E. power spectral densities (PSD) and root mean square pressure Treager (Puidue University, Lafayette, Irld 1 New Yolk. McGiaw fluctuations were calculated at all five flight conditions. PSD Hill Book Co.. 1970 470 1) $14 95 measurements and the subsequent analysis indicated that exterior Consolidated information tieatiny the Q~Stuibinc engine at the turbulent boundary layer pressure fluctuation measurements are technical level is offered to supplement what has been written contaminated by the jet engine noise at Mach 0.45 forward location, elsewhcie fiom an engineering viewpoint. Although the text is and Mach 0.78 and 0.45 aft location. Therefore, other statistical designed primarily to provide a source of information for aircraft properties, such as wideband convection velocity, wideband spatial technicians, it may be used by others interested in this type of power correlation, narrow band convection velocity, and the amplitude of plant. An attempt IS made to follow a logical presentation, and to use cross PSD, are presented only for Mach 0.78 and 0.6 forward the type of approach that does not assume a great deal of technical location. The measurements at these two flight conditions are knowledge on the part of the reader. Beginning with the background compared with laboratory measurements of the turbulent boundary and development of the gas turbine engine, the book concludes with layer pressure fluctuations on a flat plate. A physical description of a discussion of the Pratt and Whitney JTBD, the General Electric the turbulent boundary layer pressure fluctuations IS presented. O.H. J79, the Lycoming T-53, the Allison 501-D13, and the Continental J69-T-25. Sections of the text are devoted to construction and design, systems and accessories, and testing and maintenance. Fuel A71-21431 Effect of structural damping on the airborne control is considered in detail, because fuel metering is a critical sound transmission loss of ribbed panels. John M. Zalas (Lord factoi in correct engine operation, and because the fuel control IS Manufacturing Co., Erie. Pa.). Journal of Environmental Sciences, probably the most complicated and difficult to understand unit on vol. 14, Jan.-Feb. 1971, p. 16-20. 8 refs. the entire engine. F.R.L. Discussion of a series of laboratory measurements of the airborne sound transmission loss (TL) on ribbed aluminum panels with and without structural damping treatments. The purpose was to A71-21659 ,# Use of computers in air traffic control. Gustav empirically determine the controlling parameters in the transmission E. Lundquist (FAA, Washington, D.C.). University of Tennessee

210 A71-21684

Space Institute. Computer Developments and Applications Short tool that has been most important to the rapid advancxs of flight Course. Tullahoma. Tenn., Dec. 8-12, 1969, Paper. 36 p. technology. Fundamental concepts are outlined. and some early low Description of the air traffic control (ATC) automation program speed wind tunnels are briefly described. The work carried out by for en route and terminal facilities which has evolved in response to the National Advisory Committee for Aeronautics (NACA) in the the continuing growth of air traffic and is intended to provide fields of variable density wind tunnels and large wind tunnels is increased capacity and safety to the existing ATC system. A brief reviewed. Attention is given to high speed, transonic, supersonic, review is given of the characteristics of today's manual ATC system, hypersonic, and hypervelocity wind tunnels. Some recent special followed by a detailed discussion of the implementation and purpose tunnel developments are described. F.R.L. operation of the en route portion of the automation program, termed NAS En Route Stage A. Finally. the features of the terminal automation program, termed ARTS Ill, are presented. When com- A71-21679 # Technical failures in civil aircraft accidents in pleted, the combined system will provide automation at each of the Canada. T. W. Heaslip (Ministry of Transport, Accident Investigation 20 air route traffic control centers and those terminals where Engineering Laboratory, Canada). Canadian Aeronautics and Space automation is warranted. All of these facilities will be interconnected Journal, vol. 17, Feb. 1971. p. 43-50. with data transmission links, and the entire system will function as a nationwide, realtime automated system. O.H. Material failures continue to play a major role in aircraft accidents. Such failures tend to disclose some of the most serious technical problems encountered by the aircraft industry. In an endeavour to preclude similar recurrences, all material failures in A71-21660 # A small computer in range instrumentation. Canada which contribute to accidents are investigated in depth. This Lewis C. Corey (Mitre Corp.. Bedford, Mass.). University of paper initially describes the Canadian organization to ensure effective Tennessee Space Institute, Computer Developments and Applications aircraft accident investigation. Next the accident picture over the Short Course, Tullahoma, Tenn., Dec. 8-12, 1969. Paper. 31 p. past ten years is covered, followed by a survey of technical failure Review of some aspects of the methods and equipment used at investigations which reveals the significant problem areas. Typical the Test Center of the Patuxent Naval Air Station for testing the examples of material failures are also included. Finally. the manner overall performance of aircraft avionics and weapons systems as in which information will flow in future to the aviation community (Author) whole mission-implementing entities. In particular, the integration of is discussed. a computer with a radar and phototheodolite range instrumentation system is evaluated in terms of its contribution to reduced time requirenlents for obtaining useful test results (such as early diagnosis A71-21680 # A V/STOL microwave approach and landing and correction of malfunctions) as against computer investment and system. A. J. Stein (FAA. Washington, D.C.). /Canadian Aeronautics operation costs. The importance is assessed of computer-provided and Space Institute, Aerospace Electronics Symposium, Ottawa, instant replay capability of every radar report in slow motion. Some Canada, Mar. 19, 1970.1 Canadian Aeronautics and Space Journal, of the merits of off-line operations concurrently with on-line vol. 17, Feb. 1971, p. 51-55. computing are pointed out. The radarcomplementing contribution Flight characteristics of V/STOL aircraft, restricted size of of the phototheodolite ranging system is also reviewed. M.V.E. V/STOL runways and the unique locations of V/STOL ports require an approach and landing system which differs in many ways from A3?-21661 # The calculation of optimal linings for jet those now in use for conventional fixed wing aircraft. The microwave engine inlet ducts. J. P. D. Wilkinson (GE Research and Development scanning beam technique offers the best potential for satisfactory Center. Schenectady. N.Y.). Acoustical Society of America, Meeting, performance of a V/STOL ILS. An engineering model of a V/STOL 80th. Houston, Tex., Nov. 3-6,1970, Paper. 31 p. 5 refs. Contract approach and landing system being procured by the FAA is No. NASw-1992. described. (Author) A numerical method is presented for calculating the optimal lining impedance for the inlet duct of a jet engine. The calculation is based on the condition that the total radiated power from the duct shall be a minimum. Several situations are considered: first, the case of an axially symmetric duct in a stationary acoustic medium; A71-21681 Ball forming solves contouring problems. second, that of a body of arbitrary geometry in a stationary medium; Wynand W. Brandel and Lawrence S. Klass (Avco Corp.. Aero- and finally. the case of an axially symmetric duct in the presence of structures Div., Nashville, Tenn.). Metal Progress, vol. 99, Mar. 1971, spinning modes and axial air flow. In each case, the method may p. 56, 57. yield the optimal lining impedances for a given discrete frequency. Description of the ball forming technique and its application to flow velocity. and duct geometry. To demonstrate the application of the contouring of structural parts of aluminum alloys. In this the method. a number of cases are investigated. First, a cylindrical technique, steel balls of uniform size and shape are used as forming duct closed at one end with a vibrating piston is used to make media. To avoid surface roughness, the balls are delivered at low comparisons with predictions obtained analytically by Rice. Then a velocities. As an example, a procedure of wing panel forming is more complex problem of a bell-mouth compressor is investigated. A described, and the advantage of prestress tooling is discussed. Z.W. discussion of the results obtained is presented, together with a critique of the potential difficulties of the method as applied to complex duct configurations, (Author) A71 -21684 Plasma-arc welding of jet engine wmponents. J. R. Kelley and W. P. Hughes (General Electric Co., Evendale, Ohio). A71-21666 # The history, evolution, and use of wind Metal Progress, vol. 99, Mar. 1971, p. 66-68. tunnels. Kennith L. Goin (Sandia Laboratories, Albuquerque, N. The plasma-arc welding of jet engine components of titanium- Mex.). AIAA Student Journal, vol. 9, Feb. 1971, p:3-13. 12 refs. and nickel-base alloys is described and compared with gas tungsten- AEC-supported research. arc and electron beam processes. It is concluded that the effective- General discussion of wind tunnels, commencing with a histori- ness of plasma arc welding :t:;ns from the fact that the ionized gas cal review, followed by descriptions of major developments. The stream is forced to pass through a constricting chamber. In initial achievements of manned flight and the rapid advance of both comparison with the gas tungsten-arc method, there is a substantial manned and unmanned flight have followed the development of increase in arc energy generated per unit area, and the efficiency of wind tunnels and techniques for testing. The.wind tunnel is the single energy transferred to the workpiece is improved. Z.W.

21 1 A71 -21685

A71-21685 Improving structural efficiency through A71-21724 # Developments in stratospheric and rneso- materials selection. Donald Webster (Boeing Co., Seattle, Wash.). spheric analyses which dictate the need for additional upper air data. Metalprogress, vol. 99, Mar. 1971, p. 81, 84-87. Richard Scherhag, Karin Labitzke (Berlin, Freie Universitat, Berlin, Basic equations are presented for obtaining the lightest com- West Germany), and Frederick G. Finger (US. Weather Bureau, ponents of airframe structures made in the form of solid panels, Suitland, Md.). In: Meteorological observations and instrumentation; sandwich panels, columns, and floor panels. The structural efficiency American Meteorological Society, Symposium, Washington, D.C., of wide panels made of 7075-T6 aluminum, mill-annealed Ti-6AI-4V, February 10-14. 1969, Proceedings. Edited by and 4340M steel is compared. The effect of high temperature on the Sidney Teweles and James Giraytys. Boston, American Meteoro- strength and the Young's modulus of these materials is briefly logical Society (Meteorological Monographs. Volume 1 1, No. 33). examined. Z.W. 1970, p. 85-90. 13 refs. Meteorologists are still faced with the problem of explaining stratospheric phenomena such as 'explosive warmings.' The most recent event which took place in late 1967 is briefly discussed with A71-21710 Some questions related to the vibration the aid of both rawinsonde and rocketsonde data. A continual need strength of aviation gas-turbine motors with long operating times. v for more stratospheric data to the highest possible levels is stressed, 1. Omel'chenko (Prohlemy Prochnosri, vol. 2. Jan 1970, P. 95-98.) especially for studies of possible tropospheric-stratospheric relation- Strerigth of Mdterials, Jan 1970. p 95-99 Tianslation ships. Future supersonic transport operations will require this Description of the improvements in the strength and gas information, as well as space vehicles reentering the atmosphere. dynamic characteristics of gas turbine engines AI -20 by decreasing Several proposed programs, which should supply a relatively large their vibrations. Topics discussed include: (1) vibration decrease of amount of stratospheric data, are discussed. However, improvements this engine by means of elastic elements, (2) effect of the elastic in the present-day data-gathering systems are vitally necessary before supports at the bearing nodal points of the rotor on the vibration these programs can proceed. (Author) level, and (3) effect of the interaction between the engine body and the propeller on the vibrations of the engine. Z.W.

A71-21732 # The need, meaning and usefulness of meteorological observations for aviation. Peter E. Kraght, W. B. Beckwith. S. A71-21713 A review of the status of the technology of the G. Bigler, Eugene Bollay, R. D. Fletcher, and N. E. Rider (American air cushion vehicle. P. A. Sullivan (Toronto, University, Toronto, Airlines, Inc., New York, N.Y.). In: Meteorological observations and Canada). Society of Automotive Engineers, Autornorive Engineering instrumentation; American Meteorological Society, Symposium, Congress, Detroit, Mich., Jan. 11-15,1971, Paper 710183. 22 p. 28 Washington, D.C., February 10-14, 1969, Proceedings. refs. Members, $1.00; nonmembers, $1.50. Research supported by Edited by Sidney Teweles and James Giraytys. Boston, the National Research Council of Canada. American Meteorological Society (Meteorological Monographs. This paper reviews the current status of the technology of the Volume 11, No. 33). 1970, p. 173.177. air cushion vehicle (ACV) ACV economics are examined to suggest Summarization of a panel discussion on the importance of priorities for research and development, and to illustrate the effects meteorological observations and some approaches to overcome of various design decisions. The basic features of and problems weather problems in aviation. The various aspects of the problem of associated with flexible skirt systems are discussed. Problems in modifying the terminal weather, particularly that of airport fog propulsion, structures, control and other areas are reviewed. and dispersal, are examined. Recent developments in long distance topics for research are indicated. The paper concludes by suggesting remoting of radar data are reviewed. The question of what that much more development work is required to bring the vehicle to meteorological information is needed and how it can be used to a reasonable state of maturity. Operating costs and controllability are ensure the safe and efficient utilization of airspace IS discussed and singled out as requiring special attention. However, solutions to analyzed. The subject of instrumentation by which aircraft reports of many of the problems seem possible so that there are grounds for wind and temperature over data-sparse areas might be fed into optimism about the future of this vehicle. (Author) ground-based data processing systems, and the possibility of designing completely automated reporting systems. are dealt with. Finally, several remarks of a general character about rneteorologlcal observations in the terminal area are presented. O.H. A71-21722 Some basic characteristics of observational data. John C. Bellamy (Wyoming, University, Laramie, Wyo.). In: Meteoiological observations and instrumentation; American Meteoro~ logical Society, Symposium. Washington, D.C., February 10.14, A71-21739 # Problems and status of worldwide develop- 1969, Proceedings. Edited by Sidney Teweles ment of upper air sounding systems. M. F. E. Hinzpeter (Bundes- and James Giraytys. Boston. American Meteorological Society ministerium fur Verkehr, Deutscher Wetterdienst, Munich, West (Meteoiological Monographs. Volume 11, No. 33). 1970, p. 71-78. 6 Germany). In: Meteorological observations and instrumentation; refs. ESSA Contract No. E-291-68(6). American Meteorological Society, Symposium. Washington, D.C., The chaiacteristics of observational data arc andlyzed here from February 10-14. 1969, Proceedings. Edited by an overdll point of view with respect to how it can best contiibiite to Sidney Teweles and James Giraytys. Boston, American Meteoro- more complete knowledge and utilization of all scales of physical logical Society (Meteorological Monographs. Volume 11, NO. 33). occuriences thioughout the atmosphere. Several novel concepts are 1970, p. 361-377, 25 refs. formulated. among which the explicit recognition of the more About ten different sounding systems are used by the aero- ordinal than cardindl numbci chardcteristic of obscrvational dat;r is logical networks of the Northern Hemisphere. The main character- of basic impor tance Formal definitions of thc! ielationships betwrcii istics of these systems with regard to sensors and telemetry are these two quite different kinds of numbers load to definitioiis of described. The method of reducing the daytime readings of radio- 'continuous (ordindl numbei) data' and 'cooidinal' relationships sondes to nighttime readings is used in order to illustrate that among importantly related kinds of quantities. with respect to which worldwide compatibility in synoptic analyses of higher atmospheric highly infoirndtive 'residual data' can well be concisely portrayed. A levels is still unsatisfactory. Some features in the field of aero- clearer understanding is thereby also obtained concerning the basic dynamics are demonstrated. The results show that a freely rising theoretical and practical role that vaiiables such as baiometi IC balloon is not an ideal sensor for measuring wind velocity aloft, and 'altitude' could well play in meteorological as well as aeronautical that the radiation error of temperature sensors is not only a function operations. (Author) of the solar elevation angle, the air density and the rate of ascent, but is also influenced by the microstructure of the air. It is shown that

212 A71-21813 the wind speed aloft may be used as a measure of the microstructure. motor glider with a Wankel engine discussed is the model SF-24/K

A71-21742 ? Constant-level balloons for sounding systems. Vincent E. Lally (National Center for Atmospheric Research, A71-21770 Mechanics of curvilinear flight for glider pilots Boulder. Colo.). In: Meteorological observations and instrumenta- (Kurvenflugmechanik der Segelflieger). Max Haubenhofer. Deutscher tion; American Meteorological Society, Symposium. Washington, Aerokurier, vol. 15, Feb. 1971, p. 91. In German. D.C., February 10-14. 1969, Proceedings. Edited 90. The transformation of the polar for gliding into the polar for by Sidney TBweles and James Giraytys. Boston, American Meteoro- curvilinear flight is discussed taking into account relations involving logical Society (Meteorological Monographs. Volume 11, No. 33). rate of sink in the curve, flight velocitv in the curve, and curvature. A 1970. p. 392-396. 5 refs. graph for determining optimal climbing conditions in an ascending The superpressure balloon floats at a constant-density altitude, current is presented, and relations of dynamic pressure and sloping the maximum deviation from design altitude rarely exceeding 40 m. position for constant angles of attack are investigated. G.R. Balloons flying in the stratosphere will remain aloft for years. the longest flight duration to date being 15 months. Satellite location of these superpressure (GHOST) balloons is planned to provide global data on the atmospheric circulation. Icing remains the major problem in achieving long durations for flights above the freezing level and A71-21 81 1 Society of Automotive Engineers and U.S. below 10 km. The superpressure balloon can be used in conjunction Department of Transportation, Conference on Aircraft and the with satellites to provide a global description of the atmospheric Environment, Washington, D.C., February 8-10, 1971, Proceedings. circulation at all levels and at all latitudes. (Author) Part 1. New York. Society of Automotive Engineers, Inc., 1971. 309 p. $1 9.50. The subjects considered include the training of acoustical engineers, the airport and community interface, and air-pollution A71-21767 VFR at bad weather - Flights over closed problems produced by aircraft. Attention is given to airport and cloud cover, radar ntpport from the ground. Ill (VFR bei aircraft noise, community response to aircraft noise. and state, Schlechtwetter - Fliige iiber geschlossenen Woikendecken, Radar- Federal, and international regulations concerning aircraft noise. untenthung vom Boden. Ill). Max Korte. Deutscher Aerokurier, Alleged dangers in connection with the SST, and the compatibility of vol. 15. Feb. 1971, p. 68, 69. In German. city and airport, are examined. G.R. It is pointed out that blind flying even for vev short periods in order to fly through the cloud layer when the destination is reached should not be undertaken without a suitably equipped aircraft and without the required license. Conditions are analyzed which permit A71-21812 U.K. researcn in sonic boom. J. B. Large and flying above clouds. A flight altitude of at least 1000 ft above ground D. N. May (Southampton, University, Southampton, England). In: or water is required. It must be possible to stay on the intended Society of Automotive Engineers and U.S. Department of Trans- flight CCW~ZP, 2nd rl+;-telephone ~3rn~cnic??ionr:”~t 5. pcssit.!?. portation, Conference on Aircraft and the Environment, Washington, Weather conditions which make it highly inadvisable to fly above the D.C., February 8-10. 1971, Proceedings. Part 1. clouds are pointed out. Questions of radar support are discussed New York, Society of Automotive Engineers, Inc.. 1971, p. 5-8. 17 giving attention to difficulties in landing aircraft not equipped with a refs. transponder. G.R. Research regarding the effect of the sonic boom on humans is discussed taking into account physiological and behavioral effects. Work concerned with calculating and measuring the loudness of A71-21 768 Aeronautical electronics for pilots of gliders pressure transients is considered. Investigations regarding the effects and touring aircraft - Equipment for the 1971 season. II (Luftfahrt- of the sonic boom on structures are reported giving attention to Elektronik fiir Segel- und Reiseflieger - Das Angebot fiir die Saison theoretical studies and the use of simulators. It is pointed out that 1971. 11). Hans Helmut Mogling. Deuscher Aerokurier, vol. 15, Feb. the Concorde’s present overflights are accompanied by an extensive 1971, p. 72-74. In German. research program to assess the effects of the boom on cathedrals, Advantages and disadvantages of ADF are examined, and a greenhouses, museum specimens, apartment buildings, homes, cliffs, number of devices available in this field are described taking into and humans and animals. G.R. consideration equipment at prices from about $800 up to about $3000. Radio equipment not absolutely necessary for visual flight but nevertheless providing valuable navigational aid is considered. A71-21 81 3 Noise reduction operational procedures. John The merits of transponders are evaluated, and a number of 0. Powers (FAA, Washington, D.C.) and T. P. Ball (Air Transport transponder models with their prices are listed. Distance measuring Association of America, Washington, D.C.). In: Society of Auto- equipment available is reviewed, and computers for general aviation motive Engineers and US. Department of Transportation, Con- are discussed. G.R. ference on Aircraft and the Environment, Washington, D.C., February 810, 1971, Proceedings. Part 1. New York, Society of Automotive Engineers, Inc., 1971, p. 9-14. Takeoff procedures are examined. It is found that in general a A71-21769 Motor glider with Wankel engine - K8B/KM two segment climbout by transport airplanes can best serve noise 914, SF-24/KM 29 (Motorsegler mit Wankel-Motor . K8BlKM 914, abatement requirements consistent with acceptable safety margins. SF-24/KM 29). Deutscher Aerokurier, vol. 15, Feb. 1971, p. 88,89. Modifications in approach procedures for the purposes of noise In German. abatement are investigated. An increase in the glide slope by The present state of development of the project K8B/KM 914 is approximately one-half a degree is recommended. The use of reviewed. The objective of tests presently conducted is to demon- preferential runway systems is discussed. It is pointed out that the strate that the Wankel engine is suitable for the propulsion of motor implementation of a 3,000-foot glide slope intercept within the gliders which can take off under their own power. Design data and terminal control area could improve the acoustic impact during final flight characteristics of the present model are presented. Another approach. G.R.

213 A71 -21814

A71-21814 Aircraft noise, its source and reduction. R E occasioned by daily operations. Emphasis is also made with respect Russell (Boeing Co Seattle, Wash ) and J D Kester (United Aircraft to the hours of duration of such noise experience and the times of Corp, Pratt and Whitney Aircraft Div , East Hartford, Conn ) In the day. Officials concerned with airport operations and runway Society of Automotive Engineers and U S Department of Trans usage will have to cope with the problem of community reaction portation, Conference on Aircraft and the Environment. Washington, until such time when technical results reduce public reaction. Interim D C , February 8 10, 1971, Proceed,ngs Part 1 alleviation of the problem is discussed with respect to reduced long New York Society of Automotive Engineers. lnc , 1971, p 1531 time runway usage. (Author) The evolution of subsonic jet engine noise reduction effoits is traced taking into account early turbolets and turbofan engines Problems encountered with jet suppressors are examined. and noise charactei istics of turbojet aircraft at thiee locations are investigatr,d A71-21820 Gas turbine engine emission characteristics and Aspects of fan noise suppression technology are explored giving future outlook C W Bristol, Jr (United Aircraft Corp , Pratt and attention to obtaindble community benefits Design questions foi Whitney Aircraft Div, East Hartford, Conn I In Society of high bypass ratio engines in connection with noise minimization are Automotive Engineers and U S Department of Transportation, discussed Aspects involved in coping with the noise problem of Conference on Aircraft and the Environment, Washington, D c, existing aircrdft are considered taking into account a nacelle retrofit February 8 10 1971, Proceedings Part 1 New tchedule and noise reduction throuyh flight proceduies GR York, Society of Automotire Engineers Inc , 1971, P 84 92 Some of the characteristics of both the visible and invisible exhaust emissions from aircraft gas turbines are discussed Data IS presented for some of the cuirently used commercial engines A71 -2181 5 Aircraft and the environment . Airlines/ Possible means for reducing levels of some of the pollutants are community. William B. Becker (Air Transport Association of indicated Gas turbine emission characteristics are compared with America, Washington, D.C.). In: Society of Automotive Engineers those of automotive reciprocating engines (Author) and U.S. Department of Transportation, Conference on Aircraft and the Environment, Washington, D.C.. February 8-10, 1971, Proceed. ings. Part 1. New York, Society of Automotive Engineers, Inc.. 1971, p. 35-41. Three approaches to jet noise abatement are considered in- A7121821 The United States SST and air quality. John volving the reduction of noise at the source, adjustments in method M. Swihart (Boeing Co., Seattle, Wash.). In: Society of Automotive of flight, and compatible land use around airports. Alterations of Engineers and U.S. Department of Transportation. Conference on takeoff profiles undertaken for the sole purpose of reducing noise on Aircraft and the Environment, Washington, D.C., February 8-10. the ground are described, and the use of preferential runways and the 1971, Proceedings. Part 1. New York. Society of establishment of aircraft tracks over the ground are discussed. The -Automotive Engineers, Inc., 1971, p. 93-102. 19 refs. advances made by the airlines in reducing the total amount of The contribution of all turbine-powered aircraft to world pollution created per aircraft engine are examined. Some details are pollution is shown to be something less than one percent of the total presented concerning the origin and the characteristics of the tonnage of pollution generated in the energy conversion processes of pollution produced by aircraft. G.R. the world. The natural forces which may affect the global climate are briefly examined, and a brief description of the ambient conditions in which the SST fleet will operate is given. An overview of calculations made regarding the principal exhaust products of the A71 -2181 8 Land use strategies for aircraft noise allevia- SST fleet is presented. Alleged climatic modification affects of these tion. Richard H. Broun and James F. Miller (U.S. Department of substances are investigated. It is found that there is no basis to Housing and Urban Development, Washington, D.C.). In: Society of predict that the operation of a fleet of SST’s will significantly affect Automotive Engineers and US. Department of Transportation, the weather or climate. G.R. Conference on Aircraft and the Environment, Washington, D.C., February 8-10, 1971, Proceedings. Part 1. iNew York, Society of Automotive Engineers, Inc., 1971, p. 64-74. A71-21822 Water vapor pollution of the upper atmo- Legislative action resulting from an increased concern with sphere by aircraft. Lester Machta (National Oceanic and Atmospheric environmental quality is considered. A number of basic questions in Administration, Washington, D.C.). In: Society of Automotive connection with a series of metropolitan aircraft noise abatement Engineers and U.S. Department of Transportation, Conference on policy studies are discussed. These studies indicate that land use Aircraft and the Environment. Washington, D.C., February 8-10, strategies must take into account the necessity of solving the very New York, Society of serious noise problem in communities that already exist around 1971, Proceedings. Part 1. many airports, and the necessity of preventing the same situation Automotive Engineers, Inc., 1971, p. 107-120. 12 refs. from developing around other airports. Major findings and con- Residence times of atmospheric carbon dioxide and water vapor clusions from the Boston International Airport study are examined. are examined, and present and future emissions of these two G.R. substances from aviation activities are considered. The question whether the water vapor from future enlarged subsonic aircraft could produce a cirrus veil over large areas of the earth is discussed. Observed changes in high tropospheric cloudiness are examined. The A71 -2181 9 Appraisal of community response to aircraft distribution of water vapor emitted by the SST in the stratosphere is noise - At the grass roots level. Martin Gach (FAA, Washington, investigated, and the observed variability of water vapor is examined. D.C.). In: Society of Automotive Engineers and US. Department of Relations between water vapor and ozone concentration and Transportation, Conference on Aircraft and the Environment, between water vapor and stratospheric cloudiness are explored. The Washington. D.C, February 8-10. 1971, Proceedings. Part 1. role of water vapor in the stratosphere regarding the radiation New York, Society of Automotive Engineers, Inc., balance is discussed giving attention to the possible significance of SST emissions. G.R. 1971, p. 75-83. The study provides an appraisal of some of the problems that have developed as the result of the effect of aircraft overflight on neighboring communities. and from the resultant noise emissions. Specific emphasis is placed on the short-term problem and the A7121823 Air pollution at Heathrow Airport, London . reaction of individuals or community leaders to the noise experience April-September, 1970. J. Parker (Board of Trade, Warren Spring

214 A71 -21830

Laboratory, Stevenage. Herts., England). In: Society of Automotive future could be made very much quieter than those then in service. Engineers and U.S. Department of Transportation, Conference on In order to take full advantage of acoustic technological capability Aircraft and the Environment, Washington, D.C.. February 810. compulsory standards of quietness are called for. It is pointed out 1971, Proceedings. Part 1. ! New York, Society of that unless such standards for aircraft are developed on an Automotive Engineers, Inc., 1971, p. 121-146. 8 refs. international basis serious commercial discrimination between Calculations have been made of total pollution emissions at different manufacturers and airlines could result. Approaches taken Heathrow Airport, London, from aircraft operations, heating installa- to tackle the noise-at-source problem internationally are discussed tions and road traffic. Comparisons were made of concentrations of giving attention to future work required. G.R. pollution levels from the airport and from nearby residential areas. Measurements of smoke sulphur dioxide, oxides of nitrogen, carbon monoxide. total hydrocarbons and deposited matter were also carried out in different parts of the airport. The results showed that A71 -21827 The federal regulation of aircraft noise. the airport was not contributing unduly to local pollution. At no Ronald W. Pulling (FAA, Washington, D.C.). In: Society of Auto- time did pollution concentrations at the airport ever exceed values motive Engineers and US. Department of Transportation, Con- which have been found in central London. The highest values ference on Aircraft and the Environment, Washington, D.C., February 8-10, 1971, Proceedings. Part 1. New obtained came from road traffic in the Central Area. (Author) York. Society of Automotive Engineers, Inc., 1971, p. 176-182. 11 refs. Review of federal regulatory activities in the area of aircraft A71 -21824 Dispersion modeling of airport pollution. N. noise. The evolution of more and bigger aircraft, increased operation, Milford, G. C. McCoyd, L Aronowitz. and J. H.Scanlon (Grumman and urbanization of airport environs have attracted attention to the Aerospace Corp., Bethpage, N.Y.). In: Society of Automotive social and physical annoyance of aircraft noise. The elements and Engineers and US. Department of Transportation, Conference on participants in the noise problem are identified, and the historical Aircraft and the Environment, Washington, D.C., February 8-10, background leading to the enactment of federal legislation support- 1971, Proceedings. Part 1. New York. Society of ing FAA regulatory activities is presented. The scope and status of Automotive Engineers, Inc., 1971, p. 147-162. 19 refs. FAA regulations, and the constraints and alternatives affecting an This paper describes the procedures followed in developing and ultimate solution of the problem are discussed. F.R.L. validating computer models of air pollution caused by airports. Such dispersion models are used to calculate how the pollution emitted from the many contributing scurccs spread; to affect surrounding A71-21828 The legal role of states, local governments and areas. This simulation perm!ts ?. reaIis?ic eva!uatim of possible airport proprietors in regulating aircraft noise. Warren Christopher alternative strategies for air pollution abatement. The basic elements (O'Melveny and Myers). In: Society of Automotive Engineers and of a modeling problem are seen to be the emission sources, the US. Department of Transportation. Conference on Aircraft and the meteorology, and the dispersion parameters; current methods for Environment, Washington, D.C.. February 8-10, 1971, Proceedings. handling each of these are explained. The treatment of a sample Part 1. New York, Society of Automotive airport is described and typical results are presented. Finally. the Engineers, Inc., 1971, p. 183-188. paper indicates some of the areas in which limited knowledge affects Discussion of the power of state and local governments to the implementation or accuracy of airport dispersion modeling. control aircraft noise at airports not owned or operated by the (Author) governmental entity making the regulation. It is concidwed that, oecause of the pervasive federal control over the navigable airspace, local attempts to establish minimum altitudes of flight, maximum A71-21825 The role of state government in aircraft noise noise levels, or night curfews have generally been held to be abatement regulation. Joseph R. Crotti (California Department of unenforceable. Attention is given to the unsettled question of the Aeronautics, Business and Transportation Agency, Calif.). In: power of the proprietor of an airport to make and enforce Society of Automotive Engineers and US. Department of Trans regulations with respect to the control of aircraft noise. Various legal portation, Conference on Aircraft and the Environment, Washington, actions brought by interested parties are cited and evaluated. F.R.L. D.C., February 810. 1971. Proceedings. Part 1. New York, Society of Automotive Engineers, Inc., 1971. p. 163-169. 9 refs. A71 -21829 Federal regulation of aircraft noise, the legal It is pointed out that California is the first state in the nation to rights of airport neighbors, and legal aspects of compatible land use. undertake the development of noise regulations for airports. The Lyman M. Tondel. Jr. (Cleary, Gottlieb, Steen, and Hamilton). In: reason for this development is the lack of federal regulations in this Society of Automotive Engineers and U. S. Department of Trans- area. The necessity of noise regulations in a competitive economy for portation, Conference on Aircraft and the Environment, Washington, the reduction of aircraft noise is shown. Legislative aspects are D.C., February 810, 1971, Proceedings. Part 1. f examined, and the more important elements of the airport noise New York, Society of Automotive Engineers, Inc., 1971. p. 189-204. problem are analyzed. Questions of definitions of noise, noise 117 refs. exposure level, community noise equivalent level, maximum ac- Discussion of various aspects of the aircraft noise problem, ceptable noise level, the determination of noise impact area, and which has increased in magnitude over the past few years, owing to compatible land use and quieter aircraft are among the subjects the increased public need for air transport. Extensive efforts to discussed. Approaches for solving the noise problem, the requirement control noise by design, flight pattern arrangement, and modified for noise monitoring systems, and the time required to achieve noise operational procedures have only been partially successful. The most reduction are considered. G.R. significant developments in the realm of Federal legislation and regulation since 1965 are summarized, and the most significant court cases in the last five years are reviewed. Attention is given to the A71 -21826 International regulation of aircraft noise. B. W. largely unsuccessful efforts to obtain injunctions in airport noise Meynell (British Embassy. Washington, D.C.). In: Society of Auto- cases. Some of the reasons why land use planning has not been motive Engineers and U.S. Department of Transportation, Con- effective in most places are discussed, and some possible means of ference on Aircraft and the Environment, Washington, D.C.. improving the legal framework for such planning are suggested. February 810, 1971, Proceedings. Part 1. New F.R.L. York, Society of Automotive Engineers, Inc.. 1971, p. 190-175. The London conference at the end of 1966 concluded that there A71 -21830 Legal aspects of military sonic booms. William were sound reasons to expect that civil transport aircraft of the F. McCormack (USAF. Office of the Judge Advocate General,

21 5 A71 -21831

Washington, D.C.). In: Society of Automotive Engineers and US. taken into account in the construction or further development of Department of Transportation, Conference on Aircraft and the airport facilities to prevent unnecessary conflicts between airports Environment, Washington, D.C., February 8-10, 1971, Proceedings. and their neighbors. A thorough consideration of environmental Part 1. New York, Society of Automotive factors is now required by three Federal statutes . i.e.. the Airport- Engineers, Inc., 1971, p. 205-217. l00refs. and Airway Development Act of 1970, the Department of Trans- Attempt to show some of the legal developments which have portation Act of 1966, and the National Environmental Policy Act resulted from military supersonic flight. The law has developed to of 1969. The role of the Assistant Secretary for Environment and meet the new challenges, and old rules of liability have been Urban Systems in the Department of Transportation, who has the modified to meet the changed conditions. The sonic boom and the ultimate responsibility for ensuring that these legislative require- effects of high overpressure sonic booms are described. Administra- ments are fully understood and incorporated into the approval tive remedies, remedies under the Federal Tort Claims Act (FTCA), process, is discussed. O.H. discretionary function defense under FTCA, absolute liability under FTCA, liability under FTCA based on negligent or wrongful conduct, and liability for trespass and nuisance are discussed. Attention is A71-21835 Environmental aspects of airport systems given to Tucker Act cases and remedies in state courts. A large number of cases and their dispositions are reviewed. F.R.L. planning. H. C. Lamberton, Jr. (Howard, Needles, Tammen and Bergendoff, New York, N.Y.). In: Society of Automotive Engineers and U.S. Department of Transportation, Conference on Aircraft and the Environment, Washington, D.C., February 8-10, 1971, Proceed- A71-21831 Role of NAPCA in controlling aircraft ings. Part 1. New York, Society of Automotive pollutant emissions. George D. Kittredge and Barry D. McNutt Engineers, Inc., 1971, p. 245-260. (National Air Pollution Control Administration, Div. of Motor Discussion of airport system planning for environmental com- Vehicle Research and Development, Washington, D.C.). In: Society patibility. The requirements of and constraints upon airport system of Automotive Engineers and US. Department of Transportation, planning are reviewed in terms of the planning time frame, Conference on Aircraft and the Environment, Washington. D.C.. forecasting base, location and use of airports, meteorological effects, February 8-10, 1971, Proceedings. Part 1. New number of airports and runways, size of aircraft, and measures to York, Society of Automotive Engiqeers. Inc., 1971, p. 218-227. 9 increase airport capacity. The impact of airport system planning on refs. the preservation of natural and urban environment is examined in Discussion of some general results of a program initiated in 1967 detail. Several methods of both technical and institutional nature for by the National Air Pollution Control Administration (NAPCA) on effecting airport environmental compatibility are proposed and the characterization and control of emissions from aircraft opera- discussed. O.H. tions. The program, which is being carried out through contract research and cooperative government/industry studies, covers the measurement of emissions, development of testing instrumentation and procedures. and basic research in emission control technology. ~71.21836 Strategies of noise abatement through land Based on the results of this program obtained so far, characteristics use. Richard B. Ross (Market Facts, Inc.). In: Society of Automotive of emissions from aircraft are presented and it is shown how they can Engineers and U.S. Department of Transportation, Conference on be identified in a quantitative fashion suitable for predicting their Aircraft and the Environment, Washington, D.C., February 8-10, contribution to total community air quality. A brief description of 1971, Proceedings. Part 1. New York, Society of NAPCA’s plans for future research is also included. Finally, a Automotive Engineers, Inc., 1971, p. 261-266. discussion of possible emission control techniques and regulatory Discussion of land development control as an effective approach considerations which will affect future standard setting, is presented. to aircraft noise abatement. It is shown that because it is very O.H. unlikely that aircraft noise will be eliminated or reduced to a manageable level by technological improvements, land use strategies which substitute nonnoise sensitive uses foi- very sensitive uses in A71-21832 The current and future basis for aircraft air high noise exposure zones are necessary. The land development pollution control, William T. Westfield (FAA, Washington, D.C.). In: problem is significantly different at existing and at new airports so Society of Automotive Engineers and US. Department of Trans- that different noise abatement strategies must be applied. Some of portation, Conference on Aircraft and the Environment, Washington, these strategies are proposed and discussed. It is emphasized, D.C., February 8.10. 1971, Proceedings. Part 1. however, that all strategies have limitations and potential adverse New York, Society of Automotive Engineers, Inc., 1971, p. 228-233. effects on community goals other than noise reduction. Implementa. 8 refs. tion of any of the strategies is complex, requiring compromises Description of efforts to develop an efficient regulatory tool for among competing groups and community goals. O.H. assessment of aircraft smoke emissions. The present basis, the Ringelmann Smoke Chart, is described and some of the shortcomings associated with its use for aircraft are discussed. Research and development approaches devised so far in an attempt to improve this A71-21837 Comprehensive planning and aircraft noise at system are characterized. The gaseous pollutants, their relative Kansas City International Airport. John L. Taylor and Robert A. importance in an airport area, and the research underway or needed Kipp. In: Society of Automotive Engineers and U.S. Department of are discussed. O.H. Transportation, Conference on Aircraft and the Environment, Washington, D.C.. February 8-10, 1971, Proceedings Part 1. New York, Society of Automotive Engineers, Inc., 197 1, p. 287-293. A71 -21834 An environmental approach to air trans- Description of a new planning program for guidance of private portation needs . Guidelines for federal assistance. Martin Convisser land development and for the provision of transportation undertaken (U.S. Department of Transportation, Office of Environment and by the city of Kansas City, Mo.. in the vicinity of Kansas City Urban Systems, Washington, D.C.). In: Society of Automotive International Airport. The airport is an entirely new public trans- Engineers and U.S. Department of Transportation, Conference on portation facility now in the final construction stages and expected Aircraft and the Environment, Washington, D.C., February 8-10. to be operational by 1972. The development guidance system is 197 1, Proceedings. Part 1. , New York, Society of designed to take account of environmental noise utilizing FAA noise Automotive Engineers, Inc.. 197 1, p. 240-244. exposure forecasts in conjunction with land use control zones. O.H. Discussion of the various environmental aspects which must be

216 A7 1-21986 i A7121863 a Use of unsteady analogy in constructing generatrix. Ihe properttes of This shock wave in a plane ideal gas flow hypersonic flows past blunt bodies (0 primenenii nestatsionarnoi are ascertained. The case of a small supersonic incident flow velocity analogii pri postroenii giperzvukovykh techenii okolo zatuplennykh is investigated, when variations in entropy behind the shock wave tell. M. N. Kogan and V. V. Mikhailov. Prikladnaia Matematika i may be neglected. In this case it is found possible to employ a Mekhanika, vol. 34. Nov.-Dec. 1970, p. 1053-1057. 10 refs. In transonic approximation of the shock polar and of the characteristics Russian. intersecting it. The study is carried out with the aid of a mapping of Construction of a class of unsteady flows to which direct the region behind the shock wave with a Cartesian coordinate system application of unsteady analogy can be made when calculating into the plane of the velocity hodograph. A.B.K. hypersonic flow past a blunt body in a region far from the blunt part of the body. The basic idea of the method employed for this purpose is that the entropy corrections are not introduced into the flowfield A71-21922 ii Heat exchange and frictional drag during or the body configuration. but into the head wave configuration as turbulent flow of air with equilibrium ionization and dissociation determined by unsteady analogy. The shape of this shock wave is around a plate [Teplootdacha i soprotivlenie pri turbulentnom determined from the condition that the fields of the steady and obtekanii plastiny ravnovesno dissotsiirovannym i ionizirovannym unsteady solutions must totally coincide, while the body configura- vozdukhom). V. N. Popov (Moskovskii Energeticheskii lnstitut, tion corresponds to the trajectory of a particle of an unsteady flow Moscow, USSR). Teplofizika Vysokikh Temperatur, vol. 8, Nov: with an entropy equal to the entropy behind a normal shock wave. Dec. 1970, p. 1209-1217. 17 refs. In Russian. Calculation of the heat exchange and frictional drag during A.B.K. stationary longitudinal turbulent flow of dissociated and ionized air around a plate. It is assumed that the plate surface temperature and the temperature of the incident flow are constant. Equilibrium A71-21864 + Singular current surfaces in conical gas flows dissociation and ionization are also assumed - Le.. the mixture (Osobye poverkhnosti toka v konicheskikh techeniiakh gaza). A. I. composition at each point in the boundary layer is the same as that Golubinskii. Prikladnaia Matematika i Mekhanika, vol. 34, Nov.-Dec. under conditions of thermodynamic equilibrium. The effects of mass 1970, p. 1058-1066. 8 refs. In Russian. forces, dissipation, and radiation are negligibly small. Calculations are Consideration of the field of a conical perfect gas flow in the made for pressures of 1 and 10 atm and plate surface temperatures of vicinity of conical current surfaces. It is shown that, in addition to 500, 2000, and 3000 deg K. The incident flow temperature is varied ordinary (regular) current surfaces, which are constant-entropy between 2000 and 30.000 deg K, aid the Reynolds number is varied surfaces (isen?ropes!, singular cgrrent surfaces with a distributed from 24OG to 2.4 billion. T.M. variable entropy may exist on the ordinary surfaces. These singular surfaces are the envelopes of the flowfield isentropes and may be continuously joined with regular surfaces provided that the flowfield remains continuous both in the vicinity of the singular current A71-21925 # Position of the closing shock in a supersonic surface and in the vicinity of the junction. The results obtained lead underexpanded two-phase jet (Polozhenie zamykaiushchego skachka to the assumption that the flow pattern of an asymmetrical flow past v sverkhzvukovoi nedorasshirennoi dvukhfaznoi strue). L. Napolitano, Monti (Napoli, Universiti, Naples, Italy), and G. V. conical bodies has a continuous and single-valueddistribution of the R. gasdynamic parameters in the flowfield without any singular points. Tsiklauri (Moskovskii Energeticheskii Institut. Moscow, USSR 1. A.B.K. Teplofizika Vysokikh Temperatur, vol. 8. Nov.-Dec. 1970, p. 1235-1243. 9 reis. In Russian. An experimental investigation is described in which the position of the closing shock in single-phase and two-phase jets was studied in A71-21865 $ Designing a supersonic nozzle contour with a wind tunnel, using air and water vapor as the working medium. The allowance for changes in the flight conditions of a flight vehicle (0 influence of the concentration of the liquid phase on the Mach postroenii kontura sverkhzvukovogo sopla s uchetom izmeneniia number and the pressure at the nozzle exit section is determined. It uslovii poleta letatel'nogo apparata). A. N. Kraiko and A. A. Osipov. is shown that two-phase jets are characterized by a nonuniform Prikladnaia Matematika i Mekhanika. vol. 34, Nov.-Dec. 1970, p. velocity and concentration profile. In two-phase jets, the Mach 1067-1075. 11 refs. In Russian. number at the nozzle exit section in the gas phase decreases, owing Consideration of the problem of designing a rigid (unadjustable) to the mechanical work performed by the gas to accelerate the contour for the supersonic part of a nozzle which is optimal in the droplets and also to the friction losses at the particles. The ratio of sense of solving a certain trajectory problem with allowance for active to passive pressure increases due to phase slipping. V.P. changes in the flight conditions and the operating mode of the engine. The flight vehicle in this case is assumed to be a material point of variable mass, while its drag at a given moment is regarded as A71-21982 ii The NOL Hypervelocity Wind Tunnel. W. J. equal to the corresponding steady value. In addition to obtaining Glowacki, E. L. Harris, R. K. Lobb. and M. I. Schlesinger (US. Navy, general results, a detailed study is made of two cases where the Naval Ordnance Laboratory, Silver Spring, Md.). American institute solution of the problem using the optimality conditions obtained of Aeronautics and Astronautics, Aerodynamic Testing Conference, turns Out to be comparatively simple. The first case occurs if the 6th. Albuquerque, N. Mex., Mar. 10-12. 1971, Paper 71-253.14 p. 9 Mach number distribution at the nozzle inlet does not vary during refs. Members, $1.50; nonmembers, S2.00. the flight time. It is established that in this case the optimal contour The NOL Hypervelocity Wind Tunnel will provide a high belongs to a family of contours corresponding to the solution of a Reynolds number turbulent flow simulation in the Mach number variational problem with fixed conditions. The second case occurs if range 10 to 20. This facility, much needed for large-scale testing of the flow at the nozzle inlet remains uniform and supersonic during hypersonic vehicles, will be operational in late 1972. The tunnel is a the entire flight time, while the nozzle is plane and 'short.' In this blowdown type, utilizing high-pressure nitrogen as the test gas. case the generatrix of the optimal nozzle IS rectilinear. A.B.K. Supply pressures up to 40,000 psi will be maintained constant for 1 to 4 seconds during which stable, condensation-free flow conditions will prevail. This paper will highlight the gasdynamic and mechanical A71-21872 i? Formation of a hanging shock wave during design of the major components of the facility. In addition, a flow past a profile with a broken generatrix (Obrazovanie 'visiachego' comparison will be given between the tunnel operating conditions skachka uplotneniia pri obtekanii profilia s izlomom obrazuiushchei). and those required for simulating free flight. (Author) E. G. Shifrin. Prikladnaia Matematika i Mekhanika, vol. 34, Nov: Dec. 1970, p. 1159.1 167. 7 refs. In Russian. Analytical demonstration that a hanging shock wave arises A71-21986 fi Methane-air combustion gases as an aero- during uniform supersonic flow past a profile with a broken dynamic test medium. R. R. Howell and L. R. Hunt (NASA, Langley

217 A71-21990

Research Center, Hampton, Va.). American Institute ofAeronautics Theoretical and experimental tests on a 0.10 scale C-l30STOL and Astronautics, Aerodynamic Testing Conference, 6th, Albuquer- model, over a fixed ground plane, allowed a close examination both que, N. Mex., Mar. 10-12, 1971, Paper 71-258. 11 p. 31 refs. of ground-boundary-layer effects and other aspects of such high-lift Members, $1.50; nonmembers, $2.00. testing. Excellent experimental/theoretical agreement is demon- The present paper gives a review of the major problems strated for both ground pressures (vortex-lattice techniques) and associated with the use of hydrocarbon-air combustion gases as an boundary layer characteristics. Detailed prediction of ground aerodynamic test medium. Condensation of water vapor IS identified boundary layers is shown to be feasible, and retrospective allowances as the major problem, and actual experience is offered as evidence of for displacement effects may even be possible for the milder cases. its effects on aerodynamic flow parameters. Aerodynamic data Other aspects discussed include flow-breakdown criteria, contraction- obtained from tests in methane-air combustion gases are compared lag effects, strut-fairing interference and circulation around 'flow- with theory and with data obtained on the same shapes in other test over-both-sides' ground planes. (Author) facilities using other test media. The comparisons indicate that data obtained in combustion gas compare well with data obtained in other test media. (Author) A71-21993 # An evaluation of single and multiple sting support methods to obtain unmodified interference-free wind tunnel data. D. G. Hammond and C. Wilkerson, Jr. (General Dynamics A71-21990 Supersonic aerodynamic and wake character- # Corp., Convair Aerospace Div.. Fort Worth, Tex.). American istics of large-angle cones at low Reynolds numbers including effects Institute of Aeronautics and Astronautics, Aerodynamic Testing of model support. Melvin M. Carmel and Clarence A. Brown, Jr. Conference, 6th, Albuquerque, N. Mex., Mar. 10-12, 1971, Paper (NASA, Langley Research Center, Hampton, Va.). American 71-267. 10 p. Members, $1.50; nonmembers, $2.00. Institute of Aeronautics and Astronautics, Aerodynamic Testing Wind tunnel tests of a conventional force model were conducted Conference, 6th, Albuquerque, N. Mex., Mar. 10-12, 1971, Paper 71-264. 12 p. Members, $1.50; nonmembers. $2 00. in which the 'Image Sting' method of support was used in an attempt Experimental demonstration of the effects of sting diameter and to obtain corrections that could be applied to data to eliminate Reynolds number variation in the low range on the aerodynamic aerodynamic interference effects caused by the model single-sting support system. The tests were conducted over a Mach number range characteristics of a 140 deg cone at M = 1 5 and 2.0. The effects of of 0.85 to 2.20 in the General Dynamics High-speed Wind Tunnel. support interference on the wake of a 120 deg cone at M = 1.6 is also presented. The results indicate no appreciable effect of sting The test results for several single support and multiple-support sting diameter or Reynolds number on the cone aerodynamic character- arrangements are compared with the Image Sting results as a means istics other than an increase in the apial force coefficient with sting of evaluating this method of support. The Image Sting demonstrated diameters greater than about 0.3 of the ratio of sting diameter to its acceptability as a means of determining interference free wind cone diameter Also, asymmetiy of the support system for blunt tunnel model data. A single sting method that provides test data in cones may lrad to significant tirror in wake results (Author) close agreement with the Image Sting data levels was also determined. (Author)

A71-21991 fi Comparisons between sting-supported and A71-21994 fi A new wind tunnel technique for providing free-flight tests in the JPL Hypersonic Wind Tunnel on a modified simulation of flight base flow. J. C. Y. Koh (Boeing Co., Seattle. Saturn-Apollo launch configuration. Bain Dayman. Jr. (California Wash.). American Institute of Aeronautics and Astronautics, Aero- Institute of Technology, Jet Propulsion Laboratory, Pasadena, dyf?amic Testing Conference, 6th. Albuquerque, N. Mex., Mar. Calif .). American Institute of Aeronautics and Astronautics, Aero- 10-12. 1971, Paper 71-268.6 p. Members, $1.50; nonmembers. dynamic Testing Conference, 6th. Albuquerque, N. Mex., Mar. $2.00. IO 12, 1971, Paper 71-265. 12 p. 6 refs. Members, $1.50; non~ The dimensionless base pressure of a body in subsonic and members, $2 00. supersonic flows is shown to be governed by the Mach number and Trajectories predicted from sting-supported internal-balance the dimensionless boundary layer thickness. An experimental tech- model tests conducted in the Jet Propulsion Laboratory (JPL) nique is described whereby in wind tunnel tests a base pressure 21-inch Hypersonic Wind Tunnel IHWT) were compared with model is attached to a long cylindrical body extended and supported trajectories of free flight model tests on a modified Saturn-Apollo far upstream so that there is no interference in the neighborhood of launch configuration run in the JPL HWT. They were also compared the base. The boundary layer thickness is controlled by suction with tests run in the US. Naval Ordnance Laboratory (NOL) upstream of the base. Results of experiments with bluff cylinder Pressurized Ballistics Range No. 3 (PBR3). The purpose of this test bases have successfully demonstrated the validity of this technique. program was to determine, under controlled and ideal conditions, (Author) just how closely 'static' data can compare with 'flight' data. In spite of the extremely complex flow field over the model (the characteristics, attached vs separated flow, were a strong function of Mach and Reynolds numbers, ratio of model wall temperature to flow A71.21995 # A wind tunnel simulation of rocketllauncher temperature, and angle of attack) the comparisons with the interference effects. Raymond R. Maestri and Chris A. Kalivretenos sting-supported model tests were generally within 5% in drag and 2% (US. Navy, Naval Ordnance Laboratory. Silver Spring, Md.). of model diametei in center of pressure location for the wind tunnel American Institute of Aeronautics and Astronautics, Aerodynamic free-flight trajectories and were within 5% and 7%. respectively, for Testing Conference, 6th, Albuquerque, N. Mex., Mar. 10-12, 1977, the ballistics range trdjectoi ies. Pitch damping determined from the Paper 71-269. 12 p. Members, $1.50; nonmembers, $2.00. wind tunnel and ballistics raiiye free flight trajector+esalso compared Investigation of the effect of the aerodynamic interaction quite favorably. (Author) between the rocket, the rocket exhaust, the launch pod, and the free stream on the ballistic dispersion of an unguided, air-launched rocket. The aerodynamic interaction phenomenon was simulated in the Naval Ordnance Laboratory Supersonic Wind Tunnel No. 1. A71-21992 ii The aerodynamics of a fixed ground plane for Conditions simulated were a launch aircraft Mach number of 0.6 and a powered STOL wind-tunnel model. J. E. Hackett and J. L. Justice rocket exhaust let pressure to ambient pressure ratios from zero to (Lockheed Georgia Co.. Marietta, Ga.). American lnstitute of Aero- six. High-pressure air was used to simulate the rocket exhaust gas in nautics and Astronautics, Aerodynamic Testing Conference, 6th. most tests; however, in some tests high-pressure helium was used in Albuquerque, Mex., Mar. 10-12. 1971, Paper 71-266. 11 p. 10 N. order to measure the effect of exhaust gas density and speed of refs. Members, $1 50;nonmembers, $2.00. sound. Rocket forces and moments were measured at rocket

218 A7 1-22006

I positions starting within the launch tube until the aft end ot the N. Mex., Mar. 10-12, 1971. Paper 71-277. 12 p. 23 refs. Members, rocket was eight calibers in front of the launcher. The force and $1.50; nonmembers, $2.00. Contract No. NAS 1-6450. moment data were reduced to interference coefficients which were Available experimental results are reviewed and organized to then used to calculate rocket dispersion. Approximately eight mils of provide a logical explanation of aerodynamic support interference f dispersion were found to result from this aerodynamic interaction for dynamic wind tunnel testing. Configurations involving bulbous effect. The greatest part of the dispersion was found to occur before bases, mass addition, boundary layer transition near the base, and the rocket was completely out of the launch tube. O.H. hypersonic low density flows are shown to be particularly sensitive to sting interference effects. Transverse rod support interference I occurs at all Mach numbers depending on oscillation amplitude I andlor trim angle of attack. The postulated flow model predicts that A71-21996 # Static pressure port errors in hypersonic tur- cylindrical and flared stings will have opposite interference effects in I bulent flow. D. E. Nestler (General Electric Co., Re-Entry and agreement with experimental observations. An analytical method of Environmental Systems Div., Philadelphia, Pa.). American lnsritute correcting the wind tunnel results for dynamic support interference of Aeronautics and Astronautics, Aerodynamic Testing Conference, is proposed. (Author) 6th. Albuquerque, N. Mex., Mar. 10.12, 1971, Paper 71-270. 9 p. 26 refs. Members, $1.50; nonmembers, $2.00. The use of a static pressure port is known to cause local flow disturbances which may affect the pressure being measured. In this A71-22003 # Wind-tunnel free-flight testing of mnfigura- paper, several hypersonic pressure measurements for cones are tions with high-fineness ratio bodies. John E. Holmes and Frederick compared with theory. A consistent positive error is noted, as in A. Woehr (U.S. Navy, Naval Ordnance Laboratory, Silver Spring, I previous subsonic and supersonic studies. An approximate shear layer Md.). American lnstitute of Aeronautin and Astronautics, AWO- i momentum balance is used to derive a simple relation for this static dynamic Testing Conference, 6m, Albuquerque, N. Mex., Mar. pressure increase. Due to inconsistencies in correlation of the 1012, 1971, Paper 71-278. 12 p. Members, $1.50; nonmembers. experimental static pressure error with theoretical steady flow $2.00. parameters, it is concluded that unsteady effects such as turbulent The launch and data-reduction techniques used in supersonic I fluctuations may also be present. (Author) wind-tunnel free-flight testing are described. Included are descriptions of the launcher and launch head designs used with fin-stabilized, high-fineness ratio (up to 40) bodies. At the lower initial angles of attack, up to approximateiy 15 degrees, the models I A71-22000 ,; A nonlinear aerodynamic moment formulation were spun prior to iaunch. The high angie-of-attack iaunches, up lo I and its implications for dynamic stability testing. Murray Tobak and 90 degrees, were made with models having no initial spin. The Lewis B. Schiff (NASA. Ames Research Center, Moffett Field, method of differential corrections was used to fit the observed data t Calif .I, American Institute of Aeronautics and Astronautics, Aero- to the nonlinear second-order differential equations of motion for dynamic Testing Conference, 6th. Albuquerque, N. Mew., Mar. both three and six degrees of freedom. Results containing nonlinear 10-12, 1971, Paper 71-275. 8 p. 8 refs. Members, $1.50; non- forces and moments have been obtained for three-degree-of-freedom members, $2.00. flights with initial angles of attack of 40 degrees. Both the progress A nonlinear aerodynamic moment system. formulated in a and problems encountered in using the method of differential previous study to apply to arbitrary motions of bodies of revolution corrections in the development of free-flight testing are discussed. in free flight, is generalized to include nonaxisvmmetric bodies (e.9.. f Author) aircraft) within a uniform treatment. The total moment is shown to be compounded of the contributions from four simple motions and a clear physical meaning is attached to each contribution. Applied to A71-22004 8 Threedegree-of-freedom gas bearing for wind- aircraft motions, the formulation includes the nonlinear interactions tunnel dynamic measurements. Frank J. Regan and Eugene V. between motions that normally are excluded in the classical Horanoff (U.S. Navy, Naval Ordnance Laboratory, Silver Spring, treatment. The results may be useful in the design of experiments Md.). American Institute of Aeronautics and Astronautics, Aem- and the interpretation of results obtained therefrom. (Author) dynamic Testing Conference, 6th. Albuquerque, N. Mew., Mar. 10.12. 1971, Paper 71-279. 5 p. 8 refs. Members, $1.50; nonmembers, $2.00. A71-22001 # On dynamic stability testing of unconven- Supports used In the measurement of dynamic forces and tional configurations. K. J. Orlik-Rickemann, P. A. Adam, and J. G. moments in a wind tunnel often limit model motion to a single LaBerge (National Aeronautical Establishment, Ottawa, Canada). degree of freedom. NOL has relaxed this singledegree-of-freedom American Institute of Aeronautics and Astronautics, Aerodynamic restriction with the development of a threedegree-of-freedom gas Testing Conference, 6th, Albuquerque. N. Mex., Mar. 10-12. 1971, bearing which allows the model to spin, pitch and yaw simultaneous- Paper 71-276. 11 p. 5 refs. Members, $1.50; nonmembers, $2.00. ly. In the NOL design, the model is attached to the ball in a ball and Situations frequently occur when standard wind-tunnel test socket bearing. Lubricating gas (at present air1 is admitted through equipment, based on the concept of an all-containing rear-sting adjustable pads into the region between the ball and socket. Each support is impractical or even impossible to use. In this paper some pad is allowed to align itself to the center of the ball. Since each pad possible alternative test arrangements are indicated and descriptions has its own gas supply, the gas pressure to each pad can be adjusted are given of the actual experimental equipment and procedures. Full- independently to accommodate heavy models or models having high and half-model techniques are discussed and the experimental axial loads. A variety of digital and analog transducers for determin- procedures include free- and forcd-oscillation methods. Examples ing angular position and rate are under consideration. However, in contain cases such as cones at incidence and combinations of two the present discussion only photographic records are used. The pitch models in close proximity (space shuttle). at supersonic and damping of a blunted, slender cone has been measured using this gas hypersonic speeds. Comparisons of results obtained with different bearing in an NOL wind tunnel at a Mach number of 5. The methods and techniques are included. (Author) measurements have been reduced using the NOL free-flight data- reduction program and are presented in the form of the pitch- damping derivative. (Author)

A71-22002 # Dynamic support interference . Fact or fiction. J. Peter Reding and Lars E. Ericsson (Lockheed Missiles and Space Co., Sunnyvale, Calif.). American Institute of Aeronauticsand A71-22006 # Sonic-boom wind-tunnel testing techniques at Astronautics, Aerodynamic Testing Conference, 6th. Albuquerque, high Mach numbers.' Odell A. Morris and David S. Miller (NASA,

219 A71-22010

Langley Research Center, Hampton. Va.). American lnstitute of behaved like an open jet based on measurements of downwash and Aeronautics and Astronautics, Aerodynamic Testing Conference, streamline curvature correction factors; the slotted wall reduced the 6th. Albuquerque, N. Mex.. Mar. 10-12, 1971,Paper 71-280. 7 p. 10 downwash corrections to less than delta times alpha = 0.007 C sub L refs. Members, $1.50; nonmembers, $2.00. degrees and reduced the streamline curvature to less than delta times Sonic-boom wind-tunnel tests are known to present severe C sub m = 0.006 C sub L. The correction factors in both walls were problems associated not only with accurate construction of very unaffected by wing span-to-tunnel width ratios of 0.71 to 0.88. Wing small models but also with the presence of tunnel flow angularities, boundary layer transition was affected by the wall geometry. interference from model mounting apparatus, and boundary-layer (Author) effects. Recent experience has shown that some of these problems become critical at high supersonic speeds. The problems are reviewed and techniques for avoiding them or minimizing their effect are discussed. Sample of pressure signatures obtained at Mach numbers A71-22014 # Store separation from high speed aircraft with up to 4.63 through use of improved techniques are shown. (Author) emphasis on comparisons of predictions and flight test results. Donald L. Brooks (General Dynamics Corp., Convair Aerospace Div.. Fort Worth, Tex.). American Institute of Aeronautics and Astro- nautics. Aerodynamic Testing Conference, 6th. Albuquerque, N. Mex., Mar. 10.12, 1971, Paper 71-294 10 p Members, $1.50; A71-22010 # The use of a laser Doppler velocimeter in nonmembers, $2.00. supersonic flow. W. J. Yanta, D. F. Gates, and F. W. Brown (US. Three methods for predicting >

220 A7 1-22033

A71-22025 fl Fatigue and fracture mechanics. Herbert F. are presented and discussed. Tests of the modified delta wings show Hardrath (NASA. Langley Research Center, Materials Div., Hampton. that vortex breakdown is influenced much more strongly by Va.). fAmerican lnstitute of Aeronautics and Astronautics and planform changes near the apex than changes near the trailing edge. American Society of Mechanical Engineers, Structures, Structural (Author) Dynamics, and Materials Conference, 1 lth, Denver, Colo., Apr. 22-24, 1970, AlAA Paper 70512.)Journal of Aircraft, vol. 8, Mar. 1971. p. 129.142. 203 refs. A71-22029 i! Wind-tunnel boundary interference on a Review of the complex design problems involved in the V/STOL model. Ching-Fang Lo (ARO. Inc., Arnold Air Force development of an efficient airframe capable of operating economi- Station, Tenn.). (American lnstitute of Aeronautics and Astro- cally and safely for a long life. Existing design procedures for fatigue nautics. Aerodynamic Testing Conference, 5th, Tullahoma, Tenn., are based primarily on empirical rules and results taken from May 18-20, 1970, Paper 70575.1 Journal of Aircraft, vol. 8, Mar. systematic test series. Large numbers of tests are being performed to 1971, p. 162-167. 13 refs. evaluate the adequacy of designs and much judgment is employed to Boundary-layer transition experiments were conducted in the produce flightworthy structures. A purely analytical fatigue design AEDC-VKF 12- and 40-in. supersonic wind tunnels at Mach numbers method is not yet available. If it were, tremendous numbers of 3 and 4 on an adiabatic wall, 1Odeg total-angle sharp cone. The calculations would be required. The scatter inherent in fatigue effects of spherical roughness elements and free-stream disturbances behavior and in service conditions would require that results of such (radiated aerodynamic noise) on transition we e investigated. The analyses be interpreted statistically. Consequently, effective designs large variation in smooth wall transition locations which exists on will continue to be produced through a judicious combination of models in supersonic wind tunnels of different sizes is shown to experience, intuition, fatigue analysis, and evaluation testing. The use influence trip performance. These studies have also indicated that the of high-strength materials has increased the chances of major failures 'effective point' location proposed by van Driest, et al. is relatively caused by moderate damage or flaws. Fracture mechanics analysis independent of the smooth wall transition location (or free-stream procedures appear capable of treating simple problems of this sort, disturbance and tunnel size) at supersonic speeds. The correlation but are not yet adequate for complex structural and loading parameters developed by van Driest-8lummer and Potter-Whitfield conditions. However, simple applications of these procedures provide are examined, and their ability to predict the tripped transition a useful rationale for defining inspection techniques and schedules. location is discussed. (Author) M.V.E.

A71-22030 r" An efficient, steady, subsonic collocation method for rc!ving lifti-gsurface problems. Atlee M. Cunningham, Ail-22026 tt Dynamics of circular periodic structures. Jr. (General Dynamics Corp., Fort Worth, Tex.). (American Institute Thomas J. McDaniel (Dayton, University, Dayton, Ohio). Journal of of Aeronautics and AsRonautics, Aerospace Sciences Meeting, 8th. Aircraft, vol. 8, Mar. 1971, p. 143-149. 15 refs. Contract No. AF New York, N. Y., Jan. 19-21, 1970, Paper 70-191.)Journal of 33(615)-67-C-1187. Aircraft, vol. 8. Mar. 1971, p. 168-176. 18refs. The frequency response matrix is determined for a periodically In the collocation approach tor solving the integral equation of supported, periodically damped, closed circular beam structure steady subsonic lifting-surface theory, accurate integration of the which is an approximate model of a skin-stringer aircraft fuselage product of the kernel and pressure functions over the wing surface is structure. The analytical technique which IS developed depends on required before a stable solution can be achieved. A Gaussian the periodic nature of the structure to simplify the analysis. The nuadrature inteoralton technique is develooed which includes correc- dAys;s k Luinpirmriitary approacn io the transier matrix method tion terms that account for the error incbrred while integrating for determining frequency response. One purpose of the analysis is to through the singularity and discontinuity of the kernel function. It is circumvent the numerical and/or computer storage difficulties shown how inconsistent treatment of the chordwise discontinuity commonly found in computing the frequency response for typical will cause the spanwise integration to diverge with increasing aircraft fuselage structure from a transfer matrix analysis. Numerical integration chords. An optimum relationship is given between difficulty is avoided by using the properties of the transfer matrix for chordwise downwash points and excess chordwise integration points. one periodic unit and a consequence of the Cayley-Hamilton Also given is an empirically determined optimum ratio of spanwise to theorem to obtain an analytical solution for the frequency response chordwise control points based on planform geometry. By com- matrix. The second purpose of the analysis is to investigate the parison with experiment and other theories, the method is shown to spatial decay of response from a point or region of the structure be both stable and accurate as well as more efficient than methods which is being excited. This spatial decay isolates the response to a based on finite aerodynamic element representations of lifting region of structure near the excitation and reduces the overall surfaces. (Author) dynamic stress level of the structure for a general excitation. Three damping devices that utilize a viscoelastic link to produce spatial decay are evaluated. Several numerical examples are shown. (Author) A71-22032 # Minimum time turns for a supersonic airplane at constant altitude. J. Karl Hedrick and Arthur E. Bryson. Jr. (Stanford University. Stanford, Calif.). Journal of Aircraft, vol. 8, A71-22028 # Vortex breakdown on slender sharpedged Mar. 1971, p. 182.187. 9 refs. wings. W. H. Wentz, Jr. (Wichita State University, Wichita, Kan.) and Optimal control theory is used to determine thrust, bank-angle, D. L. Kohlman (Kansas. University, Lawrence, Kan.). (American and angle-of-attack programs for minimum time turns of a supersonic Institute of Aeronautics and Astronautics, Aircraft Design and airplane at constant altitude for three different terminal conditions: Operations Meeting. Los Angeles. Calif., July 14-16. 1969, Paper (1) both heading angle and velocity specified. (2) only heading angle 69-778.)Journal of Aircraft, vol. 8, Mar. 1971, p. 156-161. 14 refs. specified, (3) only velocity specified. The angle-of-attack is con- NSF-supported research; Grant No. NGR-17-002-043. strained to be less than the stall angle of the aircraft and the thrust is Systematic wind-tunnel investigations of vortex breakdown have constrained to be less than the maximum attainable thrust, which at been conducted on sharpedged delta and modified delta wings with constant altitude is a function of velocity. Numerical results are given mep angles from 45 to 85 degrees at Reynolds numbers of about for a typical supersonic airplane at two different altitudes. These ~.~.OOO,utiliz'ing a schlieren system for flow visualization. Vortex results show that in general a variable velocity, variable bank angle breakdown positions are presented as a function of angle of attack turn at full throttle is minimizing. (Author) and sweep. Lift measurements generally compare favorably with Polhamus' leading-edge suction analogy. Drag due to lift is predicted quite satisfactorily as the streamwise component of normal force for A71-22033 # Crossflow profiles for compressible, turbulent all models tested. Effects of vortex breakdown on pitching moments boundary layers. J. Richard Shanebrook (Union College, A71 -22035

Schenectady, N.Y.) and William J. Sumner. Journal of Aircraft, vol. T P Kuchinskaia Av/atsmmara Tekhnlka, vol 13, no 3, 1970, p 8, Mar. 1971, p. 188, 189. 7 refs. NSF Grant No. GK-12697. 63 69 In Russian Demonstration that a family of hodograph models, previously The characteristics of bypass engines with a bypass ratio applied to the crossflow velocity component of three-dimensional, between 1 and 8, a takeoff gas temperature in front of the turbine turbulent, incompressible boundary layers, provides an adequate between 1300 and 1500 K, a compression ratio in the inner contour representation for compressible crossflow profiles with (S-shaped between 20 and 25, and an optimal energy distribution between the profiles) and without (D-shaped profiles) flow reversal. It is contours are analyzed It is shown that an increase in bypass ratio recommended that this family of crossflow models can be considered leads to a pronounced decrease in specific impulse, and thereby in in future developments of practical momentum integral methods for the flight velocity The influence of the decrease in specific impulse predicting the behavior of three-dimensional, compressible, turbulent on the temperature level in front of the turbine in cruising flight IS boundary layers. M.M. examined Guidelines for selectin5 a design point on the character istic curve of the fan at takeoff, which provides the required vertical thrust, are proposed VP A71-22035 ii Determination of the aerodynamic characteristics of an elastic swept wing in subsonic flow (Opredelenie aerodinamicheski kh kharakteristi k uprugogo strelovidnogo kryla v A71-22044 Experimental investigation of radial-flow dozvukovom potoke). A. Kh. Karimov. Aviatsionnaia Tekhnika, vol. energy losses in the rotating circular cylindrical-profile cascade of an 13, no. 3, 1970, p. 5-13. In Russian. inward-flow-turbine wheel (Eksperimental'noe issledovanie poter' An approximate method of calculating the aerodynamic loads energii radial'nogo potoka vo vrashchaiushcheisia krugovoi reshetke acting on an elastic swept wing with given lift characteristics. In the tsilindricheskikh profilei rabochego kolesa tsentrostremitel'noi calculation of the elastic strains, the wing is schematically rep- turbiny). V B Avdeev. Avlatsionnaia Tekhnika, vol 13, no. 3, 1970, resented by a beam subjected to combined bending and torsion, and p. 75~85.6 refs In Russian. the redistribution of the aerodynamic loads caused by the deforma- An experimental procedure for determining the rotation energy tions is taken into account. The aerodynamic forces acting on a loss for an inward-flow-turbine wheel at low subsonic velocities of swept wing in subsonic flow are calculated by Belotserkovskii's the iadial flow is proposed. The procedure is applied to the (1965) method. The procedure of calculating the aerodynamic loads determination of the energy loss balance of the cascade The profile is outlined for various laws of deformation of the middle surface. losses and the exit blade angle are determined as a function oi the The method proposed is well suited for engineering calculations of anylc of incidence. V.P. external loads acting on an aircraft in the solution of static aeroelasticity problems. V.P. A71-22045 /I Probabilistic estimate of the aerodynamic imbalance of aircraft gas-turbine rotors (Veroiatnostnaia otsenka aerodinamicheskoi neuravnoveshennosti rotorov aviatsionnykh A71-22039 # Shape of the leading edge of a minimum-drag GTDI. A I. Gleizer and G. P. Fedorchenko. Aviatsionnala Tekhnika, slender wing for hypersonic velocities (Forma perednei kromki vol. 13. no. 3, 1970, p. 86 93. 111 Russian. tonkogo kryla minimal'nogo soprotivleniia pri giperzvukovykh A method of determining the aerodynamic imbalance of skorostiakh). I. Filatov. Aviatsionnaia Tekhnika, vol 13, no. 3, E. gas-turbine rotors, caused by production errors of turbine and 1970, p. 39-43. 6 refs. In Russian. compressor rotor blades, is proposed. The analysis is limited to errors The problem of the shape of the leading edge of a minimum in the flow passage cross-sectioiial ared of turbines and to errors in drag hypersonic wing is analyzed within the framework of the blade angle of compressors. The method proposed is useful for Newtonian theory, under the assumption that the bluntness curve of determining the excitation forces acting on a rotor, which are the wing profile is known. The cases where the bluntness curve is required, for example, in damper design. V.P. constant over the wing span, and where the bluntness curves are similar at each cross section of the wing, are examined. In the first case, a rectilinear leading edge is found to be the optimum configuration. In the second case, a series expansion in powers of the A71-22048 # Investigation of the flow parameters in a derivative of the radius of bluntness for the functional defining the centrifugal-pump wheel (Issledovanie parametrov potoka v rabochem characteristic drag of the leading edge is obtained under the kolese tsentrobezhnogo nasosa). D. V. Stetsiuk. Aviatsionnaia assumption that the radius of bluntness varies gradually along the Tekhnika, vol. 13. no. 3, 1970, p. 108-114. 11 refs. In Russian. leading edge. The shape of the leading edge is diagrammed for An optical method of measuring local flow velocities in examples corresponding to each case. V.P. centrifugal-pump channels is developed and IS applied to the measurements of the relative flow velocity of water in the channels. It is shown that under normal operating conditions, the flow in a A71-22041 H Flow for a sudden widening of the channel radial channel separates from the blades near the outlet. As a result, (Techenie pri vnezapnom rasshirenii kanala). G. M. Gorelov and A. E. the fluid lags behind in the rotation of the channel, and its angular Trianov. Aviatsionnaia Tekhnika, vol. 13, no. 3, 1970, p. 54-62. 11 velocity becomes smaller than that of the channel and of the fluid refs. In Russian. particles at the blades. Because of this, an excess energy is imparted The flow in a channel abruptly widening at one side is studied to the particles at the blades. These results may explain the theoretically and experimentally. A new formula for calculating the discrepancy observed between experimental and theoretical flow flow boundary in the circulation is proposed. A formula for parameters in centrifugal-pump channels. V.P. calculating the dimensionless velocity profile in the expanding region of the flow is derived within the framework of Prandtl's semiempirical turbulence theory. under the assumption of a linear shearing stress distribution across the flow. The experimental data A71-22049 # Some results of investigations of centripetal employed were obtained in a wind tunnel blown with air. V.P. 'and radial-flow stages (Nekotorye rezul'taty ispytanii radial'no- osevykh i radial'nykh stupenei). G. A. Filippov, M. F. Zatsepin. K. K. Aleksandrov, and I. E. Rozenshtein. Aviatsionnaia Tekhnika, vol. 13, no. 3, 1970, p. 115-123. In Russian. A71 22042 Selection of the design point on the charac The influence of the exit blade angle on the economic viability teristic curve of the fan of a turbotan engine with a large bypass ratlo and thrust ratio of a centripetal stage is analyzed. and the optimum (K voprosu o vybore raschetnoi tochki na kharakteristike ventiliatora exit blade angle is determined. It is shown that flow rate control by DTRD s vysokoi stepen'iu dvukhkonturnosti) N V Pervyshin and means of variable-pitch nozzle guide vanes is the most advantageous

222 of such techniques. Relations for the efficiency of centripetal, radial-flow, and axial-flow stages are obtained. It is shown that radial-flow and axial-flow stages have the same flow coefficients. A formula for calculating the pressure in the nozzle throat from the pressure behind a radial-flow cascade is proposed. V.P.

A71-22050 # Analytical methods of determining the characteristics of certain spatial maneuvers of an aircraft (Analiticheskie meto& opredeleniia kharakteristik nekotorykh prostranmennykh manevrov sarnoleta). L. B. Goroshchenko. Aviatsionnaia Tekhnika, vol. 13. no. 3, 1970, p. 124-131. In Russian. Approximate methods of determining the time, path, and fuel consumption required for climb at a constant-radius turn and a constant or variable velocity and constant engine power rating are examined. It is shown that simple formulas can be obtained by taking into account that the engine thrust and the aircraft drag component which is independent of the lifting force vary in direct proportion to the air pressure at heights above 11 km and constant aircraft speed. V.P.

A71-22052 ii Construction of lines of flow in a complex region of two-dimensional supersonic flow (K postroeniiu linii toka v slozhnoi oblasti ploskogo sverkhzvukovogo teheniia). lu. I. Tsybizov. Aviarsionnaia Tekhnika, vol. 13. no. 3, 1970, p. 135-140. 6 refs. In Russian. A method of caicuiating the lines ot flow in a two-dimensional supersanie f:o.iv ieyiun characrerized by the interaction of rarefaction waves from several disturbance sources. The flow lines are obtained in two variables which are analogs of generalized polar coordinates. By using a moving system of coordinates, flow lines can be constructed in the plane of the flow from a known solution of the hodograph equations. A numerical example is included. V.P.

223 N7 1- 16987

SYSTEMS Final Report May 1970 623 p refs (Contract DOT-C-353-66) (PB-195030: TRW-06818-6039-R0-00: FRA-RT-71-59) Avail: NTIS HC$10.00/MF$0.65 CSCL 13F The tracked air cushion vehicle is one of several advanced STAR ENTRIES ground transportation systems being studied as a possible means of providing safe, high-speed. high-capacity transportation along densely populated areas. Based on requirements and constraints chosen for an operational system. subsystem alternatives are evaluate? 3nr' the selected subsystems are synthesized into a TACV system. Cost and performance are estimated over a range Of parameters. such as design cruise speed (150 to 350 mph) and N71-16901# Lockheed Missiles and Space Co..Palo Alto. Calif. vehicle capacity (50 to 150 passengers per vehicle). The configuration ANALYTICAL SOLUTIONS FOR THE CASE OF FLYING defined consists of trainable. electrically powered TACVs which VEHICLE MOTION AT LOW ANGLES OF ATTACK, collect power from trackside power rails mounted on the side of a CHAPTER 8. THREE DIMENSIONALMOTION channel guideway. Propulsion is by linear induction motors with G. E. Kuzmak 119701 10 p refs Transl. into ENGLISH variable frequency speed control. Control of the vehicles. singly or from the book "Dinamika Neupravliaemogo Dvizheniia Letatelnykh in trains, is automated and centralized. The vehicles are supported Apparatov pri Ukhode v Atmosferu" Moscow. Nauka Press, 1970 on and guided by peripheral jet air cushions with high pressure air p 307-321 provided by electrically driven axial flow compressors. Avail: NTIS: National Translations Center. John Crerar Library. Author (GRA) Chicago, 111.6061 6 The three-dimensional motion of a flying vehicle at low N71-16951# Lockheed Missiles and Space Co.. Palo Alto. Calif. angles of attack is examined. Emphasis is given to the EE' section VISCOUS HYPERSONIC FLOW AROUND A of the trajectory, which abuts directly on the boundary of the NONAXISYMMETRIC SLENDER BODY atmosphere. A linear theory of three-dimensional motion is discussed. M. D. Ladyzhenskii I19701 9 p refs Transl. into ENGLISH of the Author book "Prostransvennye Giperzvudkovye Techentia Gaza" MOSCOW. ?.?ashinos:ioenie, 1968 p 47 -56 N71-16902# Lockheed Missiles and Space Co..Palo Alto. Calif. Avail: NTIS: National Translations Center. John Crerar Library. VISCOUS GAS FLOW IN A SHOCK LAYER IN THE Chicago. 111. 60616 PRESENCE OF EQUILIBRIUM CHEMICAL REACTIONS Results are presented of a numerical computation of viscous I. M. Breev 119701 4 p refs Transl. into ENGLISH from Prikl. hypersonic flow around a nonaxisymmetric. slender. elongated body Mekh. i Tekhn. Fiz. (USSR), no. 4. 1970 p 150 - 153 whose generator in each meridian plane IS the parabola y is Avail: NTIS: National Translations Center, John Crerar Library. approximately x(3/4). It is assumed that the streamlined body differs Chicago, Ill. 60616 slightly from a body of revolution. As the computational results Stationary supersonic air flow around a sphere is considered show. the lift on the body for the case of a heat insulated wall taking into account viscosity. heat conduction and real exrePds ?he I:+! i:: an 5~.isriC!fiov. Autnor physiochemical processes. Under the assumption of local thermodynamic equilibrium. the flow in the shock layer is investigated N71-16983# Lockheed Missiles and Space Co., Palo Alto. Calif. at flight velocities of 3 to 10 km/s. Simplified Navier-Stokes ANALYTICAL SOLUTIONS FOR THE CASE OF FLYING equations, whose solution is found by finite differences. ar6 used to VEHICLE MOTION AT LOW ANGLES OF ATTACK, describe the flow. The case of a cooled body surface is examined. CHAPTER 8. 32: PLANE MOTION, DETERMINATION OF A distribution of the gasdynamic parameters is obtained in different THE TIME OF TRANSITION OF ROTATIONAL INTO flow modes. The heat flux and friction coefficient distribution as VIBRATIONAL MOTION a function of the free stream parameters and the sphere radius is G. E. Kuzmak [1970] 8 p refs Transl. into ENGLISH investigated. The shape and location of the shock wave are from the book "Dinamika Neupravliaemogo Dvizheniia Letatelnykh determined, and streamlines and sonic lines are constructed. Apparatov pri Vkhode v Atmosferu" Moscow. Nauka Press, 1970 Author p 297-307 Avail: NTIS: National Translations Center, John Crerar Library. Chicago, 111. 6061 6 N71-16903# Lockheed Missiles and Space Co.. Palo Alto, Calif. Considered are cases of motion when the equation for ON THE QUE!XION OF THE VALUE OF ENTROPY ON THE the angle of attack on the EE' section of the trajectory directly SURFACE OF A BODY OF REVOLUTION AT A NONZERO abutting on the boundary of the atmosphere has an exact solution ANGLE OF ATTACK express& in terms of Bessel functions. The motion must occur at low M. D. Ladyzhenskii [1970] 2 p Transl. into ENGLISH from the angles of attack. This assumes compliance with definite demands book "Prostranstvennye Giperzvukovye Techeniia Gaza" Moscow. on the approach of a flying vehicle to the boundary of the Mashinostroenie. 1968 p 28 - 29 atmosphere. Solutions expressed in terms of Bessel functions allow Avail: NTIS: National Translations Center, John Crerar Library. clarification of a number of motion details when the angular Chicago. 111. 60616 velocity of the flying vehicle outside the atmosphere is quite low. The entropy takes on its maximum value on the surface Author of a body of revolution at a zero angle of attack. Computations and experiments show that the entropy retains its maximum value even at nonzero angles of attack, to the accuracy obtained in these N71-16987# Oklahoma Unlv Research lnst. Norman computations and experiments. Author STATE OF OKLAHOMA AIRPORT PLAN May 1970 150 p refs Sponsored in part by Okla Aeron Comm and HUD Prepared for Okla Ind Develop and Park Dept and N71-16904# TRW Systems Group. Redondo Beach. Calif. Okla Aeron Comm HIGH-SPEED GROUND TRANSPORTATION SYSTEMS (PB-194937) Avail NTIS CSCLOl E ENGINEERING STUDY: TRACKED AIR CUSHION VEHICLE A systematic plan for airport development over the time

225 N71-16988 period to 1980 was considered To accomplish this task, the later after the rail rapid service was opened The data from these project was separated into five work elements (1) verification and surveys were compared to determine the effect of the new rail classification of airports. (2) determinants of airport facilities. (3) transit service on the choice of travel mode by the different groups aviation development model. (4) test of the model, (5) schedule of airport users The report presents selected tabulations of projected investments for Oklahoma airports Author (GRA) Author (GRA)

N71-16988# Regional Planning Commission Cleveland Ohio N71-16992# Regional Planning Commission. Cleveland, Ohio DATA FILE EDITING AND PRELIMINARY ANALYSIS, CLEVELAND-HOPKINS AIRPORT ACCESS STUDY: SURVEY CLEVELAND-HOPKINS AIRPORT ACCESS STUDY Final PROCEDURES Final Report Report May 1970 126 p May1970 174 p (Contract DOT-OS-A9-023) (Contract DOT OS-A9-023) (PB-195046, DOT-OS-A9-023-2) Avail NTlS CSCL 138 (PB-195047 DOT-OS-A9-023 3) Avail NTlS CSCL 138 Analyzed is the impact of rapid rail extension to Hopkins An analysis of the impact of the rapid rail extensions on Airport A survey of airport users at Hopkins Airport was conducted airport users was conducted before the opening of the rail transit before the opening of the Cleveland Transit System rail transit service to the airport and another survey was conducted one year service to the airport and another survey was conducted one year later after the rail rapid service was opened The data from these later after the rail rapid service was opened The data from these surveys were compared to determine the effect of the new rail surveys were compared to determine the effect of the new rail transit service on the choice of travel mode by the different groups transit service on the choice of travel mode by the different groups of airport users The report documents the procedures used in the of airport users This report documents the procedures used in the preparation of files for analysis of the surveys Author (GRA) surveys Author (GRA)

N71-16993# Lockheed Missiles and Space Co , Palo Alto Calif N71-16989# Regional Planning Commission Cleveland, Ohio NEW ON-BOARD INSTRUMENTS DATA FILE FORMATS AND CODE DESCRIPTIONS. F Gerchikov 119701 4 p Trans1 into ENGLISH from Aviats CLEVELAND-HOPKINS AIRPORT ACCESS STUDY Final I Kosmonavt (Moscow) no 9 1970 p 20 21 Report Avail NTIS. National Translations Center, John Crerar Library Jun 1970 90 p Chicago. Ill 60616 (Contract DOT-OS-A9-0231 The design of a sensitive altimeter for high speed aircraft (PB-195048. DOT-OS-A9 023-4) Avail NTlS CSCL 138 and space vehicles is described The instrument uses radioactive The impact of rapid rail extension was analyzed A survey radiatton from the aircraft. together with energy level measurements of airport users was conducted before the opening of the rail of photons reflected from earth, for control Reflected photons transit service to the airport and another survey was conducted one proceed to a detector, through an amplifier and to an altitude year later after the rail rapid service was opened The data from pulse selection circuit whereupon the signal Poisson distribution is these surveys were compared to determine the effect of the new converted into a Gaussian distribution and then into normal signals rail transit service on the choice of travel mode by the different Altimeter accuracy at the 2 5 to 3m critical preset-down flight groups of airport users The report documents the file formats and altitude is about 2 5 cm. which is satisfactory for jet aviation demands GG code descriptions for the survey data tape Author (GRA)

N71-17044# Royal Aircraft Establishment Farnborough N71-16990# Regional Planning Commission, Cleveland. Ohio (England) Engineering Physics Dept CLEVELAND-HOPKINS AIRPORT ACCESS STUDY: SURVEY TEMPERATURE AND FLUID PROPERTY EFFECTS ON RESULTS Final Report CAVITATION IN AIRCRAFT FUEL PUMPS Jun 1970 163 p W G S Lester London Aeron Res Council 1970 27 p refs (Contract DOT-OS-A9-023) Supersedes RAE-TR-69165. ARC-31 725 (PB-195045, DOT-OS-A9-023-1) Avail NTlS CSCL 138 (ARC-CP-1128. RAE-TR-69165 ARC-31 725) Copyright Avail A survey of airport users was conducted before the opening NTIS. HMSO 40p. BIS $1 60 of the rail transit service to the airport and another survey was Problems of measuring net positive suction head (NPSH) conducted one year later after the rail rapid service was opened are considered and a test technique for examining cavitation The data from these surveys were compared to determine the performance using a closed loop system is described Results effect of the new rail transit service on the choice of travel mode from a small booster pump operating in water and kerosene fuel by the different groups of airport users The report compares the confirmed that less NPSH is required to pump the fluids at elevated results of the surveys Author (GRA) temperatures than when cold The pump performance with kerosene was inferior to that with cold water as NPSH is reduced due to the difference in air solubility between the two fluids Prediction of pump cavitation performance in aircraft fuels will be difficult because of the influence of dissolved air content and the dependence N71-16991# Regional Planning Commission. Cleveland, Ohio of the vapor pressure of multi-component fluids on vapor/liquid CLEVELAND-HOPKINS AIRPORT ACCESS STUDY: AIR ratios Author (ESRO) PASSENGER SURVEY SELECTED TABULATIONS Final Report Jun 1970 275 p N71-17046# Deutsche Forschungs- und Versuchsanstalt fuel (Contract DOT-OS-A9-023) Luft- und Raumfahrt. Porz (West Germany) lnst fuer Angewandte (PB-195049, DOT-OS-A9-023-5) Avail NTIS CSCL 138 Gasdynamik An analysis of the impact of the rapid rail extension to DATA ACQUISITION ON HYPERSONIC WIND TUNNELS Hopkins Airport was performed A survey of airport users at [MESSWERTERFASSUNG AN Hopkins Airport was conducted before the opening of the rail transit HYPERSCHALLWINDKANAELEN] service to the airport and another survey was conducted one year Josef Thelen Sep 1970 47 p refs In GERMAN, ENGLISH

226 N71- 17099 summary AND CONTROL (DLR-FB-70-44) Avail NTIS, ZLDl Munich 14.10 DM D. H. Pern/. J. C. Morrall. and W. G. A. Port London Aeron. Res. A digital data acquisition system for hypersonic wind tunnels Council 1970 80 p refs Supersedes RAE-AERO-2638; is described The hardware controlled system scans up to 50 ARC-22242 channels at high speed (10,OOO measurements/sec). digitizes the (ARC-CP-1106-Pt-3; RAE-AERO-2638-Pt-3; ARC-22242-Pt-3) input signals and records them on magnetic tape The data are Copyright. Avail. NTIS; HMSO: 85p; BIS. $3.40 punched on paper tape for further processing in a computing center Measurements of the aileron and rudder powers enabled Author (ESRO) the sideslip and damping derivatives to be determined. The control powers and sideslip derivative measurements agreed with wind tunnel measurements. and high lift coefficient changes were consistent with smoke and tuft wing flow studies. The derivatives N71-17063# National Transportation Safety Board. Washington. were used to estimate the period. damping and roll-yaw ratio of D.C the lateral oscillation which agreed with the flight measurements. AIRCRAFT ACCIDENT REPORT: COMPANIA DWlNlCANA Author (ESRO) DE AVlAClON DOUGLAS DC-4. CARVAIR ATL 98. HI-168 NEAR MIAMI INTERNATIONAL AIRPORT, MIAMI, FLORIDA.23JUNE 1969 12 Aug. 1970 34 p N71-17084# National Gas Turbine Establishment. Pyestock (NTSB-AAR-70-17; SA-415) Avail. NTIS (England). Dominicana Airlines. Flight 401, a DC-4. operating as a INGESTION OF DEBRIS INTO INTAKES BY VORTEX cargo flight from Miami. Florida, to Santo Domingo. Dominican ACTION Republic. crashed shortly after takeoff from Miami International D. E. Glenny London Aeron. Res. Council 1970 47 p refs Airport on June 23. 1969. The aircraft was destroyed by impact and Supersedes NGTE-R-307; ARC-31474 the ensuing ground fire. Several buildings in the area of the (ARC-CP-1114; NGTE-R-307; ARC-31474) Copyright. Avail: NTIS; accident site were also damaged. The four occupants of the aircraft. HMSO 48p. 61s: $2.40 as well as six persons on the ground. were fatally injured. The The impulsive lifting of particles by the ground-to-intake Safety Board determined that the probable cause of the accident vortex core is considered both theoretically and experimentally. For was the confused action on the part of the crew while attempting a given inlet velocity the strength of the vortex and the maximum to cope with the catastrophic failure of an engine during takeoff. size of particle that can be lifted depends on ambient vorticity and Author the strength of the wind bhingon to the intake. Various memods of rediicing ingestion were examined but none provided an absolute safeguard. However, a progressive opening of the throttle as the aircraft initially accelerates, may reduce the ingestion problem. N71-17081# National Physical Lab.. Teddington (England). Author (ESRO) Aerodynamics Div. AN ANALYSIS OF SOURCES OF ERROR IN TYPICAL PRESSURE MEASUREMENTS IN A BLOWDOWN SUPERSONIC TUNNEL N71-17086# National Physical Lab., Teddington (England). P. G. Pugh and J. Peto Nov. 1969 24 p refs Aerodynamics Div. (NPL-AERO-1306: ARC-31585) Avail. NTlS AN EXPERIMENTAL INVESTIG AT1 ON OF WIND-TU N NE L Pressure measurement errors at supersonic speeds due WALL CONDITIONS FOR INTERFERENCE-FREE DYNAMIC to transducer calibration, electrical noise. transducer nonlinearity. MEASUREMENTS test section flow non-uniformity. model manufacturing tolerances. as A. W. Moore and K. C. Wight Dec. 1969 50 p refs well as static hole diameter. depth. position. and quality were (NPL-AERO-1307; ARC-31704) Copyright. Avail: NTlS separately identified. The accuracy of pressure measurements in Results of dynamic tests on two model half-wings performing blowdown supersonic wind tunnels is also discussed. pitching oscillations in a tunnel with a slotted roof and floor and Author (ESRO) perforations of variable size behind the slots are presented. A porosity which gives small interference for all speeds in the range from 0.40 to 1.05 M is discussed and a method is suggested for selecting a wall porosity to give interference-free damping N71-17082# Royal Aircrah Establishment. Bedford (England). derivatives; interference-free stiffness derivatives are not Aerodynamics Dept. simultaneously obtained and small corrections to measured values LOW SPEED FLIGHT TESTS ON A TAILLESS DELTA are required. Author (ESRO) WING AIRCRAFT(AVR0 7076). PART4: WING FLOW D. H. Perry. W. G. A. Port, and J. C. Morrall London Aeron. Res. Council 1970 52 p refs Supersedes RAE-AERO-2639; ARC-22256 N71-17089# National Physical Lab . Teddington (England) (ARC-CP-1107-Pt-4: RAE-AERO-2639-Pt-4; ARC-22256-Pt-4) Aerodynamics Div Copyright. Avail: NTIS; HMSO: 50p; Bis: $2.00 SOME OBSERVATIONS ON VORTEX SHEDDING AND Flow visualization tests showed that the growth of the ACOUSTIC RESONANCES separated area occurred by progressive inboard movement of a M Gaster Jan 1970 17 p refs separation boundary which lay roughly chordwise across the (NPL-AERO-1311. ARC-31829) Copyright Avail NTlS ming so accounting for most of the changes in the aerodynamic Acoustic resonances excited by vortex shedding from cylinders characteristics of the aircraft at high incidence. Attempts to reduce and plates are discussed It is shown that very powerful resonances the longitudinal instability caused by the flow separation with wing can be produced, but that these are determined by the dimensions fences and a notch were unsuccessful. Author (ESRO) of the wind tunnel and not solely by the model as previously oromsed 4uthor (ESRO)

N71-17083# Royal Aircrah Establishment, Bedford (England). Aerodynamics Dept. N71-17099# Association Internationale des Constructeurs de LOW SPEED FUGHT TESTS ON A TAILLESS DELTA WING Materiel Aerospatial. Paris (France). AIRCRAFT (AVRO 7076). PART 3: LATERAL STABILITY INVENTORY OF THE PRINCIPAL EUROPEAN WIND

227 N71-17100

TUNNELS CAPABLE OF BEING USED FOR AERODYNAMIC N71-17108# Liverpool Univ (England) Dept of Mechanical TESTS IN THE POST APOLLO PROGRAM Engineering J Brocard 1970 9 p Presented at the 4th EUROSPACE A WIND-TUNNEL INVESTIGATION OF THE STALLING US-European Conf,Venice. 22-25 Sep 1970 PERFORMANCE OF TWO COMPRESSOR CASCADES OF Avail NTlS DIFFERENT ASPECT RATIOS AT LOW SPEED Size, stagnation pressure. Reynolds number and Mach M R A Shaalan London Aeron Res Council 1970 41 p number ranges of European wind tunnels operating in the subsonic. refs Sponsored jointly by Min of Aviation and United Arab Rep transonic. supersonic. and hypersonic ranges, and at low density. are Govt Supersedes ARC-30083 tabulated ESRO (ARC-CP-1103 ARC-30083) Copyright Avail NTIS. HMSO 50p BIS $200 The blade section profile was staggered at 36 deg with N71-17100# Royal Aircraft Establishment. Farnborough a space-chord ratio of 088. and there was no tip clearance (England) Structures Dept Changes in aspect ratio were obtained by changing the blade chord AN INVESTIGATION OF THE STRESSES IN A WIND only The high aspect ratio blade (483) gave more deflection at TUNNEL CORNER SECTION mid-span near stall but it stalled earlier and suddenly and the high pressure rise coefficient increased slightly with incidence UP D E W Stone and P S A Barter London Aeron Res Council to the 1970 62 p refs Supersedes RAE-TR-69021 ARC-31468 stall point The low aspect ratio blade (2 10) stalled more (ARC-CP-1117. RAE-TR-69021, ARC-31468) Copyright Avail progressively The increase in axial velocity for both cascades was high a greater spanwise contraction being evident for the low NTIS. HMSO 75p BIS $300 The stresses were studied with a 1/6 scale model and aspect ratio The wall stall for the high aspect ratio blade was nearly both the brittle coating technique and elevated temperature strain equally distributed between the blade surface and the end Wall gages were employed The thermal and pressure stresses were whilst it was shifted towards the blade surface for the other one simulated separately Author (ESRO) Author (ESRO)

N71-17109# Royal Aircraft Establishment. Bedford (England) Aerodynamics Dept N71-17102# Royal Aircraft Establishment Bedford (England) ON LIFTING SURFACES SUPPORTING ONE OR MORE Aerodynamics Dept PLANE SHOCK WAVES THE CONTROL CHARACTERISTICS OF AIRCRAFT J Pike London Aeron Res Council 1970 41 p refs EMPLOY I NG D I RECT- LIFT CONTROL Supersedes RAE-TR-66127 ARC-28452 W J G Pinsker London Aeron Res Council 1970 61 p (ARC-R/M-3623 RAE TR-66127 ARC-28452) Copyright Avail refs Supersedes RAE-TR-68140 ARC-30835L NTlS HMSO f_ 105 BIS $378 (ARC R/M 3629 RAE TR 68140 ARC 30835) Copyright Avail Stream surfaces from the flow through a plane shock wave NTlS HMSO A1 50 BIS $540 are used as cornpression surfaces to obtain higher lift to drag ratios The theory is developed for the control characteristics of than the two dimensional wedge ones Two such compression aircraft in which direct lift is commanded directly by the pilots surfaces can be combined into a W-Nonweiler shape, which gives stick Basic requirements are established for acceptable response in effect a central body below a swept wing The viscous drag characteristics of particular importance is the location at which tends to be high because the shapes have a large ratio of wetted direct lift acts relative to the center of gravity. the aerodynamic area to plan area For hypersonic speeds where the inviscid center and maneuver point The line of action of the control lift can improvement over a two dimensional wedge is small the high be controlled by mechanical interconnections between the viscous drag puts the W-wings at a disadvantage compared with conventional pitch control and direct lift systems Potential benefits flat-bottomed configurations At high supersonic speeds the inviscid of direct lift control include improved precision in landing large improvement is more marked and a gain in performance including aircraft more effective control of gust effects and reduced possibility viscosity over that of the two dimensional wedge and flat bottomed of stalling Author (ESRO) shapes can be shown For best performance the trailing edge of the W-wing is swept and its pressure drag and viscous drag are approximately equal Author (ESRO) N71-17103# Royal Aircraft Establishment Farnborough (England) Aerodynamics Dept RECTANGULAR AND CARET SAILS IN SUPERSONIC N71-17112# Queen Mary Coll London (England) Dept of FLOW Aeronautical Engineering L H Townsend London Aeron Res Council 1970 56 p refs DELTA WINGS WITH LONGITUDINAL CAMBER AT LOW Supersedes RAE-TR-67006, ARC 29541 SPEED (ARC-R/M-3624 RAE-TR-67006 ARC-29541) Copyright Avail R K Nangia and J Hancock London Aeron Res Council NTIS. HMSO f 1 40, BIS $5 40 G 1970 29 p refs Supersedes ARC-31 588 For free stream Mach numbers between 10 and 4 a study (ARC-CP-1 129. ARC-31588) Copyright Avail NTlS HMSO is made of the profiles assumed and isentropic waves produced 37 5p BIS $1 50 in nonviscous flows by two-dimensional sails under pure tension Comparison of experimental results for the streamwise lift and of finite weight At the higher free stream Mach numbers distribution on a delta wing of aspect ratio 1 having various large parts of the compression flow are virtually centered and even streamwise cambers with simplified slender linear theory was good for long sails (e g 100 ft chord) at a high Mach number (e g 10) even for large cambers, although linear theory is totally inadequate and low stress (eg 5 tons/sq in) the weight of such a membrane for total lift prediction Author (ESRO) need not exceed 1 Ib/sq ft The analysis is modified to include the effects of skin friction and is then extended to singly curved caret sails. which allow leading edges to be swept but can still produce two-dimensional waves. while their cuwature imparts to such sails a stiffness due-to shape it is shown that equilibrium can alternatively N71-17113# Aircraft Research Association. Ltd , Bedford be maintained by appropriately applied tensile forces Rectangular (England) and/or caret sails may find applications as wings intakes cowls TESTS~~ WITH A WING-MOUNTED FAN NACELLE WITH and nozzles for hypersonic vehicles Author (ESRO) THE FAN JET SIMULATED BY COLD AIR BLOWING

228 N71-17132

AND ALTERNATIVELY BY A GAS GENERATOR SHROUD FREQUENCY DISTRIBUTIONS AND EXTREME VALUES OF Interim Report THE CENTER OF GRAVITY ACCELERATION AND OF G. Pauley London Aeron. Res. Council 1970 47 p refs THE STRESS ON LOWER WING SURFACE OF A BOEING Supersedes ARA-M-2811; ARC-301 58 720- B [ H AE U FI G KEITSVE RTEl LUNGE N U ND (ARC-CP-1111; ARA-M-2811; ARC-301 58) Copyright. Avail: EXTREMWERTE DER SCHWERPUNKTSBESCHLEUNIGUNG NTIS. HMSO: 70p; BIS: $2.80 UND DER SPANNUNG AN DER FLUEGELUNTERSEITE Wind tunnel tests were made on a simulated high by-pass EINER BOEING 720-81 ratio fan engine mounted close to a wing to determine the 0 Buxbaum Fraunhofer Ges Mar 1970 44 p refs In interference effects in the Mach number range from 0.6 to 0.81. GERMAN, ENGLISH summary Sponsored by Bundesmin fuer The nacelle and adjacent wing surfaces were fully pressure plotted Verkehr and overall force measurements were ubtained. Comparisons with (T8-87-1970) Avail NTlS test data from a free flow nacelle supported by a pylon suggests In order to evaluate the effects of gust load seasonal variations that the nacelle has a major influence on the local wing flow. on airframes the following parameters were recorded continuously whereas a pylon could be designed to have relatively little effect during 571 flights of a Boeing 720-8 airplane during normal on this flow Free flow nacelle effects were amplified by a cold service and analyzed statistically vertical acceleration near center of fan jet. Attempts at reproducing the jet effects with a simple gas gravity. lower wing in-spar skin stress. pressure altitude and generator shroud were a complete failure. Author (ESRO) air-speed airplane takeoff and landing weights. and flight duration Author (ESRO)

N71-17114# Royal Aircraft Establishment. Farnborough (England). Aerodynamics Dept. N71-17130*# National Aeronautics and Space Administration. THE ESTIMATION OF THE LOADING ON SWEPT WINGS Lewis Research Center. Cleveland, Ohio. WITH EXTENDING CHORD FLAPS AT SUBSONIC SPEEDS INVESTIGATION OF FLOW CHARACTERISTICS OF SOME J. McKie London Aeron. Res. Council 1970 45 p refs WIRE-FORM AND LAMINATE-FORM POROUS MATERIALS Supersedes RAE-TR-69034: ARC-3 1285 Albert Kaufman and Hadley T. Richards Washington Oct. 1970 (ARC-CP-1110; RAE-TR-69034: ARC-31285) Copyright. Avail: 23 p refs NTIS: HMSO: 60p; 81s. $2.40 (NASA-TM-X-2111; E-5748) Avail: NTIS CSCLOlA A method is given for estimating lift and vortex drag increments Experime-tally de?erm!ned flow characteristics were correlated due to part span. extending chord flaps on thin. sweptback. tapered with standard flow rates and absolute filtration ratings of wire-form wings of large aspect ratio in inviscid. incompressible flow. This materials and with functions of hydraulic diameters and external hole linear theory accounts for sweepback. tip. and center effects. spacings of laminate-form materials. Effects on flow characteristics Spanwise loadings are obtained by quadrature methods. extended of specimen curvature and use of high temperature air up to 840 to include discontinuities in wing chord. and examples are given degrees F were investigated. The conclusion was drawn that flow for some typical wing and flap layouts. Author (ESAO) rates both for elevated temperature conditions and for specimen curvatures simulating leading edse radii of turbine blades can be predicted with good accuracy from correlations developed and the N71-17117# Royal Aircraft Establishment. Farnborough oasic fiow equation fc: poious ?aterials Author (England). Aerodynamics Dept. EXPERIMENTAL INVESTIGATION OF THE EFFECT OF TRAILING-EDGE SWEEPBACK ON THE SUBSONIC N71-17131*# National Aeronautics and Space Administration LONGITUDINAL CHARACTERISTICS OF SLENDER WINGS Ames Research Center. Moffett Field. Calif D. L. I. Kirkpatrick and A. G. Hepworth London Aeron. Res. CONVECTIVE HEAT TRANSFER TO THE AMES M2 AND Council 1970 33 p refs Supersedes RAE-TR-70039; ARC-32237 M2-F2 LIFTING ENTRY VEHICLES (ARC-CP-1 130; RAE-TR-70039; ARC-32237) Copyright. Avail: H Lee Seegmiller Washington Dec 1968 83 p refs NTIS: HMSO: 42.5~;81s. $1.70 (NASA-TM-X-1691) Avail NTlS CSCLOlC Measurements of the lift. drag. and pitching moment The convective heat transfer to the M2 and M2-F2 lifting characteristics on three slender ogee wings with different trailing-edge entry vehicles has been measured at angles of attack from minus sweepback angles are presented. The characteristics of these wings 7 degrees to plus 77 degrees during tests at hypersonic Mach are correlated with those of wings with unswept trailing edges. numbers Heating of the configuration is generally concentrated at Author (ESRO) the nose pitch control, and fin leading edges at low angles of attack and at the lower surface, pitch control. and extended rudders at high angles of attack Three dimensional separated flow occurred N71-17118# Royal Aircraft Establishment, Bedford (England). in the region of the lower pitch controls and extended rudders in Aerodynamics Dept. all tests at the lower angles of attack Author SUPER VC 10 CRUISE DRAG: A WIND TUNNEL INVESTIGATION. PART 1 : EXPERIMENTALTECHNIQUES C. R. Taylor. J. R. Hall. and R. W. Hayward London Aeron. Res. N71-17132*# National Aeronautics and Space Administration. Council 7979 44 p refs Supersedes RAE-TR-69180. Flight Research Center, Edwards. Calif. ARC-31771 BASE PRESSURE MEASUREMENTS ON THE XB-70 (ARC-CP-1125; RAE-TR-69180; ARC-31771) Copyright. Avail. AIRPLANE AT MACH NUMBERS FROM 0.4TO 3.0 NTIS. HMSO 60p; 61s: $2.40 Edwin J. Saltzman. Sheryll A. Goecke. and Chris Pembo Measurements were made of the longitudinal forces and Washington Sep. 1968 36 p refs moments on a 1/27 scale model of the Super VC 10 at Mach (NASA-TM-X-1612) Avail: NTlS CSCLOlC numbers between 0.60 and 0.86 The model design, test techniques Full-scale flight base pressure coefficients obtained from and corrections, and the measuring techniques are discussed. the XB-70 propulsion package are compared with predicted values Author (ESRO) based on a combination of cold jet flow wind-tunnel models and data from a two-engine side-by-side jet. full scale aircraft. At cruise Mach numbers the base pressures on the full-scale aircraft were N71-17119# Laboratorium fur Betriebsfestigkeit, Darmstadt (West higher than predicted. resulting in a favorable increment of about Germany). two percent in terms of lift-drag ratio. At low supersonic speeds

229 N71-17144 near a Mach number of 1 2. the negative base pressure coefficients INPL-AERO-1305, ARC-31514) Copyright Avail NTlS were about three times larger than predicted. resulting in a A limited series of measurements showed no appreciable significant lift-drag ratio decrement Author dependence of turbulence structure on moderate three-dimensionality although large differences between the direction of the shear stress vector and the direction of the velocity gradient N71-17144# National Physical Lab, Teddington (England) vector appeared in the outer layer Author (ESRO) Hovercraft Unit THE CORRECTION OF HOVERCRAFT PERFORMANCE TO STANDARD CONDITIONS J C Shipway Sep 1970 54 p refs (NPL- Hovercraft- 16) Copyright Avail NTI S N71-17181# Oerlikon Machine Tool Works Zurich (Switzerland) Coefficients. derived from trials with four different hovercraft PROSPECTUS FOR A EUROPEAN COMPANY WITH types. for correcting hovercraft performance to assumed standard REGARD TO THE OPERATION OF REGIONAL APPLICATION conditions are discussed The results suggest that craft performance SATELLITE SYSTEMS is best compared on the basis of achieved Froude number versus P L Burckhardt 1970 9 p Presented at the 4th EUROSPACE (observed wave height/overall craft length) Author IESRO) US-European Conf Venice 22 -25 Sep 1970 Avail NTlS Major ESRO projects proposed to European government e g telecommunication air traffic and meteorological satellites are N71-17145# Deutsche Forschungs- und Versuchsanstalt fuer outlined The importance of creating regional application satellite Luft- und Raumfahrt Oberpfaffenhofen (West Germany) lnst fuer systems and a European company (EUROSAT) are emphasized Physik der Atmosphaere Problems are analyzed and solutions suggested ESRO SYNOPTIC AEROLOGICAL CONDITIONS FOR THE OCCURRENCE OF CLEAR AIR TURBULENCE [DIE SYNOPTISCHAEROLOGISCHEN BEDINGUNGEN FUER DAS AUFTRETEN VON CLEAR-AIR-TURBULENZ] N71-17190# Idaho Nuclear Corp Idaho Falls Friedhold Weber Aug 1970 113 p refs In GERMAN, ENGLISH SEMISCALE BLOWDOWN AND EMERGENCY CORE summary COOLING (ECC) PRQlECT TEST REPORT TESTS 822 AND (DLR-FB-70-291 Avail NTIS. ZLDl Munich 34.50 DM 823 After a literature review the results of Lufthansa North D J Olson and J F Whitbeck Oct 1970 58 p refs Atlantic jet stream clear air turbulence (CAT) observations are (Contract AT(10-1)-1230) given Vertical acceleration was related to certain meteorological (IN 1393) Avail NTlS situations and different atmospheric parameters Special synoptic The preliminary test results of two decompression experiments aerological conditions during which moderate or severe CAT can be (Tests 822 and 823) performed in the Semiscale Elowdown expected are discussed Author (ESROI Emergency Core Cooling Project are presented The purpose of the Semiscale Elowdown and Emergency Core Cooling Project IS to provide the experimental data base required for the development and assessment of analytical models for the prediction of the N71-17160# National Physical Lab, Teddington (England) thermal-hydraulic behavior occurring in a large PWR during a Hovercraft Unit loss-of coolant accident Tests 822 ar.d 823 were initiated by hot leg MOVEMENT OF HIGH DENSITY LOADS breaks of a system configuration that includes both an operating A T A Wride Jut 1970 34 p loop and a simulated core with internals The break size in Test (NPL-Hovercraft-TM-3 1 ) Copyright Avail NTlS 822 was 30% of the pipe area (0027 sq ft). and the break size High density loads can be moved over 1 in obstacles using in Test 823 was 100% (009 sq ft) The measurements obtained fingered skirts giving a hoverheight of 2 in and cushion pressures provided information on fluid conditions as a function of time up to 5 psi Author (ESRO) including quality velocity and mass flow rate as well as subcooled pressure loads throughout the loop and thrust measurements on the vessel Author (NSA)

N71-17161# National Physical Lab, Teddington (England) Hovercraft Unit A COMPARISON OF THE CRUISE EFFICIENCY AND RANGE N71-17247*# National Aeronautics and Space Administration OF MARINE VEHICLESAND AIRCRAFT Lewis Research Center, Cleveland, Ohio J R Bishop Jun 1970 36 p refs STATIC-PRESSURE CONTOURS IN THE BLADE PASSAGE (NPL-Hovercraft-12) Copyright Avail NTlS ATTHE TIP OF SEVERAL HIGH MACH NUMBER ROTORS Genevieve R. Miller and Everett E. Bailey Washington Feb. 1971 The discussion also includes jet aircraft which are often excluded from comparisons with marine vehicles because their 16 p refs shaft power is not known Data are also presented for ships. aircraft (NASA-TM-X-2170: E-5875) Avail: NTlS CSCLOlA hovercraft. hydrofoils and helicopters High speed marine vehicles Static pressure contours across the blade passage at the have cruise efficiencies considerably lower than those of aircraft due tip of three high Mach number rotors are presented. Inlet relative to inferior lift-drag ratio and propulsive efficiency Author (ESRO) Mach numbers vary from 1.23 to 1.59. Flow rates vary from near choke values to those near blade stall. Blade shapes include both double circular arc and multiple circular arc. The static pressure contour plots indicate the location of the passage shock waves over N71-17179# National Physical Lab . Teddington (England) a range of Mach numbers and operating conditions. Qualitative Aerodynamics Div comparisons of flow conditions through blade passages for the two THE RESPONSE OF A TURBULENT BOUNDARY LAYER ON blade shapes can be made, However, a quantitative analysis of the Author AN INFINITE SWEPT WING TO THE SUDDEN REMOVAL data is not attempted. OF PRESSURE GRADIENT P Bradshaw (Imperial Coli ) and M G Terrell (Rolls-Royce. Ltd, N71-17263*# National Aeronautics and Space Administration Derby) Oct 1969 31 p refs La-dey Research Center, Langley Station. Va

230 N71-17373

LONGITUDINAL AERODYNAMIC CHARACTERISTICS OF George W Starkweather Jan 1971 59 p refs Revised THE VIKING LANDER CAPSULE AT MACH 6 (Grant NG L-07-002-002) Theodore J Goldberg and James C Emery Washington Feb (NASA-CR-116482) Avail NTlS CSCL 146 1971 16 p refs A study was undertaken for the purpose of obtaining an (NASA-TM-X-2205, L-7516) Avail NTlS CSCL 20D improved feedback control for a lunar landlng vehicle simulator An investlgatm of the longitudinal aerodynamtc characteratlcs The simulator. used to train astronauts for lunar landing, consists of a 0 0348-scale Viking lander capsule has been conducted at a of a cable supported. rocket propelled vehicle The lunar gravity IS Mach number of 6 and free-stream Reynolds numbers from 0 98 simulated by matntaining tensioi on the cable equal to 5/ 6 of the x 10 to the 7th power to 2 35 x 10 to the 7th power per meter vehicle weight A drum. onto which the cable is wound, IS controlled Data obtained at angles of attack from -3 deg to 20 deg were to keep the proper tension on the cable. and to allow the cable compared with analytical values obtained by the sine squared length to be changed The scope of the investigation is restricted deficiency method and modified Newtonian theory Author to a study of vehicular motion along a horizontal coordinate axis Since for small perturbations the responses of the system along the three axes are decoupled the study can to a first approximation N71-17254*# National Aeronautics and Space Administration be readily generalized to include the three dimenslonal case Lewis Research Center, Cleveland Ohio Author ACOUSTIC AND AERODYNAMIC PERFORMANCE OF A 6-FOOT DIAMETER FAN FOR TURBOFAN ENGINES. 3: ’ PERFORMANCE WITH NOISE SUPPRESSORS Edward J Rm. Charles E Feller. and Loren W Acker Washington N71-17354*# National Aeronautics and Space Administration. Feb 1971 61 p refs Lewis Research Center. Cleveland, Ohio. (NASA-TN-D-6178 E-5878) Avail NTlS CSCL2lE EFFECTS OF SPECIFIC SPEED ON THE EXPERIMENTAL Inlet and exhaust noise suppressors for a 6-ft- (1 83-m-) PERFORMANCE OF A RADIAL-INFLOW TURBINE diameter fan for a high-bypass-ratio turbofan engine were tested Milton G. Kofskey and William J. Nusbaum Washington Feb. The perforated-plate-on-honeycomb suppressors provided a much 1971 29 p refs broader band noise attenuation than was predicted Perceived noise (NASA-TN-D-6182; E-5928) Avail: NTlS CSCL 21 E level attenuations obtained due to the suppressorr were 13 and 12 A 4.97-inch(l2 62-cmhp diameter radial-inflow turbine was PNdB for simulated approach and takeoff conditions. respectively investigated over a range of specific speeds from 36 to 76 lrpml The theory used for the design of the suppressors is discussed In at equivalent design speed and pressure ratio. This specific speed general. the theory predicts the frequency for peak attenuation but range was obtained by using stators with different throat areas. underpredicts the peak attenuation amplitude For frequencies Each stator was tested with the unmodified or design rotor and with above and below peak, the observed anenuatlons are more than a rotor extension that reduced the rotor throat area to 53 percent predicted Degradations of aerodynamic performance caused by the of design. Results are presented to show the effect of the change noise suppressors were smaller than the experimental errors, which in specific speed on turbine performance. Comparison is made were estimated to be 2 percent Author between results obtained with the design rotor and with the rotor extension Author

N71-17330# Royal Aircraft Establishment, Farnborough (England). Structures Dept N71-17372# Advisory Group for Aerospace Research and AN INVESTIGATION OF THE SCATTER IN Development. Paris (France) VARIABLE-AMPLITUDE FATIGUE-TEST RESULTS OF 2024 HIGH TEMPERATURE TURBINES AND 7075 MATERIALS Jan 1971 587 p refs Presented at the 36th Meeting of the A. M. Stagg London Aeron. Res. Council 1970 119 p refs AGARD Propulsion and Energetics Panel. Florence 21 -25 Sep Supersedes RAE-TR-69110. ARC-32032 1970 (ARC-CP-1123: RAE-TR-69110; ARC-32032) Copyright. Avail: (AGARD-CP-73-71) Avail NTlS HC$6 OO/MFSO 95 NTIS: HMSO: S 1.50~.61s: $5.40 Cooling techniques for turbine blades of high temperature The fatigue life scatter of identical specimens was estimated. aeronautical gas turbine engines Advanced cooling methods and using a log-normal distribution. from several experimenters’ results. the application of improved heat resistant materials are discussed These estimates were analyzed for the effect of various test loading parameters on the magnitude of the scatter produced and the results are discussed in terms of a simple fatigue failure model. Author (ESRO)

N71-17373# Societe Nationale dEtude et de Construction de N71-17334# National Physical Lab, Teddington (England) Moteurs dAviation. Villaroche (France). Aerodynamics Div HIGH ENTRY TEMPERATURE TURBINE ON THE USE OF AERODYNAMIC-STABILIZING STRAKES ON TURBOREACTORS AND GAS TURBINES [DES HAUTES CHIMNEY STACKS SUPPORTING PIPES TEMPERATURES DEVANT TURBINE SUR D E Walshe and C F Cowdrey Feb 1970 29 p refs TURBOREACTEURS ETTURBINES A GAZ] (NPL-AERO-1310) Copyright Avail NTlS P. Alesi In. AGARD High Temp Turbines Jan. 1971 14 p Aerodynamic stability tests were carried out on linear mode In FRENCH models to compare the excitation of a model stack of circular cross Avail: NTlS HC$6.00/MF$0.95 section with that for a stack supporfing a small diameter pipe The High entry temperatures for gas turbine engines decrease presence of the pipe increased the excitation and it was reduced. specific wear and always augment reduced pressures so that gas but not eliminated. by strakes Author (ESRO) turbines can compete with Diesel engines in operational performance. Studies on turbocompressors with increased inlet temperatures showed that specific power in simple and double N71-17345*# Connecticut Univ , Storrs Dept of Electrical fluxes of moderate expansion increased and that all compressor Engineering double flux expansion rates were augmented threefold. Increased CONTROL OF DISTRIBUTED PARAMETER SYSTEMS AS temperatures at turbine inlets augment compression and improve APPLIED TO A LUNAR LANDING VEHICLE SIMULATOR the efficiency of compression diluting elements. Transl. by G.G.

23 1 N71-17374

N71-17374# National Gas Turbine Establishment, Pyestock HEAT FLUX MEASUREMENTS ON FIXED TURBINE (England) BLADES [MESURES DE FLUX DE CHALEUR SUR AUBES HEAT TRANSFER CALCULATIONS FOR TURBINE BLADE FIXES DE TURBINES] DESIGN Jacques Michard In AGARD High Temp Turbines Jan 1971 J Dunham and J P Edwards In AGARD High Temp Turbines 9 p refs In FRENCH, ENGLISH Summary Jan 1971 18 p refs Avail NTlS HC$6OO/MF$O95 Avail NTlS HC$6 OO/MF$O 95 The operating temperature of a cooled turbine blade depends Experimental results obtained on a set-up including a on the heat transfer rate from the hot gas stream, the heat moderately high temperature combustion chamber (1300 K) and conduction within the metal, and the heat convection to the cooling two stages of fixed blades are presented The first stage IS used air Discussed are methods of calculating these factors, and their as a distributor, the other one turning the flow parallel to its application to blade design The effect of cooling on turbine upstream direction at the outlet Heat transfer and local exchange performance is also considered Author coefficients obtained with an upstream Mach number of 0 2 and a Reynolds number of 25 000 per cm are analyzed Author

N71-17375# Societe Nationale d'Etude et de Construction de Moteurs d'Aviation, Villaroche (France) N71-17379# Deutsche Forschungs und Versuchsanstalt fuer TEMPERATURE DETERMINATIONS IN THE BLADES OF Luft- und Raumfahrt Brunswick (West Germany) Inst fuer CONVECTION COOLED TURBINES [DETERMINATION Luftsaugende Antriebe DES TEMPERATURES DANS LES AUBES DES TURBINES TEMPERATURE MEASUREMENTS WITH THERMOCOUPLES REFROlDlES PAR CONVECTION] INCLUDING ERRORS CAUSED BY CATALYTIC EFFECTS G Chiron In AGARD High Temp Turbines Jan 1971 13 p P Stottmann In AGARD High Temp Turbines Jan 1971 10 p refs In FRENCH refs Avail NTlS HC$6 OO/MF$O 95 Avail NTlS HC$600/MF$095 A mathematical method LS presented for calculating the Several methods for the temperature measurement in temperature distribution in a convectively cooled turbine blade by combustion gas are discussed especially the measurement with considering the temperature constraints imposed on blade life in thermocouples Corrections for compensation of the influences due the estimation Comparison between experimental and theoretical to flow velocity radiation and heat conduction are described In results verify the validity of this method for short and median case of using nable metal thermocouples the possible errors by length operations Trans1 by G G catalytic effects are studied Experimental results are presented which show the ignition of a fuel air mixture outside the boundary layer of the probe initiated by the catalytic influence of the N71-17376# Rolls-Royce. Ltd Bristol (England) Bristol Engine platinum surface The reproducible catalytic effects which initiate or Div force reactions in a gaseous fuel air mixture are dependent on the OLYMPUS 593 TURBINE COOLING external flow cond.tions gas temperature gas velocity fuel air-ratio M J Holland In AGARD High Temp Turbines Jan 1971 21 p and the distribution and evaporation of the fuel Coating the noble refs metal surfaces with A1203 avoids the catalytic effects Author Avail NTlS HC$600/MF$095 Turbine cooling effectiveness and efficiency are defined for subsequent use in descriptions of cooling performance The N71-17380# Von Karman lnst for Fluid Dynamics Rhode factors affecting the choice of cooling design point and the sources Saint-Genese (Belgium) of cooling air are discussed In particular the use of 5th stage H P DESIGN OF SMALL DIMENSION TURBINE BLADE BY compressor air in place of compressor delivery air IS shown to THEORETICAL ANALYSIS [DESSlN D'UNE AUBE DE result in lower rotor blade temperatures for the H P turbine The TURBINE DE PETITE DIMENSION AU MOYEN DE differing environments and requirements for turbine stator and rotor PROCEDURES THEORIQUES] blades are discussed together with the importance of combustion C Loudet In AGARD High Temp Turbines Jan 1971 28 p chamber outlet gas temperature profiles The turbine rotor and refs In FRENCH ENGLISH Summary stator blades are convection cooled and are fairly conventional The Avail NTlS HC$6 OO/MF$O 95 evolution of the various blade cooling designs is described together The method of blade boundary layer optimization due to with summaries of their cooling performance Author Le Foll is used for the calculation of a small turbine blade in incompressible flow with Goldstein s method for the resolution of the inverse potential flow problem A blade with a cusped trailing edge has been calculated for the following flow conditions inlet N71-17377# Sussex Univ . Brighton (England) School of Applied angle 32 deg outlet angle 54 8 deg and Reynolds number based Sciences on the chord and outlet velocity This blade gives a theoretical loss HEAT TRANSFER I NSTR UME NTATl0 N coefficient based on the dynamic outlet pressure of 4 45% The A B Turner In AGARD High Temp Turbines Jan 1971 18 p calculated losses are in good agreement with the experimental refs results taking into account the fact that a truly two dimensional flow Avail NTlS HC$6 00/MF$095 could not be obtained during the tests Author A brief review of heat transfer instrumentation with particular attention to the requirements of the gas turbine engineer IS N71-17381# United Aircraft of Canada Ltd Longueuil (Quebec) presented The work IS focused primarily on heat fluxmeters. recent develop,nents in methods of teniperature measurement and AN EXPERIMENTAL COOLED RADIALTURBINE Lj Okapuu and G Calvert (Pratt and Whitney Aircraft West thermocouple installation errors In this latter section a numerical S procedure for the problem of sensors embedded in csulation channels Palm.^ Beach Fla) In AGARD Hlgh Temp Turbines Jan 1971 is presented together with some correlations and predictions for IL P Avail NTlS HC$600/MF$095 typical examples in solid and porous surfaces Author A cooled radial turbine suitable for compressor drive in a twin spool engine was designed and IS at present undergoing N71-17378# Office National d Etudes et de Recherches experimental evaluation Assumed turbine design point conditions Aerospatiales Paris (France) were 2300 degrees F inlet temperature 17 112 atmospheres inlet

232 N7 1- 17389 pressure. 4 9 Ibs/sec mass flow rate, 5 1 1 turbine pressure ratio. CONSIDERATIONS 220 BTU/lb enthalpy drop, and a rotational speed of 67.000 rpm S. N. Suciu In AGARD High Temp. Turbines Jan. 1971 29 p Turbine components are nickel alloy castings in which cooling air refs passages are incorporated The design features of the turbine and Avail: NTlS HC$G.OO/MF$0.95 the results of thermal and stress analyses of its components are The maior technological developments which have made described Author possible the trend towards higher temperatures in modern aircraft gas turbine engines are discussed. The relative importance of manufacturing processes. material developments. cooling techniques, analytical design procedures, rupture and cyclic life considerations, N71-17382# Motoren-und Turbinen-Union Muenchen G.m.b.H. and aerodynamic and mechanical design improvements are (West Germany). EFFUSION COOLING OF TURBINE BLADES discussed along with illustrative examples and technical data. The need for a balanced design approach is stressed, and examples are H. Prechter. A. Schoenbeck. and N. Scholz In AGARD High given where trade offs can be made. It is noted that the advances Temp. Turbines Jan. 1971 14 p refs in aircraft engines during the last 10 years have been based on Avail: NTlS HC$6.OO/MF$0.95 the evolution of sound engineering principles. extensive component Theoretical and experimental investigations into the and engine development. and careful consideration of the operational aerodynamic and thermodynamic performance of effusion cooled requirements rather than a tremendous breakthrough or revolutionary turbine blades are presented. To estimate the aerodynamic and concept in any one area. Author cooling performance an extensive computer programme has been worked out, the physical background of which is described in this report Few available experimental test results are drawn on to N71-17387# Technische Hochschule Aachen (West Germany). back up the theoretical procedure. Some parametric studies are Inst. fuer Strahlantriebe. presented showing the chord- and spanwise temperature distributions EXPERIMENTAL INVESTIGATION ON A SINGLE-STAGE for an effusion cooled blade with different coolant flow distribution. AIR-COOLED GAS TURBINE The cooling effectiveness is investigated for various parametric W. Kuehl In AGARD High Temp. Turbines Jan. 1971 14 p changes and compared with that of an internally cooled blade. The refs aerodynamic behaviour reveals a considerable increase in profile Avail: NTIS HC$6.00/MF$0.95 loss coefficient of a porous turbine blade both with and without Temperature measurements made within the convection coolant effusion. The effect on overall engine performance by using air-cooled rotor blade of a gas turbine during operation cannot an effusion cooled high pressure turbine in a modern turbo-jet deliver complete information of the temperature field; for the number engine is briefly discussed. Author of measuring points is limited by technical considerations. But by using the analogy between the heat flux and the electric current within a three-dimensional model it is possible to determine the N71-173B3# Sussex Unlv , Brighton (England) School of Applled heat flow in a complete blade, i.e. the full temperature field within Sciences the blade and also the local gas side and coolant side heat transfer TRANSPIRATION-COOLED TURBINES coefficients. This paper describes the- way from temperature F J Bayley and A B Turner /n AGARD High Temp Turbines measurements at the turbine rotor to the complete temperature field Jan 1971 16 p refs within the rotor blade. Author Avail NTlS HC$6 00/MF60 95 The steps in the development chain of air cooling for gas turbine components and transpiretio~cooiiny are described The N71-17388*# Minnesota Univ , Minneapolis School of Mechanical th-ee modes of heat transfer involved in transpiration cooling (gas Aerospace Engineering side heat transfer coolant side heat transfer and interstitial heat FILM COOLING WITH INJECTION THROUGH HOLES transfer) are discussed separately Finally. consideration is given to E R G Ecken In AGARD High Temp Turbines Jan 1971 the practical problems of transpiration cooling in advanced gas 19 p refs Sponsored by NASA and the Navy turbines Author

(NASA-CR-116376) Avail NTlS CSCL21E Film cooling with ejection through a row or rows of holes N71-17384# Curtiss Wright Corp Wood-Ridge. N J is under consideration for gas turbine blades Discussed is an EXPERIENCE WITH TRANSPIRATION COOLED BLADES analytical approach to the prediction of the effectiveness of this S Lombard0 and S L Moskowiu (Sucola di Guerra Aerea) In cooling method developed in analogy to a method which proves AGARD High Temp Turbines Jan 1971 20 p refs successful for election through a slot and some experimental results which are compared with prediction obtained by this analysis Avail NTlS HCS600/MFS095 Author The propulsion system requirements of advanced aircraft necessitate incorporation of significant technological advances in the state-of-the-art of major components in the engine These N71-17389# Centre National de Recherches Metallurgiques Liege advances evolve from the use of advanced design concepts (Belgium) coupled with adequate testing to substantiate the performance and MEETING REQUIREMENTS FOR HIGH TEMPERATURE GAS durability through component and full scale engine testing TURBINESA CHALLENGE TO METALLURGISTS Achievement of high turbine inlet temperatures in turbine engines D Coutsouradis In AGARD High Temp Turbines Jan 1971 through the use of transpiration air-cooled turbine blades is 17 p refs considered Briefly reviewed are the various transpiration air-cooled Avail NTlS HC16 OO/MFSO 95 turbine blades evaluated This evaluation includes blade design Metallurgists involved in the development of materials for aspects modes of fabrication and materials of construction The high temperature gas turbines are challenged by problems of results of component and full scale engine testing, up to 3000 F increasing difficulty leading them to explore continually new areas (1650 c) are also Dresented Author Some of the current approaches used for the improvement of cobalt and nickel base alloys are reviewed and illustrated The scope N71-17386# General Electric Co.,Cincinnati. Ohio. is not limited to an increase in strength but also to insuring HIGH TEMPERATURE TURBINE DESIGN structural stability, hot corrosion resistance coatabilitv Processins

233 il N71-17390

variables such as hot deformation of normally cast alloys. controlled PROTECTION AFFORDED BY SEVERAL COMMERCIAL and directional solidification of conventional or eutectic type alloys. COATINGS ON TWO NICKEL-BASE ALLOYS powder metallurgy techniques are evaluated Author A R Stetson and v s Moore In AGARD High Temp Turbines Jan 197i 56 p refs (Contract NAS3-9401) (NASA-CR-116374) Avail NTlS CSCL 11 F Six commercially available aluminide coatings were evaluated N71-17390# National Gas Turbine Establishment. Pyestock by simulated turbine environmental testing The environment was (England) the combustion products of JP-5 fuel and air at 0 85 Mach Coating FIBRE STRENGTHENED NICKEL-BASE ALLOY performance was assessed by weight change and metallographic A W H Morris and A Burwood Smith In AGARD High Temp methods Electron microprobe X-ray analyses and to a limited Turbines Jan 1971 15 p refs extent, X-ray diffraction were carried out to identify phases and define Avail NTIS HC$6 OO/MF$O 95 compositional differences which could be related to performance The development and application of high temperature Types of aluminide coatings included in this evaluation program composites for gas turbine blading is discussed Of the currently were those containing significant quantities of (1) silicon. (2) available reinforcements examined. only tungsten-5% rhenium wire chromium applied either before or after the aluminum, and (3) affords acceptable stability in nickel-base alloys and a satisfactory ceramic material Coatings were also represented that were hyper- increase in stress-rupture strength but only by incurring a weight and hypo stoichiometric in the betaNiAl system In general. the penalty The maximum volume fraction reinforcement IS controlled coatings with the greatest initial aluminum reservoir (thickness) by composite density and blade geometry at the low levels provided the greatest protection Hyper- rather than hypo- imposed the advantage of reinforcement IS controlled by composite stoichiometric coatings appeared to provide longer protection at density and cooled blade If adopted fibre reinforcement is likely the maximum test temperature The substrate also influenced to be used in solid blades in engine stages where cooling IS coating performance with the coatings on 61900 showing con- prohibitive and then only as a selected area reinforcement Indeed sistently better performance than coatings on IN 100 Author the whole question of application may rest on the thermal fatigue behavior Laboratory tests on cylindrical specimens indicate very poor thermal fatigue crack resistance Application Of the newer low N71-17394# von Karman lnst for Fluid Dynamics Rhode density single crystal alumina fibre IS also discussed Author Saint-Genese (Belgium) APPLICATION OF FILM COOLING TO GAS-TURBINE BLADES N71-17391# Office National d Etudes et de Recherches C Liess and J Carnel In AGARD High Temp Turbines Jan Aerospatiales Paris (France) 1971 11 p refs THERMO-CHEMICAL PROTECTION OF REFRACTORY Avail NTI S HC $6 001 MF $0 95 SUPERALLOYS FOR AIRCRAFT GAS TURBINES The injection of a secondary flow into a high velocity main [PROTECTION DES SUPERALLIAGES REFRACTAIRES POUR stream was investigated The secondary flow was heated and TURBINES A GAZ AERONAUTIQUES PAR VOlE injected by a row of inclined holes into a main flow of ambient THERMO-CHIMIQUE] temperature The geometry of the inlection holes and the main flow Philippe Galmiche In AGARD High Temp Turbines Jan 1971 velocity corresponded to conditions encountered on real turbine 12 p refs In FRENCH ENGLISH summary blades After a brief review of the application of film cooling to gas turbine blades the results of the measurements are presented The Avail NTlS HC$600/MF$095 tests concerned the adiabatic wall effectiveness and the flow field A first part of the paper is devoted to a survey of the downstream of the injection holes The test results show that Lorrosion problems of refractory materials for gas turbines as they approximate two-dimensional flow conditions can be obtained not appear at present in the case of the most advanced superalloys far downstream of the holes provided that the spacing to diameter After recalling briefly the main protection methods of refractory ratio of the holes is small Author superalloys now in use or under study the second part of the paper describes the chromaluminization method that has been developed Author N71-17395# Arizona State Univ Tempe EVALUATION OF FILM COOLING PERFORMANCE ON N71-17392# Societe Nationale d'Etude et de Construction de GASTURBINE SURFACES Moteurs d'Aviation, Corbeil (France) D E Metzger J R Biddle and J M Warren In AGARD High MATERIALS DEVELOPMENT FOR HIGH TEMPERATURE Temp Turbines Jan 1971 10 p refs TURBINES [EVOLUTION DES MATERIAUX POUR Avail NTlS HC$600/MF$095 TURBINES A HAUTE TEMPERATURE] Film cooling of gas turbine components is often characterized Robert Brunetaud In AGARD High Temp Turbines Jan 1971 by relatively short cooled lengths and injection geometries which 8 p In FRENCH ENGLISH summary are dictated primarily by fabrication and stress considerations For Avail NTlS HC$6 00/MF$O95 many of the resulting configurations film cooling information based Turbine blades and vanes work in complex conditions with on adiabatic wall temperatures alone is inadequate for design creep, thermal fatigue corrosion erosion etc Base cobalt and base purposes In addition the complexity of the film cooling process nickel alloys are developed for these turbine parts in new makes extrapolation of results from one injection configuration to processes (vacuum melting vacuum 'precision casting unidirectional another uncertain A transient method is described that has been solidification) Spectacular advantages are possible with niobium used to rapidly assess the relative performance of various film alloys but the problems of niobium coatings are not resolved Low cooling configurations Advantages as well as inherent cycle fatigue has to be considered more than creep aspects in disk some disadvantages of the method are discussed The experimental facilities fabrication New techniques of isothermal forging or the use of wrought sintered products are indicated for the manufacturing of are described and typical results are presented for a variety of flush. angled injection ports Emphasis is placed on recent results modified alloys from materials used for blades Author obtained for high injection rates with variable injection angle where the heat transfer is dominated by the film flow and effective N71-17393*# Solar, San Diego. Calif heat transfer coefficients are much larger than those associated THE COMPOSITION. MICROSTRUCTURE AND with the primary flow alone Author

234 N71-1741 4

N71-17396# Rolls-Royce Ltd . Derby (England) Aero Engine illustrated Problems of this nature have recently been encountered Div and it is demonstrated how a means of overcoming such problems NOZZLE GUIDE VAN COOLING: THE STATE OF THE without resorting to expensive and time consuming rig testing can ART be provided Author G A Halls In AGARD High Temp Turbines Jan 1971 19 p ref Avail NTlS HC$600/MF$095 Reviewed is the present state of the art on air cooling N71-17401# National Gas Turbine Establishment. Pyestock of nozzle guide vanes for aircraft gas turbines It shows how the (England) design of the cooling system. and manufacturing techniques have SOME MECHANICAL DESIGN PROBLEMS OF TURBINE changed over the years to keep pace with increased turbine BLADES AND DISCS entry temperatures The compromise has gradually shifted towards J B Bullard and B B Baxendale In AGARD High Temp tailoring the design of the vane to operate within the Iimctatmns of Turbines Jan 1971 19 p refs available materials Author Avail NTlS HC$6 OO/MF $0 95 Internally air-cooled turbine rotor blades usually have a N71-17397# Societe Nationale dEtude et de Construction de non-uniform temperature dstribution The non-uniform stress pattem Moteurs d’Aviation. Villaroche (France) thus created is redistributed by creep occurring at different rates COOLING OF TURBINE DISTRIBUTION BLADES within the blade depending on the local value of stress and THROUGH IMPACT EFFECT [REFROIDISSEMENT DES temperature The effect of this process on the blade life is discussed AUBES DE DISTRIBUTEUR DE TURBINE PAR EFFET and experiments to check the validity of some of the assumptions D‘IMPACT] are described The stress patterns in rotating discs are modified E Bassinot In AGARD High Temp Turbines Jan 1971 I9 p when plastic strain occurs dependent on the strain-hardening refs In FRENCH characteristics of the disc material This places limitations on the use Avail NTlS HCf600/MF$O95 of conventional material properties as design data These limitattons One of the improved methods for turbine cooling is the and the effect of the material stress-strain curve on stress utilization of the impact effect in generating a discharge flow that redistribution are discussed Author allows very sensitive temperature corrections Discussed are experimental studies that use slotted blades surfaces for distributing N71-?7402# Air Force Systems Command Wright-Patterson cooling air through tmpacting pressure and theoretcal calculatcons of AFB. Ohio the effects of certain parameters on the impact The expenmental AIR FORCE AERO PROPULSION LAB. AIR-COOLED blade consisted of a heat resistant exterior shell and an inner lining TURBINE DESIGN CRITERIA that sewed as distributor of the cooling air and guided it into the Jack Richens In AGARD High Temp Turbines Jan 1971 6 p convective cooling regions The functmnal motor pressure provided the impact effect It is concluded that this improved impact cooling Avail NTlS HC$6 00/MF$095 method is suitable for distributing blades of advanced A new technology for gas turbine engines is developed turbomachinerv Transl by G G and applied in new engines In order to accomplish thiq B phased develoomwt cycle Cas been established that permits high levels of risk in the early stages of development reducing to low levels N71-37398# Gffice National d’Etudes et de Recherches of risk prior to commitment of the substantial resources necessary Aerospatiales. Paris (France) for development for production The development cycle with COOUNG OF TURBINE BLADES BY LIQUID METALS particular attention to the design or Selection criteria that have been or [REFROIDISSEMENT DES AUBES DE TURBINES PAR LES are being successfully applied to air-cooled turbines is described METAUX UQUIDES] Author E Le Grives and J Genot In AGARD High Temp Turbines Jan 1971 20 p refs In FRENCH. ENGLISH summary

Avail NTlS HC$600/MF$095 N71-17404# Societe Nationale d’Etude et de Construction de Mass transfer conditions m thermosyphon or evaporative Moteurs dAviation, Villaroche (France). cycles under high centrifugal acceleration are first briefly analyzed TECHNOLOGICAL ASPECTS OF TURBINE BLADE Sodium potassium alloys are shown to be best suited on account COOLING BY AIR FILM [LES ASPECTS TECHNOLOGIQUES of their heat transfer ability with air cooled exchangers at the blade DU REFROIDISSEMENT DES AUBES DE TURBINE PAR roots A high rotation speed test set-up on which the heat flux on FILM D‘AIR] the blades is comparable to that of a real turbine has been Jacques M. Bertrand In AGARD High Temp. Turbines Jan. extensively used for an experimental study of these processes Both 1971 18 p cycles lead to a temperature drop as high as 650 C at the blade Avail: NTlS HC$6.00/MF$0.95 tips. with a mass flow rate of cooling air of 10 g per sec kW Technological aspects of placing coding air emissii holes m However, several advantages are shown to be expectable for the turbine Made tip pottions are considered by evaluating mechanical evaporative cycle in view of its application to high temperature gas blade resistance. internal duct organization resulting in an air film. turbine cooling Author and fabrication methods suitable for multiple cooling. Theoretical and experimental studies of the operatbnal problems connected with the multiple hole cooling method for turbine blades prove the validity of the concept for application in technically advanced turbo N71-17- Rolls-Royce. Ltd . Derby (England) Aero Engine machinery. Transl. by G.G. Div THERMAL FATIGUE (FILM) In AGARD High Temp Turbines Jan 1971 9 p N71-17414*# National Aeronautics and Space Administration. Lewis Research Center. Cleveland. Ohio. Avail NTlS HC$600/MF$O95 PERFORMANCE OF A SHORT MODULAR TURBOJET The incidence of thermal fatigue in cooled tuhine blades is COMBUSTOR SEGMENT USING ASTM-A1 FUEL

235 N71-17415

Richard W Niedzwiecki and Harry M Moyer Washington Feb several sample cases, and a listing of the FORTRAN computer 1971 33 p refs program. Author (NASA TN-D 6167 E-5726) Avail NTlS CSCL 21 E A 27-inch long recectangular combustor segment consisting of an array of 48 combustor modules was tested to determine its N71-17425*# National Aeronautics and Space Administration performance Each module mixed and swirled fuel with air and Langley Research Center Langley Station. Va stabilized combustion Test conditions were inlet temperatures of SOME TRANSONIC AND SUPERSONIC DYNAMIC 600 and 1150 F a pressure of 3 atmospheres and reference STABILITY CHARACTERISTICSOF A velocities to 160 ft/sec Results were combustion efficiencies of VARIABLE-SWEEP-WING TACTICAL FIGHTER MODEL 100 percent a pressure loss of 5 4 percent for an inlet Mach number Robert A Kilgore Washington Feb 1971 45 p refs of 0 25 a heat release rate of 11 860 000 Btu per (hr)(ft3)(atml (NASA-TM-X-2163 L-7428) Avail NTlS CSCLOl c for a temperature ratio of 2 5 and pattern factor spans of 0 30 Wind-tunnel tests were made by using a small-amplitude to 0 37 and 0 22 to 0 28 with 600 and 1150 F inlet air forced-oscillation mechanism to determine the damping and temperatures respectively Altitude blowout and relight data as well oscillatory stability in pltch and in yaw and the effective-dihedral as a Comparison of results with a longer combustor are also parameter at angles of attack from about -5 deg to 17 deg at included Author Mach numbers from 040 to 2 50 The effect of individual model components tail incidence, and wing-sweep angle was investigated The data are presented without analysis Author N71-17415*# National Aeronautics and Space Administration Langley Research Center Langley Station Va AERODYNAMIC DAMPING AND OSCILLATORY STABILITY N71-17426*# Boeing Co Seattle Wash IN PITCH AND YAW OF A VARIABLE-SWEEP SUPERSONIC STUDY AND DEVELOPMENT OF TURBOFAN NACELLE TRANSPORT CONFIGURATION AT MACH NUMBERS MODIFICATIONS TO MINIMIZE FAN-COMPRESSOR NOISE FROM 0 40 TO 1 80 RADIATION VOLUME 5 SONIC INLET DEVELOPMENT Robert A Kilgore Washington Feb 1971 30 p refs Contractor Report, 1 May 1967 1 Nov 1969 (NASA TM-X-2164 L-7429) Avail NTlS CSCLOlC Washington NASA Jan 1971 121 p Wind-tunnel measurements have been made with wing (Contract NAS1-7129) leading-edge sweep angles of 25 deg at Mach numbers of 040 (NASA CR 1715) Avail NTlS CSCLOlC and 0 80 50 deg at Mach numbers of 0 80 0 90 1 00 and 1 20 Several sonic throat inlet concepts were investigated as and 75 deg at a Mach number of 180 The investigation was a means of reducing the forward-radiated fan noise of turbofan made at an oscillation amplitude of about 1 deg by using a JT3D powered 707 320B/C airplanes The acoustic internal forced-oscillation technique The effects of horizontal and vertical aerodynamic and operational characteristics of a selected contracting tails as well a5 the effect of horizontal tail height were investigated cowl inlet were evaluated in model and full scale ground rig tests The engine inlets were blocked since internal flow throuqh the Statis and in flight inlet operation was simulated for both the engines could not be simulated In order to determine qualitatively noise suppressed and unsuppressed modes of operation Tests were the effect of blocking the engine inlets tests were also made with conducted for a range of engine speeds inlet Mach numbers a confiquration having an ogive nose Author throat areas and boundary layer control configurations with both fixed and variable geometry inlets Results are presented for fan noise attenuation Mach number distributions total and static pressure recovery and effects on engine operation Results are shown also N71-17423*# National Aeronautics and Space Adminlstration for the dynamic response characteristics of the inlet and engine Langley Research Center Langley Station Va while operating with the inlet under automatic control At simulated FLIGHT INVESTIGATION OF A V/STOL TRANSPORT landing approach conditions the results indicate that a 14- to MODEL WITH FOUR POD-MOUNTED LIFT FANS 16 PNdB reduction of fan noise from the inlet was achieved with William J Newsom Jr and Sue 8 Grafton washington Feb inlet center line Mach numbers of 0 7 to 0 8 Principal airplane 1971 32 p refs performance penalties appear ti) be associated with the increased (NASA TN-D 6129) Avail NTlS CSCLOlC weight and drag of the acoustic nacelles Author The investigation consisted of free flight model tests in hovering and forward flight through the transition speed range up to the point where conversion would be wingborne flight Dynamic N71-17432# Advisory Group for Aerospace Research and stability characteristics of the model were also calculated for Development Paris (France) correlation with flight results Because of a small static margin and MANUAL ON AEROELASTICITY. SUBJECT AND AUTHOR speed instability artificial damping in pitch was needed to obtain INDEX satisfactory pitch characteristics No problem was experienced with E C Pike. ed Jan 1971 28 p refs roll or yaw through the transition speed range Author (AGARD-R-578-71) Avail NTlS The Subject Index and Author Index cover all the chapters in the six loose-leaf volumes of the Manual on Aeroelasticity and were up to date in April 1970 Since that date new chapters of N71-17424*# National Aeronautics and Space Administration the manual have been published in the AGARD Report series The Langley Research Center Langley Station Va Indexes are published in two forms in the AGARD Report series VORTEX-LATTICE FORTRAN PROGRAM FOR ESTIMATING as AGARD Report 578 and in loose-leaf form for insertion in SUBSONIC AERODYNAMIC CHARACTERISTICS COMPLEX Volume VI of the Manual Entries are given by volume chapter and PLANFORMS page number For example 11/9/56 denotes Volume I1 Chapter 9 Richard J Margason and John E Lamar Washington Feb 1971 page 56 The letter S after a chapter number denotes a supplement 141 p refs to that chapter The letters TG denote the section of tables and (NASA TN D 6142 L 7262) Avail NTlS CSCLOlA graphs in Volume VI The abbrevlation INTRO denotes the A computer program was developed for estimating the introductory survey in Volume I Author subsonic aerodynamic characteristics of complex planforms The program represents the lifting planform with a vortex lattice The material presented is intended as a users guide and includes a N71-17433*# National Aeronautics and Space Administration study of the effect of vortex lattice arrangement on computed results Langley Research Center. Langley Station. Va

236 N7 1- 17483

SIMULATOR STUDY OF FLIGHT CHARACTERISTICS OF A (NASA-TN-D-6077. M-165) Avail NTlS CSCL 20D JET-FLAP STOL TRANSPORT AIRPLANE DURING The feasibility of measuring statistical properties of supersonic APPROACH AND LANDING aerodynamic turbulence by statistical correlation of signals remotely William D. Grantham. Robert W. Sommer. and Perry L. Deal retrieved by optical probing without the use of tracers was Washington Feb. 1971 42 p refs investigated Theoretical analyses and qualitatwe experimental results (NASA-TN-D-6225: L-7582) Avail. NTlS CSCL 01C are presented concerning the application of laser schlieren and A fixed-base simulator study was conducted to provide laser shadow-correlation remote sensing systems Cross-correlation a preliminary determination of the low-speed handling qualities of measurements made on-line with parallel and crossed beams are a STOL transport configuration equipped with an external-flow iet shown and discussed A one-shot statistical correlation concept IS flap and high-bypass-ratio turbofan engines. Real-time digital introduced and experimentally verified that allows the time-history simulation techniques were used. The computer was programmed of the decay of turbulent structures to be computed from a single with equations of motion for six degrees of freedom and the composite signal and displayed on an oscilloscope while data are aerodynamic inputs were based on measured wind-tunnel data. A being retrieved Author visual display of a STOL airport was provided for simulation of the flare and touchdown characteristics. The primary piloting task was an instrument approach to a breakout at a 200-fool ceiling. with a visual landing. Author N71-17468*# Scientific Translation Service Santa Barbara Calif THE AIRFOILTHEORY Caius Jacob Washington NASA Feb 1971 16 p refs Transl N71-17441*# Scientific Translation Service. Santa Barbara. Calif. into ENGLISH from Proceedings of the 8th Symp on Advanced ESTABLISHMENT OF TAKE-OFF AND LANDING SAFETY Probl and Methods in Fluid Dyn (Tarda) 18 -25 Sep 1967 MARGINS FOR THE BREGUET 941 [ESTABLISSMENT p 35-43 DES MARGES DE SECURITE AU DECOLLAGE ET A (Contract NASw-2035) L’ATTERRISSAGE POUR LE BREGUET9411 (NASA-TT-F- 13471) Avail NTlS CSCL 20D J. Bastidon Washington NASA Feb. 1971 15 p Transl. into The thin airfoil theory is discussed by taking into account ENGLISH from Proc. of the 37th Meeting of the AGARD Flight the solution of a harmonic Dirichlet problem for the complex plane Mech. Panel. (Baden Baden). 20 -23 Oct 1970 6 p The function representing the solution of this problem is (Contract NASw-2035) investigated The results obtained make it possible to resolve direct15 (NASA-IT-F-13453) Avail: NTlS CSCLOlC the Dirichlet problem for the harmonic function considered ?he Two types of safety margins are considered: (1) speed explicit solution of the problem of the thin airfoil is discussed and margins (take-off speed and approach speed). and (2) field length an example for the determination of the complex velocity is margins. These two types of margins are examined and discussed presented Author from the point of view of one individual aircraft. the BR 941. The establishment of these margins depends on theoretical consideration, results of in-flight measurements, and operational tests. Discussions with the F.A.A. are also taken into consideration with respect to N71-17475# National Transportation Safety Board Washington. establishing special considerations for civil certification of this DC aircraft. Author AIRCRAFT ACCIDENT hEPORTS: BRIEF FORMAT: US CIVIL AVIATION, ISSUE NO. 5: 1969 ACCIDENTS N71-17443*# Techtran Corp Glen Burnie. Md Nov 1970 450 p FLOW WITH A SEPARATED SHOCK WAVE PAST A INTSB-BA-70-6) Avail NTIS. HC$6 OO/MF$O 95 WEDGE-SHAPED PROFILE [OBTEKANIYE KLINOVIDNOGO Statistical tables and accident briefs are presented on general PROFILYA S OTSOEDINENNOY UDARNOY VOLNOY] aviation and supplemental air carrier accidents NEN V G Bukovshin Washington NASA Feb 1971 6 p refs Transl into ENGLISH from Izv Akad Nauk SSSR Mekh Zhidk Gaza (USSR). no 2. Mar Apr 1969 p 83-85 (Contract NASw-2037) N71-17476# National Transportation Safety Board Washington. (NASA-TT-F-13469) Avail NTlS CSCL 200 DC A supersonic gas flow past a wedge at zero degree angle AIRCRAFT ACCIDENT REPORT: TEXAS INTERNATIONAL of attack and with a separated shock wave is analyzed by the AIRLINES, INCORPORATED, DOUGLAS DC-9, N1308T. integral relations method Numerical values are given for the velocity HARUNGEN, TEXAS, 11JANUARY 1970 gradient at the stagnation point and for distribution of pressure and 2 Dec 1970 25 p refs drag at the wedge at Mach numbers from 3-20 and semiapex (NTSB-AAR-70-28) Avail NTlS angles from 60- 85 deg These values are compared with values The investigation report is presented for the accident in obtained by the Newtonian theory and by a modified formula of which the aircraft struck a tree and two power poles 12.000 feet Newton The values obtained by the integral relations method for short of the runway threshold during a predawn instrument pressure distribution and drag coefficient differ significantly from the approach in fog It was concluded that the probable cause was the values obtained by the Newtonian formulas The velocity gradient continuation of descent through the minimum descent altitude as increases with an increase of Mach number and a decrease of the a result of inadequate crew monitoring of altimeters Contributing semiapex angle Author factors were a lack of awareness of the actual meteorological conditions. caused by crew fatigue and company workload priorities which prevented normal communications and deferred the dissemination of essential meterorological information Author N71-17444*# National Aeronautics and Space Administration Marshall Space Flight Center Huntsville. Ala OPTICAL PROBING OF SUPERSONIC AERODYNAMIC TURBULENCE WITH STATISTICAL CORRELATION. PHASE N71-17483# National Aviation Facilities Experimental Center, 1 : FEASIBILITY Atlantic City, N J B H Funk. Jr and H A Cikanek. Jr Washington Feb 1971 INVESTIGATION OF JET ENGINE COMBUSTION CHAMBER 143 p refs BURN-THROUGH FIRE Final Report, 1963 -1969

237 N7 1- 1 7506

Thomas Rust Jr Mar 1971 49 p refs AIRLINES, INCORPORATED. CONVAIR 580, N2W5, O'HARE (FAA-RD-70 68. FAA NA 70-401 Avail NTlS INTERNATIONAL AIRPORT. CHICAGO, ILLINOIS, 27 Test conditions for testing materials which are intended for DECEMBER 1968 use as fire barriers for protection against a let engine combustion 12 Nov. 1970 52 p chamber burn-through type of failure are presented The (NTSB-AAR-70-27) Avail. NTlS development of such a failure was accomplished on a General North Central Airlines. Flight 458. a Convair 580. crashed Electric J-47 let engine The resulting flame was quite severe while it was on an instrument approach at O'Hare International penetrating the present standard firewall material in 2 seconds Airport, Chicago, Illinois. at approximately 2022 c.s.t.. on December Studies were made of the flame impingement characteristics 27, 1968. The aircraft struck the side of a hangar. located adjacent including impingement temperatures and pressures and various to the approach end of the runway. in a near-inverted attitude, and potential firewall materials were tested for effectiveness as fire was destroyed by impact and resultant ground fire Twenty-seven barriers for protection against such a failure Most materials tested of the 45 persons on board the aircraft. including the pilot, copilot. in this manner failed to provide adequate protection against such an and an additional crewmember who was occupying the observer's engine failure An investigation was conducted toward development seat, were fatally injured. One person in the hangar also received fatal of a means of simulating a combustion chamber burn-through injuries as a result of the accident. The National Transportation failure with the ultimate goal of developing a suitable laboratory test Safety Board determines that the probable cause of this accident was flame for evaluating potential firewall materials A combustion spatial disorientation of the captain precipitated by atmospheric chamber simulator which will produce a flame of similar severity refraction of either the approach lights or landing lights at a critical to the flame produced in the J 47 engine was developed point in the approach wherein the crew was transitioning between Author flying by reference to flight instruments and by visual reference to the ground Author

N71-17506*# National Aeronautics and Space Administration Lewis Research Center, Cleveland, Ohio N71-17524# Laboratorium fur Betriebsfestigkeit Darmstadt (West ANALYTICAL HEAT TRANSFER INVESTIGATION OF Germ any ) INSULATED LIQUID METHANE FUSELAGE TANKS FOR STRENGTH OF LIGHT METAL ALLOY RODS WITH SUPERSONIC CRUISE AIRCRAFT IRREGULAR NOTCHES UNDER CYCLIC TENSILE LOADS Eugene J Pleban Washington Feb 1971 15 p refs A N D P ER I 0 D I CA L LY I NTE R SPE R SE D C 0 MP R ESSI 0 N (NASA-TN-D-6157, E-5910) Avail NTlS NTlS CSCL2OM LOADS [ZUR FRAGE DES FESTIGKEITSVERHALTENS Liquid methane boiloff from fuselage tanks was computed REGELLOS IM ZUG-SCHWELL-BEREICH BEANSPRUCHTER for typical SST missions for cruise Mach numbers of 2 7 and 3 5. GEKERBTER LEICHTMETALLSTAEBE BE1 PERlODlSCH insulation thicknesses of 0 5 1 0. and 2 0 in, various vent pressure EI NG ESTR EUTE N D R U CKBE LASTU NG EN] settings, and saturated and subcooled fuel Boiloff rates during fuel E Haibach D Schuetz and 0 Svenson Fraunhofer Ges Mar fill and ground hold are discussed Boiloff losses less than 2 5 1970 25 p refs In GERMAN ENGLISH summary Sponsored percent are possible for a cruise Mach number of 2 7 and an by Deut Forsch Gerneinschaft insulation thickness of 10 in Author (FB-78.1969) Avail NTlS The cyclic plastic strains and stresses occurring at the notch root during a typical flight-by-flight load sequence were used to study the effect of the ground to air cycle on the fatigue life Local N71-17511# National Transportation Safety Board. Washington. stress histories were determined by recording local strain histories D.C. during cycling and reproducing these histories in simple unnotched 2024 material specimens Author IESRO) AIRCRAFT ACCIDENT REPORT: EXECUTIVE JET AVIATION INCORPORATED LEAR JET U3A. N434W NEAR THE EMMET COUNTY AIRPORT PELLSTON. MICHIGAN, N71-17527# National Aviation Facilities Experime a1 Center 9 MAY 1970 Atlantic City N J 22 Dec. 1970 31 p ref FIELD TEST AND EVALUATION OF THE NAS EN ROUTE (NTSB-AAR-7 1-3) Avail. NTlS STAGE A MODEL lb WEATHER SUBSYSTEM Final Report, On May 9, 1970, Lear Jet N434EJ. .operated by Executive Feb. -Nov. 1969 Jet Aviation. Inc, was on a nonscheduled air taxi flight from Howard L McFann Mar 1971 122 p Detroit, Michigan to Pellston. Michigan. The aircraft crashed at (FAA-NA-70-62) Avail NTlS approximately 2128 during an instrument approach to the Emmet Four weather outline generators produced contours around County Airport at Pellston. Both crewmembers and the four radar weather clutter at two different intensity levels The contours passengers aboard received fatal injuries. The aircraft made initial were processed by the radar video digitizers for transmission to air contact with trees on a hill located approximately 2-1/4 miles route traffic control centers as weather map messages A series southwest of the approach end of Runway 5. A swath approximately of technical and operational tests were run in the field to obtain 45 feet wide and 254 feet long. on a true heading of 107 deg, performance data pertinent to the preparation of specifications for had been cut through the trees by the aircraft The highest mean future systems Calibration methods and trouble shooting aids were sea level (m.s.1.)elevation of the trees at the break points was E86 established It was concluded that the generators were capable of feet. The Board determines the probable cause of this accident to producing reliable contours around the periphery of clutter without be illusions produced by the lack of visual cues during a circling interference from aircraft signal returns The dynamic range of the approach over unlighted terrain at night to a runway not equipped systems. when using logarithmic video inputs, was sufficient to with approach lights or other visual approach aids These illusions. permit contouring of weather cells from 42 to 50 db above the which made the pilot think that he was higher than his true radar receiver minimum discernible signal levels Effective control of position. were made more acceptable to him because of a strong weather map data rates was achieved by a sampling and possibility of an erroneously high indication on his altimeter. interleaving technique that transmitted outer contour data every 8 4 Author deg and inner contour data every 2 1 deg Author

N71.17512# National Transportation Safety Board. Washington, N71-17646# Department of Transportation. Washington. D.C. D.C. Office of Supersonic Transport Development. AIRCRAFT ACCIDENT REPORT: NORTH CENTRAL SUPERSONIC TRANSPORT DEVELOPMENT

238 N71-17591

ENVIRONMENTAL IMPACT STATEM E NT N71-17585* National Aeronautics and Space Administration. 7 Dec. 1970 34 p Goddard Space Flight Center. Greenbelt, Md. Avail: NTlS ANGULAR POSITION AND VELOCITY SENSING A discussion is presented concerning the knowledge that APPARATUS Patent is now possessed and that which will be required in order to Leo J Veillette. inventor (to NASA) Issued 17 Mar. 1970 (Filed determine the environmental impact of supersonic transports. Current 28 Jul. 1967) 13 p CI. 318-138; Int. CI. H02p7/28 research directed at the major environmental concerns is briefly (NASA-Case-XGS-05680, US-Patent-3.501.664: summarized and covers the following areas (1) airport and US-Patent-AppCSN-656953) Avail: US Patent Office CSCL 148 community noise, (2) weather and climate modification. (3)cosmic A system is described for regulatlng brushless DC motors radiation. and (4) sonic booms. The present status of U.S. plans of the type where an internal stator field is rotated in space 90 for development of the SST is reviewed and alternatives for future deg ahead of the rotor field. To maintain the correct spatial relation direction of efforts are discussed. D.L.G. between the stator and rotor fields. the angular position of the rotor is continually sensed and the position indication is used to continually change the stator field orientation as the rotor rotates. N71-17546# Federal Aviation Administration. Washington. D.C. The rate of rotation of the rotor is also determined to provide Airports Service. controlled-damping and rate-limiting of the motor. PLANNING THE METROPOLITAN AIRPORT SYSTEM Official Gazette of the U.S. Patent Office May 1970 11 1 p refs Original Contains Color Illustrations (FAA-AC-150/5070-5) Avail: SOD$1.25 A systematic approach to planning for the nation’s airport N71-17589*# National Aeronautics and Space Administration. needs is presented The metropolitan airport system planning Lewis Research Center. Cleveland. Ohio. process involves the preparation of both broad and specific policies, TWO-DIMENSIONAL CASCADE TEST OF A JET-FLAP plans. and programs needed to establish a viable. integrated TURBINE ROTOR BLADE network of airports at the metropolitan level The planning process Stanley M. Nosek and John F. Kline Washington Feb. 1971 is described in detail under the following chapter headings: (1) 18 p refs organization for the planning process. (2) funding the planning (NASA-TM-X-2183: E-5989) Avail: NTlS CSCL 21 E process, (3) general criteria and policy objectives. 14) study design, A jet-flap turbine blade was tested in a two-dimensional (5)inventories. (6) forecasting. (7) consideration of new technology, cascade of six blades to study the effectiveness of the concept as (8) general facility requirements. (9) development of alternative a boundary-layer control device and as a variable-area device. system plans. i 10) plan implementation. and (11) the continuing Principal measurements were surveys of blade surface static pressure and blade exit total pressure, static pressure. and flow angle at =!anmng process D.L.G. midspan. Data were taken at constant pressure ratio for jet flows from 0 to 4 percent of primary flow. Results are presented in terms of primav flow, blade surface pressure distribution. blade specific N71-17553# Federal Aviation Administration. Washington D C force, kinetic energy loss coefficient. total pressure loss. and exit Flight Standards Service flow angle. Author TENTATIVE AIRWORTHINESS STANDARDS FOR POWERED LIFT TRANSPORT CATEGORY AIRCRAFT Aug 1970 144 p N71-17590*# h/stmqai .A.ermau:ics and Space Aaniinistrarion. Avail NTlS Lewis Research Center, Cleveland, Ohio Tentative airworthiness standards are presented which are COLD-AIR INVESTIGATION OF A TURBINE WITH intended for study trial application and comment during the TRANSPI RATION-COOLED STAT0 R BLADES. 2: design and development of verticraft and other powered lift aircraft PERFORMANCE OF STATOR WITH WIRE-MESH SHELL Because of the wide variety of novel features of these emerging BLADING aircraft and lack of experience in their certification and operation. Frank P. Behning. Herman W. Prust. Jr.. and Thomas P. Moffin the proposed standards are not expected to be appropriate for all Washington Feb. 1971 28 p refs designs However the tentative standards are aimed at providing (NASA-TM-X-2166: E-5939) Avail: NTlS CSCL 21 E useful guidelines for designers and the FAA in arriving at the The effects on stator performance of transpiration coolant acceptable level of airworthiness Author discharge from wire-mesh shell blading were experimentally determined for ratios of coolant flow to primary flow of 0 to 0.07. The results showed that transpiration coolant discharge from this type of blading caused an efficiency loss relative to comparable N71-175!54*# National Aeronautics and Space Administratmn noncooled blading The results for transpiration discharge from Lewis Research Center. Cleveland. Ohio wire-mesh shell blading are similar to results previously obtained for PERFORMANCE OF AN AUXILIARY INLET EJECTOR transpiration discharge from discrete hole blading. A comparison of NOZZLE WITH FLOATING INLET DOORS AND FLOATING the effects on stator efficiency of transpiration discharge and SINGLE-HINGE TRAILING-EDGE FLAPS trailing-edge discharge shows a significantly larger loss for AlbertL Johns Washington Feb 1971 45 p refs transpiration discharge. Author (NASA-TM-X-2173- E-5883) Avail NTlS CSCL2lA A nozzle designed for a supersonic-cruise aircraft was tested at off-design Mach numbers from 0 to 10 Two primary throat areas were tested one to simulate both dry acceleration and N71-17591*# Boeing Co, Seattle. Wash subsonic cruise. and the other to simulate reheat acceleration Tha STUDY AND DEVELOPMENT OF TURBOFAN NACELLE auxiliary inlet doors included single- and double-hinge types which MODIFICATIONS TO MINIMIZE FAN-COMPRESSOR NOISE were free-floating either with or without synchronization Results RADIATION. VOLUME 2: ACOUSTIC LINING from this cold-flow model are compared with a similar nozzle DEVELOPMENT, 1 MAY 1967 - 1 NOVEMBER 1969 which was optimized using fixed inlet doors and flaps The inlet Washington NASA Jan 1971 184 p refs doors and trailing edge flaps did not float to the maximum (Contract NASl-7 129) thrust condition at subsonic-cruise Mach numbers In addition. the (NASA-CR-1712) Avail NTlS CSCLOlB single-hinge flaps were unstable at many of the assumed flight An acoustic lining development program is described. which conditions Author covers selection of facing materials and lining concepts suitable for

239 N71-17610 attenuating turbofan engine noise generated by a fan compressor placed performance goal achievement above minimum weight and development of acoustic lining design technology. A theoretical considerations The estimated airplane empty weight increase of a method for predicting lining attenuation in a duct without airflow weight-oriented production design is 3 140 Ib Four nacelles were is presented and is combined with an empirical prediction fabricated and each was subjected to ground calibration testing method developed from parametric results of the flow-duct tests to Compared to baseline ground test results of an existing 707 establish a lining design procedure. Concurrent and interrelated airplane nacelle, static takeoff thrust of the flighworthy nacelle was investigations, which comprised the acoustic lining development shown to be essentially unchanged. with 2 percent less fuel program, are described as is the facilities equipment used. Evaluation consumption at cruise Attainment of the 15-PNdB reduction in of more than 40 types of acoustic facing materials resulted in the perceived noise level set as a program goal for flight operations was selection of woven metallic fiber. metallic felt. reinforced metallic indicated Author felt, and resin impregnated fiberglass laminate facing materials as most suitable for acoustic linings in a turbofan nacelle environment. A study of lining concepts resulted in selecting a broadband N71-17686; Technidyne. Inc, West Chester, Pa resistive-resonator type lining as best suiting engine-fan-duct and METHODS AND APPARATUS EMPLOYING VIBRATORY inlet-installation requirements. Results are presented of analytical ENERGY FOR WRENCHING Patent and experimental investigations undertaken to develop an acoustic Nicholas Maropis. William A. Wilson. and Herman T Blaise. lining design procedure and to select suitable lining concepts and inventors (to NASA) Issued 1 Sep. 1970 (Filed 7 Dec 1967) materials for reducing fan-compressor-generated noise in turbofan 10 p CI. 29-428: Int. CI. B23pl 1/00, 19/00, 19/04 engines. A comprehensive acoustic-lining flow-duct test program Continuation-in-part of US-Patent-Appl-SN-674999. Filed 12 Oct. established the parameters controlling the amount and peak frequency 1967 Sponsored by NASA of attenuation provided by a lining Test results also showed (NASA-Case-MFS-20586: US-Patent-3,526.030: metallic and nonmetallic linings. having the same flow resistance US-Patent-Appl-SN-688868) Avail: US Patent Office CSCL 131 and geometry. provide similar attenuation characteristics Author A wrench is described for applying vibratory energy primarily to mechanical fasteners which are elastically compliant along the radius vector so as to effect improved tightening or loosening of N71-17610* National Aeronautics and Space Administration. fasteners. The direction of the particle motion constituting the Langley Research Center, Langley Station, Va. introduced vibration is essentially along the radius vector of the THERMAL PUMP-COMPRESSOR FOk SPACE USE Patent fastener to which the vibration is introduced Provision is made for Franklin W. Booth and Hubert K. Clark. inventors (to NASA) tightening the fastener to a predetermined specified torque level Issued 14 Mar. 1967 (Filed2 Apr. 1963) 4 p CI. 230-162 and for applying the requisite vibratory energy while simultaneously (NASA-Case-XLA-00377: US-Patent-3.309.01 2; rotating the fastener an additional amount without extending the US-Patent-Appl-SN-2701 18) Avail. US Patent Office CSCL 20M said torque level. Official Gazette of the U S Patent Office A thermal pump-compressor for converting solar energy is described. The energy is converted into air pressure to operate pneumatic equipment The pump comprises a solar reflector, a N71 17697# Committee on the District of Columbia (U S Senate) thermal bulb containing a volatile liquid for creating gas pressure, UTILIZATION AND FUTURE OF MAlOR AIRPORTS IN and a numping means. E.C. THE NATIONAL CAPITAL REGION PART 2 STRETCH JETS AT NATIONAL AIRPORT Washington GPO 1970 175 p refs Hearings before Comm 19 May 1970 N71-17641 '# National Aeronautics and Space Administration on the District of Columbia 91st Congr 2d Sess Lewis Research Center Cleveland Ohio Avail Subcomm on Business and Commerce COMPUTER PROGRAM FOR PRELIMINARY DESIGN AND Discussions in support of and against permitting Boeing ANALYSIS OF V'STOLTIP-TURBINE FANS 727 jets to land at Washington National Airport are presented Henry C Haller Seymour Lieblein and Bruce M Auer Washington Specific problems associated with the let use of the airport overall Feb 1971 143 p refs impact on affected and other airlines phasing controls premium (NASA TN-D 6161 E-5660) Avail NTlS CSCL2lE fees and community relations are covered A study of the An analysis of a tip turbine driven lift fan was developed for Baltimore/Washington biregional air facilities plan and program and use in preliminary design or parametric investigation of tip-turbine a staff information report on the current and future prospects problems and needs of the National Airport are included N E N lift fan systems applicable to V/STOL aircraft The analysis was programmed for an electronic digital computer with provisions for treating a fan rotor with either one or two-stage tip turbines mounted on the fan periphery Both turbine types have tmpulse N71-17702 Stanford Univ, Calif rotors with single stage designs employing impulse diffusing or no AN EXPERIMENTAL STUDY OF THE EFFECTS OF exit stators The program includes tip-turbine velocity diagram LEADING-EDGE BLOWING UPON THE CHARACTERISTICS determination blade row loss analysis partial admission and OF AJET-FLAPPED AIRFOIL turbine to fan leakage A sample calculation is given Author Timothy Wang (Ph D Thesis) 1969 166 p Avail Univ Microfilms HC $7 80/Microfilm $3 00 Order NO 70- 1624 N71-17668*1 Boeing Co Seattle. Wash The extent to which maximum lift and stalling angle can STUDY AND DEVELOPMENT OF TURBOFAN NACELLt be increased by diverting a portion of the jet flap momentum efflux MODIFICATIONS TO MINIMIZE FAN-COMPRESSOR NOISE through a leading edge blowing slot is discussed The basic wing RADIATION. VOLUME 4: FLIGHTWORTHY NACELLE model tested has a 1 ft chord a 2 ft span a truncated NACA DEVELOPMENT. 1 MAY 1967 1 NOVEMBER 1969 001 5 profile (thickness of 18 percent chord) and an 8 3 percent Washington NASA Jan 1971 192 p refs chord trailing edge flap incorporating shroud blowing Two nose (Contract NAS1-7129) configurations one having a blowing slot at the leading edge and (NASA-CR-1714) Avail NTlS CSCLOlB the other having a blowing slot at 112 percent chord were tested A flightworthy configuration of the treated inlet and fan exhaust with the model A full span slide valve within the model enabled duct resulted from further development of acoustic. aerodynamic. diversion of up to approximately 113 of the total let momentum and structural design of the nacelle concept developed and tested efflux through the nose slot Substantial increases in stalling Both the desiqn and manufacturing processes that developed avle and maximum lift were achieved with the incorporation of

240 N71-17753 leading-edge blowing For the same total jet momentum coefficient. N71-17747# Air Force Systems Command. Wright-Patterson flap deflection. and angle of attack. the addition of leading-edge AFE. Ohio Foreign Technology Div. blowing was found to increase the nose-down quarter chord CERTAIN PROBLEMS OF STRUCTURAL SYNTHESIS OF pitching moment. the fraction of jet momentum recovered as thrust, SPATIAL MOTION CONTROL SYSTEMS FOR AN ORBITAL and the lift of a jet-flapped airfoil Dissert Abstr AIRCRAFT IN THE EARTH’SATMOSPHERE E. N. Petrov et al 13 Aug. 1970 23 p refs Transl. into ENGLISH from 4th Congr. Guidance and Control in Space, Intern. Federation of Autom. Control (Warsaw). 1969 p 3- 18 N71-17725 Alabama Univ University . (AD-714796: FTD-HT-23-392-70) Avail: NTlS CSCL 22/1 THE EFFECT OF TAILPIPE LENGTH ON COMBUSTOR A theoretical analysis is given of linear multichannel control STABILITY systems for vehicles orbiting in the atmosphere of the earth at John Amos Eelding Jr IPh D Thesis) 1969 184 p supersonic velocities. A procedure is developed for obtaining a set Avail Univ Microfilms HC $8 40/ Microfilm 53 00 Order No of control system structures providing a selection invariance which 70-1365 can be used as a basis for the optimization of such control systems A theoretical analysis of an adiabatic homogeneous reactor in terms of both quality and simplicity of realization. Equations was carried out for a ramjet type combustor in order to describe describing the spatial motion of such vehicles and a graphic the effect of an increase in tailpipe length on stability limits mathematical model of these equations are derived in the process. The Correlationof combustion loading with known homogeneous reactor methods of graph theory are applied in developing the algorithms data was made in order to veri+ results of the theoretical analysis GRA General theoretical computer programs are included A ramjet type for constructing such control systems. combustor using premixed air-fuel was constructed The combustor consisted of a two inch diameter tube which housed a disk bluff N71-17762 California lnst of Tech Pasadena body flameholder Various tailpipe lengths were also constructed THE HYPERSONIC LAMINAR BOUNDARY LAYER NEAR A Experimental data pertinent to the combustor loading parameter SHARP EXPANSION CORNER were obtained These data included total and static pressure Keith Jordis Victoria (Ph D Thesis) 1969 142 p measurements outside the flame front flame front radii and Avail Univ Microfilms HC $6 EO/Microfilm $3 00 Order No recirculation zone radii all measured at various locations down the 70-1426 duct In addition the lengths of the recirculation zone were The integral moment method for treating interactions between measured Dissert Abstr a laminar boundary layer and an external supersonic flow is applied to the problem of the hypersonic laminar boundary layer near sharp and slightly rounded convex (expansion) corners The general N71-17728# Air Force Systems Command. Wright-Patterson features of this type of interacting flow are established by an AFE. Ohio. Foreign Technology Div. analytical solution of the integral equations using the method of DETERMINATION OF THE EFFECT OF ATMOSPHERIC matched asymptotic expansions for the case of small interaction HUMIDITY ON THE CHARACTERISTICS OF A TURBOFAN parameter Numerical solutions are obtained for flows for which the ENGINE interaction parameter can no longer be considered small An E. D. Fishbeyn et al [1970] 13 p refs Transl. into ENGLISH experimental study is carried out in the GALCIT Mach 8 hypersonic from IZY Vyssh. ucheb. Zaveo.. Aviats. Tekn. (Kazan). no. 2. 1967 wind tunnel In order to sruoy me two otmensionai laminar oounaary p 112-118 layer expansion Major emphasis is placed on the acquisition of (AD-7 15232: FTD-HT-23-290-68) Avail NTlS CSCL 21/5 detailed data near the corner region The basic measurements A mathematical method is presented for the study of the consist of the model surface pressure distribution and pitot pressure humidity effect on parameters of any gas-turbine engine surveys of the boundary layer and inviscid flow field between the Author (GRA) boundary layer and the leading edge shock wave both upstream and downstream of the corner region The surface pressure measurements illustrate the striking departure of the flow field at Prandtl-Meyer description N71-17733# Naval Weapons Lab.. Dahlgren. Va. hypersonic speeds from the classical ON RESONANCE INSTABILITY FOR FINNED Dissert Abstr CONFIGURATIONS HAVING NON-LINEAR AERODYNAMIC PROPERTIES N71-17753# Pennsylvania State Univ., University Park. Dept. Thomas A. Clare Oct. 1970 51 p refs of Aerospace Engineering. (AD-7151 10: NWL-TR-2473) Avail: NTlS CSCL20/4 AN INVESTIGATION OF THE TRAILING VORTEX SYSTEM An approximate solution is presented for the angular motion. GENERATED BY A JET-FLAPPED WING OPERATING AT at and near resonance, of finned configurations (with small HIGH WING LIFT COEFFICIENTS Final Report aerodynamic asymmetries) having non-linear aerodynamic properties Barnes W. McCormick and William J. Schumacher Wright-Patterson An extension of the Method of Slowly Varying Parameters (or AFE. Ohio AFFDL 5 Jun. 1970 48 p refs Averaging Method) is used to solve the simultaneous pitch and yaw (Contract F33615-69-C-1165) equations of motion. in terms of amplitude-rate equations. at the (AD-715315: AFFDL-TR-70-90) Avail. NTlS CSCL 1/3 resonance point. Included in this analysis are the non-linear The purpose of the investigation was to measure the geometry variations of the restoring. damping. and Magnus moments with of the trailing vortex generated behind a jet-flapped wing. Such angle of attack. Both transient and steady state.solutions are vortices can pose a serious hazard to aircraft that penetrate them. obtained A detuning of the rolling velocity from its resonant value Previous investigations performed on conventional wings indicate is performed to yield a solution in the critical near-resonant region. that these vortices persist for some time and have maximum This result is shown to give rise to the well-known resonance jump tangential velocities which increase linearly with the lift coefficient. in the steady state case. Finally. allowing the detuning parameter As future aircraft may employ high lift devices such as jet-flapped to vary with time enables an examination of the non-linear wings, the vortices generated could be even stronger. Two semispan catastrophic yaw problem in which both the rolling velocity and the models of a jet-flapped wing were tested in a subsonic wing roll orientation angle may vary with time. In this regard, the effects tunnel. Parameters varied during testing included the jet flap angle. of a non-linear variation of the induced side moment with angle angle of attack. aspect ratio, and jet momentum coefficient. of attack are determined. The accuracy of these solutions is Vortex measurements were obtained using a vortex meter which evaluated by comparison with exact numerical integrations of the measured the rotational speed of the fluid within the vortex. equations of motion. Author (GRA) Values obtained were numerically integrated to yield the tangential

24 1 N71-17766 velocity and circulation distributed through the vortex Experimental stick controller in place of the normally used wheel controller to results indicate that the maximum tangential velocity increases to determine if the type of controller affected the lateral-directional a maximum and then decreases with continually increasing let dynamics for acceptable handling qualities No difference was found to blowing At high values of jet blowing. the vortex was found to exist A detailed comparison with MIL-F-8785B(ASG) requirements decay rapidly downstream Author (GRA) is included and generally shows the present requirements to be too consewative in the landing approach flight phase Author (GRA)

N71-17766# Naval Research Lab, Washington. D C Security Systems Branch N71-17798# Civil Aeronautics Board. Washington. D c AN EXTENSION OF NONSYNCHRONOUS CIVIL AERONAUTICS BOARD CAREERS FOR ECONOMISTS INTERROGATION REPETITION FREQUENCY SELECTION AND TRANSPORTATION I N DUSTRY ANALYSTS METHODS [1970] 12 p W K Gardner Nov 1970 38 p refs Avail Issuing Activity (AD-715335, NRL-MR-2175) Avail NTlS CSCL 17/7 Economist and air transportation analyst employment Consideration of the timewise occupancy within the overall opportunities and qualification specifications are outlined Employee period band due to initial choices of nonsynchronous Interrogation benefits provided by the Civil Aeronautics Board are summarized Repetition Frequencies IIRFs) for application to radar beacon EC systems results in the ability to determine as well the open time slots remaining for succeeding choices Thus all possible succeeding choices that could become members of a particular nonsynchronous N71-17799# Civil Aeronautics Board Washington D C IRF set can be located A simple method has been found for REMARKS TO THE EXECUTIVE PROGRAM ON progressively locating by computer all open slots (integer period TRANSPORTATION AND LOGISTICS values) for each next choice of a given nonsynchronaus IRF set The Secor D Browne 6 Aug 1970 12 p Conf held at Boston blocked/open slot concept further results in a detailed understanding 6 Aug 1970 of the effects upon the selection process of changes in the Avail Issuing Activity parameter n the number of interrogations and the parameter delta The following topics are considered air piracy prevention. the dead time of a transponder, and explains the great dependency effects of reductions in air passenger capacity, controlling labor upon n and delta of the total number of available nonsynchronous costs smoke and noise control air traffic control procedure revisions IRFs Author (GRA) and airways congestion An edited transcript of the question and answer session is also presented EC

N71-17779# Civil Aeronautics Board Washington D C REMARKS PREPARED FOR DELIVERY BEFORE THE 1970 N71-17832# Air Force Systems Command Wright-Patterson ATA ENGINEERING AND MAINTENANCE CONFERENCE AFB Ohio Foreign Technology Div Secor D Browne 7 Oct 1970 8 p Conf held at Atlanta AUTOMATION OF TECHNOLOGICAL PROCESSES IN Georgia. 7 Oct 1970 AIRCRAFT-ENGINE CONSTRUCTION Avail Issuing Activity M I Evstigneev 10 Sep 1970 275 p refs Trans1 into The status of certain operational and administrative issues ENGLISH of the book Avtomatizatsiya Tekhnologicheskikh Protsessov in civil aeronautics is summarized Topics cited include route v Avia Dvigatelestroyenii Moscow Izd-Vo Mashinostoyeniye 1969 systems. scheduling air traffic control, air space and terminal p 1 267 congestion. noise control SST development and air fare rates (AD-714858 FTD-MT-24 102 70) Avail NTlS CSCL 1318 EC The book expounds on questions of planning the technological processes of automated production The systems and mechanlsms of the automatic control of technological units and machine-tool N71-17792# Cornell Aeronautical Lab Inc Buffalo N Y lines are described The methods and means of automating the AN IN-FLIGHTINVESTIGATION OF machining and quality control of components and subassemblies of LATERAL-DIRECTIONAL DYNAMICS FOR THE LANDING aircraft engines and the principles of setting up automatic APPROACH Final Technical Report machine-tool lines are examined the technical and economic bases of G Warren Hall and Edward M Boothe Wright-Patterson AFE the selection of rational methods of automating the technological Ohio AFFDL Oct 1970 288 p refs processes in aircraft engine construction are presented (Contract F33615 69 C-1664) Author (GRA) (AD-715317 CAL-EM 2821-F 5 AFFDLTR 70-145) Avail NTlS CSCL 1/3 Lateral directional handling qualities and roll control power requirements for executive jet and military Class II Airplanes in the N71-17843*+ Georgia lnst of Tech, Atlanta landing approach flight phase were investigated in the variable INTERURBAN AIR TRANSPORTATION SYSTEM: A stability T-33 airplane Particular emphasis was placed on the effects GRADUATE PROJECT IN COMPLEX SYSTEMS DESIGN. of crosswinds and turbulence Simulated IFR ILS approaches and PRESENTED BY THE STUDENTS OF AE-EE-ME 655-656 VFR offset and crosswind approaches were made Specifically two (WINTER-SPRING QUARTERS. 1969) Dutch roll frequencies three Dutch roll damping ratios three Cassius Mullen. ed Dec 1969 409 p refs roll-to sideslip ratios and three roll mode time constants were (Grants NGT-11-002-064, NGR-11-002-081, NSF GU-2161) investigated It was found that lateral directional dynamics do not (NASA-CR-116431) Avail NTlSHC$600 CSCL 01E establish a limiting crosswind value however they do determine A systems approach was used to study the interurban public the ease or difficulty with which a crosswind approach can be air transportation problem for the 1975 to 1985 period The nature accomplished Roll control power requirements were determined of this problem was determined alternate solutions were posed from actual control usage data obtained throughout the evaluation and measures of effectiveness and cost were applied Basic areas program In addition a number of configurations were reevaluated of demand and route structure, air vehicles. terminals and with limited roll control power to determine minimum acceptable ground facilities, and air traffic control were used to formulate a levels Available roll control power can establish a limiting Crosswind mathematical model for common carrier air transportation in the component A number of configurations were evaluated with a United States of America Author

242 N71-17908

N71-17854#' Naval Aerospace Medical Inst.. Pensacola. Fla. N71-17897' National Aeronautics and Space Administration. ORIENTATION-ERROR ACCIDENTS IN REGULAR ARMY Langley Research Center. Langley Station. Va. HU-1 AIRCRAFT DURING FISCAL YEAR 1967: RELATIVE HEAT PROTECTION APPARATUS Patent INCtDENCE AND COST Paul R Hill and Otto F. Trout. Jr., inventors (to NASA) Issued W. Carroll Hixson, Jorma I. Niven, and Emil Spezia 25 Aug. 1970 20 Sep. 1966 (Filed 19 Dec. 1962) 9 p a.62-467 38 p refs (NASA-Case-XU-00892; US-Patent-3.273.355; (AD-715107; NAMRL-1108: USAARL-71-11 Avail: NTlS CSCL US-Patent-Appl-SN-245941) Avail: US Patent Office CSCL2OM 1/2 A thermal protection system for application to the wing, The report dealing with the magnitude of the pilot control. and other surfaces of hypersonic aircraft and reentry disorientation/vertigo accident problem in Regular Army UH-1 vehicles is described. A fiber oriented pile is applied as a covering helicopter operations. Incidence and cost data presented for fiscal element to the vehicle surfaces exposed to the greatest amount year 1967 include a total of 50 major and minor orientation-error of aerodynamic heating. Orientation of the fibers in the direction accidents (15 of which were fatal). resulting in 38 fatalities. 88 of airflow insures radiation away from the surfaces and eliminates nonfatal injuries. and a total UH-1 aircraft damage cost of penetration of the heated air below the outer face of the fibers. $7.542.177. Author (GRA) NASA

N71-17876*# National Aeronautics and Space Administration N71-17906# Office of Naval Research, London (England). Lewis Research Center, Cleveland Ohio THIRD INTERNATIONAL CONFERENCE ON RAIN DRILLED-CORE STORAGE HEATER FOR A HYPERSONIC EROSION AND ASSOCIATED PHENOMENA TUNNEL E. I. Salkovit 20 Oct. 1970 31 p Conf held at Hartley Wintney. Erwin A Lezberg Washington Mar 1971 23 p refs Engl., 1 1 - 13 Aug. 1970 (NASA TM-X-2202. E-5850) Avail NTlS CSCL 14B (AD-715100: C-25-70) Avail: NTlS CSCL 1/3 A design for a graphite drilled-core storage heater for supplying Equipment was described to test rain, hail and sand erosion heated nitrogen gas to a hypersonic propulsion facility was damage to aircraft components flying at sub- and supersonic developed using results from a transient-heat-transfer program Hole velocities. Materials were evaluated in terms of such meteorological size and spacing were determined from the results of the computer exposure, and appropriate modeling techniques were described. program and from consideration of tharmal stress and cost factors Analyses were given of various factors influencing rain erosion A model of the proposed matrix design was fabricated and tested in resistance. and investigations were conducted on the na?ure and a piliX storage heater facility to evaluate thermal stress limitations consequences of raindrop disintegration on impact. Author (GRA) and to compare performance of the heater with predictions based on the heat-transfer calculations No cracking or deterioration Of the matrix had occurred during the test program Measured matrix temperatures were only in fair agreement with the results of a N71-17907# Honeywell. Inc.. Minneapolis, Minn. Systems and two-dimensional transient-heat-transfer program. but the Research Div. discrepancies are believed to be due to thermocouple installation HELICOPTER APPLICATION STUDIES OF THE VARIABLE errors Author DEFLECTION THRUSTERJET FLAP Final RepH Ronald G. Bailey and Jeffrey M. Hammer Nov. 1970 117 p refs (Contract NOOO 14-69- C-0267 1 N71-17877*# National Aeronautics and Space Administration. (AD-715071: Doc-12153-FRI(R)) Avail: NTlS CSCL 1/3 Ames Research Center, Moffen Field. Calif. The results of an analytical study to determine the application AN EXPERIMENTAL INVESTIGATION OF THE AIRFLOW of a blown flap device called the Variable Deflection Thruster (VDT) OVER A CAVITY WITH ANTIRESONANCE DEVICES to a helicopter rotor are presented and analyzed. The study is part Donald A. Buell Washington Mar 1971 72 p refs of a longer-range program to investigate and develop control (NASA-TN-D-6205: A-3691 Avail. NTlS CSCL 20D techniques for stabilization of the higher harmonic modes of Aifflow over deep cavities was investigated in a wind tunnel helicopter rotor blades. A high-speed digital computer program was and in flight at high subsonic speeds at equivalent or actual used to calculate the aerodynamic characteristics and performance altitudes of 7 to 12 km. The cavities were large, with opening of a Sikorsky CH-34 rotor system as though equipped with a dimensions on the order of 1 m. Pressures were measured in and blown two-dimensional section. The study was made over a range near the cavities with and without externally mounted devices of rotor flight profiles and operating parameters including advance intended to suppress resonances in the cavities. Some of the ratio, shaft angle of attack. blade pitch. tip Mach number, jet devices reduced the pressure fluctuations from as much as 50 to 2 deflection angle and blowing rate. Performance of the blown rotor or 3 times the amplitude occurring in a normal attached boundary is compared to the conventional CH-34 rotor to illustrate VDT layer. The pressure data were analyzed for spectral content, application effectiveness. Results show that the operating lift coherence. phase. shear-layer thickness, and shear-layer location. capability and propulsive force of the CH-34 rotor are increased Author when the rotor is equipped with a blown device. A preliminary analysis of the attenuation of rotor hub-shear variation by N71-17882*# Naional Aeronautics and Space Administration programmed blowing is also shown. In all cases. improved Lewis Research Center. Cleveland Ohio performance through application of blown control requires additional OVERALL PERFORMANCE IN ARGON OF A 3.7-INCH power. Author (GRA) SIX-STAGE AXIAL-FLOW COMPRESSOR Edward R Tysl, Laurence J Heidelberg and Carl Weigel Washington Mar 1971 23 p refs N71-17908# Army Foreign Science and Technology Center, (NASA-TM-X-2194. E-5522) Avail NTlS CSCL 21 E Washington. D C Overall performance from the compressor inlet to the collector PRACTICAL AERODYNAMICS OF THE Mi-6 HELICOPTER exit and overall performance from the compressor inlet to the exit M S Yatsunovch 2 Nov 1970 212 p Trans1 into ENGLISH from of the sixth-stage stator are presented as a function of equivalent THE PUEC 'Prakticheskaya Aerodinamika Vertoleta Mi-6' Moscow. weight flow Peak efficiency (compressor inlet to collector exit) was Moscow Transport. 1969 0 755 at the design equivalent rotative speed of 49.213 rpm and (AD-714915. FSTC-HT-23-1172-70) Avail NTlS CSCL 1/1 occurred at an equivalent weight flow of 1 55 Ib/sec (070 kg/sec) The book presents a bnef description of the hellcopter. The pressure ratio at peak efficiency was 2 72 Author the aerodynamics of its lifting system and fuselage, characteristics

243 N71-17951

N71-18015*# National Aeronautics and Space Administration The of the D-25V gas turbine engine and the pitch-gas system Langley Research Center, Langley Station Va basic flying modes of the helicopter, methods for performing them REAL-GAS EFFECTS ON THE DRAG AND TRAJECTORIES and flying limitations for the Mi-6 helicopter with trapezoidal and OF A NONLIFTING 140 DEG CONICAL AEROSHELL rectangular lifting rotor blades, as well as problems of balanc- DURING MARSENTRY ing. control centering and stability of the helicopter and Dennis 0 Allison and Percy J Bobbitt Washington Feb 1971 special cases in flight are analyzed The diagrams of forces 28 p refs in flying modes with forward speed are presented for simplicity (NASA TN D-6240 L 7522) Avail NTlS CSCL 22A without considering banking or slipping with which the helicopter The influence of real gas effects on the drag and trajectories should be balanced These problems are discussed in the of a 140 deg conical aeroshell during entry into five model Mars analysis of balancing of the helicopter Author (GRA) atmospheres is discussed Drag coefficients are obtained by using an approximate technique which enables their determination at every point along a trajectory with reasonable computer time The standard point mass trajectory equations are used and a spectrum N71-17951*# National Aeronautics and Space Administration of entry conditions are considered that consist of velocities of 4 27 Flight Research Center, Edwards, Calif 4 57 and 4 88 km/sec (14 000 15 000 and 16 000 ft/sec) and ACOUSTIC ATTEN U AllON DETER MI NED entry flight path angles of 13 5 deg 15 deg and 17 5 deg All EXPERIMENTALLY DURING ENGINE GROUND TESTS ON calculations were made for an entry spacecraft with a ratio of mass THE XB-70 AIRPLANE AND COMPARISON WITH to maximum cross sectional area of 76 5 kg/square meter (0487 PREDICTIONS slug/square foot) It is shown that a single curve may be chosen to NormanJ McLeod Washington Mar 1971 15 p refs represent the drag coefficient variations within 2 percent (NASA-TM-X-2223. H-633) Avail NTlS CSCLOlC accuracy for all five model atmospheres and all the entry conditions Acoustic data obtained during ground runs of the XB-70 considered Author airplane enabled the attenuation of sound to be determined for ground-to-ground propagation over distances of 500 feet (152 meters) and 1000 feet (305 meters) for one set of atmospheric conditions The considerable scatter in the experimentally determined attenuations seemed to be associated with variations in N71-18018# Human Resources Research Organization the wind parameters For downwind propagation. reducing the Alexandria Va predicted acoustic-attenuation values ARP 866 by 50 percent FUNCTIONAL REOUIREMENTS FOR GROUND-BASED for octave bands above 1000 hertz resulted in good agreement TRAINERS. HELICOPTER RESPONSE CHARACTERISTICS between the present experimentally determined and predicted W G Matheny and L E Wilkerson Oct 1970 121 p refs values Author (Contract DAHC19 70-C-0012) (AD 714954 HUMRRO TR 70 17) Avail NTlS CSCL5/9 The overall research purpose was to develop methods for analyzing the helicopter pilots control tasks as a basis for deciding N71-17958*# Pratt and Whitney Aircraft East Hartford, Conn characteristics needed in a ground based trainer for use in pilot AERODYNAMIC BROADBAND NOISE MECHANISMS training The report covers one phase the response characteristics APPLICABLE TO AXIAL COMPRESSORS of the helicopter as it reacts to control inputs and external forces Robert A Arnoldi Washington NASA Mar 1971 46 p refs Analyses were made of (a) characteristics of each dimension of (Contract NASw-19081 control (b)interaction among the dimensions (c) effect of external (NASA-CR-1743 PWA-3930) Avail NTlS CSCL 21 E forcing functions such as wind (d) information the pilot receives by A study of broadband noise produced by the interactions kinesthetic feedback from the controls A measure of man machine of turbulence with the shock system upstream of a supersonic system characteristics was postulated the effective time constant compressor and with the surface of the rotor blade has been made the time it takes for the displayed output of the system to rise The dynamic response of the rotor blade in the latter interaction was above the pilots threshold of perception Dealing with the effects constructed empirically. based on the results of a complementary of interaction among the controls proved to be one of the most experimental program This program obtained the lift response of difficult pilot tasks of the single dimensions pitch control is the an instrumented airfoil subjected to periodic upwash fluctuations most difficult The characteristics of the system were identified in Both source mechanisms are found to produce noise levels of such a way that they can be varied quantitatively in research on significant magnitude. either might be a prime source of broadband task difficulty and transfer of training Author (GRA) engine noise. and further study of both is recommended The effect of incidence past stall on the unsteady response is shown to be a small reduction in magnitude and a slowly increasing delay in phase neither of which make any substantial modifications in N71-18022 Rennsselaer Polytechnic Inst Troy N J predicted noise Output This result was measured at a reduced OPTIMIZATION OF COMPOSITE STRUCTURES OPTIMUM frequency of 3 9. further investigations over a wider range is COST AND WEIGHT DESIGN FOR A CYLINDRICAL SHELL recommended Author SUBJECTED TO RE-ENTRY LOADS AND HEATING Edgar Gebrath Menkes (Ph D Thesis) 1969 17 1 p Avail Univ Microfilms HC $800/Microfilm $300 Order No N71-17963# American Airlines Inc, New York ATC Research 70-2631 Dept An improved method of structural optimization is presentea ATC STOLTASK FORCE which encompasses recent advances in nonlinear mathematical May1970 21 p programming methods and methods of analysis for fibrous Avail NTlS composite materials The methodology IS based on a transformation The feasibility of STOL operations in the Northeast Corridor of an inequality constrained minimization problem into a sequency is reviewed. including the viability of a proposed intercity STOL of unconstrained minimizations by applying a penalty function operation in areas heavily congested with air traffic Area navigation formulation Advances include the formulation and solution of a routes and the corresponding en route and terminal area operational composite shell design problem including constraints on procedures are proposed for a STOL operation between Boston joint-discontinuity stresses and the development of a methodology Logan Airport. a Manhattan STOLport and Anacostia Naval Air for assessing the effects of uncertainties in system parameters on Station Author the optimum design The optimization method is first developed by

244 N71-18072

considering a classic structural design application. the redundant three bar truss Next an application to a composite shell structure The article presents the results of investigation of the gas is demonstrated Dissert Abstr dynamics of fan jets at various injection angles from 60 degrees to 135 degrees To increase the effectiveness of GTE afterburners, the flame is converted to jet or gas dynamic stabilization which produces a zone of backflows by injecting the gas jet lair. gaseous fuel. or a mixture) into the flow of combustible mixture The limits N71-18025*# National Aeronautics and Space Administration. of stable combustion in jets depend essentially on the parameters Langley Research Center. Langley Station. Va. AN ANALYTIC STUDY OF RADIATIVELY COOLED determined by the gas dynamics of the stream in the zone of Author (GRA) DELTA-WING STRUCTURES FOR HYPERSONIC AIRCRAFT interaction of jets with a flow James C. Robinson, Robert W. Mc Withey. and George F. Klich Washington Feb. 1971 65 p refs (NASA-TN-D-6138: L-6666) Avail: NTlS CSCLOlA A thermal analysis and a stress and deflection analysis of five structural configurations for a radiatively cooled discrete delta wing were carried out by using design conditions characteristic N71-18036# Cincinnati Univ, Ohio Dept of Aerospace of a Mach 8 research vehicle. The configurations included wing Engineering cover panels possessing either biaxial or uniaxial stiffness. support ESTIMATION OF SUPERSONIC COMPRESSOR EFFICIENCY systems along the root chord or at two points on the root chord, W Wells and R E Pavri Oct 1970 16 p refs and airfoil sections having either positive or negative camber. (Contract DAHC04-69-C-0016. Proj Themis) Results indicate that for configurations supported along the full root (AD-715005. THEMIS-AE-70.15. AROD-T-4-21-E) Avail NTlS chord. no excesswe thermal or airload deformations occur. However. CSCL 1317 high thermal stresses occur in the wing cover panels that possess A semi-empirical determination of the adiabatic efficiency axial stiffness in the chordwise direction. Configurations in which of a supersonic compressor stage is obtained The method utilizes the the cover panels possess only spanwise axial stiffness exhibit normal shock relations. a recently developed efficiency expression significantly lower thermal stress in the panels but require that the for subsonic cascade flow and experimental pressure loss data from supersonic cascades of various geometrical shapes A correction rib caps carry larger thermal loads Author factor is determined which makes it possible to convert the subsonic stage efficiency to the case of supersonic flow involving shock losses Author (GRA)

N71-18029*# New York Univ, N Y DIFFRACTION OF A PULSE BY A THREE-DIMENSIONAL CORNER Lu Ting and Fanny Kung Washington NASA Mar 1971 92 p refs N71-18040# Federal Aviation Administration. Washington, D C 'Era-? YGC 33 C?6 3 '9) Sy6:tms Reaea:& and 3a,clopment Sen,ce \NASA-CR-1728 NYU-AA-70-06) Avail NTlS CSCL 20D EXECUTIVE SUMMARY OF ANALYTICAL STUDY OF AIR For the diffraction of a pulse by a three dimensional corner TRAFFIC CAPACITY IN THE NEW YORK METROPOLITAN the solution is conical in three variables zeta = r/(Ct) theta AREA AND NEW YORK AIR TRAFFIC CAPACITY STUDY and alpha The three-dimensionaleffect is confined inside the unit (REALTIME SIMULATION) Final Reports sphere zeta = 1 with the vertex of the corner as the center The Feb 1970 15 p t boundary data on the unit sphere is provided by the appropriate (FAA-RD-70-7. FAA-RD-70-4 FAA-NA-70-15) Avail NTlS solutions for the diffraction of a pulse by a two dimensional wedge The air traffic system capacity in the New York Metropolitan The solution exterior to the corner and inside the unit sphere is Area was examined The effects of adding runways at Kennedy constructed by the separation of the variable zeta from theta and International and Newark Airports and the use of standardized alpha The associated eigenvalue problem is subjected to the instrument arrival and departure procedures, a revised route structure differential equation in potential theory with an irregular boundary based on area navigation capability. and automated control aids in theta - eta plane A systematic procedure is presented such that and regulating traffic are estimated Estimates were derived from a the eigenvalue problem is reduced to that of a system of linear dynamic real-time simulation study and an analytical study covering algebraic equations Numerical results for the eigenvalues and system aspects not amenable to dynamic simulation Estimates functions are obtained and applied to construct the conical solution include practical annual capacity. severe congestmn annual capacity. for the diffraction of a plane pulse For the diffraction of a general and airspace system capacity in terms of controller workload and incident wave by corners or edges two theorems are presented airspace physical capacity Author 50 that the value at the vertex of the corner or along the edges can be determined without the construction of the three-dimensional nonconical diffraction solutions Relevant numerical programs for the analysis are presented in the appendix Author

N71-18072# Department of Transportation. Washington, D C NATIONALTRANSPORTATION PLANNING MANUAL (1970 - 1990). MANUAL A: GENERAL INSTRUCTIONS N71-18034# Air Force Systems Command, Wright-Patterson Jul 1970 187 p AFB. Ohio Foreign Technology Div (PB-194964. BOB-004-S700028) Avail NTlS THE EFFECT OF THE INJECTION ANGLE ON GAS General instructions are given on how to present and DYNAMICS OF FAN JETS IN THE DEFLECTED FLOW summarize cooperative comprehensive and continuing planning for V A Kosterin et al 4 Sep 1970 11 p refs Trans1 into the economic development of a national transportation system The ENGLISH from Aviats. lnst. Kazan, Tr (USSR), no 101. 1968 P 32-38 Overall process covers all modes of domestic transportation and (AD-714790 FTD-HT-23-443-70) Avail NTlS CSCL 21 /5 includes both private and public sectors of the economy G G

245 N71-18078

N71-18078# Civil Aeronautics Board Washington, D C resulting from airport construction are discussed. emphasizing cost REMARKS PREPARED FOR DELIVERY BEFORE THE per unit. output determination from operating levels, adjustment for ASSOCIATION OF LOCAL TRANSPORT AIRLINES FALL increased productivity. and total output and employment Gross QUARTERLY REGIONAL MEETING and net economic impact of purchases by airport activities of north Secor D Browne 28 Sep 1970 8 p Conf hetd at Anchorage central Texas region are reviewed along with air transportation and Alaska. 28 Sep 1970 regional growth JAM Avail Issuing Activity The present state of local air transport and the main aspects to be considered in deciding future transpon service are briefly discussed The topics mentioned include the following current N71-18100# Institute of Transport Aviation Paris (France) economic plight of local airlines the new Class Rate 5 formula being ATTITUDES TAKEN WITH REGARD TO AMENDMENTS TO developed the need for cooperation between local representatives THE WARSAW CONVENTION (LES PRISES DE POSITION Systems Analysis Research Corporation and the Civil Aeronautics AU REGARD DES AMENDEMENTS A LA CONVENTION Board Mutual Aid Pact encouragement of industries to locate DE VARSOVIE] away from urban areas suitability of serving all existing points on H Beaubois 1970 58 p refs routes where there is Competition fares and marketing (Rept-1970/8-E) Avail NTlS departments NEN An investigation is presented on the attitudes of members towards the revised limits of liability to international air transport passengers as fixed by the Warsaw Convention and amended by The Hague Protocol The positions adopted in light of proposed amendments, since the first meeting of the ICAO Legal Committee in 1968 and how the different viewpoints evolved before N71-18079# Civil Aeronautics Board Washington D C crystallizing in the conclusions finally formulated by the Legal REMARKS PREPARED FOR DELIVERY BEFORE THE 1970 Cornmitree itself are studied The proposed amendments primarily NATIONAL AIRPORTS CONFERENCE concern the following six points laws governing liability in Secor D Browne 6 Oct 1970 6 p Conf held at Norman. Okla passenger transport and means of defence open to the carrier 6 Dct 1970 fhancial limitations on liability and possible exceptions the limit Avail Issuing Activity sum or sums revising the limit sum legal costs and jurisdictional The airport community noise problem and ways of noise competence The discussions pursued during 1968 1969 and reduction are discussed The retrofit programs were examined and 1970 stemmed from the initial stands adopted and made known to the found to be high in cost and dubious in outcome Suggestions Subcommittee by IATA and the US Government Their arguments were made to the FAA, which could be implemented immediately are set out in detail after the more pertinent comments formulated and cut noise exposure up to 90% raise the approach floor of the by the Subcommittee s panel of experts are mentioned The stands ILS system 3000 feet and change the departure noise abatement adopted by certain delegations throughout the legal Committee s procedures to allow pilots to take full advantage of the jet transport labors on the six points are explained Author climb capability It is also felt that effort should be spent on producing new quiet. clean engines in the 20 000 to 30.000 pound thrust class NEN

N71-18101# Federal Aviation Administration Washington D C ALPA A SURVEY OF AIRPORT FIRE AND RESCUE FACILITIES N71-18087# Commerce Dept Washington D C B V Hewes 1970 84 p NATIONAL EXPORT EXPANSION COUNCIL: REPORT OF Avail NTlS THE INDUSTRY COMMllTEE ON COMMERCIAL AIRCRAFT The annual survey of crash fire and rescue equipment at Robert J Murphy Jr May 1970 38 p airports being served on at least a daily basis by the 11 trunks Avail Issuing Activity 9 local service and 7 Alaskan and Hawaiian airlines is presented Civil aircraft export strategy and recommendations for increased Airports served exclusively by third level or airline operators are not exports during the 1970s are discussed It is pointed out that included due to the problems encountered when collecting the significant cornpetition comes not only from the United Kingdom but necessary data The purpose of the survey is to (a) inform the also from Japan and the USSR It is felt that to meet the increased airline pilot of the crash fire and rescue equipment available at the competition industry and Government must work closely together airports and (b) inform government agencies airline authorities and and adequate long term financing will be crucial Financing from other responsible groups and individuals of the facts concerning the the Export Import Bank commercial banks. and Government IS recommended It is also considered that overseas procurement status of crash fire and rescue equipment at North American and Canadian airports Author and production and politico/military policies should be reviewed NEN

N71-18103# National Aviation Trades Associatlon. Inc , N71-18099# Regional Science Research lnst Philadelphia Pa Washington. D C ECONOMIC IMPACT OF THE DALLAS-FORT WORTH TESTIMONY OF MIDAIR COLLISION HAZARD BEFORE REGIONAL AIRPORT ON THE NORTH CENTRAL TEXAS THE NATIONAL TRANSPORTATION SAFETY BOARD REGION IN 1976 Frank Kingston Smith Nov 1969 182 p refs Robert E Coughlin Robert C Douglas Thomas W Langford Jr Avail NTlS and Benjamin H Stevens Jan 1970 78 p refs Sponsored An analysis of midair collisions between commercial aircraft in part by Dept of Housing and Urban Develop and general aviation aircraft is presented The causes of midair Avail NTlS collisions occurring during 1969 are discussed Recommendations Air transportation activities are proiected for the Dallas-Fort are made for measures to be employed for reducing the midairPNF Worth area Proposed dollar value of purchases and employment collision hazards

246 N71-18117

N71-18104# American Airlines Inc , New York N71-181 l4# Stanford Research Inst.. Menlo Park. Calif INTER-METROPOLITAN STOL EVALUATION (PHASE 10) TESTS OF ORTHO-DECOUPLED AIRCRAFT STATIC Final Report DISCHARGERS Jan 1970 146 p R. L. Tanner and J. E. Nanevicz [1970] 18 p refs (Rept-50) Avail NTlS Contracts AF 33(616)-6561, AF 19(604)-3458) An integrated inter-metropolitan transport system was Avail: NTlS investigated to serve the expanding short-haul market The McDoonell Fhght tests were conducted to evaluate devices for discharging Douglas Model 188 STOL aircraft (Breguet 941 S) was selected for static electricity from aircrah without the production of radio the evaulatlon of the navigation systems. ATC procedures. and interference. The devices employed a principle. known as operational procedures It was concluded that effective airline use ortho-decoupling. by which the radio interference generated from of STOL aircraft is now operationally and technically feasible It is corona discharges taking place at the devices is decoupled from the recommended that the air carriers develop a STOL transport radio antennas. Two different installations of dischargers were 'system. starting with existing aircraft ana simple interim facilities. to tested. In one installation the ortho-decoupling principle was demonstrate the market and economics of a continuing passenger incorporated in flush-mounted dischargers installed along the trailing carrying service FOS edges at the tips of wing and tail surfaces The flush-mounted dischargers were supplemented by small external blade dischargers. also incorporating the ortho-decoupling principle, which were installed in the region of vortex formation at the tips of the airfoil 1 N71-18105 California Univ Los Angeles Div of Vocational surfaces. In the second installation a number of simple externally Education mounted rod dischargers replaced the flush-mounted dischargers AIR TRAFFIC CONTROL A FEASIBILITY STUDY on the trailing edges. Author David Allen, Willram K Bowers Richard L Lano and John M Meyer 1970 177 p Copyright Avail NTlS A Task inventory of the air traffic controller occupation N71-181 15# Institute of Transport Aviation Paris (France) was conducted and development of performance obiectives was REGIONAL STATISTICS ON SAFEN IN AIR TRANSPORT analyzed A preliminary listing of curriculum content is identified A [STATISTIQUES REGIONALES SUR LA SECURITE DU task :nve-to+ qt,estnoiinalre was developed data were collected TRANSPORT HERlE N] and ?aSulated and th,e data w?r= anaiyzsd wlth recommendations R Mathieu 1970 69 p refs for curriculum content rncluding the depth of required learning for (Rept-l970/10-E) Avail NTlS each topic Author Accidents incurred by scheduled airlines are examined by countty or region of the operator A comparison between the share of each region in scheduled traffic and its share in accidents shows differences in the safety levels of the operators of each region All accidents occurring in air transport to aircraft of over 5700 kg are N71-18109# Radio Technical Commission for Aeronautics considered Because of lack of data on the corresponding traffic Washington. D C the accident rates between the operators in the various regions are MINIM UM OPERATIONAL CH OR ACT€ RISTI CS FOR ~tiri,,,die The piuportlori ui idiai dccioents is snown 10 De higher AIRBORNE ATC TRANSPONDER SYSTEMS in air transport accidents as a whole than in scheduled Service 12 Mar 1970 56 p refs accidents as a whole Accidents are also studied by region and type (00-144) Avail NTlS of accident. and differences are noted in the proportion of the The requirements of basic characteristics for navigatton and same type of accident in total accidents for each region Author communication systems used in air traffic control are discussed Equipment specifications and environmental and international standards are Dresented RB N71-18116# Federal Aviation Administration Washington D C systems Research and Development Service SURVEY OF AIR TRAFFIC CONTROL RADAR BEACON SYSTEM OPERATIONAL PROBLEMS (30 DAY ATC N71-18112# Institute of Transport Aviation. Paris (France). CONTROLLER SURVEY) THE FREQUENCY OF SCHEDULED SERVICES: AN Kenneth Wise Jan 1970 50 p ANALYSIS OF AIR TRANSPORT SUPPLY Avail NTlS G. Oesmas and R. Mathieu 1970 92 p The survey results presented include the significant findings (Rept-l970/1-E) Avail: NTlS of over 12.OOO individual trouble reports received from air traffic A detailed analysis of air transport supply on scheduled Selvces controllers at beacon sites The reports were collected from civil in one month of 1967 is presented for the Europe-Mediterranean and military towers and centers and include problems connected region and Southeast Asia. Supply was measured by a set of with ground equipment as well as those of the aircraft D L G four variables: the number of stages, flights. available seats. and available seat-km. The distribution of these variables was examined according to three parameters: frequency. the level of supply (in available seats). and stage length. A double classification was N71-18117# Federal Aviation Administration Washington D C carried out and the stages sorted by frequency and distance. and Aviation Weather Systems Branch then by frequency and supply level. The study was continued with METE0 ROLOGlCAL EFFECTS 0 N AI R TR ANSPORTATI 0 N mean values and. after determining the area in which the Arthur Hilsenrod Jan 1971 26 p refs Presented at the 51st mean frequency/mean capacity combinations varied at the different Ann Meeting of the Am Meteorol Soc San Francisco, 21 Jan supply levels. the relations existing between the mean frequency and 1971 mean supply level calculated for homogeneous groups of stages. Avail NTIS and between the mean frequency and mean distance were Data are presented on the frequency of and costs resulting from investigated. An analysis was also made of aircraft type use and environmental restrictions on air transportation An operational share in overall activity. It was found that the utilization of different system that overcomes the restrictive conditions is described. along aircraft was dispersed over a wide frequency range The analysis with specific programs of FAA and the Department of was applied to Italy and Japan. Author Transportation Author

247 N71-18118

N71-18118 Michigan Univ.. Ann Arbor. Bureau of Business N71-18187*# National Aeronautics and Space Administration Research Manned Spacecraft Center. Houston, Tex ALTERNATIVE LOGISTICS SYSTEMS FOR EXPENSIVE A SUMMARY OF AVAILABILITY AND ACCURACY OF PARTS: AN AIRLINE STUDY LANDING AIDS FOR SHUTTLE APPLICATIONS William G. Browne 1969 242 p refs Richard J Labrecque 14 Aug 1970 6 p refs Copyright. Avail: NTlS (NASA-TM-X-66720, MSC-70-FM22-137) Avail NTlS CSCL The overhaul and inventow procedures of commercial airlines for 17G major aircraft parts are analyzed. along with the policy alternatives Observations on landing the shuttlecraft and navigational for providing the services with increased efficiency. A computer aid capabilities are summarized Findtngs show that if emergency simulation was developed to examine the impact on cost and landings at almost any airport are attempted some of the current service levels of different inventory and overhaul configurations for navigational aids should be included in the shuttle equipment the GE-4 engine. which will be used to propel the SST. There are a variety of navigational aids available accurate enough Experimentation with the different locations of overhaul facilities and to vector the shuttle to the landing area and perform a guided inventory was conducted. The simulation included provisions for approach There is no system however that has demonstrated changes in ownership. engine status, number of overhaul facilities guided landings at the large glide angles in unpowered shuttle in the system. engine failure rates, overhaul times. and rates of landings A transponder type RR set right at the landing site could fleet growth and system expansion. A survey of management help vector the shuttle in an emergency or serve to update the attitudes toward increased consolidation indicates that overhau! inertial system Author facility location is the most critical factor inhibiting consolidation efforts. The major conclusions were: (1) considerable cost savings can be achieved through policy changes providing for intercompany N71-18269# School of Aerospace Medicine Brooks AFB Tex consolidation of engine overhaul and storage facilities. and (2) the NOISE ASSOCIATED WITH OPERATION OF THE C-9A attainment of an overhaul and inventory consortium with more (AEROMEDICAL EVACUATION) AIRCRAFT than three or four members is likely to be most difficult, considering Donald C Gasaway Oct 1970 37 p refs present industry attitudes. Author (AD-715222 SAM TR-70-63) Avail NTlS CSCL20/1 Noise within the Douglas C 9A during various phases of operation is described and illustrated Near-field acoustic exposures are alw discussed and illustrated Degrees of speech interference and N71-18138*# National Aeronautics and Space Administration auditory risk are discussed and methods of controlling potentially Lewis Research Center Cleveland Ohio undesirable effects are proposed Author (GRA) UNSTART AND STALL INTERACTIONS BETWEEN A TURBQlET ENGINE AND AN AXISYMMETRIC INLET WITH 60-PERCENT INTERNAL-AREA CONTRACTION David A Choby Paul L Burstadt and James E Chalogeras N71-18367*# National Aeronautics and Space Administration. Washington Mar 1971 38 p refs Ames Research Center, Moffett Field, Calif. (NASA-TM-X-2192 E-5923) Avail NTlS CSCL 21 E PRELIMINARY STUDY OF ADVANCED HYPERSONIC The effects of inlet unstart on engine operation and the RESEARCH AIRCRAFT characteristics of stall propagation through the compressor and Le Land H. Jorgensen. Walter P. Nelms, Jr.. and Lionel L. Levy. inlet system are discussed With inlet unstarts at Mach 1 98. the Jr. Washington Mar. 1971 18 p refs instantaneous compressor pressure ratio which stalled the engine (NASA-TM-X-2222: A-3567) Avail: NTlS CSCL 01 C correlated with the steady-state value of the stall compressor Important flight constraints for hypersonic research aircraft are pressure ratio The unstart transient was so large at Mach 2 50 that reviewed. Maximum lift-drag ratios for state-of-the-art hypersonic it caused abrupt compressor stall at all engine operating conditions aircraft in trimmed flight have been derived from wind-tunnel tests Compressor stalls obtained by back-pressuring the engine at Mach Weights. cruise times. and ranges for rocket-boosted research 2 50 initiated hammer shocks through the inlet which caused airplanes with air-breathing cruise engines are estimated and surface static pressures to exceed freestream total pressure compared, Both horizontal take-off from the ground and air launch Author from a subsonic airplane are considered Author

N71-18161# Atomic Energyof Canada Ltd, Chalk River (Ontario) N71-18397*# Techtran Corp, Glen Burnie. Md RESULTS OF TWO-PHASE BLOW-DOWN EXPERIMENTS MEASUREMENTS OF INTERFERING UNSTEADY FORCES PART 1 STRAIGHTTUBE TEST SECTION BETWEEN LIFTING SURFACES IN TANDEM [MESURES R F White Aug 1970 73 p refs DES FORCES INSTATIONNAIRES D'INTERACTION ENTRE (AECL-3664) Avail AEC Depository Libraries Atomic Energy of SURFACES PORTANTES EN TANDEM] Can Ltd Chalk River $2 00 R Destuynder Washington NASA Feb 1971 18 p refs Transl Experiments on the blowdown rig have yielded detailed into ENGLISH from French Report ONERA-TP-890 information of the behavior of flowing two-phase steam-water (Contract NASw-2037) mixtures during the first 100 ms after rupture of a diaphragm at (NASA-TT-F-13482 ONERA-TP-890) Avail NTlS CSCLOlA the end of a pipe 15 feet long and 0 621 in ID Blowdown tests Wind tunnel tests were conducted in order to determine were made from initial pressures of 485 psia and 1002 psia and the effect of interference between two lifting surfaces in tandem steam qualities from 8% to 31% Pressure transients measured Models of rectangular and swept wings were used with variable at three positions about 7 feet apart in the test section showed horizontal and vertical separations The tests were limited to pure that the transition from the pre blowdown pressure gradient to that pitch and translation of the wings Author corresponding to critical discharge occurred in about 100 ms after rupture Measured rarefaction wave velocities were in the range 1520 to 1570 ft/sec and all were within 6% of corresponding theoretical values Measured masses of water discharged during the N71-18401*# Scientific Translation Service. Santa Barbara. Calif first 100 ms after diaphragm rupture agreed with values predicted CONTRIBUTION TO THE STUDY OF SONIC FLOWS PAST by the homogeneous model for steady state two-phase critical AN OBSTACLE flow contrary to critical discharge rates measured under steady D Euvrard Washington NASA Feb 1971 17 p refs Transl state conditions which agree with an annular two-phase critical flow into ENGLISH from Proceedings of the 8th Symp on Advanced model Author (NSA) Probl and Methods in Fluid Dyn (Tarda). 18 -25 Sep 1967

248 N71-18441

p 369-377 N71-18425# National Physical Lab , Teddington (England) (Contract NASw-2035) Aerodynamics Div (NASA-TT-F-13472) Avail NTlS CSCL 20D NUMERICAL APPRAISAL OF MULTHOPP'S The main findings of a series of investigators dealing with LOW-FREQUENCY SUBSONIC LIFTING-SURFACE THEORY sonic flow past an obstacle of finite dimensions are summarized H C Garner London Aeron Res Council 1970 102 p refs A detailed study is made of the regions upstream and downstream Supersedes NPL-AERO-1278. ARC-30607. N69-38133 from the shock waves in the case of an airfoil in a flow (ARC-R/M-3634 NPL-AERO-1278 ARC-30607) Copyright Avail which is uniform and sonfc at infinity Cases of symmetrical and NTlS HMSO E260 BIS $936 asymmetrical flow are also considered A case involving a Extensive tabulated results are presented for 17 varied three-dimensional flow is also presented FS planforms at uniform incidence or in low-frequency pitching oscillation Numerical accuracy and convergence are studied in relation to parameters representing chordwise and spanwise collocation. spanwise integration and central rounding of sweptback N71-18422*# National Aeronautics and Space Administration Flight Research Center, Edwards. Calif wings. general criteria for selecting these are recommended EXPERIENCE WITH THE X-15 ADAPTIVE FLIGHT Collocation error is reduced by doubling the central rounding. but CONTROL SYSTEM no improvement is obtained unless its aerodynamic influence is Washington Mar 1971 28 p refs subtracted Author (ESRO) (NASA-TN-D-6208 H-618) Avail NTlS CSCLOlC The X- 15 adaptive flight control system is briefly described. and system development and flight-test experiences in the X-15 research airplane are reviewed Airplane handling qualities with the N71-18428*# National Aeronautics and Space Administration system and system reliability are also discussed Author Flight Research Center. Edwards. Calif. LIFTING-BODY Progress Report Milton 0. Thompson 1970 4 p Presented at the ELDO/NASA Space Transportation Systems Briefing. Bonn. 7 -8 Jul. 1970 N71-18423# Centre National de la Recherche Scientifique. (NASA-TM-X-66712) Avail: NTlS CSCL 22A Meudon (France) Lab d'Aerothermique The lifting body flight test program, concerning mainly the DELTA WING STUDY IN A LOW DENSITY HYPERSONIC HL-10 reentry vehicle. the M2-F2 lifting body, and the X-24A FLOW [ETUDE D'UN ECOULEMENT HYPERSONIQUE A aircraft is described. The flight test results demonstrate that BASSE DENSITE AUTOUR D'AILES DELTA] configurations designed for lifting entry can have acceptable low Jean Hilegre ana Jean-Llaude resringer Sep 1970 59 p refs speed flight characteristics and adequate maneuverability for approach In FRENCH, ENGLISH summary and landing and are suitable for the shuttle mission. ESRO (Rept-70-9) Avail NTlS Experiments are performed in a rarefied hypersonic flow characterized by a Mach number of 8 and a free stream Reynolds number of 2200 per cm Present results include wall pressure and N71-18439# Office National d'Etudes et de Recherches heat transfer distributions along 60 and 70 deg delta wings. Aerospatiales. Paris (France) considering both incidence and leading edge thickness effects Wall WING LIFT1NG LI NE REPRESENTATION : APPLICATION pressure and heat transfer data on the wing axis are compared TO THE TWO WINGS IN TANDEM lNTERACTlON witn previous theoretical laws valid in the strong interaction regime [REPRESENTATION O'UNE AILE PAR DES LIGNES Drag and lift coefficients are deduced from aerodynamic force PORTANTES: APPLICATION AU CALCUL DE measurements In order to point out the skin friction effect. L'INTERACTION DE DEUX AILES EN TANDEM] aerodynamic force components due only to the wall pressure are Roland Dat and Yoshio Akamatsu 1970 18 p refs In FRENCH; calculated and compared with total aerodynamic force values ENGLISH summary Presented at the AGARD Symp. on Unsteady Author (ESRO) Aerodyn. for Aeroelastic Anal. of Interfering Surfaces. Toensberg. Norway. 3 -4 Nov 1970 Submitted for publication (ONERA-TP-891; Rept-5) Avail NTlS The simulation of wings by a lattice of lifting lines appears N71-18424# Cambridge Univ (England) Dept of Engineering to be suitable for the computation of unsteady aerodynamic IMPROVED ENTRAINMENT METHOD FOR CALCULATING forces on combinations including several lifting surfaces. such as TURBULENT BOUNDARY LAYER DEVELOPMENT wing-horizontal tail or fin-horizontal tail It can be considered as a compromise between the doublet lattice method. which is M R Head and V C Patel London Aeron Res Council Mar advantageous for its flexibility. and the so-called lifting surface 1968 27 p refs SupersedesARC-31043 method. the results of which are more accurate for a given number (ARC-R/ M-3643 ARC-31043) Copyright Avail NTIS. HMSO of collocation points. A numerical program has been developed for 70p BIS $280 the application to wings in two parallel planes. The particular (ARC-RJM-3643 ARC-31043) features of the calculation method are presented, as well as some A simple integral method is presented for the calculation numerical results Author (ESRO) of two dimensional incompressible turbulent boundary layers Use is made of established relationships to determine values of the entrainment coefficient for equilibrium layers and the entrainment N71-18441# Aviatest GrnbH. Duesseldorf (West Germany) coefficient for nonequilibrium conditions is obtained by multiplying the INVESTIGATIONS OF HYPERSONIC CHARACTERISTICS corresponding equilibrium value by a suitable empirical function OF TWO PHASE FLOWS AN0 THECR POSSIBLE USE FOR This increases the entrainment when the rate of growth of the AERODYNAMIC MEASUREMENTS [UNTERSUCHUNGEN layer is less than that of the corresponding equilibrium layer and ZUM UEBERSCHALLVERHALTEN VON decreases it when the rate of growth is greater This variation Of ZWEIPHASENSTROEMUNGEN UND lHRER MOEGLICHEN entrainment is in accordance with ObservatiOn, and a simple ANWENOUNG FUER AEROOYNAMISCHE MESSUNGEN1 physical explanation IS proposed to account for it This explanation V Denk, B Feldmann. and H Griesser Bonn Bundeswehramt further suggests how the effects of flow convergence may be taken 1970 147 p refs In GERMAN, ENGLISH summary Sponsored into account Comparisons with measured boundary layer by Bundesmin fuer Verteidigung developments show the general accuracy of the method (BMVtdg-FBWT-70-1) Avarl NTIS. Bundeswehramt. Bonn 25 Author (ESRO) DM

249 N71-18442

The pilot plant for generation of quasi-homogeneous airplanes The tests have been limited to two types of motion pure water-air-mixture flows IS described Emphasis IS made on the translation and pure pitching oscillation of one wing The model measurement of the two phase flow characteristics and various consisted of two rectangular or swept wings whose relative position measurement methods are dealt with The tests performed confirm could be adjusted continuously in the horizontal and in the vertical the theoretically expected supersonic characteristics of the two direction Several conclusions can be drawn from the test results phase flow at slight flow rates and show the possibility to apply and the phenomena of interaction are shown to be important for the test results to aerodynamics Author (ESRO) certain configurations Some comparisons between theory and experiment have been undertaken Author (ESROI

N71-18442*# National Aeronautics and Space Administration Flight Research Center Edwards Calif N71-18452# Royal Aircraft Establishment Farnborough (England) FLIGHT EVALUATION OF ANGLE OF ATTACK AS A A SURVEY OF SOME EUROPEAN HYPERSONIC RESEARCH CONTROL PARAMETER IN GENERAL-AVIATION AIRCRAFT D Kuechemann 1970 13 p refs Presented at the 4th Shu W Gee Harold G Gaidsick, and Einar K Enevoldson EUROSPACE US-European Conf Venice 22 25 Sep 1970 Washington Mar 1971 23 p refs Avail NTlS (NASA TN D-6210 H-603) Avail NTlS CSCLOlC The aim of the Eurohyp program relating to hypersonic The use of angle of-attack information for a pilots display in boundary layer and flow fields IS reviewed The experimental a general-aviation airplane was investigated to determine whether facilities available in Europe for investigating compressible boundary this form of information would improve performance and flight layers lifting bodies propulsion aerodynamics and fluid dynamics safety An angle-of attack system consisting of a wing-mounted of real gases are listed and discussed It IS concluded that the vane an electronic computer unit and a display instrument was Eurohyp activities may well provide the basis for a future official installed and flight tested in a typical twin-engine general-aviation European research program including the aerodynamic design of airplane The flight test maneuvers were limited to the low-speed hypersonic transport aircraft a space shuttle and its launcher flight region where the benefits of angle of attack presentation ESRO were likely to be greatest Some of the expected advantages of this parameter such as visual indication of stall margin and its independence of gross weight and flap position were realized however certain aerodynamic characteristics of the airplane such N71-18456# National Physical Lab Teddington (England) as the phugoid and directional control capability were found to Aerodynamics Div limit and tended to negate some of the expected advantages As WAKE BLOCKAGE CORRECTIONS IN A CLOSED WIND a result this use of angle of attack did not show a significant TUNNEL FOR ONE OR TWO WALL-MOUNTED MODELS improvement in performance and flight safety Author SUBJECTTO SEPARATED FLOW R W F Gould London Aeron Res Council Feb 1969 23 p refs Supersedes NPL-AERO-1290 ARC 31007 (ARC-R/M-3649. NPL-AERO-1290 ARC 31007) Copyrighf Avail N71-18444# Deutsche Forschungs- und Versuchsanstalt fuer Luft- NTlS HMSO 60p BIS $240 und Raumfahrt Porz (West Germany) Abteilung Ueberschallkanal Measurements described show that wake blockage corrections EFFECT OF THE POSITION OF MAXIMUM THICKNESS apply to rectangular plates normal to the flow over the aspect AND OF THE LENGTH OF BODIES OF REVOLUTION ON ratio range from 1/3 to 3 tested, whether the plates are mounted AERODYNAMIC COEFFICIENTS IN SUPERSONIC FLOW on the tunnel axis or adjacent to a wall Only small nonlinear [EINFLUSS DER DICKENRUECKLAGE UND DER effects were found even when the corrections approached 100% RUMPFLAENGE VON ACHSENSYMMETRISCHEN Blockage correction formulas are developed for use when two FLUGKOERPERN AUF DIE AERODYNAMISCHEN BEIWERTE models are present in the working section at the same time (but IM UEBERSCHALL] each outside the wake of the other) The method of determining Hansgeorg Riedel. Hans Emunds and Franz Joachim Niezgodka the required blockage factors is described with examples from Nov 1970 190 p refs In GERMAN ENGLISH summary measurements on flat plates mounted normal to a wall and on (DLR-FB-70-54) Avail NTIS. ZCDl Munich 66.60 DM lattice models Author (ESROI The aerodynamic coefficients of bodies of revolution consisting of ogive-cylinder combinations were determined in a 30 x 30 sq cm supersonic wind tunnel by force and pressure measurements for the Mach number range from 1 57 to 4 15 A comparison is made of the results with the slender body theory and a first and N71-18461# Royal Aircraft Establishment Farnborough second order theory Author (ESROI (England1 Aerodynamics Dept WIND-TUNNEL INVESTIGATIONS OF INSTABILITY IN A CABLE-TOWED BODY SYSTEM N71-18449# Office National d Etudes et de Recherches A R Mettam London Aeron Res Council Feb 1969 23 p Aerospatiales Paris (France) refs Supersedes RAE-TR-69022 ARC 31372 MEASUREMENT OF UNSTEADY AIR LOADS OF (ARC-R/M 3644 RAE-TR-69022 ARC 31372) Copyright Avail INTERACTING LIFTING SURFACES IN TANDEM [MESURES NTlS HMSO 8Op BIS $320 DES FORCES INSTATIONNAIRES D’INTERACTION ENTRE A brief investigation was made into instability of a body SURFACES PORTANTES EN TANDEM] towed by a helicopter This was undertaken after an incident in Roger Destuynder 1970 13 p refs In FRENCH ENGLISH which a divergent oscillation led to cable failure in flight Stability summary Presented at the AGARD Symp on Unsteady Aerodyn boundaries in terms of cable length and forward speed were for Aeroelastic Anal of Interfering Surfaces Toensberg. Norway determined for the original cable/body system The effects of various 3 4 Nov 1970 Submitted for publication body and suspension modifications were then studied Existing (ONERA-TP-890) Avail NTlS theory was compared with the experimental results and both were Wind tunnel tests have been performed for analyzing the used in forecasting the behavior of a new cable/body system influence of several parameters on the aerodynamic interference Subsequent expenmental work elsewhere confirmed the validity of between two lifting surfaces in tandem The aim was lo determine the these estimates Enhanced stability of the system was observed at magnitude of the coupling terms in order to provide a theoretical short cable lengths and a possible explanation is suggested explanation of the flutter instabilities occurring on variable sweep Author (ESRO)

250 N71- 18480

N71-18462# Office National d'Etudes et de Recherches Versuchsanstalt No 47 Aerospatiales. Paris (France). Avail NTlS COMPUTATION OF THE AERODYNAMIC INTERACTIONS A procedure is shown for calculating the potential flow BETWEEN AIRCRAFT LIFTING ELEMENTS IN around rotationally symmetrical ring profiles using the singularity SUPERSONIC STEADY OR UNSTEADY FLOW [CALCUL method Contrary to linearized methods. utilizing singularity D'INTERACTIONS AERODYNAMIOUES ENTRE LES distributions on a cylindrical substitute body. this procedure uses ELEMENTS PORTANTS D'UN AVION EN ECOULEMENT vortex distributmns on the curved profile surface Main problems of SUPERSONIOUE STATIONNAIRE OU INSTATIONNAIRE] profile theory for ring profile skeletons and thick ring profiles are Michel Enselme. Jean-Paul Boisseau. and Andre Guillois 1970 solved ESRO 8 p refs In FRENCH; ENGLISH summary Presented at the AGARD Meeting on Aerodyn. Interference. Silver Spring. MD.. 28 - 30 Sep. 1970 Submitted for publication (ONERA-TP-850) Avail: NTlS N71-1&471# Deutsche Forschungs- und Versuchsanstalt fuer Luft- After recalling the principle of analog computation of a und Raumfahrt. Berlin (West Germany) Abteilung Aeroakustik lifting assembly in supersonic steady or unsteady flow a numerical und Instabilitaet process copied on the analog process using an explicit method for A NOTE ON THE SPATIAL JET-INSTABILITY OF THE computing the solutions of the wave equation is presented COMPRESSIBLE CYUNDRl CAL VORTEX SHEET Results obtained either by analog or bv numerical computation are Alfons Michalke Oct 1970 20 p refs presented. They concern wing-body or wing-pod interactions. and (DLR-FB-70-51) Avail NTIS. ZLDl Munich 6 20 DM The linearized inviscid disturbance equations were derived the computation of a wing of arbitrary planform in unsteady flow. Author IESRO) for a compressible circular jet with variable temperature and density profile The eigenvalue changes of the instability problem for the cyldindrical vortex sheet were computed and discussed for the variations with Strouhal and Mach numbers, and temperature N71-18464# Office National d Etudes et de Recherches ratios It was found that contrary to temporal amplification the Aerospatiales Paris (France) phase velocity of spatially growing disturbances can exceed the let WIND TUNNEL INVESTlGATiON INTO AERODYNAMIC velocity Furthermore. additional disturbance modes can exist in the INTERACTIONS INDUCED BY DROP LOADS [ETUDE spatial case Author (ESRO) EN SOUFFLERIE DES INTERACTIONS AERODYNAMIQUES DUES AUX CHARGES LARGABLES] Jean Christophe and Jacques Gxte 1970 13 p refs In N71-18472# Max-Planck-lnstitut fur Stromungsforschung. FRENCH. ENGLISH summary Presented at the AGARD Meeting Gottingen (West Germany)

on Aerodyn Interference. Silver Spring MD I 28-30 Sep 1970 PECULIARITIES OF TURBULENT WAKES Submitted for publicatton [E iG E NTUE M LI CHKEI TE N TUR B U LE NTER (ONERA-TP-849) Avail NTlS NACHLAUFSTROEMUNGEN] The wind tunnel techniques currently used for the investqatlon R Ermshaus 1970 94 p refs In GERMAN Its Mitt aus dem into aerodynamic interactions induced by drop loads are reviewed Max-Planck-lnst fuer Stroemungsforsch und Aerodyn and some representative results shown Special attention is paid Versuchsanstalt No 46 to directly tracing the tralectories of dropped loads and Avail NTlS microrocket-propelled missiles by high-speed filming in the tunnel Mean and turbulent parameters of plane and rotationally The results so obtained are compared with those of the newly symmetrical wakes were investigated in a wind tunnel The results developed alternative method of weighing the load in the show distinct differences in the profiles of their wakes For both aerodynamic field of the arcraft and reconstructing its trajectory by types of wake a uniform exponent of width development was a computing routine Author (ESRO) found ESRO

N71-18466# Cambridge Univ. (England). Dept. of Engineering. CALCULATION OF THE TURBULENT BOUNDARY LAYER N71-18473# Office National d'Etudes et de Recherches IN A VORTEX DIFFUSER Aerospatiales. Paris (France). T.-S. Cham and M. R. Head London Aeron Res. Council May APPLICATION OF LIFTING SURFACE THEORY TO WINGS 1969 32 p refs Supersedes ARC-31237 WlTH CONTROL' SURFACES [APPLICATION DE LA (ARC-R/M-3646; ARC-31 237) Copyright. Avail: NTIS: HMSO: THEORIE DE LA SURFACE PORTANTE A DES AILES 80p. BIS: $3.20 MUNIES DE GOUVERNES] In two dimensional potential flow the combination of a source Bertrand Darras and Roland Dat 1970 15 p refs In FRENCH: and free vortex produces an axisymmetric flow with streamlines in ENGLISH summary Presented at the AGARD Symp. on Unsteady the form of equiangular spirals Calculations have been made of Aerodyn. for Aeroelastic Anal. of Interfering Surfaces. Toensberg. the turbulent boundary layer developing beneath such a flow and the Norway. 3 - 4 Nov. 1970 Submitted for publication results have been compared with measurements made elsewhere. (ONERA-TP-889) Avail: NTlS The integral equations of momentum and entrainment are satisfied The problem of control surfaces in subsonic unsteady flow in a streamline coordinate system in the calculation method used. is considered. The method for solving it is based on the formulation Author (ESRO) of the logarithmic singularity of the pressure field and on an analysis of the usual matrix solution of the integral equation. This method is extended here to an arbitrary planform. The comparison of experimental and theoretical results obtained for the rectangular N71-18469# Deutsche Forschungs- und Versuchsanstalt fuer wing is also shown Author (ESRO) Luft- und Raumfahrt. Goetttingen (West Germany) CALCULATION OF THE POTENTIAL FLOW AROUND ROTATiONALLY SYMMETRICAL RiNG PROFILES [BERECHNUNG DER POTENTIALSTROEMUNG UM N71-18480*# National Aeronautics and Space Administration. ROTATIONSSYMMETRISCHE RINGPROFILE] Langley Research Center. Langley Station. Va. W Geissler 1970 120 p refs In GERMAN Its Mitt aus dem EXPERIMENTAL WAKE SURVEY BEHIND A 120 DEG Max-Planck-lnst fuer Stroemungsforsch und Aerodyn INCLUDED ANGLE CONE AT ANGLES OF ATTACK OF 0

251 N71-I8499

DEG AND 5 DEG, MACH NUMBERS FROM 1.60 TO 3.95, being about 82 deg Ellipticity is as low as 0 5 d8 with a AND LONGITUDINAL STATIONS VARYING FROM 1.0 TO maximum of 3 0 d8 at 800 MHz The feed impedance is 50 ohms 8.39 BODY DIAMETERS unbalanced and the gain is about 7 dE relative to a circular Clarence A Brown, Jr James F Campbell and Dorothy H Tudor isotropic source It is particularly suitable where projections beyond Washington Jan 1971 344 p refs the aircraft hull are undesirable Author (ESRO) (NASA-TM-X-2139. L-7517) Avail NTlS CSCL 200 An investigation was conducted to obtain flow properties in the wake of a 120 deg-included-angle cone at Mach numbers from 1 60 to 395 and at angles of attack of 0 deg and 5 deg The wake flow properties were calculated from total and static N71-18532# Laboratorium fur Eetriebsfe6tigkeit. Darmstadt (West pressures measured with a pressure rate at longitudinal stations Germany) varying from 0 42 to 3 0 body diameters These measurements SERVICE LOADS OCCURRING ON MAIN LANDING GEARS showed a consistent trend throughout the range of Mach numbers OF F-104G TYPE AIRPLANES [BETRIEBSKRAEFTE AN and longitudinal distances and an increase in dynamic pressure HAUPTFAHRWERKEN DES FLUGZEUGES F-104Gl with increasing downstream position Author 0 Buxbaum Fraunhofer Ges Jan 1970 104 p refs In GERMAN ENGLISH summary Sponsored by Eundesmin fuer Verteidigung Prepared for Entwicklungsring Sued N71-18499*# Boeing Co Seattle Wash (FE-82-1969) Avail NTlS STUDY AND DEVELOPMENT OF TURBOFAN NACELLE At the main landing gears of two airplanes vertical lateral MODIFICATIONS TO MINIMIZE FAN-COMPRESSOR NOISE and drag loads have been recorded continuously during 50 flights ' RADIATION VOLUME 7. SUBJECTIVE EVALUATION and have been analyzed statistically The loading conditions such TESTS Contractor Report, 1 May 1967 1 Nov 1969 as landing springback taxi transition braking engine run-up Washington NASA Jan 1971 104 Q refs turning and pivoting the cumulative frequencies and extreme value (Contract NAS1-7129) (NASA CR 17171 Avail NTlS CSCLOlC distributions of the different loads in the three axes are presented Judgments of relative annoyance caused by flyover noises The correlations between simultaneously occurring load components from a standard Eoeing 707 3208 and one with acoustically are also discussed Author (ESRO) treated nacelles were made by 180 persons The primary aim of the experiment was to determine whether the noise reductions measured during previous flight tests of the acoustically treated N71-18556# Aerospace Corp El Segundo Calif Lab Operations nacelles would be perceived by a sample of persons from the NEAR-CONTINUUM AXISYMMETRIC HYPERSONIC FLOW community This aim was achieved by determining the relationship PAST VERY SLENDER BODIES, OCTOBER 1969 -JULY between the noise ratings of the 180 judges and each of 18 1970 engineering calculation procedures that convert sound pressure John W Ellinwood 30 Oct 1970 45 p refs spectra into subjective units Author (Contract F04701 70 C-00591 (AD 715901 TR-0059 6240-10 2 SAMSO TR 70-409) Avail NTlS CSCL 20/4 N71-18509*# National Aeronautics and Space Administration The hypersonic theory for boundary layers with large transverse Flight Research Center Edwards, Calif curvature is relaxed to allow surface slip and lump Slip and jump VERIFICATION OF TAKEOFF PERFORMANCE coefficients for use with this contmuum theory are found to be' PREDICTIONS FOR THE XB-70 AIRPLANE essentially unaffected by transverse curvature of the Knudsen layer Terry J Larson and William G Schweikhard Washington Mar This finding follows from a study of the linearized model equation 1971 29 p refs including transverse curvature terms with diffuse reflection and total (NASA-TM-X-2215. H-574) Avail NTlS CSCL 01C accommodation assumed at the surface When used to estimate XE-70 airplane standardized takeoff data are compared with skin friction on an insulated 5-deg half-angle cone in helium at simple predictions based on aerodynamic and engine estimates Mach 29 the present theory proved to be both sufficient and useful Effects of atmospheric and aircraft variables on takeoff distance are over most of the transitional flow regime The slip velocity ratio evaluated Although experimentation with various techniques for us is two and a half times as large as Mach number over root aircraft rotation to liftoff attitudes was limited the effects of the Reynolds number which measures other neglected near continuum pilot techniqiies used are discussed and compared Predictions of effects Author (GRA) distance from brake release to initiation of rotation as a function of velocity were found to be accurate to approximately 100 feet Because of the significant drag at the high aircraft attitudes N71-18558*# National Aeronautics and Space Administration required for takeoff the standardized ground roll distance for a given Ames Research Center Moffett Field Calif velocity was increased nominally by 400 feet over the distance AERODYNAMIC CHARACTERISTICS OF A LARGE-SCALE which would occur with no increase in drag Standardized V/STOL TRANSPORT MODEL WITH TANDEM LIFT FANS performance during climb from liftoff to a heiiqht of 35 feet with MOUNTED AT MID-SEMISPAN OF THE WING all engines operating was marginal because of low longitudinal Stanley 0 Dickinson Leo P Hall and Brent K Hodder accelerations resulting from high induced drag at liftoff attitude Washington Mar 1971 64 p refs Author (NASA-TN-D-6234 A 31891 Avail NTlS CSCLOlC The low-speed aerodynamic characteristics of a large scale V/STOL transport model powered by tip-turbine driven fans were N71-18519# Royal Aircraft Establishment Farnborough (England) investigated The model has four fans tandem mounted in pods THE DESIGN AND DEVELOPMENT OF AN AIRCRAFT fore and aft of the wing at mid-semispan The high mounted wing MOUNTING PRINTED-CIRCUIT SPIRAL AERIAL COVERING had an aspect ratio of 58 was swept back 35 deg at the THE RANGE 200-800 MHz quarter-chord line and had a taper ratio of 0 3 The results showed D P L May G F Milne and F 0 Baker Apr 1970 41 p a large increase in lift with forward speed in spite of the refs unloading of the wing induced by front fan operation Longitudinal (RAE TR 700621 Copyright Avail NTlS characteristics with four fans operating appear to be similar to the The measured characteristics of a right hand circularly polarized characteristics of conventlonal aircraft A comparison of test results uiidirectional aerial covering from 200 to 800 MHz in two past and present, indicates that a configuration with the front fans octave-wide ranges are given The beam width and circularity are at wing mid-semispa? dnd the aft fans inboard near the wing root remarkably constant throughout the band half power beam width may have good induced lift characteristics Author

252 N71- 18593

N71-18559*# National Aeronautics and Space Administration. Gilbert G. Robinson and Michael J. Bondi Washington Mar. Ames Research Center, Moffett Field. Calif. 1971 22 p refs FURTHER STUDIES OF THE EXTRAPOLATION OF NEAR (NASA-TN-D-6232; A-2842) Avail: NTlS CSCLOl C FIELO OVERPRESSURE DATA The system described provides the necessary precise range Joel P. Mendoza and Raymond M. Hicks Washington Mar. 1971 measurements for the trilateration technique used in guiding 34 p refs V/STOL aircraft during all-weather and variable approach operation. (NASA-TM-X-2219: A-3716) Avail: NTlS CSCL2OD In a trilateration schdme. two or three ranges are measured from The technique of extrapolating measured near-field overpressure the aircraft to transponders on the ground. Each range is measured data to any larger altitude has been applied to wird-tunnel by determining the phase delay of a continuous radio wave overpressure data for a wide variety of wing-body combinations. A transmitted from the aircraft to a ground transponder and back. For compilation of measured and extrapolated overpressure data is precision, three radio waves of different frequencies are transmitted presented here in an effort to show the range of configurations for to each transponder to provide a coarse. a fine. and a very fine which the extrapolation technique is applicable. Included are simple measurement of range. Thus to obtain the inherent accuracy of the shapes. such as cone-cylinder and unswept wing-alone models. as very fine measurement unambiguously. this measurement must be well as complete airplane configurations. The range of test Mach combined properly with the fik and coarse range data Furthermore. numbers was 1.41 to 3.0. while the altitude to model length ratio the effect of noise on the range words should be minimized. To varied from 1 to 20. Except for the case of a high aspect ratio achieve maximum accuracy. the system investigated presented the wing-alone model. the extrapolation procedure was shown to give primary range data in digital form. A range resolution a!gorithm is almost perfect agreement with experimental measurement: even described that allows three ambiguous digital range words derived for the high aspect ratio wing alone. the agreement was adequate. from a phase measuring system to be combined into a single range A method for determining the validity of the extrapolation is word that is unambiguous up to 32 miles. The word retains the discussed. Author very fine resolution afforded by the most precise of the three range words and eliminates the effect of noise to a high degree. The algorithm is developed theoretically and is mechanized. Examples are given showing typical operation. Measurements of the range to N71-18560*# National Aeronautics and Space Administration an aircraft making an overhead pass indicate that range can be Lewis Research Center Cleveland. Ohio measured to a precision of at least 1.6 feet under actual flight COMBUSTION STABILITY LIMITS FOR SWIRL JET conditions. Author COMBUSTOR MODULES COMBINING AIR SWIRL AND iMPlNGlNG JEl ATOMIZATION OF ASTM A-1 FUEL Robert0 lngebo Washington Mar 1971 13 p refs (NASA-TM-X-2218) Avail NTlS CSCLZlE N71-18572# Centre National de la Recherche Scientifique. Eight different designs of swirl-jet combustor modules were Meudon (France) Lab d'Aerothermique tested in a 3 25-inch-diameter duct with 600 F air at reference EXTERNAL SOUND FIELD EFFECT ON A TURBULENT velocities of 200 to 500 feet per second and atmospheric pressure LAYER [INFLUENCE O'UN CHAMP ACOUSTIQUE The highest ratio of rich-to-lean combustion stability limits was EXTERIEUR SUR UNE COUCHE LIMITE TURBULENTEI obtained with a module consisting of a single air swirler. a single Pierre Gougat Sep 1970 103 p refs In FRENCH pair of 180 deg impinging fuel jets 10 076-cm diameter ), and a (Rept-70-8) Avail NTlS LGk&Srip-type fianie staoiiizer Results were consideraaly better The response of a boundary layer to harmonic OscillatiOnS than those obtained in recent investigations using swirl-can is analyzed The study is restricted to the influence of an acoustic combustor modules Author field on heat exchange in a turbulent boundan/ layer on a flat plate Wind tunnel tests have been performed using a hot-wire anemometer linked to a Wheatstone bridge It IS shown that an N71-18561*# National Aeronautics and Space Administration. ultrasonic fteld is not appropriate and that with the wind tunnel used Lewis Research Center. Cleveland. Ohio. measurements were not possible for low frequencies ESRO EFFECT OF VARIOUS DIFFUSER DESIGNS ON THE PERFORMANCE OF AN EXPERIMENTAL TURBOJET COMBUSTOR INSENSITIVE TO RADIAL DISTORTION OF N71-18586# Deutsche rorschungs- und Versuchsanstalt fuer INLET AIRFLOW Luft- und Raumfahrt. Brunswick (West Germany) lnst fuer James A. Biaglow Washington Mar. 1971 19 p refs Flugmechanik (NASA-TM-X-2216; E-5975) Avail: NTlS CSCLZlE DETERMINATION OF THE COEFFICIENTS IN Tests were performed on an experimental combustor MULTIVARIABLE SYSTEMS OF FLIGHT DYNAMICS BY A insensitive to shifts in the radial velocity profile at the compressor MODEL WITH AUTOMATIC PARAMETER ADJUSTMENT outlet. The purpose was to investigate alternate diffuser designs for USING AN ANALOG COMPUTER [BESTIMMUNG DER this type combustor. Test conditions were atmospheric pressure, KOEFFIZIENTEN IN MEHRGROESSENSYSTEMEN DER 600 F inlet air temperature. and average exit temperatures up to FLUGMECHANIK DURCH EIN MODELL MIT 2200 F. The fuel used was ASTM A-1. The performance of a AUTOM ATISCHER PARAMETEREI NSTELLU NG AM dump-type diffuser and a 53 deg wide-angle diffuser showed that ANALOGRECHNER] these designs of simple construction may be interchanged with Ruthard Koehler Jul 1970 27 p refs In GERMAN. ENGLISH that of the previously developed combustor without penalty. Tests summary of three diffusers with different axial lengths but similar to the (DLR-FB-70-30) Avail NTlS ZLDI Munich 9 DM design used in the previously developed combustor were investigated A multivariable system described by a system of linear only at isothermal conditions with 600 F inlet air. When the differential equations with constant or slowly varying coefficients diffuser length to inlet height ratio was changed from 4.0 to 7.0. can be analyzed by a model with automatic parameter adjustment at an inlet Mach number of 0.30. the combustor total-pressure loss For checking the method, the longitudinal motions of an aircraft decreased from a nominal value of 7.1 to 5.4 percent. Author and a helicopter were simulated and analyzed using an analog computer The results are discussed Author (ESRO)

N71-18566*# National Aeronautics and Space Administration Ames Research Center. Moffett Field. Calif N71-18593# Deutsche Forschungs- und Versuchsanstalt fuer AN ALGORITHM FOR DIGITAL RESOLUTION OF RANGE Luft- und Raumfahrt. Goettingen (West Germany) FOR VfSTOLAIRCRAFT HYPERSONIC LOW DENSITY WIND TUNNEL PLANT

253 N71-18628

[EINE HYPERSONISCHE WINDKANAIANIAGE FUER KLEINE crosswind velocity are considered for single-. two-, and four-nozzle GASDICHTEN] (rectangular) arrangements. Author G Hefer. G Koppenwallner H Legge and W Wuest Bad Godesberg West Ger Bundesmin fuer Bildung und Wiss Sep 1970 93 p refs In GERMAN. ENGLISH summary Sponsored N71-18717# Air Force Systems Command Wright-Patterson AFB by Bundesmin fuer Bildung und Wiss Ohio Aero Propulsion Lab (BMBW-FB-W-7051) Avail NTIS. ZLDl Munich 19 10 DM OPERATING CHARACTERISTICS OF THE AFAPL A new plant consisting of a vacuum tunnel with two test HYPERSONIC SHOCK TUNNEL Technlcal Report, Jun sections of different sizes and Mach number ranges and a high 1966 Feb 1969 vacuum tunnel with two separate pumping systems IS described R R Craig Aug 1970 41 p refs The auxiliary equipment serving mainly the electroforming and (AD 71 5907 AFAPL TR 70 2) Avail NTlS CSCL 14/2 electroplating of the wind tunnel models and the cooling of models A description is pvesented of the development efforts and nozzles by liquid nitrogen is also described A short survey accomplished to make the AFAPL Hypersonic Shock Tunnel an on research work carried out in the hypersonic tunnel is given operational aerodynamic facility A semiconductor strain gage Author (ESRO) pressure transducer was developed to overcome calibration problems with the original pressure transducer design Heat transfer measurements were initially made using standard shock tunnel thin N71-18628*# National Aeronautics and Space Administration film gage technology Gage erosion problems were solved through Lewis Research Center Cleveland Ohio use of a surface thermocouple which uses n-p germanium crystal NUCLEAR POWER FOR SURFACE EFFECT VEHICLE AND elements Improved data recording capability was achieved with AIRCRAFT PROPULSION the installation of a 64 channel digital data system A contoured Frank E Rom [1970] 21 p refs Presented at the 7th Ann nozzle with interchangeable throats to provide parallel uniform Meeting of the AlAA Houston Tex 19 22 Oct 1970 flows at Mach 8 9 10 and 11 was installed and calibrated The (NASA TM-X-52963) Avail NTlS CSCL 1BL nozzle produced good flow profiles up to six feet from the nozzle Preliminary results of an economic study of large nuclear exit Author (GRA) surface effect vehicles and aircraft indicate that these vehicles may have the potential for hauling transoceanic commerce at rates of 1 to 2 cents per ton mile Transoceanic commerce forecast for N71-18729# Air Force Systems Command, Wright-Patterson 1980 indicates that it would take 1500 10,000 ton gross weight AF8. Ohio. Aero Propulsion Lab. surface effects vehicles to handle all the cargo that is worth A KINETIC STUDY, OF THE CATALYTIC shipping at 1 to 2 cents per ton mile Similarly it would take 500 DEHYDROGENATION OF METHYLCYCLOHEXANE AT 600, 10 000 ton aircraft to handle this same volume One of the most 860, AND 700 F AND APRESSURE OF 5 ATMOSPHERES important technical problems is the problem of safety during high Herbert R. Lander, Jr. Oct. 1970 137 p refs speed impacts Tests of mobile reactor models indicate a potential for (AD-7 15926: AFAPL-TR-70-46) Avail: NTlS CSCL 2 1/4 withstanding impacts up to 1000 feet per second with reinforced Fuel enthalpy offers a readily available heat sink and can concrete without rupturing or producing leaks in the reactor be used to dissipate the aerodynamic heating that results from containment vessel Author sustained high speed flight in the earths atmosphere, but is effective only up to certain levels of temperature. Catalytically enhanced heat-absorbing chemical reactions, however. can be used to increase N71-18651# Air Force Systems Command Wright Patterson the heat sink capacity from the fuel enthalpy. These reactions AFB Ohio Materials Lab include dehydrogenation, dehydrocyclization. depolymerization. and DEVELOPMENT AND CALIBRATION OF A MACH 12 hydrocracking. The dehydrogenation of methylcyclohexane over a RAIN EROSION TEST APPARATUS Technical Report, Mar commercially available platinum-alumina catalyst bed will 1966 Aug 1969 approximately double the heat sink from fuel enthalpy. The Charles J Hurley and George F Schmitt Jr Oct 1970 79 p dehydrogenation reaction was studied at temperatures of 600.650. refs and 700 degrees F and a pressure of 5 atmospheres. Tabulations (AD-715909. AFML-TR-70 240) Avail NTlS CSCL 14/2 and plots of test data are presented on the effects of time. reaction Development of 3 Mach 1 2 rain erosion test apparatus rate. molar feed ratio, presence of toluene, presence of reactor is described This rotating arm apparatus is capable of evaluating the inerts. reaction pressure, and temperature. Author (GRA) relative rain erosion resistance of materials and can be operated at speeds of 450 to 900 mph in a 1 or 2 inch/hour simulated rainfall The report describes the design and development of the N71-18733*# National Aeronautics and Space Administration apparatus including the rotating arm power train. test enclosure Lewis Research Center, Cleveland, Ohio. rain simulation and control systems Calibration and correlation PARAMETRIC ENGINE STUDY FOR A MACH 0.98 experiments are also described Author (GRA) COMMERCIAL AIR TRANSPORT John B. Whitlow. Jr., Gerald A. Kraft. and Kestutis C. Civinskas Feb. 1971 33 p refs N71-18714.# Dynasciences Corp.. Blue Bell. Pa. Scientific (NASA-TM-X-52961- E-6154) Avail: NTlS CSCL21 E Systems Div. Advanced engine weight technology. compatible with a PRACTICAL ENGINEERING METHODS FOR PREDICTING mid-decade introduction into commercial service. was used in the HOT GAS REINGESTION CHARACTERISTICS OF V/STOL study of the three-engine, 300-passenger airplane with the AIRCRAFT JET LIFT ENGINES supercritical wing. A takeoff gross weight of 386.000 pounds was L. Gray and E. Kisielowski Feb. 197 1 17 1 p refs selected to provide a range of about 3000 nautical miles. Fan (Contract NAS1-9465) pressure ratios (FPR) from 1.50 to 2.25 and takeoff turbine-inlet (NASA-CR-111845; DCR-323) Avail: NTlS CSCLZlE temperatures from 2460 to 2860 R were considered. Significant Engineering methods are presented for predicting the improvements in range were obtained by raising the FPR over this temperatures and vel,ocities in the vicinity of vertical lift engines of spectrum when bypass ratio (BPR) and overall pressure ratio (OPR) jet V/STOL aircraft operating near the ground. The methods are were optimized. An increase in inlet temperature over the spectrum based on existing theoretical analyses, available test data. and considered here had much less effect on range than an increase empirical and semiempirical approaches. Parametric variations in in FPR. Neither the approach nor the (lift-off) sideline noise engine nozzle diameter, pressure, temperature, height, and ambient requirements of F.A.R could be met with any of these engines

254 N71-18836 without acoustic treatment of the nacelles. Even with acoustic AIRCRAFT WITH AN APPLICATION TO THE LANDING treatment, only one-stage fan engines could meet the approach APPROACH requirement for the maximum suppression of 15 PNdb assumed in Stuart C Brown and Homer 0 Lee Washington Mar 1971 this study. Unfortunately. FPR must therefore be limited to about 46 p refs 1.7. Author (NASA-TN-D-6230. A-3244) Avail NTlS CSCL 01 C A method involving the minimuation of a performance criterum was used to analyze the ability of automatically controlled aircraft to N71-18734# Human Engineering Labs..Aberdeen Proving Ground. maintain accurate flight-path control during the landing approach Md. The criterion was based primarily on the ability of the aircraft to VISUAL DETECTION OF ILLUMINATING SURFACES follow a constant slope glide path in the presence of statistically RichardT. Maruyama Oct. 1970 74 p refs described gust disturbances Constraints on the adjustments of the (AD-71 5851; HEL-TM-26-70) Avail: NTlS CSCL 1/3 linear control system parameters were included as part of the Determining the requirements of helicopter lighting requires method The method was implemented by means of a digital selecting the major factors that contribute to the lighting power computer to perform the parameter search required for the of a surface light source. Since the light source must be functional. minimization of the performance index The utility of the method sky brightness. atmospheric attenuation and other characteristics of was evaluated by determining effects of variations in several aircraft light sources such as size, shape and angular velocity must be parameters on the control of longitudinal motions of a subsonic and a supersonic jet transport aircraft Author studied. The report presents a model that looks at each of these variables separately. More investigation is needed in the field of search time to improve the reliability of the model for given background luminances. The necessary light output for an area light N71-18801# Curtiss-Wright Corp.. Wood-Ridge. N.J. source can be determined by methods described: in addition the WTF-48 SINGLE ROTOR COMPRESSOR DEVELOPMENT required boundary range for a surface light source can be computed Final Technical Rapon for almost all conditions. Author (GRA) Charles H. Muller 6 Nov. 1970 61 p refs (Contract NOOOl9-69-C-0533) (AD-7 15626: CW-WR-69-098F) Avail: NTlS CSCL 21 /5 N71-18739# Illinois Univ. Urbana Aviation Research Lab Development of the redyced scale WTF-48 lift fan engine THE FREQUENCY-SEPARATED DISPLAY PRINCIPLE, was continued under this program. The objective of the program PHASE 2 Annual Summary Report. 1 Apr. 1969 -31 Oct. 1970 was improvement of the pressure ratio, efficiency and diffusion of David C Denny, Steven L Johnson, and Stanley N Roscoe Oct the Compressor rotor. This program investigated the effects of 1970 18 p refs debtunting and sweep of the rotor trailing edge and modification of (Contract NOOOl4-67-A-0305-0014) the passage area schedule and wall contours. The modifications (AD-7 15458. TR-ONR-70-3) Avail NTlS CSCL 1 /4 investigated in this program did not produce increased rotor pressure The report includes (1) a brief review of the ratio or efficiency. An increase of 11% in rotor static pressure. frequency-separated display problem, (2) a summary of the work accompanied by a 20% reduction in diffuser losses. was accomplished during Phase I. (3) work accomplished during Phase accomplished. This improvement produced a 5 point increase in 11. (41 research plans for Phase 111. and (5) personnel involved in stage efficiency of the compressor. Author (GRA) the research Author (GRA)

N71-lB815# Federal Aviation Agency, Washington. D.C. N71-18749*# General Motors Corp.. Indianapolis. Ind. Detroit SYSTEM DESCRIPTION OF THE FIELD TEST MODEL OF Diesel Allison Div. THE MODULAR ALPHA NUMERIC NON-TRACKING ATC SINGLE STAGE EXPERIMENTAL EVALUATION OF SYSTEM (ARTS2J BOUNDARY LAYER BLOWING AND BLEED TECHNIQUES Nov. 1969 37 p FOR HIGH LIFT STATOR BLADES, 5 Final Report Avail: NTlS R J. Loughery. R. A. Horn, Jr. and P. C. Tramm Mar. 1971 106 p refs The field test model of the automated radar terminal system (Contracts NAS3-7619; NAS3-7900) (ARTS :) is described. The system is suitable for application to (NASA-CR-54573: EDR-6060) Avail: NTlS CSCL 01A radar terminal facilities that do not meet the requirements for the Tests were conducted on a single-stage compressor rig ARTS 3 system. Various aspects of the system are treated in to determine the feasibility of increasing stator Made loading separate sections and include: (1) a presentation on the system's beyond current levels by bleeding or blowing the suction surface background, environment. design objective. and expansion: (2) a boundary layer. The compressor rig employed stator hub and tip end description of the equpment and computer programs empbyd in the wall boundary layer bleeds. Six highly loaded stator configurations programmable ARTS 2 feld evaluation model; (3) an operational were tested. One of the configurations employed no suction surface description of the capability of the system when applied to existing boundary layer bleeding or blowing features and was used to facilities utilizing present radar and beacon subsystems: and (4) a establish a performance base line. Two stator configurations provided section illustrating the system functions for typical arrival and for Suction Surface boundary layer bleed and the other three stator departure control actions. D.LG. configurations employed features to reenergize the suction surface boundary layer by blowing. A significant improvement in stator performance was achieved withsuction surface boundary layer bleed compared to the baseline configuration. Performance with suction N71-18836*# National Aeronautics and Space Administration surface boundary layer blowing was generally inferior to that of the Ames Research Center, Moffett Field. Calif baseline contiguration. Author A QUADRATIC PERFORMANCE INDEX FOR A VTOL AIRCRAFT PREFILTER MODEL REFERENCE ATTITUDE CONTROL SYSTEM Terrence D Gossett and Lloyd D Corliss (Army Mobility R and D N71-18761*# National Aeronautics and Space Administration Lab ) Washington Mar 1971 46 p refs Ames Research Center, Moffett Field. Calif (NASA-TN-D-6231, A-2897) Avail NTIS CSCLOlC A TECHNIQUE FOR EVALUATING PARAMETER Several performance criteria methods for optimizing a prefilter VARIATIONS FOR AUTOMATICALLY CONTROLLED model reference control system are reviewed. and the quadratlc

255 N7 1- 18838 performance index is studied in detail The prefilter model reference (NASA-CR-1752) Avail NTlS CSCLOl C system consisted of a second order model and a fourth order Various flyover noise measures are reported for noise data follower The form of this follower system was typical of that recorded at five ground positions located underneath and to the required for a VTOL aircraft in hover For the VTOL problem the side of the flight path during 20 controlled level flight flyovers of quadratic performance index was found to be the most versatile two aircraft. (a four-engine piston airplane and a four-engine and comprehensive criterion Weighting matrices for various turbojet airplane) during one day of flight tests Noise measures are sytem states can be iterated until the desired system response is compared to show the degree of variability among flyover obtained that is if the response is too oscillatory the elements of the measurements during repeat runs or among measurements made at weighting matrices can be changed to produce a less oscillatory different positions during the same flyover and to show the degree of response A major advantage of the quadratic performance index correlation between different flyover noise measures The reported is that it can be minimized through the use of readily available flyover measures range from those derived from simple frequency digital computer programs The solution of these programs provides weighting networks, such as the A- or N-weighted sound levels. a set of optimal gains for a given system configuration and the to those computed from one-third octave band spectra such as the chosen configuration Constraints on the use of the quadratic perceived noise level Author performance index are that the index must be expressed in terms of states and the control vector all states must be observable and only linear system formulations are acceptable Author N71-18867*# National Aeronautics and Space Administration Flight Research Center Edwards, Calif LIFT AND DRAG CHARACTERISTICS OF THE HL-10 N71-18838 Royal Air Force Farnborough (England) lnst LIFTING BODY DURING SUBSONIC GLIDING FLIGHT of Aviation Medicine Jon S Pyle Washington Mar 1971 26 p refs AN EVALUATION OF THE USEFULNESS OF FOUR (NASA-TN-D-6263) Avail NTlS CSCL 01C SECONDARY TASKS IN ASSESSING THE EFFECT OF A Subsonic lift and drag data obtained during the HL-IO lifting LAG IN SIMULATED AIRCRAFT DYNAMICS body glide flight program are presented for four configurations for H F Huddleston and R V Wilson Jul 1969 18 p refs angles of attack from 5 deg to 26 deg Mach numbers from 0 35 (IAM-R-479) Copyright Avail Issuing Activity to 0 62 These flight data where applicable. are compared with Eight male subjects were required to perform a tracking results from small scale wind-tunnel tests of an HL-10 model task using an electronic windshield display The task had two levels full scale wind tunnel results obtained with the fltght vehicle and fltght of difficulty, an essentially unlagged condition and a condition results for the MZ-FZ lifting body The lift and drag characteristics chosen to be perceptibly more difficult having an exponential lag obtained from the HL-10 flight results showed that a severe flow of 0 5 sec Integrated tracking error scores alone were unable to problem existed on the upper surface of the vehicle during the first distinguish between the two difficulty levels Four secondary tasks flight test This problem was corrected by modifying the leading were utilized involving a response to digits presented in the edges of the tip fins The vehicle attained lift-drag ratios as high forward field of view These four tasks were arranged to be of as 40 during the landing flare (performed with the, landing gear comparable difficulty level in pretests using the same subjects Two up) which is approximately 14 percent higher than demonstrated secondary tasks indicated a difference between the primary task by the MZ-FZ vehicle in similar maneuvers Author conditions The addition of a secondary task also permitted tracking error scores themselves to indicate a difference Author

N71-18882*# National Aeronautics and Space Administration Lewis Research Center, Cleveland Ohio N71-18863*# National Aeronautics and Space Administration EXPERIMENTAL PERFORMANCE AND COMBUSTION Lewis Research Center Cleveland Ohio STABILITY OF A FULL SCALE DUCT BURNER FOR A EFFECT OF EXIT AREA VARIATION ON THE SUPERSONIC TURBOFAN ENGINE PERFORMANCE OF AN AUXILIARY INLET WECTOR J Robert Branstetter. Albert J Juhasz. and Peter W Verbulecz NOZZLE AT MACH NUMBERS FROM 0 TO 1 27 Washington Mar 1971 84 p refs Bernard J Blaha and Albert L Johns Washington Mar 1971 (NASA-TN-D-6163, E-5679) Avail NTlS CSCL 20M 38 p refs A 67 7-11- (172-cm) diameter flight weight annular diffuser (NASA-TM-X-2182, E-5945) Avail NTlS CSCL 21A and combustor assembly for the fan stream of a duct burning An auxiliary inlet ejector nozzle designed for a supersonic-cruise turbofan underwent numerous modifications to achieve a highly aircraft was tested in the Lewis 8 by 6 foot supersonic wlnd tunnel efficient geometry and stable combustion The apparatus was tested to determine the effect of internal expansion on the performance in a connected pipe facility at conditions simulating those of a of the nozzle, especially at subsonic cruise Internal area ratio was supersonic transport plane Two zones of fuel inlection provided varied from 2 0 to 3 7 with a series of fixed exit areas simulating the overall fuel-air ratios of 0 to 0050 Air entered the upstream movement of a triple-hinge trailing-edge flap A smaller primary combustion zone by means of ram-scoops Effort was devoted to area simulated subsonic cruise and dry acceleration and a larger combating combustion instability (70 to 470 Hz) encountered at primary area simulated reheat acceleration The nozzles were tested many test conditions These efforts only partially successful. are over a range of nozzle pressure ratio from 1 9 to 80 At a described along with other performance results Author subsonic cruise Mach number of 0 9 and a nozzle pressure ratio of 3 2 an increase in internal expansion from 2 0 to 2 9 reduced the nozzle gross thrust coefficient about 1 0 percent A further increase in expansion ratio to 3 74 however resulted in an additional N71-18920# Western Gear Lorp Lynwood Calif Researdl 10-percent loss in performance Author Dept PRECISION FORGING OF SPIRAL BEVEL GEARS FOR ARMY HELICOPTERS Final ReportJan. 1968-Apr 1970 Millard R Berger 15 Sep 1970 81 p N71-18865*# Bolt. Beranek. and Newman. Inc .Van Nuys. Calif (Contract DAAJOl-68-C-1446) VARIABILITY OF FLYOVER NOISE MEASURES FOR (AD-715419, Rept-7003-310) Avail NTlS CSCL 13/8 REPEATED FLIGHTS OF TURBCNET AND PISTON ENGINE The objective of the project was to develop an alternate TRANSPORT AIRCRAFT manufacturing method for spiral bevel gears used in Army Dwight E Bishop Washington NASA Mar 1971 38 p refs helicopters The report covers the technical description of a program (Contract NAS1-8168) to develop high velocity forging techntques to produce spiral bevel

256 N7 1-189% gears to pre-grind tolerances. Initial objectives were to obtain PUBLIC TRANSPORTATION YO AIRPORTS: 7 REPORTS as-forged gears with .005 inches excess material on the side of 1970 42 p refs Presented at the 49th Ann Meeting of the each tooth for finish grinding after the heat treating. The report Highway Res Board Its Highway Res Record No 330 includes a discussion of die design parameters. the manufacturing Avatl Issuing Activity techniques for dies, forging parameters. dimensional checks of the forged gears. machining techniques for determining as-forged CONTENTS geometry and macroscopic and microscopic metallurgical data 1 MASS TRANSIT TO+AIRPORTS AN OVERVIEW showing grain flow and micro-structure. Also included is a K E Cook p 1-4 ref discussion of difficulties experienced and recommendations for future 2 THE AIRPORT ACCESS PROBLEM IN TOKYO T investigations. Author 1 GRA Akiyama (Japan Airport Terminal Co . Ltd , Tokyo) p 5- 12

3 AIRPORT ACCESS TO HEATHROW AIRPORT LONDON N71-18929*# National Aeronautics and Space Administration. G Hole (British Airport Authority.) p 13 -15 Ames Research Center, Moffen Field. Calif. NOISE MEASUREMENT EVALUATION OF TAKEOFF AND 4 PROVIDING GROUND ACCESS TO THE KANSAS APPROACH PROFILES OPTIMIZED FOR NOISE CITY AIRPORT W lcenogle (Kansas City Area Transportation ABATEM E NT Authority Mo I p 16 - 20 H. Rodney Peen/ and Heinz Erzberger Washington Mar. 1971 5 CLEVELAND RAIL TRANSIT AIRPORT SERVICE G 29 p refs F Wiggers (DOT. Washington. D C p 21 - 24 (NASA-TN-D-6246; A-3548) Avail: NTlS CSCL 01C A flight investigation to determine the effective perceived 6 AIRPORT ACCESS PLANS FOR BOSTON R Muehlberger noise level associated with certain takeoff and landing profiles has (Mass Bay Transportation Authority) p 25-29 refs been conducted. The tests were designed to evaluate noise-optimum takeoff profiles. previously obtained in an analytical study. and to 7 THE PHILADELPHIA AIRPORT ORIGIN-DESTINATION investigate the potential for noise abatement of nonstandard SURVEY. A STATISTICAL ANALYSIS J C Corradino (Simpson approach procedures. During the takeoff tests. the flaps were set and Curtin. Philadelphia. Pa ) p 30-36 refs at either 27 deg or 10 deg and the climb airspeeds varied from V sub 2 + 15 to V sub 2 + 50 knots (V sub 2 refers to the takeoff safety speed of the aircraft). Power was reduced to yield either 500 or 750 ft/min rate of climb when the aircraft N71-18952# National Academy of Sciences National Research reached 1500 ft altitude. The assumed noise sensitive ground track Council, Washington D C Highway Research Board extended along the runway centerline from 3.5 to 5.7 nautical miles MASS TRANSITTO AIRPORTS. AN OVERVIEW from the start of the takeoff roll. The average of the noise Kenneth E Cook In Ifs Public Transportation to Airports 7 Rept measurements taken at points along the noise sensitive portion of 1970 p 1-4 ref the ground track was used to compare the various takeoff profiles. Avail Issuing Activity The takeoff that produced the least average noise. 905 EPNdB. The current patterns in airport access systems are briefly used takeoff flaps of 10 deg and a climb airspeed of V sub 2 + discussed with the advantages and disadvantages of mass transit 50 knots to 1500 h altitude, at which point mwer was reduced systems The potential applications of rail and bus transit systems to yield a 750 ft/min rate of climb The landing profiles were flown are also presented FOS along a 3 deg glide slope at constant flap settings of 50 deg. 27 deg. 10 deg, and 0 deg. The approach speed for each profile was 1.3 V sub S1 + 10 knots (V sub S1 refers to stall speed of the aircrah at the flap setting and gross weight used in the approach). N71-18953# Japan Airport Terminal Co Ltd Tokyo In addition, a decelerating profile with engines at flight idle and THE AIRPORT ACCESS PROBLEM IN TOKYO 0 deg flaps was flown over a single noise measuring station at Toru Akiyama In NAS-NRC Public Transportation to Airports an altitude of 1000 h. Reducing the flap setting from 50 deg to 7Rept 1970 p 5-12 0 deg on the approach reduced the noise from 110.5 to 106.5 Avail Issding Activity EPNdB along the ground track between 5 and 1 nautical miles The mass transit systems used for access to the Tokyo from the touchdown. The decelerating overflight with engines at International Airport are studied A statistical analysis of the traffic flight idle reduced the noise an additional 12.5 EPNdB compared patterns shows that 70% of the passengers use automobiles for to the 0 deg flap approach at the same altitude. Author arrivals and departures Conclusions reached in considering the access problems to the new Tokyo airport are (1) City terminals that have passenger check-in facilities are desirable (2) The city N71-18937# Cornell Aeronautical Lab Inc Buffalo, N Y terminals should be located in strategic points with easy access THE FEASIBILITY AND USE OF ANTI-TORQUE SURFACES to downtown and the airport (3)Limousine/bus service should be IMMERSED IN HELICOPTER ROTOR DOWNWASH established with specially designed vehicles FOS Technical Report.Jan 1968 -Dec. 1969 Chee Tung. John C Erickson. Jr and Frank A DuWaldt Feb 1970 59 p refs (Contract N00014-68-C-0241) N71-18954# Britfish Airports Authority. London (England) (AD-715438. CAL-BB-2584-S-2) Avail NTlS CSCL 1/3 AIRPORT ACCESSTO HEATHROW AIRPORT, LONDON An analytical investigation was made of the effectiveness George Hole In NAS -NRC Public Transportation to Airports of anti-torque aerodynamic surfaces immersed in helicopter rotor 7 Rept 1970 p 13 -15 Avail Issuing Activity downwash It is shown that additional vertical tail surface having areas equal to about two percent of the main rotor disk area could The public transportation requirements for access to London's provide torque trim for speeds above about 75 ft/sec for airports are discussed by considering the traffic position of Heathrow The existing transportation systems of bus subway. and representative current vehicles Author (GRA) trail services to Heathrow are described and it is concluded that the British Rail duorail system can be adapted to meet the traffic requirements of 2000 passengers per hour in each direction N71-18951# National Academy of Sciences National Research FOS Council. Washington. D.C. Highway Research Board.

257 N71-18955

N71-18955# Kansas City Area Transportation Authority Mo N71-18962*# Aerojet-General Corp Sacramento, Calif Nuclear PROVIDING GROUND ACCESS TO THE KANSAS CITY Systems AIRPORT WATER DROPLET SIZE DETERMINATION FOR BREAKUP Willim lcenogle /n NAS NRC Public Transportation to Airports OF LARGE DIAMETER JETS 7Rept 1970 p 16-20 May 1970 153 p refs Avail Issuing Activity (Contract SNP-1) Based on the recommendations of an engineering survey (NASA-CR-116820. FAC-FTROl-W224-3. ANSC-1) Avail NTlS of the traffic requirements for a freeway system to service the CSCL 20D Kansas City International Airport. the design and location of a The drops generated by the breakup of water lets from nozzles transitway is presented One end of the recommended transitway ranging in diameter from 025 to 1 5 in were photographed in a is in the business district. near downtown hotels and at the airport series of wind tunnel tests The volume mean drop size generated buses operate on an elevated road separate from general vehicular in these tests compared favorably with that calculated using the traffic The total cost of this access system is estimated at $30 empirical equation generated by lngebo for nozzles from 0 01 to million FOS 004-in in diameter An empirical expression is presented that characterizes the water-jet mass distribution in a cross flow of gas A series of tests of flat spray nozzles indicates that the penetration N71-18956# Department of Transportation Washfngton D C is decreased to 50 to 60% of that attained with a penetration or Office of the Secretary fire-hose nozzle Author (NSA) CLEVELAND RAILTRANSIT AIRPORT SERVICE George F Wiggers ln NAS NRC Public Transportation to Airports N71-18987*# Translation Consultants Ltd Arlington Va 7 Rept 1970 p 21 -24 A NUMERICAL METHOD OF DETERMINING THE Avail Issuing Activity AERODYNAMIC COEFFICIENTS OF THIN SUPERSONIC The rail rapid transit system to Hopkins International Airport WINGS WHICH ARE DEPENDENT ON THE ANGLE OF was studied to develop the means to make accurate forecasts of ATTACK [NUMERISCHES VERFAHREN ZUR BESTIMMUNG transit demands as a mode for airport access Four types of A NSTE LLWl N KE LA B H AE N GI GE R AE R ODY N AMI SC HE R tripmakers are included in the study These are inbound and BEIWERTE DUENNER UEBERSCHALLFLUEGEL] outbound air passengers persons meeting or seeing off air W H Diesinger Washington NASA Feb 1971 62 p refs passengers casual visitors to the airport such as sightseers and Trans1 into ENGLISH from German report DLR-FB-71-01 employees at the airport The transit system is a publicly owned (Contract NASw-2038) 19-mile two-track rail rapid transit line with 17-stations on the (NASA-TT-F-13521) Avail NTlS CSCLOlA line The airport is the last stop on the west end Travel time to The numerical method makes use of the linearized potential downtown Cleveland is 25-minutes with trains departing every flow theory and IS limited to wings where Evvards theorem can 10-minutes It is concluded that most of the air travelers are not be applied the method is especially suited for preliminary design residents of Cleveland and do not have their private automobiles calculations where the effects of warping and the wing thickness available to them They require high frequency dependable and are not needed The aerodynamic coefficients are determined by time saving transportation services FOS numerical integration of the velocity potential for which the numerical accuracy can be determined by simple addition Because N71-18957# Massachusetts Bay Transportation Authority Boston of the comparatively small number of calculations the method may AIRPORT ACCESS PLANS FOR BOSTON be applied in order to reduce the running time of existing computer Ronald Muehlberger In NAS-NRC Public Transportation to programs For application to desk calculators, tables are given and Airports 7 Rept 1970 p 25 29 refs simple computational examples included Author Avail Issuing Activity The existing access systems for Logan International Airport are presented with plans and recommendations for improvement N71-18989 Syracuse Univ N Y It is shown that almost 69% of the travelers use private A THEORETICAL AND EXPERIMENTAL INVESTIGATION automobiles as the access mode The recommended improvements OF THE STABILITY OF PIPE FLOW WITH RESPECT TO center around a proposed third harbor tunnel to alleviate the severe THREE-DIMENSIONAL DISTU R BA NCE S congestion during rush hours at the Callahan Tunnels and the Thomas Michael Houlihan (Ph D Thesis) 1969 66 p Mystic River Bridge A survey of the airport populations showed that Avail Univ Mtcrofilms HC $3 80/Microfilm $3 00 Order No each passenger generated almost one nonflying visitor The available 70- 1955 parking spaces number 5800. by 1980 it is estimated that 17,700 The stability of fully developed laminar flow in a circular parking spaces will be required The greatest single improvement pipe perturbed by an infinitesimal three-dimensional helical to existing systems is considered to be an extension of the rail disturbances is presented A method analogous to the classical routes to provide direct connection of the airport with the downtown boundary layer study of Tollmien has been followed in the analysis sections of Boston FOS This yielded a neutral stability curve which while unlike the classical hairpin result. nevertheless could conceivably describe pipe N71-18958# Simpson and Curtin Philadelphia. Pa flow instability Preliminary results of experiments in a carefully THE PHILADELPHIA AIRPORT ORlGl N-DESTI NATION constructed wind-tunnel facility are presented for flow in a 1 25 in SURVEY: A STATISTICAL ANALYSIS diameter pipe at a Reynolds number of order 12,000 It was Joseph C Corradino In NAS-NRC Public Transportation to verified that the flow was quite stable to axisymmetric disturbances Airports 7 Rept 1970 p 30 36 refs But more significantly it was shown that a point source form Of Avail Issuing Activity helical disturbance did seem to grow with a wavelength predicted A statistical survey of ground and air traffic at the Philadelphia by the theory for the given test Reynolds number Author International Airport was taken to help in solving the ground air interface problems confronting airport activities An in-flight survey of arriving and departing flights was conducted Results indicate that a one-directional survey accurately mirrors the reverse direction of N71-18996*# Johns Hopkins Univ, Baltimore, Md Dept Of travel and that any analysis of airport ground travel based on Physics data from home-interview surveys should be supplemented by an A REPORT ON SOME RESULTS FROM THE NASA 1968 examination of nonresident air passenger travel FOS AIRBORNE AURORAL EXPEDITION

258 N71-19170

I( A Dickand W G Fastie Aug 1970 44 p refs The schedule of AGARD 1971 technical meetings IS presented (Grant NGR-2 1-001-001 ) The announcement includes these panel activities aerospace (NASA-CR-116855. TR-24) Avail NTlS CSCL04A medicine avionics. electromagnetic propagation. fluid dynamics. guidance and control. propulsion and energetics. structures and The spectrometer scanned a regan n lambda (12.400-14.ooO A). with the capability of isolating second, third. and fourth orders materials and technical information The membership of the various by means of Corning color glass filters The photometer sampled panels is given. and summaries of the 1970 AGARD publications each feature two out of every ten seconds, the spectrometer are included FOS scanned every 1 5 seconds The results are reviewed for some 124 hours of flying of approximately a quarter million photometer N71-19122*# General Electric Co,Pinsfield, Mass readings and thirty thousand spectral scans (each with as many as MEASUREMENTSAND ANALYSIS OF 40Q resolution intervals) Author LI G HTNI N G-I ND U CE D V 0 LTA G E S I N AI R C R AF T ELECTRICAL CIRCUITS K J Lloyd, J A Plumer. and L C Walko Washington NASA N71-19040# National Transportation Safety Board. Washington. Feb 1971 170 p refs D.C. (Contract NAS3-12019) AIRCRAFT ACCIDENT REPORT: MARTIN 404, N464M. 8 (NASA-CR-1744. HVL-69-161) Avail NTlS CSCLO9E STATUTE MILES WEST OF SILVER PLUME. COLORADO, An experimental investigation of voltages induced by lightning 2 OCTOBER 1970 in aircraft electrical circuits is described An extensive series of 24 Dec. 1970 56 p refs measurements was made of voltages induced in circuits within a (NTSB-AAR-71-41 Avail: NTIS metallic aircraft wing by full-scale simulated lightning currents The circumstances leading to the crash of a transport aircraft flowing through its skin and structure The measured data were which caused 30 fatalities are reported. The probable cause of the mathematically analyzed to enable determination of voltages accident was the intentional operation of the aircraft over a across load impedances to which the circuits might be connected mountain valley route in an altitude from which the aircraft could elsewhere in the aircraft Relationships between induced voltages neither climb over the obstructing terrain ahead. nor execute a and lightning current. wing structure, and circuit parameters successful course reversal. Significant contributions to the accident were determined Induced voltages of magnitudes likely to cause were: (1) overloaded condition. (2) lack of flight planning. (3) lack damage or interference with avionics were measured Author of understanding of the aircraft capabilities and limitations. and (4) supervisory error. Author N71-19139*# TRW Systems Group. Redondo Beach Calif A STUDY OF THE USE OF LIQUID BASE FOAMS FOR JET N71-19041# National Transportation Safety Board Washington. NOISE REDUCTION DC L Manson S Lieberman and H L Burge Washington NASA AIRCRAFT ACCIDENT REPORT: JETCO AVIATION. Feb 1971 142 p refs INCORPORATED, SHORT BROTHERS AND HARLAND. (Contract NAS1-9426) LIMITED, SKYVAN SERIES3(SC-7), N21CK. WASHINGTON (NASA-CR-16951 Avail NTlS CSCL 20A NATIONAL AIRPORT, WASHINGTON, D.C.. ZJULY 1970 An experimental investigation of the acoustical properties 13381 197i 20 p refs ui itquid b8>t. fodrns drld of jet riuise reductron through foam (NT: .-AAR-71-6) Avail NTIS inlectlon is discussed Results are given for an analytlcal effort to build The circumstances preceding a fatal crash of a cargo aircraft a mathematical model of the sound propagation and absorption are discussed The aircraft assumed a steep descent and left turn of foams The expenmental investigation showed attenuation while approaching the airport and crashed in a small body of constants on the order of 3 nepers/inch Jet noise reduction values water The accident investigation determined that the cause of the up to 10 PNdB were recorded The analytical effort confirmed the accident was a forward shift of improperly secured cargo hypothesis of a resonant response of foams to sound waves The Author overall results indicate foam has a high potential as a sound attenuation medium Author

N71-19043# National Transportion Safety Board. Washington. D.C. N71-19170# Weapons Research Establishment, Salisbury REPORT OF PROCEEDINGS OF THE NATIONAL (Australia). TRANSPORTATION SAFETY BOARD INTO THE MIDAIR FURTHER FLOW CALIBRATION IN THE BLOWDOWN COLUSION PROBLEM WIND TUNNELS3 12 Nov. 1970 138 p refs Conf held in Washington. D.C. 4 10 M. L Robinson Jun. 1970 29 p refs Supersedes Nov. 1970 WRE-TN-HSA-1 15 (NTSB-AAS-70-2) Avail: NTlS (WRE-TN-HSA-171) Avail: NTlS The proceedings and recommendations of a conference The distribution of Mach number in the 7 in by 6 in working conerning the subject of midair collisions are presented. Subjects section of wind tunnel S3 was measured at Mach numbers 2.8. 3.5. 4 0 and 5.0. The results given supersede those of the previous discussed are: (1) traffic segregation in the terminal area. (2) collision avoidance systems, (3) pilot warning indicators, (4) calibration tests carried out in 1965 at which time no Mach number 3.5 nozzle was available. The present calibration results standardized traffic patterns. (5)flightcrew training program. (6) area differ by navigation. (7) visual detection of aircraft on collision course. and about 0-02 in Mach number from the previous test results for (8)primary radar target enhancement. Author the unmodified Mach number 2.8 and 4.0 nozzles. Remachining of the Mach number 5.0 nozzle blocks has not improve& the uniformity of flow produced by the nozzle The standard deviation N71-19114# Advisory Group for Aerospace Research and of Mach number in the working section is 0.3% for the Mach Development. Paris (France). number 2.8 and 3.5 nozzles. 0.4% for the Mach number 4.0 nozzle AGARD BULLETl N: MEETINGS, MEMBERSHIP. and 0.6% for the Mach number 5.0 nozzle. Design ordinates for PUBLI CAT1ON S. J A NU ARY 1971 the Mach number 3-5 nozzle are given. and Mach number Jan. 1971 61 p refs distributions for all nozzles are presented in tabular and graphical (AGARD-Bul-71/1) Avail: NTlS form. Author

259 N7 1 - 19217

N71-19217# Joint Publications Research Service. Washington were digitized at a sample rate of 100 000 samples per second and DC digital shock spectrum analyses were performed with a damping TRANSLATIONS ON EASTERN EUROPE PROJECT OF ratio of 5% For each accelerometer comparison plots were made DOLPHl N-LIKE Dl RlGI BLE DISCUSSED of the spectra obtained from the bare structure and three different 4 Feb 1971 17 p Transl into ENGLISH from Various E weight configurations The results are presented graphically and a European Publications Its Scientific Affairs No 157 discussion of the significant findings is given D LG (JPRS-52330) Avail NTlS The design and characteristics of a double hulled dirigible are discussed The airship consists of a symmetric airfoil body with N71-19276*# Grumman Aerospace Corp Eethpage N Y end plates for accomodating the crew and passengers The gas cells are located in the center section of the airship Propellers are FINITE ELEMENT ANALYSIS OF STRUCTURES IN THE located fore and aft on the center structure and nuclear propulsion PLASTIC RANGE is proposed The advantages of the dirigible lie in its large cargo H Armen Jr A Pifco and H S Levine Washington NASA capacity aerodynamic stability and vertical let down capability Feb 1971 281 p refs (Contract NAS1-7315) PNF (NASA-CR 1649) Avail NTlS CSCLZOK An extension of finite element methods to provide analytical N71-19220# Lockheed Missiles and Space Co Palo Alto Calif means for determining the nonlinear response of aircraft structures SCANNING SYSTEMS FOR THERMAL VIEWERS is presented Consideration is given to material and geometric E la Karizhenskii et al 1970 6 p refs Transl into ENGLISH nonlinearity acting separately or in combination The methods from Opt -Mekh Prom (USSR) no 9 1970 p 39 42 developed are applicable to loading conditions that cause either Avail NTlS National Translations Center John Crerar Library membrane stresses or pure bending or both in combination The Chicago, Ill 60616 finite element analysis methods for material nonlinearity can account Peculiarities of detector scanning systems intended for thermal for the Bauschinger effect for biaxial stress states by using the viewers producing a picture similar to television and operating Prager-Ziegler kinematic hardening theory of plasticity Application from a fixed base are analyzed The engineering possibilities and of the methods is made to several simple structures including advantages of utilizing an alternate-line sweep in these instruments notched bars and rectangular circular and annular plates although are shown Fundamental relationships are determined between the it should be noted that these methods are fully capable of being output parameters of the thermal viewer the frequency band of applied to complex built up structures Good correlation IS ob the amplifier channel and the size characteristics of the scanning tained between results from the present analysis and existing ex- system The value of the coefficient of mirror facet utilization and perimental and/or analytical results Author the possibility of its application as a criterion to estimate the degrees of optimality of the scanning systems of such instruments are shown Author N71-19281*# National Aeronautics and Space Administration Washington D C NASA SPACE VEHICLE DESIGN CRITERIA (STRUCTURES); STRU CTU RAL VIBRATION PREDICTION N71-19239*# Boeing Co Wichita Kans J S Archer (TRW Systems Group) Jun 1970 41 p refs THE SIMULATION OF A LARGE JET TRANSPORT (NASA SP-8050) Avail NTlS CSCL 20K AIRCRAFT VOLUME 1 MATHEMATICAL MODEL Space vehicle structural vibration resulting from induced C Rodney Hanke Washington NASA Mar 1971 59 p or natural environments and with methods of determining internal (Contract NAS2 5524) structural loads and stresses caused by such vibrations are (NASA CR 1756) Avail NTlS CSCLOlC considered Structural vibration causes internal loads and stresses The mathematical models used in the manned Simulation in structural components and localized loads at attachment points of a jumbo jet transport aircraft are described Included are the where equipment is supported by the structure The degree or models of the basic airframe the longitudinal lateral and directional magnitude of structural response may be expressed as an acceleration control systems the high lift system the propulsion system and or displacement of various critical points as a function of time as the landing gear system In addition the low speed buffet a weighted average acceleration (root mean square) or as spectra characteristics and atmospheric model are described Included is a of acceleration or stresses as functions of frequency at discrete list of necessary tests of the simulation to insure validity of the times Severe vibration of space vehicle structural elements usually model of the computer program and of the quantitative values results from rocket noise and from aerodynamic noise and buffet Author Severe vibration can also result from other sources such as thrust oscillation and rocket-engine resonances wind gust and shear N71-19250*# Martin Marietta Corp, Denver Colo transportation tests operation of internal equipment. and unstable AEROSPACE SYSTEMS PYROTECHNIC SHOCK DATA dynamic coupling of the structure with the control system or with the propulsion system Author (GROUND TEST AND FLIGHT). VOLUME 7: INVESTIGATION OF MASS LOADING EFFECTS Final Report, 12 May 12 Nov. 1970 lvar K Engelsgjerd and W P Rader 12 Nov 1970 127 p N71-19287* National Aeronautics and Space Administration (Contract NAS5-21241) Goddard Space Flight Center, Greenbelt. Md. (NASA-CR-116019) Avail NTlS CSCLZOK TRAFFIC CONTROL SYSTEM AND METHOD Patent The results are presented of a test and analysis program to Charles R. Laughlin. Roger C. Hollenbaugh, and Walter K Allen. determine the effect of weight variation in mounted subassemblies inventors (to NASA) Issued 13 Oct 1970 (Filed 30 Jan 19681 on the pyrotechnic shock environment at the interface of the 22 p CI. 343-112: Int. CI. GOls5/14 subassembly and the mounting structure This effect designated as (NASA-Case-GSC-10087-1 : US-Patent-3.534.367: mass loading was studied for two types of aerospace mounting US-Patent-Appl-SN-701679) Avail. US Patent Office CSCL 17G structures (1) airframe. skin. and stringer structure and (2) truss A system is described in which the position of a vehicle. structure, An explosive device was used as a controlled source of such as a transoceanic SST, is determined by a computer at a shock to the loaded and unloaded structures High frequency central ground station, supplied to a central air traffic controller. and accelerometers and associated electronics were utilized to give a transmitteo to a number of adjacent vehicles in flight via a frequency capability of 20 000 Hz The recorded shock transients synchronous satellite. Side tone ranging patterns. as well as the

260 N71-19320 digital arid voice signals, are modulated on a carrier transmitted from the central station and recelved on all of the supersonic transports Each aircraft communicates with the ground stations via a different frequency multiplexed spectrum Position is determined in response to variable phase informatan imposed on the slde tones at the aircrafts with a number of different side tone techniques being employed. and relayed back to the transports Common to all of the side tone techniques IS Doppler compensation for the supersonic transport velocity Official Gazette of the U S Patent Office

N71-19289*# AiResearch Mfg Co , Los Angeles. Calif COMPARISON OF HYDROGEN AND METHANE AS COOLANTS IN REGENERATIVELY COOLED PANELS C E Richard and F M Walters Washington NASA Mar 1971 43 p refs Revised (Contract NAS1-5002) (NASA-CR-1652. Rept-67-2490-Rev-1) Avail NTlS CSCL 20M Comparisons are made of the minimum weights. ranges of applicability. and coolant requirements of methane-cooled. and hydrogen-cooled, structural panels determined from analytical studies of flat panels designed for heat fluxes up to 500 Btu/sec-sq ft and pressure loads up to 250 psi Author

N71-19320# Detroit Edison Co Mich Great Lakes Area Trade Oevelopment TRANSPORTATION OF FREIGHT IN THE YEAR ZOO0 WITH PARTICULAR REFERENCE TO GREAT LAKES AREA James Easton Sep 1970 140 p refs Avail Issuing Activity The main modes of transportation for the Great Lakes Area in the year 2000 are examined to assess the freight movement by each mode The intercity ton milage during the next 30 years is expected to triple the 1970 figure Shipping on the St Lawrence Seaway and Great Lakes railroads trucking inland waterways. barges, pipeline system. and air transport are considered with ~92~1sor :he .r.!:,ence of fuiu,e governnlent policies i 0 S

26 1 t 1 SUBJECT INDEX

I AERONAUTICAL ENGINEERING / A Special Bibliography (Suppl. 5) MAY 1971

Typical Subject Index Listing

ACCIDEIT PREVEZIPTIOId suwEcT 1 errors due to nonlinearities and noise effects omputer proqrams and predictor displars for A71-20405 air traffic control problems ADIABATIC CDIDITIOIS ,171-1146% Supersonic air flow pattern over rectangular indentations on plane and axisymmetric surfaces, I __L_I examining static pressure and adiabatic temperature distributions 1171-19744 Semi-empirical determination of adiabatic efficiency of supersonic compressor stage The suben heading is a key to the sublect mntent of the document The [ AD-71 5005 ] 1171-18036 ADIABATIC Notation of Content INOC) rather than the title of the document is used FLOW Approximation of Chaplygin equation for subsonic to provide a more exact description of the subiect matter The repcft number ideal gas plane adiabatic flow, applying to helps to Indicate the tvpe of document cited (e g NASA report translation discharqe from flat channel with contraction , NASA contractor report) The accesston number IS located beneath and A71-20083 to the right of the Nmat~onof Content e g N7 1-1 1466 Under any one AERODYIAEIC BALAICB subiect heading the a~cession numbers are arranged in sequence wlth Probabilistic estimate of aerodynamic imbalance of the IAA accession numbers appearing fist aircraft gas turbine rotors due to production errors in compressor blade angle I h71-22045 I AERODIIAIIC BRAISES Low speed wind tunnel stability tests of small A guide surface, slotted solid. ring slot, cross A-7 AIRCBAPT and streamer decelerators. considerinq A-7 low altitude tactical fighter spin evaluation parachutes and drag measurement program. discussing maneuvering capability, A71-20310 external stores and departure mode AERODYIAIIC CEABACTERISTICS A71-19094 Sailuing aerodynamic characteristics, obtaining ABSORPTIVITI aerodynamic loadiuq by tu7 dimensional flexible Aircraft flyover noise samples. obtaining airfoil and Prandtl lifting line theories atmospheric absorption coefficients A71-20303 177-27 (125 Loviet book ai, 'i.a.k-43 pasaauyer tratlaport aircraft IC 6EIEBATOBS confiqurational design and aerodynamic I Integrated drive AC generator for aircraft, characteristics covering stability, discussing design improvements in power-weight controllability and flight under special ratio conditions 1171-19494 A71-20750 ACCELEEATIOI (PETSICS) Aerodynamic characteristics of conical and I Center of qravity vertical acceleration and wing pyramidical configurations with various I planforms by slender body theory, replacing stresses of Eoeinq 720-E aircraft r TB-87-1970 J 871-17119 three dimensional flow by two dimensional flow ACOUSTIC AREIUATIOI A71-20776 I Acoustic attenuation determined experimentally Potential flow past cylinder rith sources and durinq engine qround tests of XB-70 airplane and sinks singularities. deriving formulas for comparison uith predictions aerodynamic characteristics of infinite span [ NASA-TU-X-22231 1171-17951 wings with boundary layer control ACOUSTIC IEASUUEIEITS 1171-20777 Aircraft flyover noise samples. obtaining Larqe angle cones supersonic aerodynamic and wake I atmospheric absorption coefficients characteristics at low Reynolds numbers, 171-21 425 including model support interference effects Aircraft noise abatement control on international ~AIAA PAPEB 71-2641 171-21990 , basis by setting acoustic technological Elastic swept wing subsonic aerodynamic I capability compulsory standards of quietness characteristics, taking into account aerodynamic A71-21826 load redistribution due to aeroelastic I Measurement of variability of aircraft noise deformations durinq level flight flyovers 1171-22035 r~~s~-crt-i-x2] N71-18865 Longitudinal aerodynamic characteristics of Vikinq Noise measurement evaluation of takeoff and lander spacecraft at hypersonic speed approach profiles optimized for noise abatement r NASA-TU-X-2205] N71-17253 r NASA-TN-D-6246 1 1171-18929 Acoustic and aerodynamic performance of six foot ACOUSTIC PROPERTIES diameter fan for turbofan enqines vith noise Acoustical properties of liquid base foams and suppressors application for jet noise reduction NASA-TI-D-6178 J N71-17254 [ NASA-CR-16951 171-19139 Pitch and vaw characteristics of supersonic ACOUSTIC vELocIxr transport aircraft with variable sweep winqs at Nonstationary isentropic low density flows with varions Bach nunbers axial or central symmetry. sugqestinq [ NASA-TU-X-2164 J N71-17415 characteristics with flou rate and sound speed Plight characteristics of V/STOL transport model variation as in stationary source flow with four pod-mounted lift fans 1171-19729 [ NASA-TN-D-6129 J N71-17423 LDAPTIVL CORBOL Vortex-lattice POBTBAN program for estimatinq Automatic Carrier Landing System with linear subsonic aerodynamic characteristics of complex adaptive aircraft saviqation computer, planf oris investigating effectiveness in reducinq system TRASA-TN-D-61421 N71-17424

A- 1 AEBODYIAIIC COBFFICIBITS SUBJXT IIDBI

Feasibility evaluation on optical probinq of Hathematical models for aerodynamic forces of supersonic aerodynamic turbulence with aircraft tandem wings using lifting line wing statistical correlation representat ion [ NASA-TN-D-60771 N71-17444 (ONERA-TP-8913 N71-18439 Dirichlet solution for thin airfoil problems ABRODIIAIIC BEAT TBAISFEB [ NASA-TT-P-134711 N71-17468 upper air sounding systems problems, discussing Investigating effects of leading-edge blowing on aerodvnamic heat transfer between temperature aerodynamic characteristics of jet flapped senso; and ambient air airfoil A71-21739 N71-1770 2 ABRODTIAIIC EEATIUG Resonance instability of finned bodies with Optimal weight of aerodynamic heat protection nonlinear aerodynamic characteristics layers of stressed skin and optimal efficiency [ AD-715110) N71-17733 of cooling system for hypersonic aircraft Helicopter application studies of variable compartments deflection thruster jet flaps 171-20836 l AD-7150713 N71- 17907 Development of thermal insulation system for Wing Practical aerodynamics of Hi-6 helicopter - lift and control surfaces of hypersonic aircraft and system and fuselaqe reentry vehicles I AD-7149151 1171-17908 [ NASA-CASE-XLA-0 0892 1 N71-17897 Real qas effects on draq and trajectories of Aerodynamic heating and structural analyses for nonliftinq conical shell durinq Hars atmospheric radiativelp cooled delta winq of hypersonic entry aircraft [NASA-TN-D-62401 N71-18015 [ NASA-TN-D-6138 1 N71-18025 Aerodynamic characteristics of V/STOL transport ABEODTUAIIC LOADS model with tandem lift fans mounted at Rotary inertia effect on critical dynamic pressure mid-semispan of wing parameters and supersonic flutter of in- plane [ NASA-TN-D-62341 N71-18558 loaded sandwich plates Lift and drag characteristics of HL-10 liftinq A71-19887 body durinq subsonic qlidinq fliqht Elastic swept winq subsonic aerodynamic [ NASA-TN-D-62631 N71-18867 characteristics, taking into account aerodynamic Desiqn and characteristics of double hull load redistribution due to aeroelastic dirigible airship deformations [ JPRS-52330 1 N71-19217 A71-22035 AEEODYNAIIC COEFFICIENTS ABEODTNAIIC BOISE Free fliqht measurement of aerodynamic Acoustic radiation spectra from turbulent jets, coefficients on fixed cruciform fin stabilized assuminq approximate Gaussian statistics and bombs, determining aerodynamic forces and second order velocity correlation space-time moments dependence on anqular velocity characteristics obtainable from frozen flow components A71-19959 A71-19872 Aerodynamic broadband noise mechanism applicable Aerodynamic coefficients, pressure, load and force to axial compressors distributions on cambered delta winqs [ NASA-CR-17431 N71-17958 IARC-CP-1129 1 N71-17112 ABRODYIAIIC STABILITY Trailinq vortex systems qenerated by let-flapped Axisymmetric body rapirl rotation under center of winq operatinq at hiqh rinq lift coefficients qravity velocity vector conditions, solving for [AD-7153151 N71- 17753 plane glidinq motion stability in air Dependence of aerodynamic coefficients on maximum A71-19354 thickness and lenqth of axisymmetric bodies in Nonlinear aerodynamic moment system for supersonic flow nonaxisymmetric bodies free flight motion [ DLR-PB-70-54 1 N71-18444 analysis, taking into account interactions Numerical determination of aerodynamic excluded in classical treatment coefficients for thin supersonic wings at [AIAA PAPER 71-2751 A71-22000 various anqles of attack Vortex breakdown on slender sharp edqed and [ NASA-TT-F-13521 1 N71-18987 modified delta winqs with varyinq sweep anqles AEBODYNAIIC CONFIGURATIONS investigated in wind tunnel using schlieren Aerodynamic support interference in wind tunnel system for flow visualization A71-22028 testinq of confiqurations involving bulbous [AIAA PAPER 69-7781 base, mass addition, transition near base and Resonance instability of finned bodies with hypersonic low density flows nonlinear aerodynamic characteristics [AIAA PAPER 71-2771 A71-22002 r AD-915110 1 N71-17733 European hypersonic wind tunnels for testing Compressible circular jet instabilities with hypersonic transport aircraft, and space shuttle respect to spatially-growing disturbancesN71- 18471 aerodvnamic confiqurations r DLR-PB-70-511 N71-18452 ABROD~IAIIC STALLIUG ABEODYUAIIC DRAG DC-10 fliqht test proqram, discussing handling, Lift and aerodynamic draq due to trailing-edqe takeoff and landinq, and flutter, stall and flaps on sweptback winqs in inviscid subsonic stability characteristics flow A71-19085 ~ARC-CP-~~~O~ N71-17114 USAP P-4E Stall/Near stall Investiqation, Lift and aerodynamic draq data on slender winqs discussing testing requirements, fighter with trailinq edge sweepback aircraft improvement, spin avoidance and high IARC-CP-11301 N71-17117 anqle of attack limitations Aerodynamic draq measurements on VC-10 aircraft A71-19095 subsonic wind tunnel models ABUODYUAIICS [ ARC-CP- 1 1251 N71-17118 Inverse boundary value problems in ABEODTIAIIC FOECES hydroaeromechanics, involving profile Free fliqht measurement of aerodynamic construction from qiven velocity or pressure coefficients on fixed cruciform fin stabilized distribution and supersonic flow boundaries bombs, determininq aerodynamic forces and determination moments dependence on anqular velocity A71-20078 components Water vapor condensation effects on methane-air A71-19872 combustion qases for aerodynamic test medium Elastic, inertial and aerodynamic forces [AIAA PAPER 71-2581 A71-21986 aeroelastic trianqle. examining lift chanqes due Subject and author index on aeroelasticity to aircraft structure deformation, dynamic documents fliqht stability and space shuttle development [ AGARD-R-578-711 N71-17432 problems ABEOBLASTICITT A71-20063 Subject and author index on aeroelasticity documents

A-2 SUBJECT IJDEI AIR POLLUTIOU

[AGABD-R-578-71 J 871-17432 Efficiency of air cooling blade desiqn for Olympus AEROIAIRICAL EIGIUBEBI16 593 gas turbine engine Ground based flight simulation as engineering aid 871-17376 in aircraft desiqn for evaluation of aircraft Beat transfer in air coolinq and sueat cooling dynamics, handling qualities and control system techniques for high temperature gas turbine characteristics over entire fliqht envelope engine components A71-20309 871-17383 AEWIAOTICS Temperature field measurements uithin convection Vorlduide aeronautical charts maintenance for cooled rotor blade of gas turbine engine weapon systems support, discussing data sources 1171-17387 A71-21254 Air cooling systems for nozzle guide vanes of AEPOSPACE E16IUBERII6 aircraft gas turbines Aircraft and environment - Conference. Aeu York. 1171-17396 February 1971. Part 1 Operational design criteria for gas turbine A71-21811 engines AEROSPACE EITIROIIIBUTS n7i-17402 Internal loads and stresses caused by space Performance of stator uith uire mesh shell blading vehicle vibration resulting from induced or durinq cold air investigation of turbine uith natural environments transpiration cooled stator blades - Vol. 3 [ BASA-SP-8050 J 871-1 9281 [ AASA-Tll-I-2166] 671-17590 AEROSPACE IUDUSTEY AIR 11011 European aerospace and electronic eqnipment Blunt cylinder uith small thread in anomalous industrial cooperation for air traffic control seeded flow in hypersonic uind tunnels, and commnnication satellites observing separated shock uave distortion 1171-17 181 171-18924 AEROSPACE UEDICIIE Interaction betueen radiation from shock uave Hoise associated uith operation of C-9A region and oncoming cold air flou in hypersonic /aeromedical evacuation/ aircraft flou past blunt body [AD-7152223 n7i-18269 A71-19730 Schedule of AGARD conferences for 1971. and Supersonic air flou pattern over rectangular summaries of 1970 AGARD publications- indentations on plane and axisymmetric surfaces. r AGARD-BUL-71/11 B71-19114 exauninq static pressure and adiabatic AEROSPACE SISTEES temperature distributions Avionics subsystem desiqn improvements for 1171-19744 aeronaztical systems, considering Dissociating airflou oser two dimensional blunt standardization. ueiqht impact, environmental body. determining laminar boundary layer control, maintainability and equipment grouth chemical reaction suppression effects on heat A71-18829 exchange llass loading effects on pyrotechnic shock A71-19748 environment of aerospace systems Stationary longitudinal turbulent flou of air with [ NASA-CR-116019 1 871-19250 equilibrium ionization and dissociation around AEROSPACE VEBICLES plate, calculating heat exchange and frictional Lightninq stroke probability model for point drag selection on aerospace vehicles A71-21922 A71- 19928 Performance prediction for tnrbine blade film AEBOSPACEPLAIES coolinq uith injection throuqh holes Linear mnltichannel control systems for supersonic NASA-CB- 1163761 871-17388 aerospace vehicles orbitinq in earth atmosphere Impact cooling method for turbine rotor blades [ AD-71 47961 871-17747 1171-17397 AFTERBURIII6 AIR IITALES Concorde aircraft Olympus 593 tuo-spool turbojet Air temperature effects on internal combustion engine, discussing variable nozzle and intake engines intake process, using similarity theory assembly. afterburner and control system 171-20782 171-19081 AIR lATI6ATIOI Gas dynamics of fan jets at various injection Communications. navigation and surveillance for angles aircraft and marine vessels in North Atlantic [AD-7147901 871-18034 reqion. discussing baseline traffic control A6RICULTURE model Transavia Airtruk aqricultoral aircraft, A71-18808 discussing efficiency, uork capacity. economics, Aircraft final approach and landing aids. configuration and performance describing ILs, VHP omnidirectional radio ranqe. A71-21224 distance measuring equipment and satellite AIR systems for air navigation Bypersonic tuo phase flou realized by air-uater A71-19014 mixtnres Buman role in Aerospace Defense Command [BIVTDG-PBPT-70-1] 171-1 8441 navigation, discussing Airborne Darning And. AIR BREATEIIS EI6IIES Control System and navigational aspects of ADC Composite rocket CUI hypersonic airbreathing mission propulsion reducing space exploration program 171-20346 cost Automatic Carrier Landing System with linear A71-2130 1 adaptive aircraft Navigation Computer, AIR CAR60 investigating effectiveness in reducinq system Report of aircraft accident due to foruard shift errors due to noulinearities and noise effects of improperly secured cargo A71-20405 [ ITSB-AAR-71-6] 171-19041 Aircraft radio compass navigation errors due to AIR COIDITIOIIW EQIJIPlEIT loop antenna inclinations during maneuverinq Aircraft fuel and air conditioninq systems vortex A71-20787 valves and diodes. examining flou patterns into VOR/DUE ground station oriented aircraft area and out of chambers navigation horizontal guidance capability, A71-20556 discnssing digital input/output flight control AIR COOL116 A71-21166 Turbocharged diesel engine precompressed inlet air AIR POLLOTI01 cooling by evaporation cooling, considering Combustor design for minimum exhaust smoke water inlection effects on centrifpgal emission from aircraft gas turbine jet engines, compressor considering air pollution A71-20781 A71-20867 mathematical model for calculating blade Commercial supersonic fliqht, investigating air temperatures in convective cooled gas turbines pollution and alleged climate and ueatber 871- 17375 modification effects due to principal exhaust

A-3 AIR TRAFFIC SUBJECT INDEX

products N71-18815 A71-21821 Traffic control system for supersonic transports Air pollution emissions at Heathrow Airport, usinq synchronous satellite for data relay London, from aircraft operations, heating between vehicles and qround station installations and road traffic [NASA-CASE~GSC-10087-17 N71-19287 1171-21823 AIR TRAYSPORTATION Airport PollUtiOn dispersion modelinq, simulatinq Airships and balloons potential commercial use in effect on surroundinq areas for abatement Canada, discussing carqo, passenger and military strateqies calculation applications A7 1-2 1824 1171-19916 National Air Pollution Control Administration Federal assistance to air transportation, control of aircraft enqine pollutant emissions considerinq airport development-environment coverinq measurement, test instrumentation, conflicts research, standards and requlations A71-21834 A71-21831 civil aeronautics operations review Aircraft enqine smoke emission control, discussinq 171-17779 Rinqelmann chart assessment for various Problems in civil air transportation and logistics commercial jet aircraft and airport qaseous N71-17799 pollutants Systems analysis and mathematical model for air A71-21832 transportation desiqn N71-17843 AIR TRAFFIC rNASA-CR-116431] Urban transit and ATC vehicle identification and Hembers attitudes on revisions to Warsaw position determination system, considerinq Convention and The Hague Protocol amendments on surface and airborne traffic real time liability to international air transport information communication passengers A71-21169 rREPT-1970/8-E] N71-18 100 Survey of rapid transit railway impact on airport Feasibility of inter-metropolitan transport System passenqer traffic usinq Breguet 941 STOL aircraft I PB-195045 1 N71-16990 [ REPT-50 1 N71-18104 Tabulations for rapid transit system effect on Air transport supply on scheduled services in airport traffic Europe-Hediterranean and Southeast Asia reqions TPB-195049 ] N71-16991 r REPT-1970/1-E] N71-18112 Rapid transit railway effect on airport passenqer Heteoroloqical effects on air transportation, traffic includinq atmospheric and runway conditions r PB-195046 1 N71- 16992 N71-18117 AIR TRAFFIC COlTROL Statistical analysis of oriqin-destination survey Computer aided automatic fault data loqqinq, at Philadelphia International Airport classification, analysis and reporting methods N71-18958 in inteqrated ATC system AIRBORNE BQUIPHENT A71-19556 Aircraft midair collision avoidance. discussing System automation evolutionary process in terminal Elimination Ranqe zero system operation Air Traffic Control environment procedures and cost [AIAA PAPER 71-2421 A71- 19717 1171-19079 ATC automated systems, discussinq National Airborne surveillance for environmental Airspace system En Route Staqe A and Advanced aanaqement, discussinq earth resources program, Radar Terminal System aerial sensors for thermal water pollution, crop lAIAa PAPER 71-2441 A71-19719 disease, salinity and qeological structure Computer display channel for en route air traffic A71-19080 control flexible real time data processinq and Draw-throuqh coolinq of electronic equipment in display subsystem subsonic and supersonic commercial jet AIAA PAPER 71-247 1 A71-19721 transports, discussinq internal circulation Associative diqital processor with associative system desiqn memory for hiqh speed llTC data processinq. r SAE-AIR-64A J A71-19642 discussinq desiqn and operation Establishing minimum operational requirements for A71-19997 airborne air traffic control transponder systems 0.5. domestic ATC airspace enroute and terminal [ DO-144 1 N71-18109 area naviqation system effects on pilot AIRBOBIE/SPACEBORNE COIPUTBES workload, projectinq future FAA requirements Navy avionic modular multiprocessing diqital A71-20347 computer operating system reliability, comparing Optimal air traffic control coordinatinq flow and totally software and partly hardware approaches holdinq patterns of aircraft landinq in single A71-18833 runwaY usinq linear-uuadratic techniaue Passive airborne computer auqmented aircraft A71-21335 antenna pointing control system for ATC automation program for en route and terminal conmunication satellites tracking centers. discussing combined nation ide system [AIAA PAPER 71-2331 A71- 19710 features, IFR volume and video diqitizer data Aircraft naviqation system requiring computer and links display for approach guidance to circular orbit A71-21659 over fired ground area European aerospace and electronic equipment [ AIAA PAPER 69-9861 A71-20 305 industrial cooperation for air traffic control Automatic Carrier Landinq System with linear and communication satellites adaptive aircraft Naviqation Computer, N71-17181 investiqatinq effectiveness in reducing system Proposed STOL operations in Northeast Corridor errors due to nonlinearities and noise effects with respect to air traffic control 171-20405 N71-17963 AIECEAIT ACCIDElT IIVISTIGATIOU Systems analysis summary on New York metropolitan Haterials failure role in Canadian civil aircraft area air traffic capacity accidents, discussinq organized investiqation N71-18040 and data flow Surveyinq air traffic controller occupation and 1171-21679 development of performance objectives Investigating aircraft crash landing caused by N71-18105 engine failure and aircrew errors Establishinq minimum operational requirements for [NTSB-AAR-70-171 N71-17063 airborne air traffic control transponder svst0.c,--__- Investigation of Douqlas DC-9 accident at I DO-144 J N71-18109 Harlinqen. Texas, on 11 Jan. 1970 Survey of air traffic control radar beacon system [ NTSB-AAR-70-28 1 1171-17476 operational problems Investigating statistics of aircraft accidents by N7 1- 1811 6 reqion and operator system description of field test model of ARTS 2 [ REPT-1970/10-E] N71-18115 modular alphanumeric nontrackinq ATC system

A-4 SOBJZCT IIDII AIRCRAPT II6IIBS

AIRCIAR ACCIB- [ ARC-R/E-36293 171-17 102 Aircraft miaair collkion avoidance, discussing AIPCRYZ DBSI6I Elimination Range Zero system operation naval aircraft testing, discussing ueapons procedures and cost systems, funding commitments, outfitting A71-19079 schedules. time frames, contracts and management US general aviation ana supplemental air carrier problems accident statistical tables for 1969 171-19077 [ RSB-BA-70-6 ] 171- 17475 ARAVA STOL aircraft, describing payloads. Causes ana results of aircraft accident of Lear configuration. design flight testing, stability jet aircraft and landing characteristics r JTSB-ARB-71-3 1 171-1751 1 A71-19082 Cause and result -of transport aircraft accident BD-1 Yankee aircraft development, design and [ UTSB-AAR-70-27) 171-17512 construction Incidence and costs of orientation-error accidents A71-19084 in Army 08-1 helicopter operations Design objectires for subsonic, transonic and [ AD-7151071 117 1- 17854 supersonic civil transport flying Surveying crash fire and rescue eqnipment at North Characteristics based on IIL-F-8785, considering American and Canadian airports aircraft control 171-18101 [ SAE-ARP-842Bl A71-19645 Bidair collision hazards, incidents. and Aerospace Becornsended Practice criteria for flight recommendations for safe aircraft operations deck crew escape systems applicable to all 1171-18103 commercial aircraft propnlsion systems, design Report of transport aircraft accident and probable speeds and payloads causes [ SAE-ARP-808A] 171-19646 [ ITSB-LAB-71-4 3 1171-19040 Airplane wing high lift and flap designs by Report of aircraft accident due to foruard shift interactive computer graphics system of improperly secured cargo [AlAA PAPER 71-2271 A71- 19705 CSTSB-AAR-71-63 171-19041 Slept lightning stroke effects on aircraft design Proceedings and recommendations of conference on involving Ti and A1 sheets prevention of midair collisions A71-19936 [ 1TSB-AAS-70-23 171-19043 Plastics and metals as construction materials in AIRCRAR A.fI.IAS aircraft, missile and rocket design Passive airborne computer augmented aircraft A71-20044 antenna pointing control system for Ground based flight simulation as engineering aid communication satellites tracking in aircraft design for evaluation of aircraft [AIAA PAPER 71-2331 1171-19710 dynamics, handling qualities and control system Ultrahigh frequency directional spiral aircraft characteristics over entire fliqht envelope antennas for spacecraft communication 171-20309 r RAE-TR-70062] 171-18519 Soviet book on Yak-40 passenger transport aircraft AIRCRAR APPROACE SPACII6 confiqnrational design and aerodynamic Optimal air traffic control coordinating flow and characteristics covering stability, holding patterns of aircraft landing in single controllability ana flight under special runway using linear-quadratic technique conditions A71-21335 A71-20750 UpCPIm COIIIIU.ICATIO1 Q-Star experimental aircraft design and acoustical Commnnications, navigation and surveillance for characteristics te st~syPuiet Aircraft aircraft and marine vessels in Worth atlantic Technology reqion. discassing baseline traffic control A71-2 144 1 model motorized glider equipped with Wankel engine for A71-18808 self powered takeoff, describing prototype AIBCRA?T COI?ICURATIO1S design and flight test data Soriet book on Yak-40 passenger transport aircraft All-21769 configurational design and aerodynamic iiigh speed aircraft external store separation characteristics corering stability, testinq and prediction techniques, considering controllabilitv and flight under special flow field survey, dynamically similar drop conditions models and captive trajectory methods 171-20750 [AIAA PAPER 71-2943 A71-22014 Transaria Airtruk aqricnltural aircraft, Complex airframe design for economic and safe discussing efficiency. work capacity.-. economics. operation arid long life using fatigue and confisuration and pekformance fracture mechanics A71-21224 (AIAA PAPER 70-5121 All-22025 wind tunnel dynamic stability testing of AIRCRA?T EIGIIGS unconventional aircraft configurations uithout Eigh performance fighter aircraft engine pressure stinq support ratio and turbine inlet temperature measurement [LILA PAPER 71-2763 1171-22001 using fluidic sensors AIRCRAFT COITROL A71-20586 F-104D aircraft side stick control system design Fluidic pressure ratio control for vertical and function. curriculum maneuvers and component takeoff aircraft lift engine fnel system, reliability describing breadboard circuit, test bed and A71-19092 fliqht standard Desiqn objectives for subsonic, transonic and A71-20587 supersonic civil transport flying Soriet book on aircraft gas turbine and internal characteristics based on IIL-P-8785. considering combustion engines coverinq structural design aircraft control schemes, inlet devices. combustion chambers. [ SAE-ABP-842Bl A7 1-19645 materials, compressors, etc Aircraft electronic control systems, considering A71-20674 hydraulic servocontrol. force simulation and Equivalent test resnlts, studying damaginq factors reliability models in aircraft enqine compared uith regular tests A 7 1- 2 0 0 64 A71-21115 Airliner acceptance checks characteristics for microelectronic circuits reliability in aircraft official licensing prerequisites, investigating engine control applications, discussing testing takeoff, landing. ascent, stability and control and selection for severe temperature and A71-20065 vibration environments TWO dimensional aircraft automatic landing motions [SAE PAPER 7008221 A71-21369 control processes by simulation uithout use of Book on aircraft gas turbine engine technology moving cockpit simulator covering combustion chambers, exhaust systems, A71-20066 lubricating oils, thrust auqmentation. inlet Aircraft pilot direct lift control for aircraft ducts and overhaul procedures landing and reducing gust load effects 171-21625

A-5 AIRCRAFT EQUIPMENT SUBJECT INDEX

Aircraft turbine engines strenqth and qas dynamic discussing technology, tolerances, materials and characteristics improved by vibration decrease costs using elastic elements A71-20075 A71-21710 US commercial aircraft export strategy and National Air Pollution Control Administration recommendations for financing and expansion control of aircraft engine pollutant emissions N71-18087 coverinq measurement. test instrumentation, AIRCRAFT IUSTRUIENTS research, standards and regulations LOW profile optical system producing annular cone A71-21831 of radiation from point source for high speed Aircraft enqine smoke emission Control. discussinq aircraft beacon Rinqelmann chart assessment for various A71-19203 commercial jet aircraft and airport gaseous Terrain-followinq radar for TSR-2 aircraft, pollutants discussing reliability trials and improvement A7 1-2 1832 A71-19557 Probabilistic estimate of aerodynamic imbalance of Aircraft visual warninq indicating System, aircraft qas turbine rotors due to production outlining design criteria, color and brightness errors in compressor blade angle recommendations A71-22045 [ SAE-ARP-1088] A71-19644 Inqestion of debris into aircraft engine inlets Soviet book on supports and suspensions of durinq takeoff aircraft qyroscopic devices coverinq accuracy, ARC-CP-1 1143 N71-17084 reliability and lifetime factors related to Automation of technoloqical processes in aircraft quality and operational conditions enqine production A71-20299 [AD-714858] N71-17832 Aircraft radio compass naviqation errors due to AIRCRAFT EQUIPMEUT loop antenna inclinations durinq maneuverinq Inteqrated drive AC qenerator for aircraft, A71-20787 discussing design improvements in power-weiqht Aircraft altimeter containinq X ray source ratio N71-16993 A71-19494 Development and characteristics of frequency nilitary aircraft zinc silver oxide battery separated display devices for aircraft control service requirements and performance [AD-7154581 N71-18739 A71-21103 Selection of scanninq systems for aircraft thermal AIRCEAFT FUEL SYSTEMS viewers Aircraft fuel and air conditioning systems vortex N71-19220 valves and diodes, examiniuq flow patterns into AIRCRAFT LAUDING and out of chambers Aircraft automatic landing improvement throuqh use A71-20556 of space diversity ILS receivinq system AIECRAFT FUELS A71-18830 Suction and pressure head and temperature effects structures electromagnetic scatterinq and on cavitation flow in aircraft fuel pumps multipath transmission effects on aircraft r ARC-CP- 1128 1 N71-17044 instrument landinq system localizer siqnals, AIRCRAFT GUIDANCE using computer proqram A71-18831 Aircraft uaviqation system requirinq computer and display for approach quidance to circular orbit Boeinq 737 aircraft takeoff and landing over fixed qround area performance, emphasizinq high lift systems and [AIAA PAPER 69-9861 A71-20305 stoppinq capability Optimum automatic fliqht control techniques in A71- 19083 horizontal quidauce of aircraft at terminal Airliner acceptance checks characteristics for A71-20306 official licensinq prerequisites, investiqatinq VOR/DME qround station oriented aircraft area takeoff, landinq, ascent, stability and control naviqation horizontal guidance capability, A71-20065 discussing diqital input/output fliqht control TWOdimensional aircraft automatic landinq motions 1171-21 166 control processes by simulation without use of Strapdown inertial naviqator aliqnment by diqital moving cockpit simulator filterinq techniques, discussing. application to A71-20066 aircraft and spacecraft Automatic Carrier Landinq System with linear A71-21170 adaptive aircraft Navigation Computer, AIRCRAFT KAXARDS investiqatinq effectiveness in reducinq system Static discharqe hazards for aircraft, discussinq errors due to nonlinearities and noise effects causes for static charqe build-up, dangers and A71-20405 precautionary methods durinq refuelinq Aircraft pilot direct lift control for aircraft operations landiuq and reducinq qust load effects A71-19424 [ ARC-R/R-3629] N71-17102 Statistical information on liqhtninq and static Establishment of take-off and landing safety hazards relative to airworthiness marqins for Brequet 941 A71-19929 [ N A SA-TT- P- 134 5 3 3 N71-17441 Composite plastic aircraft structures liqhtninq In-fliqht determination of lateral-directional protection, considerinq hazard to composite dynamics for landing approach materials and use of metal filled or plasma [ AD-7 153173 N71-17792 sprayed coatinqs and metal foil coverings Noise measurement evaluation of takeoff and A71-19943 approach profiles optimized for noise abatement Aircraft collision avoidance dynamical system, [ NASA-TN-D-62461 N71-18929 determininq barriers between possible capture AIRCRAFT LAUNCBIUG DEVICES reqions by optimal control problem solution Noise abatement power cutback takeoff procedures. A71-21322 maximum altitude approaches and preferential Comnercial supersonic fliqht, investiqatinq air runway systems for noise relief pollution and alleqed climate and weather A7 1-21813 modification effects due to principal exhaust AIRCRAFT MAINTENANCE products Civil aviation aircraft mean fliqht time overhaul A71-21821 schedules, considerinq statistical evaluation Of synoptic meteoroloqical conditions for clear air relationship between operational characteristics turbulence and turbulence effects on aircraft and time between overhauls fliqht characteristics 1171-20797 [DLR-PB-70-291 N71-17145 AIRCRAFT MODELS neasurements and analysis of liqhtninq-induced Inteqrated project informatiou and simulation voltaqes in aircraft electrical circuits system for mauaqement of aerospace vehicle NASA-CR- 1744 1 N71-19122 development, discussing simulation models AIRCRAFT INDUSTRY application raTaA closed die forqinqs for aircraft industry, , .. .. .PAPER~~ 71-2381 A71-19714

A- 6 SUBJECT IIIDEX AIBCBAPT STBIJCTUBES

Ground boundary layer effects of fixed ground Alternate reduced order particle dynamics model in Plane for powered STOL wind tunnel model. aircraft mission analysis featuring discussing flow breakdown criteria, contraction instantaneously variable speed by time scale laq. strnt fairing interference, etc separation [AIAA PAPER 71-2663 A71-21992 A71- 19913 AIBCBAR 11OISE Transavia Airtruk agricultural aircraft, Noise nuisance value index /noise pollution discussing efficiency, work capacity, economics, level/, considering aircraft and motor vehicle configuration and performance noise surveys and tradeoff of intensity against A71-21224 duration Fliqht time, path and fuel consumption in climb at 171-20802 constant radius turn, variable or constant Aelicopter noise minimization by various pilotinq velocity and constant engine power, derivinq maneuvers, discussinq takeoff and landing. approximate simple formulas transition to forward flight. route selection, 1171-22050 etc Quadratic performance index for VTOL aircraft A71-21049 model reference attitude control system Sound field interaction with sinnsoidally [ NASA-TN-D-62313 R71-18836 corrngated surface. considering aircraft noise AIRCBAPT PILOTS measurement implications Aircraft pilot direct lift control for aircraft A71-21162 landing and reducinq gust load effects Aircraft flyover noise samples, obtaining ARC-B/l- 3629 3 1171- 17102 atmospheric absorption coefficients AIBCBAPT BELIABILITT 1171-21425 statistical information on lightning and static Q-Star experimental aircraft desiqn and acoustical hazards relative to airworthiness characteristics to study Qniet Aircraft A71-19929 Technology Antomatic Carrier Landing System with linear A71-2144 1 adaptive aircraft navigation Computer, Land use strateqies and noise reduction by source investiqatinq effectiveness in reducinq system control and fliqht procednres for noise exposed errors due to nonlinearities and noise effects areas minimization A71-20405 A71-21818 Tenative airworthiness standards for powered lift Commgnity reactions to aircraft noise, discussing transport category aircraft short term interim alleviation measnres in N71-17553 airport operations and rnnway usage schedolinq AIBCBAFT SAFETI A71-21819 Cargo aircraft crew safety and survival, Noise pollution control and airport noise levels describing restraint, escape, flight deck abatement requlation by state government. taking interior doors, fire and smoke hazards and into account economic and technical feasibility personnel environmental protection A71-21825 [ SAE-ABP- 11 39 ] A71- 19643 Aircraft noise abatement control on international Materials and construction techniqnes in lightninq basis by settinq aconstic technoloqical protection for aircraft and helicopters capability compulsory standards of quietness A71-19930 A71-21826 Lightning current transfer tests of p-static Federal legislation and regolatory activities for discharqer for aircraft installations rontrol and =.batelent of aircraft noise A71-19935 171-21827 lightninq ax? snrg- protection devices for State, local qovernment and airport proprietor survivability of aircraft electrical systems legal role in requlating aircraft noise at A71-19941 airports Establishment of take-off and landing safety A71-21828 margins for Brequet 941 Federal legislation and regolation of aircraft [ NASA-TT-F-134531 1171-17441 noise, legal rights of airport ueiqbbors and AIBCBAPT STABILITT leqal aspects of compatible laud nse, discussing DC-10 flight test program, discussing handling. noise control efforts takeoff and landinq. and flntter, stall and A71-21829 stability characteristics Land use control in aircraft noise abatement. A71-19085 considering airport development and commnnity Airliner acceptance checks characteristics for qoals official licensing prerequisites, investigating A71-21836 takeoff, landing, ascent, stability and control Land development planning ana aircraft noise at A71-20065 Kansas City International Airport Aircraft elastic rode control for turbulence A71-21837 /gust/ alleviation, noting riding quality, Development of acoustic lining for turbofan structural fatique life and peak loads nacelle modification to iinimize fan compressor A71-20301 noise radiation AIBCRAFT STROCTOBES C IIASA-CR-1712] 1171- 17591 BD-1Yankee aircraft development, design and Plightworthy nacelle development to minimize fan construction compressor noise radiation - Vol. 4 A71-19084 [NASA-CB-1714 J 1171-17668 Artificial liqhtning generation facilities for leasnrement of variability of aircraft noise aircraft component developmental testinq by during level fliqht flyovers manufacturer I BASA-CB-1752 J 1171-18865 A71-19931 Noise measurement evaluation of takeoff and Elastic, inertial and aerodynamic forces approach profiles optimized for noise abatement aeroelastic triangle, examining lift changes due C NASA-TR-D-6246 J 1171-18929 to aircraft structnre deformation, dynamic AIRCBAPT PEBPOBIIAICS flight stability and space shuttle development F-15 air superiority fighter. describing military problems requirements, prograi manaqement and procedures A71-20063 in terms of speed, manenverability, acceleration Filament winding manufacturing methods using and weaponry unidirectional qlass reinforcements for desiqn A71-19078 and fabrication of aircraft wing structure Boeinq 737 aircraft takeoff and landing [SUE PAPER El-70-4061 A71-20546 performance. emphasizing high lift systems and Bent strncture failure under pulse floor stopping capability acceleration shocks, concerning aircraft seat 171-19083 damage during crash landing DC-10 flight test program. discussinq handling. A71-20747 takeoff and landing. and flutter. stall and Aircraft systems assembly methods. discussinq stability characteristics rigidity effects on error redistribution in A71-19005 external and internal force field application AIRFOIL PROFILES SUBJECT INDEX

A71-20792 AIRPORT PLANNING cost aspects of carbon fiber reinforced composites Airport lighting facilities in Japan, considering in aircraft structures, suqgesting increased fixtures, marker and obstruction lights and aviation market for carbon fiber apron floodliqht rPLASTICS INST. PAPER 463 1171-20929 A71-20355 Finite element analysis of structures in plastic Noise reduction at source, flight methods ranqe adjustments and airport compatible land use for [NAS&-CR-l649J N7 1-19276 jet noise abatement Comparison of hydrogen and methane as coolants in A71-21815 reqeneratively cooled panels Airport pollution dispersion modelinq. simulatinq NASA-CR-1652J N7 1-19289 effect on surrounding areas for abatement AIRFOIL PROFILES strategies calculation lonoqraph on transonic shock free potential flow A71-21824 around quasi-elliptical airfoil sections, Noise pollution control and airport noise levels investiqatinq flow stability under unsteady abatement regulation by state qovernment, taking disturbances into account economic and technical feasibility A7 1- 19773 A71-21825 Computer calculation of hiqh Reynolds number Federal assistance to air transportation, viscous and inviscid flow over arbitrary shaped considering airport development-environment two dimensional bodies and airfoils conflicts A71-20313 A71-21834 Hanging shock wave in small supersonic flow past AirDort svstem Dlannina for natural and urban profile with broken qeneratrix in plane ideal environment compatibility qas A71-21835 1171-21872 Land nse control in aircraft noise abatement, Airfoil profile draq measurements. correlatinq considering airport development and community full scale fliqht tests and scale model tests in qoals transonic and hiqh Reynolds number wind tunnels A71-21836 rAIAA PAPER 71-2897 A71-22012 Land develoament Dlanninq and aircraft noise at AIRFOILS Kansas City International Airport A71-21837 Viscous qas flow interaction on delta win9 and oblique airfoil at Hach number of infinity Planninq system for metropolitan airportsN71-17546 A71-19739 C PAA-AC-~~O/~O~O-~~ Computerized transonic airfoil design from SPstemS analvsis summarv on New rork metropolitan predetermined supercritical velocity 'area air tkaffic capacity mi-18040 distribution, obtaininq equivalent incompressible flow through streamline and AIRPORTS potential line network transformation neteorological observations for terminal ueather h71-20304 modification in aviation, noting airport fog Reqions upstream and downstream from shock waves dispersal of airfoils in uniform and transonic flow A71-21732 [NASA-TT-F-13472 J N71-18401 Air pollution emissions at Heathrow Airport, AIRFNAIE MATERIALS London, from aircraft operations, heatinq Structural efficiency improvement by materials installations and road traffic selection for airframe structures, discussinq A71-21823 Al. Ti-Al-V and steel panels Development model for Oklahoma airport A71-21685 [PB-1949371 N71-16987 Aluminum alloy stress cycles and fatique life of Data processing and impact analysis on rapid rail airframe materials access system for airport IFB-78-19691 N71-17524 rPB-195047J N71-16988 AIRPRAUES Data recordings and computer codes for airport Complex airframe desiqn for economic and safe rapid transit access system study operation and long life using fatique and r~~-i950481 N71-16989 fracture mechanics Survey of rapid transit railway impact on airport rAIAA PAPER 70-5121 1171-22025 passenqer traffic International conference on rain erosion and CPB-1950451 N71-16990 associated phenomena Tabulations for rapid transit system effect on AD-715100 J N71-17906 airport traffic IIRLINE OPERATIONS [~~-igso491 171-16991 Airliner acceptance checks characteristics for Rapid transit railway effect on airport passenger official licensinq prerequisites, investiqatinq traffic takeoff, landing, ascent, stability and control CPB-1950461 N71-16992 A71-20065 Economic analysis of airport construction in north Civil aviation aircraft mean flight time overhaul central Texas region, emphasizing employment and schedules. considering statistical. evaluation of dollar value of purchases N71-18099 relationship betueen operational Characteristics and time betueen overhauls Pnblic transportation in airport access systems A71-20797 N71-18951 Jet aircraft noise over residential areas, Mass transport systems for airport access discussinq actual and permissible noise levels N71- 18952 and proposals for remedial action Problems in mass transportation systems for access A71-21163 to Tokyo airport Airline collision avoidance system test and N71-18953 evaluation proqram, considering range, rate and Public transportation requirements for Eeathron altitude accuracy, communications reliability, Airport STnchroniZation and system integration with air 171-18954 traffic control Providing ground access to Kansas City Airport A71-21167 N71- 18955 Civil aeronautics operations review Existing access systems for Logan International N71-17779 Airport, and plans for improvement Problems in civil air transportation and loqistics 171-18957 171- 17799 AIBSEIPS Problems facinq local air transport industry, Airships and balloons potential commercial use in communities. and government agencies Canada. discussinq cargo, passenger and military 171-18078 applications Iuvestiqatinq statistics of aircraft accidents by A71-19916 region and operator Design and characteristics of double hull rREPT-1970/10-EJ 1171-181 15 dirigible airship [ JPRS-52330 J N71- 19217

A-0 SWBJECT 11DII A8601

URSPACI A71-19695 ATC automated systems. discussing national Hose bluntness, angle of attack and oscillation Airspace System En Route Stage A and Advanced aaplitnde effect on hypersonic unsteady Eadar Terminal System aerodynamics of slender cones IAIAA PAPBR 71-2441 A71-19719 [AIAA PAPBR 70-2161 A71- 19895 Systems analysis summary on neu Tork metropolitan Bxauning three-dimensional motion of flying area air traffic capacity vehicle entering atmosphere at low angles of 171-18040 attack ALGOPITEES 871-16901 Kalman-Bncy linear filtering algorithm application Eeasnring value of entropy on surface of body of to nonlinear estimation of single channel revolution at nonzero angle of attack missile attitude control system parameters 871-16903 A71-18035 Investigation of angle of attack information Soviet book on qas flow past blunt bodies. Part 1. display for pilots to increase efficiency of Plow analysis and calculation methods covering general aviation aircraft operation finite difference theory, algorithms. etc tiASA-T!I-D-6210] 871-18442 A71-19049 Al6ULAR TILOCITI Algorithm for digital resolution of range for Axisymmetric body rapid rotation under center of V/STOL aircraft gravity velocity vector conditions, solving for I MASA-TR-D-6232] 1171-18566 plane gliding motion stability in air ALIGBMIIT 1171-19354 Strapdown inertial naviqator alignment by digital Free flight measurement of aerodynamic filtering techniqnes. discussing application to coefficients on fixed cruciform fin stabilized aircraft and spacecraft bombs. determining aerodynamic forces and 171-21170 moments dependence on angular velocity ALL-SIATEXR UR IATIGATIOI components Ean-machine considerations in all-ueather low- A71-19872 altitude navigation system design, discussing Describing angular position and velocity sensing computer generation of roll command guidance. apparatus visual display and pilot modelinq [ RASA-CASE-IGS-05680 J 1171-17585 A71-20344 IlTIIIA ARRAYS Reather outline qenerators for producing contours Planar microuave array antenna for scan around radar ueather clntter for all ueather air requirement, discnssinq tilt angle and element navigation arrangement optimization [ FAA-EA-70-62] 871-17527 [AIAA PAPEE 70-1911 A71-22030 ALTIIIETXRS IITIPRICTIOI BEARIIGS Aircraft altimeter containing X ray source Aircraft gear pumps bearing elements design for 1171-16993 increasing service life ALUIIIMUM A71-20793 Ribbed aluminum panels airborne sound transmission APOLLO SPACECPAPT loss, evaluating structural dampinq effects Comparative sting supported and free flight tests A71-21431 in hypersonic wind tunnel on modified Apollo structural efficiency improvement by materials launch configuration selection for airframe structures, discnssinq [AIAA PAPER 71-2651 A71-21991 A1. ?i-.K-Y and steel ranela APPROACB 1171-21685 In-flight determination of iater~i-directional UUIIIIUM ALLOTS dynamics for landing approach Ball forminq technique application to A1 alloys r AD-7153173 871-17792 structural part contouring. discnssinq 1-1011 APPROACE COlTROL wing panel forminq and prestress toolinq Aircraft navigation system requiring computer and A71-21681 display for approach guidance to circular orbit Random errors in aluminum alloy fatigue tests and over fixed ground area failure modes [AIAA PAPER 69-9861 1171-20305 IARC-CP-1123 J 871-17330 Noise abatement power cutback takeoff procedures. Aluminum allov stress cycles and fatigue life of maximum altitude approaches and preferential airframe materials runway systems for noise relief [ FB-78-19691 1171-17524 A71-21813 ALWEIIUM COATIIbS minimizing performance criterion to analyze Performance of alnminide coatings in simulated ability of automatically controlled aircraft to hiqh temperature tests on qas turbine engine maintain accnrate flight path control during inlets landing approach IRASA-CR-1163741 1171-17393 [ NASA-TB-D-6230] 871-18761 A!IPLIFICATIOI APPROACE IIDICATOPS Kalman filter application as observer of Aircraft final approach and landing aids, observable siqnals derivatives, using gain describing ILS, VEP omnidirectional radio range. matrix to minimize variance estimate for distance measuring eqnipment and satellite instrument landinq systems systems for air navigation A71-21343 A71-19014 AMPLITODB DISTRIBOZIOI AIALTSIS APPROIIMATIOI Rose bluntness. angle of attack and oscillation Approximation of Chaplyqin egnation for subsonic amplitude effect on hypersonic unsteady ideal gas plane adiabatic flow, applying to aerodynamics of slender cones discharge from flat channel with contraction [AlAA PAPER 70-2161 A71-19895 1171-20083 AIALOG TO DIGITAL COITXBrXRS TWO link approximation of Chaplygin function by ATC automation program for en route and terminal conplinq to integral equations. applying to centers, discnssinq combined nationside svstem ideal qas jet separatton flow past symmetrical features, IPE volume and video digitizer data arc links A71-20004 A71-21659 Enltilink approximation of Chaplygin function in AIXEOMXTIRS subsonic and supersonic flou regions, deriving Velocity and density measurements in hypervelocity coupling conditions relative to modified stream ballistic projectile turbulent uakes, usinq hot function at approrimation nodes film anemometers 1171-20090 [AIAA PAPEE 68-7011 A71-19891 AEGOI AIGLI OF ATTACK Performance of axial flow compressor for Brayton USAP F-4E Stall/lear Stall Investigation. cycle electrical power generating system with discussing testing requirements. fiqhter arqon aircraft improvement, spin avoidance and hiqh [ RASA-TE-X-2194 1 871-17882 angle of attack limitations

A-9 ASPECT RATIO SUBJECT INDEX

ASPECT EAT10 of space diversity ILS receiving system Low speed boundary layer separation on compressor A71-18830 blades of varyinq aspect ratios ATC automation program for en route and terminal r ARC-CP-I 103 1 N71-17108 centers, discussing combined nationwide system ASSEMBLIIIG features, IPR volume and video digitizer data Aircraft systems assembly methods, discussing links rigidity effects on error redistribution in A71-21659 external and internal force field application System description of field test model of ARTS 2 A71-20792 modular alphanumeric nontracking ATC system ASIMPTOTIC METEODS N71-18815 Lifting surface nonstationary aperiodic motion in AUTOMATIC PLIGET COIITBOL incompressible fluid solved by asymptotic method Optimum automatic flight control techniques in of function parameters, using algorithm for horizontal quidance of aircraft at terminal Cauchy problem A71-20306 A71-20778 AUTOMATIC LAlDIIIG COIITROL ATLANTIC OCEAN Two dimensional aircraft automatic landing motions Communications, navigation and surveillance for control processes by simulation without use of aircraft and marine vessels in North Atlantic noving cockpit simulator reqion, discussinq baseline traffic control A71-20066 model aininizinq performance criterion to analyze A71-18808 ability of automatically controlled aircraft to ATMOSPEERIC ATTESUATIOII maintain accurate flight path control durinq Aircraft flyover noise samples, obtaining landinq approach atmospheric absorption coefficients [ NASA-TN-D-6230) N71-18761 A71-21425 AUTOMATIC PILOTS ATMOSPEERIC CIRCULATION Automatic Carrier Landing System vith linear Sounding system coustant level superpressure adaptive aircraft Navigation Computer, balloons for atmospheric circulation qlobal investiqating effectiveness in reduciuq system description at all levels and latitudes in errors due to nonlinearities and noise effects conjunction with satellite observations A71-20405 A71-21742 AUTOMATIOE ATMOSPEERIC EIITBI System automation evolutionary process in terminal maximum staqnation temperature on swept winq Air Traffic Control environment leadinq edqe for equilibrium qlide entry of lAIA.4 PAPER 71-2421 A71-19717 space shuttle Automatiou of technological processes in aircraft A71-18902 enqine production Exanininq three-dimensional motion of flyinq r AD-7148581 N71-17832 vehicle enterinq atmosphere at low anqles of AUXILIARI POWER SOURCES attack Inteqrated drive AC qenerator for aircraft, N71-16901 discussing desiqn improvements in power-weiqht ATMOSPHERIC IONIZATIOII ratio Nonequilibrium multicomponent ionization A71-19494 calculations for staqnation merqed shock layer AVIONICS of hypersonic blunt body by successive Avionics subsystem design improvements for accelerated replacement aeronautical systems, considering fAIAA PAPER 69-6551 A71-19890 standardization. weiqht impact, environmental ATMOSPHERIC MODELS control, maintainability and equipment growth Airport pollution dispersion modelinq, simulatinq A71-18829 effect on surroundinq areas for abatement Navy avionic modular multiprocessinq diqital strategies calculation computer operating system reliability, comparing A71-21824 totally software and partly hardware approaches ATMOSPHERIC MOISTURE A71-18833 Effect of atmospheric humidity on characteristics Draw-throuqh cooling of electronic equipment in of turbofan enqine subsonic and supersonic commercial jet r AD-7 15232 1 N71-17728 transports, discussing internal circulation ATMOSPRERIC PHYSICS system desiqn Observational data characteristics analysis as [ SAE-AIR-64A1 A71-19642 contributor to knowledqe and utilization of all Late model F-4 air superiority aircraft and atmospheric physical occurrences electronic fliqht control systems protection A71-21722 aqainst lightninq discharqes damage to electric ATNOSPHERIC TENPERATURE and electronic systems Air temperature effects on internal combustion A71-19940 enqines intake process, usinq similarity theory Liqhtninq and surge protection devices for A71-20782 survivability of aircraft electrical systems ATTITUDE COSTROL A71-19941 Kalman-Buc? linear filterinq alqorithm application Avionics for qliders and tourinq aircraft. to nonlinear estimation of sinqle channel considerinq safety and VHF radio equipment missile attitude control system parameters A71-20684 871-18835 Performance test methods and equipment for Planar microwave array antenna for scan aircraft avionics and weapons systems, requirelent, discussinq tilt anqle and element discussing computer integration with radar and arranqemeut optimization phototheodolite range instrumentation system rbIAh PkPER 70-1911 A71-22030 A71-21660 AUDIO PREQUEIICIES Avionics for qliders and tourinq aircraft, Low speed wind tunnel pressure and audio frequency surveyinq available electronic equipment for resonance measurements on circular cylinders and 1971 thin flat plates A71-21768 r NPL-AERO-13111 N71-17089 Development and characteristics of frequency AUDITORY PERCEPTION separated display devices for aircraft control Subjective evaluation tests of qround observers on TAD-7154581 N71- 18739 relative noise from acoustically treated enqine AVRO 707 AIRCRAFT nacelles of Boeinq 707 aircraft Boundary layer separation and lonqitudinal and [NASA-CR-17171 N71-18499 lateral stability of Avro 707 aircraft during AURORAS fliqht tests N71-17082 Photometer observations of auroras from cv-990 [ ARC-CP-1107-PT-4 1 aircraft Low speed lateral stability and control fliqht f NASA-CR-1168551 N71-18996 tests on Avro 707 aircraft AUTONATIC COlTROL r ARC-CP-1106-PT-3 I N71-17083 Aircraft automatic landinq improvement throliqh use

A-10 SUBJECT IIDEI BOEIIG 707 AIECEAFT

AXIAL COIPEESSIOll LOADS ELIlD LAlDIIG Determininq feasibility of increasing stator blade VPR flying nnder bad weather conditions, loadinq of single stage compressor riq by discnssing flight throngh and above clond bleeding or blowing snction snrface bonndary layers. need for radiotelephone communication layer and gronnd radar snpport r NASA-CR-54573 J N71-18749 A71-21767 AIISTIIETEIC BODIES BLOPWWI WIPD TOIEELS Axisymmetric body rapid rotation nnder center of Error analysis for pressnre measnreients on gravity velocity vector conditions, solving for blowdown snpersonic wind tnnnel models plane gliding motion stability in air [ NPL-AERO-13061 1171-17081 A71-19354 Semiscale blowdown and emergency core cooling Reacting and nonreactinq gases laminar bonndary project test report layer flows over two dimensional and r1~-13931 1171-17190 axisymmetric bodies at zero lift, coaparinq Investigating effects of leading-edqe blowing on numerical methods aerodynamic characteristics of jet flapped A71-19860 airfoil Dependence of aerodynamic coefficients on maximum 871- 17702 thickness and length of axisymmetric bodies in Resnlts of two-phase blowdown experiments with snpersonic flow straiqht tube test section and steam-water f DLR-PB-70-54 1 N71-18444 mixtures Singularity method for calcnlation of potential [ AECL-36641 N71-18161 flow aronnd axisymmetric rings Nozzle flow calibration in blowdown wind tnnnel N71-18469 r WE-TN-ESA-1713 1171-19170 AIISTIIETEIC ?LOW BLUIT BODIES Nonstationary isentropic low density flows with Solid particle impurity effects on hypersonic axial or central symaetry. snqgestinq shock tnbe flow. determininq error in blnnt body characteristics with flow rate and sonnd speed measurements variation as in stationary sonrce flow A71-18916 A71-19729 Soviet book on gas flow past blnnt bodies. Part 1. Near-continnum arisymmetric hypersonic flow past Plow analysis and calcnlation methods coverinq very slender bodies finite difference theory, algorithms, etc [AD-715901 J 171-18556 A71-19049 AZIIUTE Soviet book of gas dynamic fnnction tables for two Gyrocompass strapdown three coil synchro sensor and three dimensional flows past blnnt bodies maqnetometer in con-Junction with vertical qyro. A71-19050 eliminatinq azimnth detector inertial platforms Eypersonic radiating gas inviscid flow past blnnt 171-20340 bodies, nsing spherical harmonics approximation A71-19183 Interaction between radiation from shock wave B region and oncoming cold air flow in hypersonic 8-70 AIECRAR flow past blnnt body Base pressnre measnrements on XB-70 aircraft at A71-19730 Each numbers from 0.4 to 3.0 Dissociating airflow over two dinensional blnnt r IIAS A-TB-X- 1612 1 N7 1- 17132 body, determining laminar bonndary layer BAF?LZIS chemical reaction suppression effects on heat Vertical motion of static loads over baffles exchange dnrinq loadinq operations usinq qround effect A71- 19748 machines Nonegnilibrinm mnlticomponent ionization [NPL-EOVEECRAPT-TE-3lJ R71-17160 calcnlations for stagnation merged shock layer BALLISTIC TEAJECTORIES of hypersonic blnnt body by snccessive Bessel fnnction solutions for low anqle of attack accelerated replacement approach of flyinq vehicle to atmospheric [ AIAA PAPER 69-655 J 1171-19890 bonndary and transition into vibrational motion Nose bluntness, anqle of attack and oscillation N71-16983 amplitude effect on hypersonic nnsteady BALL001 SOUID116 aerodynamics of slender cones Sonndinq system constant level snperpressnre CAIAA PAPER 70-2163 1171-19895 balloons for atmospheric circulation global Unsteady analogy for hypersonic flows past blnnt description at all levels and latitudes in bodies with shock deformation coninuction with satellite observations A71-21863 A71-21742 Trajectories prediction for subsonic spin BALLOOMS stabilized projectiles via water tnnnel tests, Airships and balloons potential commercial nse in considering blunt nose and tail and ronnded nose Canada. discnssing cargo. passenger and military right circnlar cylinders applicqtions [AIAA PAPER 71-2961 A71-22016 A71-19916 Investigating snpersonic viscous gas flow aronnd BASE PRESSURE blnnt bodies Wind tnnnel testing of base pressnre model 171-16902 attached to long cylindrical body extended and BODIES OF PEIOLOTIOl snpported far npstream Snrface constrnction of body of revolntion in [AIAA PAPER 71-2681 A71-21994 snpersonic gas flow from distribntion of Base pressure measnrements on IB-70 aircraft at velocity vector modulus along generatrix of Each nnmbers from 0.4 to 3.0 body, nsing Prank1 method of characteristics EASA-TB-1- 1612 3 171-17132 A71-20089 BEACOIS Ieasnrinq value of entropy on snrface of body of LOW profile optical system prodncinq annular cone revolntion at nonzero anqle of attack of radiation from point sonrce for hiqh speed N71-16903 aircraft beacon Tnrbnlent wakes of flat and rotationally A7 1- 19203 symmetrical bodies noting width development BESSEL FlJICl'IOlS N71-18472 Bessel fnnction solutions for low anqle of attack BODT-9116 A1D TAIL CO1FI6UPATIOIS approach of flying vehicle to atmospheric Transverse and torsional vibrations of fnselage- boundary and transition into vibrational motion wing combination with winq tip fuel tanks, 1171-16983 calcnlating mass and stiffness matrix for BLLDE TIPS elastic beam Transonic compressor rotors blade camberline shape A71-20364 optimization by various tip diffnsion BOLIlG 707 AIRCRUT factor-ratio combinations Static tests to determine effects of throat inlet A71-20200 concepts on forward-radiated fan noise of 707-320B/C airplanes

A-11 BOEING 727 AIRCRAFT SUBJECT INDEX

[ NASA-CR- 1715 1 N71-17426 construction from qiven velocity or pressure BOEING 727 AIRCRAFT distribution and supersonic flow boundaries Conqressional hearinqs on Boeing 727 use of determination Uashinqton National Airport A71-20078 N71-17697 BRATTON CYCLE BOEING 737 AIRCRAFT Performance of axial flou compressor for Brayton Boeinq 737 aircraft takeoff and landinq cycle electrical power qeneratinq system with performance, emphasizing hiqh lift systems and argon stoppinq capability [ NASA-TH-X-2194] N71-17882 A7 1- 19083 BREGUET 941 AIRCRAFT Turbulent boundary layer pressure fluctuations Establishment of take-off and landinq Safety in-fliqht measurements on Boeinq 737 aircraft, marqins for Brequet 941 obtaininq power spectral densities and RHS [ NASA-TT-F-134531 N71- 1744 1 pressure fluctuations for various Hach numbers Feasibility of inter-metropolitan transport system 1171-21426 usinq Brequet 941 STOL aircraft BOHBS (ORDIIANCE) r REPT-50 1 N71-18104 Free fliqht measurement of aerodynamic BRISTOL-SIDDELEY OLYHPUS 593 EIIGINR coefficients on fixed cruciform fin stabilized Efficiency of air coolinq blade design for OlympUS bombs, determininq aerodynamic forces and 593 qas turbine engine moments dependence on anqular velocity N71- 17376 components BROADBAND A71-19872 Aerodynamic broadband noise mechanism applicable BORON to axial compressors Liqhtninq protective coatinqs for boron and [NASA-CR-17431 N71-77958 qraphite fiber reinforced plastics BURIIIIIG RATE 871-19944 pressure wave distortion effects on combustor BOUIDARY LAYER CONTROL acoustic mode instability based on model with Potential flow past cylinder with sources and burninq rate related to Reynolds number sinks sinqularities, derivinq formulas for A71-19906 aerodynamic characteristics of infinite span uinqs with boundary layer control A71-20777 C BOUNDARY LAYER FLOU CABLES (ROPES) Reactinq and nonreacting qases laminar boundary Derivation of stability boundaries in wind tunnels layer flous over two dimensional and for bodies towed by cables axisymmetric bodies at zero lift, comparinq [ ARC-R/H-3644] N71-18461 numerical methods CAlBER A71-19860 Transonic compressor rotors blade camberline shape Unsteady boundary layers on sphere or cone movinq optimization by various tip diffusion alonq axis, determininq skin friction anqular factor-ratio combinations response A71-20200 A71-20098 CAIIBERED SINGS Uind tunnel boundary interference on V/STOL model Aerodynamic coefficients, pressure, load and force calculated in test section with solid vertical distributions on cambered delta winqs and slotted horizontal walls, usinq image method [ ARC-CP-1129 1 N71-17112 and Fourier transforms CAPTIVE TESTS [AIAA PAPER 70-5751 A71-22029 External store surface pressure distributions BOUNDARY LAYER SEPARATION durinq captive fliqht aboard P-4B aircraft, Viscosity effects on three dimensional supersonic considerinq carryinq aircraft effects on flow flow around circular half cones on flat plate, field about airborne ordnance examininq turbulent boundary layer separation [AIAA PAPER 71-2951 A71-22015 A71-19743 CARBOII DIOXIDE LASERS Boundary layer discontinuity on helicopter roter Foq removal by hiqh power carbon dioxide lasers, blade in hoverinq usinq flow visualization evaluating possibility of clearing airport [AIAA PAPER 69-1971 A71-20307 runways Boundary layer separation and lonqitudinal and AIAA PAPER 69-6703 A71-20308 lateral stability of Avro 707 aircraft durinq CARBOII FIBERS fliqht tests Cost aspects of carbon fiber reinforced composites [ ARC-CP-1107-PT-4 1 N71-17082 in aircraft structures, suqgesting increased Low speed boundary layer separation on compressor aviation market for carbon fiber blades of varying aspect ratios [PLASTICS INST. PAPER 461 A71-20929 lARC-CP-1103] N71-17108 CARET SINGS BOUNDARY LAYER TRAIISITIOII Caret wing serial tests in Hach 8 to 15 hypersonic Boundary layer optimization for small turbine flow. including three component force, spanwise blade desiqn with cusped trailing edqe direction pressure distribution and shock wave N71-17380 anqular measurements by flow visualizationA71-20015 BOUIIDART LAYERS Nonequilibrium electron temperature, concentration Rectangular and caret wing sails in supersonic and and reflection in reentry boundary layers, hypersonic turbulent flou for hypersonic discussinq heat transfer and ionization energy vehicles diffusion [ ARC-R/B-3624] N71-17103 rAIAA PAPER 69-821 A71-19879 CARGO Ground boundary layer effects of fixed ground Freiqht transportation in Great Lakes area for plane for powered STOL wind tunnel model, year 2000 discussinq flow breakdown criteria, contraction N71-19320 laq. strut fairinq interference, etc CARGO AIRCRAFT [AIAA PAPER 71-2661 A71-21992 Cargo aircraft crew safety and survival, Determininq feasibility of increasinq stator blade describing restraint, escape, flight deck loading of sinqle staqe compressor riq by interior doors, fire and smoke hazards and bleedinq or blowing suction surface boundary personnel environmental protection laver [ SAE-ARP-11391 A71-19643 INASA-CR-54573 1 N71-18749 Report of aircraft accident due to forward shift BOUlDARY VALUE PPOBLEES of improperly secured cargo Boundary value problems and applications in fluid [ NTSB-AAR-71-61 N71-19041 and gas mechanics - Conference, Kazan. U.S.S.R., CASCADE FLOW nay 1969 Gas-particle mixture cascade flow over turbine A71-20076 blades, considering momentum/heat transfer and Inverse boundary value problems in particle trajectories hydroaeromechanics, involvinq profile [AIAA PAPER 70-7121 A71-20311

A-12 SUBJET IIDEI CIVIL AVIATIOI

Low aspect ratio compressor blade cascade discharge from flat channel with contraction performance at blade span center, discussing A71-20083 pressure loss, anqle of attack and staggering Two link approximation of Chaplyqin function by A71-20624 conpling to integral equations, applying to Radial flow energy losses in rotating cylindrical ideal gas jet separation flow past symmetrical cascade of inward-flow turbine wheel. arc determining profile losses and exit blade angle A71-20084 A71-22044 nultilink approximation of Chaplygin function in CASCADSS subsonic and supersonic flow regions, deriving Two dimensional cascade test of let flan turbine coupling conditions relative to modified stream rotor blade function at approximation nodes I EASA-TO-1-2183 J 1171-17589 A71-20090 CATALYSIS CHAP6116 Catalytic surface effects on thermocouple Helicopter charging 8eChaniSDS. considering engine combustion gas temperature measurements in jet and rain precipitation charging engines A71-19933 E7 1- 17379 Electrostatic charging noise measnrement. CATALYTIC ACTIVITY reduction and flight test verification Kinetics of catalytic dehydrogenation of A71-19937 methylcyclohexane at 600. 650. and 700 deg P and CHAETS 5 atm pressure Worldwide aeronautical charts maintenance for [ AD-7159261 1171-18729 weapon systems support, discussing data sources CAUCEY PEOBLEII A7 1- 2 1254 Lifting surface nonstationary aperiodic motion in CHBIIICAL PEACTIOIS incompressible flnid solved by asymptotic method Dissociatinq airflow over two dimensional blunt of function parameters, using algorithm for body, determining laminar boundary layer Cauchy problem chemical reaction suppression effects on heat A71-20778 exchange CAVITATIOI PLOW 171-19748 Cavitation flow of fluid with free surface past Reacting and nonreacting gases laminar boundary underwater ring with jet flap, solving equations layer flow over two dimensional and of motion for thin foil with jet emergent from axisymmetric bodies at zero lift, comparing trailinq edge numerical methods A71-20086 171-19860 Heavy fluid flow past paztially cavitating flat CEIOIEYS plate with cavity closed by fictitions plate, Wind tunnel aerodynamic stability tests on Considering lifting force under gravity chimnevs with DiDes.. and helical windina A71-20087 stabilizers Suction and pressare head and temperature effects [APL-AEEO-1310 J 1171-17334 on cavitation flow in aircraft fuel pumps CIECUIT PPMBCTIOH r ARC-CP-1128J n7i-17044 Late model P-4 air superiority aircraft and CAVITY PESOIATOES electronic flight control systems protection Pressure measurements of flow induced cavity against lightning discharges damage to electric resonance and effects of resonance suppressing and electronic systems devices A71-19940 r EASA-TU-D-62051 1171-17877 Liqhtning and surge protection devices for CEETEII OF SEAVITY sdrvivability of aizczaft electrical systems Axisymmetric body rapid rotation under center of A71-19941 gravity velocity vector conditions. solving for CIPCUIT BELIABILITY Plane qliding motion stability in air nicroelectronic circuits reliability in aircraft 171-19354 engine control applications, discussing testing Center of gravity vertical acceleration and ring and selection for severe temperature and stresses of Boeing 720-8 aircraft vibration environments [TB-87-19703 171-17119 [SAE PAPER 7008221 A71-21369 CEITEIFU6AL COIIPEBSSOPS CIECUITS Turbocharqed diesel engine precompressed inlet air neasurements and analysis of lightning-indnced cooling by evaporation cooling. considering voltages in aircraft electrical circuits water injection effects on centrifugal [ EASA-CR-17443 1171-19122 compressor CIRCULAE CILIIDERS A71-20781 wind tunnel experiments on vortex shedding from Centrifuqal compressor vaneless diffnser. circnlar cylinders in oscillating free stream estimating energy losses with hydrodynamic model A71-19908 A71-21266 Trajectories prediction for subsonic spin Axial-radial and radial compressor stage optimum stabilized projectiles via water tunnel tests. exit blade angle. considering flow rate control considering blunt nose and tail and rounded nose by variable pitch nozzle guide vanes riqht circular cylinders A71-22049 f AIAA PAPER 71-2961 A71-22016 CBITRIPWAL PUIIPS Low speed wind tunnel pressnre and audio frequency Centrifuqal pump channels flow velocity resonance measurements on circular cylinders and measurement by optical method, noting flow thin flat plates separation near blade exits [ BPL-AERO-1311 J ~71-17089 A71-22048 CIECULAP TUBES CEAIIEL PLOU Periodically supported and damped closed circular Flow in channel with abrupt asymmetric widening. beam structure, determining frequency response calculating expanding flow velocity profile by matrix Prandtl semiempirical turbulence theory A71-22026 A71-22041 CIVIL AVIATIOI Centrifuqal pump channels flow velocity Civil aviation aircraft mean flight time overhaul measurement by optical method, noting flor schedules, considering statistical evaluation of separation near blade exits relationship between operational characteristics A71-22048 and time between overhauls CBAIIELS (DATA TEAHSIIISSIOE) A71 -20797 Computer display channel for en route air traffic Commercial aviation stratospheric water vapor control flexible real time data processing and injections influence on radiation budget, ozone. display subsystem polar night cloudiness and potential climatic [AIAA PAPEH 71-2471 A71-19721 effects CEAPLY6II EQOATIOil A71-21822 Approximation of Chaplygin equation for subsonic OS general aviation and supplemental air carrier ideal qas plane adiabatic flow, applying to accident statistical tables for 1969

A-13 CLBAB AIR TURBULBNCI SUBJECT INDEX

[ NTSB-BA-70-6 1 N71-17475 Combustor design for minimum exhaust smoke Conqressional hearinqs on Boeinq 727 use of emission from aircraft gas turbine jet engines, Uashinqton National Airport considering air pollution N71-17697 A71-20867 Civil aeronautics operations review Book on aircraft gas turbine enqine technology N71-17779 covering combustion chambers, exhaust systems, Employment opportunities for economists and air lubricating oils, thrnst augmentation, inlet transportation analysts with Civil Aeronautics ducts and overhaul procedures Board A71-21625 N71-17798 Performance of short modular turbojet combustor Problems in civil air transportation and loqistics sequent with ASTH-A1 foe1 N71-17799 TNASA-TN-D-61671 N71-17414 Problems facinq local air transport industry, Jet engine combustion chamber burn-through fire communities, and qovernment agencies and methods for controlling damage N71-18078 FAA-RD-70-681 N71-17483 Air transport supply on scheduled services in Effect of tailpipe length on conbuster stability Europe-Hediterraneau and Southeast Asia regions in ramjet conbusters r REPT-1970/1-E] N71-18112 N71-17725 CLBAR AIR TURBULENCE Combustion stability limits for swirl-iet Turbulent/total flight mile ratio in high altitude combustor modules combining air swirl and clear air turbulence /HICAT/ proqram impinginq jet atomization of ASTn A-1 fuel A71-20314 [ NASA-TH-X-2218] N71-18560 synoptic meteorological conditions for clear air Effect of various diffuser desiqns on performance turbulence and turbulence effects on aircraft of experimental turbojet combustor insensitive fliqht characteristics to radial distortion of inlet airflow DLR-PB-70-291 171-17145 [ N AS A-TH-X- 22 161 N71-18561 CLOUD COVER Annular diffuser and combustor assembly in full VPR flyinq under bad weather conditions, scale duct burner for supersonic turbofan engine discussing fliqht throuqh and above cloud r NASA-TN-D-6 1631 N71-18882 layers, need for radiotelephone communication COMBUSTIOU PEYSICS and qround radar support Performance of short modular turbojet combustor A71-21767 seqment with ASTH-A1 fuel N71-17414 CLOUD PHYSICS r NASA-TN-D-6 167 1 Spatial correlations between inside cumulus cloud Combustion stability limits for swirl-jet conditions and precipitation onset and intensity combustor modules combiniuq air swirl and for modification experiments from aircraft impinging jet atomization of ASTH A-1 fuel penetration measurements [ N ASA-TI-X- 221 81 N71-18560 A71-21450 COMBWSTION PRODUCTS CLOUDS (METEOROLOGY) water vapor condensation effects on methane-air Soviet hook on foq, cloud and humidity measuring combustion qases for aerodynamic test medium instruments, discussing artificial foq formation rAIA.4 PAPER 71-2581 A71-21986 and natural foq dispersion problems COUBUSTIOU STABILITY A71-20298 Pressure wave distortion effects on combustor COANDA BPPBCT acoustic mode instability based on model with Ground effect vehicles limitinq volumetric burning rate related to Reynolds number dissipations from air cushion and propulsion A7 1- 19906 systems with fluid boundary by Coanda effect COMBUSTION TRMPBRATWBB A71-19923 Catalytic surface effects on thermocouple COBALT ALLOIS combustion qas temperature measurements in let Cobalt and nickel based alloy metallurqy for hiqh engines temperature qas turbine materials N71-17379 N71-17389 COMMBBCIAL AIRCRAFT COBALT ISOTOPES Desiqn objectives for subsonic, transonic and Aircraft altimeter containinq X ray source supersonic civil transport flyinq N71-16993 characteristics based on HIL-P-8785, considerinq COCKPITS aircraft control Aerospace Recommended Practice criteria for fliqht r SAE-ARP-842BI A71-19645 deck crew escape systems applicable to all Commercial aviation stratospheric water vapor commercial aircraft propulsion systems, desiqn injections influence on radiation budget, ozone. speeds and payloads polar niqht cloudiness and potential climatic [ SAE-RRP-808Al A71-19646 effects COLLISIOII AVOIDANCB A71-21822 Aircraft midair collision avoidance, discussing Problems facinq local air transport industry, Elimination Range Zero system operation communities, and qoverument agencies procedures and cost N71-18078 1171-19079 US commercial aircraft export strateqy and Three-phase time-ordered functional organization recommendations for financinq and expansion for qround based collision avoidance, discussinq N71-18087 information flow, display capability and dynamic Hidair collision hazards, incidents, and simulation model recommendations for safe aircraft operations rRIAA PRPER 71-2401 A71-19716 N71-18103 Airline collision avoidance system test and Computerized simulation of alternate loqistics for evaluation proqram, considerinq ranqe, rate and overhaul and expensive parts inventory altitude accuracy, communications reliability, procedures of commerical airlines synchroiization and system integration with air N71-18118 traffic control Parametric enqine study for Hach 0.98 commercial A71-21167 air transport with supercritical winq Aircraft collision avoidance dynamical system. NASA-TH-X-52961 1 N71-18733 determininq barriers between possible capture COUUUIICATION CABLES reqions by optimal control problem solution Surge voltaqes produced by transient currents on A71-21322 siqnal conductors in shielded cables Proceedinqs and recommendations of conference on A71-19946 prevention of midair collisions COUMUUICATIOU SATBLLITES r NTSB-AAS-70-2 1 N71-19043 passive airborne computer auqmented aircraft COMBWSTION CEAMBBRS antenna pointing control system for Pressure wave distortion effects on combustor communication satellites tracking acoustic mode instability based on model with [AIAA PAPER 71-2331 A71-19710 burninq'rate related to Reynolds number European aerospace and electronic equipment A71-19906 industrial cooperation for air traffic control

1-14 SUBJECT IlDEI COEPUTEBIZED SIEULATIOII

and commnnication satellites Thermal pump-compressor for converting solar N71-17181 energv COUPASSES [NASA-CASE-XLA-003771 N71-17610 Aircraft radio compass navigation errors due to COEPUTEB DESIGII loop antenna inciinations-during maneuvering Compnter display channel for en ronte air traffic 171-20787 control flexible real time data processinq and COEPOIEST BELIABILITT display snbsystem P-104D aircraft side stick control system desiqn r AIAA PAPER 71-247 J 1171-19721 and function. curriculum manenvers and component Associative digital processor with associative re1 iability memory for hiqh speed ATC data processing. A71-19092 discussing design and operation COEWSITE UATEBIALS A71-19997 Lightning protection for dielectric composites. COEPUTEB GBAPUICS analyzing damage from shock waves. vaporization Airplane wing high lift and flap designs by pressure, magnetic forces and burning interactive compnter graphics system A71-19942 [AIAA PAPER 71-2271 A71-19705 Cost aspects of carbon fiber reinforced composites TWO dimensional aircraft autonatic landing motions in aircraft strnctures, sngqesting increased control processes by simulation without use of aviation market for carbon fiber moving cockpit simulator FPLASTICS INST. PAPER 463 A71-20929 A71-20066 Tetra-Core structnral composite material. COEPUTEB PBOGBAES discussing fabrication techniqnes, test results. Strnctures electromagnetic scattering and potential and applications multipath transmission effects on aircraft 1171-21225 instrument landing system localizer signals, Plow characteristics of wire-form and usinq computer proqram laminate-form porous materials A71-18831 [ RASA-TE-X-21111 U7 1- 17130 Aerospace Recommended Practice for qas turbine COUPOSITB STRUCTURES engine steady state performance presentation for Composite plastic aircraft structures lightning digital computer programs, describing enqine protection. considering hazard to composite type, operating and control characteristics materials and use of metal filled or plasma [ SAE-ABP-681B J A71-19647 sprayed coatinqs and metal foil coverings Vortex-lattice FORTRAN program for estimating 171-19943 subsonic aerodynamic characteristics of complex COIIPBBSSIBLE BOUSDABY LATER planf orms Cross flow profiles for compressible turbulent [ NASA-TR-E-6142] 1171-17424 boundary layers with and withont flow reversal System description of field test model of ARTS 2 via hodosrauh-~ models familr modular alphanumeric nontracking ATC system A71-22033 N71-18815 COUPBBSSIBLE PLOU COIIPUTEB STORAGE DETICES Prandtl-Glanert pressnre distribution rnle Associative digital processor with associative improvement subsonic planar flow memory for hiqh speed ATC data processing. A71-20312 discnssing desiqn and operation COUPBBSSIBLE FLUIDS A71-19997 Compressible circular jet instabilities with COEPUTEB TECEIIQOES respect to spatially qrowinq disturbances Computer aided automatic fault data logginq, [ DLR-PB-70-51 J N71- 18471 classification, analysis and reporting methods CO!LPEESSIOI PATES in inteorated ITC svstem Plane compression waves propagation into constant 1171-19556 state nonviscons flnid. considering shock Computer calculation of hiqh Reynolds number formation of pressnre pnlses and overpressure as viscous and inviscid flow over arbitrary shaped function of time two dimensional bodies and airfoils A71-19961 A71-20313 COUPBESSOR BLADES Performance test methods and equipment for Low aspect ratio compressor blade cascade aircraft avionics and weapons systems. performance at blade span center, discnssinq discussing computer integration with radar and pressure loss, angle of attack and staggering phototheodolite range instrumentation system A71-20624 A71-21660 hxial compressor blades snrface finish and fatigue COEPUTEBIZED DESIGU strength restoration by vibrational tumbling Computerized transonic airfoil design from A71-20843 _-YLedetersined supercritical velocity Probabilistic estimate of aerodynamic imbalance of distribution, obtaininq eqnivalent aircraft gas turbine rotors due to production incompressible flow throngh streamline and errors in compressor blade angle potential line network transformation A71-22045 A71-20304 Axial-radial and radial compressor stage optimum nultistaqe gas turbine desiqn optimization. wing exit blade angle, considering flow rate control parameter and component analysis with comput'er by variable pitch nozzle guide vanes calculations A71-22049 B71-21267 Low speed boundary layer separation on compressor Compnterized optimization of thermal resistant gas blades of varying aspect ratios turbine blades [ ARC-CP-11031 N71-17108 N71-17400 COEPBESSOB BFFICIBlCI COEPUTEEIZED SIUULATIOl Jet propnlsion optimization by exergy and anergy Two dimensional aircraft automatic landing motions for minimum total cost flux by varying unit control processes by simnlation without use of compressor pressure ratio moving cockpit simnlator A71-21300 1171-20066 COUPBBSSOB ROTORS Ean-machine considerations in all-weather low- Transonic compressor rotors blade camberline shape altitnde navigation system desiqn, discnssing optimization by various tip diffusion computer generation of roll command guidance. factor-ratio combinations visnal display and pilot modeling 1171-20200 A71-20344 Design and tests of PTP-48 single rotor compressor Airport pollution disperdion modeling, simnlatinq engine effect on snrroundinq areas for abatement I AD-7156261 N71-18801 strategies calculation COEPRESSOBS 871-21824 Equation derived for operation of turboprop engine Computerized simulation of alternate logistics for with high pressure compressor controlling gas overhaul and expensive parts inventory temperatnre at turbine front procedures of commerical airlines A71-20831 871-18118 COIICORDE AIRCRAFT SUBJECT IUDEI

Coefficient determination of fliqht dynamics COUTBOL EQUIPIEUT multivariable systems by means of computer Nonlinear control systems with transport lag, simulated aircraft dynamic models obtaining parameter plane equations for r DLR-FB-70-30 1 N71-18586 stability analysis COUCORDE AIRCRAFT A71-20369 Concorde aircraft Olympus 593 two-spool turbojet COUTBOL SIIULATIOU enqine, discussinq variable nozzle and intake Aircraft electronic control systems, considering assembly, afterburner and control system hydraulic servocontrol, force simulation and A71-19081 reliability models COUES A71-20064 Viscosity effects on three dimensional supersonic COUTROL STABILITY flow around circular half cones on flat plate, Nonlinear control systems with transport laq, examininq turbulent boundary layer separation obtaininq parameter plane equations for A71-19743 stability analysis Larqe anqle cones supersonic aerodynamic and wake A71-20369 Characteristics at low Reynolds numbers, COIITBOL SUPPACES includinq model support interference effects mathematical models for control surface wings in rAIA4 PAPER 71-2641 1171-21990 subsonic unsteady flow COIFEBEUCES r ONERA-TP-889 1 U71-18473 Fliqht tests - Conference, Beverly Rills. COITB~L TBBOBY September 1970 Development proqram for multiple access real time A71-19076 tactical information distribution System. Liqhtninq and static electricity - Conference, San designing and constructinq tactical air control Dieqo, December 1970 system test facility A71-19926 [AIAA PAPER 71-2431 A71-19718 Boundary value problems and applications in fluid Linear multichannel control systems for supersonic and qas mechanics - Conference, Razau, U.S.S.R.. aerospace vehicles orbiting-in earth atmosphere Hay 1969 r AD-7147961 N71-17747 A71-20076 COUTR~LLABILITY Electronics - Conference. Chicaqo. December 1970 Air cushion vehicle technology, considerinq A71-20401 economics, propulsion, structures, Aircraft and environment - Conference. New York, controllability, flexible skirt systems and R February 1971, Part 1 and D A71-21811 [SAE PAPER 7101831 A71-21713 Advanced coolinq systems and heat resistant COIIVBCTITE EBAT TBAUSPEB materials for turbine blades of hiqh temperature Convective heat transfer characteristics of H2 and aeronautical qas turbine engines H2-P2 lifting entry vehicles N71-17131 r AGARD-CP-73-711 N71-17372 TNASA-TU-X-16911 International conference on rain erosion and COIVKBGEIT-DIVEBGEUT UOZZLES associated phenomena Transonic gas flows in axisymmetric small throat r~~-7151001 U71-17906 curvature radius Lava1 nozzle with appreciable Proceedinqs and recommendations of conference on flow parameters variation in transverse prevention of midair collisions direction r NTSB-AAS-70-2 J N71-1904 3 A71-19732 Schedule of AGARD conferences for 1971. and COOLIIG summaries of 1970 AGARD publications Draw-tbrouqh coolinq of electronic equipment in r AGARD-BUL-71/1 J N71-19114 subsonic and supersonic commercial let COIGBESS transports, discussinq internal circulation Conqressional hearinqs on Boeinq 727 use of system desiqn Yashinqton National Airport SAE-AIR-64A J A71-19642 N71-17697 COOLIUG SYSTEMS COUICAL BODIES Optimal weight of aerodynamic heat protection Incompressible hypersonic laminar boundary layer layers of stressed skin and optimal efficiency flow over sharp cone, based on asymptotic inner of coolinq svstem for hypersonic aircraft and outer flow field expansion compartments A71-19892 A71-20836 Unsteady boundary layers on sphere or cone moving Semiscale blowdown and emergency core cooling alonq axis, determininq skin friction anqular project test report response [IN-13931 N71-17190 A71-20098 Advanced cooling systems and heat resistant Aerodynamic characteristics of conical and Baterials for turbine blades of high temperature pyranidical configurations with various aeronautical gas turbine engines planforms by slender body theory, replacing r AGARD-CP-73-711 N71- 17372 three dimensional flow by two dimensional flow Imbact cooling meihod for turbine rotor blades A71-20776 N71-17397 Real qas effects on draq and trajectories of Heat transfer in liquid metal cooled gas turbine nonliftinq conical shell during mars atmospheric blades entry N71-17398 r NASA-TN-D-6240 J N71-18015 COOBDIUATBS Wake flow properties of conical bodies at Calculation of streamline coordinates for three SUPerSOniC speeds and various angles of attack dimensional turbulent boundary layer in vaneless INASA-TH-X-21391 1171-18480 diffuser COIICAL FLOW r ARC-R/H-3646 1 U71-18468 Flowfield isentropes in conical gas flow with CORIB'aS . sinqular current surfaces Thermal stress analysis of wind tunnel corners A7 1-21 864 IARC-CP- 1 117 J R71- 17100 COISTPOCTIOI IATKBILLS Three dimensional diffraction of sonic booms by Plastics and metals as construction materials in corners of structures aircraft, missile and rocket desiqn NASA-CR-17281 171-18029 A71-20044 COST AIALYSIS Tetra-Core structural composite material. Aircraft midair collision avoidance, discussing discussinq fabrication techniques, test results, Elimination Range Zero system operation potential and applications procedures and cost A71-21225 A71-19079 COITAIIIAITS Cost aspects of carbon fiber reinforced composites Gas turbine engines emission characteristics, in aircraft structures, suggesting increased discussing methods for pollutants reduction aviation market for carbon fiber A71-21820 [PLASTICS IUST. PAPER 461 A71-20929

A-16 SUBJECT IIDEI DEPEISE PROGUAI

COST REDUCTIO1 Potential flou past cylinder with sources and Jet propulsion optiuzation by exergy and anergy sinks singularities. deriving formulas for for minimum total cost flux by varying unit aerodynamic characteristics of infinite span compressor pressure ratio wings with boundary layer control A71-21300 1171-20777 Composite rocket cum hypersonic airbreathing CILIIDRICAL SEELLS propulsion reducing space exploration program Desiqn optimization for cylindrical shell cost subjected to reentry loads and heating A71-2 1301 871-18022 COUPLIIG Tro link approximation of Chaplygin fnnction by coupling to integral equations, applying to D ideal gas jet separation flou past symmetrical DAEPIIS arc Ribbed aluminnm panels airborne sound transmission A71-20084 loss, evaluatinq structural damping effects Uultiliuk approximation of Chaplygin function in A71-2 1431 subsonic and supersonic flou regions. derivinq DATA ACQOISITIOI coupling conditions relative to modified stream Bypervelocity wind tunnel data acquisition function at approximation nodes [ DLR-PB-7 0-4 4 3 11-11-17046 A71-20090 DATA COREELATIOI CRACKIIG (?RACTORIl6) Parachute ueight, configuration and strength Cyclic thermal cracking and fatigue analysis in correlations for tradeoffs and design large steam turbine rotors with three A71-18900 dimensional temperature and triaxial stress DATA PROCESSIIG computation Computer aided automatic fault data logging. lASIE PAPER 70-PIE-1 1 A71-20198 classification, analysis and reporting methods CEASE LAlDIlG in integrated ATC system Bent structure failure under pulse floor A71-19556 acceleration shocks, concerning aircraft seat Statistical methods for inventory boundary damage during crash landing determination and data compression in automatic A71-20747 processing of multispectral scanner remote Investiqating aircraft crash landing caused by sensor earth observations from aircraft and enqine failure and aircrew errors spacecraft IWTS8-AAR-70-171 1171-17063 [AIAP. PIPES 71-2341 171-19711 CRASEIS Associative digital processor uith associative Canse and result of transport aircraft accident memory for high speed ATC data processing, [ITSB-AAR-70-27] 117 1- 1751 z discussing design and operation CRITICAL EIPl!BIIERS A71-19997 Results of tuo-phase blowdoun experiments with Observational data characteristics analysis as straight tube test section and steam-water contributor to knowledqe and utilization of all mixtures atmospheric physical occurrences [ AECL-36641 1171-18161 All-21722 CRITICAL PRESSURE Data recordinqs and computer codes for airport Rotary inertia effect on critical dynamic pressure rapid transit access system study paraneters and supersonic flutter of in- plane [ PB-1950481 N71-16989 loaded sandwich plates Bypervelocity Mind tunnel data acquisition 871- 7 9387 x?-m-x-n4 1 n7i-17046 CROP GBOITB Weather outline generators for producing contours Airborne surveillance for environmental sround radar ueather clutter for all ueather air manaqement, discussing earth resources proqram, navigation aerial sensors for thermal water pollution, crop [ FAA-NA-70-62 ] ~71-i7527 disease. salinity and geological structure DATA REDUCTIO1 A71-19080 Observational data characteristics analysis as CROSS nov contributor to knowledqe and utilization of all Cross flor profiles for compressible turbulent atmospheric physical occurrences boundary layers with and without flow reversal A71-21722 via hodograph models family DATA TRAISIISSIOI A71-22033 Jet engine rotor strain and temperature data CRYOGEIIC EQUIPIElT transmission, examining special purpose Thermodvnamic properties of insnlated liquid telemeters desiqn methane fuselage tanks for supersonic cruise A71-19628 aircraft Data communication role in National Airspace f 11ASA-TII-D-6157] 171-17506 System, concerning radar and flight data COIOLOS CLOUDS acquisition, intersystem transfer and voice Spatial correlations between inside cumulus cloud control conditions and precipitation onset and intensity [AIAA PAPER 71-2481 A71-19722 for modification experiments from aircraft DC 10 AIECRAFT penetration measnrements DC-10 flight test proqram, discussing handling, A71-21450 takeoff and landing. and flutter, stall and CI-990 AIRCRAFT stability characteristics Photometer observations of auroras from CV-990 171-1 9085 aircraft DC 9 AIRCRAFT [ NASA-CR- 1168551 n7i-ia996 Investigation of Douglas DC-9 accident at CYCLIC LOADS Karlinqen. Texas, on 11 Jan. 1970 Cyclic thermal cracking and fatigue analysis in NTSB-AAR-70-281 1171-174-16 larqe steam turbine rotors with three DEBRIS dimensional temperature and triaxial stress Ingestion of debris into aircraft enqine inlets computation durinq takeoff [ASUE PAPER 70-PWE-l] A71-20198 [ ARC-CP-1114 ] n7i-17084 CYCLOEEIAlE DECOUPLIIG Kinetics of catalytic dehydrogenation of Pliqht testinq devices for discharqinq static methylcyclohexane at 600. 650, and 700 deg P and electricity from aircraft without production of 5 atm pressure radio interference f AD-7159261 1171-18729 1171-18114 CILIIDRICAL BODIES DEPEISE PROGRAI Blunt cylinder uith small thread in anomalous Euman role in Aerospace Defense Command seeded flou in hypersonic rind tunnels, navigation. discussing Airborne Warninq And observinq separated shock wave distortion Control System and navigational aspects of ADC A7 1- 18924 mission

A-17 DEFLECTIOH SUBJECT IUDEX

A71-20346 [ ARC-R/B-3629] N71-17102 DEFLECTIOII DIRECT POWER GEIERATOES Helicopter application studies of variable Thermal pump-compressor for converting solar deflection thruster jet flaps energy [ AD-7150711 N71-17907 [ N A S A-C A SE- XIA-0 0 377 3 N71-17610 DEATDROGEMATION DIRECTIOUAL AUTEUUAS Kinetics of catalytic dehydrogenation of Ultrahigh frequency directional spiral aircraft methylcyclohexane at 600, 650, and 700 deg P and antennas for spacecraft communication 5 atm pressure [ RAE-TR-70062 3 N71-18519 [ AD-7159261 N71-18729 DIRECTIOIAL COITROL DEICIUG In-flight determination of lateral-directional Runway deicing methods, discussinq spreading of dynamics for landing approach chemicals by qround vehicles and aircraft [ AD-7 15317 ] N71-17792 A71-19425 DIRICHLIT PROBLBII DELTA llIIGS Dirichlet solution for thin airfoil problems viscous qas flow interaction on delta wing and [NASA-TT-F-13471 J N71-17468 oblique airfoil at aach number of infinity DISKS (SHAPES) A71-19739 Sphere and disk draq measurements for Reynolds Vortex breakdown on slender sharp edqed and numbers from 5 to 100,000, examining forces. modified delta winqs with varying sweep anqles moments, flow visualization. unsteady modes and investiqated in wind tunnel using schlieren constant acceleration system for flow visualization A71-19893 [AIAA PAPER 69-7781 A71-22028 DISORIEUTATIOI Aerodynamic coefficients, pressure, load and force Incidence and costs of orientation-error accidents distributions on cambered delta winqs in Army OH-1 helicopter operations [ ARC-CP-1129 J N71-17112 [AD-7151071 N71-17854 Aerodynamic heatinq and structural analyses for DISPLAY DEVICES radiatively cooled delta wing of hypersonic Fiber optic faceplates for contrast enhancement aircraft under hiqh ambient light conditions for I NASA-TN-D-6138 1 N71-18025 commercial and military cockpits, eliminating Wall pressure and heat transfer distribution on ghost, halo and direct sunliqht problems delta winqs in rarefied hypersonic flow A71-19175 [ REPT-70-91 N71-18423 Aircraft visual warninq indicating system, DEBAHD (ECOMOBICS) outlininq desiqn criteria, color and briqhtness Cost aspects of carbon fiber reinforced composites recommendations in aircraft structures, suqgestinq increased SAE-ARP-1088 J A71-19644 aviation market for carbon fiber Three-phase time-ordered functional organization rPLASTICS INST. PAPER 46) A71-20929 for qround based collision avoidance, discussing DEUSITI BEISUREBENT information flow, display capability and dynamic Velocity and density measurements in hypervelocity simulation model ballistic projectile turbulent wakes, usinq hot [AIAA PAPER 71-2401 A71-19716 film anemometers Computer display channel for en route air traffic IAIAA PAPER 68-701 1 A71-19891 control flexible real time data processing and Laser Doppler velocimetric technique for display subsystem supersonic flow particle trajectory and density rAIA.4 PAPER 71-2471 1171-19721 measurements, noting particle laq Aircraft naviqation system requiring computer and IAIAA PAPER 71-2871 1171-22010 display for approach quidance to circular orbit DIELECTRICS over fixed ground area Liqhtninq protection for dielectric composites. [AIAA PAPER 69-9861 A71-20305 analyzinq damaqe from shock waves, vaporization Manned aircraft crew lonq ranqe navigation, pressure, maqnetic forces and burninq discussinq sensor, information processing and A71-19942 display systems for future commercial and DIES military missions Closed die forqinqs for aircraft industry, A71-20343 discussinq technoloqy, tolerances, materials and Investiqation of anqle of attack information costs display for pilots to increase efficiency of A71-20075 qeneral aviation aircraft operation DIESEL EUGINES r NASA-TN-D-6210 3 N71-18442 Turbocharqed diesel enqine precompressed inlet air Development and characteristics of frequency coolinq by evaporation cooling, considerinq separated display devices for aircraft control water injection effects on centrifuqal r AD-7 154583 N71-18739 compressor selection of scannino~. systems for aircraft thermal A71-20781 viewers DIFFEREUTIAL EQUATIONS N71-19220 Coefficient determination of fliqht dynamics DISTANCE MEASURING EQUIPBENT multivariable systems by means of computer 0.5. domestic ATC airspace enroute and terminal simulated aircraft dynamic models area navigation system effects on pilot IDLR-PB-70-30 1 N71-18586 workload, projecting future FAA requirements DIGITAL COOPOTERS A71-20347 Navy avionic modular multiprocessinq diqital VOR/DME qround station oriented aircraft area computer operatinq system reliability. comparinq naviqation horizontal guidance capability, totally software and partly hardware approaches discussinq diqital input/output fliqht control A71-18833 A71-21166 Associative diqital processor with associative DISTORTIOII memory for hiqh speed ATC data processing, Pressure wave distortion effects on combustor discussinq desiqn and operation acoustic mode instability based on model with 871- 19997 burninq rate related to Reynolds number A71-19906 DIGITAL DATA Alqorithm for diqital resolution of ranqe for DISTRICT OF COLUBBIA V/STOL aircraft Congressional hearinqs on Boeinq 727 use of NASA-TN-D-62321 N71-18566 Yashinqton National Airport DIGITAL FILTERS N71-17697 Strapdown inertial naviqator aliqument bv diqital DOPPLER EFFECT filterinq techniques, discussinq application to Laser Doppler velocimetric technique for aircraft and spacecraft supersonic flow particle trajectory and density A71-21170 measurements, notinq particle lag DIRECT LIFT CONTROLS [ AIAA PAPER 71-2871 A 7 1- 220 10 Aircraft pilot direct lift control for aircraft DRAG IEASUREIIEUT landinq ahd reducinq gust load effects Sphere and disk draq measurements for Reynolds

A-18 SUBJECT IIDEX ELECTRIC POTEITIAL

numbers from 5 to 100.000. examining forces, management, discussing earth resources program, moments. flow visualization. unsteady modes and aerial sensors for thermal water pollution. crop constant acceleration disease, salinity and geological structure 1171-19893 A71- 19080 Lou speed wind tunnel stability tests of small ECOlOIIC AIALYSIS quide surface, slotted solid. ring slot, cross Economic analysis of airport construction in north and streamer decelerators, considerinq central Texas reqion, emphasizing employment and parachutes and drag measurement dollar value of purchases A71-20310 871-18099 Airfoil profile draq measnrements. correlating BCOIOIIC FACTORS fall scale flight tests and scale model tests in Economic and safety factors of nuclear powered transonic and high Reynolds number wind tunnels surface vehicles and aircrafts in transoceanic [AIAA PAPER 71-289] A71-22012 commerce Aerodynamic drag measurements on VC-10 aircraft r IASA-TI-I-52963 J 871-18628 subsonic wind tunnel models ECOlOlICS r ARC-CP-1125] 1171-17118 Air cushion vehicle technology, considerinq DROP SIZE economics, propulsion. structures, Wind tunnel photography for determining uater controllability, flexible skirt systems and R droplet size in breakup of uater iets and D r NASA-CR-~I~~~O3 N71-18962 rSAE PAPER 7101833 171-21713 DUCTED PA1 E16IlES EJECTORS Annular diffuser and combustor assembly in full Performance of auxiliary inlet ejector nozzle with scale duct burner for supersonic turbofan enqine floating inlet doors and floating single hinge [AASA-TU-D-6163] n71-1~88~ trailing edge flaps DUCTED PLOP NASA-TE- I-2173 ] N71-17554 Larqe aspect ratio rectanqnlar duct uith Auxiliary inlet ejector nozzle desiqned for nonuniform surface texture. investiqatinq supersonic cruise aircraft turbulent flou. maximum velocity positions and [ NASA-TI-X-2182] N71-18863 zero shear stress ELASTIC DEPORIATIOI A71-18772 Elastic, inertial and aerodynamic forces Qptimal lining impedance for jet enqine inlet aerwlastic triangle. examining lift changes dne duct. yieldinq discrete frequency. flow relocity to aircraft structnre deformation, dynamic and qeometry on basis of minimum radiated power flight stability and space shuttle development A71-2 1661 prob1 em s DYIAIIC LOADS A71-20063 Dynamic loads on P-104G aircraft landing gears Elastic swept wing subsonic aerodynamic [PB-82-1969] 871- 18532 characteristics, taking into account aerodynamic DYlAIIIC HODELS load redistribution due to aerwlastic Three-phase time-ordered functional organization deformations for qronnd based collision avoidance, discussing A71-22035 information flow, display capability and dynamic ELASTIC PROPBRTIES simulation model Aircraft elastic mode control for turbulence [AIAA PAPEE 71-2401 1171-19716 /gost/ alleviation, noting riding qnality. Alternate reduced order particle dynamics model in structural fatigue life and peak loads aircraft mission analysis featuring A71-20301 iostantaneously variable saeed by time scale ILASTIC WAVES separation Pressure uave distortion effects on combustor 171-1 991 3 acoustic mode instability based on model uith Centrifugal compressor vaneless diffuser. burninq rate related to Reynolds number estimating energy losses with hydrodynamic model 1171-19906 A7 1-2 1266 Plou lines construction in tu0 dimensional Aircraft collision avoidance dynamical system, supersonic flow reqion with rarefaction waves determining barriers between possible capture interaction from several disturbance sources reqions by optimal control problem solution A71-22052 171-21322 ELBCTEIC CELLS Coefficient determination of flight dynamics Silver zinc batteries and cells case cover multivariable systems by means of computer materials and sealing techniques for space simulated aircraft dynamic models missions I DLR-Fa-70-3iJJ 871-18586 1171-21097 DYlAlIC PEISSOBE Zinc-silver oxide batteries underwater and aerial Rotary inertia effect on critical dynamic pressure applications, designing medium high rate long parameters and supersonic flutter of in- plane life cells loaded sandwich plates A71-21102 1171-19887 ELBCTBIC CEAE6E DTlAIIC BESPOPSE Eelicopter charging mechanisms, considerinq engine Three degree of freedom gas bearing for wind and rain precipitation charging tunnel dynamic measurements, allowing models 1171-19933 simultaneous spin, pitch and yaw motions Supersonic aircraft electrification measurements IAIAA PAPER 71-279 J A71-22004 using projectile frictional charginq in ice-fog DYIAIIC STABILITY cloud Elastic, inertial and aerodynamic forces A71-19934 aeroelastic triangle. exaaining lift changes due ELBCCTBIC COBOPA to aircraft structure deformation, dynamic Plight testing devices for discharginq static flight stability and space shuttle development electricity from aircraft without production of problems radio interference A71-20063 n71-18114 Wind tunnel dynamic stability testing of ELBCTBIC CUPBIR unconventional aircraft configurations without Lightning current transfer tests of p-static sting support discharger for aircraft installations [AIAA PAPER 71-2763 A71-22001 A71-19935 Surge voltages produced by transient currents on signal conductors in shielded cables E A71-19946 EARTH ORBITS ILECTBIC IIOZOBS Linear multichannel control systems for snpersonic Describing angular position and velocity sensing aerospace vehicles orbiting in earth atmosphere apparatus [AD-7147961 871-17747 [ UASA-CASE-XGS-05680 3 871-17585 EAETB BESOBBCES PBOGBAI ELBCTBIC POTBICTIAL Airborne surveillance for environmental Surge voltages produced by transient currents on

1-19 ELECTRICAL FAULTS SUBJECT INDEX

siqnal conductors in shielded cables Electrostatic charginq noise measurement, A71-19946 reduction and flight test verification ELECTRICAL FAULTS A71-19937 measurements and analysis of liqhtninq-induced BllPLOYllENT voltaqes in aircraft electrical circuits Employment opportunities for economists and air [ NASI-CR-1744 1 N71-19122 transportation analysts with Civil Aeronautics ELECTRIPICATION Board Supersonic aircraft electrification measurements N71-17798 usinq projectile frictional charqinq in ice-foq Economic analysis of airport construction in north cloud central Texas reqion, emphasizing employment and A71-19934 dollar value of purchases N71-18099 ELECTROPOBMING Hypersonic low density wind tunnel includinq EBBRGY DISSIPATION auxiliary equipment for electroforminq and centrifuqal compressor vaneless diffuser, electroplatinq wind tunnel models estimatinq enerqv losses with hydrodynamic171-21266 model f BBBA-PB-Y-70-511 N71-18593 ELECTROLOIIINESCENCE Radial flou enerqy losses in rotating cylindrical Feasibility of electroluminescent panels and rotor cascade of inward-flow turbine wheel, tip liqhtinq for military helicopters to aid in deteroininq profile losses and exit blade anqle observation by other vehicles in formation A71-22044 f AD-7158511 N71- 18734 EBGIBE COBTEOL ELBCTRORAGNETIC FIELDS Concorde aircraft olympus 593 two-spool turbojet Supersonic wind tunnel electromagnetic balance ensi.De. discussinq variable nozzle and intake with superconductinq coils assembiy, afterburner and control system A71-20151 1171-19081 ELECTROCIAGRETIC NOISE Aerospace Recommended Practice for gas turbine Electrostatic charqinq noise measurement, enqine steaay state performance presentation for reduction and fliqht test verification diqital computer proqrams, describinq engine A71-19937 type. operating and control characteristics ELECTROIIAGIETIC SCATTERING [ SAE-ARP-68181 A71-19647 Structures electromaqnetic scatterinq and Experimental arranqement for delay times in multipatb transmission effects on aircraft propeller/rpm controller system A71-20832 instrument landinq system localizer signals, usinq computer proqram microelectronic circuits reliability in aircraft A71-18831 enqine control applications, discussinq testing ELECTROMAGNETIC SEIELDING and selection for severe temperature and Surqe voltaqes produced by transient currents on vibration environments siqnal conductors in shielded cables [SAE PAPER 700822) A71-21369 1171-19946 BIGIIE DESIGI ELBCTROMAGNETIC WAVE TRAISMISSIOI Soviet book on aircraft qas turbine and internal Schedule of AGARD conferences for 1971, and combustion enqines coverinq structural design summaries of 1970 AGAHD publications schemes, inlet devices, combustion chambers, IAGARD-BOL-71/1 1 N71-19114 materials, compressors, etc ELECTRON DENSITY PROFILES A71-20674 Nonequilibrium electron temperature, concentration combustor desiqn for minimum exhaust smoke and reflection in reentry boundary layers, emission from aircraft qas turbine let enqines. discussinq heat transfer and ionization enerqy considerinq air pollution diffusion A71-20867 I AIAA PAPER 69-82 J A71-19879 Multistaqe qas turbine desiqn optimization, Using ELECTBOB BIERGY parameter and component analysis with cemputer Nonequilibrium electron temperature, coucentration calculations and reflection in reentry boundary layers, A71-2 1267 discussinq heat transfer and ionization energy Desiqn point selection on fan characteristic curve diffusion of turbofan enqines, discussing bypass ratio [AIAI PAPER 69-82] A71-19879 effect on specific impulse, flight velocity and ELECTRONIC CONTROL turbine inlet temperature Aircraft electronic control systems, considerinq A71- 22042 hydraulic servocontrol, force simulation and Desion of qas turbine enqines for hiqh operatinq reliability models temperature A71-20064 N71-17386 ELECTRONIC EQUIPIIEBT operational desiqn criteria for gas turbine Avionics for qliders and tourinq aircraft, enqines considerinq safetv and VHP radio eauioment.. N71-17402 871-20684 Computer proqram for desiqn and analysis of V/STOL Avionics for qliders and tourinq aircraft, tip turbine fans surveyinq available electronic equipment for r NASA-TN-D-61611 1171-17641 1971 BIGIIE FAILUEE 171-21768 Equivalent test results, studying damaging factors BLBCTBONIC EQOIPHBNT TESTS in aircraft enqine compared with reqular tests Microelectronic circuits reliability in aircraft 1171-21115 enqine control applications, discussinq testinq Investiqatinq aircraft crash landinq caused by and selection for severe temperature and enqine failure and aircrew errors vibration environments r NTSB-AAR-70-171 N71-17063 [SAE PAPER 7008221 A71-21369 BBGIIE IBLETS BLECTEONICS Mathematical model of nonstationary intake and Electronics - Conference, Chicaqo, December 1970 exhaust gas motion in two cycle internal A71-2040 1 combustion engine cylinders BLICTBOPLATING A71-20780 Hypersonic low density wind tunnel includinq Turbocbarqed diesel enqine precompressed inlet air auxiliary equipment for electroforming and cooling by evaporation CoOlinq, COnSiderinq electroplatinq wind tunnel models uater injection effects on centrifuqal I BREW-FB-Y-70-511 N71- 18593 compressor ELICTROSTATIC CHARGE A71-20781 Static discharqe hazards for aircraft, discussinq Air temperature effects on internal combustion causes for static charqe build-up. danqers and engines intake process, using similarity theory precautionary methods durinq refuelinq A71-20782 operations Inaestion of debris into aircraft engine inlets A71-19424 durinq takeoff [ ARC-CP-I 114 1 1171-17084

A-20 SUBJECT IIDEI BIPERIHIITAL DES161 msxm IOISE underwater wing with jet flap, solving equations SST noise suppression research, discussing engine of motion for thin foil with let emerqent from noise suppressor conceptual designs and test trailing eage results with installed devices A71-20086 171-20302 Aircraft optimum minimum noise takeoff profile, noise nuisance value index /noise pollution solving by equations of motion system for jet level/, considering aircraft and motor vehicle aircraft noise surveys and tradeoff of intensity against A71-20779 duration llonlinear aerodynamic moment system for A71-20802 nonaxisymmtric bodies free flight motion Development of acoustic lining for turbofan analysis, taking into account interactions nacelle modification to minimize fan compressor excluded in classical treatment noise radiation [AIAA PAPER 71-275 J A71-22000 [ MASA-CE-1712 J U71-17591 ERROR AIALTSIS Flightworthy nacelle development to minimize fan Solid particle impurity effects on hypersonic compressor noise radiation - Vol. 4 shock tobe flow. determining error in blunt body [UASA-CR-1714 J 1171-17668 measurements Jet aircraft noise reduction near airports 171-18916 171-18079 Aircraft systems assembly methods. discussing EIGIIE PARTS rigidity effects on error redistribution in Gas dynamic test stand for cyclic thermal load external and internal force field application testinq of gas turbine engine materials and A71-20792 components at variable heating and cooling rates Error analysis for pressure measurements on and mechanical loads blowdown supersonic wind tunnel models A71-208 39 [ UPL-AERO-1306 1 171-17081 Plasma arc welding of jet engine components of Ti ESCAPE STSTXHS and Hi alloys. comparing to gas tungsten arc and Aerospace Recommended Practice criteria for flight electron beam processes deck crew escape systems applicable to all A71-21684 commercial aircraft propulsion systems, design 1116111 TESTS speeds and payloads Equivalent test results, studying damaging factors SAE-AEP-808A J A71-19646 in aircraft enqine compared with regular tests EUROPE A71-21115 Buropean subsonic, supersonic, transonic, Effects of specific spee0 311 experimental hypervelocity and low density wind tunnel performance of radial inflow turbine characteristics [MASA-TU-D-6182 J 171-17354 1171-17099 Acoustic attenuation determined experimentally Air transport supply on scheduled services in durinq enqine ground tests of XB-70 airplane and Europe-Mediterranean and Southeast Asia regions comparison with predictions [ EEPT-1970/1-E J 1171-18112 [ 1151-TU-I-2223 J 171-17951 European hypersonic wind tunnels for testing Effects of turbojet engine unstart on engine hypersonic transport aircraft, and space shuttle operation and characteristics of stall aerodynamic configurations propagation through compressor and inlet sTstem 1171-18452 iiii3&i-'i;-z-2;92 j 871-18138 BIAPORATIIE COOL116 ElTEAIIIIEYT Turbocharged diesel engine precompressed inlet air Entrainment coefficient used for compuration of exdinq by evaporation =oolizq:. c?rsi

A-21 BITBRUAL STORBS SUBJECT IUDBI

BITBBIAL STORBS A71-19175 Riqh speed aircraft external store separation PIBBR STBBIGTE testinq and prediction techniques, considerinq Parachute weight, configuration and strength flow field survey, dynamically similar drop correlations for tradeoffs and design models and captive trajectory methods A71-18900 ~AIAA PAPER 71-2941 A71-22014 PIGETBR AIRCRAFT External store surface pressure distributions F-15 air superiority fighter, describing military during captive fliqht aboard F-4B aircraft, requirements, proqram management and procedures considerinq carryinq aircraft effects on flow in terms of speed, maneuverability, acceleration field about airborne ordnance and weaponry rAIAA PAPER 71-2951 A71-22015 A71-19078 Aigh performance fighter aircraft engine pressure ratio and turbine inlet temperature measurement. F usinq fluidic sensors P-104 AIRCRAFT A71-20586 F-104D aircraft side stick control system desiqn Transonic and supersonic dynamic stability and function, curriculum maneuvers and component characteristics of variable sweep wing tactical reliability fiqhter aircraft A71-19092 [ NASA-TR-X-2 163 1 N71-17425 Dynamic loads on F-104G aircraft landinq gears PILAMBIT WIIDIUG [ FB-82-19691 N71-18532 Filament winding manufacturing methods usinq P-15 AIRCRAFT unidirectional glass reinforcements for design F-15 air superiority fiqhter, describinq military and fabrication of aircraft wing structure requirements, proqram management and procedures rSnE PAPER Etl-70-4063 A71-20546 in terms of speed, maneuverability, acceleration Tetra-Core structural composite material, and weaponry discussinq fabrication techniques, test results, A71-19078 potential and applications P-4 AIRCRAFT A71-21225 USAP P-4E Stall/Near Stall Investiqation, FILM COOLIUG discussinq testinq requirements, fighter Performance prediction for turbine blade film aircraft improvement, spin avoidance and hiqh coolinq with injection through holes anqle of attack limitations r NISA-CR- 1163761 N71-17388 A71-19095 Film coolinq of qas turbine blades by air Late model P-4 air superiority aircraft and injection throuqh holes electronic fliqht control systems protection N71-17394 aqainst liqhtninq discharqes damaqe to electric Effective heat transfer coefficients in film and electronic systems coolinq systems of qas turbine surfaces A71-19940 N71-17395 External store surface pressure distributions Technoloqical aspects of film coolinq for blades durinq captive fliqht aboard P-4B aircraft, in hiqh temperature gas turbines considerinq carryinq aircraft effects on flow N71-17404 field about airborne ordnance PIIITB DIPPBRBUCB TEBORT rAIAA PAPER 71-2951 A71-22015 Soviet book ou qas flow past blunt bodies, Part 1. PABRICATIOI Plow analysis and calculation methods covering Filament windinq manufacturinq methods usinq finite difference theory, algorithms, etcA71-19049 unidirectional qlass reinforcements for desiqn and fabrication of aircraft winq structure FIUITB ELBMEUT HBTHOD rSNE PAPER EM-70-4061 A71-20546 Finite element analysis of structures in plastic FAILURE &UALlSIS range Computer aided automatic fault data logging, r NASA-CR-16491 U71-19276 classification, analysis and reportinq methods PIIUBD BODIES in inteqrated ATC system Resonance instability of finned bodies with 1171-19556 nonlinear aerodynamic characteristics FAILURE MODES rAD-71511o-J N71-17733 Random errors in aluminum alloy fatique tests and Fins failure modes Free fliqht measurement of aerodynamic r ARC-CP- 1123 1 N71-17330 coefficients on fixed cruciform fin stabilized PASTBIERS bombs, determininq aerodynamic forces and Ultrasonic wrench for applyinq vibratory enerqy to moments dependence on angular velocity mechanical fasteners components r NASA-CASE-tlFS-20586 1 N71-17686 A71-19872 FATIGUE (HATBRIALS) FIRE FIGBTIUG Cyclic thermal crackinq and fatique analysis in Surveyinq crash fire and rescue equipment at North larqe steam turbine rotors with three American and Canadian airports dimensional temperature and triaxial stress N71-18101 computation PIRB PREVEIITIOU r AStlE PAPER 70-PWR-1 1 871-20198 Carqo aircraft crew safety and survival, FATIGUE LIFE describinq restraint, escape, fliqht deck Aluminum alloy stress cycles and fatique life of interior doors, fire and smoke hazards and airframe materials personnel environmental protection rP~-m-i969i N71-17524 [ SAE-ARP- 1139 1 A71-19643 FATIGOB TBSTS Jet enqine combustion chamber burn-throuqh fire Random errors in aluminum alloy fatique tests and and methods for controllinq damaqe N71-17483 failure modes .r ~----PIA-RD-70-68-~ 1 [ARC-CP-13231 N71-17330 FIITURBS PBBDBACK COUTROL Airport liqhtinq facilities in Japan, considerinq Improved feedback control of distributed parameter fixtures. marker and obstruction liqhts and systems for lunar landinq vehicle simulator apron floodliqht [NASA-CR-1164821 N71-17345 A71-20355 tlinimizinq performance criterion to analyze FLAPS (COUTROL SORPACBS) ability of automatically controlled aircraft to aulticomponent plane flap mechanism with maintain accurate fliqht path control durinq transmission angles diverqinq minimally from landinq approach ninety deqrees, discussing synthesis by least r NASA-TN-D-6230 1 N71- 1876 1 squares method FIBER OPTICS A71-19361 Fiber optic faceplates for contrast enhancement FLASK POIIT under hiqh ambient liqht conditions for Liquid fuel pool ignition at superflash and commercial and military cockpits, eliminating subflash temperatures involving adjacent heat qbost, halo and direct sunliqht problems source. cross wind and fluid motion

A-22 SUBJECT IIDBX PLIGET TESTS

A71-19245 PLIGET LIECEA11ICS FLAT PLATES Glider flight mechanics for turninq fliqht. Seaplane step /flat plate/ ricochet off ideal discussing relationships betueen turning radius, incompressible fluid surface, determining free flight speed, sink rate and aerodynamic surface shape by accounting for trailing characteristics vortices effects A71-21770 A71-19355 PLIGET OPTILIIZATIOB Viscosity effects on three dimensional supersonic Supersonic airplane minimum time turns at constant flow around circular half cones on flat plate. altitude. determining thrust, bank anqle and examininq turbulent boundary layer separation angle of attack proqrams uith optimal control 1171-19743 theory Reavy fluid flow past partially cavitating flat A71-22032 plate with cavity closed by fictitious plate, PLISUT PATES considerinq lifting force under qravity Aircraft naviqation system requiring computer and 171-20087 display for approach guidance to circular orbit Lou speed uiud tunnel pressure and audio frequencv over fixed ground area resonance measurements on circular cylinders and [ AIAA PAPER 69-986 J 171-20305 thin flat plates Supersonic airplane miuiium tine turns at constant INPL-AERO-1311] N71-17089 altitude. determining thrust, bank angle and Turbulent wakes of flat and rotationally angle of attack proqrams uith optimal control symmetrical bodies notinq uidth development theory N71-18472 A7 1-220 32 Sound field effects on flat plate heat transfer in PLIGET SAPRY turbulent boundarv laver Aerospace Recommended Practice criteria for flight [ REPT-70-8 1 deck crew escape systems applicable to all PLISET CEABACTERISTICS commercial aircraft propulsion systems. desiqn Desiqn objectives for subsonic, transonic and speeds and payloads supersonic civil transport flyinq [ SAE-ARP-808A] A71-19646 characteristics based on BIL-P-8785. considcrina Surveying air traffic controller occupation and aircraft control development of performance objectives rSAE-ARP-842Bl 171-19645 N71- 18105 Turbulent/total *fliqht mile ratio in hiqh altitude Investigating statistics of aircraft accidents by clear air turbulence /EICAT,/ program region and operator 871-20314 fREPT-1970/10-E] N71-18115 Plight testinq of Diamant 18 glider, discussinq PLIGET SIBULATIOB aircraft behavior at lor and high fliqht speed, Ground based flight simulation as engineering aid stall, spin, stability and control in aircraft design for evaluation of aircraft characteristics. design and construction dynamics. handlinq qualities and control system A71-20686 characteristics over entire flight envelope Noise reduction at source. fliaht methods A71-20309 adjustments and airport-compatible land use for Riqh turbulent flow simulation in hypervelocity jet noise abatement uind tunnel for reentry vehicles operational A7l-21815 testing. discussing nozzle gas dynamic and Land use strategies and noise reduction by sonrce mechanical design control and flight procedures for noise exposed fAIAA PAPER 71-2531 A71-21982 areas minimization PLIGET SILIULIITORS A71-21818 Functional reguirements for qround-based trainers, Pliqht time, path and fuel consniption in climb at helicopter response characteristics constant radius turn. variable or constant [ AD-7149541 N71- 180 18 velocity and constant enqine pouer, derivinq Peasibility of visual tracking to determine effect approximate simple formnlas of lag in simulated aircraft dynanics A71-22050 [IAB-R-479] N71-18838 Synoptic meteorological conditions for clear air PLIGET TESTS turbulence and turbulence effects on aircraft Flight tests - Conference, Beverly Rills, flight characteristics September 1970 r DLR-PR-70-29 I 1171-17145 A71-19076 Plight characteristics of jet-flap STOL transport Naval aircraft testing, discussinq ueapons aircraft during approach and landing systems. funding commitments. outfittinq r 1(&,SA-T?t-D-62253 N71-17U33 schedules, tire frames, contracts and aanageaent PLI6ET COlTEOL problems ATC automated systems, discnssing National A71-19077 Airspace System En Route Stage A and Advanced ARAVA SML aircraft. describing payloads, Radar Terminal System configuration, design flight testing, stability [AIAA PAPER 71-2441 A7 1-1 9719 and landing characteristics Late model P-4 air superiority aircraft and 171-19082 electronic fliqht control systems protection DC-10 fliqht test program, discussing handling, against liqhtning discharges damage to electric takeoff and landinq, and flutter, stall and and electronic systems stability characteristics 1171-19940 A71- 19085 VOR/DRE ground station oriented aircraft area Eeiqht velocity /E-V/ fliqht testing. giving navigation horizontal guidance capability, results from OH-58A Kioua and AH-1G Huey Cobra discussing diqital input/output flight control helicopters A71-21166 A71-19093 Functional requirements for qround-based trainers. DSAP P-&E Stall/Near Stall Investiqation, helicopter response characteristics discussing testing requirements. fighter f AD-7149541 N71-18018 aircraft improvement, spin avoidance and high Plight tests to detersine reliability of X-15 self angle of attack limitations adaptive fliqht control system A71-19095 r NASA-TB-D-6208 3 A7 1- 18U22 Electrostatic charqing noise measurement. PLIGET CEBQS reduction and flight test verification Cargo aircraft crew safety and survival, 171-19937 describing restraint, escape, flight deck Plight testinq of Diamant 18 qlider. discussing interior doors. fire and smoke hazards and aircraft behavior at lor and high flight speed, personnel environmental protection stall, spin, stability and control [ SAE-ARP-11391 A71-19643 characteristics, design and construction FLIGET EAZAEDS 171-20686 Report of transport aircraft accident and probable Lou speed lateral stability and coutrol flight causes tests on Avro 707 aircraft [ !?TSB-AAR-71-4] 871-19090 [ARC-CP-1 106-PT-3 J Y71-17083

A-23 FLOORS SUBJECT INDEX

Fliqht tests to determine reliability of x-15 self field about airborne ordnance adaptive flight control system rAIAA PAPER 71-2953 A71-22015 r NASA-TA-D-6208 J N71-18422 Cross flow profiles for compressible turbulent KL-10 and M-2P2 liftinq body fliqht tests boundary layers with and uithout flow reversal r NASA-TM-X-66712 J N71-18428 via hodograph models family FLOORS 1171-22033 Bent structure failure under pulse floor Uake flow properties of conical bodies at acceleration shocks, concerninq aircraft seat supersonic speeds and various angles of attack damaqe durinq crash landing. (NASA-TU-I-2139 J N71-18480 171-20747 FLOU GEOlETRI ?LOW CEABBERS Shock wave interaction with wedqe movinq at Aircraft fuel and air conditioninq systems vortex supersonic speed, calculating geometry of valves and diodes, examininq flow patterns into reqions formed intersectinq wavefronts and out of chambers 171-19741 1171-20556 ?LOW IIBASURKIIEIlT FLOW CHARACTERISTICS Uind tunnel experiments on vortex shedding from Transonic gas flows in axisymmetric small throat circular cylinders in oscillating free streamA71-19908 curvature radius Lava1 nozzle with appreciable flow parameters variation in transverse ?LOW BETS direction Flow lines construction in two dimensional A71-19732 supersonic flow reqion with rarefaction waves Plow characteristics of wire-form and interaction from several disturbance sources laminate-form porous materials A71-22052 INASA-TM-X-2111] 1171-17130 FLOU STABILITY PLOW COEPFICIEITS Monograph on transonic shock free potential flow small curvature radius/throat radius ratio around quasi-elliptical airfoil sections, supersonic nozzles mass flow rate coefficients investiqating. flow stability under unsteady at hiqh Reynolds numbers, appraisinq isentropic disturbances flow prediction methods A71-19773 A71-19877 Stability of laminar flow in circular pipes with PLOW DEPLECTIOR respect to three dimensional disturbances Hypersonic radiatinq qas inviscid flow past blunt N71-18989 bodies, usinq spherical harmonics approximation FLOW TEEOEI A71-19183 Soviet book on qas flow past blunt bodies, Part 1, Plow pattern around arbitrary star-shaped coutour, Flow analysis and calculation methods coverinq derivinq expression for complex potential as finite difference theory, alqorithms, etc velocity function A71-19049 A71-19745 FLOW VELOCITY Jet enqine contribution to lift at supersonic Nonstationary isentropic low density flows with fliqht velocities via air mass heatinq, studyinq axial or central symmetry, suqgesting three dimensional flow with heat supply and characteristics with flow rate and sound speed stream deflection variation as in stationary source flow A71-19746 A71-19729 Cavitation flow of fluid with free surface past Plow in channel with abrupt asymmetric widening, underwater winq with let flap, solvinq equations calculatinq exoandinq flow velocity profile by of motion for thin foil with jet emerqeut from Prandtl semieepirical turbulence theory trailing edqe A71-22041 A71-20086 FLOW VISUALIZATIOR Heavy fluid flow past partially cavitatinq flat multiple stirce schlieren system for flow plate with cavity closed by fictitious plate, visualization in Canadian trisonic wind tunnel. considerinq liftinq force under qravity usinq integrated logic circuitry for control 1171-20087 171-19924 Continuous flow past plate located perpendicular Caret winq serial tests in Mach 8 to 15 hypersonic to wall with inviscid incompressible fluid flow, including three component force, spanwise havinq linear variation of velocity with heiqht direction pressure distribution and shock wave A71-20828 angular measurements by flow visualization Unsteady analoqy for hypersonic flcws past blunt A71-20015 bodies with shock deformation 1LOCTUATXOU THEOEI A71-21863 Fluctuating circulation, lift and flow induced ?LOW DISTORTIOU structural vibrations of two dimensional bodies, Hanqing shock wave in small supersonic flow past including vortex shedding on sluice gates profile with broken qeneratrix in plane ideal A71-19592 qas ?LOID BOUIDAEIES A71-21872 Ground effect vehicles limiting volumetric PLOW DISTBIBUTION dissipations from air cushion and propulsion Supersonic air flow pattern over rectangular systems with fluid boundary by Coanda effect indentations on plane and axisymmetric surfaces, A71-19923 examininq static pressure and adiabatic FLUID IIBCEAIICS temperature distributions Boundary value problems and applications in fluid A71-19744 and qas mechanics - Conference, Kazan, U.S.S.R.. Plow pattern around arbitrary star-shaped contour, Hay 1969 derivinq expression for complex potential as A71-20076 velocity function ?LUIDICS A71-19745 Pressure regulator design and construction, using Transient and turbulent flow structure in wake hiqh pressure fluidic proportional chain behind thin plates in wind tunnel, notinq 1171-20580 velocity fields, temperature and initial Riqh performance fighter aircraft engine pressure boundary layers ratio and turbine inlet temperature measurement, A71-19750 usinq fluidic sensors Aircraft fuel and air conditioninq systems vortex A71-20586 valves and diodes, examininq flow patterns into Fluidic pressure ratio control for vertical and out of chambers takeoff aircraft lift enqine fuel system, A71-20556 describinq breadboard circuit, test bed and Flowfield isentropes in conical qas flow with flight standard sinqular current surfaces A71-20587 171-21864 FLOTT1R External store surface pressure distributions DC-10 flight test program, discussing handling, durinq captive fliqht aboard F-4B aircraft, takeoff and landing, and flutter, stall and considerinq carryinq aircraft effects on flow stabilitF characteristics

A-29 WBJXT IIDSI 615 ?LO1

A71-19085 ?on c01suIIPTIoI nmxl(p UALlSIS Fuel consumption and propulsive and thermodynamic ?lntter analysis of stressed flat simply supported efficiency comparisons for ships, hydrofoil skeu panels in supersonic flou. using small craft. helicopters, jet aircraft, and ground deflection thin plate theory effect machines A71-21302 [lPL-IiOVERCBA?~121 871-17161 ?OAES ?Urn COPEOSIOl Acoustical properties of liquid base foams and Jet fuels thermal stability and corrosive application for jet noise reduction properties during prolonged storage [ 8ASA-CR-l695] n7i-19139 A71-19492 ?06 ?OEL IIJBCTXOW Soviet book on fog, cloud and humidity measuring Gas dmamics of fan lets at various inlection instruments. discussing artificial fog formation angies and natural fog dispersion problems r AD-7147901 B71-18034 A71-20298 ?UEL SYSTKBS Poq removal by high power carbon dioxide lasers. Fluidic pressure ratio control for vertical evaluating possibility of clearing airport takeoff aircraft lift engine fuel system. rnnuays describing breadboard circnit, test bed and [AIAA PAPER 69-670] 171-20308 flight standard Beteorological observations for terminal ueather A71-20587 modification in aviation. noting airport fog ?OH. TAITS dispersal Thermodynamic properties of insulated liquid A71-21732 methane fnselaqe tanks for supersonic cruise ?OBCE DISTBIBOTIOI aircraft Elastic, inertial and aerodynamic forces [ BASA-TU-D-6157] 871-17506 aeroelastic triangle. examining lift changes due ?ULL SCALE TKSTS to aircraft structure deformation, dynamic Airfoil profile draq measurements. correlating fliqht stability and space shuttle development full scale flight tests and scale model tests in problems transonic and high Reynolds nnmber wind tunnels. A71-20063 [AIAA PAPER 71-2891 1171-22012 Aircraft systems assembly methods. discussing ?USELA6BS rigidity effects on error redistribution in Practical aerodynamics of Ili-6 helicopter - lift external and internal force fiela application system and fuselage A71-20792 [AD-7149153 171-17908 Aerodynamic coefficients, pressure. load and force distributions on cambered delta wings [ARC-CP-1129] 1171-17112 G POBGIIG 61s BEABIIGS Closed die forgiuqs for aircraft industry. Three degree of freedom gas bearing for rind discussing tecbnology, tolerances, materials and tunnel dynamic measurements, allouing models costs simultaneous spin, pitch and yaw motions 1171-20075 [AIAA PAPER 71-2793 A71-22004 Precision forqing of spiral bevel gears for Amy 61s DISSOCIATIOI helicopters Dissociating airflou over tu0 dimensional blunt TAD-7154193 B71-18920 body, determining laminar boundary layer WBIIIBG TECiilIQUES ?hemica1 reaction suppression effects on heat Ball forming technique application to A1 alloys exchanqe structural part contouring. discussinq L-1011 A71-19748 wing panel forming and prestress toolinq Stationary lonqitndiual turbulent flou of air uith A71-21681 equilibrium ionization and dissociation around Fabrication of cobalt alloy and nickel alloy gas plate, calcnlatinq heat exchange and frictional tnrbine blades and disks drag 871-17392 171-21922 POBTBAI 61s DTBAEICS Vortex-lattice PORTRAII program for estimating Soviet book of gas aynamic function tables for tu0 snbsonic aerodynamic characteristics of complex and three dimensional flous past blunt bodies planf oris A71-19050 r NASA-TI-D-6 142 3 1171-17424 Bonndary va,lne problems and applications in fluid PEKE ?LIGHT and qas mechanics - Conference. Ktazan. !?.S=S.a., Free fliqht measnrement of aerodynamic nay 1969 coefficients on fixed cruciform fin stabilized A71-20076 bombs. determining aerodynamic forces and Aircraft tnrbine enqines strength and gas dynamic moments dependence on angnlar velocity characteristics improved by vibration decrease components using elastic elements A71-19872 A71 -2 171 0 FREE ?LS68T TEST APPARATUS Eigh tnrbnlent flou simulation in hypervelocity Comparative stinq supported and free flight tests uind tunnel for reentry vehicles operational in hrpersonic wind tunnel on modified ApOllo testing, discussing nozzle gas dynamic and launch confiqnration mechanical design [AIAA PAPER 71-2651 1171-21991 [AIAA PAPER 71-253) A7 1-2 1982 launch and data rednction in supersonic wind 61s PLOI tunnel free flight testinq of high fineness Soviet book on gas flow past blunt bodies, Part 1, ratio bodies Plou analysis and calcnlation methods covering rAIAA PAPER 71-278) 171-22003 finite difference theory, algorithms, etc PBEE ?MI A71- 19049 Rind tunnel experiments on vortex shedding from Bypersonic radiating qas inviscid flou past blunt circnlar cylinders in oscillating free stream boaies, using spherical harmonics approximation A71-19908 A71-19183 ?BEQOElCT BESPOISE Transonic gas flows in axisymmetric small throat Periodically supported and damped closed circnlar curvature radius Lava1 nozzle uith appreciable beam structure, determininq frequency response flou parameters variation in transverse matrix direction 171-22026 A71-19732 ?OEL COIBOSTIOI Viscous gas flou interaction on delta uing and Liquid fuel pool iqnition at soperflash and oblique airfoil at Each nnmber of infinity snbflash temperatures involvinq adjacent heat A71-19739 source, cross wind and fluid motion Approximation of Chaplygin equation for subsonic A71-19245 ideal gas plane adiabatic flou, applying to discharqe from flat channel uith contraction

A-25 GAS IONIZATION SUBJECT INDEX

171-20083 Heat transfer in air cooling and sweat cooling Surface construction of body of revolution in techniques for high temperature gas turbine supersonic qas flow from distribution of euqine components velocity vector modulus alonq generatrix of N71-17383 body, usinq Prank1 method of characteristics Transpiration cooled blades for high temperature A71-20089 inlets in gas turbine engines Mathematical model of nonstationary intake and N71- 17384 exhaust gas motion in two cycle internal Desiqn of gas turbine enqines for high operating combustion enqine cylinders temperature A71-20780 N71-17386 Plowfield isentropes in conical gas flow with Temperature field measurements within convection sinqular current surfaces cooled rotor blade of qas turbine engineN71-17387 A71-21864 Stability of laminar flow in circular pipes with Cobalt and nickel based alloy metallurgy for hiqh respect to three dimensional disturbances temperature qas turbine materials N71-18989 N71-17389 GAS IONIZATIOl Thermal control coatings for refractory gas Stationary lonqitudinal turbulent flow of air with turbine materials equilibrium ionization and dissociation around N71- 17391 plate, calculatinq heat exchange and frictional Performance of aluminide coatinqs in simulated draq high temperature tests on qas turbine enqine A71-21922 inlets GAS JETS [ NASA-CR- 116 374 1 N71-17393 Two link approximation of Chaplyqin function by Film cooling of gas turbine blades by air couplinq to integral equations, applyinq to injection throuqh holes ideal qas jet separation flow past symmetrical N71-17394 arc Effective heat transfer coefficients in film A71-20084 coolinq systems of qas turbine surfaces Ideal qas jet sonic flow past wedge accordinq to N71-17395 Kirchhoff scheme, testinq sine series solution Air cooling systems for nozzle guide vanes of for convergence aircraft gas turbiues A71-20085 N71-17396 GAS TORBINB ElGIllES Operational design criteria for qas turbine Aerospace Recommended Practice for qas turbine enqines euqine steady state performance presentation for N71-17402 diqital computer proqrams, describinq enqine GAS TDRBIUES type, operatinq and control characteristics nultistaqe qas turbine desiqn optimization. using SAE-ARP-68181 A71-19647 parameter and component analysis with computer Soviet book on aircraft qas turbine and internal calculations A71-21267 combustion enqines coverinq structural desiqn schemes, inlet devices, combustion chambers, GAS-SOLID IIITERFACES materials, compressors, etc Solid particle impurity effects on hypersonic A71-20674 shock tube flow, determininq error in blunt body Gas dynamic test stand for cyclic thermal load measurements testinq of qas turbine engine materials and A71-18916 components at variable heatiuq and cooling rates GEARS and mechanical loads Aircraft qear pumps bearinq elements desiqn for A71-20839 increasinq service life Combustor desiqn for minimum exhaust smoke A71-20793 emission from aircraft qas turbine jet enqines, Precision forqinq of spiral bevel qears for Army considerinq air pollution helicopters A71-20867 r AD-7154191 N71-18920 Book on aircraft qas turbine engine technoloqy GENERAL AVIATIOII AIRCRAFT coverinq combustion chambers, exhaust systems, Avionics for qliders and tourinq aircraft, lubricatinq oils, thrust auqmentation, inlet considerinq safety and VHP radio equipment ducts and overhaul procedures 1171-20684 A71-21625 Avionics for qliders and tourinq aircraft, Aircraft turbine enqines strenqth and gas dynamic surveyinq available electronic equipment for characteristics improved by vibration decrease 1971 usinq elastic elements A71-21768 A71-21710 US qeneral aviation and supplemental air carrier Gas turbine enqines emission characteristics, accident statistical tables for 1969 discussinq methods for pollutants reduction r NTSB-EA-70-6 1 N71-17475 A71-21820 Midair collision hazards, incidents, and Probabilistic estimate of aerodynamic imbalance of recommendations for safe aircraft operations aircraft qas turbine rotors due to production N71-18103 errors in compressor blade anqle Investiqation of anqle of attack information A71-22045 display for pilots to increase efficiency of Advanced coolinq systems and heat resistant qeneral aviation aircraft operation N71-18442 materials for turbine blades of hiqh temperature r NASA-TN-D-62101 aeronautical qas turbine enqines GLASS FIBERS r AGARD-CP-73-71 1 N71-17372 Filament windinq manufacturinq methods usinq Hiqh entrance temperatures for improved unidirectional qlass reinforcements for desiqn performance .of turboqenerators and qas turbine and fabrication of aircraft wins structureA71-20546 enqines r SflE PAPER En-70-406 1 N71-17373 GLIDE PATES nathematical model for calculatinq blade flaximum staqnation temperature on swept winq temperatures in convective cooled qas turbines leadinq edqe for equilibrium qlide entry of N71-17375 space shuttle Heat transfer and heat flux measurinq sensors for A71-18902 qas turbine enqines GLIDERS N71-17377 Avionics for qliders and tourinq aircraft, Desiqn and component testinq of cooled radial qas considering safety and VHF radio equipment turbine enqine A71-20684 N71-17381 Glider fliqht in thermal air currents, discussinq Aerodynamic and thermodynamic performance of sweat aircraft behavior, pilot sensory perceptions and cooled qas turbine enqine blades reactions and use of variometers for ascent rate R71- 17382 determination A71-20685

A-26 SUBJECT IIIDEX EELICOPTER DES1611

Fliqht testing of Diamant 18 qlider. discussinq landinq and reducinq qust load effects aircraft behavior at low and high fliqht speed, r ABC-R/E-3629 3 N71-17102 stall, spin, stability and control GTBOCOIPASSES characteristics, desiqn and construction Gyrocompass strapdown three coil synchro sensor A71-20686 maqnetometer in conjunction with vertical gyro. Avionics for qliders and touring aircraft, eliminatinq azimuth detector inertial platforms surveying available electronic equipment for A71-20340 1971 GTBOSCOPBS A71-21768 Soviet book on supports and suspensions of Eotorized qlider equipped with Uankel enqine for aircraft qyroscopic devices covering accnracy. self powered takeoff, describinq prototype reliability and lifetime factors related to desiqn and fliqht test data quality and operational conditions A71-21769 A71-20299 Glider flight mechanics for torninq flight, discussinq relationships between turning radius, fliqht speed, sink rate and aerodynamic H characteristics EBAT EICHAD6EBS A71-21770 Graphite drilled-core storage heater for supplying GLIDI116 heated nitrogen gas to supersonic tunnel Lift and drag characteristics of HL-10 liftinq [ NASA-TE-X-2202] N71-17876 body during subsonic qlidinq flight BEAT FLUX I NASA-TU-D-62631 N71-18867 Heat transfer and heat flux measurinq sensors for GOIEBIIEEFT/IIDUSTBT BELATIOIS gas turbine enqines Noise pollution control and airport noise levels 871-17377 abatement regulation by state government, takinq EBAT BESISTAlT ALLOTS into account economic and technical feasibility Thermal control coatings for refractory gas A71-21825 turbine materials Federal legislation and regulatory activities for N71-17391 control and abatement of aircraft noise Fabrication of cobalt alloy and nickel alloy gas A71-21827 turbine blades and disks State, local qovernment and airport proprietor 1171-17392 legal role in regulating aircraft noise at HEAT TBAISFBP airports Dissociating airflow over two dimensional blunt 171-21828 body, determining laminar boundary layer GBAPEIPE chemical reaction suppression effects on heat Liqhtuiug protective coatinqs for boron and exchanqe qraphite fiber reinforced plastics 171-19748 A71-19944 Gas-particle mixture cascade flow over turbine 6BEAT BBITAIII blades, considering momentum/heat transfer and Air pollution emissions at fleathrow Airport. particle trajectories London, from aircraft operations. heatinq [AIAA PAPER 70-7121 A71-20311 installations and road traffic Stationary longitudinal turbulent flow of air with 1171-21823 equilibrium ionization and dissociation around GBOUDD EFFECT plate, calculating heat exchange and frictional Ground bonndary layer effects of fixed qround drag Plane for powered STOL uind tonne1 model, A71-21922 discussinq flow breakdown criteria, contraction Beat transfer prediction for turbine blade desiqn laq. strut fairing znterference, etc N71-17374 fAIAA PAPER 71-2661 All-21992 Beat transfer and heat flux measuring sensors for GBOUID EFFECT EACHIIES qas turbine enqines Ground effect vehicles limiting volumetric S71-17377 dissipations from air cushion and propulsion Wall pressure and heat transfer distribution on systems with fluid boundary by Coanda effect delta wings in rarefied hypersonic flow A71-19923 [ REPT-70-91 871-18423 Air cnshion vehicle technology, considering Sound field effects on flat plate heat transfer in economics, propnlsion. structures, turbulent boundary layer controllability. flexible skirt systems and B [ REPT-70-8 1 1171-18572 and D BEAT TBAISFBB COEPPICIEITS [SAE PAPER 7101831 A71-21713 Beat transfer and exchange measnrements on fixed Examining tracked air cushion vehicles as advanced turbine blades in high temperature combustion ground transportation system chamber [PB-195030] 1171-16904 A71 -17378 Sea state, wind velocity and wind direction Heat transfer in air cooling and sueat coolinq i regression analysis for ground effect machines techniques for high temperature gas turbine [UPL-EOVERCRAFT-16] 1171-17144 engine components Vertical motion of static loads over baffles 1171-17383 during loading operations using ground effect Effective heat transfer coefficients in film machines coolinq systems of gas turbine surfaces [ lIPL-EOVEBCEAFT-TH-31] 871-17160 1171-17395 GBOUID STATIODS Beat transfer in liquid metal cooled gas tnrbine VORDEE ground station oriented aircraft area blades navigation horizontal quidance capability, 1171-17398 discussing digital input/ontput fliqht control HELICAL lIIDI16S A11-21 166 Uind tunnel aerodynamic stability tests on Traffic control system for supersonic transports chimneys with pipes and helical winding using synchronous satellite for data relay stabilizers between vehicles and ground station [ NPL-AERO-1310 3 1171-17334 [iiASA-CASE-GSC-l0087-11 1171- 19287 BBLICOPTBB CO.TBOL GUIDE VADES Eelicopter longitudinal stability in forward Air coolinq systems for nozzle guide vanes of fliqht and hover modes under attitude, heiqht

aircraft aas~ turbines____ and speed constraints, notinq need for cyclic R71-17396 pitch control dne to instabilities GUST ALLEVIATOBS A71-19421 Aircraft elastic mode control for turbulence EBLICOPTBP DE31611 /gust/ alleviation, noting riding quality. Aerodynamic synthesis of helicopter rotor under structural fatigue life and peak loads hover and vertical ascent conditions, using A71-20301 nonlinear vortex approach GUST LOADS A71-19700 Aircraft pilot direct lift control for aircraft

1-27 EBLICOPTEB PERFOBmANCB SUBJECT IEDEI

materials and construction techniques in liqhtninq A71-20306 protection for aircraft and helicopters EOVEEIIG A71- 19930 Boundary layer discontinuity on helicopter roter Liqhtninq and static electricity effects on blade in hovering using flow visualization helicopter desiqn. considerinq rotor protection, [AIAA PAPER 69-1973 A71-20307 carao hook overation and passive discharqers for EOVBEING STABILITY radio interference reduction Helicopter longitudinal stability in forward A71- 19938 fliqht and hover modes under attitude, height EELICOPTEE PERFOEIANCB and speed constraints, notinq need for cyclic Heiqht velocity /A-V/ fliqht testinq, qivinq pitch control due to instabilities results from OH-58A Kiowa and AH-1G Huey Cobra A71-19421 helicopters EUUAN BBEAVIOR A71-19093 Sonic boom effects on human physiology and Helicopter noise minimization by various piloting behavior and structures, based on theoretical maneuvers, discussinq takeoff and landing, studies and simulators A71-21812 transition to forward fliqht. route selection, etc EUMAI PACTOES BEGINBBEIHG 171-21049 Fiber optic faceplates for contrast enhancement EBLICOPTEES under hiqh ambient liqht conditions for Helicopter charqinq mechanisms, considerinq engine commercial and military cockpits, eliminating and rain precipitation charqinq qhost, halo and direct sunlight problems171-19175 A71-19933 Boundary layer discontinuity on helicopter roter Aerospace Recommended practice criteria for fliqht blade in hoverinq usinq flow visualization deck crew escape systems applicable to all [AIAA PAPER 69-1971 A71-20307 commercial aircraft propulsion systems, design Fuel consumption and propulsive and thermodynamic speeds and payloads efficiency comparisons for ships, hydrofoil r SAE-ARP-808A-J A71-19646 craft, helicopters, jet aircraft, and qround EUIIAN PEEFOEIANCE effect machines manned aircraft crew long range navigation, r NPL-HOVERCRAFT- 12] 871-17161 discussing sensor, information processing and Practical aerodynamics of ni-6 helicopter - lift display systems for future commercial and system and fuselaqe military nissions A71-20343 [ AD-7149151 N71-17908 Functional requirements for qround-based trainers, EOIAN EEACTIONS helicopter response characteristics community reactions to aircraft noise, discussinq TAD-7149541 N71-18018 short term interim alleviation measures in Effectiveness of anti-torque aerodynamic surfaces airport operations and runway usaqe schedulinq immersed in helicopter rotor downwash A71-21819 TAD-715438 1 N71-18937 EOIIDITT EIGE ALTITUDE Effect of atnospheric humidity on characteristics Turbulent/total flight mile ratio in hiqh altitude of turbofan engine clear air turbulence /HICAT/ proqram r~~-7152321 N71-17728 A71-20314 EUIIIDITI IEASOBBIBNT EIGE ASPECT RATIO Soviet book on fog, cloud and humidity measuring Larqe aspect ratio rectangular duct rith instruments, discussing.artificia1 fog formation nonuniform surface texture, investigating and natural foq dispersion problems turbulent flow, maximum velocity positions and 171-20298 zero shear stress EIDEAULIC COETBOL A71- 18772 Aircraft electronic control systems, considering EIGE PEESSUEE hydraulic servocontrol, force simulation and Pressure requlator desiqn and construction, usinq reliability models hiah~. Dressure fluidic vronortional.. chain 1171-20064 A71-20580 EIDELOLIC JETS EIGE TBlPBRATUEE GASES Uind tunnel photoqraphy for determining water Advanced coolinq systems and heat resistant droplet size in breakup of water jets materials for turbine blades of hiqh temperature NASA-CR- 116820 ] N71-18962 aeronautical qas turbine enqines ETDBAULIC TEST TUNEELS I r AGARD-CP-73-711 N71- 17372 Trajectories prediction for subsonic spin I Hiqh entrance temperatures for improved stabilized projectiles via water tunnel tests, performance of tnrboqenerators and qas turbine considerinq blunt nose and tail and rounded nose enqines riqht circular cylinders N7 1-17373 [AIAA PAPER 71-2961 A71-22016 Heat transfer and exchanqe measurements on fixed EIDEOCAEBOI COIBUSTIOI 4 turbine blades in hiqh temperature combnstion Water vapor condensation effects on methane-air chamber combustion gases for aerodynamic test medium 1171-17378 [AIAA PAPER 71-2581 A71-21986 Desiqn of qas turbine enqines for high operatinq ETDEODTltAIICS temperature centrifuqal compressor vaneless diffuser, 1171-17386 estimating energy losses with hydrodynamic model Computerized optimization of thermal resistant qas A71-21266 turbine blades ETDEO?OILS N71- 17400 Cavitation flow of fluid with free surface past EIGEUAIS underrater ring with jet flap, solving equations nass transport systems for airport access of motion for thin foil with jet emergent from N71-18952 trailinq edqe EL-10 REEETBI VEEICLII A71-20086 HL-10 and H-2F2 liftinq body fliqht tests ETDEOGBI FUELS [NASA-TB-I-667121 871-18428 Comparison of hydrogen and methane as coolants in Lift and drag characteristics of AL-10 liftinq reqeneratively cooled panels body durinq subsonic qliding fliqht I NASA-CR-16521 N71-19289 [ NASA-TN-D-62631 N71-18867 EYPEESOIIC AIECEAFT EODOG1lPES Optimal reight of aerodynamic heat protection cross flow profiles for compressible turbulent layers of stressed skin and optimal efficiency boundary layers with and without flow reversal of cooling system for hypersonic aircraft via hodograph models family compartments A71-22033 1171-20836 EOEIZOETAL FLI6ET Aerodynamic heatinq and structural analyses for Optimum automatic fliqht control techniques in radiatively cooled delta wing of hypersonic horizontal quidance of aircraft at terminal aircraft

A-28 SUBJECT IIDLI IICOUPPLSSIBLB PLOW

ISA SA-TW-E-6138 J 171-18025 ballistic projectile turbulent rakes. using hot Pliqht constraints and aerodynamic characteristics film anemometers of hypersonic research aircraft [AIAA PAPER 68-7011 A71-19891 [ lASA-TU-I-2222] 171-18367 HIPERILLOCITY lIWD TUllELS Enropean hypersonic vind tnnuels for testing Blunt cylinder vith small thread in anomalous hypersonic transport aircraft, and space shuttle seeded flou in hypersonic wind tnnnels, aerodynamic configurations observing separated shock uave distortion 871-18452 A71-18921 EYPXESOlIC BOIIIDABY LAY- rind tnnnel history. evolution and use, covering Hypersonic laminar boundary layer near sharp lor speed variable density, high speed expansion corner transonic, supersonic, hypersonic and 171-17752 hypervelocity vind tunnels lear-continnum axisymmetric hypersonic flov past 171-21 666 very slender bodies Eigh tnrbulent flov simnlation in hypervelocity [ AD-715901 J 171-18556 vind tnnnel for reentry Tehicles operational EIPLPSOlIC ?LICET testing. discussing nozzle gas dynamic and Iloneqoilibrium multicomponent ionization mechanical design calculations for stagnation merged shock layer ~AIAA PAPER 71-253J A71-21982 of hypersonic blunt body by successive Comparative sting supported and free flight tests accelerated replacement in hypersonic vind tnnnel on modified Apollo [AIAA PAPER 69-6551 A71-19890 lannch confignration Hypersonic minimum drag slender uinq leading edge [AIAA PAPER 71-2653 A71-2 199 1 shape for given airfoil section, using Sertonian AerOdyUamiC support interference in vind tunnel theory testing of configurations involving bnlbons A71-22039 base, mass addition, transition near base and Plight constraints and aerodynamic cbaracteristics hypersonic lov density flows of hypersonic research aircraft [AIAA PlPER 71-2771 A71-22002 [ SAS1-TU-1-2222 J 171-18367 Bypervelocity rind tnnnel data acqnisition EIPSPSOWIC ?LOW [ DLR-PB-70-44 J 1171-17046' Hypersonic radiating gas inviscid flow past blunt Enropean subsonic, snpersonic. transonic. bodies. nsing spherical harmonics approximation hypervelocity and low density wind tunnel A7 1- 1918 3 characteristics Interaction between radiation from shock wave 171-17099 region and oncoming cold air flov in hypersonic Enropean hypersonic vind tunnels for testing flow past blunt body hypersonic transport aircraft, and space shuttle A71- 19730 aerodynamic confignrations Incompressible hypersonic laminar boundary layer n7 1- 18052 flov over sharp cone, based on asymptotic inner Hypersonic lov density wind tunnel including and outer flov field expansion anxiliary eqnipment for electroforming and A71-19892 electroplating vind tunnel models Caret uing serial tests in Uach 8 to 15 hypersonic [ BEBU-FB-0-70-513 871-18593 flov, inclnding three component force, spanvise Bypersonic shock tunnel of APAPL direction pressure distribntion and shock wave TAD-7159071 87 1- 18717 angular measnrements by flov visualization A71-20015 I Unsteady analogy for hypersonic flovs past blunt bodies vith stock deformation IDEAL 611s A71-21863 Approximation of Chaplygin eqnation for snbsonic Static pressure port errors in hypersonic ideal qas plane adiabatic flou, applyinq to tnrbulent flou, nsinq approximate shear layer discharge from flat channel with contraction

momentna balance for~ ~~ Dressnre~ increase ~~ ~ ~~ A7 1- 200 8 3 derivation Tu0 link approximation of Chaplygin function by [AIAA PAPER 71-2701 A7 1-2 1996 conpling to integral egnations, applyinq to Uumerical compntation of viscons hruersonic-. flov ideal gas jet separation flou past symmetrical aronnd slender bodies arc vi-16951 A71-20064 Rectangular and caret wing sails in supersonic and Ideal gas jet sonic flou past uedge according to hTperSOniC turbnlent flou for hypersonic Kirchhoff scheme, testing sine series solntion vehicles for convergence [ ARC-R/U-3624 ] U71-57103 871-20085 Pall pressure and heat transfer distribution on 1611TIOS LIBITS delta wings in rarefied hypersonic flov Liquid fuel pool iqnition at superflash and r ~~m-70-9J 871- 18423 subflash temperatures involving adjacent heat Hypersonic tvo phase flow realized by air-vater source, cross vind and flnid motion mixtures A71- 19245 [ BUVTD6-FBPT-70-13 1171- 18141 IUASB COREAST EIPLESOWIC SEOCK Fiber optic faceplates for contrast enhancement Solid particle impnrity effects on hypersonic under hiqh ambient light conditions for shock tnbe flou. determininq error in blunt body commercial and military cockpits. eliainating measnrements ghost, halo and direct snnliqht problems A71-18916 A71-19175 Hypersonic shock tunnel of APAPL IUPICT ACCELLPATIOI r AD-715907 J 871-18717 Bent strncture failnre under pnlse floor EIPBESOlIC SPm acceleration shocks. concerning aircraft seat Viscous drag on variable sweep vings and wedges at damaqe during crash landing supersonic and hypersonic speeds 171-207U7 rARC-R/E-3623 ] 1171-17109 IWPLIGET UOlIXIEI16 ETPBBSOlIC ILEICLES In-flight determination of lateral-directional Composite rocket cum hypersonic airbreathing dynamics for landing approach propnlsion redncing space exploration program [AD-715317] 1171-17792 cost 18COUPPLSSIBLL ?LOW A7 1-2 130 1 Incompressible hypersonic laminar boundary layer BYPBESOIICS flou over sharp cone, based on asymptotic inner nose bluntness, angle of attack and oscillation and onter flor field expansion amplitude effect on hrpersonic unsteady A71-19892 aerodmamics of slender cones Solid foil small oscillations in nnsteady [AIAA PAPER 70-216 J 1171-19895 incompressible flou. 8apping physical plane and EYPIPVKLOCITT PPWECTILS corresponding complex potential region onto Velocity and density measnrements in hypervelocity cnrvilinear half strip

A-29 IUCOIPBBSSIBLB FLUIDS SUBJECT IUDEI

A71-20088 during takeoff Computerized transonic airfoil desiqn from [ ARC-CP-11141 N71-17084 predetermined supercritical velocity IULBT PLOU distribution, obtaining equivalent High performance fighter aircraft engine pressure incompressible flow throuqh streamline and ratio and turbine inlet temperature measurement, potential line network transformation using fluidic sensors A71-20304 1171-20586 Entrainment coefficient used for computation of Air temverature effects on internal combustion two dimensional incompressible turbulent engines intake process, using similarity theory boundary layers A71-20782 rARC-R/H-3643 1 N71-18424 optimal lininq impedance for jet engine inlet IKOIIPRBSSIBLB FLUIDS duct, yieldinq discrete frequency, flow velocity Seaplane step /flat plate/ ricochet off ideal and qeometry on basis of minimum radiated power incompressible fluid surface, determining free 1171-21661 surface shape by accountinq for trailinq High entrance temperatures for improved vortices effects performance of turbogenerators and qas turbine 171-19355 enqines Liftinq surface nonstationary aperiodic motion in N71-17373 incompressible fluid solved by asymptotic method IULBT NOZZLBS of function parameters, usinq algorithm for Auxiliary inlet elector nozzle desiqned for Cauchy problem supersbnic cruise aircraft 871-20778 r NASA-TU-I-21821 N71-18863 Continuous flow past plate located perpendicular IUSTRUIBBT BEEOES to wall with inviscid incompressible fluid Aircraft radio compass navigation errors due to havinq linear variation of velocity with heiqbt loop antenna inclinations during maneuverinq A71-20828 A71-20787 IUDBIBS (DOCUIBUTATIOU) Static pressure port errors in hypersonic Subject ard author index on aeroelasticity turbulent flow, using approximate shear layer documents momentum balance for Pressure increase IAGARD-R-578-711 N71-17432 derivation IUDICATIUG IUSTBUlEUTS TAIAA PAPER 71-2701 A71-21996 Aircraft visual warninq indicatinq system. IUSTBbClBUT PLIGET BULBS- outlininq desiqn criteria, color and briqhtness ATC automation program for en route and terminal recommendations centers, discussinq combined nationwide system [SAE-ARP-10881 A71-19644 features, IFR volume and video diqitizer data IUBRTIAL UAVIGATIOU links Gyrocompass strapdown three coil synchro sensor A71-21659 maqnetometer in conjunction with vertical qyro. IUSTBUIIBUT LAUDIUG SYSTBIS eliminatinq azinutb detector inertial platforms Aircraft automatic landinq improvement throuqh use A71-20 340 of space diversity ILS receivinq system U.S. domestic ATC airspace enroute and terminal A71-18830 area naviqation system effects on pilot Structures electromaqnetic scattering and workload, projecting future FAA requirements multipath transmission effects on aircraft A71-20347 instrument landinq system localizer siqnals. Strapdown inertial naviqator alignment by diqital usinq computer pfoqram filterinq techniques, discussinq application to A71-18831 aircraft and spacecraft Aircraft final approach and landing aids, A71-21170 describing ILS, VHF omnidirectional radio range, IUFIUITB SPAU UIUGS distance measurinq equipment and satellite Potential flow past cylinder with sources and systems for air naviqation sinks sinqularities, derivinq formulas for A71-19014 aerodynamic Characteristics of infinite span Kalman filter application as observer of winqs with boundary layer control observable siqnals derivatives, usinq qain A71-20777 matrix to minimize variance estimatp for Pressure qradient effects on three dimensional instrument landinq systems turbulent boundary laver of infinite span A71-21343 sweptback winq IUTAKB STSTELIS ~NPL-AERO-~~OS1 N71-17179 Static tests to determine effects of throat inlet IUFLATABLB STBUCTURBS concepts on forward-radiated fan noise of Desiqn and characteristics of double hull 707-320B/C airplanes diriqible airship r NASA-CR-1715 1 N71-17426 r JPRS-52330 J N71-19217 Effect of various diffuser desiqns on performance INPOBEATIOI SYSTBlS of experimental turbojet combustor insensitive Inteqrated project information and simulation to radial distortion of inlet airflow system for manaqement of aerospace vehicle rNASA-TH-X-2216] N71-18561 development, discussinq simulation models IUTBGBAL EQUATIOUS application Two link approximation of Chaplyqin function by rAIAA PAPER 71-2381 1171-19714 couplinq to inteqral equations, applyinq to Three-phase time-ordered functional orqanization ideal qas jet separation flpw past symmetrical for qround based collision avoidance, discussinq arc information flow, display capability and dynamic A71-20084 simulation model IUTBRPBREICE rAIAA PAPER 71-2401 A71- 19716 Rocket/launcher aerodynamic interference effects Development .Proqram for multiple access real time investiqation by wind tunnel simulation, tactical information distribution system, determining interference coefficients for desiqninq and constructinq tactical air control rockets ballistic dispersion calculations system test facility [AIAA PAPER 71-2693 1171-21995 rAIAA PAPER 71-2431 A7 1-1971 8 Transonic wind tunnel wall interference effects Uanned aircraft crew lonq ranqe naviqation, experimental determination, investiqatinq porous discussinq sensor, information processinq and ani slotted walls display systems for future commercial and IAIAA PAPER 71-2921 171-220 13 military missions IUTERFBBBUCBLIFT A71-20343 Wind tunnel boundary interference on V/STOL model Observational data characteristics analysis as calculated in test section with solid vertical

contributor to knowledqe and utilization of all and~~~ slotted__~ horizontal walls, usinq imaqe method atmospheric physical occurrences and Fourier transforms A71-21722 [AIAA PAPER 70-5751 A71-22029 INGESTION (ENGINES) wind tunnel testinq of interference lift of tandem Inqestion of debris into aircraft enqine inlets winq aircraft lifting surfaces

A-30 SUBJECT INDEX JET EIEAUST

F ONERA-TP-890 J N71-18449 Bathematical model for aircraft liftinq surface interference in steady or unsteady supersonic J flow JET AlBCBAPT [ ONERA-TP-850] N71-18462 aircraft engine smoke emission control, discussing IETERNAL COIBUSTIOR ERGIIES Ringelmann chart assessnent for various Soviet book on aircraft gas turbine and internal commercial jet aircraft and airport gaseous combustion enqines coverinq structural design pollutants schemes, inlet devices, combustion chambers, A71-21832 materials. compressors, etc Fuel consumption and propulsive and thermodynamic A71-20674 efficiency comparisons for ships, hydrofoil Oathematical model of nonstationary intake and craft, helicopters, jet aircraft, and ground exhaust qas motion in two cycle internal effect uachines combustion engine cylinders [ NPL-KOVERCRAPT-12] 1171-17161 A71-20780 causes and results of aircraft accident of Lear Air temperature effects on internal conbustion jet aircraft enqines intake process, using similarity theory [NTSB-ARR-71-3] 1371-17511 A7 1- 207 82 Bathematical model of large jet transport aircraft IRTEBIATIOIAL COOPEBATIOI simulation Aircraft noise abatement control on international NASA-CR-17561 N71- 19239 basis by setting acoustic technological JET AIRCRAFT ROISE capability compulsory standards of quietness SST noise suppression research, discussinq enqine A71-21826 noise suppressor conceptual designs and test European aerospace and electronic equipment results with installed devices industrial cooperation for air traffic control A71-20302 and communication satellites Aircraft optimum minimum noise takeoff profile, 871-17181 solvinq by equations of motion system for jet International conference on rain erosion and aircraft associated phenomena All-20779 [AD-715100J N71-17906 Jet aircraft noise over residential areas, IETBBIATIOIAL LAW discussing actual and permissible noise levels Bembers attitudes on revisions to Warsaw and proposals for remedial action Convention and The Kaque Protocol amendments on 171-21163 liability to international air transport iroise reduction at source, flight methods Passengers adjostseatr and airport compatible laz!a nse for

[REPT-l970/@-E] A71-18100 iet. noise~~ abatement IITEBIATIOIAL TBADE A71-21815 US commercial aircraft export strategy and Static tests to determine effects of throat inlet recommendations for financinq and expansion concepts on forward-radiated fan noise of 1171-18087 707-32OB/C airplanes IIVEITOBIBS I NASA-CR-17 151 N71-17426 Statistical methods for inventory boundary Je't aircraft noise reduction near airports determination and data compression in automatic 1171-18079 processing of multispectral scanner remote Noise associated with operati-on of C-91 sensor earth observations from aircraft and /aeromedical evacuation/ aircraft spacecraft [AD-7152221 1171-18269 [BIBB FAPEB 71-2343 b7:-:77:1 ;ilbll-ctive evaluatioIi ti-sto of grudG: uboe~ve~son INVERTOBI OARAGERBIT relative noise from acoustically treated engine Computerized simulation of alternate loqistics for nacelles of Boeinq 707 aircraft overhaul and expensive parts inventory f NASA-CR- 17 17 3 N71-18499 procedures of coimerical airlines Acoustical properties of liquid base foams and 1171- 181 18 application for jet noise reduction IIVISCID FLOW [ NASA-CR-1695 J N71- 19 139 Ewersonic radiating gas inviscid flow past blunt JET EI6IIE FUELS bodies, using spherical harmonics approximation Jet fuels thermal stability and corrosive 1171-19183 properties during prolonged storage Computer calculation of hiqh Reynolds number A71-19492 viscous and inviscid flov over arbitrary shaped Device for jet fuels antiuear properties tvo dimensional bodies and airfoils measurement under rolling friction A71-20313 A71-19493 Continuous flou past plate located perpendicular JET EIGIIES to uall with inviscid incompressible fluid Concorde aircraft Olympus 593 two-spool turbojet havinq linear variation of velocity uith height engine, discussing variable nozzle and intake A71-20828 assembly. afterburner and control system Lift and aerodynamic drag due to trailing-edge A71-19081 flaps on sveptback wings in inviscid subsonic Jet engine rotor strain and temperature data flov transmission. examining special purpose [ ARC-CP-11101 171-17114 telemeters design IOIOSPEKEIC SOUIDII6 A71-19628 Upper air sounding systems problems. discussinq optimal linin4 impedance for jet engine inlet aerodynamic heat transfer between temperature duct. yielding discrete frequency, flow velocity sensor and ambient air and geometry on basis of minimum radiated pover A71-21739 A71-21661 ISEITROPIC PBOCKSSES Plasma arc welding of jet engine components of Ti Ronstationary isentropic lor density flows with and Ni alloys, comparing to gas tungsten arc and axial or central symietry. soggestinq electron beam processes characteristics with flov rate and sound speed A71-21684 variation as in stationary source flou Subsonic jet enqine noise reduction, considering A71-19729 turbojets, turbofans and jet suppressors Small curvature radius/throat radius ratio A71-21814 supersonic nozzles mass flow rate coefficients Jet engine combustion chamber burn-throngh fire at high Reynolds numbers. appraising isentropic and methods for controlling damage flou prediction methods [ FAA-RD-70-681 N71-17483 A71-19877 JET EIEAUST Plowfield isentropes in conical qas flow with Combustor design for miniium exhaust smoke singular current surfaces emission from aircraft gas turbine jet engines, 171-21864 considering air pollution 1171-20867

A-31 JET FLAPS SIJBJBCT IIDEX

Jet exhaust nacelle subsonic flow simulation Land development planning and aircraft noise at f ARC-CP-11113 171-17113 Kansas City International Airport JET FLAPS A71-21837 cavitation flow of fluid with free surface past LAMDIIG AIDS underwater winq with jet flap, solving equations Aircraft final approach and landing aids, of motion for thin foil with let emerqent from describinq ILS, VHP omnidirectional radio range. trailing edge distance measuring equipment and satellite A71-20086 systems for air navigation Investiqatinq effects of leading-edge blowing on A71- 190 14 aerodynamic characteristics of let flapped Poq reaoval by high power carbon dioxide lasers, airfoil evaluating possibility of clearing airport N71-17702 runways Trailinq vortex systems qenerated by jet-flapped [AIAA PAPER 69-6701 A71-20308 winq operatinq at hiqh winq lift coefficients V/STOL microwave scanning beam approach and r AD-7153153 N71-17753 landinq system, describinq ground and airborne Helicopter application studies of variable station equipment and operation deflection thruster let flaps A71-21680 r AD-715071I N71- 17907 Shuttlecraft landing and navigational aid JET FLOP capabilities Ideal gas jet sonic flow past wedqe accordinq to [ NASA-T8-X-667201 071-18187 Kirchhoff scheme, testinq sine Series solution LAMDIIG GEAR for converqence Dynamic loads on P-104G aircraft landing gears A71- 20085 [ F8-82-19693 N71-18532 JET LIFT LASER OUTPUTS Jet enqine contribution to lift at supersonic Fog removal by hiqh power carbon dioxide lasers, fliqht velocities via air mass heating, studyinq evaluating possibility of clearing airport three dimensional flow with heat supply and runways stream deflection [AIAA PAPER 69-6701 A71-20308 A71-19746 LASERS JET UOZZLES Inteqrated electro-optical microwave radar and Air coolinq systems for nozzle quide vanes of laser /lidar/ systems for earth oriented, aircraft qas turbines environmental and domestic applications 171-17396 1171-18827 JET PROPULSIOI Laser Doppler velocimetric technique for Jet propulsion optimization by exerqy and anerqy supersonic flow particle trajectory and density for minimum total cost flux by varying unit measurements, notinq particle lag compressor pressure ratio [AIAA PAPER 71-2871 171-22010 A71-21300 LATERAL COITROL Auxiliary inlet ejector nozzle desiqned for Low speed lateral stability and control flight supersonic cruise aircraft tests on Avro 707 aircraft r NASA-TU-X-2182 1 N71- 18863 [ ARC-CP-1106-PT-33 N71-17083 JETTISOMIUG In-fliqht determination of lateral-directional Wind tunnel testinq of aerodynamic interactions dynamics for landing approach between aircraft and jettisoned loads usinq [ AD-7 15317 3 N71-17792 trajectory analysis LATXRAL STABILITY IONERA-TP-849 1 N71-18464 Boundary layer separation and lonqitodinal and lateral stability of Avro 707 aircraft during flight tests L r ARC-CP-1107-PT-43 N71-17082 L-1011 AIRCRAFT Low speed lateral stability and control flight Ball forming technique application to A1 alloys tests on Avro 707 aircraft structural part contourinq, discussinq 1-1011 [ ARC-CP-1106-PT-33 1171-17083 uinq panel forminq and prestress tooling LAW (JURISPRIJDEICE) A7 1-21 68 1 Federal legislation and regulatory activities for LALIIIAR BOUIDARY LAYER control and abatement of aircraft noise Dissociating airflow over two dimensional blunt A71-21827 body, determining laminar boundary layer state, local government and airport proprietor chemical reaction suppression effects on heat leqal role in regulating aircraft noise at exchange airports A71-19748 A71-21828 Reactinq and nonreacting gases laminar boundary Federal legislation and regulation of aircraft layer flows over two dimensional and noise, legal rights of airport neighbors and axisymmetric bodies at zero lift, comparing leqal aspects of compatible land use, discussing numerical methods noise control efforts A71-19860 A71-21829 Incompressible hypersonic laminar boundary layer Legal aspects of military sonic booms, discussinq flow over sharp cone, based on asymptotic inner administrative reaedies, liability and various and outer flow field expansion cases k71-19892 A71-21830 Hypersonic laminar boundary layer near sharp LXADIIG EDGX SLATS expansion corner Investigating effects of leading-edge blowing on N71-17752 aerodynamic characteristics of jet flapped LAIIIAR ?LOU airfoil Incompressible hypersonic laminar boundary layer 1171-17702 flow over sharp cone, based on asymptotic inner LEADIIG EDGES and outer flow field expansion naximum stagnation temperature on swept ring A71- 19892 leading edge for equilibrium glide entry of Stabilitl of laminar flow in circular pipes with space shuttle respect to three dimensional disturbances A71-18902 1171-18989 Hypersonic minimum drag slender wing leading edge LAID WSE shape for given airfoil section, using Newtonian Land use strategies and noise reduction by source theory control and fliqht procedures for noise exposed A71-22039 areas minimization LBAST SQUARBS IIBTEOD A71-21818 nulticomponent plane flap mechanism with Land use control in aircraft noise abatement, transmission angles diverging minimally from considerinq airport development and community ninety degrees, discussing synthesis by least qoals squares method A71-21836 A71-19361

A-32 SOBJICT IIDBI LIQUID-SOLID IITERPACBS

LB6U LIABILITY Diego, December 1970 Legal aspects of military sonic booms, discussing 1171-19926 administrative remedies. liability and various Liqhtninq stroke probability .Odd for point cases selection on aerospace vehicles A71-21830 171-19928 LIABILITIIIS Statistical information on lightning and static Members attitudes on revisions to Varsau hazards relative to airuorthiness Convention and The Hague Protocol amendments on A71-19929 liability to international air transport Baterials and construction techniques in lightning passengers protection for aircraft and helicopters [ REPT-l970/8-E] U71-18100 1171-19930 LIR Artificial lightning generation facilities for Fluctuating circulation, lift and flow induced aircraft mmponent developmental testing by structural vibrations of tuo dimensional bodies, manufacturer including vortex shedding on slnice gates 171-19931 A71-19592 Lightning current transfer tests of p-static Eeavy fluid flou past partially cavitatinq flat discbarqer for aircraft installations plate uith cavity closed by fictitious plate, A71-19935 considerioq lifting force under gravity Suept lightning stroke effects on aircraft design A71-20087 involving Ti and A1 sheets Lift and aerodynamic drag due to trailing-edge A71-19936 flaps on sreptback uings in inviscid subsonic Lightning and static electricity effects on flow helicopter design. considerinq rotor protection, [ ARC-CP-11101 117i-i7ii4 carqo hook operation and passive dischargers for Lift and aerodynamic drag data on slender wings radio interference reduction with trailinq edge sueepback A71-19938 [ARC-CP-1130] n7i-17117 Lightning protection for nonmetallic helicopter Trailing vortex systems generated by iet-flapped rotor blades winq operating at high winq lift coefficients A71-19939 [ AD-7 153153 1171-17753 Late model P-4 air superiority aircraft and Practical aerodynamics of Ei-6 helicopter - lift electronic flight control systems protection system and fuselage aqainst lightning discharges dasage to electric [ AD-7 14915 ] 171-17908 and electronic systems LIPT CETICIS A71-19990 Boeinq 737 aircraft takeoff and landina Liahtning and surqe protection devices for performance, emphasizing high lift systems and survirability of aircraft electrical systels stopping capability 171-19941 A7 1-19083 Lightning protection for dielectric composites, Airplane wing high lift and flap desiqns by analyzing damage from shock wares, vaporization interactive computer graphics system pressure, magnetic forces and burning [AIAA PAPER 71-2271 171-19705 A71-19942 Lifting surface nonstationary aperiodic motion in Composite plastic aircraft structures lightninq incompressible fluid solved by asymptotic method protection, considering hazard to composite of function parameters, using algorithm for materials and use of metal filled or plasma Canchy problem sprayed coatings and metal foil coverings A71-20778 A71-19943 Pattematical mcdel for aircraft liftiog surface Li;Ltni=q pzotectivs ciatinqs for borer 133 interference in steady or unsteady supersonic qraphite fiber reinforced plastics flow A71-19944 (ORERA-TP-850 3 171-18962 Beasurements and analysis of lightning-indnced LIFT PAIS voltages in aircraft electrical circuits Lift fan propulsion for civil VTOL transports, [ NASA-CB-17441 171-19 122 considerinq applicability. attitnde control. LIJBAE BPUATIOIS system design. fan transition and cross flou Coefficient determination of fliqht dynamics noise multivariable systems by means of computer A71-20373 simulated aircraft dynamic models Aerodynamic characteristics of V/STOL transport [ DLE-FB-70-303 171-18586 lode1 with tandem lift fans mounted at LIIIBAE FILTERS mid-semispan of winq Kalman-Bncy linear filtering algorithm application r NASA-TR-D-62341 171-18558 to nonlinear estimation of singie channel LIlV116 BODIES missile attitude control system parameters wind tunnel tests to determine unsteady 171-18835 aerodynamic forces between two lifting surfaces Kalman filter application as observer of in tandem observable signals derivatives, using gain [ HA SA-TT-F- 13482 1 171-18397 aatrir to minimize variance estimate for numerical analysis of low frequency subsonic instrument landing systems lifting surface theory noting winq oscillations A71-21343 in steady flow LIJI16S [ ARC-R/E-3634] 171- 18425 optimal linioq impedance for jet engine inlet LIFT116 PBB1TBT VIISICLBS duct, yielding discrete frequency, flou velocity Convective heat transfer characteristics of E2 and and geometry on basis of minimnm radiated power E2-P2 lifting entry vehicles A71-21661 [ UASA-Tll-X-l691] 171-17131 LIQOBFIBD SASBS LIRI16 BOMBS Thermodynaiic properties of insulated liquid Aerodynamic synthesis of helicopter rotor under methane fnselaqe tanks for supersonic cruise hover and vertical ascent conditions, using aircraft nonlinear vortex approach [ 1ASA-T1-D-61571 N71-17506 A71-19740 LIPOID EETALS L16ET &IBCRAFT Beat transfer in liquid metal cooled gas turbine BD-1 Yankee aircraft development, design and blades construction 171-17398 A71-19084 LIQUID-61s EIITUPES LI68T1JS IQOIPEBR Bypersonic two phase flow realized by air-water Airport lighting facilities in Japan, considerinq mixtures fixtures, marker and obstruction liqhts and [BIVTDG-PBUT-70-1] 171-18441 apron floodlight LIQUID-SOLID IRIBFACBS A71-20355 Seaplane step /flat plate/ ricochet off ideal LI6ETUI16 incompressible fluid surface, determining free Lightning and static electricity - Conference, San surface shape by accountinq for trailing

A-33 LOAD DISTRIBUTIOI (PORCBS) SUBJECT IIIDBX

vortices effects systems for lunar landing vehicle simulator A71-19355 [ NASA-CR- 1764821 N71-17345 LOAD DISTRIBUTIOI (PORCBS) Aerodynamic coefficients, pressure. load and force distributions on cambered delta wings M [ARC-CP-11293 871-17112 11-2 LIPTIIG BODY LOADIEG OPBBATIOIS Convective heat transfer characteristics of B2 and Vertical motion of static loads over baffles M2-P2 liftinq entry vehicles durinq loadinq operations using qround effect [NASA-TN-X-l691] N71-17131 machines I-2P2 LIPTIIG BODY [ NPL-HOVERCRAPT-TH-31] N71-17160 AL-10 and M-2P2 liftinq body fliqht tests LOGISTICS [ NASA-TH-X-667121 N71-18428 Problems in civil air transportation and loqistics MACE IUllBBE N71-17799 Parametric enqine study for Hach 0.98 commercial computerized simulation of alternate logistics for air transport with supercritical wing overhaul and expensive parts inventory [NASA-TH-X-52961] N71-18733 procedures of commerical airlines IAGUETIC COILS N71-18118 Gyrocompass strapdown three coil synchro sensor LOUGITUDIIAL STABILITY maqnetometer in conjupction with vertical gyro, Helicopter lonqitudinal stability in forward eliminating azimuth detector inertial platforms fliqht and hover modes under attitude, height A71-20340 and speed constraints, notinq need for cyclic MAGIETOIBTEBS pitch control due to instabilities Gyrocompass strapdown three coil synchro sensor 171-19421 maqnetometer in conjunction with vertical gyro, Boundary layer separation and longitudinal and eliminating azimuth detector inertial platforms lateral stability of AVrO 707 aircraft durinq 1171-20340 fliqht tests MAIITBIAICE r ARC-CP-I~O~-PT-QI N71-17082 computerized simulation of alternate loqistics for LOU ASPBCT BAT10 overhaul and expensive parts inventory Low aspect ratio compressor blade cascade procedures of commerical airlines performance at blade span center, discussinq N71-18118 pressure loss, anqle of attack and staqqerinq MAN MACEIIB SYSTEMS A71-20624 Hanned aircraft crew lonq ranqe navigation, LOW DENSITY PLOW discussing sensor, information processing and Nonstationarv isentropic low density flows with display systems for future commercial and axial or central symmetry, suqqestinq military missions characteristics uith flow rate and sound speed A71-20343 variation as in stationary source flow Ran-machine considerations in all-weather low- A71-19729 altitude naviqation system design, discussing LOW DEUSITY WIID TURIELS computer qeneration of roll command quidance, Aerodynamic support interference in wind tuuuel visual display and pilot modeliuq testinq of confiqurations involvinq bulbous A71-20344 base, mass addition, transition near base and Human role in Aerospace Defense Command hypersonic low density flows naviqation, discussing Airborne Warninq And rAIIA PAPER 71-2771 A71-22002 Control System and naviqational aspects of ADC European subsonic. supersonic, transonic, mission hypervelocity and low density wind tunnel A71-20346 character istics Functional requirements for qround-based trainers, N71-17099 helicopter response characteristics Hypersonic low density wind tunnel includinq [AD-7149541 N71-18018 auxiliary equipment for electroforminq and IAIAGBIBIIT PLAAMIIG electroplatinq wind tunnel models Development model for Oklahoma airport r BHBW-FB-W-70-51] N71-18593 r PB-1949371 N71-16987 LOW SPBBD Development planuinq manual for national Low speed boundary layer separation on compressor transportation system blades of varyinq aspect ratios r~~-i94964] N71- 18072 r ARC-CP-1103 3 N71-17108 Preiqht transportation in Great Lakes area for LOW SPEED WIND TUNNELS year 2000 Wind tunnel history, evolution and use, coverinq N71-19320 lou speed variable density, hiqh speed IANBUVBBABILITY transonic, supersonic, hypersonic and A-7 low altitude tactical fiqhter spin evaluation hypervelocity wind tunnels moatam... . discussina maneuverinq capability, A71-21666 external stores and departure mode Low speed wind tunnel pressure and audio frequency A71-19094 resonance measurements on circular cylinders and MAIBUVBBS thin flat plates Fliqht time, path and fuel consumption in climb at TNPL-AERO-13111 N71-17089 constant radius turn, variable or constant LUBBICATING OILS velocity and constant enqine power, derivinq Book on aircsaft qas turbine enqine technoloqy approximate simple formulas coverinq combustion chambers, exhaust systems, A71-22050 lubricatinq oils, thrust auqmentation, inlet MAUOBETBRS ducts and overhaul procedures Hanometric equipment arrauqement in nose cone of A7 1-21 625 oriented satellite with aerodynamic system LUMINAIRES stabilization Feasibility of electroluminescent panels and rotor A71-21022 tip liqhtinq for military helicopters to aid in IAIIUAL COITBOL observation by other vehicles in formation ~-104~aircraft side stick control system desiqn r AD-7158511 N71-18734 and function, curriculum maneuvers and component LUNAR BASES reliability nanned fliqht from Hontqolfier Balloon to ~poiio A71-19092 13, discussinq future space Proqrams including MAUUALS lunar base and space shuttle Development planninq manual for national A71-19417 transportation system LUNAR GRAVITY SIMULATOR PB-194964 1 N71-18072 Improved feedback control of distributed parameter MARS (PLAIBT) systems for lunar landinq vehicle simulator Real gas effects on draq and trajectories of [NASA-CR-1164821 N71-17345 nonliftinq conical shell durinq Hars atmospheric LURAB LAIDIIG MODULES entry Improved feedback control of distributed parameter INASA-TN-D-62401 N71-18015

A-34 SOBJECT IUDEI IIICBOWAVE EQWIPIIEBT

IIASS DISTEIBWION IECEAUICAL SEOC6 lass loading effects on pyrotechnic shock Aerodynamic broadband noise mechanism applicable environment of aerospace systems to axial compressors [ NASA-CR- 116019 3 mi-19250 [NASA-CR-17431 n7i-17958 ' IIASS PLOU BATE IIESOSPBEBE Small curvature radiusfthroat radius ratio Besasphere and stratosphere data from hiqh level snpersonic nozzles mass flow rate coefficients observations for supersonic transport and at high Reynolds numbers, appraisinq isentropic reenterinq space vehicle operations flow prediction methods 171-21724 A71-19877 IIETAL PATIGOB IATBBIUS TESTS Axial compressor blades surface finish and fatigue Gas dynamic test stand for Cyclic thermal load streuqth restoration by vibrational tumhlinq testing of gas tnrbine engine materials and 171-20843 components at variable heatinq and coolinq rates HETAL FOILS and mechanical loads Coaposite plastic aircraft structures liqhtninq A71-20839 protection, considerinq hazard to composite IATBEIIATICAL IIODELS materials and use of metal filled or plasma Pressure wave distortion effects on combustor sprayed coatinqs and metal foil coverinqs aconstic mode instability based on model with a7i-19943 burninq rate related to Reynolds number HETAL SBEETS A71-19906 Swept liqhtninq stroke effects on aircraft design Alternate reduced order particle dynamics model in involvinq Ti and A1 sheets aircraft mission analysis featuring A71- 19936 instantaneously variable speed by time scale IIETALS separation Plastics and metals as construction materials in A71-19913 aircraft, missile and rocket design Hathematical model of nonstationary intake and A71-20044 exhanst gas motion in two cycle internal IIBTBOBOLOSICAL PLIS€lT combnstion enqine cylinders Spatial correlations between inside cunulus cloud 1171-20780 conditions and precipitation onset and intensity Iaproved feedback control of distributed parameter for modification experiments from aircraft systems for lunar landinq vehicle simulator penetration measurements [NASA-CR-1164821 871-17345 A71-21450 Systems analysis and mathematical model for air IIETBOEOLOGICAL PABAlBTEBS transportation desiqn Ueteoroloqical observations for terminal weather [NASA-CR-116431 J 871-17843 modification in aviation, noting airport fog Rathematical models for aerodynamic forces of dispersal aircraft tandem wings using liftinq line wing 171-21732 representation Reteorological effects on air transportation, [ ORERA-TP-891 J 871-18439 includinq atmospheric and runway conditions Bathematical model for aircraft liftinq surface 1171- 181 17 interference in steady or unsteady supersonic IIETBOBOLOGICAL BADAB flow Ueather outline qenerators for producing contours [ OAERA-TP-850 1 871-18462 around radar weather clutter for all weather air Hathematical models for control snrface wings in navigation subsonic unsteady flov r FAk-NA-7C-62J V71-17577 r ONERA-TP-889 ] N7 1- 18473 IBTEOBOLOGICU. SERVICES Quadratic performance index for YTOL aircraft Observational data characteristics analysis as model reference attitude control system contributor to knowledqe and utilization of all I UASb-TN-D-6231] n7i-ie836 atmospheric physical occurrences IIATBICES (IIATBEIIATICS) 871-21122 Kalman filter application as observer of IIBTEAUB observable siqnals derivatives, using gain water vapor condensation effects on methaneair matrix to minimize variance estimate for combustion gases for aerod7namic test medium instrument landinq systems [aIaa PAPER 71-2581 A71-21986 A71-21343 Comparison of hydrogen and methane as coolants in IIATEII HWHODS regeneratively cooled panels Periodically supported and damped closed circular r NASA-CR-1652 3 mi-19289 beam strwtnre. deternininq frequency response IETBOD OJ! CBABACTEBISTICS matrix Surface construction of body of revolution in A71-22026 supersonic gas flow from distribution of lEASOBIUG IUSTBOHElTS velocity vector modnlus along generatrix of Device for jet fnels antiwear properties body, usinq Prank1 method of characteristics measurement under rolling friction 1171-20089 A71-19493 IIETITL COIIPOOUDS Soviet book on foq. cloud and humidity measuring Kinetics of catalytic dehydrogenation of instruments, discussing artificial fog formation methylcyclohexane at 600, 650. and 700 deg P and and natural fog dispersion problems 5 atm pressure A71-20298 [ AD-7159261 1171-18729 IECIiANICAL IBSIIIEBBIlG IIICBOBLECTEOIICS lulticomponent plane flap mechanism with Uicroelectronic circuits reliability in aircraft transmission angles diverqinq minimally from enqine control applications, discussing testing ninety degrees. discussing synthesis by least and selection for severe temperature and squares method vibration environments 1171-19361 [SAE PAPER 7008221 171-21369 IIECHAlICAL IIIPEDAUCB IICBOUAVE AllTEllAS Optimal lininq impedance for jet engine inlet Planar microwave array antenna for scan duct, yieldinq discrete frequency. flow velocitr requirelent. discussing tilt angle and element and geometry on basis of minimum radiated power arranqement optimization A71-21661 rAIAA PAPEE 70-1911 A71-22030 IIKCEAlICAL PEOPBETIBS aIcuowmB EQOIWEIT lechanical properties of plastic composites with Integrated electro-optical microwave radar and boron, beryllium, silicon carbide and graphite laser /lidar/ sTstems for earth oriented, fiber reinforcement environmental and domestic applications [PLASTICS IUST. PAPER 291 171-20917 1171- 18027 Cobalt and nickel based alloy metallurqy for high V/STOL microwave scanuinq beam approach and

temperature gas turbine materials ~ landiuq system, describing qronnd and airborne n7i-17389 station equipment and operation 171-21680

A-35 MIDAIR COLLISIONS SUBJECT IUDEX

MIDAIR COLLISIONS MULTISPECTRAL BAED SCANUERS Aircraft midair collision avoidance, discussinq Statistical methods for inventory boundary Elimination Ranqe Zero system operation determination and data compression in automatic procedures and cost processing of multispectral scanner remote A7 1- 19079 sensor earth observations from aircraft and Midair collision hazards, incidents, and spacecraft recommendations for safe aircraft operations [AIAA PAPER 71-2341 A71-19711 N71-18103 MILITARY AIRCRAFT Development Proqram for multiple access real time N tactical information distribution system, UACELLES desiqninq and constructinq tactical air control Jet exhaust nacelle subsonic flow simulation system test facility r ARC-CP-111 1 ] N71-17113 rlrIAA PAPER 71-2431 A71-19718 IASA PBOGBAIS Rilitary aircraft zinc silver oxide battery Manned flight from Montgolfier Balloon to Apollo service requirements and performance 13, discussinq future space programs includinq A71-21103 lunar base and space shuttle MILITARY AVIATION A71-19417 Leqal aspects of military sonic booms, discussinq UATIOIIAL AIRSPACE UTILIZATIOR SYSTEM administrative remedies, liability and various Data communication role in National Airspace cases System, concerninq radar and flight data A71-21830 acquisition, intersystem transfer and voice MILITARY EELICOPTERS control Heiqht velocity /H-V/ fliqht testinq, qivinq [AIAA PAPER 71-2481 A71-19722 results from 08-588 Kiowa and AH-1G Huey Cobra IIAVIGATIOII AIDS helicopters manned aircraft crew lonq range naviqation, A71-19093 discussing sensor, information processing and Feasibility of electroluminescent panels and rotor display systems for future commercial and tip liqhtinq for military helicopters to aid in military missions observation by other vehicles in formation A71-20343 [ AD-7 15851 1 N71-18734 VPR flyinq under adverse weather conditions, IILITARY TECEUOLOGY discussing radio navigational aid equipment and Human role in Aerospace Defense Command communication with qround stations naviqation, discussinq Airborne Uarninq And A71-20683 Control system and naviqational aspects of ADC Shuttlecraft landinq and naviqational aid mission capabilities A71-20346 NASA-TM-X-66720 ] N71-18187 IIUIMUM DRAG UAVIGATIOS IUSTBOMEUTS Hypersonic minimum draq slender winq leadioq edqe Aircraft naviqation system requirinq computer and shape for qiven airfoil section, usinq Newtonian disvlav for avvroach quidauce to circular orbit theory over fixed qr.bind area 1171-22039 TAIAA PAPER 69-9861 1171-20305 MISSILE COUTROL Gyrocompass strapdown three coil synchro sensor Kalman-Bucy linear filterinq alqorithm application maqnetometer in conjunction with vertical qyro. to nonlinear estimation of sinqle channel eliminatinq azimuth detector inertial platforms missile attitude control system parameters A71-20340 A71-18835 UAVI IISSILE DESIGU Naval aircraft testinq, discussinq weapons Plastics and metals as construction materials in systems, funding commitments, outfittinq aircraft, missile and rocket desiqn schedules, time frames, contracts and manaqement A71-20044 problems MISSILE LAOUCRERS A71-19077 Launch and data reduction in supersonic wind IICKEL ALLOYS tunnel free fliqht testinq of hiqh fineness Plasma arc welding of jet engine components of Ti ratio bodies and Ni alloys, comparinq to gas tunqsten arc and [AIAA PAPER 71-2781 A71-22003 electron beam processes MISSIOU PLAUUIIIG A71-21684 Alternate reduced order particle dynamics model in Cobalt and nickel based alloy metallurqy for hiqh aircraft mission analysis featurinq temperature qas turbine materials instantaneously variable speed by time scale N71-17389 separation Thermal fatiaue behavior of fiber reinforced A71-19913 nickel alloy qas turbine blades IOLECULAE COLLISIONS N71-17390 Acoustic attenuation determined experimentally UOISE IUTEIISITY durinq enqine qround tests of XB-70 airplane and Noise nuisance value index /noise pollution comparison with predictions level/, considerinq aircraft and motor vehicle r NASA-TH-X-22231 N71-17951 noise surveys and tradeoff of intensity against MOLECULAR DIFFUSIOU duration Intensified molecular diffusion durinq turbulent A71-20802 mixinq of supersonic slipstreams in cylindrical Jet aircraft noise over residential areas, mixinq chamber. usinq optical Prudnikov method discussinq actual and permissible noise levels A71-19733 and propoLals for remedial action MOIEUTUI TRANSFER All-21163 Gas-particle mixture cascade flow Over turbine UOISE REDUCTIOU blades, considerinq momentum/heat transfer and Electrostatic charging noise measurement, particle tralectories reduction and fliqht test verification [AIIA PAPER 70-7121 A71-20311 A71-19937 MOTIOS STABILITY SST noise suppression research, discussinq engine Axisyimetric body rapid rotation under center of noise suppressor conceptual designs and test qravitv velocity vector conditions, solvinq for results with installed devices plane qlidinq motion stability in air k71-20302 A71- 19354 Aircraft optimum minimum noise takeoff profile. IOLTIPATB TBAIISMISSIOU solvinq by equations of notion system for jet Structures electromaqnetic scatterinq and aircraft multipath transmission effects on aircraft h71-20779 instrument landiuq system localizer signals, Eelicopter noise minimization by various piloting usinq computer proqran maneuvers, discussing takeoff and landing, A71-18831 transition to forrard flight, route selection. etc

A-36 SUBJECT IlDXI OPTICAL PIDAP

1171-21009 A71-21022 1 Jet aircraft noise over residential areas. IOXILl DBSIEl discussing actual and permissible noise levels High turbulent flow simulation in hypervelocity and proposals for remedial action uind tunnel for reentry vehicles operational A71-21163 testing, discussing nozzle gas dynamic and Q-Star experimental aircraft design and acoustical mechanical design characteristics to study Quiet Aircraft [ AIAA PAPER 71-253 J A 71-21 982 TeChnOlogy Performance of auxiliary inlet ejector nozzle with A71-21041 floating inlet doors and floating single hinge Boise abatement power cutback takeoff procedures. trailinq edge flaps maximum altitude approaches and preferential [ IASA-TB-1-2173 J 171-77554 rnuay systems for noise relief lOZLLll m1 A71-21813 Hind tunnel photography for determining water Subsonic jet engine noise reduction, considering droplet size in breakup of water jets turbojets. turbofans and jet suppressors [ AASA-CR-116820 1 n7i-18962 A71-21814 nozzle flow calibration in blowdown uind tunnel loise reduction at source. flight methods [ WEE-TB-HSA-171] 871-19170 adjustments and airport compatible land use for IOLILX 610SXrPI let noise abatement Transonic gas flous in axisymmetric small throat A71-21815 curvature radius Lava1 nozzle with appreciable Land use strategies and noise reduction by source flow parameters variation in transverse control and fliqht procedures for noise exposed direction areas minimization 171- 19732 A71-21818 Small curvature radius/throat radius ratio Community reactions to aircraft noise. discussing supersonic nozzles mass flou rate coefficients short term interim alleviation measures in at hiqh Reynolds numbers, appraising isentropic airport operations and runway usage scheduling flou prediction methods A71-21819 A71-19877 noise pollution control and airport noise levels Optimal design of rigid unadjustable contour for abatement regulation by state government. taking supersonic nozzle, taking into account vehicle into account economic and technical feasibility flight conditions A71-21825 A71-21865 Aircraft noise abatement control on international IUCLBAB PROPOLSO1 basis by setting acoustic technoloqical Economic and safety factors of nuclear pouered capability compulsory standards of qnietness surface vehicles and aircrafts in transoceanic A71-21826 commerce Federal legislation and regalatory activities for [ 1ASA-TB-1-52963 J 1171-18628 control and abatement of aircraft noise 1UBBPIC.I a1ALLISI.S A71-21827 numerical computation of viscous hTperSOniC flow Federal legislation and regulation of aircraft around slender bodies noise, legal rights of airport neighbors and N71- 16951 legal aspects of compatible land use. discussinq numerical analysis of low frequency subsonic noise control efforts lifting surface theory noting ring oscillations A71-21829 in steady flou Land use control in aircraft noise abatement. [ AEC-E/n-3634 J H71-18425 considering airport development and community goals A71-21836 0 Development of acoustic lining for turbofan OlBOAUD EQUIPIIElT nacelle modification to minimize fan compressor Zincsilver oxide batteries underwater and aerial noise radiation applications, designinq medium high rate long [BASA-CR-1712] 1171-17591 life cells Jet aircraft noise reduction near airports A71-21102 871-18079 OPBRATIlG SISTBIIS (COBPUTEUS) Subjective evaluation tests of ground observers on navy avionic modular multiprocessing digital relative noise from acoustically treated enqine computer operating system reliability, COBparing nacelles of Boeing 707 aircraft totally software and partly hardware approaches [ XASA-CE-17173 871-18499 171-18833 lOlBQUILIBUIUII COlDITIOlS OPBPATI16 TBIIPEUATUPB Noneguilibrium electron temperature, concentration Aerodynamic and thermodynamic performance of sweat and reflection in reentry boundary layers, cooled gas turbine engine blades discussing heat transfer and ionization energy 871-17382 dif f usion Temperature field measurements within convection [AIAA PAPER 69-82 J A71-19879 cooled rotor blade of gas turbine engine IOlBPUILIBUIUB IOIILATIOI 871-17387 Bonequilibrium electron temperature, concentration OPBPATIOlAL PXOBLBBS and reflection in reentry boundary layers, Technological aspects of film cooling for blades discussing heat transfer and ionization energy in high temperature gas turbines diffusion 871-17404 IAIAA PAPER 69-82J A71-19079 Survey of air traffic control radar beacon system Bonequilibrium multicomponent ionization operational problems calcnlations for stagnation merqed shock layer A71-18116 of hypersonic blunt body by successive OPERATOU PERFOUBAlCEB accelerated replacement Feasibility of visual tracking to determine effect [AIAA PAPER 69-6551 A71-19890 of lag in simulated aircraft dynamics 101LIIBAR SISTBBS [ 1111-E-479 J 871-18838 nonlinear control systems with transport laq, OPTICAL EQUIPIIElT obtaining parameter plane equations for LOW profile optical system producing annular cone stability analrsis of radiation from Point source for hiqh speed 171-20369 aircraft beacon lOlSIlCEBOlIZARO11 A71-19203 Bonsynchronous interroqatiou repetition frequency OPTICAL BBASUPI1G IISTRUBBITS selection methods applied to radar beacon Feasibility evaluation on optical probing of systems supersonic aerodynamic turbulence uith [ AD-7153351 871-17766 statistical correlation 871-17944 IOSL COIBS [ 11ASA-Tl-D-60771 Banometric equipment arrangement in nose cone of OPTICAL RADAR oriented satellite uith aerodvnamic system Inteqrated electro-optical microuave radar and stabilization laser /lidar/ systems for earth oriented,

1-37 OPTIMAL CONTROL SUBJECT INDEX

environmental and domestic applications [ PB- 1950451 N71-16990 A71- 18827 Tabulations for rapid transit system effect on OPTIMAL CONTROL airport traffic Aircraft collision avoidance dynamical system, [ PB-195049 3 N71-16991 determininq barriers between possible capture neobers attitudes on revisions to Uarsaw reqions by optimal control problem solution Convention and The Haque Protocol amendments on 871-21 322 liability to international air transport Optimal air traffic control coordinating flow and passenqers holdinq patterns of aircraft landinq in sinqle [ REPT-1970/8-E 1 N71-18100 runway usinq linear-quadratic technique PERFOREANCE PREDICTION A71-21335 Hiqh speed aircraft external store separation Supersonic airplane minimum time turns at constant testing and prediction techniques, considerinq altitude, determining thrust, bank anqle and flow field survey, dynamically similar drop anqle of attack programs with optimal control models and captive trajectory methods theory [AIAA PAPER 71-2941 A71-22014 A7 1-22032 Pliqht time, path and fuel consumption in climb at Quadratic performance index for VTOL aircraft constant radius turn, variable or constant model reference attitude control system velocity and constant enqine power, deriving I NASA-TN-D-62311 N71-18836 approximate simple formulqs OPTIIIZATION 171-22050 Aircraft optimum minimum noise takeoff profile, Heat transfer prediction for turbine blade desiqn solvinq by equations of motion system for jet N71-17374 aircraft Operational design criteria for gas turbine A71-20779 enqines Planar microwave array antenna for scan N71-17402 requirement, discussinq tilt anqle and element Helicopter application studies of variable arranqement optimization deflection thruster jet flaps rAIAA PAPER 70-1911 A71-22030 r AD-7150711 N71-17907 Desiqn optimization for cylindrical shell Acoustic attenuation determined experimentally subiected to reentry loads and heatina durinq enqine ground tests of XB-70 airplane and N71-18022 comparison with predictions ORDNANCE [NASA-TN-X-22231 N71-17951 External store surface pressure distributions Takeoff performance predictions for XB-70 delta durinq captive fliqht aboard P-48 aircraft, winq supersonic aircraft considerins carrying aircraft effects on flow r NASA-TN-X-2215] N7 1- 18509 field about airborne ordnance PERFORMANCE TESTS [AIAA PAPER 71-2951 A71-220 15 Terrain-followinq radar for TSR-2 aircraft, OSCILLATING FLOE discussinq reliability trials and improvement uind tunnel experiments on vortex shedding- from A71-19557 circular cylinders in oscillatinq free stream Low aspect ratio compressor blade cascade h71-19908 performance at blade span center, discussinq OVERPRESSURE pressure loss, anqle of attack and staggerinq Plane compression waves propaqation into constant A71-20624 state nonviscous fluid, considerinq shock Airline collision avoidance system test and formation of pressure pulses and overpressure as evaluation proqram. considerinq ranqe, rate and function of time altitude accuracy, communications reliability, A71-19961 synchronization and system inteqration with air traffic control 1171-21167

P Performance test methods and equipment for PANEL FLUTTER aircraft avionics and weapons systems, Flutter analysis of stressed flat simply supported discussinq computer inteqration with radar and skew panels in supersonic flow, usinq small phototheodolite ranqe instrumentation system deflection thin plate theory A71-21660 A71-21302 Semiscale blowdown and emerqency core cooling PANELS project test report Ribbed aluminum panels airborne sound transmission [ IN-13931 N71-17190 loss, evaluatinq structural damuina effects Performance of aluminide coatings in simulated A7 1-21 431 hiqh temperature tests on qas turbine enqine PARACEUTES inlets Parachute weiqht, confiquration and strenqth r NASA-CR-116374 1 N71-17393 correlations for tradeoffs and deeiqn Performance of axial flow compressor for Brayton A71-18900 cycle electrical power qeneratinq system with Low speed wind tunnel stability tests of small arqon quide surface, slotted solid, rinq slot, cross [ NASA-TM-X-2194 1 N71-17882 and streamer decelerators, considerinq Hypersonic shock tunnel of AFAPL

parachutes and draa measurement~~ [ AD-7159071 N71-18717 A71-20310 Desiqn and tests of UTF-48 sinqle rotor compressor PARALLEL PROCESSING (COEPUTERS) enqine Navy avionic modular multiProcessina diaital,~ r AD-7156261 N71-18801 computer operatinq system reliability. comparinq PERSONNEL SELECTION totally softwarp and partly hardware approaches Employment opportunities for economists and air A71-18833 transportation analysts with Civil Aeronautics PILRTICLE SIZE DISTRIBUTION Board wind tunnel photoqraphy for determininq water N71-17798 droplet size in bieakup of water jets Surveyinq air traffic controller occupation and TNASA-CR-1168201 N71-18962 development of performance objectives PARTICLE TRAJECTORIES N71-18105 Gas-particle mixture cascade flow over turbine PETSIOLOGICAL EFFECTS blades, considerinq momentum/heat transfer and sonic boom effects on human physioloqy and particle tralectories behavior and structures, based on theoretical [AIAA PAPER 70-7121 A71-20311 studies and simulators Laser Doppler velocimetric technique for A71-21812 supersonic flow particle traiectory and density PILOT ERROR measurements, notinq particle laq Investigating aircraft crash landinq cgused by rAIAA PAPER 71-2871 A71-22010 enqine failure and aircrew errors PASSENGERS [ NTSB-AAR-70-17 1 N71-17063 survey of rapld transit railway impact on airport PILOT PERFOREANCE passenqer traffic U.S. domestic ATC airspace enroute and terminal

A-38 SUBJECT IUDEI PRESSURE IEASUEEIIEUTS

area naviqation system effects on pilot derivation workload, proiectinq future FAA requirements [AIAA PAPER 71-2701 1171-21996 A71-20347 POSITIOI IIDICATOBS Glider flight in thermal air currents, discossinq Describinq auqular position and velocity sensinq aircraft behavior, pilot sensory perceptions and a ppar atus reactions and use of variometers for ascent rate r NASA-CASE-XGS-05680 J N71-17585 determination POTEITIAL FLOP A71-20685 Eonoqraph on transonic shock free potential flow Helicopter noise minimization by various pilotinq around quasi-elliptical airfoil sections. maneuvers, discussinq takeoff and landing, investiqating flow stability under unsteady transition to forward fliqht, route selection, disturbances etc h71-19773 171-21 049 Potential flow past cylinder with sources and Functional requirements for qround-based trainers, sinks sinqularities. deriving foraulas for helicopter response characteristics aerodynamic characteristics of infinite span IAD-714954 J N71-18018 winqs with bouudarv layer control PIPES (TUEES) 1171-20777 Wind tunnel aerodynamic stability tests on Sinqularitv method for calculation of potential chimners with pipes and helical windiuq flow around arisymmetric rings stabilizers N71-18469 [NPL-AERO-13101 N71-17334 PRECIPITATIOI (RITEOROLOGT) PITCBIUG BOIIEllTS Spatial correlations between inside cumulus cloud Lift. pitchinq moments and dampinq of delta winqs conditions and precipitation onset and intensity in slotted transonic wind tunnels with for modification experiments from aircraft perforated walls penetration measurements TNPL-AERO-13071 W71-17085 A71-21450 PLAIFORIS PREDICT101 AUALTSIS TECRUIQUES Vortex-lattice FORTRAN program for estimatinq Data processing and impact analysis on rapid rail subsonic aerodynamic characteristics of complex access system for airport planforms r PB-195047 J 171-16988 [NASA-TN-D-6142 J N71-17424 Enqiueering methods for predictinq temperatures PLASBA ARC PELDIUG and velocities in vicinity of vertical lift Plasma arc welding of jet enqine components of Ti enqines of iet V/STOL aircraft operating near and ui alloys. comparinq to gas tungsten arc and qrouud electron be35 processes r ~lasa-tfi-ii38451 x7:- 18714 A71-21684 PRESSURE DISTRIBUTIOU PLASTIC AIRCRAFT STRUCTURES Caret winq serial tests in nach 8 to 15 hypersonic Liqhtninq protection for nonmetallic helicopter flow, including three component force, spanvise rotor blades direction pressure distribution and shock rave A7 1-19939 angular measurenents by flow visualization Composite plastic aircraft structures liqhtninq 171-20015 protection, considerinq hazard to composite Inverse boundary value problems in materials and use of metal filled or plasma hvdroaeromechauics. involvinq profile sprayed coatinqs and metal foil coverinqs construction from given velocity or pressure A71-19943 distribution and supersonic flow boundaries PLASTICS determination riasrics and netals as construction materials in 1171-20078 aircraft, missile and rocket design Jet propulsion optimization by exerqy and anergy Al1-2001)4 for minimum total cost flux by varyinq unit PLATES compressor pressure ratio Continuous flow past plate located perpendicular A71-2 1300 to wall with inviscid incompressible fluid External store surface pressure distributions havinq linear variation of velocity with heiqht during captive fliqht aboard P-9B aircraft, A71-20828 considerinq carrying aircraft effects on flow PUEUIATIC COllTROL field about airborne ordnance Fluidic pressure ratio control for vertical [AIAA PAPER 71-2953 1171-22015 takeoff aircraft lift enqiue fuel system, Aerodynamic coefficients, pressure, load and force describing breadboard circuit, test bed and distributions on cambered delta uinqs fliqht standard r ARC-CP-1129 1 N71- 17 112 A71-20587 Static pressure contours of turbine rotor blade PODS (EXTXRUAL STORES) tips at hiqh aach numbers Wind tunnel testing of aerodynamic interactions I UASA-TI-X-2170] 871-17247 between aircraft and jettisoned loads using Technique of extrapolating measured near-field trajectory analysis overpressure data to larger altitude applied to [ ONERA-TP-849 1 N 7 1- 1896 4 wind tunnel overpressure data POIUT SOURCES [ NASA-TI-X-2219 J N71-18559 Low profile optical system producing annnlar cone nozzle flow calibration in blovdovn wind tunnel of radiation from point source for hiqh speed [ ERE-TN-BSA-171 J R71-19170 aircraft beacon PRBSSURE EPFECTS A71-19203 Impact cooliuq method for turbine rotor blades POIUTIIG COUTROL STSTEIIS N71-17397 Passive airborne computer augmented aircraft PRESSURE GRADIEITS antenna pointing control system for Pressure qradient effects on three dimensional communication satellites tracking turbulent boundary layer of infinite span [AIAA PAPER 71-2333 A71-19710 sweptbact winq POLAR RXTEOROLOGT [ UPL-?.ERO-1305] N71-17179 Commercial aviation stratospheric water vapor Determiuinq feasibility of increasinq stator blade injections influence on radiation bodqet. ozone, loading of single staqe compressor riq by polar niqht cloudiness and potential climatic bleedinq or blowinq suction surface boundary effects layer A71-21822 [ UASA-CR-54573] N71-18749 POROUS RATERIALS PRESSURE BEADS Plow characteristics of vire-form and Suction and pressure head and temperature effects laminate-form porous materials on cavitation flow in aircraft fuel pumps r UASA-TI-1-2111 J N71-17130 [ ARC-CP-1128] 1171- 17044 PORTS (OPBUSlGS) PRESSURB BEASUBBBEITS Static pressure port errors in hrpersonic Turbulent boundary layer pressure fluctuations turbulent flou, using approximate shear layer in-flight measurements on Boeinq 737 aircraft, moaentum balance for pressure increase obtaining power spectral densities and RIS

A-39 PRESSURE PULSES SUBJECT IUDEI

pressure fluctuations for various Hhih numbers PROPULSION SYSTEM COHPIGURATIOUS A7 1-2 1426 Ground effect vehicles limitinq volumetric static pressure port errors in hypersonic dissipations from air cushion and propulsion turbulent flow, usinq approximate shear layer systems with fluid boundary by Coanda effect momentum balance for pressure increase A71-19923 derivation Lift fan propulsion for civil VTOL transports, [AIAA PAPER 71-2701 A71-21996 considerinq applicability, attitude control, Error analysis for pressure measurements on system desiqn, fan transition and cross flow blowdown supersonic wind tunnel models noise r NPL-AERO-13061 N71-17081 A71-20373 Lou speed wind tunnel pressure and audio frequency Composite rocket cum hypersonic airbreathing resonance measurements on circular cylinders and propulsion reducing space exploration program thin flat plates cost [NPL-AER0-13111 N71- 17089 A71-21301 Base pressure measurements on XB-70 aircraft at Air cushion vehicle technoloqy, considerinq Hach numbers from 0.4 to 3.0 economics, propulsion, structures. r NASA-TH-X-16121 N71-17132 controllability, flexible skirt systems and R Pressure measurements of flow induced cavity and D resonance and effects of resonance suppressinq [SAE PAPER 7101831 171-21713 devices PROPOLS101-~ SISTEH PERPORHAUCE r NASA-TN-D-62053 N71-17877 Aerospace Recommended Practice for gas turbine Technique of extrapolatinq measured near-field engine steady state performance presentation for overpressure data to larqer altitude applied to diqital computer programs, describing enqine wind tunnel overpressure data type, operatinq and control characteristics INASA-TH-X-22191 N71-18559 SAE-ARP-68181 A71-19647 PRESSURE PULSES Effects of turbojet enqine unstart on enqine Plane compression waves propaqation into constant operation and characteristics of stall state nonviscous fluid, considerinq shock propaqation throuqh compressor and inlet system formation of pressure pulses and overpressure as r NASA-TH-X-2192 J N71- 18138 function of time PROPULSIVE EPPICIEICT A71-19961 Fuel consumption and propulsive and thermodynamic PRESSURE REGULATORS efficiency comparisons for ships, hydrofoil Pressure requlator desiqn and construction, usinq craft, helicopters, jet aircraft, aud ground hiqh pressure fluidic proportional chain effect machines A71-20580 r UPL-HOVERCRAFT-121 171-17161 PRESSUEE SEISORS PROTECTIOU Hiqh performance fiqhter aircraft euqine pressure Haterials and construction techniques in liqhtninq ratio and turbine inlet temperature measurenent, protection for aircraft and helicopters usinq fluidic sensors A71-19930 1171-20586 Liqhtninq protection for nonmetallic helicopter PRESSURIZED WATER REACTORS rotor blades Semiscale bloudoun and emerqency core coolinq A71-19939 project test report Liqhtninq protection for dielectric composites, [IN-1393 J N71-17190 analyzinq damaqe from shock waves, vaporization PPOBABILITI TEEORI pressure, maqnetic forces and burninq Liqhtninq stroke probability model for point A71-19942 selection on aerospace vehicles PROTECTIVE COATINGS A71-19928 Composite plastic aircraft structures lightninq Probabilistic estimate of aerodynamic imbalance of protection, considering hazard to composite aircraft qas turbine rotors due to production materials and use of metal filled or plasma errors in compressor blade anqle sprayed coatings and metal foil coverings 871-22045 A71-19943 PRODUCT DEVELOPIEUT Lightninq protective coatinqs for boron and BD-1 Yankee aircraft development, desiqn and qraphite fiber reinforced plastics construction A71-19944 A71-19084 Development of thermal insulation system for wing PRODUCT101 EUGIIEERING and control surfaces of hypersonic aircraft and Automation of technoloqical processes in aircraft reentry vehicles enqine production [NASA-CASE-XLA-008921 N71-17897 IAD-7148581 N71-17832 PUlPS PEOJECT HANAGEIEUT Aircraft qear pumps bearing elements design for P-15 air superiority fiqhter, describing military increasinq service life requirements, proqram manaqement and procedures A71-20793 in terms of speed, maneuverability, acceleration Thernal numc-comDressor.. for convertina solar and weaponry euerqy A71-19078 [ NASA-CASE-XLA-003771 N71-17610 Inteqrated project information and simulation PIRAIIDAL BODIES system for manaqement of aerospace vehicle Aerodynamic characteristics of conical and development, discussinq simulation models pyramidical configurations with various application planforms by slender body theory. replacinq [AIAA PAPER 71-2383 1171-19714 three dimensional flow by two dimeusional flow PEOJECTILES 1171-20776 Trajectories prediction for subsonic spin PIROTECEUICS stabilized projectiles via water tunnel tests, lass loadinq effects on pyrotechnic shock considerinq blunt nose and tail and rounded nose environment of aerospace systems riqht circular cylinders NASA-CR- 1160191 1171-19250 rAIAA PAPER 71-2961 A71-22016 PROPELLAUT STORAGE Jet fuels thermal stability and corrosive R properties durinq prolonged storaqe EADAE APPROACE COITROL A71-19492 V/STOL microwave scanning beam approach and PROPELLERS landing system, describins ground and airborne Experimental arrangement for delay times in station equipment and operation propeller/rpm controller system- A71-2 1680 A71-20832 EADAR BEACOIS PROPORTIOIIL CORROL sonsynchronous interrogation repetition frequency Pressure requlator desiqn and construction, usinq selection methods applied to radar beacon hiqh pressure fluidic proportional chain Systems A71-20580 f AD-7153351 N71-17766

A-40 SUBJBCT IIDEI PEEITBY TBlJECiOBIES

Survey of air traffic control radar beacon system [ AD-7151001 171-17906 operational problems RAMET EIGXIBS 171- 18116 Effect of tailpipe length on combuster stability RADAR DATA in ramjet combusters Data communication role in lational Airspace 871-17725 System. concerning radar and flight data B11Wll EBROPS acquisition. intersystem transfer and voice Random errors in aluminum alloy fatique tests and control failure .odes [AIAl PAPER 71-2483 171-19722 [ ARC-CP-l123] 171-17330 RlDlP EPUIPIIElT E1161 IIIDERS

Terrain-followina radar for TSB-2 aircraft. Alaorithm for diuital resolution of ranae~~ for discussing reliability trials and improvement ~/STOL aircrafi 171- 19557 [UlSl-TI-D-6232] 171-18566 System description of field test model of ARTS 2 RAPID TEAISIT SXSTBES modular alphannmeric nontracking ATC system Examining tracked air cushion vehicles as advanced 171-18815 ground transportation system RADAR IlTI6ATIO~~.___._ [ PB-l95030] 171-16904 ATC automated systems, discussing national Data processing and impact analysis on rapid rail airspace system En Route Stage A and Advanced access system for airport Radar Terminal System r~~-i950471 n7i-16988 [AIAA PAPER 71-2441 171- 19719 Data recordinqs and computer codes for airport RADIAL ?LOP rapid transit access system study Radial flow energy losses in rotating cylindrical [ PB-1950483 171-16989 cascade of inuard-flou turbine uheel. Survey of rapid transit railway impact on airport determininq_. profile losses and exit blade anale passenger traffic A71-22044 [ PB-195C451 171-16990 Axial-radial and radial cospressor stage optimum Tabulations for rapid transit system effect on exit blade angle, considering flow rate control airport traffic by variable pitch nozzle gnide vanes r PB-1950491 1171-16991 A71-22049 Rapid transit railuay effect on airport passenger Design and component testing of cooled radial gas traffic turbine engine r~~-i950461 171-16992 171- 17381 BElCTIOl KIIETICS RlDIlTIOI ABSOPPIIOI Kinetics Jf catalytic d&iydrogenation of Interaction between radiation from shock uave methylcyclohexane at 600. 650, and 700 deq P and region and oncoming cold air flow in hypersonic 5 at. pressure flow past blunt body [ AD-7159261 171-18729 171-19730 BBlCToB corns PADIATIOI DISTPIBUTIOI Semiscale blowdoun and emergency core cooling Lou profile optical system producing annular cone project test report of radiation from point source for high speed [ IR-13931 n7i-17190 aircraft beacon BEACTOB SAFETY A71-19203 Semiscale blowdorn and emergency core cooling RlDIlTIOl SPXCTPA project test report Acoustic radiation spectra from turbulent jets, [ 11-13931 171-17190 assuminq approximate Gaussian statxstxcs and REAL BASSS second order velocity correlation space-time Real gas effects on drag and trajectories of characteristics obtainable from frozen flow nonlifting conical shell during Ears atmospheric A71-19959 entry RADIO FBEPUBICY IITEBFEBEICE [ NASA-TN-D-62401 mi-18015 Lightninq and static electricity effects on REAL TIllE OPEBATIOI helicopter desiqn, considerinq rotor protection, Development program for multiple access real time carqo hook operation and passive dischargers for tactical information distribution system. radio interference reduction designing and constructing tactical air control A71-19938 system test facility BAD10 lAVI6ATIOI [AIAA PAPER 71-2431 171-19718 Aircraft radio compass navigation errors due to BECTAIGULAB GUIDES loop antenna inclinations durinq maneuvering Large aspect ratio rectangular duct with A71-20787 nonnniform surface texture. investigating PAD10 PECEIVEPS turbulent flow. maximnm velocity positions and Aircraft automatic landing improvement through use zero shear stress of space diversity ILS receivinq system A71-18772 171-18830 PBCTAIGULAR SIID TU111LS RAIL TRlISPOUTlTIOI Return circuit rectangular wind tunnel design. Data processing and impact analysis on rapid rail constroction. instrumentation and calibration. access system for airport discussing drive. jet inclination, velocity [ PB-1950471 871-16988 distribution, etc Data recordings and computer codes for airport A71-21305 rapid transit access system stnay PSIITBY [ PB-1950481 1171-16989 Nonequilibrinm electron temperature, concentration Rapid transit railuay effect on airport passenger and reflection in reentry boundary layers, traffic discussinq heat transfer and ionization energy [PB-195046] n7i-16992 diffusion Public transportation in airport access systems [AIAl PAPEE 69-82] A71 - 19879 171-18951 BllRlTBY EFFECTS nass transport systems for airport access Desiqn optilization for cylindrical shell n7i-18952 snbjected to reentry loads and heating Public transportation requirements for Eeathron A71-18022 Airport RBBITPY PBYSICS 871-18954 mesosphere and stratosphere data from high level Cleveland rapid rail transport system to Eopkius observations for supersonic transport and International Airport reentering space vehicle operations 1171-18956 A71-21724 Existing access systems for Logan International BS31TBI TBAJXCrOPIES Airport. and Plans for improvement Examining three-dimensional motion of flyina 171-1 8957 vehicle entering atmosphere at low angles of BAIIDBOPS attack International conference on rain erosion and 171-16901 associated phenomena

A-4 1 REEUTRY TERICLES SUBJECT INDEX

REENTET VEHICLES RESEARCE FACILITIES Aiqh turbulent flow simulation in hypervelocity Bypersonic shock tunnel of APAPL wind tunnel for reentry vehicles operational [AD-7159073 871-18717 testinq, discussinq nozzle qas dynamic and RESIDUAL STRESS mechanical desiqn Internal loads and stresses caused by space rAIAA PAPER 71-2531 A71-21982 vehicle vibration resulting from induced or Bessel function solutions for low angle of attack natural environments approach of flying vehicle to atmospheric [ NASA-SP-8050] N71-19281 boundary and transition into vibrational motion RESOUAUCE N71-16983 Lor speed wind tunnel pressure and audio frequency REFRACTORY MATERIALS resonance measurements on circular cylinders and Advanced coolinq systems and heat resistant thin flat plates N71-17089 materials for turbine blades of hiqh temperature [NPL-AERO-13117 aeronautical qas turbine engines EBSOUANT FREQUENCIES AGARD-CP-73-71] N7 1- 17 37 2 Pressure measurements of flow induced cavity EEFRACTORY METAL ALLOTS resonance and effects of resonance suppressinq Thermal control coatinqs for refractory qas devices N71-17877 turbine materials [ NASA-TN-D-62051 N71-17391 REVERSED PLOP REFUELING Cross flow profiles for compressible turbulent Static discharqe hazards for aircraft, discussinq boundary layers with and without flow reversal causes for static charqe build-up, danqers and via hodoqraph models family precautionary methods durinq refuelinq A71-22033 operations RETUOLDS NUMBER A71-19424 Small curvature radius/throat radius ratio REGEUERATIVE COOLING supersonic nozzles mass flow rate coefficients Desiqn and component testinq of cooled radial qas at hiqh Reynolds numbers, appraisinq isentropic turbine enqine flow prediction methods A71-19877 N71-17381 Comparison of hydroqen and methane as coolants in Sphere and disk drag measurements for Reynolds reqeneratively cooled panels numbers from 5 to 100,000. examininq forces, [NASA-CR-16523 N71-19289 moments. flow visualization, unsteady modes and REGRESSION AUALTSIS constant acceleration A71-19893 Sea state, wind velocity and wind direction reqression analysis for qrounC effect machines Computer calculation of hiqh Reynolds number r NPL-HOVERCRAFT-16 1 N71-17144 viscous and inviscid flow over arbitrary shaped EEIUPORCED PLASTICS two dimensional bodies and airfoils Liqhtninq protective coatinqs for boron and A71-20313 qraphite fiber reinforced plastics RIBS (SUPPORTS) A71-19944 Ribbed aluminum panels airborne sound transmission Mechanical properties of plastic composites with loss, evaluatinq structural dampinq effectsA71-2 1431 boron, bervllium, silicon carbide and qraphite fiber reinforcement RIGIDITY [PLASTICS INST. PAPER 291 A71-20917 Aircraft systems assembly methods, discussinq REIIPORCING FIBERS riqidity effects on error redistribution in Liqhtainq protective coatinqs for boron and external and internal force field application qraphite fiber reinforced plastics A71-20792 A71-19944 RIUG STRUCTURES Filament windinq manufacturinq methods usinq Sinqularity method for calculation of potential unidirectional qlass reinforcements for desiqn flow around axisymmetric rinqs N71-18469 and fabrication of aircraft winq structure [ SME PAPER EM-70-406 1 1171-20546 ROCKET EUGINE DESIGN Mechanical properties of plastic composites with Plastics and metals as construction materials in boron, beryllium, silicon carbide and qraphite aircraft, missile and rocket desiqn fiber reinforcement A71-20044 rPLASTICS INST. PAPER 291 1171-20917 ROCKET LAOUCHING Cost aspects of carbon fiber reinforced composites Rocket/launcher aerodynamic interference effects in aircraft structures, suqqestinq increased investiqation by wind tunnel simulation, aviation market for carbon fiber determininq interference coefficients for [PLASTICS INST. PAPER 461 A71-20929 rockets ballistic dispersion calculations Thermal fatique behavior of fiber reinforced [AIAA PAPER 71-2691 A71-21995 nickel alloy qas turbine blades ROLLIUG COUTACT LOADS N71-17390 Device for jet fuels antiwear properties RELIABILITY measurement under rollinq friction Terrain-followinq radar for TSR-2 aircraft, A71-19493 discussinq reliability trials and improvement ROTARY PINGS A71-19557 Liqhtninq and static electricity effects on RELIABILITY ENGINEERING helicopter desiqn, considerinq rotor protection, Navy avionic modular multiprocessinq diqital carqo hook operation and passive discharqprs for computer operatinq system reliability, conparinq radio interference reduction A71-19938 totally software and partly hardware approaches A71-18833 Liqhtninq protection for nonmetallic helicoptrr REMOTE SENSORS rotor blades Statistical methods for inventory boundary A71-19939 determination and data compression in automatic Boundary layer discontinuity on helicopter roter processinq of multispectral scanner remotp blade in hoverinq usinq flow visualization sensor earth observations from aircraft and [AIAA PAPER 69-1971 A71-20307 spacecraft Helicopter application studies of variable [AIAA PAPER 71-2341 A71-19711 deflection thruster jet flaps RESCUE OPERATIONS [AD-7150711 N71-17907 Surveyinq crash fire and rescue equipment at North Effectiveness of anti-torque aerodynamic surfaces American and Canadian airports immersed in helicopter rotor downwash N71-18101 [AD-7154381 N71-18937 RESEARCH AIRCRAFT ROTATING BODIES Q-Star experimental aircraft desiqn and acoustical ~~isymmetricbody rapid rotation under center of characteristics to study Quiet Aircraft qravity velocity vector conditions, solvinq for Technoloqy plane qlidinq motion stability in air A71-21441 A71-19354

A-b2 SIeJECT INDEX SERVICE LIFE

POTATIBG DISKS airfoil and Prandtl lifting line theories Fabrication of cobalt alloy and nickel alloy gas 171-20303 turbine blades and disks SALIBITY N71-17392 Airborne surveillance for environsental ROTOR AERODYIAEICS nanaqement, discussinq earth resources proqram, Aerodynamic synthesis of helicopter rotor under aerial sensors for thermal water pollutioo. crop hover and vertical ascent conditions, using disease. salinitv and aeoloaical-~ structure nonlinear vortex approach A71-19080 1171-19740 SATELLITE OBSERVATIOB Probabilistic estimate of aerodynamic imbalance of soundinq system constant level superpressure aircraft gas turbine rotors due to production balloons for atmospheric circulation qlobal errors in compressor blade angle description at all levels and latitudes in 171-22045 coniunction uith satellite observations BOTOR BLADES 1171-21742 Transonic compressor rotors blade camberline shape SATELLITE ORIEFTATION optimization by varions tip diffusion lanometric equipment arranqenent in nose cone of factor-ratio combinations oriented satellite uith aerodynamic system 171-20200 stabilization Boundary layer discontinuity on helicopter roter A71-21022 blade in hovering nsinq flov visualization SATELLITE TBACKIBG [AIAA PAPER 69-1971 A71-20307 Passive airborne computer augmented aircraft ROTOR BLADES (TOEBOIIACEIIERr) antenna pointinq control system for Static pressure contours of turbine rotor blade comnnnication satellites trackinq tips at hiqh Mach numbers fAIr4 PAPER 71-2331 871-19710 [NASA-TR-X-2170 J 1171-17247 SCALE IIODELS Temperatnre field measurements within convection Airfoil profile draq aeasnrements, correlating cooled rotor blade of gas turbine enqine full scale fliqht tests and scale sodel tests in N71-17387 transonic and high Reynolds number wind tunnels Impact cooling method for tnrbine rotor blades [AIAA PAPER 71-289 J A71-22012 R71-17397 SCANIERS Beat transfer and thermal stress calculations for V/STOL microwave scanning beaa approach and qas turbine rotor blade desiqn landing system, describinq ground and airborne N71-17401 station equipment and operation ROTORS A71-21680 Jet engine rotor strain and temperature data Selection of scanning systems for aircraft thermal transmission, ezamining special purpose viewers telemeters desiqn N71-19220 A71-19628 SCELIEREN PEOTOGBAPEI Describing anqular position and velocity sensing Multiple source schlieren system for flov apparatus visualization in Canadian trisonic wind tunnel. [NASA-CASE-XGS-O568OJ N71-17585 nsinq inteqrated logic circuitry for control RONllAY COIDITIONS A71-19924 Runvay deicing methods, discnssinq spreadinq of SEA STATES chemicals by qround vehicles and aircraft sea state, vind velocity and vind direction A71-19425 regression analysis for ground effect machines Poq r-moval by hioh power carbon dioxide lasers, I NFL-BOVERCRAPT-16 J N71-17144 evaluating possihilitT of clearinq airport SBAPLANES runvays Seaplane step /flat plate/ ricochet off ideal lAIAA PAPER 69-6703 A71-20308 incompressible flnid surface, determining free Noise abatement pover cutback takeoff procedures, surface shape by accountinq for trailing maximum altitude approaches and preferential vortices effects runway systems for noise relief A71-19355 A71-21813 SECONDARY INJECT101 Meteorological effects on air transportation, Performance prediction for turbine blade film includinq atmospheric and runvay conditions cooling with injection tbrouqh holes ~71-18117 [NASA-CR-1163763 N71-17388 RINIIAYS SELF ADAPTIVE COITBOL SYSTEES Ingestion of debris into aircraft engine inlets Plight tests to determine reliability of X-15 self diiiinq takeoff adaptive flight control system [ ARC-CP-11141 N71-17084 [ NASA-TN-D-62081 N71-18422 SEESOBS Manned aircraft crev long ranqe navigation, S discussing sensor, information processing and SAFETY DEVICES display systems for future commercial and Aircraft midair collision avoidance, discussinq military missions Elimination Ranqe Zero system operation A71-20343 procedures and cost SBPABATED FLOW 171- 19079 Blunt cylinder uith small thread in anomalous Cargo aircraft crew safety and snrvival, seeded flow in hypersonic wind tunnels, describing restraint, escape, fliqht deck observing separated shock wave distortion interior doors, fire and smoke hazards and 171-18924 personnel environmental protection Tvo link approximation of Chaplyqin function by [ SAE-ARP-1139 J A71-19643 coupling to integral equations, applying to SAFETY FACTORS ideal gas jet separation flov past symmetrical Surveying crash fire and rescue eqnipaent at North arc American and Canadian airports A71-20084 N71- 18101 wake blockaqe corrections for rectangular flat Economic and safety factors of nuclear powered plates subjected to separated flow in closed surface vehicles and aircrafts in transoceanic vind tunnel commerce [ ARC-R/U-3649 3 N71-18456 [ NASA-TI!-I-52963 J 871-10628 SBEVICE LIFE SAILS Aircraft qear pnmps bearing elements design for Rectangular and caret vinq sails in supersonic and increasing service life hypersonic tnrbulent flow for hypersonic A71-20793 vehicles Zinc-silver oxide batteries undervater and aerial IARC-R/I-3624] N7 1-17 103 applications, designing medium hiqh rate long SAILPISGS life cells Sailsinq aerodynamic characteristics, obtaining 171-21102 aerodynamic loading by two dimensional flexible

A43 SEEAR LAYERS SUBJECT IUDEX

Hilitary aircraft zinc silver oxide battery 1171-21925 service requirements and performance Supersonic flou with separated shock wave past A71-21103 wedqe shaped profile Complex airframe desiqn for economic and safe [ NASA-TT-P-13469 J N71-17443 operation and lonq life using fatique and Semi-empirical determination of adiabatic fracture mechanics efficiency of supersonic compressor staqe [AIAA PAPER 70-5121 A71-22025 [ AD-715005] N71-18036 SEIAR LAYERS Reqions upstream and downstream from shock waves Static pressure port errors in hypersonic of airfoils in uniform and transonic flow turbulent flow. usinq approximate shear layer [ NASA-TT-F- 13472 J N71-18401 momentum balance for pressure increase SEORT TAKEOFF AIRCRAFT derivation ARAVA STOL aircraft, describing payloads, [AIAA PAPER 71-270J 1171-21996 confiquration, desiqn flight testinq, stability SEIPS and landinq characteristics Fuel consumption and propulsive and thermodynamic A71-19082 efficiency comparisons for ships, hydrofoil Ground boundary layer effects of fixed qronnd craft, helicopters, jet aircraft, and qround plane for powered STOL wind tunnel model, effect machines discussinq flow breakdown criteria, contraction [ NPL-HOVERCRAFT-121 N71-17161 laq, strut fairing interference, etc SEOCK DISCONTIUUITY rAIAA PAPER 71-2661 A71-21992 Unsteady analoqy for hypersonic flows past blunt Pliqht characteristics of jet-flap STOL transport bodies with shock deformation aircraft during approach and landinq A71-21863 [NASA-TN-D-62253 N71-17433 SEOCK FROUTS Proposed STOL operations in Northeast Corridor Shock wave interaction with wedqe movinq at with respect to air traffic control supersonic speed, calculatinq qeometry of N71-17963 reqions forned intersectinq wavefronts Feasibility of inter-metropolitan transport system A7 1-1 974 1 usinq Brequet 941 STOL aircraft SEOCK LAYEBS [ REPT-50 J N71-18104 Nonequilibrium multicomponent ionization SIGUAL PROCESSIMG calculations for staqnation merqed shock layer Kalman filter application as observer of of hypersonic blunt body by successive observable siqnals derivatives, using qain accelerated replacement matrix to ninimize variance estinate for [AIAA PAPER 69-6551 171-19890 instrument landinq systems Investiqatinq supersonic viscous qas flow around A71-21343 blunt bodies SILTIR ZIUC EAlTIRIES U71-16902 Silver zinc batteries and cells case cover SEOCK LOADS materials and sealinq techniques for space Bent structure failure Under pulse floor missions acceleration shocks, concerninq aircraft seat A71-21097 damaqe durinq crash landinq Zinc-silver oxide batteries underwater and aerial A71-20747 applications, designing mediun high rate lonq SEOCK SPECTRA life cells lass loadinq effects on pyrotechnic shock A71-21102 environment of aerospace systems nilitary aircraft zinc silver oxide battery NASA-CR- 116019 1 N71-19250 service requirements and performance SEOCK TUBES A71-21103 Solid particle impurity effects on hypersonic SIIIOLATIOI shock tube flow. determininq error in blunt body Rocket/launcher aerodynamic interference effects measurements investiqation by wind tunnel simulation, 871- 18916 determininq interference coefficients for SEOCK WAVE GENERATORS rockets ballistic dispersion calculations Plane compression waves propagation into constant [AIAA PAPER 71-2691 A71-21995 state nonviscous fluid, considerinq shock Neasurements and analysis of lightninq-induced formation of pressure pulses and overpressure as voltaqes in aircraft electrical circuits function of time r NASA-CR-1744 J N71-19122 A71-19961 Mathematical model of larqe let transport aircraft SEOCK WAVE IUTERACTIOU simulation Interaction between radiation from shock wave r NASA-CR-1756 1 N71-19239 reqion and oncominq cold air flow in hypersonic SIIGL's-PEASE PLOW . flow past blunt body Closing shock position in supersonic underexpanded 1171-19730 sinqle and two phase jets, determining liquid Shock wave interaction with wedqe moving at phase concentration effects on Mach number and supersonic speed, calculatinq qeometry of nozzle pressure in wind tunnel reqions forned intersecting wavefronts A71-21925 171-19741 SIIGULAEITI (IIATEEEITICS) SEOCK WAVE PROFILES Potential flow past cylinder with sources and Caret wing serial tests in Mach 8 to 15 hypersonic sinks sinqularities, derivinq formulas for flow, includinq three component force, spanwise aerodynamic cbaracteristics of infinite span direction Pressure distribution and shock wave wings with boundary layer control anqular measurements by flow visualization A71-20777 A71-20015 Sinqularity method for calculation of potential SEOCK WAVE PBOPAGITIOI flow around axisymmetric rings Aanqinq shock wave in small supersonic flow past 171-18469 profile with broken qeneratrix in plane ideal SKII FRICTIOI qas Unsteady boundary layers on sphere or cone movinq A71-21872 alonq axis, determininq skin friction anqular SEOCK WATES response Blunt cylinder with small thread in anomalous 1171-20098 seeded flow in hypersonic wind tunnels, SKIRTS observinq separated shock vave distortion Air cushion vehicle technoloqy, considering A71-18924 economics, propulsion, structures, Shock wave diffraction by two dimensional veak controllability, flexible skirt systems and R disturbances. usinq aerodynamics blast method and D 871-19255 [SAE PAPER 7101833 A71-21713 Closinq shock position in supersonic underexpanded SLENDER BODIES sinqle and two phase jets, determininq liquid Aerodynamic characteristics of Conical and phase concentration effects on Mach number and pyramidical confiqurations with various nozzle pressure in wind tunnel planforms by slender body theory, replacing

A-43 SUBJBCS IIDEX SPII DIIAIIICS

three dimensional flou by tu0 dimensional flou SOUTEEAST ASIA A71-20776 Air transport supply on scheduled services in Vortex breakdoun on slender sharp edged and Europe-Eediterranean and Southeast Asia regions modified delta wings uith varying sueep angles [ REPT-1970/1-E J mi- 1811 2 investigated in rind tunnel using schlieren SPACE EIPLOIATIOI system for flou visualization Co8posite rocket cum hypersonic airbreathing [AIAA PAPER 69-778 J A71-22028 propulsion reducing space exploration proqram Aumerical computation of viscous hypersonic flou cost around slender bodies A71-21301 n7i-16951 SPACE EISS100.5 Hear-continuum axisymmetric hypersonic flow past Silver zinc batteries and cells case cover very slender bodies materials and sealing techniques for space [ AD-715901 ] 1171-18556 missions SLmDIIA COIXS A71-21097 lose blnntness. angle of attack and oscillation SPACE SEUWLBS amplitude effect on hypersonic unsteady maximum stagnation temperature on suept wing aerodynamics of slender cones leading edge for equilibrium glide entry of [AIAA PAPER 70-2161 A71-19895 space shuttle SLEIDIIB WIB6S A71-18902 Bypersonic minimum drag slender wing leading edge Banned flight from Eontgolfier Balloon to Apollo shape for given airfoil section, using Aertonian 13, discnssing future space programs including theory lunar base and space shuttle A71-22039 A71-19017 Lift and aerodynamic drag data on slender wings Elastic, inertial and aerodynamic forces with trailing edge sueepback aeroelastic triangle, examining lift changes due [ ARC-CP- 1 130 J 1171-17117 to aircraft structure deformation, dynamic SLIPSTRSMS flight stability and space shuttle development Intensified molect~lar diffusion during turbulent problems mixinq of supersonic slipstreams in cylindrical A71-20063 mixinq chamber. using optical Prodnikov method shuttlecraft landing and navigational aid A71-19733 capabilities SLOTTED WIID TUIIELS [ AASA-TO-X-667201 n7i-18187 Lift, pitching moments and damping of delta wings European hypersonic uind tunnels for testing in slotted transonic uind tnnnels uith hypersonic transport aircraft, and space shuttle perforated ualls aerodynamic configurations TAPL-AERO-13073 171-17085 1171-18452 SIIOKE SPACBCRAR COIIEUIICATIOI Combustor desiqn for minimum exhaust smoke Oltrahigh frequency directional spiral aircraft emission from aircraft gas turbine jet engines, antennas for spacecraft communication consiaering air pollution [ RAE-TR-70062 3 171-18519 171-20867 SPACECCPAR SUIDAICE Aircraft engine smoke emission control. discussing strapdown inertial navigator alignment by digital Rinqelmann chart assessment for various filtering techniques. discussinq application to commercial jet aircraft and airport gaseous aircraft and spacecraft pollntants A71-21170 17?-21832 SP1CKRIR IISTEOEEITS SOLAR PLFLXXOBS Manometric equipment arrangement in nose cone of Thermal pump-compressor for converting solar oriented satellite with aerodynamic system enerqy stabilization [ AASA-CASE-XLA-00377 J n71-176io A71-21022 SOIIC Boons SPACECEAR REl!!.ZRT Sonic boom effects on human physiology and Mesosphere and stratosphere data from hiqh level behavior and structures. based on theoretical observations for supersonic transport and studies and simulators reentering space vehicle operations A71-21812 A71-21724 Legal aspects of military sonic booms. discussinq SPACECRAR STABILITY administrative remedies, liability and various Longitudinal aerodynamic characteristics of Viking cases lander spacecraft at hypersonic speed A7 1-2 1830 [AASA-TE-X-2205 J N71-17253 Sonic boom wind tunnel testing techniques at high SPACECRAFT STRBDCTURBS Each numbers, giving sample pressure signatures Internal loads and stresses caused by space [AIAA PAPER 71-280 J A71-22006 vehicle vibration resulting from induced or Three dimensional diffraction of sonic booms by natural environments corners of structnres [ NASA-SP-8050 ] 1171-19281 [ UASA-CE-1728 J 171-18029 SPECTROPEOrO~TEPS SOUID FIELDS Photometer observations of auroras from CV-990 Sound field interaction with sinusoidally aircraft corrugated surface. considering aircraft noise [ NASA-CR-116855 J mi-le996 measnrement implications SPXED CORROL A71-21162 Effects of specific speed on experimental Sound field effects on flat plate heat transfer in performance of radial inflou turbine turbulent boundary layer [AASA-TB-L+61821 mi-17354 REPT-70-8 J 1171-18572 SPEERES SOUID PBOPAGATIOI Sphere and disk drag measurements for Reynolds Acoustic attenuation determined experimentally numbers from 5 to 100,000, examininq forces, durinq engine qroond tests of XB-70 airplane and moments, flou visualization, unsteady modes and comparison with predictions constant acceleration [ AASA-TI-X-2223 J 1171-17951 A71-19893 SOUlD TPAISIISSIOI Unsteady boundary layers on sphere or cone movinq Ribbed aluminum panels airborne soond transmission along axis, determining skin friction anqular loss, evaluatinq structural damping effects response L71-2143 1 A71-20098 SOUID WAVES SPEEEICAL ELPIIOIICS Aconstic radiation spectra from turbulent jets, Aypersonic radiating gas inviscid flow past blnnt assuminq approximate Gaussian statistics and bodies, using spherical harmonics approximation second order velocity correlation space-time A71-19183 characteristics obtainable from frozen flow SPI1 DIIAIIICS A71-19959 h-7 low altitude tactical fighter spin evaluation program, discussing manenrering capability, L A45 SPIU STABILIZATION SUBJECT IUDEI

external stores and departure mode STATISTICAL AUALYSIS A71-19094 Statistical methods for inventory boundary USAF F-4E Stall/Near Stall Investiqation, determination and data compression in automatic discussinq testing requirements, fighter processing of multispectral scanner remote aircraft improvement, spin avoidance and hiqh sensor earth observations from aircraft and anqle of attack limitations spacecraft 171-19095 [AIAA PAPER 71-2341 A71-19711 SPIN STABILIZATIOU Statistical information on liqhtninq and static Trajectories prediction for subsonic spin hazards relative to airworthiness stabilized projectiles via water tunnel tests, A71-19929 considerinq blunt nose and tail and rounded nose statistical analysis of origin-destination survey riqht circular cylinders at Philadelphia International Airport rAIRA PAPER 71-2961 A71-22016 N71-18958 SPIRAL ANTBNNAS STATISTICAL CORRELATIOU Ultrahiqh frequency directional spiral aircraft Feasibility evaluation on optical probing of antennas for spacecraft communication supersonic aerodynamic turbulence with r RAE-TR-70062 1 N71-18519 statistical correlation SPOILERS r NASA-TN-D-6077 1 N71-17444 Pressure measurements of flow induced cavity STATOR BLADES resonance and effects of resonance suppressinq Determining feasibility of increasinq stator blade devices loadinq of sinqle staqe compressor riq by [ NASA-TN-D-6205 1 N71-17877 bleeding or blowinq suction surface boundary STABILITY DERIVATIVES layer Nonlinear aerodynamic moment system for r NASA-CR-54573 1 N71-18749 nonaxisymmetric bodies free fliqht motion STEADI FLOW analysis, takinq into account interactions Numerical analysis of low frequency subsonic excluded in classical treatment liftinq surface theory notinq winq oscillations [AIAA PAPER 71-2751 A71-22000 in steady flow STABILIZERS (FLUID DIUAflICS) r ARC-R/U-3634 1 N71-18425 Wind tunnel aerodynamic stability tests on STEAM FLOW chimneys with pipes and helical windinq Results of two-phase blowdown experiments with stabilizers straiqht tube test section and steam-water TNPL-AERO-1310 1 N71-17334 mixtures STAGUATION POIUT [ AECL-36641 N71-18161 Nonequilibrium multicomponent ionization STEAII TURBIUES calculations for staqnation merqed shock layer Cyclic thermal crackinq and fatique analysis in of hypersonic blunt body by successive larqe steam turbine rotors with three accelerated replacement dimensional temperature and triaxial stress rAIAA PAPER 69-6551 A71-19890 computation STAGUATIOU TEUPERATURE [ ASHE PAPER 70-PWR-1 1 A71-20198 naximum staqnation temperature on swept winq STEEL STRUCTURES leadinq edqe for equilibrium qlide entry of Structural efficiency improvement by materials space shuttle selection for airframe structures, discussing A71-18902 Al, Ti-A1-V and stee!. panels STAUDARDS A71-21685 Tenativr airworthiness standards for powered lift STEERABLE AUTENUAS transport cateqory aircraft Planar microwave array antenna for scan N71-17553 requirement, discussing tilt anqle and element STATIC DISCAARGERS arranqement optimization Liqhtninq current transfer tests of p-static rAIAA PAPER 70-1911 A71-22030 discharqer for aircraft installations STOPPIUG A71-19935 Boeinq 737 aircraft takeoff and landinq Flight testinq devices for discharqinq static performance, emphasizing hiqh lift systems and electricity from aircraft without production of stoppinq capability radio interference A71-19083 N71-18114 STRAPDOWU IUERTIAL GUIDAUCE STATIC ELECTRICITY Strapdown inertial naviqator aliqneent by diqital Liqhtninq and static electricity - Conference, San filterinq techniques, discussinq application to Dieqo. December 1970 aircraft and spacecraft A71-19926 A71-21170 Statistical information on liqhtninq and static STRATOSPEERE hazards relative to airworthiness Uesosphere and stratosphere data from hiqh level A71-19929 observations for supersonic transport and Liqhtninq and static electricity effects on reentering space vehicle operations helicopter desiqn, considerinq rotor protection, 1171-21724 carqo hook operation and passive discharqers for STRATOSPEERE RADIATION radio interference reduction Commercial aviation stratospheric water vapor 871-19938 injections influence on radiation budget. ozone, STATIC LOADS polar niqht cloudiness and potential climatic Vertical motion of static loads over baffles effects durinq loadinq operations usinq qround effect A71-21822 machines STRBAU PUUCTIOUS (FLUIDS) NPL-HOVERCRAFT-TU-31 1 N71-17160 Uultilink approximation of Chaplyqin function in STATIC PRESSURE subsonic and supersonic flow reqions, derivinq supersonic air flov pattern over rectanqular couplinq conditions relative to modified stream indentations on plane and axisymmetric surfaces, function at approximation nodes examininq static pressure and adiabatic A71-20090 temperature distributions STRESS AUALYSIS A71-19744 Heat transfer and thermal stress calculations for Static pressure port errors in hypersonic qas turbine rotor blade desiqn turbulent flow, usinq approximate shear layer N71-17401 nompntum balance for pressure increase STRBSS COUCEUTRATIOU derivation center of qravity vertical acceleration and winq [AIAA PlPER 71-2701 A71-21996 stresses of Boeinq 720-E aircraft STATIC TESTS [TB-87-1970 1 N71-17119 Static tests to determine effects of throat inlet STRESS CYCLES ConceDts on forward-radiated fan noise of Aluminum alloy stress cycles and fatigue life of 707-320B/C' airplanes airframe materials [NASA-CR-17151 N71-17426 [ FH-78-1969 1 N71-17524

A-46 SUBJEC? IEDEX SUPEBSOEIC PLOW

STRESS BEASUREEEIT Elastic swept wing subsonic aerodynamic Jet enqine rotor strain and temperature data characteristics, takinq into account aerodynamic transmission, examining special purpose load redistribution due to aeroelastic telemeters desiqn deformations A71-19628 1171-22035 STRESSED-SKII STRUCTURES Jet exhaust nacelle subsonic flow simulation Optimal weight of aerodynamic heat protection r ARC-CP-11111 N71-17113 layers of stressed skin and optimal efficiency Lift and aerodynamic drag due to trailing-edge of coolinq system for hypersonic aircraft flaps on Sveptback wings in inviscid subsonic compartments flow A71-20836 r ARC-CP-1 1101 N71-17114 STRUCTURAL AIALYSIS Numerical analysis of low frequency subsonic Aerodynamic heatinq and structural analyses for liftinq surface theory notinq wing oscillations radiatively cooled delta winq of hypersonic in steady flow aircraft ARC-R/E-3634] N71-18425 [NASA-TN-D-6138 1 N71-18025 Hathematical models for control surface uings in Finite element analysis of structures in plastic subsonic unsteady flow range [ OAERA-TP-889 1 N71-18473 r~nsR-c~-i649) 8-11-19276 SUBSOIIC SPEED STRUCTURAL DESIGE Trajectories prediction for subsonic spin Air cushion vehicle technology, considerinq stabilized projectiles via water tunnel tests, economics, propulsion, structures, considerinq blunt nose and tail and rounded nose controllability, flexible skirt systems and R right circular cylinders and D [AIAA PAPER 71-2961 A71-22016 [SAE PAPER 7101831 A71-21713 Vortex-lattice FORTRAN program for estimating Complex airframe design for economic and safe subsonic aerodynamic characteristics of complex operation and long life using fatique and planforms fracture mechanics [NASA-TN-D-61421 N71-17424 [AIAA PAPER 70-5121 A71-22025 SUBSOSIC EIID TUIEBLS Heat transfer prediction for turbine blade desiqn European subsonic. supersonic, transonic, N71-17374 hyperrelocity and low density wind tunnel Efficiency of air coolinq blade desiqn for Olympus characteristics 593 qas turbine engine N71-17099 N71-17376 Aerodynamic drag measurements on VC-10 aircraft Eonndary layer optimization for srall turbine sirbsonic sin2 tunnel Eodels blade desiqn with cusped trailinq edqe r ARC-CP- 1125 J N71-17118 N71-17380 SUPKRCOIDUCTI1G IIAGIETS Heat transfer and thermal stress calculations for Supersonic wind tunnel electromagnetic balance qas turbine rotor blade desiqn with superconducting coils N71-17401 A71-20151 Design optimization for cylindrical shell SUPERCRITICAL PIIGS subjected to reentry loads and heatinq Parametric engine study for Each 0.98 commercial N71-18022 air transport with supercritical winq STRUCTURAL EUGIEEERING r NASA-TE-X-52961 J N71-18733 Structural efficiency improvement by materials SUPEBSOlIC AIRCRAFT selection for airframe structures, discussinq Supersonic aircraft electrification measurements 111. Ti-AI-V and steel panels using proiectile frictional ccarqing in ice-foq 171-21685 cloud STRUCTURAL FAILURE 1171-19934 Bent structure failure under pulse floor Supersonic airplane minims time turns at constant acceleration shocks, concerning aircraft seat altitude, determining thrust, bank auqle and damage durinq crash landing anqle of attack programs with optimal control A71-20747 theory Eaterials failure role in Canadian civil aircraft A71-22032 accidents, discussing organized investiqation Performance of auxiliary inlet ejector nozzle with and data flow floating inlet doors and floatinq single hinge 871-21679 trailinq edqe flaps STRUCTURAL RELIABILITY [ NASA-TU-X-2173 J 1171-17554 Complex airframe desian for economic and safe Linear multichannel control systems for supersonic operation and long life using fatigue and aerospace vehicles orbiting in earth atsosphere fracture mechanics [ AD-7147961 N71-17747 [AIAA PAPER 70-5121 A71-22025 Takeoff perfornance predictions for XB-70 delta SY!RUCTURAL STABILITT winq supersonic aircraft Aircraft turbine engines strenqth and gas dynamic [NASA-TE-X-2215J N71-18509 characteristics improved by vibration decrease SUPERSOEIC COIIIIERCIAL AIR TRAESPORT using elastic elements Commercial supersonic fliqht, investigatinq air A71-21710 pollution and alleqed climate and weather STRUCTURAL VIBPATIOI modification effects due to principal exhaust Pluctuatinq circulation, lift ana flow induced products structural vibrations of two dimensional bodies, A71-21821 including vortex shedding on sluice gates SUPERSOlIC COIIPPESSOES 171-19592 Semi-empirical determination of adiabatic SUBSOIIC AIRCRAFT~- efficiency of supersonic compressor staqe Subsonic jet engine noise reduction. considerinq [ AD-7150053 R71-18036 turbojets. turbofans and jet suppressors SUPERSOIIC PLIGBT 1171-21814 Jet engine contribution to lift at supersonic SUBSOUIC PLOP flight velocities via air mass heatinq, studyinq Approximation of Chaplygin equation for subsonic three dimensional flow with heat supply and ideal gas plane adiabatic flow. applying to strean deflection discharqe from flat channel with contraction 171-19746 A71-20083 Numerical determination of aerodynamic Hultilink approximation of Chaplygin function in coefficients for thin supersonic wings at subsonic and supersonic flow reqions, deriving various angles of attack couplinq conditions relative to modified strean r NASA-TT-F-13521 1 N71-18987 function at approxination nodes SUPERSOEIC PLOW 871-20090 Intensified molecular diffusion during turbulent Prandtl-Glauert pressure distribution rule mixinq of supersonic slipstreams in cylindrical improvement subsonic planar flow mixing chamber, usinq optical Prudnikov method A71-20312 A71-19733

A-87 SUPKRSOUIC PLUTTKR SUBJECT INDKI

Shock wave interaction with wedqe movinq at supersonic nozzles mass flow rate coefficients snpersonic speed, calcnlatinq qeometry of at hiqh Reynolds numbers, appraisinq isentropic reqions formed intersecting wavefronts flow prediction methods A7 1-19741 A71-19877 Viscosity effects on three dimensional supersonic Optinal design of rigid unadjustable contour for flow around circular half cones on flat plate, supersonic nozzle, takinq into account vehicle examininq turbulent boundary layer separation fliqht conditions A7 1- 19743 All-21865 Supersonic air flow pattern over rectangular SUPERSOlIC SPEEDS indentations on plane and arisymnetric surfaces, viscous drag on variable sweep wings and wedges at examininq static pressure and adiabatic supersonic and hypersonic speeds temperature distributions [ ARC-R/H-3623] 171- 17109 All-19744 supmsonIc TEST APPAEATUS Jet enqine contribution to lift at supersonic Development and calibration of Hach 1.2 rain fliqht velocities via air mass heatinq, studyinq erosion test apparatus three dimensional flow with heat supply and [AD-715909J N71-18651 stream deflection SUPKRSONIC TEAlSPORTS All-19746 SST noise suppression research, discussing engine Inverse boundary value problems in noise suppressor conceptual designs and test hydroaeromechanics, involvinq profile results rith installed devices construction from given velocity or pressure All-20302 distribution and supersonic flow boundaries Hesosphere and stratosphere data from hiqh level determination observations for supersonic transport and A71-20078 reentering space vehicle operations Surface construction of body of revolution in 171-21724 supersonic qas flow from distribution of Pitch and yaw characteristics of supersonic velocity vector modulus along qeneratrix of transoort aircraft with variable sweep winqs at body, nsing Prank1 method of characteristics variois Hach numbers 171-20089 INASA-TH-X-21641 N71-17415 Hultilink approximation of Chaplyqin function in Environmental impact of supersonic transport subsonic and supersonic flow regions, deriving N71-17545 couplinq conditions relative to nodified stream Traffic control system for supersonic transports function at approximation nodes using synchronous satellite for data relay A71-20090 between vehicles and ground station Flutter analysis of stressed flat simply supported [ NASA-CASE-GSC-10087-1 J N71-19287 skew panels in supersonic flow, usinq small SUPKESOIIC IIAKKS deflection thin plate theory Large angle cones supersonic aerodynamic and wake 171-21302 characteristics at low Reynolds numbers, Hanqing shock wave in small supersonic flow past including model support interference effects profile with broken generatrix in plane ideal [AIAA PAPER 71-2641 A71-21990 qas Wake flow properties of conical bodies at A71-21872 supersonic speeds and varions angles of 1171-attack 18480 Laser Doppler velocimetric technique for TNASA-TH-X-21391 supersonic flow particle trajectory and density SOPKRSOIIIC WIID TUNIsLS measurements. notinq particle laq Hultiple source schlieren system for flow [AIAA PAPER 71-287 J A71-22010 visualization in Canadian trisonic wind tunnel, Plow lines construction in two dimensional using inteqrated loqic circuitry for control supersonic flow reqion with rarefaction waves A71-19924 interaction from several distnrhance sources wind tunnel history, evolution and use, coverinq All-22052 low speed variable density, high speed Investiqatinq supersonic viscous gas flow around transonic, supersonic, hypersonic and blunt bodies hypervelocity wind tunnels N71-16902 A7 1-21666 Rectanqular and caret winq sails in supersonic and Sinqle and multiple stinq snpport evaluation for hypersonic turbulent flow for hypersonic unmodified interference free wind tnnnel data vehicles over 0.85 to 2.2 H range osinq imaqe method [ ARC-R/H-3624 1 N71-17103 [AIAA PAPER 71-2673 All-21993 Transonic and supersonic dynamic stability Launch and data reduction in supersonic Wind characteristics of variable sweep wing tactical tunnel free fliqht testinq of high fineness fiqhter aircraft ratio bodies [NASA-TIT-X-21631 N71- 17425 [AIAA PAPER 71-2781 All-22003 Supersonic flow with separated shock wave past Error analysis for Pressure measurements on wedqe shaped profile blowdown’ supersonic wind tunnel models INASA-TT-P-13469 J N 7 1- 1744 3 TNPL-AERO-13061 171-17081 Feasibility evaluation on optical probinq of European subsonic, supersonic, transonic, supersonic aerodynamic turbulence with hypervelocity and low density wind tnnnel statistical correlation characteristics [ NASA-TN-D-6077 1 N71-17444 171-17099 Dependence of aerodynamic coefficients on maximum Graphite drilled-core storage heater for supplyinq thickness and lenqth of axisyometric bodies in heated nitroqen gas to supersonic tunnel supersonic flow (NASA-TK-1-2202 ’) N71-17876 [DLR-PB-70-541 N71-18444 Auxiliary inlet ejector nozzle designed for Hathematical model for aircraft lifting surface supersonic cruise aircraft interference in steady or unsteady supersonic [ NASA-TH-I- 21 821 N71-18863 flow SUPPORT IWTERFERBNCK [ONERA-TP-850 J N71-18462 Comparative sting supported and free flight tests SUPERSOIIC FLWTTEE in hypersonic wind tunnel on modified Apollo Rotary inertia effect on critical dynamic pressure launch configuration parameters and supersonic flutter of in- plane [AIAA PAPER 71-2651 A71-21991 loaded sandwich plates Sinqle and multiple sting support evaluation for A71-19887 unmodified interference free wind tunnel data SUPERSOIIC JKT FLOW over 0.85 to 2.2 H ranqe using image method Closinq shock position in supersonic underexpanded [AIAA PAPER 71-2671 L71-21993 sinqle and two phase lets. determining liquid Aerodynamic support interference in wind tunnel Dhdse zoncentration effects on Hach number and testinq of confiqurations involving bulbous nozzle pressure in wind tunnel base, mass addition. transition near base and All-21925 hypersonic low density flows SUPERSOIIIC IOZZLES [AIAA PAPER 71-277’) A71-22002 Small curvature radius/throat radius ratio

A-48 SOBJBCT IIDEI TAKEOFF

SOPF’OBTS SSEEP A1618 Soviet book on supports and suspensions of Vortex breakdown on slender sharp edged and aircraft qyroscopic devices covering accuracy, modified delta wings with varying sweep angles reliability and lifetime factors related to investigated in wind tunnel using schlieren quality and operational conditions system for flor visualization A71-20299 [AIAA PAPER 69-7781 A71-22028 SUPPRESSORS SEBPT EIW6S SST noise snppression research, discussing enqine naximnm stagnation temperature on srept wing noise suppressor conceptual designs and test leading edge for eqnilibrinm qlide entry of results vith installed devices space shuttle A71-20302 171-18902 SIRFACE COOLUG Elastic swept wing subsonic aerodynamic Effective heat transfer coefficients in film characteristics, taking into account aerodynamic coolinq systems of gas turbine surfaces load redistribution due to aeroelastic 171-17395 deformations SOPFACE PISISHI16 1171-22035 Axial compressor blades surface finish and fatigne SEEPTBACK EI16S strenqth restoration bv vibrational tumblina Lift and aerodynamic drag due to trailing-edge A7l-20883 flaps on sreptback wings in inviscid subsonic SURFAC11 1ATIGATIOI flow Communications. navigation and surveillance for [ ARC-CP-1110 ] n7i-17114 aircraft and marine vessels in Worth Atlantic Pressure qradient effects on three dimensional reqion. discussinq baseline traffic control tnrbnlent bonndary layer of infinite span model sreptback rinq 1171-18808 [ RPL-AERO-1305] 871-17179 SOBFACE PROPERTIES srmixtowoas SATELLITES Large aspect ratio rectangular duct with Traffic control system for supersonic transports nonuniform snrface texture. investigating nsing synchronous satellite for data relay tnrbulent flow. maximum velocity positions and between vehicles and ground station zero shear stress [HASA-CASE-GSC-l0087-1] 171-19287 A71- 18772 STBOPTIC IIETEOBOL06I SUPIACE ROIIGEIESS ERECTS Synoptic meteorological conditions for clear air Sound field interaction vith sinnsoidally turbulence and turbulence effects on aircraft corrugated snrface. considerinq aircraft noise flight characteristics measnrement implications r DLR-PB-70-29 ] 171-17145 A71-21162 SISTIII FAILOBIS SOBFACE VBIIICLIIS Computer aided automatic fault data logging, Urban transit and ATC vehicle identification and classification, analysis and reporting methods position determination system, considering in inteqrated ATC system surface and airborne traffic real time A71 -19556 information communication STSTEIIS AIALTSIS A71-21169 Environmental impact of snpersonic transport SOP615 871-17545 Snrqe voltages produced by transient currents on Systems analysis and mathematical model for air signal conductors in shielded cables transportation design A71-19946 [ NASA-CB-1164311 8-11-17843

SOPVEILLAICE~ ~~ Srsteas analysis sommary on PPW Iork xetrzpclitan Communications. navigation and snrveillance for area air traffic capacity aircraft and marine vessels in north Atlantic 1171-18040 region. discussinq baseline traffic control Development planninq manual for national model transportation system A71-18808 [PB-194964] 171-1807? Airborne snrveillance for environmental Snrvey of air traffic control radar beacon system management, discussing earth resources program. operational problems aerial sensors for thermal water pollution, crop 871-18116 disease. salinity and geological structure STSTEES BlGIllEEBIlG A71-19080 Avionics snkystem design improvements for SORVIILLAPCE BADAR aeronautical systems, considering Inteqrated electro-optical microrave radar and standardization. reight impact, environmental laser /lidar/ systess fsr earth orieoted, control, saintainability and equipment growth environmental and domestic applications A71-18829 A71-18827 P-104D aircraft side stick control system desiqn SURVIVAL EQOIPIIEIT and function, curriculum aanenvers and component Cam0 aircraft crew safety and survival. reliability describing restraint, escape, flight deck 1171- 19092 interior doors. fire and smoke hazards and Ean-machine considerations in all-weather low- personnel environmental protection altitnde naviqation system design. discussing [ SAE-ARP-11393 A71-19643 compnter qeneration of roll command quidance, SOSPBPDI16 (HA16116) visual display and pilot modelinq Soviet book on supports and suspensions of A71-20344 aircraft qyroscopic devices coverinq accuracy. Planning system for metropolitan airports reliability and lifetime factors related to [ PAA-AC-150/5070-5] N71-17546 quality and operational conditions Selection of scanning systems for aircraft thermal A71-20299 viewers SEBAT COOL116 871-19220 Aerodynamic and thermodmamic performance of sweat cooled gas turbine enqine blades 87 1- 17382 T Beat transfer in air coolinq and sweat coolinq TABLES (DATA) techniques for high temperature gas turbine Soviet book of gas dynamic function tables for tro enqine components and three dimensional flows past blunt bodies 871-17383 A7 1- 19050 Transpiration cooled blades for hiah temperature TACLI inlets in qas tnrbine engines U.S. domestic ATC airspace enronte and terminal N71-17384 area naviqation system effects on pilot Performance of stator with wire mesh shell blading workload, prolectinq future FAA requirements during cold air investiqation of turbine uith A71-20347 transpiration cooled stator blades - Vol. 3 TAKEOFF [ 1ASA-TI!-I-21661 N 7 1- 17590 Boeing 737 aircraft takeoff and landing

A-49 TAKEOFF RUNS SUBJECT INDEX

performance, emphasizing high lift systems and [AIAA PAPER 71-2421 A71-19717 stoppinq capability ATC automated systems, discussinq National A71-19083 Airspace System En Route Stage A and Advanced Aircraft optimum minimum noise takeoff profile, Raaar Terminal System solvinq by equations of motion system for jet [AIAA PAPER 71-2443 A71-197 19 aircraft U.S. domestic ATC airspace enroute and terminal A71-20179 area naviaation system effects on pilot Inqestion of debris into aircraft enqine inlets workload, -prolectinq future FAA reiuireeents durinq takeoff A71-20341 r ARC-CP-1114 1 N71-17084 Airport liqhtinq facilities in Japan, considerinq Establishment of take-off and landinq safety fixtures, marker and obstruction lights and narqins for Brequet 941 apron floodlight [NASA-TT-P-134531 N71-17441 1171-20355 Noise measurement evaluation of takeoff and ATC automation proqram for en route and terminal approach profiles optimized for noise abatement centers, discussinq combined nationwide system [ NASA-TN-D-6246 1 N71-18929 features, IPRvolume and video diqitizer data TAKEOFF ROUS links A71-21659 Takeoff performance predictions for XB-70 delta winq supersonic aircraft System description of field test model of ARTS 2 r NASA-Tf!-X-2215] N71-18509 modular alphanumeric nontrackinq ATC system TAUDEM WING AIRCRAFT N71- 18815 Eathematical models for aerodynamic forces of TEREIUAL GUIDAUCE aircraft tandem uinqs usinq liftinq line winq ODtimum automatic fliqht control techniques in represectation horizontal quidance of aircraft at terminal [ ONERA-TP-8911 N71-18439 A71-20306 Mind tunnel testinq of interference lift of tandem TEST EQUIPMENT winq aircraft liftinq surfaces Performance test methods and equipment for r ONERA-TP-890 1 N71-18449 aircraft avionics and weapons systems. TECAUOLOGY ASSESSMENT discussinq computer inteqration with radar and Aircraft noise abatement control on international phototheodolite ranqe instrumentation system basis b9 settinq acoustic technoloqical A71-21660 capability compulsory standards of quietness TEST FACILITIES A71-21826 Artificial lightninq qeneration facilities for TECRUOLOGY UTILIZATION aircraft component developmental testinq by Avionics subsystem desiqn improvements for manufacturer aeronautical systems, considerinq A71-19931 standardization, weiqht impact, environmental TEST PILOTS control, maintainability and equipment qrowth Fliqht tests - Conference. Beverly Hills, A7 1- 18829 September 1970 TELEMETRY A71-19076 Jet enqine rotor strain and temperature data TEST STAUDS transmission, examininq special purpose Gas dynamic test stand for cyclic thermal load telemeters desiqn testinq of qas turbine enqine materials and A71-19628 comuonents at variable heatins and coolinq rates TEHPERATURE COUTROL and' mechanical loads Equation derived for operation of turboprop enqine A71-20839 with hiqh pressure compressor controlling qas TETRAEEDRONS temperature at turbine front Tetra-Core structural composite material, A71-20831 discussinq fabrication techniques, test results, TEMPERATURE DISTRIBUTIOR potential and applications A71-21225 supersonic air flow pattern over rectanqular indentations on plane and axisymmetric surfaces, TEXAS examininq static pressure and adiabatic Economic analysis of airport construction in north temperature distributions central Texas reqion, emphasizinq employment and A71-19744 dollar value of purchases Enqineerinq methods for predicting temperatures N11-18099 and velocities in vicinity of vertical lift TRERHAL CONTROL COATINGS enqines of jet V/STOL aircraft operatinq near Thermal control coatinqs for refractory qas qround turbine materials r NASA-CR-1118451 N71-18714 N71-17391 TEEPERATORE EFFECTS Performance of aluminide coatinqs in simulated Air temperature effects on internal combustion hiqh temperature tests on qas turbine enqine enqines intake process, usinq similarity theory inlets A71-20782 [NASA-CR-1163741 N71-17393 TEMPERATURE MEASUREMENT TEERMAL CYCLIBG TESTS Jet enqine rotor strain and temperature data Gas dynamic test stand for cyclic thermal load transmission, examininq special purpose testing of qas turbine enqine materials and telemeters desiqn components at variable heatinq and cooling rates A71-19628 and mechanical loads Catalytic surface effects on thermocouple A71-20839 combustion qas temperature measurements in jet TEERMAL FATIGUE enqines Thermal fatique behavior of fiber reinforced N11-17379 nickel alloy qas turbine blades TEMPERATURE HEASURING IUSTRUilEUTS N71-17390 Heat transfer and heat flux measurinq sensors for TEEBEAL IUSULATIOU qas turbine enqines Development of thermal insulation system for win4 N71-17377 and control surfaces of hypersonic aircraft and TEMPERATURE SENSORS reentry vehicles Hiqb performance fiqhter aircraft enqine pressure r NASA-CASE-XLA-00892 1 N71-17897 ratio and turbine inlet temperature measurement, TEERMAL PROTECTIOU usinq fluidic sensors Optimal weiqht of aerodynamic heat protection A71-20586 layers of stressed skin and optimal efficiency Upper air soundinq systems problems, discussinq of coolinq system for hypersonic aircraft aerodynamic heat transfer between temperature compartments sensoc and ambient air A71- 20836 1171-21739 TEERMAL RESISTAUCE TERMINAL FACILITIES CO.DUteriZed optimization of thermal resistant qas System automation evolutionary process in terminal turbine blades Air Traffic Control environment N71-17400

11-50 SUBJECT IUDEX TRAIS?IISSIOU LOSS

lubricatinq oils, thrust augmentation, inlet ducts and overhaul procedures A71-21625 TIIE LAG Nonlinear control systems rith transport lag. obtaining parasetel' plane equations for stability analysis A71-20369 Experimental arranqeaent for delay times in propeller/rpm controller system A71-20832 [ ARC-CP-1117 ] 871-17100 Feasibility of visual trackinq to determine effect Beat transfer and thermal stress calculations for of lag in sisulated aircraft dynamics qas turbine rotor blade design [IAa-R-479] N71-18838 N71- 17401 TXTAIIUU 1LLLOIS TEEEIOCOUPLES Plasma arc welding of jet engine components of Ti Catalytic surface effects on thermocouple and Ai alloys, comparinq to qas tunqsten arc and combustion qas temperature measurements in jet electron beam processes enqines 171-21684 171-17379 Structural efficiency improvement by materials TBERIODTIAIIC EPPICIEICT selection for airframe structures, discussinq Optimal veiqht of aerodynamic heat protection A1, Ti-A1-V and steel panels layers of stressed skin and optimal efficiency A71-21685 1 of cooling svstem for hvpersonic aircraft TORQUE compartments Effectiveness of anti-torque aerodynamic surfaces I 171-20836 immersed in helicopter rotor downwash Fuel consumption and propulsive and thermodynamic [ AD-7154381 N71-18937 efficiencv comparisons for ships, hydrofoil TORSIOHAL VIBRATIOI craft. helicopters, jet aircraft. and ground Transverse and torsional vibrations of fuselaqe- I effect machines winq combination with wing tip fuel tanks, r NPL-BOVERCEAPT-121 N71-17161 calculatinq mass and stiffness matrix for elastic beam 1171-20364 TOUED BODIES Derivation of stability boundaries in wind tunnels for bodies towed by cables [ ARC-R/?I-3644 3 N71-18461 TRACKIIG (POSIl'IOI) Feasibility of visual trackinq to determine effect of laq in simulated aircraft dynamics [ IAN-R-4791 N71-18838 TRAFFIC COITROL Communications. naviqation and surveillance for aircraft and marine vessels in North Atlantic region, discussinq baseline traffic control model .~ a71-13830 A71-21302 Urban transit and ATC vehicle identification and TEIU UIIICS position determination system, considering Cavitation flow of fluid with free surface past surface and airborne traffic real time underwater wins with jet flap, solving equations information communication of motion for thin foil with jet emergent from 171-21169 trailinq edqe TRAILIIIG EDGES A71-20086 cavitation flow of fluid with free surface past Numerical determination of aerodynamic underwater winq with jet flap, solving equations coefficients for thin supersonic wings at of motion for thin foil with jet emerqent from various angles of attack trailinq edqe [ NASA-TT-F-13521 J 871- 189 87 A71-20086 TEEBE DIIEUSIOIAL BOUIIDART LATER Lift and aerodynamic drag data on slender wings Prfssuie gradient effects on three dimensionai with trailinq edqe sweepback turbulent boundary layer of infinite span r ARC-CP-1130 J mi-1711-1 sueptback winq Boundary layer optimization for small turbine [UPL-AERO-1305] 871- 17 179 blade design with cusped trailing edqe TEREE DIEEBSIOIAL PLOW N71-17380 Jet engine contribution to lift at supersonic TEAILIIG-ED6E ?LAPS fliqht velocities ria air mass heating, studyinq Lift and aerodynamic draq due to trailing-edge three dimensional flov with heat supply and flaps on sreptback winqs in inviscid subsonlc stream deflection flow A71-19746 ARC-CP-1110 ] 171-17114 Aerodynamic characteristics of conical and TRAIUIIG DEVICES wramidical confiquratious vith various Surveyinq air traffic controller occupation and planforms bv slender body theory, replacinq development of perforaance objectives three dimensional flov by two dimensional flow N71-18105 A71-20776 TRAJECTOBT ASALTSIS Three dimensional diffraction of sonic booms by Trajectories prediction for subsonic spin comers of structures stabilized projectiles via water tonne1 tests. [ NASA-CR-17283 N71-18029 considering blunt Dose and tail and rounded nose Calculation of streamline coordinates for three riqht circular cylinders dimensional turbulent boundary layer in vaneless [AIAA PAPER 71-296) 1171-22016 dif fuser Real qas effects on draq and trajectories of ARC-R/M-3646] N71-18468 nonliftinq conical shell durinq nars atmospheric TBEEE DIIEISIOIAL IOTIOB entry Three degree of freedom gas bearing for vind [ NASA-TN-D-62401 N71-1 80 15 tunnel dynamic measurements. allowinq models wind tunnel testinq of aerodynamic interactions simultaneous spin, pitch and yaw motions between aircraft and jettisoned loads usinq [AIAA PAPER 71-279) 871-22004 trajectory analysis TBEIJST AUGIEHTATIOU [ OUBRA-TP-849 J N71-18464 Book on aircraft gas turbine engine technoloqy TRAISIISSIOB LOSS covering combustion chambers. exhaust systems, Bibbed aluminum panels airborne sound transmission TRANSONIC COMPRESSORS SWBJECT INDEX

loss, evaluatinq structural dampinq effects Parametric engine study for Mach 0.98 commercial A71-21431 air transport with supercritical winq TRANSONIC COHPRESSORS r NASA-TM-X-529611 N71-18733 Transonic compressor rotors blade camberline shape Report of transport aircraft accident and probable optimization by various tip diffusion causes factor-ratio combinations r NTSB-AAR-71-4 1 N71-19040 A7 1-20200 Mathematical model of larqe jet transport aircraft TRANSONIC PLOP simulation Transonic qas flows in axisymmetric small throat [ NASA-CR-17561 N71-19239 curvature radius Lava1 nozzle with appreciable TRANSPORT VEEICLES flow parameters variation in transverse Economic and safety factors of nuclear powered direction surface vehicles and aircrafts in transoceanic A71-19732 commerce nonoqraph on transonic shock free potential flow [ NASA-TH-X-52963 1 N71-18628 around quasi-elliptical airfoil sections, TRAISPORTATIOI investiqatinq flow stability under unsteady Preiqht transportation in Great Lakes area for disturbances year 2000 A71-19773 N71- 19320 Ideal qas jet sonic flow past wedqe accordinq to TRANSVERSE OSCILLATION Kirchhoff scheme, testinq sine series solution Transverse and torslonal vibrations of fuselaqe- for converqence wing combination with winq tip fuel tanks, A71-20085 calculatinq mass and stiffness matrix for Computerized transonic airfoil design from elastic bean predetermined supercritical velocity A71-20364 distribution, obtaining equivalent TSR-2 AIRCRAFT incompressible flow throuqh streamline and Terrain-followinq radar for TSR-2 aircraft, potential line network transformation discussinq reliability trials and improvement A7 1- 20 304 A71-19557 Transonic and supersonic dynamic stability TWUBLING HOTION characteristics of variable sweep winq tactical Axial compressor blades surface finish and fatiqne f iqhter aircraft strenqth restoration by vibrational tumblinq [NASA-TN-X-21631 N71-17425 A71-20843 Reqions upstream and downstream from shock waves TWRBINE BLADES of airfoils in uniform and transonic flow Gas-particle mixture cascade flow over turbine I NASA-TT-P-13472 1 N71-1840 1 blades, considerinq momentum/heat transfer and TRANSONIC RIND TWNNELS particle trajectories Wind tunnel history. evolution and use. coverinq [AIAA PAPER 70-7121 A71-20311 low speed variable density, hiqh speed Static pressure contours of turbine rotor blade transonic, supersonic, hypersonic and tips at hiqh nach numbers hvpervelocitv wind tunnels I NASA-TR-X-2170 1 N71-17247 A71- 2 1666 Advanced coolinq systems and heat resistant Sinqle and multiple stinq support evaluation for materials for turbine blades of hiqh temperature unmodified interference free wind tunnel data aeronautical qas turbine enqines over 0.85 to 2.2 n ranqe usinq imaqe method r AGARD-CP-73-71 1 N71-17372 [AIAA PAPER 71-2671 1171-21993 Heat transfer prediction for turbine blade desiqn Transonic wind tunnel wall interference effects N71-17374 experimental determination, investiqatinq porous Mathematical model for calculatinq blade and slotted walls temperatures in convective cooled gas turbines [AIAI PAPER 71-2921 A71-22013 N71-17375 Lift, pitchinq moments and dampinq of delta winqs Efficiency of air coolinq blade desiqn for OlymPUS in slotted transonic wind tunnels with 593 qas turbine enqine perforated walls N71-17376 I NPL-AERO-1307 1 N71-17085 Heat transfer and exchanqe measurements on fixed European subsonic, supersonic. transonic. turbine blades in hiqh temperature combustion hypervelocity and low density wind tunnel chamber characteristics N71-17378 N7 1- 17099 Boundary layer optimization for small turbine TEAISPONDERS blade desiqn with cusped trailinq edge Establishinq minimum operational requirements for N71-17380 airborne air traffic control transponder systems Aerodynamic and thermodynamic performance of sweat [DO-1441 N71-18109 cooled qas turbine engine blades TRANSPORT AIRCRAFT N71-17382 Draw-throuqh coolinq of electronic equipment in Transpiration cooled blades for hiqh temperature subsonic and supersonic commercial jet inlets in qas turbine engines transports, discussinq internal circulation N71-17384 system desiqn Performance prediction for turbine blade film ISAE-AIR-64A 1 1171-19642 coolinq with injection through holes Desiqn objectives for subsonic, transonic and r NASA-CR-11637b 1 N71-17388 supersonic civil transport flyinq Thermal fatique behavior of fiber reinforced characteristics based on MIL-P-8785, considerinq nickel alloy gas turbine blades aircraft control N71- 17390 rSAE-ARP-842dl A71-19645 Fabrication of cobalt alloy and nickel alloy qas Pliqht characteristics of V/STOL transport model turbine blades and disks with four pod-mounted lift fans N71-17392 I NASA-TN-D-61291 N71-17423 Film coolinq of qas turbine blades by air Pliqht characteristics of let-flap STOL transport injection throuqh holes aircraft durinq approach and landinq N71-17394 INASA-TN-D-62251 1171-17433 Heat transfer in liquid metal cooled qas turbine Causes and results of aircraft accident of Lear blades jet aircraft N71-17398 INTSB-ARR-71-3 1 N71-17511 Computerized optimization of thermal resistant gas Cause and result of transport aircraft accident turbine blades NTSB-AIR-70-27 1 N71-17512 N71-17400 Tenative airworthiness standards for porered lift Technoloqical aspects of film coolinq for blades transport cateqory aircraft in hiqh temperature qas turbines N71-17553 N71-17404 Noise associated with operation of C-9A TWO dimensional cascade test of let flap turbine /aeromedical evacuation/ aircraft I AD-7152221 1171-18x9

A-52 SWBJECT IIDBI TVBBULXIZ FLOW

performance of stator uith uire mesh shell bladinq performance of turbogenerators and qas turbine during cold air investigation of tnrbine uith engines transpiration cooled stator blades - Vol. 3 1171-17373 [ BASA-TB-X-2166 J 117 1- 17590 TWBBOJET XI61WXS TORBI- 13161BES Subsonic jet engine noise reduction. considerinq Effects of specific speed on experimental turbojets, turbofans and jet suppressors performance of radial inflou tnrbine A71-21814 [ 11ASA-TU-D-6182 J 1171-17354 Performance of short modular tnrbojet combustor Tuo dimensional cascade,test of jet flap tnrbine segment uith ASTB-A1 fuel rotor blade [HASl-TU-D-6167] 1171-17414 [ EASA-TB-1-2183 J 1171-17589 Effects of turbojet engine unstart on engine Performance of stator uith 'uire mesh shell blading operation and characteristics of stall during cold air investiqation of tnrbine uith propaqation through compressor and inlet system transpiration cooled stator blades - Vol. 3 [ BASA-21-1-2192 J 1171-18138 [ HASA-TB-X-2166] 1171-17590 Combustion stability limits for suirl-jet Computer program for design and analysis of V/STOL combustor modules combining air suirl and tip turbine fans impinqinq jet atomization of ASTB A-1 fuel r IASA-T8-D-6161] 1171-17641 [ IASA-TI-1-2218 1 1171-18560 Plightuorthy nacelle development to minimize fan Effect of various diffuser designs on performance compressor noise radiation - Vol. 4 of experimental turbojet combustor insensitive [ BASA-CB-1714 1 1171-17660 to radial distortion of inlet airflou TUBBIIX WHXXLS [ nASA-TB-1-2216J 1171-18561 Cyclic thermal crackinq and fatigue analysis in TWBBOPBOP EIGIFlIS larqe steam turbine rotors uith three Equation derived for operation of turboprop engine dimensional temperature and triaxial stress uith high pressure compressor controlling gas computation temperature at turbine front [ ASBE PAPER 70-PUB-1 ] 171-20198 A71-20031 Radial flou energy losses in rotatinq cylindrical TWBBWLXICE cascade of inuard-flow turbine uheel, Feasibility evaluation on optical probing of determining profile losses and exit blade angle snpersonic aerodynamic turbulence uith A7l-22014 statistical correlation TWPBOCOBPBESSOBS SASA-TB-D-6077 J 1171-17444 Turbocharged diesel engine precompressed inlet air TWBBULEICE XFFXCTS cooling by evaporation cooling, considering Synoptic meteorological conditions for clear air iiater injection effects on centrifuqal turbulence and turbulence effects on aircraft compressor flight characteristics A71-20781 [ DLB-PB-70-29 J 1171-17145 Axial compressor blades surface finish and fatigue Aerodynamic broadband noise mechanism applicable strength restoration by vibrational tumbling to axial compressors A71-20843 [ 11ASA-CB- 1743J 1171-17958 Bultistage gas turbine design optimization. usiuq TWBBULEIT BOWIDART LATER parameter and component analysis uith computer Viscosity effects on three dimensional supersonic calculations flou around circular half cones on flat plate, 171-21267 examining turbulent boundary layer separation Performance of axial flow compressor for Brayton A71-19743 cycle electrical pouer generating svstem with Turbulent boundary layer pressure fluctuations arqon in-flight measurements on Boeing 737 aircraft, r11ASA-TU-X-21941 1171-17882 obtaining power spectral densities and BUS Aerodynamic broadband noise mechanism applicable pressure fluctuations for various Mach numbers to axial compressors A71-21426 [UASA-CB-1743 J 171-17958 cross flou profiles for compressible turbulent TOBBOIAI XI611115 boundary layers with and uithout flou reversal Subsonic jet engine noise reduction, considerinq ria hodoqraph models family turbojets. turbofans and let suppressors A71-22033 A71-21014 Pressure gradient effects on three dimensional Design point selection on fan characteristic curve turbulent boundary layer of infinite span of turbofan engines, discossinq bypass ratio sueptback wing effect on specific impulse, flight velocitv and [ APL-AERO-1305 J n7i-1-1179 turbine inlet temperature Entrainment coefficient used for computation of A71-22042 tvo dimensional incompressible turbulent Acoustic and aerodynamic performance of six foot boundary lavers diameter fan for turbofan engines uith noise [ ABC-R/B- 36 43 ] 1171-18424 suppressors Calculation of streamline coordinates for three [ UASA-T11-D-6178] 1171-17254 dimensional turbulent boundary layer in vaneless Effect of atmospheric humidity on characteristics diffuser of turbofan engine [ ABC-B/B-3646 J N71-18468 [ AD-7 152321 971-17728 Sound field effects on flat plate heat transfer in Gas dynamics of fan jets at various injection turbulent boundarv layer angles [ BEPT-70-8 J n7i-18572 [ AD-7147901 171- 18034 TWBBWLXIT ?LOW Design and tests of UTF-48 single rotor compressor Large aspect ratio rectangular duct uith enqine nonuniform surface texture. investiqatinq IAD-7156261 U71-10801 turbulent flou, maximum velocity positions and Annular diffuser and combustor assembly in full zero shear stress scale duct burner for supersonic turbofan engine A71-18772 [ BASA-TN-D-6163 J 1171-18802 Transient and turbulent flow structure in rake TOBBO?AIS behind thin plates in uind tunnel. noting Acoustic and aerodynamic performance of six foot velocity fields. tenperature and initial diameter fan for turbofan enqines uith noise boundary layers suppressors A71-19750 [ BASA-TU-D-6178 J 1171-17254 Stationary longitudinal turbulent flou of air uith Computer program for design and analysis of V/STOL equilibrium ionization and dissociation around tip turbine fans plate. calculatinq heat exchange and frictional r11ASA-TS-D-6161 J 1171-17641 draa Pliqhtuorthy nacelle development to minimize fan A71-21922 compressor noise radiation - Val. 4 Biqh turbulent flou simulation in hlperTelOCity [ HAS A-CB- 1710 ] 1171-17668 wind tunnel for reentry vehicles operational TWBBOGXIIUTOPS testinq, discussing nozzle qas dynamic and nigh entrance temperatures for improved mechanical design

A-53 VIRGINII SUBJECT INDEX

lander spacecraft at hypersonic speed r NASA-TU-X-2205 1 N71-17253 VIRGINIA W Conqressional hearinqs on Boeinq 727 use of WALL PLOW Hashinqton National Airport continuous flow past plate located perpendicular N71-17697 to wall vith inviscid incompressible fluid VISCOSITY havinq linear variation of velocity with heiqht viscosity effects on three dimensional supersonic A71-20828 flow around circular half cones on flat plate, HALL PRESSURE examininq turbulent boundary layer separation Hall pressure and heat transfer distribution on A71-19743 delta winqs in rarefied hypersonic flow VISCOUS DRAG r REPT-70-9 3 1171-18423 viscous draq on variable sweep winqs and wedges at WAUKEL BUGINES supersonic and hypersonic speeds aotorized glider equipped with Wankel enqine for r ARC-R/R-3623] N71-17109 self powered takeoff, describing prototype VISCOUS PLOW desiqn and flight test data viscous qas flow interaction on delta wing and A71-21769 oblique airfoil at Hach number of infinity WARUIUG STSTEPIS 1171-19739 Aircraft visual warninq indicatinq system, Computer calculation of hiqh Reynolds number outlininq desiqn criteria, color and brightness viscous and inviscid flow over arbitrary shaped recommendations two dimensional bodies and airfoils [ SAE-ARP-1088] A71-19644 A71-20 3 13 Human role in Aerospace Defense Command Investiqatinq supersonic viscous qas flow around naviqation, discussinq Airborne warning And blunt bodies control Svstem and naviqational aspects of ADC N71-16902 mission Numerical computation of viscous hypersonic flow A71-20346 around slender bodies WATER EROSIOU N7 1- 16951 International conference on rain erosion and VISUAL AIDS associated phenomena N71-17906 Aircraft visual warninq indicatinq system, r ~~-715100 1 outlininq desiqn criteria, color and briqhtness Development and calibration of nach 1.2 rain recommendations erosion test apparatus ISAE-ARP-1088 J 811-19644 [AD-7159091 N71-18651 VISUAL PLIGET RULES WATER PLOW VPR flyinq under adverse weather conditions, Results of two-phase blowdown experiments with discussinq radio naviqational aid equipment and straiqht tube test section and steam-water communication with qround stations mixtures A71-20683 [ AECL-36641 N71-18161 VPR flyinq under bad weather conditions, WATER IUJICTIOU discussinq fliqht throuqh and above cloud Turbocharqed diesel enqine precompressed inlet air layers, need for radiotelephone communication coolinq by evaporation coolinq, considering and qround radar support water injection effects on centrifuqal A71-21767 compressor VISUAL OBSERVATION A71-20781 Feasibility of electroluminescent panels and rotor HATER VAPOR tip liqhtinq for military helicopters to aid in Commercial aviation stratospheric water vapor observation by other vehicles in formation injections influence on radiation budget, ozone, [AD-715851 J N71- 18734 polar niqht cloudiness and potential climatic VISUAL TASKS effects Feasibility of visual trackinq to determine effect A71-21822 of laq in simulated aircraft dynamics Hater vapor condensation effects on methane-air rnn-R-479 J N71-18838 combustion qases for aerodynamic test medium VOICE COllUUICATION [AIAA PAPER 71-2581 A71-21986 Data communication role in National Airspace Hypersonic two phase flow realized by air-water System, concerninq radar and fliqht data mixtures acquisition, intersystem transfer and voice [ BRVTDG-PBHT-70-13 N71-18441 control WAVE DIFFRACTION [AIAA PAPER 71-2481 A71-19722 Shock wave diffraction by two dimensional weak VOLUlETRIC STRAIU disturbances, usinq aerodynamics blast method Ground effect vehicles limitinq volumetric A71-19255 dissipations from air cushion and propulsion Three dimensional diffraction of sonic booms by systems with fluid boundary by Coanda effect corners of structures A71-19923 NASA-CR-1728 J N71-18029 VORTEX BREAKDOWN SATE PBOPAGATIOI Vortex breakdown on slender sharp edqed and Plane compression waves propaqation into constant modified delta winqs with varyinq sweep anqles state nonviscous fluid, considering shock investiqated in wind tunnel usinq schlieren formation of pressure pulses and overpressure as system for flow visualization function of time [AIAA PAPER 69-7781 171-22028 A71-19961 TORTICBS WBAPOI SISTElS Pluctuatinq circulation, lift and flow induced P-15 air superiority fighter, describinq military structural vibrations of two dimensional bodies, requirements, program management and procedures includinq vortex sheddinq on sluice qates in terms of speed, maneuverability, acceleration All-19592 and weaponry Hind tunnel experiments on vortex shedding from A71-19078 circular cylinders in oscillating free stream Worldwide aeronautical charts maintenance for A71-19908 weapon systems support, discussing data sources Aircraft fuel and air conditioninq systems vortex A11-21254 valves and diodes, examininq flow patterns into Performance test methods and equipment for and out of chambers aircraft avionics and weapons systems, A71-20556 discussing computer integration with radar and Vortex-lattice FORTRAN proqram for estimating phototheodolite range instrumentation system subsonic aerodynamic characteristics of complex A71-21660 planforms WEAR TESTS r NASA-TN-D-61421 171-17424 Device for jet fuels antiwear properties Trailinq vortex systems qenerated by jet-flapped measurement under rolling friction winq operatinq at high winq lift coefficients All-19493 l AD-715315 1 1171-17753

&-56 SUBJECT IlDEI

UEATHKS wind tunnel testing of base pressure model VPR flying under adverse weather conditions, attached to long cylindrical body extended and discussing radio navigational aid equipment and snpported far upstream communication with ground stations [ AIAA PAPER 71-268 J 171-21994 171-20683 RocketAauncher aerodynamic interference effects VPB flying under bad weather conditions, investigation by wind tunnel simulation, discussing flight through and above cloud determining interference coefficients for layers. need for radiotelephone communication rockets ballistic dispersion calculations and ground radar snpport [AIAA PAPER 71-2691 A71-21995 A71-21767 Three deqree of freedom gas bearing for uind UKATHKK DODIFICATIO1 tunnel dynamic measurements, allouing models Spatial correlations betueen inside cumulus cloud simultaneous spin, pitch and yau motions conditions and precipitation onset and intensity [AIAA PAPER 71-2791 A71-22004 for modification experiments from aircraft Airfoil profile draq measurements, correlating penetration measurements full scale flight tests and scale model tests in A71- 21I50 transonic and high Reynolds number wind tunnels leteorological observations for terminal weather [AIAA PAPER 71-2893 A71-22012 modification in aviation. noting airport fog Eiqh speed aircraft external store separation dispersal testing and prediction techniques, considering A71-21732 flow field survey, dynamically similar drop SED61 FLOU models and captive trajectory methods Shock wave interaction with wedge moving at [ AIAA PAPER 71-294) A71-22014 snpersonic speed, calculating geometry of wind tunnel boundary interference on V/STOL model regions formed intersecting wavefronts calcnlated in test section with solid vertical A71-19741 and slotted horizontal walls, using image method Ideal gas jet sonic flow past wedge according to and Fourier transforms Kirchhoff scheme, testing sine series solution [AIAA PAPER 70-5751 A71-22029 for convergence Aerodynamic draq measurements on VC-10 aircraft A71-20085 subsonic wind tunnel models Supersonic flow witb separated shock wave past [ ARC-CP-1125 ] 171-17118 wedqe shaped profile rake blockage corrections for rectangnlar flat [ BASA-TT-P-13469 J 117 1- 17443 plates subjected to separated flor in closed WBDGBS wind tunnel Viscons draq on variable sweep wings and uedges at IARC-R/l-3649] 1171-18456 supersonic and hypersonic speeds Aypersonic lor density wind tunnel includinq [ ARC-B/I-3623] 1171-17109 auxiliary equipment for electroforming and IEI6HT AIALYSIS electroplating wind tunnel models Parachute weiqht. configaration and strength [ ElEU-PB-U-70-51] U71-18593 correlations for tradeoffs and design Auxiliary inlet ejector nozzle designed for 171-18900 supersonic cruise aircraft UEI6HT IIDICATOBS [ RASA-T!I-X-2182] 871-18863 Snpersonic rind tunnel electromagnetic balance @IUD TUUHEL STABILIR TESTS with superconducting coils Low speed wind tunnel stability tests of small A71-20151 guide surface. slotted solid, ring slot, cross IKSTLAUD UHIBLUIUD HBLICOPTEP and streamer decelerators, considering Eerixation of ztability bonndzries in wind tnnn-Is oarachutes and draa measurement for bodies towed by cables A71-20310 rAPC-R/l-3644] H71-18461 wind tunnel dynamic stability testing of WIDTH unconventional aircraft confiqurations without Turbulent wakes of flat and rotationally stinq support symmetrical bodies noting width development [AIAA PAPER 71-2761 171-22001 1171-18472 Aerodynamic support interference in wind tnnnel WIlD DIBBCTIOII testing of configurations involving bulbous Sea state, wind velocity and wind direction base, mass addition, transition near base and reqression analysis for ground effect machines hypersonic low density flows [ UPL-ROVERCRAPT-16 ] 1171-17144 [AIAA PAPER 71-277 J 171-22002 IIID BFPECTS Launch and data reduction in supersonic wind linimizinq performance criterion to analyze tunnel free fliqht testing of high fineness ability of automatically controlled aircraft to ratio bodies maintain accurate flight path control durinq [AIAA PAPER 71-2781 A71-22003 landinq approach Uind tunnel aerodynamic stability tests on [ BASA-TB-D-6230 1 1171- 18761 chimneys rith pipes and helical winding WIlD TUlIIKL APPAUATUS stabilizers Supersonic wind tunnel electromagnetic balance [ UPL-AERO-1310 1 H71-17334 uith superconducting coils Transonic and supersonic dynamic stability 1171-20151 characteristics of variable sweep ring tactical IIID TU11111 CALIBBATIOII fighter aircraft Return circuit rectanqular wind tunnel design. [ BASA-TI-X-2163 1 871-17425 construction, instrumentation and calibration, Uind tunnel tests to determine unsteady discussinq drive. jet inclination, velocity aerodynaaic forces between two lifting surfaces distribution, etc in tandem A71-21305 [ UASA-TT-P-13482) 171-18397 UIDD TUUUBL DRIVES Uind tunnel testinq of interference lift of tandem Return circuit rectanqular wind tunnel desiqn, winq aircraft lifting surfaces construction, instrumentation and calibration, [ OBERA-TP-890] ~71-18449 discussing drive, jet inclination, velocity Derivation of stability boundaries in wind tunnels distribution, etc for bodies towed by cables A71-21305 ARC-R/B-3644 J 171-18461 IIUD TUlIIBL BODEL5 wind tunnel testinq of aerodynamic interactions Ground boundary layer effects of fixed ground between aircraft and jettisoned loads nsing plane for powered STOL rind tunnel model, trajectory analysis discussinq flow breakdown criteria. contraction r OBERA-TP-8491 871-18464 laq. strut fairinq interference, etc WIDD TUllEL UALLS IAIAA PAPER 71-2661 A71-21992 Transonic wind tunnel wall interference effects Sinqle and multiple stinq support evaluation for experiaental determination, investigating porous unmodified interference free rind tunnel data and slotted walls over 0.85 to 2.2 I ranqe using imaqe method [AIAA PAPER 71-2921 A71-22013 [AIAA PAPER 71-267J A71-21993 wind tunnel boundary interference on V/STOL model calculated in test section with solid vertical

A-57 WIUD TUNUELS SUBJECT IUDEI

and slotted horizontal walls, using imaqe method WEENCUBS and Fourier transforms Ultrasonic wrench for applying vibratory enerqy to [AIAA PAPER 70-5751 A71-22029 mechanical fasteners Lift, pitchinq moments and damping of delta wings r NASA-CASE-IPS-20586 ] A71-17686 in slotted transonic wind tunnels with perforated walls [NPL-AERO-13071 N71-17085 X WIND TIJNlELS I EAIS Transient and turbulent flow structure in wake Aircraft altimeter containinq X ray source behind thin plates in wind tunnel, notinq 171-16993 velocity fields, temperature and initial 1-15 AIRCRAFT boundary layers Plight tests to determine reliability of X-15 self A71-19750 adaptive flight control system Three deqree of freedom gas bearinq for wind [ NASA-TN-D-62081 1171-18422 tunnel dynamic measurements. allowing models simultaneous spin, pitch and yaw motions lAIAA PAPER 71-2793 A71-22004 Y Sonic boom wind tunnel testinq techniques at hiqh YAK 40 AIRCRAFT Hach numbers, qivinq sample pressure siqnatures Soviet book on Yak-40 passenqer transport aircraft [AIAA PAPER 71-2801 A71-22006 confiqurational design and aerodynamic Thermal stress analysis of wind tunnel corners characteristics covering stability, [ARC-CP-11171 N71-17100 controllability and fliqht under special Wake blockaqe corrections for rectanqular flat conditions plates subjected to separated flow in closed 871-20750 wind tunnel [ARC-R/fl-3649] N71-18456 Technique of ertrapolatinq measured near-field Z overpressure data to larqer altitude applied to ZERO LIFT wind tunnel overpressure data Reactinq and nonreacting qases laminar boundary [NASA-Tfl-X-22191 N71-18559 lager flows over two dimensional and WIND VELOCITT axisymmetric bodies at zero lift, compariuq Sea state, wind velocity and wind direction numerical methods reqression analysis for ground effect machines A71-19860 r NPL-HOVERCRAFT-16 1 N71-17144 WING FLAPS Airplane winq hiqh lift and flap designs by interactive computer qraphics system [AIAA PAPER 71-2271 A71-19705 Trailinq vortex systems qenerated bv let-flamed winq operatinq at hiqh winq lift coefficients r AD-7 15315 1 N71-17753 WING LOADING Sailwinq aerodynamic characteristics, obtaininq aerodynamic loadinq by two dimensional flexible airfoil and Prandtl liftiuq line theories A71-20303 Center of qravity vertical acceleration and winq stresses of Boeiuq 720-8 aircraft [TB-87-1970 1 N71-17119 WING OSCILLATIONS Solid foil small oscillations in unsteady incompressible flow, mappinq physical plane and correspoudinq complex potential reqion onto curvilinear half strip A71-20088 Numerical analysis of low frequency subsonic liftinq surface theory notinq winq oscillations in steady flow [ARC-R/H-36341 N71-18425 WING PANELS Ball forminq technique application to A1 alloys structural part contourinq, discussinq 1-1011 winq panel formiuq and prestress toolinq A71-21681 WING PLAUPOEIS Hypersonic minimum draq slender winq leadinq edqe shape for qiven airfoil section, usinq Newtonian theory 1171-22039 WING PEOPILES Wind tunnel tests to determine unsteady aerodynamic forces between two liftinq surfaces in tandem r~~~~-~~-~-134821 N71-18397 WING TANKS Transverse and torsional vibrations of fuselaqe- winq combination with winq tip fuel tanks, calculatiuq mass and stiffness matrix for elastic beam b71-20364 WIEGS Filampnt windinq nanufacturinq methods usinq unidirectional qlass reinforcements for desiqu and fabrication of aircraft viuq structure r snE PAPER ~n-70-4061 A71-20546 Iathematical models for control surface winqs in subsonic unsteady flow [ONERA-TP-889 1 N71-18473

A-58 PERSONAL AUTHOR INDEX

AERONAUTICAL ENGINEERING / A Special Bibliography (Suppl. 5) MAY 1971

Typical Personal Author Index Listing

PERSONAL AUTHOR ALLISOI. D. 0. for improvinq the Real-qas effects on the draq and trajectories of a crashrorthiness of intearal fuel tanks Final nonliftinq 140 deg conical aeroshell dorinq Kars report, 1967 - 1Q70 entry [FRA-YA-70-46 J [ NASA-TN-D-62401 N71-18015 ALIASOI. 1. P. Lightning current transfer characteristics of the p-static discharger installations A71-19935 NUMBER NUMBER ABCEEB, J. S. NASA space vehicle design criteria /structures/ - Structural vibration prediction Ltstings in this index are arranged alphabetically by personal author The [ NASA-SP-8050 J 171-19281 title of the document provides the user wtth a brief descrrptton of the ABIBI. E., JB. subject matter The report number helps to indicate the type of document Finite element analysis of structures in the cited le 9 . NASA report translation. NASA contractor report) The accession plastic range r NASA-CR-1649 J 1171-19276 number is lscated beneath and to the right of the title eg N71-11019 ABIOLDI. E. A. Under any one author's name the accession numbers are arranged In se- Aerodynamic broadband noise mechanisms applicable quence with the IAA accession numbers appearmg first to axial compressors [ AASA-CR-1743 J 1171- 17958 ilROIIOUITZ. 1. Dispersion modeling of airport pollution A A71-21024 ACKEE. 1. U. ABTEIEIKO. I. P. Acoustic and aerodynamic performance of a Service life of bearing elements of aircraft gear 6-foot-diameter fan for turbofan enqines. 3 - pumps Performance with noise suppressors A71-20793 I'NASA-TN-D-6178 1 1171-17254 ABUTIOIIAI, G. I. ADAIS. P. A. Limits of applicability of one exact solution of Jn dynamic stabilitv testina of unconventional the problem involving interaction of a shock configurations . wave with a wedge moving at supersonic speed [AIAA PAPER 71-2761 A71-2200 1 A71 - 1974 1 ADI. C. E. ASEBIBI, E. V. Filament winding an aircraft wing structure Ratio of turbulent flight miles to total fliqht r SEE PAPER EI-70-406] 171-20546 miles in the altitude ranqe 45.000-65.000 ft AKAHATSU. I. 1171-20314 Uing lifting line representation - Application to ATEAIS, I. the two winqs in tandem interaction System aspects of air traffic control [ ONERA-TP-8911 1171-18439 A71-21335 AKITAIA. T. ATTUOOD. T. V. The airport access problem in Tokyo The application of computer aids in the analysis n7i-18953 of fault data generated by a large data handling AKSEBOV, A. F. system Laboratory device for studying antiwear properties A71-19556 of jet fuels AUER, E. @. All-19493 Computer program for preliminary design and ALECSAIDEESCO. C. analysis of V/STOL tip-turbine fans Design principles of a ground effect vehicle in [ EASA-TN-D-6161] N71-17641 which the limitation of volumetric dissipations AVDEET, V. E. is accomplished with the help of a flnia Experimental investigation of raaial-flow energy boundary obtained by means of the Coanda effect losses in the rotating circular 1171-19923 cylindrical-profile cascade of an inward-flow- ALBKSAIDBOV. K. K. turbine wheel Some results of investiqations of centripetal and 171-22044 radial-flaw staqes AVDUBTSKII* 1. S. A71-22049 Investigation of three-dimensional separation.flow ALEIASOVA. I. A. around half-cones mounted on a flat plate Calculation of losses in the vaneless diffuser of 1171- 19743 a centrifnqal compressor A71-21266 ALESI, P. B High entry temperature turbine on turboreactors BACK, 1. E. and qas turbines Plow coefficients for supersonic nozzles with 1171-17373 comparativelr small radins of curvature throats ALLEGBE. J. 171-19877 Delta wing study in a low density hypersonic flou BAILBT, B. E, CREPT-70-9 J N71-18423 Static-pressure contours in the blade passage at ALLEI. D. the tip of several high aach number rotors Air traffic control - A feasibility study [ R AS A-TI-I- 2170 ] 1171-17247 171-18105 BAILET. E. G. ALLEI. U. K. Helicopter application studies of the variable Traffic control system and method Patent deflection thruster jet flap Final report [ NASA-CASE-GSC-10087-1 J 1171-19287 [ AD-715071 1 N71-17907

E- 1 BAKER. P. 0. PERSONAL AOTEOR INDEX

BAKER, P. 0. BEZROKIKE, S. D. The desiqn and development of an aircraft mountinq Study of inviscid flows of a radiating gas with printed-circuit spiral aerial covering the ranqe the aid of differential approximations 200-800 HHZ All-19183 I r RAE-TR-700623 N71-18519 BBAT. U. V. BhKLAIKIN. V- I. Pliqht test measurement of exterior turbulent Analysis of aircraft radio-compass error boundary layer pressure fluctuations on Boeinq All-20787 model 737 airplane BAKUH, B. I. A71-21926 Characteristics of the working flow in hypersonic BIAGLOU, J. A. shock tubes in the presence of solid-particle Effect of various diffuser desiqns on the impurities performance of an experimental turbojet 171-18916 combustor insensitive to radial distortion of Nature of the anomalous seeded flow past blunted inlet airflow bodies in hypersonic wind tunnels r NASA-TH-X-2216 1 N71-18561 A71-18924 BIDDLE. J. E. BALL. T. P. Evaluation of film cooling performance on gas Noise reduction operational procedures turbine surfaces A71-21813 N71-17395 BALLENGEE, D. B. BIERACE, I(. P.. JE. Vortex sheddinq from circular cylinders in an The role of communications in the National oscillating freestrean Airspace System A71-19908 rAIAA PAPER 71-2481 All-19722 BARSBAI. 1. 1. BIGLEU. s. G. Nonlinear theory of a rotor in an axial reqime The need, meaning and usefulness of meteorological 1171-19740 observations for aviation BASSIUOT, E. A71-21732 Coolinq of turbine distribution blades throuqh BISEOP. D. E. impact effect Experimental atmospheric absorption values from N71-17397 aircraft flyover noise signals BASTIDON, J. A71-21425 Establishment of take-off and landinq safetr Variability of flyover noise measures for repeated marqins for the Brequet 941 fliqhts of turbojet and piston engine transport r NASA-TT-F-13453 1 N71-17441 aircraft BAIENDALE. E. B. INASA-CR-17521 N71-18865 Some mechanical desiqn problems of turbine blades BISEOP. J. B. and discs A comparison of the cruise efficiency and range of N71- 17401 marine vehicles and aircraft BAXTEB. P. S. A. r NPL-HOVERCRAFT-121 N71-17161 An investiqation of the stresses in a wind tunnel BLAE~; B. J. corner section Effect of exit area variation on the performance r ARC-CP-1 1171 N71-17100 of an auxiliary inlet ejector nozzle at nach BAYLBI, P. J. numbers from 0 to 1.27 Transpiration-cooled turbines r N AS A-TH- X- 2 1823 N71-18863 N71-17383 BLAISB. E. T. BEAOBOIS, 8. Hethods and apparatus employing vibratory energy Attitudes taken with reqard to amendments to the for wrenchinq Patent warsaw Convention [ NASA-CASE-HFS-20586 3 1171-17686 r REPT-1970/8-E1 N71-18100 BLAUD. II. P. BECKER. 1. B. Fluidic sensors for measurinq engine pressure Aircraft and the environment - Airlines and ratio and turbine inlet temperature community A7 1-20586 A71-21815 BLASER, D. A. BECKVITE, a. B. Boundary-layer discontinuity on a helicopter rotor The need, meaninq and usefulness of meteoroloqical blade in hoverinq observations for aviation rAIAA PAPER 69-1973 1171-20307 A71-21732 BLOII. 1. E. BEBUIUG, P. P. Flight testinq the DC-IO Cold-air investiqation of a turbine with A71-19085 transpiration-cooled stator blades. 2 - BOBBITT. P. J. Performance of stator with wire-mesh shell Real-gas effects on the draq and trajectories of a bladinq nonliftinq 140 deq conical aeroshell during Hars r NASA-TH-X-2166] N71-17590 entry BELDIUG. J. A., JB. NASA-TN-D-6240 3 171-18015 The effect of tailpipe length on combustor BOBOBYKIU. 10. A. stability Evaluaiion of the precision of executinq the N71-17725 outside contours of units with allowance for the BELLAlY, J. C. elastic characteristics of the elements Some basic characteristics of observational data assembled and equipment All-21722 All-20792 BEEEZIUK, A. I. BOGOSLAVSKII. 1. E. Evaluation of the precision of executinq the Practical aerodynamics of the Iak-40 aircraftA71-20750 outside contours of units with allowance for the elastic characteristics of the elements BOISS1AO. J.-P. assembled and equipment Computation of the aerodynamic interactions A 71- 20 79 2 between aircraft lifting elements in supersonic BEBGEB, 1. 8. steady or unsteady flow N71-18462 Precision forqinq of spiral bevel qears for Army r ONERA-TP-850 1 helicopters Final report, Jan. 1968 - Apr. 1970 BOLLAY. E. I AD-7 15919 1 N71-18920 The need, meaning and usefulness of meteoroloqical BBBSOPP. I!. E. observations for aviation A71-21732 Operatins system reliability for the Navy advanced avionic diqital computer BOIDI. 1. J. A71-18833 An alqorithm for digital resolution of ranqe for BEBTBAUD. J. 8. V/STOL aircraft N71-18566 Technoloaical aspects of turbine blade cooling by [ NASA-TN-D-62321 air film BOOTB, 1. If. N71- 17404 Thermal pump-compressor for space use Patent [ NASA-CASE-XLA-00377] N71-17610

E-2 PSPSOIAL AQTUOP IIDSI CAUPBSLL. J. 1.

BOOTES. S. E. BBOWBS. 5. D. An in-fliqht investigation of lateral- directional Remarks prepared for delivery before the 1970 ATA dynamics for the landing approach Final Engineering and maintenance Conference technical report 171-17779 [ AD-715317 J 171-17792 Remarks to the EXeaItiTe Program on Transportation BOWSW. 1. K. and Logistics Air traffic control - A feasibility study 1111-17799 1171-18105 Remarks prepared for deliver7 before the BOWCLI. A. Associaticat of Local Transport Airlines Fall IAE multi-source schlieren apparatus for 5-foot x Quarterly Regional meeting 5-foot trisonic wind tunnel 879-18078 A71-19924 Remarks prepared for delivery before the 1970 BBADSEAW, P. Uational Airports Conference The response of a turbulent bonndary layer on an 1171-18079 /infinite/ suept uing to the sadden reaoval of BROWFlI. I. 6. pressure gradient Alternative logistics STstems for expensive parts r 11PL-AERO-1305] 871-17179 - An airline stndy BBAIDLL. D. L. 871-18118 Communications. naviqation and surveillance for BBQDIII. S. 0. aircraft and marine vessels operating in the Analysis of aircraft radio-compass error north Atlantic region 171-20787 A71-18808 BRIIETAQD. B. BEAIDEL. W. 1. materials development for high temperature Ball forming solves contourinq problems turbines A71-21681 1171-17392 BBAISTSPTSB, J. E. BPTSOI. A. S.. JB. Experimental performance and combustion stability minimum time turns for a snpersonic airplane at of a full scale duct burner for a supersonic constant altitude turbofan engine A71-22032 [ 8ASA-TI-E6163J 1171-18882 BQSLL. D. A. BBSEV, I. U. An experimental investigation of the airflow over Viscous gas flow in a shock layer in the presence a cavity with antiresonance devices of equilibrium chemical reactions [ lIASA-T11-D-6205] 871-17877 871-16902 BQKOTSBII. T. 6. WSLAID. J. 6.. JB. Plow with a separated shock rave past a Lightning protective coatings for boron and weage-shaped profile graphite fiber reinforced plastics [HASA-TT-F-13469 I 171-17443 A71-19944 BQLLAPD. J. B. BRICK, E. 0. Some mechanical design problems of turbine blades The effects of lightning attachment phenomena on and discs aircraft design 1171-17401 A71-19936 BQPCKHABDT. P. 1. BPISCOL, J. Prospectus for a European company with regard to De-icing of runways from the air the operation of reqional application satellite A71-19425 systems BBISTOL. C. W.. JB. 871-17181 Gas turbine enqme enssion characteristics and BURGE. E. 1. future outlook A study of the use of liquid base foams for jet A71-21820 noise reduction BPOCABD. J. [ UASA-CR- 16951 871-19139 Inventory of the principal European wind tnnnels BQBLACOI. 1. I. capable of being used for aerodynamic tests in Equivalent tests of aircraft engines the Post Apollo proqramme A71-21115 871-17099 BQPSTADT, P. 1. BBODT. E. I. Unstart and stall interactions between a turbojet Displays in the National Airspace System enqine and an axisyametric inlet with 60-percent [AIAA PAPER 71-2471 A11- 19721 internal-area contraction BROOKS. D. 1. [ SASA-TI-X-2192) 1171-18138 Store separation from high speed aircraft with BURWOOD-SUITE. A. emphasis on comparisons of predictions and Pibre strengthened nickel-base alloy flight test results 1111-17390 [AIAA PAPER 71-2941 A71-22014 BUIBAQU, 0. BBOQI. B. E. Frequency distribntions and extreme values of the Land use strateqies for aircraft noise alleviation center of gravity acceleration and of the stress A71-21818 on lower wing snrface of a Boeing 720-B BBOPB. C. A., JB. [ TB-87-1970 J 871-17119 Supersonic aerodynamic and wake characteristics of Service loads occurring on main landing gears of larqe-angle cones at low Reynolds numbers F-104G type airplanes including effects of model support [FB-82-1969 J 871-18532 [AIAA PAPER 71-264') A7 1-21990 Experimental wake survey behind a 120 deg included ansle cone at angles of attack of 0 deg and 5 C d9. nach numbers from 1.60 to 3.95, and CAE11. 1. 5. lonqitndinal stations varying from 1.0 to 8.39 Transonic airfoil design body diameters All-20304 [ HASA-T!l-X-2139] 1171-1~1480 CALOGBPAS. J. E. BBOWI. F. W. Unstart and stall interactions between a tnrbolet The use of a laser Doppler velocimeter in engine and an axisysmetric inlet with 60-percent snpersonic flow internal-area contraction [AIAA PaPER 71-287 J All-22010 [ U AS A-T 0-1- 2 192 ] 871-18138 BBOPI. 5. C. CALTERT, 6. S. A technique for evaluatinq parameter variations An experimental cooled radial turbine for automatically controlled aircraft with an 1171-17381 application to the landing approach CAUPBSLL. J. F. [ EASA-TU-D-6230 J 1171-18761 Experimental wake survey behind a 120 deq included BBOPI. T. J. anqle cone at angles of attack of 0 deq and 5 Statistics of the sound field of a source above a deq, Each numbers from 1.60 to 3.95, and rowh. imperfectly reflectinq surface longitndinal stations varying from 1.0 to 8.39 A71-21162 body diameters CAUTOE, S. E. PERSONAL AUTEOE IUDEX

[ NASA-TM-X-21391 N71-18480 COUVISSEE, I. CkITOE. S. B. An environmental approach to air transportation communications. navigation and surveillance for needs - Guidelines for federal assistance aircraft and marine vessels operating in the A71-2 1834 North Atlantic reqion COOK. K. E. b71-18808 lass transit to airports - An overview CAEIEL. n. M. 171-18952 Supersonic aerodynamic and wake characteristics of CORE?. 1. C. large-anqle cones at low Reynolds numbers A small computer in range instrumentation includinq effects of model support 1171-21660 [AIAA PAPER 71-2641 A71-21990 COELISS, 1. D. CARUEL, J. A quadratic performance index for a VTOL aircraft Application of film cooling to qas-turbine blades prefilter model reference attitude control N71-17394 System CARVER. J. A. NASA-TN-D-62311 N71-18836 Closed-die forqinqs for the aircraft industry. I COEEADINOI J. C. A71-20075 The Philadelphia Airport oriqin-destination survey CEAI. T.-S. - A statistical analysis Calculation of the turbulent boundary layer in a N71-18958 vortex diffuser COSTE. J. r ARC-R/M-3646 1 N71-18468 wind tunnel investiqation into aerodynamic CEEPPY, D. C. interactions induced by drop loads Development of a fluidic pressure ratio control [ONERA-TP-849] N71-18464 unit for a vertical take-off aircraft lift COOGELIU, E+ B. enqine Economic impact of the Dallas-Fort worth Regional A71-20587 Airport on the north central Texas reqion in CEEN, C. P. 1975 Vortex sheddinq from circular cylinders in an N71-18099 oscillatinq freestream COOTSOURADIS, D. 171-19908 neetinq requirements for high temperature qas CREII, I. K. turbines a challenge to metallurgists Analysis of nonlinear control systems with N71-17389 transport lag COIIDEEY. C. P. 671-20 369 The use of aerodynamic-stabiliziog strakes on CEIEOU. G. chimney stacks supportinq pipes Temperature determinations in the blades of NPL-AERO-13101 N71-17334 convection cooled turbines CRAIG, E. E. 871-17375 Operatinq characteristics of the AFAPL hypersonic CAOBX. D. 1. shock tunnel Technical report, Jun. 1966 - Peb. Unstart and stall interactions between a turbojet 1969 enqine and an axisymmetric inlet with 60-percent [ AD-7159071 N71-18717 internal-area contraction CRAIIPOED, D. A. INASA-TH-X-21921 N71- 181 38 Estimation of the maximum temperature of a swept moa, c. L. leadinq edqe for an equilibrium qlide entry Thermal stress and fatique analysis in turbine A71-18902 rotors CBOTTI, J. R. IASHE PAPER 70-PYR-1 1 A71-20198 The role of state aovernaent in aircraft noise CEREITZBEEG. A. 1. abatement requlation Cell and battery case materials, cell sealinq A71-21825 techniques for sealed silver-zinc batteries COPPEL. R. P. A71-21097 Plow coefficients for supersonic nozzles with CERISTIAUSEII. U. E. comparatively small radius of curvature throats A study of foq clearinq usinq a CO2 laser A71-19877 IAIAA PAPER 69-6701 A71-20308 CUIUIUG, D. P. CEEISTOPEE, J. Experimental wall interference studies in a wind tunnel investiqation into aerodynamic transonic wind tunnel interactions induced by drop loads IAIAA PAPER 71-2921 A71-22013

[ONERA-TP-849 1 N71-18464 COUUIHGEAE, A. I., JR. ~ CERISTOPBER, 1. An efficient, steady, subsonic collocation method The leqal role of states, local qovernments and for solvinq liftinq-surface problems airport proprietors in requlatinq aircraft noise [AIAA PAPER 70-1911 A71-22030 A71-21828 CZAJA, J. J. CICEOU, G. Man's future role as an aircraft navigator Guenter Cichon conducts a test with Diamant 18 A71-20343 A71-20686 CIKAUEK, A. A., JR. Optical probinq of supersonic aerodynamic D turbulence with statistical correlation. Phase 1 DAIIODAEAII, K. A. - Feasibility Hvpersonic airbreathinq enqines for launching INASA-TN-D-60771 N71-17444 space vehicles CIVIUSKAS. I. C. A71-21301 Parametric enqine study for a Uach 0.98 commercial DANILEIKO, G. I. air transport Fundamentals of aircraft enqine desiqn INASA-TH-X;529611 N71-18733 871-20674 CLARE, T. A. DAEEAS. 8. On resonance instability for finned confiqurations ADolication of liftina surface theorv to winqs havinq non-linear aerodynamic properties with control surfaces r AD-7 15110 1 471-17733 TONERA-TP-889 1 N71-18473 CLARK, E. K. DAT. E. Thermal pump-compressor for space use Patent Uinq liftiuq line representation - Application to INASA-CASE-XLR-00377 1 N71-17610 the two winqs in tandem interaction CLIFF, E. n. [ONERA-TP-8911 N71-18439 On barriers in a problem of collision avoidance Application of liftinq surface theory to winqs A71-21322 with control surfaces COLAUGELO, D. IONERA-TP-8891 N71-18473 Special purpose telemeter for a jet enqine DAXIAU. B., JB. environment Comparisons between stinq-supported and free- 1171-19628 fliqht tests in the JPL Hypersonic wind Tunnel on a modified Saturn-Apollo launch confiquration

B-4 PEESOIAL AUTHOR IRDBX ERMSEAUS. 8.

laIAA PAPER 71-2653 171-21 99 1 DU UALDT. P. A. DEAL. P. 1. The feasibility and use of anti-torque surfaces Simulator study of flight characteristics of a immersed in helicopter rotor downwash Technical iet-flap STOL transport airplane durinq approach report, Jan. 1968 - Dec. 1969 and landinq TAD-7154381 1171-18937 TNASA-TN-D-62253 871-17433 DUIEAE. J. DEL BALZO. J. E. Beat transfer calculations for turbine blade Inertial systems and area navigation in the U.S. desiqn domestic airspace N71-17374 A71-20347 DURVASULA. S. DELLIIGEB. T. C. Platter of siaply supported skew panels with Computation of nonequilibrium merged staqnation aid-plane forces in supersonic flow shock layers by successive accelerated 171-21302 replacement DIIBR. E. A. rAIAA PAPER 69-6551 1171-19890 Boundary layer on a hypersonic sharp cone at small DERK. V. anqle of attack Investigations of hypersonic characteristics of 171-19892 two phase flows and their possible use for Rapid calculation of inviscid and viscous flow aerodynamic measurements over arbitrary shaped bodies BBVTDG-PBWT-70- 1 J N71-18441 1171-20313 DEIIIS,. A. S. DXEOBDZEIO. I. '1. Condztions inside cumulus clouds preceding the Arranqement of manometric equipment on an oriented onset of precipitation satellite A71-21450 A71-21022 DEIII, D. C. The frequency-separated display principle. phase 2 Annual summary report, 1 Am. 1969 - 31 Oct. E 1970 EASTOI, J. T AD-7154581 N71-18739 Transportation of freiqht in the year 2000 with DESIAS, 6. particular reference to Great Lakes area The frequency of scheduled services - An analysis N71-19320 of air transport supply BCKEET, B. E. 6. T REPT-1970/1-E] 1171-18112 Film cooling with injection throuqh holes DBSTUIIIDER. E. T NASA-CE-116376] 871-17388 Measurement of interfering unsteady forces between EDWARDS. J. P. lifting surfaces in tandem Heat transfer calculations for turbine blade TIIASA-TT-P-13482 J N71-18397 desiqn 871-17374 Measurement of unsteady air loads of interacting ELLI1100D. J. il. lifting surfaces in tandem Near-continuum arisyametric hypersonic flow past f ONERA-TP-890 1 N71-18449 very slender bodies, October 1969 - July 1970 DBTABAIDO. A. E. [ AD-715901 1 N71-18556 Fiber optic faceplates for contrast enhancement BEERY. J. C. under high ambient light conditions for cockpit Longitudinal aerodynamic characteristics of the displays Viking lander capsule at Each 6 A71-19175 T EA S A-T E-X- 220 5 1 N71-17253 DTILCW?RKO. T. A. BIIUEDS. E. Certain new approximations of the Chaplygin Effect of the position of maxima thickness and of function in the snbsonic ranqe of qas flow the lenqth of bodies of revolution on A71-20083 aerodynamic coefficients in supersonic flow DICK. K. A. I DLR-PB-70-54 J N71-18444 A report on some results from the NASIL 1968 BIEVOLDSOI. B. K. Airborne Auroral Expedition Pliqht evaluation of anqle of attack as a control [ AASA-CR-1168551 N71-18996 parameter in general-aviation aircraft DICKIIISOI. S. 0. [ NASA-TN-E-62101 E71-18442 Aerodynamic characteristics of a large-scale E16BLS6JEED. I. K. V/STOL transport model with tandem lift fans Aerospace systems pyrotechnic shock data /ground mounted at mid-semispan of the wing test and flight/. Volume 7 - Investigation of T NASA-TN-D-6234 1 1171-18558 mass loading effects Final report. 12 nay - 12 DIBSIIGEB. 5. E. NOV. 1970 A numerical method of determininq the aerodynamic [ NASA-CR-116019 J R71- 19250 coefficients of thin supersonic wings which are BIGLII. 8. A. dependent on the angle of attack Variation of the high-temperatnre properties of [ NASA-TT-P-l3521] 171-18987 jet fuels durinq prolonged storage DILLBISCEEEIDER, P. 6. 1171-19492 Use of ground based simulators in aircraft desiqn BISELIE, I. A71-20309 Computation of the aerodynamic interactions DOEE, 6. between aircraft lifting elements in supersonic A project information and simulation system for steady or unsteady flow aerospace manaqement [ ONERA-TP-850) 171-18462 TAIAA PAPER 71-2381 A71-19714 EITIIBR. E. S. WSS. E. D. Operatinq system reliability for the Navy advanced Rapid calculation of inviscid and viscous flow avionic digital computer over arbitrary shaped bodies A71-18833 A7 1- 20 3 13 ERICKSOI, J. C., JR. DOUSLAS, B. C. The feasibility and use of anti-torque surfaces Economic impact of the Dallas-Port Worth Regional immersed in helicopter rotor downwash Technical Airport on the north central Teras reqion in report, Jan. 1968 - Dec. 1969 1975 f AD-715438) N71-18937 N71-18099 ERICSSOI. 1. E. DOWDY. il. 1. Effects of nose bluntness, anqle of attack, and Airborne measurement, key to environmental oscillation amplitude on hypersonic unsteady manaqement aerodynamics of slender cones A71-19080 [ AIAA PAPER 70-2161 1171-19895 DRA6AIOT. 8. KE. Dynamic support interference - Pact or fiction Influence of air temperature on the intake process [ AIAA PAPER 71-277 J A71-22002 of internal combustion engines EBBSEAUS. P. 171-20782 Peculiarities of turbulent wakes 871-18472

B-5 EROSEIN, V. A. PERSONAL AUTEOR XNDEI

EROSEIN, V. A. POKXE, V. 0. Ricochetinq of a plate from the surface of an synthesis of a multicomponent mechanism with ideal incompressible fluid transmission anqles diverginq minimally from A71-19355 ninety degrees ERZBERGER, E. A71-19361 Optimum horizontal quidance techniques for FOIIIN, V. 1. aircraft Certain new approximations of the Chaplyqin A71-20306 function in the subsonic range of gas flow Noise neasurement evaluation of takeoff and A71-20083 approach profiles optimized for noise abatement Iultilink approximation of the Chaplygin function r NA S A-T N-D-6 246 1 N71-18929 in snbsonic and supersonic flow regions EUVRARD, D. A71-20090 Contribntion to the study of sonic flows past an FOIIIE, T. 1. obstacle Study of inviscid flows of a radiating gas with NASA-TT-F- 13472 J N7 1- 18401 the aid of differential approximations EVSTIGEEBV, I. I. A71-19183 Autonation of technoloqical processes in POllIIA. A. II. aircraft-enqine construction Variation of the high-temperature properties of [AD-7148581 N71-17832 jet fuels durinq prolonged storage A71-19492 I POI, J. F Anemometer measurements of velocity and density in PASTIE, W. G. projectile rakes A report on some results from the NASA 1968 IAIAA PAPER 68-7011 A71-19891 Airborne Auroral Expedition FUAY, J. [NASA-CR-1168551 N71-18996 Carbon-fibre aircraft structures - Some cost PAUUER, 6. aspects The employment of plastics and metals in [PLASTICS INST. PAPER 461 A71-20929 aeronautical desiqn comparatively considered FEENCB. K. E. using some practical examples A new correlation of parachute weight data A71-20044 A71-18900 PEWRCEEEKO, G. P. FRIES. J. B. Probabilistic estimate of the aerodynamic Improvement of automatic landinq through the use imbalance of aircraft qas-turbine rotors of a space diversity ILSreceiving system A7 1- 2204 5 A71-18830 PEILEE. C. E. FULIER. 1. C. Acoustic and aerodynamic performance of a The coainq of age of the associative processor 6-foot-diameter fan for turbofan enqines. 3 - A71-19997 Performance with noise suppressors FUEK. 9. E.. JR. [NASA-TN-D-61781 N71-17254 Optical probiuq of supersonic aerodynamic PELDIIAE. 9. turbulence with statistical correlation. Phase 1 Investiqations of hypersonic characteristics of - Feasibility two phase flows and their possible use for [ NASA-TN-D-60773 N71-17444 aerodynamic measurements r8flVTDG-P8UT-70-1] 171-18441 PELDUN, E. 1. G Fundamentals of aircraft enqine desiqn GACB, 1. A71-20674 Appraisal of connunity response to aircraft noise PELDIIAN, 1. 1. - At the qrass roots level Service life of bearinq elements of aircraft qear A71-21819 pumps GAIDSICK;. E. 6. A71-20793 Plight evaluation of anqle of attack as a control PESTINGER, J.-C. parameter in qeueral-aviation aircraft Delta winq study in a low density hypersonic flow [ NASA-TN-D-62 10 1 N71-18442 [ REPT-70-91 N71-18423 GALIICEE. P. PIGGE, I. E.. SR. Thermo-chemical protection of refractory Tetra-Core - A three-dimensional space structure superalloys for aircraft gas turbines A71-21225 871-17391 PILATOV, E. I. GARCIA. J. E. Shape of the leadinq edge of a minimun-draq Transonic airfoil desiqn slender win4 for hypersonic velocities 1171-20304 A71-22039 GABDEER. W. K. PILIPPOT. 6. A. An extension of nonsynchronous interrogation Some results of investiqations of centripetal and repetition frequency selection methods radial-flow stages [AD-7153351 N71-17766 A71-22049 GARIBR, E. C. PIEGER. P. G. Numerical appraisal of lulthopp's low-frequency Developments in stratospheric and mesospheric subsonic lifting-surface theory analyses which dictate the need for additional [ ARC-R/1-3634 1 171-18425 upper air data GASAWAI. D. C. 1171-21724 Noise associated with operation of the C-91 FISBBBTN. B. D. /aeromedical evacuation/ aircraft Determination of the effect of atmospheric [ AD-7152221 1171-18269 humidity on the characteristics of a turbofan 6ASTEB. I. enqine Some observations on vortex sheddinq and acoustic [AD-7152323 1171-17728 resonances IISEER. F. A. [NPL-AERO-1311] 1171- 17089 Voltages produced by transient currents flowinq GATES, D. F. upon shields of cables The use of a laser Doppler velocimeter in A71-19946 supersonic flow lLCTCEBR. U. D. [AIAA PAPER 71-2871 A71-22010 The need, meaninq and usefulness of meteoroloqical 611, S. W. observations for aviation Plight evaluation of angle of attack as a control 171-21732 parameter in general-aviation aircraft FOLRSCEIEG, E. l NASA-TN-D-62101 171-18442 Aeroelastic and related problems for aircraft and GEISSLER, 1. spacecraft Calculation of the potential flow around 1171-20063 rotationally symmetrical rinq profiles 1171-18469

9-6 PEESOIU AWEOE IIDSI

GKSOT. J. GEAI. 1. Cooling of turbine blades by liquid metals Practical engineering aethods for predicting hot 171-17398 gas reingestion characteristics of V/STOL GSOEGK-FALVX. D. aircraft jet lift engines Scale effect studies of airfoil profile drag at [nASA-CR-l11845] 171- 18714 high subsonic speed G8ltKm. J. E. [AIAA PAPER 71-2893 A71-22012 Experience gained from reliability trails on an GBPfEIKOV, 1. airborne radar new on-board instrnments A71-19557 171-16993 SRETSOV. V. I. GILBERT. W. E. Investigation of three-diaensional separation flor Plight measurement of aerodynamic coefficients on around half-cones mounted on a flat plate a bomb A71-19743 A71-19872 GPIAZIOT. A. P. GILOOTE. E. E. Variation of the high-temperature properties of To the moon and beyond let fuels during prolonqed storage A7 1- 19117 A71-19492 GLEIXEE, A. I. GRIESSEE. E. Probabilistic estimate of the aerodynamic Investigations of hypersonic characteristics of imbalance of aircraft gas-turbine rotors tro phase flows and their possible use for A71-22045 aerodynamic measureaents GLEIlX. D. 1. [ BIVTDG-PBUT-70- 1 3 8-11-18441 Inqestion of debris into intakes by vortex action GBIFFITE. E. D. [ ARC-'2-1 114 I 171-17084 Q-star experimental quiet aircraft GLOUACKI. U. J. A7 1-2 1441 The MOL Bypervelocity Wind Tunnel GUILLOIS, A. [AIAA PAPER 71-2531 A71-21982 Computation of the aerodynamic interactions GOSCKB. S. A. betreen aircraft liftinq elements in supersonic Base pressure measurements on the IB-70 airplane steady or unsteady flor at Bach nnmbers from 0.4 to 3.0 [ OBERA-TP-850 I n7i-18462 [ IASA-TI-I- 1612 3 871-17132 SUPTA, T. E. 6011. I. 1. Response of skin friction to the angle parameter The history. evolution, and use of rind tnnnels in flor past an axisymmetric bodv moving in the 171-21666 direction of its axis 60LDBEEG. T. J. A71-20098 Longitudinal aerodynamic characteristics of the GUREEV, A. A. Viking lander capsule at Mach 6 Variation of the high-temperature properties of [ EASA-TI-1-2205] 171-17253 jet fuels during prolonged storaqe GOLDBAI. A. A71-19492 Rapid calculation of inviscid and viscoas flor over arbitrary shaped bodies A71-20313 H GOLUBIISKII. A. I. EACE. J. P. Sinqular current surfaces in conical gas flows Pioblems of air navigation A71-21864 A71-19014 GOEBLOV, 6. II. EACKEIBBEGBB, 6. I.. JE. Plor for a sudden ridening of the channel Liqhtning protection for non-metallic rotor blades All-LLOYI All-19939 GOREAH, E. 1. BACKETT, J. E. Airborne measurement. key to environmental The aerodynamics of a fixed ground plane for a management powered SmL wind-tunnel model A7 1- 19080 [AIAA PAPER 71-2661 A71-21992 GOEOSECEEIKO. I. B. EACOEEI, A. Analytical Bethods of determininq the Pliqbt test of the @ARAVA* Israel STOL airplane characteristics of certain spatial maneuvers of 171-19082 an aircraft EAIBACE, E. A71-22050 Strength of light metal alloy rods with irregular GOSSETT, T. D. notches under cyclic tensile loads and A quadratic performance index for a VTOL aircraft periodically interspersed compression loads prefilter model reference attitnde control [ PB-78-19691 871-17524 system EALL, 6. U. [ HASA-TU-D-6231 1 171-18836 An in-Pliqht iuvestiqation of lateral- directional GOSTELOW, J. P. dynamics for the landinq approach Final Design and performance evalnation of four technical report transonic compressor rotors l AD-7153171 171-17792 A71-20200 EALL. J. E. GOUGAT. P. Snper VC 10 cruise draq - A rind tunnel External sound field effect on a turbulent layer investigation. Part 1 - Experimental techniques [REPT-70-81 171-18572 [ ARC-CP-11251 n7i-17118 GOULD. E. U. F. BALL. 1. P. Wake blockage corrections in a closed wind tunnel Aerodynamic characteristics of a larqe-scale for one or two wall-aounted models subject to V/STOL transport model with tandem lift fans separated flor mounted at mid-semispan of the wiuq [ ARC-R/I-3649 1 1171-18456 [ WASA-Til-D-6234J 1171-18558 GBAPTOI. S. B. EALLER. E. C. Plight investigation of a V/STOL transport model Compater program for preliminary desiqn and with fonr pod-mounted lift fans analysis of V/STOL tip-turbine fans [ IiASA-TA-D-6129J 871-17023 rlASA-TB-D-61611 871-17641 GEAITEAI, U. D. EALLS; G. A. Simnlator study of flight characteristics of a nozzle guide vane coolinq - The state of the art let-flap STOL transport airplane during approach 871-17396 and landing EALUES. D. B. r BASA-TU-D-6225 J n7i-1-1433 Pliqht operations to ainimize noise GOAITEAI, U. J. 1171-21049 On barriers in a problem of collision avoidance EABLET, I. 1. A71-21322 university of Virqinia superconductinq wind- GEAX, K. P. tunnel balance An overrier of the national Airspace System A71-20151 [AIAA PAPER 71-2441 A71-19719 EAIIIBR, J. 1. PEBSOUAL AOTEOE IUDEI

EAIIER, J. 1. EEXUOOD. J. E. Eelicopter application studies of the variable Smoke emission from jet engines deflection thruster jet flap Final report A71-20867 r AD-7150711 171-17907 EICKS, E. 1. EA1IlOlD. D. 6. Further studies of the extrapolation of near field An evaluation of single and multiple stinq support overpressure data methods to obtain unmodified interference-free [ UASA-TM-X-2219 J U71-18559 wind tunnel data BILL. P. E. [AIAA PAPER 71-2671 A71-21993 Beat protection apparatus Patent EAU. K. U. [ NASA-CASE-XLA-00892 J N71-17897 Analvsis~. of nonlinear control SYSteOS with EILSEUEOD. A. transport laq Meteoroloqical effects on air transportation A71-20369 N71-18117 EAUCOCK. G. J. EIUXPETEB, E. P. E. Delta winqs with longitudinal camber at low speed Problems and status of worldwide development of [ ARC-CP-I 1291 N71-17112 upper air soundinq systems A71-21739 EAUJALIC, K. Fully-developed flow in rectanqular ducts of EIISOU, U. C. non-uniform surface texture. I - An Orientation-error accidents in regular Army EU-1 experimental investiqation aircraft durinq fiscal year 1967 - Relative A71- 18772 incidence and cost EAUKE. C. R. [ AD-7151071 N71-17854 The simulation of a larqe let transport aircraft. EODDER. E. K. Volume 1 - Mathematical model Aerodynamic characteristics of a large-SCale r NASA-CR-17561 N71-19239 V/STOL transport model with tandem lift fans EARDIU. J. C. mounted at mid-semispan of the ring Statistics of the sound field of a source above a NASA-TN-D-62341 N71-18558 rouqh, imperfectly reflectinq surface EOPPIAU, C. S. 1171-21162 Man's future role as an aircraft navigator EABDEATE, E. P. A71-20343 Fatique and fracture mechanics EOGE. P. E. rAIAA PAPER 70-5121 A71-22025 Inteqrated electro-optical systems for earth- EAERIS. E. 1. oriented, environmental, and domestic The NOL Avperveloclty Hind Tunnel applications [AIAA PAPER 71-2531 A71-21982 A7 1- 18827 EAOBEUEOPER. 1. BOLE, G. The art of centerinq Airport access to Eeathron Airport, LondonN71-18954 A71-20685 mechanics of curvilinear fliqht for qlider pilots EOLLAUD. 1. J. A71-21770 olympus 593 turbine cooling N71-17376 EAXASEI, S. Performances of cascade of blades with small EOLLEUBAOGA, R. C. aspect ratio. I - Performances at the center of Traffic control system and method Patent blade span r NASA-CASE-GSC-10087-11 N71-19287 A71-20624 EOLIES. J. E. EIYUARD. E. 1. Hind-tunnel free-fliqht testinq of configurations Super VC 10 cruise draq - A wind tunnel with hiqh-fineness ratio bodies investiqation. Part 1 - Experimental techniques rAIAA PAPER 71-2781 A71-22003 [ARC-CP-1125 J N71-17118 EORAUOPP, E. V. HEAD, 1. 8. Three-deqree-of-freedom qas bearinq for wind- Improved entrainment method for calculatinq tunnel dynamic measurements A71-22004 turbulent boundary layer development [AIAA PAPER 71-2793 ARC-R/H-3643 1 N71-18424 BORN. R. A., JR. Calculation of the turbulent boundary layer in a Sinqle staqe experimental evaluation of boundary vortex diffuser layer blowinq and bleed techniques for hiqh lift r ARC-R/H-3646 1 N71-18468 stator blades, 5 Final report HEASLIP, T. U. r NASA-CR-54573 I N71-18749 Technical failures in civil aircraft accidents in EOEOIITZ. D. 1. Canada Man-machine considerations in system desiqn for A71-21679 all-weather, low-level naviqation AEDBICK, J. K. 871-20344 Minimum time turns for a supersonic airplane at EOOLIEAH. T. 1. constant altitude A theoretical and experimental investiqation Of A71-22032 the stability of pipe flow with respect to EEPER, G. three-dinensional disturbances Hypersonic low density wind tunnel plant N71- 18989 r BaBH-Pa-H-70-511 N71-18593 EOUARD. P. 1. EEIDELBERG, 1. J. Applications of zinc-silver oxide batteries Overall performance in arqon of a 3.7-inch A71-21102 sir-staqe axial-flow compressor EOUELL. 8. E. [NASA-TH-X-21941 N71-17882 Methane-air combustion qases as an aerodynamic REIDIANU, 1. P. test medium Amplification by wave distortion in unstable rAIAA PAPER 71-2581 A71-21986 combustors EOBBB, 8. P. A71-19906 Liqhtninq test facilities measurement techniques EEPUOBTA. 1. G: A71-19931 Experimental investiqation of the effect of EODDLESTOU, E. P. trailinq-edqe sweepback on the subsonic An evaluation of the usefulness of four secondary lonqitudinal chaiacteristics of slender winqs tasks in ;ssessinq the effect of a laq in ARC-CP-1130 1 N71- 171 17 simulated aircraft dynamics EERSAKOUITZ, R. 1. r IAH-R-4791 N71-18838

communications. uaviqatj In and surveillance for ELIGEES, u. P. ~ aircraft and marine vessels operatinq in the plasma-arc weldinq of let enqine components North Atlantic reqion A71-21684 A71-18808 EUUT. 1. R. EEUES. E. V. nethane-air combustion qases as an aerodynamic ALPA - II survey of airport fire and rescue test medium facilities [AIAA PAPER 71-2581 A71-21986 N71- 18101 PBBSOPAL AUTEOR IIDBX KELLEY. J. E.

EWlT. E. D. Effect of exit area variation on the performance The development of a collision avoidance system of an auxiliary inlet ejector nozzle at Each A71-19079 numbers from 0 to 1.27 EIIBDLE. P. [NASA-Tn-X-2182 J N71-18863 Jet aircraft noise over residential areas JOEISOI. P. E. 171-21163 Perspective of SST aircraft noise problem. I1 - RUBLEY. C. J. Thrust losses and installation factors Development and calibration of a nach 1.2 rain 171-20302 erosion test apparatus Technical report, nar. JOElS01. S. 1. 1966 - Auq. 1969 The frequency-separated display principle. phase 2 r AD-7159091 871-18651 Annual summary report, 1 APT. 1969 - 31 Oct. EUSSEIl. 1. P. 1970 Beasurements of particulated gas flor pressure on [ AD-7 15458J U71-18739 cascade nozzles JOEUSTOI. E. 8.. JB. rAIAA PAPER 70-7123 171-20311 Effects of rotary inertia on the supersonic BILL. E. flutter of sandwich panels Liqhter-than-air in Canada A71-19887 A71-19916 JOEISTOU. J. A. A new approach to helicopter E-V testing with preliminary results from the 08-582. Kiora and I AH-lG Euey Cobra helicopters IAKOVLEISKII, 0. I. 1171-19093 Experimental study of flow in the rake behind thin JOIBS, K. m. plates Boundary-layer discontinuity on a helicopter rotor A71-19750 blade in hoverinq IASIISKII. P. 6. [AIAA PAPER 69-1971 171-20307 Determination of the optimal parameters of aqents JOBGElSEI. 1. E. for protectinq the compartments of a fliqht Preliminary study of advanced hypersonic research vehicle from aerodynamic heatinq during long aircraft flights at high fliqht speeds [ NASA-T8-I-2222 J N71-18367 171-20836 JUEASZ. A. J. IASKBIICE, E. P. Experimental performance and conbustion stability Arrangement of manometric equipment on an oriented of a full scale duct bnrner for a supersonic satellite tnrbofan engine A71-21022 NASA-TR-D-61631 171-18882 IATSEIKO. I. K. JUSTICE. J. 1. Restoration of the working blades of compressors The aerodynamics of a fixed ground plane for a by vibrational tumblins powered STOL rind-tunnel model A71-20843 [AIAA PAPER 71-2661 1171-21992 ICElOGLE. il. Providinq ground access to the Kansas City Airport 1171-18955 K ILIITSKII. I.. IA. K~LIVEETElOS. C, L. Analysis of aircraft radio-compass error A wind tonne1 simulation of rocket and launcher A71-20787 interference effects IlGBBO. E. D. [AIAA PAPER 71-2693 171-21995 Combustion stability limits for swirl jet KAUBKO, V. P. combustor modules combining air swirl and Arranqenent of manometric equipment on an oriented impinqinq -jet atomization of ASTB A-1 fuel satellite I UASA-TI-X-2218 J 871-18560 A71-21022 IPATOI. A. K. KAPP. II. E. Study of a 2500-EP turboprop engine as a plant for Liqhtning and surge protective devices for controlling the gas temperature in front of the survivability of electrical systems turbine All-19941 A71-20831 KAPPL. J. J. An experimental arrangement for studying the delay nonlinear estimation via Kalman filtering time in the components of the propeller rpm A71-18835 controller system of a turboprop enqine SAPUSTIl. 1. I. A71-20832 Fundamentals of aircraft enqine design ISADA. 1. I. 171-20674 Damaqe to structures due to floor shocks KABEUAA, A. A71-20747 llirplane high-lift system design by interactive ISEIGURO. K. graphics system The latest airport lighting facilities r AIAA PAPER 71-227 J 171-19705 A71-20355 KARIUOOI. A- KE. ISODA. E. Determination of the aerodynamic characteristics A study of some factors influencing the ignition of an elastic srept winq in subsonic flow of a liquid fuel pool 171-22035 A71- 19245 KAPIZHBISKII. E. IA. IUHIKOT. T. P. Scanning systems for thermal viewers Equivalent tests of aircraft engines N71-19220 A71-21115 KAOPUAl. A. Investigation of flou characteristics of some wire-form and laminate-form porous materials J [ NASA-TII-X-2111 J 171-17130 JACOB. C. KAWIBCKI. C. 3. Thin airfoil theory Lightninq test facilities measurement techniques [ NASA-TT-P-134711 871-17468 A71-19931 JBAI. 1. C. Lightninq and surge protective devices for On the transverse and torsional vibrations of a survivability of electrical systems fuselage-rinq combination rith ring-tip fuel 1171-19941 tanks KELLBI. E. J. A71-20364 Reduced-order modeling in aircraft mission JOEIS. A. 1. analysis Performance of an auxiliary inlet eiector nozzle A71-19913 rith floatinq inlet doors and floating KELLEI. J. E. sinql e- hinge t r ailin q- ed ge flaps plasma-arc welding of jet engine components [ lASA-Ta-X-2173] 171-17554 A71-21684

B-9 REMIPER, R. R. PERSOUAL AUTEOR IUDEI

KEUPER. R. E. KOEELER, R. I The development of the Yankee Determination of the coefficients in multivariable A71-19084 systems of fliqht dynamics by a model with KBUUETT, R. J. automatic parameter adiustment usinu an analoa

Inteqrated drive qenerators for aircraft computer ~ A71-19494 rDLR-P8-70-30] N71 - 18586 RESTER, J. D. KOERTE. 1. Aircraft noise, its source and reduction VFR-at bad weather - Hhat is to be taken into A71-21814 consideration. I1 - Radio naviqation and KEOLIAVKO, V. I- radio-telephone communication Liftinq properties of some confiqurations A71-20683 accordinq to the slender body theory VFR at bad weather - Fliqhts over closed cloud 1171-20776 cover, radar support from the qround. I11 Eddy flow of an ideal incompressible fluid past a A71-21767 flat partition KOPSKXY, 1. G. 1171-20828 Effects of specific speed on the experimental KILGORE, 8. A. perfogmance of a radial-inflow turbine Aerodynamic dampinq and oscillatory stability in r NASA-TN-D-6 182 1 N71-17354 pitch and yaw of a variable-sweep supersonic KOGAU, 1. u. transport confiquration at nach numbers from Use of unsteady analoqy in constructinq hypersonic 0.40 to 1.80 flows past blunt bodies 7 I NASA-TR-X-21641 N7 1-1741 5 A71-21863 some transonic and supersonic dynamic stability KOE, J. C. I. characteristics of a variable-sweep-winq A new wind tunnel technique for providing tactical fiqhter model simulation of fliqht base flow NASA-TH-X-2163 1 N71-17425 rAIAA PAPER 71-2683 A71 -2 1994 KILGORE. R. S. KOELBAU, D. 1. University of Virqinia superconductinq wind- Vortex breakdown on slender sharp-edqed winqs tunnel balance rAIAI PAPER 69-7781 A71-22028 A71-20 151 KOUEV. V. A. KIPKE, K. A gasdynamic stand for testing materials and Experimental investiqations of caret winqs in structural elements for their resistance to hypersonic flow cyclic thermal loadinq 171-200 15 1171-20839 KIPP, R. A. KOPPEUULLLUEE, G. Comprehensive planninq and aircraft noise at Hypersonic low density wind tunnel plant Kansas City International Airport [ BnBY-FB-H-70-51 1 N71-18593 A71-21837 KORBIEVSKII. E. IL. KIREEV, V. I. Restoration of the workinq blades of compressors Transonic qas flow in arisrma+=tric Lava1 nozzles by vibrational tumblinq with steep walls A71-20843 171-1 9732 KOSTERIII, A. V. KIBKPLTRICK. D. 1. I. Solution of certain let problems by the couplinq Experimental investiqation of the effect of method trailinq-edqe sreepback on the subsonic A71-20084 longitudinal characteristics of slender winqs Sonic flow past a wedge according to Kirchhoff's r ARC-CP-1130 1 N71-17117 scheme KISEI, P. A. A71-20085 Approach quidance to circular fliqht paths KOSTERIII, V. A. IAIAA PAPER 69-9863 A71-20305 The effect of the injection anqle on gas dynamics KISBIIIOTO, 8. of fan lets in the deflected flow The latest airport liqhtinq facilities [ AD-7147901 N71-18034 A71-20355 KOTLIAB. 1. 8. KISIELOUSKI. E. notion of a cavitating foil with a jet flap under Practical enqineerinq methods for predictinq hot the free surface of a fluid qas reinqestion characteristics of V/STOL A71-20086 aircraft jet lift enqines Flow of a heavy fluid past a plate with partial r NASA-CR-1118451 1171- 187 14 cavitation KITTEEDGE, 6. D. A71-20087 Role of NAPCA in controllinq aircraft pollutant KOVALEV. A. 1. emissions Equivalent tests of aircraft enqines A71-21831 A71-21115 KLASS, 1. S. KOVALEV. 1. P. Ball foraing solves contourinq problems supports and suspensions of gyroscopic devices A71-21681 A71-20299 KLICH, G. P. KOVTIIUEIKO, V. 8. An analytic study of radiatively cooled delta-winq Arranqement of manometric equipment on an oriented structures for hypersonic aircraft satellite r NASA-TN-D-61381 N71-18025 A71-21022 KLINE, J. P. KOPLOVL. I. G. Two-dimensional cascade test of a let-flap turbine stronq viscous interaction on a delta wing and on rotor blade an oblique airfoil INASA-TH-X-21831 N71-17589 L71-19739 KIIGET, D. D. KRAFT, G. A. Electron thermochemical nonequilibrium effects in Parametric enqine study for a nach 0.98 commercial re-entry boundary layers air transport rAIAA PAPER 69-62] A71-19879 r NASA-Tn-X-529611 1171-18733 KUIGIII, 1. 1. KBAGE~. P. E. Evaluation of the precision of executinq the The need. meaninq and usefulness of meteorological outside contours of units with allowance for the observations for aviation elastic characteristics of the elements A71-21732 assembled and equipment KBAIKO. A. I. A71-20792 Desiqninq a supersonic nozzle contour with KOEYLIAUSKII, A. A. allowance for chanqes in the flight conditions Determination of the optimal parameters of aqents of a flight vehicle for protectinq the compartments of a fliqht A71-21865 vehicle from aerodynamic heatinq durinq lonq KBAUSB. 1. R. fliqhts at hiqh fliqht speeds Automatic processing of multispectral observations A71-20836 [AIAA PAPER 71-2341 A71-19711

E-10 PEPs01.l Aoz1IOE IPDBI LEPIS. c. E.

TpISHlASWAIIT. 2. 1. 171-2 1e35 Design features and characteristics of the 9 x 6 LAIIBlDOLA. J. ft wind tunnel at E.A.L.. Bangalore A study of some factors inflaencing the ignition A7 1-21 305 of a liquid fuel pool KUCHIISKAIA. 2. P. A71-19245 Selection of the design point on the LAlDER, E. P., JP. characteristic curve of the fan of a tarbofan A kinetic study of the catalytic dehydrogenation engine with a large bypass ratio of aetbylqclohexaue at 600. 650, and 700 F and A71-2 204 2 a pressure of 5 atmospheres KUDSIASHOV. I). IA. [ AD-7159261 111-18729 A gasdynamic stand for testinq materials and 1111. S. 8. stractural elements for their resistance to Jet aircraft noise over residential areas cyclic thermal loading A71-21163 A71-20839 LAIGIOPD, T. U.. JP. KUBCCwMWl. 0. Economic impact of the Dallas-Fort worth Regional A survey of some European hypersonic research Airport on the north central Texas region in 171-18452 1975 KUEHL. W. 171-18099 Experimental investigation on a sinqle-stage LAlO, E. 1. air-cooled gas turbine Air traffic control - A feasibility stady 171-17387 171-18105 KUKUSHKI1. A. A. LAlZKP01. P. W. Variation of the bigh-temperature properties of Displays in the lrational Airspace System jet fuels during prolonged storage [AIAA PAPER 71-2471 A71-19721 A71-19492 LAPSHOT. V. 1. KUIIAP. P. E, A gasdynamic stand for testing materials and Some notes on helicopter stability ander structural elements for their resistance to constraint cyclic thermal loading A71-19421 A71-20839 KU16, ?. LA8611, J. 8. Diffraction of a pulse by a three-dimensional U.K. research in sonic boom corner 1171-21812 [ tIASA-CR-172BJ 171-18029 LUSOl. f. J. XU#;. J. T. Verification of takeoff performance predictions Lightning current transfer characteristics of the for the XB-70 airplane p-static discharger installations [ NASA-TI-X-22151 171-18509 A71-19935 LAU6HLIP. C. 9. KUO. C. J. Traffic control system and method Patent Liqhtning protective coatinqs for boron and [ ASA AT CASE-GSC-10087-1 ] 171-19287 graphite fiber reinforced plastics LAOIDEB. B. E. A71-19944 Pally-developed flow in rectanqnlar ducts of KUZllAK. 6. 1. non-uniform surface texture. I - An Analytical solations for the case of flying experimental investigation vehicle motion at low angles of attack, Chapter A71-18772 8. 33 - Three dimensional motion LAXAREV. T. A. W71-16901 nutior, of a cavitatinq foil uith a jet flap under Analytical solutions for the case of flyinq the free surface of a fluid vehicle motion at low angles of attack, Chapter A71-20086 8. 32 - Plane motion, determination of the time LE 6RIVBS. B. of transition of rotational into vibrational cooling of turbine blades by liquid wtals motion 171-17398 171-16983 LEBEDBV. 1. 1. KOZlETSOV. A. V. Construction of a body of revolution in a An unsteady problem of flow past a solid foil supersonic gas flow from a given chord diagram A71-20088 A71-20089 LEDOKBOVICE. A. A. Instruments for studying foqs and clouds and L measuring humidity LABBPOE. J. 6. A71-20298 On dynamic stability testinq of anconventional LEX, c. I. con fignrations On the transverse and torsional vibrations of a [AIAA PWER 71-2761 A71-22001 faselage-winq combination with wing-tip fuel LABITLKE. K. tanks Developments in stratospheric and mesospheric A71-20364 analyses which dictate the need for additional LEE, E. Q. umer._ air data optimum horizontal gaidance techniqaes for A71-21724 aircraft LABBIICQUE. 8. J. A71-20306 A sammary of availability and accnrac7 of landing A technique for evalnatinq parameter variations aids for shuttle applications for automatically controlled aircraft uith an r 1ASA-Tl-X-66720 1 N71-18187 application to the landing approach LADTZHElSKII, 1. D. [NASA-TN-D-62301 171-18761 On the question of the valae of entropy on the LB66E. H. surface of a body of revolution at a nonzero Bypersonic low density wind tonne1 plant angle of attack r BIBW-PB- u-70- 5 1 ] 871-18593 171-16903 LESTER. W. G. 5. Viscous hrpersonic flow around a nonaxisymmetric Temperature and flaid property effects on slender body cavitation in aircraft fael pumps 171-1 695 1 ARC-CP-1128 ] N71-17044 LALIT, V. B. LEVIlB. 8. 5. Constant-level balloons for soanding Systems Finite element analysis of structures in the A7 1- 2 174 2 plastic range LAIIAP. J. E. [ UASA-CR-16491 1171-19276 Vortex-lattice FORTRAl proqram for estimating LEVY. 1. 1.. JP. sabsonic aerodynamic characteristics of complex Preliminary study of advanced hypersonic research planforms aircraft [ BASA-TI-D-6142 J 171-17424 [ RASA-Tl-X-22221 171-18367 LAIIBEUTOI. 8. C., JP. LBWIS. c. E. Environmental aspects of airport systems planning Uumerical methods for nonreacting and chemically IOERLBEBGER, B. PEBSOUAL AOTROB IHDEX

IOEELEERGER, R. UOSEK, S. II. Airport access plans for Boston Tuo-dimensional cascade test of a jet-flap turbine 171-18957 rotor blade IOLLAUET, G. J. [ NASA-TM-X-2183 1 1171-17589 A study of foq clearinq usinq a CO2 laser UOSBAOII. W. J. [AIAA PAPER 69-6701 A71-20308 Effects of specific speed on the experimental IOLLEII. C. performance of a radial-inflow turbine Interurban air transportation System - A qraduate r NASA-TN-D-6182l Y71-17354 project in complex Systems desiqn. presented by UOZEI1, I. T. the students of AE-EE-ME 655-656 /Hinter-Spring Inverse boundary value problems and their quarters, 1969/ applications in hydroaeromechanics [NASA-CR-116431 J N71-17843 A71-20078 IOLLER, C. A. HTSTROI, E. G. A station-oriented area naviqation system The role of communications in the national A71-21166 Airspace system IULLER, C. A. [AIAA PAPER 71-2481 A71-19722 HTF-48 sinqle rotor compressor development Final technical report r AD-7156261 N71- 1880 1 0 IOUSETOKOV, D. A. 08, 1. 1. Mathematical model of nonstationary gas motion in The effects of lightning attachment phenomena On internal conbustion enqines aircraft desiqn A71-20780 A71-19936 IIOBAD. 8. J. OKAPOO. 0. A study of some factors influencinq the iqnition An experimental cooled radial turbine of a liquid fuel pool 171-17381 A71-19245 OKEE1E. J. V. IOBPEI. B. J., JB. Perspective of SST aircraft noise problem. I1 - National Export Expansion Council - Report of the Thrust losses and installation factors industry committee on commercial aircraft A71-20302 N71-18087 OLSOI, D. J. Semiscale bloudoun and EmerqenCy Core CoOlinq /ECC/ project test report - Tests 822 and 823 N r In-i 393 1 N71-17190 HAUEVICZ. J. E. OIKLCBSIKO, V. I. Studies of supersonic vehicle electrification Some questions related to the vibration strength A71-19934 of aviation gas-turbine motors uith long Tests of ortho-decoupled aircraft static operatinq times discharqers A71-21710 1171-18114 OBLIK-BOKCKEIIUI, K. J. UAHGII. I(. K. On dynamic stability testinq of unconventional Delta rinqs with lonqitudinal camber at lou speed confiqurations r ARC-CP-1129 J N71-17112 f AIAA PAPER 71-2761 171-22001 UAPOLITAHO, 1. ORIISTOI. E. A. Position of the closinq shock in a supersonic Theoretical and experimental aerodynamics of the underexpanded two-phase jet sailuinq A71-21925 A71-20303 UAAJES. 1. OSIPOT, A. A. Optimization methods for jet-propulsion uith Desiqninq a supersonic nozzle contour uith respect to exergy allouaace for changes in the flight conditions 171-21300 of a flight vehicle IELIS, 1. P.. JB. A71-21865 Preliminary study of advanced hypersonic research OTSOKA. S. aircraft Performances of cascade of blades with small INASA-TM-X-2222] N71-18367 aspect ratio. I - Performances at the center of HELSOU, J. C. blade span Automation of terminal Air Traffic Control - Past, A71-20624 present and future [AIAA PAPER 71-2423 A71-19717 HESTLER. D. E. P static pressure port errors in hyprsonic turbulent PAK, I. I. flow Plou around an arbitrary star-shaped contour rAIAA PAPER 71-2701 A71-21996 A71-19745 HEWIIU, a. I. PII. T. s. Recent developments in liqhtning protection for On the diffraction of a shock rave by general aircraft and helicopters tuo-dimensional disturbances 171-19930 171- 19255 IEWSOI. W. J., JR. PAICBSIKOV, A. 1. Pliqht investiqation of a V/STOL transport model Uonstationary aperiodic motion of a lifting with four pod-mounted lift fans surface in an incompressible fluid [NASA-TN-D-6129 J 1171- 17423 A71-20778 IIEDZWIECKI, 8. W. PARK=, 8. I. Performance of a short modular turbojet combustor Oniversity of Virqinia superconducting uind- seqment usinq ASTI-A1 fuel tunnel balance [NASA-TN-D-61671 N71-17414 A71-20151 IIKXGODKA, 1. J. PABKSH, J. Effect of the position of maximum thickness and of Air pollution at Aeathrou hirport, London - the lenqth of bodies of revolution on April-September, 1970 aerodynamic coefficients in supersonic flow A71-21823 I DLR-FB-70-54 1 1171- 18444 PAPKBOISIKO. 1. 1. IIIEI. J. I. Evaluation of the precision of executing the Orientation-error accidents in reqular Army 80-1 outside contours of units uith allouance for the aircraft durinq fiscal year 1967 - Relatite elastic characteristics of the elements incidence and cost assembled and equipment [ AD-7151071 N71-17854 A71-20792 UOUSZBOD, E. PATSL. 1. C. A correction for compressible subsonic planar flou Improved entraiument method for calculating 171-20312 turbulent boondary layer detelopment 1171-18424 [ ARC-R/I-3643]

B-19 PEESOYAL AUTEOP 11Dm IIISOLDS. a. J.

PLI11IX. 6. POET. P. 6. L. Tests with a wing-mounted fan nacelle with the fan Low speed flight tests on a tailless delta wing jet simulated by cold air blowing and aircraft /Am0 707B/. Part 4 - Ping flow alternatively by a gas generator shroud Interim [ ARC-CP-1107-PT-4 1 171-17082 report Low speed flight tests on a taiiless delta wing [ARC-CP-11111 171-17113 aircraft /Am0 707B/. Part 3 - Lateral PAVX.11. C. stability and control The-design and construction of a pressure [APC-CP-1106-P?--3] 1171-17083 regulator including fluidic elements POST. E. I. A71-20580 wind-tunnel tests of small decelerator stahilizars PLTRI. E. E. 171-20310 Estimation of supersonic compressor efficiency P0ilM.L- F. D. [ AD-7150051 1171-18036 An adaptive landing system PISRY. E. E. A71-20405 noise measurement evalnation of takeoff and POPIRS. J. 0. approach profiles optimized for noise abatelent moi& rednction operational procedures 111ASA-TU-D-62461 171-18929 A71-21813 PIIIIBO, c. PRAIK'B. W. T. Base pressure measurements on the 16-70 airplane Lightning and surge protective devices for at lach nnmbers from 0.4 to 3.0 survivability of electrical systems [ UASA-TU-1-1612 1 171-17132 171-19941 PIPPIE. P. 8. PRXUTW. 8. Wind-tunnel tests of small decelerator stabilizers Effusion cooling of turbine blades A71-20310 1171-17382 PIEPI, B. 1. PPOCUASKA. B. J. Static discharge Ninimum variance estimates of signal derivatives - A71-19624 A problem in instrnment landing systems Liqhtning and static hazards relative to A71-21343 airworthiness PRIJST. 8. u., Jp. A71-19929 Cold-air investigation of a turbine with PIIPEI, D. E. transpiration-cooled stator blades. 2 - Low speed flight tests on a tailless delta wing Performance of stator with wire-mesh shell aircraft /Avro 707B/. Part 4 - wing flow blading [ ARC-CP-1107-PT-4 1 1171-17082 r 11ASA-TN-1-21661 171-17590 Low speed flight tests on a tailless delta wing PIJ68,'P. 6. aircraft /Avro 707B/. Part 3 - Lateral An analysis of sonrces of error in typical stability and control pressure measurements in a blowdown supersonic [ ARC-CP-1106-PT-31 171-17083 tunnel PIPIYSEII. I. v. [ IIPL-AERO-1306] 1171-17081 Selection of the design point on the PIJBLIAII. 6. characteristic curve of the fan of a tnrbofan Problems of the acceptance check of airliners engine with a large bypass ratio A71-20065 A71-22042 PULLI1G. E. 1. PIITO. J. The federal regnlation of aircraft noise An analysis of sources of error in typical ~71-2ia27 preasuze measurements in a blovdovn supersonic PILB. J. S. tunnel Lift and drag characteristics of the BL-10 lifting [ APL-AERO-13061 1171-17081 body during subsonic gliding flight PIITROT. B. 1. [ AASA-TU-D-6263] 1171-18867 Certain problems of structural synthesis of spatial motion control systems for an orbital aircraft in the earth's atmosphere Q [ AD-7147961 1171-17747 PIJIHLIIAI. J. T. PIEXFIR, I. Liqhtninq protective coatings for boron and Approach quidance to circnlar flight paths graphite fiber reinforced plastics IAIAA PAPER 69-9861 A71-20305 1171-19944 PIFCO. A. Finite element analrsis of structures in the plastic ranqe R r NASA-CR-16491 1171-19276 BABE, J. U. PIKE, I. C. An overview of the national Airspace System lanual on aeroelasticity - Subject and anthor [ AIAA PAPER 71-2441 A71-19719 index RADKR, U. P. [ AGARD-E-578-711 117i-17432 Aerospace systems pyrotechnic shock data /ground PIKB. J. test and flight/. volnme 7 - Investigation of On lifting surfaces supporting one or more plane mass loading effects Final report, 12 lay - 12 shock uaves Uov. 1970 IARC-R/N-3623] 1171-17109 r IIASA-CR- 11 60 193 1171-19250 PIISKBP. P. J. 6. BAJU. 6. V. S. The control characteristics of aircraft employing Ban-machine considerations in system design for direct-lift control all-weather, lor-level navigation [ ARC-R/N-3629 ] B71-17102 A71-20344 PLBBAI, I. J. RAY. J. D. Analytical heat transfer investigation of lechanical properties of high-performance plastics insulated liquid methane fuselage tanks for composites supersonic cruise aircraft rPLASTICS IAST. PAPER 291 A71-20917 [ AASA-TA-D-6 157 1 171-17506 IIBDIIG. J. P. PLwa~n. J. A. Dynamic support interference - Fact or fiction Beasurements and analysis of lightning-indnced [ AIAA PAPER 71-2771 A71-22002 roltaqes in aircraft electrical circnits R16AI. F. J. [ NASA-CR-1744 1 Three-deqree-of-freedom gas bearing for wind- wLL3YT. J. tunnel dynamic measurements The Concorde powerplant rAIAA PAPER 71-2791 171-22004 A71-19081 RBIIOLDS, a. J. wwv, v. I. The application of computer aids in the analysis Beat exchange and frictional drag durinq turbnlent of fault data generated by a large data handling flow of air uith equilibrium ionization and system dissociation aronnd a plate 171-19556 A71-21922

B-15 RICE. E. J. PERSONAL AUTEOR INDEX

RICE, E. J. RUSANOV. '1. V. hcoustic and aerodynamic performance of a Gas flows past blunt bodies. Part 1 - Methods of 6-foot-diameter fan for turbofan engines. 3 - calculating and analyzing flows Performance with noise suppressors A71-19049 [ NASA-TN-D-61783 1171-17254 Gas flows past blunt bodies. Part 2 - Tables of RICEIRD, C. B. gasdynamic functions Comparison of hydrogen and methane as coolants in A71-19050 reqeneratively cooled panels RUSSELL. D. A. TNASA-CR-16521 N71-19289 A study of fog clearing using a COZ laser RICEIRDS, E. r. [AIAA PAPER 69-6701 A71-20308 Investiqation of flow characteristics of some RUSSELL. R. E. wire-form and laminate-form porous materials Aircraft noise, its source and reduction [ NASA-TN-X-2111] N71-17130 A71-21814 RICEEIS, J. RUST, T,. JR. Air-cooled turbine desiqn criteria Investigation of jet engine CoBbUStiOn chamber N71-17402 burn-throuqh fire Final report, 1963 - 1969 RIDER, 1. E. [ FAA-RD-70-681 N71-17483 The need, meaning and usefulness of meteorological RUTAII. B. observations for aviation Fiqhter testing - Spin test or spin prevention A7 1-2 1732 test BIEDEL, E. A71-19095 Effect of the position of maximum thickness and of RUITON-DAVIES, 9. D. T. the length of bodies of revolution on An adaptive landing system aerodynamic coefficients in supersonic flou A71-20405 [ DLR-PB-70-541 171-18444 RISEV. 0. V. ROBB. J. D. Nonstationary low-density flows possessinq Recent developments in liqhtninq protection for symmetry aircraft and helicopters 871-19729 A71-19930 Liqhtninq test facilities measurement techniques A71-19931 S Lightninq protection for dielectric composites SABLIIIA, Z. A. A71-19942 Variation of the hiqh-temperature properties of ROBIISOI. D. if. jet fuels durinq prolonged storaqe Towards a unified system of noise assessment A71-19492 A71-20802 SADOVSKII. V. S. ROBIIISON, G. 6. Supersonic three-dimensional flow with heat supply An alqorithm for diqital resolution of ranqe for and stream deflection V/STOL aircraft 1171- 19746 r NASA-TN-D-6 2 32 ] N71-16566 SLKEIIO. A. G. ROBIIISON. J. C. Liftina properties of some configurations An analvtic study of radiative17 cooled delta-viag according to the slender body theory structures for hypersonic aircraft A71-20776 r NASA-TN-D-61381 N7 1- 186 25 SALKOVITZ. E. 1. ROBIISOI. 1. 1. Third International Conference on Rain Erosion and Further flow calibration in the blowdown wind Associated Phenomena tunnel S3 I AD-7 15 100 1 N71-17906 URE-TN-RSA-1713 N71-19170 SALTZIAN, E. J. ROEIER, C. E. Base pressure measurements on the XB-70 airplane A strapdown maqnetic azimuth detector at aach numbers from 0.4 to 3.0 1171-20340 [NASA-Tlf-X-1612] N71-17 132 ROGERS. n. E. SARIA, G. I. A study of some fundamental helicopter charqinq Response of skin friction to the angle parameter mechanisms in flow past an axisymmetric body moving in the 171-19933 direction of its axis ROI. P. E. 871-20098 Nuclear power for surface effect vehicle and SATO. 0. aircraft propulsion The latest airport liqhtinq facilities I NASA-TU-X-52963 J N71-18628 A71-20355 ROIISEBVSKII, E. A. SCAIILOI. J. 8. Role of radiation absorption in front of a shock Dispersion modelinq of airport pollution wave in the hypersonic flow past a blunted body A71-21824 671-19730 SCBAIRRB, G. S. BOOS, P. S. Perspective of SST aircraft noise problem. I1 - Some experimental results on sphere and disk draq Thrust losses and installation factors A71-19893 A71-20302 ROSATI, J. J. SCEATT. P. A project information and simulation system for Problems of the acceptance check of airliners aerospace mznagement A71-20065 [AIAA PIPER 71-2381 1171- 19714 SCBBREAG. R. ROSCOE, S. I. Developments in stratospheric and mesospheric The frequency-separated display principle, phase 2 analyses which dictate the need for additional Annual summary report, 1 Apr. 1969 - 31 Oct. upper air data 1970 A71-21724 r AD-7154581 N71-18739 SCEIPP. 1. B. ROSS. R. 8. A nonlinear aerodynamic moment formulation and its Strateqies of noise abatement throuqh land use implications for dynamic stability testing A7 1-2 1836 rAIAA PAPER 71-2751 171-22000 ROZENSRTEIN, I. E. SCEIPFER, s. P. Some results of investiqations of centripetal and Aircraft zinc-silver oxide batteries radial-flow staqes A71-21103 A71-22049 SCEIIIDLER, G. I. BUWLPE, J. A. Propaqation, distortion, and shock formation of The coming of aqe of the associative processor pressure pulses in a nonviscous fluid of A71-19997 constant state RUIGALDIER, E. A71-19961 Anemometer measurements of velocity and density in SCELERETE. P. projectile wakes Special purpose telemeter for a jet engine [AIAA PIPER 68-7011 A71-19891 environment

6-16 PERSOlAL AUTHOR IlDEX STAHIAIR. J. P.

A71-19628 SEIPPII. E. 6. SCELESIIGEB. El. I. Formation of a hanqing shock wave during flow past The AOL Eypervelocity Uind Tnnnel a profile with a broken generatrix [AIAA PAPER 71-2531 A71-21982 A71-21872 SCELUETEB. E. 6. SBIH. s. 1. Demonstration system for two-dimensional aircraft ILS localizer mnltipath analysis motions A71-18831 171-20066 SEIPUAT. J. C. SCHIITT, 6. F.. JB. The correction of hovercraft performance to Development and calibration of a Each 1.2 rain standard conditions erosion test apparatus Technical report, mar. [ APL-EOVEBCBAFT-16 J n7i-17184 1966 - Ang. 1969 SEKAlOI. I. 1. [ AD-7159091 mi-18651 Egnivalent tests of aircraft engines SCEIEIDEB. S. D. A71-21115 The effects of lightninq attachment phenomena on SHIAKOV. I. P. aircraft design Method of determininq the optimnm minimum-noise A71-19936 take-off profile of an aircraft SCEOCK. I. E. A71-20779 Conditions inside cnmnlns clonds preceding the SBIA1E1KOV. I. 1. onset of precipitation Aatnre of the anomalous seeded flow past blnnted A71-21450 bodies in hypersonic wind tnnnels SCBOEIBECK. A. A71-18924 Effnsion coolinq of turbine blades SHIITE. E. El. 871-17382 The role of man in Aerospace Defense Command SCEOLX. 1. naviqation Effnsion coolinq of tnrbine blades A71-20346 1171-17382 SIElPSOl. I. A. SCWETZ. D. Experimental atmospheric absorption values from Strength of liqht metal alloy rods with irregnlar aircraft flyover noise signals notches nnder cyclic tensile loads and A71-21425 periodically interspersed compression loads SIISBAL. A. C. [ PB-78- 1969 ] n7i-i7524 A project information and simnlation system for SCHUIACHER. P. 3. aerospace management An investiqation of the trailing vortex system [AIAA PAPER 71-2381 A71-19714 qenerated by a jet-flapped wing operatinq at SIITB. D. D. high wing lift coefficients Final report Spinninq the A-7 [AD-7153153 871-17753 A71-19094 SCEPARTZ. A. E. SIITE. 1. I(. Low profile optical system for an aircraft beacon Testimony of midair collision hazard before the 1171-19203 National Transportation safety Board SCHVEIKEABD. P. 6. 871-18103 Verification of takeoff performance predictions SUITE, E. 5. for the XB-70 airplane Are microelectronic circuits reliable enough for I NASA-Ta-I-22151 ~71-18509 aircraft engine control applications SEEGIIUEB. E. 1. [SAE PAPER 7008221 A71-21369 Convective heat transfer to the Ames I2 and I2P2 SSESIREV. 1. A. lifting entry vehicles A gasdynamic stand for tesring materials and [ AASA-TU-X-16911 871- 17 131 strnctnral elements for their resistance to SEIDEI. 1. cyclic thermal loading A comparison of flight test data for two subsonic A71-20839 spln stabilized proiectiles with trajectory SOLAK. E. J. predictions based on aerodynamic data obtained Inflnence of liqhtninq and static electricity as in a water tunnel applied to helicopter design FAIAA PAPER 71-2961 A71-22016 1171-19938 SEKUUDOI. A. 1. SOIIER. E. U. Experimental studv of flow in the wake behind thin Simulator stndy of flight characteristics of a plates let-flap STOL transport airplane during approach A71-19750 and landing SEAALLN, n. E. a- [NASA-TA-D-62251 1171-17433 A wind-tnnnel investigation of the stalling SOOSA, P. E. performance of two compressor cascades of Displays in the Bational Airspace System different aspect ratios at low speed fAIAA PAPER 71-2471 A71- 19721 [ ARC-CP-1103 J 871-17108 SOIICEE. 6. SEABOKEII. I. A. The design and construction of a pressnre Arrangement of manometric eqnipment on an oriented regulator includinq flnidic elements satellite A71-20580 A71-21022 SPEE, B. I. SEAIEBPOOK. J. P. Investigations on the transonic flow around Crossflow profiles for compressible, tnrbulent aerof oils bonndary layers A71-19773 1171-22033 SPEZIA, E. SBAPIBO. U. A. Orientation-error accidents in regnlar Lrmy 88-1 A strapdown magnetic azimuth detector aircraft during fiscal year 1967 - Relative A71-20340 incidence and cost SEAU. A. U. [ AD-7151071 mi-17854 Ose of qronnd based simulators in aircraft design STASG. A. n. A71-20309 An investigation of the scatter in SEAP, T. 1. variable-amplitude fatique-test resnlts of 2024 On the nature of fluctuating circnlation, lift and and 7075 materials flow-indnced strnctnral vibrations [ ARC-CP-1123 J 871-17330 A71-19592 STABIAll. J. P. SBEAP, U. 6. Iodel studies of stroke probability to selected The airline collision avoidance program points on aerospace vehicles A71-21167 A71-19928 SEESTAKOI. IO. 1. Becent developments in lightninq protection for lature of the anomalous seeded flov past blnnted aircraft and helicopters bodies in hypersonic wind tunnels 171-19930 A71-18924 Liqhtninq protection for non-metallic rotor blades A71-19939 STAUZIONE, D. C. PERSOUAL AUTEOR INDEX

STAUZIONE, D. C. Hinimum variance estimates of siqnal derivatives - A problem in instrument landinq systems T A71-21343 TABAKOPP, W. STARKUEATEER. G. U. Heasurements of particulated gas flow pressure on Control of distributed parameter systems as cascade nozzles applied to a lunar landing vehicle simulator [AIAA PAPER 70-7121 A71-20311 NASA-CR-116482] 1171-17345 TAGAUOV, G. I. STATEU. 1. E. Snpersonic three-dimensional flow with heat supply P-104D side stick control system and stream deflection 1171-19092 A71-19746 STEIU. A. J. TALIAUKBE, 1. E. A V/STOL microwave approach and landinq systea Investigation of the influence of operatinq A71-21680 conditions on the mean fliqht time between STEIUEOPP. E. J. overhauls Liqhtninq and surqe protective devices for A71-20797 survivability of electrical systems TAUIS. C. A71-19941 Filament windinq an aircraft winq structure STETSIUK, D. V. r SHE PAPER EH-70-406 3 A71-20546 Investiqation of the flow parameters in a TANUBR. R. 1. centrifuqal-pump wheel Tests of ortho-decoupled aircraft static A71-22048 dischargers STETSON, A. R. N71-18114 The composition, microstructure and protection TAYLOR, A. P. afforded by several commercial coatinqs on two Vortex devices in aircraft fluid systems nickel-base alloys A71-20556 INA SA-CR- 11637 4 1 N71- 17393 TAYLOR, C. E. STBVEIS. B. E. Super VC 10 cruise draq - A wind tunnel Economic impact of the Dallas-Port Worth Regional investiqation. Part 1 - Experimental techniques Airport on the north central Texas reqion in [ARC-CP-11251 1171-17118 1975 TAYLOB. J. 1. N71-18099 Comprehensive planning and aircraft noise at STOUE. D. 1. W. Kansas City International Airport An investiqation of the stresses in a wind tunnel A71-21837 corner section TELAUG, S. R. r ARC-CP-1117 1 17 1- 17100 Desiqn features and characteristics of the 9 I 6 STOTTlllUU. P. ft Yind tunnel at A.A.L., Bangalore Temperature measurements with thermocouples A71-21305 includinq errors caused by catalytic effects TEBEUTEV. A. G. N71-17379 Plow of a heavy fluid past a plate with partial STBUIIKIN, V. A. cavitation Improvement of multistaqe turbines in qas turbine A71-20087 enqine desiqns TEBRELL. 1. 6. A71-21267 The response of a turbulent boundary layer on an so. 1. I. /infinite/ sweDt wina to the sndden removal of

Automatic processing of multispectral observations pressure bradient ~ lAIAA PAPER 71-2341 A7 1- 19711 TNPL-AERO-13051 N71-17179 SUCIU. s. I. TEALBE, 6. J. Aiqh temperature turbine desiqn considerations Analysis of nonlinear control systems with 1171-17386 transport lag SUDEEEUDEA, K. 5. A71-20369 Desiqn features and characteristics of the 9 x 6 TEELBN. J. ft wind tunnel at 8.1.1.. Banqalore Data acquisition on hypersonic wind tunnels A71-21305 DLR-PB-70-44 ] N71-17046 SULLIVAU. P. A. TEEUBEE. B. W. A review of the status of the technoloqy of the P-104D side stick control system air cushion vehicle A71-19092 [SAE PAPER 7101833 A71-21713 TEOIIPSOI, m. 0. SUIIIEEl'IELD. 1. Liftinq-body Proqress report A study of some factors influencinq the iqnition [ NASA-TM-I-66712] 1171-18428 of a liquid fuel pool TEOIIPSOU. 8. E. 171-19245 Liqhtninq and surge protective devices for SUIIUER. W. J. survivability of electrical systems Crossflow profiles for compressible, turbulent A71-19941 boundary layers TIIG, LO. 171-22033 Diffraction of a pulse by a three-dimensional SUUDERIIAII, E. P. corner Automation of terminal Air Traffic Control - Past, [ NASA-CR-17281 N71-18029 present and future TOBAK. m. [AIAA PAPER 71-2421 1171-19717 A nonlinear aerodynamic moment formulation and its SUPEUU. v. !I. implications for dynamic stability testing Approximate theoretical model of a winq with (AIAA PAPER 71-2751 A71-22000 suction and blowinq TOKABII. V. I. A71-20777 Method of determininq the optimum minimum-noise SVEUSOU, 0. take-off profile of an aircraft Strenqth of light metal alloy rods with irregular h71-20779 notches under cyclic tensile loads and TOUDEL. 1. II.. JB. periodically interspersed compression loads Federal regulation of aircraft noise, the legal IPB-78-1969 1 N71-17524 rights of airport neighbors, and leqal aspects SUAIII. E. 1. of coapatible-land use Aircraft elastic mode control 171-21829 171-20301 TOWUSEUD. 1. E. su1us0u. u. E. Rectanqular and caret sails in supersonic flow Avionics for aeronautical systems r ARC-R/M-3624 1 171-17103 A71-18829 TEA11. P. C. SUIEAET, J. !I. single stage experimental evaluation of boundary The united States SST and air quality layer blovinq and bleed techniques for high lift 171-21821 stator blades, 5 Final report INASA-CR-545731 1171-18749

8-18 UISET. K. C.

'2lBAEER. I. 1. Pumps Aircraft gas turbine engine technoloqy A71-20793 A71-21625 TOPOlKIl. T. 6. '2111111. '2- '2. Influence of the suppression of chemical reactions Position-determination systems for urban transit in a nonegnilibrium laminar boundary layer on and air traffic control the heat exchange A71-21169 171-19748 TSIAIOT. A. E. Plow for a sudden wideninq of the channel A71-2204 1 W nom. 0. P.. J.. WACO. D. 11. Beat protection apparatus Patent Eatio of turbulent flight miles to total flight [I&SA-CASB-XLA-O0892] 171- 17897 miles in the altitude range 45.000-65,000 ft '21EAI. 1. L. 171-20314 Electrostatic charging and noise quieting .ALKO. L. c. All-19937 Measurements and analysis of liqhtning-indnced '2SIcLAUBI. 6. T. voltages in aircraft electrical circuits Position of the closing shock in a supersonic [ EASA-CR-1744 ] 117 1- 19122 underexpanded two-phase let UALSBX. D. X. A71- 21 925 The use of aerodynami~stabilizing strakes on TSTBIZOT. IU. I. chimney stacks supporting pipes Construction of lines of flou in a complex region [ IPL-AERO-1310 1 1171-17334 of tuo-dimensional supersonic flow UALTIXS. I. II. A71-22052 Comparison of hydrogen and methane as coolants in TUDOR, D. E. regeneratirely cooled panels Experimental wake survey behind a 120 deq included [ EASA-CB-1652) 1171-19289 angle cone at angles of attack of 0 deg and 5 SAW, 2. deq. Mach numbers from 1.60 to 3.95. and An experimental study of the effects of longitudinal stations varying from 1.0 to 8.39 leadinq-edge blouing upon the characteristics of body diameters a jet-flapped airfoil [ IASA-TM-1-2139 J 171-18480 1171-17702 TUMASHET. 6. 6. PARD, T. 9. Inrerse boundary value problems and their A comparisoh of fligbt test data for tu0 subsonic applications in hydroaeromechanics spin stabilized projectiles uith trajectory A71-20078 predictions based on aerodynamic data obtained '2816. C. in a water tunnel The feasibility and use of anti-torque surfaces [AIAA PAPER 71-2961 A71-22016 immersed in helicopter rotor domwash Technical PA8PX1. J. II. report, Jan. 1968 - Dec. 1969 Evaluation of film cooling.. performance on qas [AD-7154381 171-18937 turbine snrfaces TUPlXB. A. B. 1171-17395 Beat transfer instrumentation llXBXRB. 1. 171-17377 Synoptic aerological conditions for the occurrence Transpiration-cooled turbines of clear air turbnlence 171-17383 [ DLR-PB-70-293 871-17145 RSL. x. s. EBBSTEB. D. Overall performance in argon of a 3.7-inch Improving structural efficiency through materials six-stage axial-flou compressor selection [ 1ASA-TO-1-2194 J 171-17882 A71-21685 WxISxL. c. Overall performance in arqon of a 3.7-inch V six-stiqe axial-flow compressor TALXXT. K. 6. r 1ASA-TM-X- 2194 1 171-17882 Method of determining the optimum minimum-noise .BIlSiocK. 6. 1. takeoff profile of an aircraft Liqhtninq protection on advanced fiqbter aircraft A71-20779 171-19940 TAKX. E. ?. UXLLS.. P. studies of supersonic vehicle electrification Estrmation of supersonic compressor efficiency A71-19934 [ AE-715005] 871- 18036 TIILLFRE. 1. J. 111IlT%. U. E., JE. Anqular position and velocity sensing apparatus Vortex breakdown on slender sharp-edged wings Patent [AIAA PAPER 69-7781 A71-22028 CIASA-CASL-X6S-O5680J 1171-17585 WBST?IXLD. E. '2. TELCOF?. 1. B. The current and future basis for aircraft air Boundary-layer discoutinnity on a helicopter rotor pollution control blade in hoverinq 171-21832 r AIAA PAPBB 69-197 J 1171-20307 PBIlIRI. D. 6. VXBBULBS. P. 1. Filament uinding an aircraft uing structure Experimental performance and combustion stability [SUE PAPEE Elf-70-406 J A71-20546 of a full scale duct burner for a supersonic WBITBXCK. J. ?. turbofan engine semiscale blowdom and Emergency Core Cooling [ IASA-TI-D-6163 J 171-18882 /ECC/ project test report - Tests 822 and 823 ~BTUSEKIl, T. K. ~II-13931 1171-17190 Role of radiation absorption in front of a shock WHITE. 1. 1. wave in the hypersonic flou past a blunted body Results of tuo-phase blou-down experiments. Part 1 A71-19730 - Straight tube test section TIICN)PI1. K. J. [AECL-3664] 871-1 E161 The hypersonic laminar boundary layer near a sharp WITLOW. J. 1.. JP. expansion corner Parametric enoine studv for a Mach 0.98 commercial 171-17752 air transpokt TIlCXR. '2. L. [ 11ASA-TU-X-529611 1171-18733 On barriers in a problem of collision avoidance ilI66EBS. 6. 1. A71-21322 Cleveland rail transit airport service TIlOK8.OV. I. 1. 171-18956 Service life of bearinq elements of aircraft gear WISEIT, K. C. mmes An experimental investigation of wind-tunnel mall A71-20793 conditions for interference-free dynamic TOLOSEfl. 33. I. measurements Service life of bearinq elements of aircraft gear [ UPL-AERO-1307 J 871-17085

8-19 IILKEBSON, C., JB. PERSONAL AUT808 IUDEI

IILKEBSON~ C., JB. a centrifugal conpressor on the compressor An evaluation of sinqle and multiple sting support parameters methods to obtain unmodified interference-free A71-20781 rind tunnel data ZOIIICK, D. A. [AIAh PAPER 71-2671 171-21993 Diqital-filter alignment of strapdown navigators IILKEBSOU. 1. B. A71-21170 Functional requirements for ground-based trainers - Helicopter response characteristics [ AD-7149541 N71-18018 IIILKIUSON, J. P. D. The calculation of optimal linings for let engine inlet ducts A71-21661 IILLIIABTW, I. I. some experimental results on sphere and disk draq A71-19893 WILSOU, 8. V. An evaluation of the usefulness of four secondary tasks in assessing the effect of a lag in simulated aircraft dynamics fIAII-R-479] N71-18838 WILSON. W. A. methods and apparatus employing vibratory energy for urenchinq Patent NASA-CASE-IPS-20586 1 N71-17686 IIUTEBBOTHAI, J. A. Airtruk A71-21224 WISE, K. survey of air traffic control radar beacon system operational problems /30 day ATC controller survey/ N71-18116 WISSLIB. 3. G. Navy testing in the next decade 1171-19077 WOEWB, 1. A. wind-tunnel free-flight testinq of confiqurations uith hiqh-fineness ratio bodies rAIA& PAPER 71-2783 A71-22003 WOOD. J. I. Tha P-15 air superiority fighter A71-19078 WOODSUM, G. T. Liqhtuinq protection for advanced composite aircraft structures A71-19943 WRIDE. A. T. A. Novement of high density loads r NPL-EOVERCRAPT-Tn-31 1 N71-17160 WUEST; w. Aypersonic low density wind tunnel plant [ BNBY-FB-W-70-51 J N71-18593 Y YANTA. I. J. The use of a laser Doppler velocimeter in supersonic flow [AIAA PAPER 71-2871 A71-22010 XATSUNOVICH, II. S. Practical aerodynamics of the mi-6 helicopter IAD-71491 5 1 N71-17908 Z ZAITSEV. V. A. Instruments for studyinq foqs and clouds and neasurinq humidity 171-20298 ZILAS. J. II. Effect of structural dampinq on the airborne sound transmission loss of ribbed panels A71-2143 1 ZAPATA. R. 1. university Of virqinia superconducting uind- tunnel balance A71-20151 ZAPOLIN, 8. E. Explorinq future tactical air information distribution bv simulation ~AIAAPAPER 7112431 1171-19718 ZATSEPIN. 1. P. some iesults of investiqations of centripetal and radial-flow staqes A71-22049 IELDES. 1. 1. methodology of the experimental investigation of the influence of water snpplied to the inlet of

B-20 CONTRACT NUMBER INDEX

AERONAUTICAL ENGINEERING / A Special Bibliography(Suppl.5) MAY 1971

Typical Contract Number Index Listing 81153-12019 12U-07-01-03-00-21 09 871-19122 02 n7i-17131 8155-21241 125-17-03-01-00-21 Flr 32 87 1-19250 02 871-18566 NUYSER NUYSER 8ASU-1908 125-19-01-03-24 12 8-11-17958 02 871-18442 Lstings in this index are arranged alphanumerically by contract number 8ASW-1992 12 5-19-0 3- 1 1-00-21 Under each contract number the accession numbers denoting documents 28 A7 1-21 661 10 171-18836 that have been produced a5 a result of research done under that contract are arranged In ascending order w* the IAA accession numbers appearing EA 51-20 35 125-19-03-15-00-21 21 1171-18761 first The accession number denotes the number by which the citatnn IS 02 871-17441 01 17 1-1 7468 identified in either the IAA or STAR section 12 871-18401 126-13-10-04 02 A7 1-1 741 5 AASU-2037 02 871-17425 AP 04/694/-992 12 871- 17443 01 A7 1 - 19891 P33615-69-C- 1664 01 871-18397 126-13-10-06 02 871-17792 01 871-17424 AP 04/701/-68-C-0041 IIASU-2038 01 A71-19891 PA-SS- 6 7- E 01 E71-18987 126-1 5-1 3 02 A7 1- 19936 28 N71-18733 AP 04/701/-69-C-0119 8GL-07-002-002 01 1171-19891 100014-67-A-0305-0014 11 N71-17345 126-61 02 171-18739 28 AP 19/604/-3458 NGL-22-009-124 02 871-18114 E00014-68-C-0241 21 A71-21335 126-61-03-01-24 02 171-18937 02 A71-1795 1 AP 33/615/-67-C-1187 8GL-33-016-119 32 A71-22026 noooi4-69-c-0267 33 A71- 19255 126-62-03-05-00-21 02 871-17907 12 1171-18029 02 871-18929 AP 33/61 5/-69-C- 1552 02 A71-20314 noooig-68-c-0075 UGB-03-002-011 129-01-22-10 11 A71-20309 21 A71-21322 30 171-1 8015 AP 33/616/-6561 02 171-181 14 noooi9-69-c-oioi IGB-11-002-081 188-48-01-01-00-21 10 A71-18835 34 1171-17843 01 1171-17877 AF 33/657/-7868 11 A71-20309 noooig-69-c-0533 NGB-17-001-043 720-01-10-02-00-21 28 871-18801 01 A71-22028 02 871-18559 AP 44/620/-68-C-0018 12 171-19908 8ASl-5002 NGR-21-001-001 720-03 33 871-19289 13 1171-18996 01 871-17130 AP-APOSB-69-17241 01 N7 1-17247 21 A71-21335 8AS1-6450 8GB-22-009-378 28 N71-174 14 01 A7 1-2200 2 28 A71-20867 28 871-17506 AT/10-1/-1230 28 8-11-17554 22 8-11-17190 NAS 1-7 129 NGR- 4 1 - 0 01 -0 24 01 8-11-17589 02 871-17426 10 A71-21343 01 1171-17590 DAAJO 1-68-C- 1446 02 1171-17591 28 1171-18138 15 171-18920 02 871-17668 8GB-47-005-029 28 8-11-18560 02 87 1- 1 8499 11 A71-20151 33 N71-18561 DAEC04-69-C-00 16 28 871-18863 01 1171-20311 8AS1-7315 EGT-11-002-064 33 871-18882 28 E71-18036 32 871-1 9276 34 ti7 1 - i 7843 720-51- 0-07-24 DABCl9-7 0-C-00 12 tIAS1-8168 ASP GJ-9 02 871-18509 05 171- 1801 8 02 871-18865 32 A71-19887 72 1-01 -1 1-06 DOT-C-353-66 8AS1-9426 ESP GK-12697 02 871-17423 02 171- 16 904 28 171-19139 01 A71-22033 02 N7 1-17433 WT-OS-A9-023 8AS1-9465 nsp GO-2161 721-03 11 871-16988 28 171- 18714 34 E7 1-17843 28 171-17641 11 871-16989 11 1171-16990 8AS2-5524 PES-EC-00287 721-03-00-06-00-21 11 871-16991 02 171-19239 32 A71-20747 01 1171-18558 11 171-16992 1AS3-7619 SEP-1 722-01-00-02-00-21 E-291-68/6/ 01 871-18749 12 171-18962 02 E71-18367 20 1171-21722 EAS3-7900 OSDI-14-061D-5979 722-02-10-02 PO4701-70-C-0059 01 1171-18749 20 A71-21450 32 871-18025 01 1171-1 8556 RAS3-9401 120-27 722-03 P336 15-69-C- 1165 17 871-17393 01 117 1 - 17 354 11 171-17876 02 171-17753 01 871-17882

c-1 1

722-51-00-06-28 02 U71-18U22

732-01-00-02-24 02 971-17132 81s-io-91-02 12 171-18480 81 5-20-09-08 01 971-17253 976-30-20-00-62 12 u71-17uuu 1. Report NO. 2. Government Aaarion No. 3. Recipient's Catalog No. NASA SP-7037 (05) 4. Title and Subtitle 5. Report Date May 1971 AERONAUTICAL ENGlNEERlNG A Special Bib1 iography (Supplement 5) 6. paforming Organization code

7. Author(s) 8. PerformingOrganization Report No.

10. Work Unit No. 9. Petforming Otpnization Name and Adchsa

National Aeronautics and Space Administration 11. Contract or Grant No. Washington, D. C. 20546 I 13. Type of Report and Paiod Covered 12. Sponsoring Agency Name md Address

14. sponsoring Agency Code

15. Suppiementarv Notes t 16. Abstmct

This special bibliography lists 570 reports, articles, and other documents introduced into the NASA scientific and technical information system in April 1971. Emphasis is placed on engineering and theoretical aspects for design, construction, evaluation, testing, operation and performance of aircraft (including aircraft engines) I and associated components, equipment and systems. Also included are entries on research I and development in aeronautics and aerodynamics and research and ground support for aeronautical vehicles.

~ 1 i I I I

Aerodynamics Aeronautical Engineering Unclassified - Unlimited Aeronautics Bib1 iographies

19. Security assif. (of thii repon) 20. Security Clwif. (of this pagel 21. No. of Pages 22. Rice* Unclassified Unclassified 169 $3.00 HC

For sale by the National Technical information Service, Springfield, Virginia 22151 tjeposlts ss :ecftn:cat documenrs and brbikgraptr' n &eve8 Federal Rmgtcmal T%&n& ~eptlrt&fi:ers ;mated tn $he organuations fisted befow.

NASA documents for retentm

f and PiB%%sponxlred

EUROPEAN An extensive colfection of NASA and NASA-sponsored pubkatrons 1s maintained by the Nationat Lending Library for Science and Technology Boston Spa. Ywkshiie, Engiand By virtue of arrange- rnenfs o?hw than vrrth NASA the National Cendrng Library also has avarlabte many of the non-NASA pzbittrcatxms ated in STAR €gropean reqwsterr may purchase faesimiie copy or mmofrche of NASA and NASA sponsored documents. those rdenttfted by bath t ks "f'and "*". from- ESRO/ EFnO Space Documenlation Sarvrce, European Space Res anizatton. t 14, BV de Meuilly. 92-NeujHy-sur-Seine. France NATIONALAERONAUTICS AND SPACE ADMIh‘ISTRA1 ION WASHINGTON,D. C. 20446 OFFICIAL BUSINESS FIRST CLASS MAIL PENALTY FOR PRIVATE USE $300 POSTAGE AXD FEES PAID NATIONAL AERONAUTICS A SPACE ADMINISTRATION

If Undeliverable (Seicion 158 POSTMASTER : Postal Manual) Do Not Recur,

‘The aerouadcnl and space activities of the United States shall be condtdcted so as to contribzdte . . , to the expansion of himan knod- edge of phenoiifend ia ?he ~.!viorphc:c find spJct3. The Administration shall provide for the widest practicable nnd appropriatc dissemination of ivforiualion concerning its dsirrilirr nnd ibe resdts thereof.”

-NATIONAL AERONAtiTICS AND SPACE ACT OF 1958

NASA SCIENTIFIC AND TECHNICAL PUBLICATIONS

TECHNICAL REPORTS: Scientific and TECHNICAI. TRANSLATIONS: Informtion techn ical informat ion considered important, published in ;I foreign Ianguage considered complete, and a lasting contribution to existing to merit NASA distriburion in English. knowledge. SPECIAL PUBLICATIONS: Information TECHNICAi. NOTES: Informarion less broad derived from or of value to NASA activiries, in scope but nevertheless of importance as a Ptiblications include conference proceedings, contribution to existing knowledge. monographs, data campilations, handbooks, sourcebooks, ani! special bibliographies. TECHNIC A I. MEMORANDUMS : In formt ion receiving limited distribution TECMNOI.OGY IJTILIZATION hcc;iiise of prclirninary data, stciirity classifica- PUBLICATIONS: Information on rechnology tion, or otlicr reasons. used by NASA that may be of particular interest in commercial and other non-aerospace CONTKACTOK REPORTS: Scientific and applications. Publications include Tech Briefs, rcc1u~ic.dinformition gencrared under a NASA Ttciinology Utilizdtion Reports and contr.iit or grmt ,ind consiiicrcd an importmt ‘Tc.chnc)log~Stirveys. conrrihition to csisting kr1clatfedjic.

Details on the availability of these publications may be obtained from: SC I ENT I F IC AND TEC t t N I CA L I N FORMAT ION 0 F F ICE NATIONAL AERONAUTICS AND SPACE AD MINISTRATION Washington, D.C. PO546